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DEPARTMENT DEFENSE INTERFACE STANDARD AIRCRAFT/STORE ELECTRICAL INTERCONNECTION SYSTEM
AMSC:
AREA: GDRQ
DISTRIBUTION STATEMENT Approved public release; distribution unlimited.
MIL-STD-1760C
FOREWORD
This standard approved Departments Agencies Department Defense. Prior this standard, aircraft stores which carried were typically developed independently each other were developed exclusively each other. This usually resulted unique aircraft/store electrical interconnection requirements, general proliferation overall store interface designs, levels interoperability, costly aircraft modifications achieve required store utilization flexibility. Trends store technology toward more complex store functions which require increasing amounts avionics data control information from aircraft systems were predicted lead insurmountable aircraft/store interfacing problems. goal develop aircraft that compatible with wide variety stores stores that compatible with wide variety aircraft. This standard supports this goal defining standard electrical (and fiber optic) interconnection system aircraft stores. This interconnection system based standard connector, standard signal standard serial digital data interface control, monitor, release stores. [Note1] Application this standard existing aircraft stores will significantly reduce stabilize number variety signals required aircraft/store interfaces, minimize impact stores future stores management systems, increase store interoperability among services, within NATO, with other allies. Revision does change fundamental MIL-STD-1760 interface. includes newly defined requirements high bandwidth interface, bandwidth interface, carriage stores umbilical cables. also attempts simplify document deleting requirements (such those dealing with electromagnetic interference) that were necessary interface document. Other refinements include grouping initialization connector requirements together re-numbering paragraphs ".1" eliminated from most numbers sections guidance from section been re-written into handbook, published separately. extensive changes between Revision Revision changes marked this document. draft version with changes marked annotated available from Responsible Engineer this document. Some requirements MIL-STD-1760 stated invoking other documents, including MIL-STD1553 MIL-C-38999. tiering requirements limited level particular contract, necessary include references these second tier documents contractual specification.[Note2] following areas limitations this standard: Requirements mechanical, aerodynamic, logistic, operational compatibility covered. Since factors such size, shape, loads, clearances, functional limitations specified, full operability stores aircraft cannot assured. Signals emergency jettison stores specified. However, this does preclude signals this standard they compatible with requirements emergency jettison. [Note3] [Note4] This standard does attempt establish EMI/EMC requirements aircraft store, although does define interface that generally capable meeting these requirements.[Note5] Beneficial comments (recommendations, additions, deletions) pertinent data which improving this document should addressed ASC/ENSI, 2530 Loop Road West, WrightPatterson AFB, Ohio 45433-7101, using Standardization Document Improvement Proposal Form 1426) appearing this document letter.
MIL-STD-1760C CONTENTS PARAGRAPH PAGE
FOREWORD. SCOPE. Scope. Purpose. Application. APPLICABLE DOCUMENTS General. Government documents. 2.2.1 Specifications, standards, handbooks. 2.2.2 Other government documents, drawings, publications. Non-Government publications. Order precedence. DEFINITIONS Definitions. 3.1.1 Aircraft. 3.1.2 Aircraft/store Electrical Interconnection System (AEIS). 3.1.3 Electrical interface types. 3.1.3.1 Aircraft Station Interface (ASI). 3.1.3.2 Carriage Store Interface (CSI). 3.1.3.3 Carriage Store Station Interface (CSSI). 3.1.3.4 Mission Store Interface (MSI). 3.1.3.5 Routing Network Aircraft Subsystem Port (RNASP). 3.1.4 Provisions. 3.1.5 Store. 3.1.5.1 Carriage stores. 3.1.5.2 Mission stores. 3.1.6 Stores management system. 3.1.7 Suspension release equipment (S&RE). 3.1.8 Random noise. 3.1.9 Periodic noise. 3.1.10 Impulse noise. 3.1.11 Stimulated noise. 3.1.12 Common mode noise. 3.1.13 Latency. 3.1.14 Delay. 3.1.15 Power interruption. Acronyms abbreviations. GENERAL REQUIREMENTS Aircraft/store configurations. Interface classes. 4.3. Primary interface signal set. 4.3.1. High bandwidth (HB) interfaces. 4.3.1.1 Type signal requirements. 4.3.1.2 Type signal requirements. 4.3.1.3 Signal assignment. 4.3.2 Digital multiplex data interface. 4.3.3 bandwidth (LB) interface. 4.3.3.1 signal requirements. 4.3.3.2 Signal assignment. 4.3.4 Release consent interface. 4.3.5 Primary interlock interface.
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4.3.6 Address interface. 4.3.7 Primary structure ground. 4.3.8 Primary power. 4.3.9 Fiber optic (FO) interfaces. Auxiliary power interface signal set. 4.4.1 Auxiliary power. 4.4.2 Auxiliary interlock interface. 4.4.3 Auxiliary structure ground. Interface connectors. DETAILED REQUIREMENTS Aircraft requirements. 5.1.1 Aircraft interfaces. 5.1.1.1 Minimum transfer capacity. 5.1.1.2 Type signal path requirements. 5.1.1.2.1 Return loss. 5.1.1.2.2 Transient response. 5.1.1.2.3 Insertion gain. 5.1.1.2.4 Representative pulse delay. 5.1.1.2.5 Equalization. 5.1.1.2.6 Dynamic range. 5.1.1.2.7 Signal path offset. 5.1.1.2.8 Noise requirements. 5.1.1.2.8.1 Random noise. 5.1.1.2.8.2 Periodic noise. 5.1.1.2.8.3 Impulse noise. 5.1.1.2.8.4 Stimulated noise. 5.1.1.2.8.5 Common mode noise. 5.1.1.3 Type signal path requirements. 5.1.1.4 Ground reference. 5.1.2 Aircraft digital data interface. 5.1.2.1 Functional characteristics. 5.1.2.2 Electrical characteristics. 5.1.2.2.1 Output characteristics. 5.1.2.2.2 Input characteristics. 5.1.2.2.3 Shield grounding. 5.1.3 Aircraft interface. 5.1.3.1 Minimum transfer capacity. 5.1.3.2 Input/output impedance. 5.1.3.3 Insertion gain. 5.1.3.4 Equalization requirements. 5.1.3.5 Signal path offset. 5.1.3.6 Noise. 5.1.3.6.1 Periodic random noise. 5.1.3.6.2 Impulse noise. 5.1.3.6.3 Stimulated noise. 5.1.3.6.4 Common mode noise. 5.1.3.7 Ground reference. 5.1.4 Aircraft release consent interface. 5.1.4.1 Voltage level. 5.1.4.2 Current level. 5.1.4.3 Stabilization time. 5.1.4.4 Enable lead time.
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5.1.4.5 Inhibit delay. 5.1.4.6 Ground reference. 5.1.5 Aircraft interlock interface. 5.1.6 Aircraft address interface. 5.1.6.1 Address assignment. 5.1.6.2 Address signal. 5.1.6.3 Logic thresholds. 5.1.6.4 Response characteristics. 5.1.6.5 Address isolation. 5.1.7 Aircraft structure ground. 5.1.8 Aircraft power interface. 5.1.8.1 Independent control. 5.1.8.2 Voltage level. 5.1.8.3 Current capacity. 5.1.8.3.1 Primary signal set. 5.1.8.3.2 Auxiliary power signal set. 5.1.8.3.3 Simultaneous current. 5.1.8.4 Overcurrent protection. 5.1.8.5 Off-state leakage current. 5.1.8.6 Stabilization time. 5.1.8.7 Ground reference. 5.1.8.8 Power application. 5.1.9 Aircraft 115/200 power interface. 5.1.9.1 Independent control dead facing. 5.1.9.2 Voltage level. 5.1.9.3 Current capacity. 5.1.9.3.1 Primary signal set. 5.1.9.3.2 Auxiliary power signal set. 5.1.9.3.3 Simultaneous current. 5.1.9.4 Overcurrent protection. 5.1.9.5 Off-state leakage current. 5.1.9.6 Stabilization time. 5.1.9.7 Phase rotation. 5.1.9.8 Load power factor. 5.1.9.9 Phase power unbalance. 5.1.9.10 Ground reference. 5.1.9.11 Power application. 5.1.10 Aircraft power interface. 5.1.11 Aircraft fiber optic interface. 5.1.12 Initialization. 5.1.12.1 Pre-initialization conditions. 5.1.12.2 Power application. 5.1.12.3 First communication. Mission store requirements (measured MSI). 5.2.1 Mission store interfaces. 5.2.1.2 Electrical characteristics (type 5.2.1.2.1 Return loss. 5.2.1.2.2 Dynamic range. 5.2.1.3 Electrical characteristics (type 5.2.1.4 Ground reference. 5.2.2 Mission store data interface. 5.2.2.1 Functional characteristics.
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5.2.2.2 Electrical characteristics. 5.2.2.2.1 Output characteristics. 5.2.2.2.2 Input characteristics. 5.2.2.2.3 Shield grounding. 5.2.3 Mission store interface. 5.2.3.1 Input/output impedance. 5.2.3.2 Ground reference. 5.2.4 Mission store release consent interface. 5.2.4.1 Voltage level. 5.2.4.2 Current level. 5.2.4.3 Stabilization time. 5.2.4.4 Enable lead time. 5.2.4.5 Inhibit lead time. 5.2.4.6 Ground reference. 5.2.5 Mission store interlock interface. 5.2.6 Mission store address interface. 5.2.6.1 Address assignment. 5.2.6.2 Address signal. 5.2.6.3 Logic threshold. 5.2.6.4 Response characteristics. 5.2.7 Mission store structure ground. 5.2.8 Mission store power interface. 5.2.8.1 Voltage level. 5.2.8.2 Load current. 5.2.8.2.1 Primary signal set. 5.2.8.2.2 Auxiliary power signal set. 5.2.8.2.3 Simultaneous load. 5.2.8.3 Load isolation. 5.2.8.4 Overcurrent compatibility. 5.2.8.5 Off-state leakage current. 5.2.8.6 Stabilization time. 5.2.8.7 Ground reference. 5.2.8.8 Power utilization. 5.2.9 Mission store 115/200 power interface. 5.2.9.1 Voltage level. 5.2.9.2 Load current. 5.2.9.2.1 Primary signal set. 5.2.9.2.2 Auxiliary power signal set. 5.2.9.2.3 Simultaneous load. 5.2.9.3 Load isolation. 5.2.9.4 Overcurrent compatibility. 5.2.9.5 Off-state leakage current. 5.2.9.6 Stabilization time. 5.2.9.7 Load power factor. 5.2.9.8 Phase unbalance. 5.2.9.9 Ground reference. 5.2.9.10 Power utilization. 5.2.10 Mission store power interface. 5.2.11 Mission store fiber optic interface. 5.2.12 Store initialization. 5.2.12.1 Pre-initialization conditions. 5.2.12.2 Power application.
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5.2.12.3 Address determination. 5.2.12.4 First response. 5.2.12.5 First required non-busy response. Carriage store requirements. 5.3.1 Carriage store interfaces. 5.3.1.1 Minimum transfer capacity. 5.3.1.2 Type signal path characteristics. 5.3.1.2.1 Return loss. 5.3.1.2.2 Transient response. 5.3.1.2.3 Insertion gain. 5.3.1.2.4 Representative pulse delay. 5.3.1.2.5 Equalization. 5.3.1.2.6 Dynamic range. 5.3.1.2.7 Signal path offset. 5.3.1.2.8 Noise. 5.3.1.2.8.1 Random noise. 5.3.1.2.8.2 Periodic noise. 5.3.1.2.8.3 Impulse noise. 5.3.1.2.8.4 Stimulated noise. 5.3.1.2.8.5 Common mode noise. 5.3.1.3 Signal path electrical characteristics (type 5.3.1.4 Ground reference (type 5.3.1.5 Ground reference (type 5.3.2 Carriage store data interface. 5.3.2.1 CSI. 5.3.2.2 CSSI. 5.3.3 Carriage store interface. 5.3.3.1 Minimum transfer capacity. 5.3.3.2 Input/output impedance. 5.3.3.3 Insertion gain. 5.3.3.4 Equalization. 5.3.3.5 Signal path offset. 5.3.3.6 Noise. 5.3.3.6.1 Periodic random noise. 5.3.3.6.2 Impulse noise. 5.3.3.6.3 Stimulated noise. 5.3.3.6.4 Common mode noise. 5.3.3.7 Ground reference. 5.3.4 Carriage store release consent interface. 5.3.4.1 CSI. 5.3.4.2 CSSI. 5.3.4.3 CSSI transfer. 5.3.5 Carriage store interlock interface. 5.3.5.1 CSI. 5.3.5.2 CSSI. 5.3.5.3 Isolation. 5.3.6 Carriage store address interface. 5.3.6.1 CSI. 5.3.6.2 CSSI. 5.3.7 Carriage store structure ground. 5.3.8 Carriage store power interface. 5.3.8.1 CSI.
MIL-STD-1760C CONTENTS PARAGRAPH PAGE
5.3.8.2 CSSI. 5.3.9 Carriage store 115/200 power interfaces. 5.3.9.1 CSI. 5.3.9.2 CSSI. 5.3.10 Carriage store power interfaces. 5.3.11 Carriage store fiber optic interface. 5.3.12 Carriage store initialization. Umbilical cable requirements. 5.4.1 Primary umbilical interfaces. 5.4.2 Primary umbilical data interface. 5.4.3 Primary umbilical interface. 5.4.4 Primary umbilical release consent interface. 5.4.5 Umbilical interlock interface. 5.4.6 Primary umbilical address interface. 5.4.7 Umbilical structure ground. 5.4.8 Umbilical power interface. 5.4.9 Umbilical power interface. 5.4.10 Umbilical power interface. 5.4.11 Primay umbilical fiber optic interface. 5.4.12 Umbilical gross shield. Power interface interrupts. 5.5.1 Mission store compatibility. 5.5.2 Carriage store compatibility. 5.5.3 Aircraft compatibility. 5.5.3.1 Full initialization. 5.5.3.2 Partial initialization. 5.5.4 Store power interrupt notification. Connector characteristics. 5.6.1 Primary interface connectors. 5.6.2 Auxiliary power interface connector. 5.6.3 Connector receptacle. 5.6.4 Plugged cavities. 5.6.5 Umbilical primary interface connectors. 5.6.5 Umbilical auxiliary interface connectors. 5.6.6 Connector keyway orientation. 5.6.6.1 CSSI. 5.6.6.2 CSI. 5.6.6.3 Umbilical cable. 5.6.7 Connector location. 5.6.7.1 CSSI. 5.6.7.2 CSI. NOTES. Intended use. 6.1.1 Implementation. Issue DoDISS. International standardization agreements. Tailoring guidance. Keyword listing. Changes from previous issue. SCOPE B.1.1 Purpose.
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MIL-STD-1760C CONTENTS PARAGRAPH PAGE
APPLICABLE DOCUMENTS B.2.1 References. B.2.2 Government documents. B.2.3 Other Government documents, drawings, publications. B.2.4 Non-Government publications. B.2.4.1 AMERICAN NATIONAL STANDARDS INSTITUTE B.2.4.2 INTERNATIONAL STANDARDS ORGANIZATION. B.2.4.3 SOCIETY AUTOMOTIVE ENGINEERS DEFINITIONS. B.3.1 Definitions. B.3.1.1 Data entity. B.3.1.2 Data set. B.3.1.3 Data validity B.3.1.4 Mass data transfer. B.3.1.4.1 Back-to-back transfer. B.3.1.4.2 Block. B.3.1.4.3 Download. B.3.1.4.4 File. B.3.1.4.5 Record. B.3.1.4.6 Upload. B.3.1.4.7 Buffer. B.3.2 Acronyms abbreviations. REQUIREMENTS B.4.1 Communication rules. B.4.1.1 Command word. B.4.1.1.1 Remote terminal address field. B.4.1.1.2 Subaddress/mode field. B.4.1.1.3 Mode commands. B.4.1.1.3.1 Mandatory mode commands. B.4.1.1.3.1.1 Transmit status word. B.4.1.1.3.1.2 Transmitter shutdown. B.4.1.1.3.1.3 Override transmitter shutdown. B.4.1.1.3.1.4 Reset remote terminal. B.4.1.1.3.1.5 Transmit vector word. B.4.1.1.3.1.6 Synchronize with data word. B.4.1.1.3.1.7 Transmit last command. B.4.1.1.3.2 Prohibited mode commands. B.4.1.1.3.3 Permitted mode commands. B.4.1.2 Status word. B.4.1.2.1 Service request bit. B.4.1.2.2 Busy bit. B.4.1.2.3 Subsystem flag bit. B.4.1.2.4 Terminal flag bit. B.4.1.3 Data words. B.4.1.4 Internal state change. B.4.1.5 Protocol execution. B.4.1.5.1 Protocol checks. B.4.1.5.2 Checksum requirement. B.4.1.5.2.1 Checksum algorithm. B.4.1.5.3 Execution time. B.4.1.5.3.1 Aircraft compatibility
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B.4.1.5.3.2 Busy time. B.4.1.5.3.3 Busy time measurement. B.4.1.5.4 Service request notification. B.4.1.5.4.1 Additional request service. B.4.1.5.5 Request servicing. B.4.1.5.6 Vector word demand. B.4.1.5.7 General form service request routine. B.4.1.5.8 Mass data transfer. B.4.1.5.9 Carriage store routing. B.4.1.5.10 Data consistency. B.4.1.5.11 Broadcast. B.4.1.5.11.1 Broadcast restricted subaddresses. B.4.1.5.11.2 Broadcast verification. B.4.1.5.11.3 Broadcast command received bit. B.4.1.5.11.4 Stores compatibility with non-broadcast. B.4.2 Message requirements. B.4.2.1 Base message data format. B.4.2.1.1 Data word B.4.2.1.2 Data words 2-32 2-30. B.4.2.2 Standard messages. B.4.2.2.1 Store control. B.4.2.2.2 Store monitor. B.4.2.2.3 Store description. B.4.2.2.4 Nuclear weapon control. B.4.2.2.5 Nuclear weapon monitor. B.4.2.3 Mass data transfer messages. B.4.2.3.1 File Structure. B.4.2.3.2 Message formats. B.4.2.3.2.1 Transfer Control (TC) message. B.4.2.3.2.1.1 message header word. B.4.2.3.2.1.2 message instruction word. B.4.2.3.2.1.3 message subaddress select word. B.4.2.3.2.1.4 message file number word. B.4.2.3.2.1.5 message record number word. B.4.2.3.2.1.6 message block number word. B.4.2.3.2.1.7 message file/record checksum word. B.4.2.3.2.1.8 message checksum word B.4.2.3.2.2 Transfer Monitor (TM) message. B.4.2.3.2.2.1 message header word. B.4.2.3.2.2.2 message last received instruction word. B.4.2.3.2.2.3 message transfer mode status word. B.4.2.3.2.2.4 message current selected subaddress word. B.4.2.3.2.2.5 message current file number word. B.4.2.3.2.2.6 message current record number word. B.4.2.3.2.2.7 message current block number word. B.4.2.3.2.2.8 message current file/record checksum word. B.4.2.3.2.2.9 message checksum word position. B.4.2.3.2.3 Transfer Data (TD) message. B.4.2.3.2.3.1 message record/block number word. B.4.2.3.2.3.2 message file data words. B.4.2.3.2.3.3 message file data words with message checksum option. B.4.2.3.3 file/record checksum.
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B.4.2.3.4 Modes operation. B.4.2.3.4.1 Download mode. B.4.2.3.4.1.1 Initiation download mode. B.4.2.3.4.1.2 Erasure files. B.4.2.3.4.1.3 Erasure specific file. B.4.2.3.4.1.4 Erasure specific record B.4.2.3.4.1.5 File transfer initiation. B.4.2.3.4.1.6 File transfer. B.4.2.3.4.1.7 File checksum test. B.4.2.3.4.1.8 Record checksum test. B.4.2.3.4.1.9 Transmission/checksum error recovery aircraft. B.4.2.3.4.1.10 Transmission error recovery store request. B.4.2.3.4.1.11 Download transmission completion. B.4.2.3.4.1.12 Exit from download mode. B.4.2.3.4.1.13 Downloading with back-to-back transfer. B.4.2.3.4.2 Upload mode. B.4.2.3.4.2.1 Initiation upload mode. B.4.2.3.4.2.2 File transfer initiation. B.4.2.3.4.2.3 File transfer. B.4.2.3.4.2.4 Transmission error recovery. B.4.2.3.4.2.5 File checksum test. B.4.2.3.4.2.6 Record checksum test. B.4.2.3.4.2.7 Checksum error recovery. B.4.2.3.4.2.8 Upload transmission completion. B.4.2.3.4.2.9 Exit from upload transmission. B.4.2.3.4.2.10 Uploading with back-to-back transfer. B.4.2.3.4.3 Status Update. B.4.2.3.4.3.1 Download mode message. B.4.2.3.4.3.2 Download mode message. B.4.2.3.4.3.3 Upload mode. B.4.2.3.4.4 Back-to-back transfer operation. B.4.2.3.4.5 System start. B.4.2.3.4.5.1 System start download mode. B.4.2.3.4.5.2 System start upload mode. B.4.3 Standard data entities.
MIL-STD-1760C CONTENTS PARAGRAPH PAGE
TABLE Carriage store signal transfer. TABLE Primary signal connector contacts/termini seal plugs. TABLE III. Primary signal contact functional assignment. TABLE Auxiliary power signal connector contacts seal plugs. TABLE Auxiliary power signal contact functional assignment. TABLE B-I. Subaddress/mode field application. TABLE B-II. Vector word (asynchronous message demand) format. TABLE B-III. Vector word (asynchronous action demand) format. TABLE B-IV. Synchronize data word (real time clock) format. TABLE B-V. Synchronize data word (minor cycle frame memory map) format. TABLE B-VI. Synchronize data word (minor cycle frame user defined) format. TABLE B-VII. Base message format (BC-RT transfer). TABLE B-VIII. Base message format (RT-BC transfer). TABLE B-IX. Base message format (RT-RT transfer). TABLE B-X. Header word. TABLE B-XI. Store control (BC-RT transfer). (Note TABLE B-XII. Store monitor (RT-BC transfer). (Note TABLE B-XIII. Store description message. (Note TABLE B-XIV. Country code. TABLE B-XV. Store identity (binary). TABLE B-XVI. Store identity (ASCII). TABLE B-XVII. Transfer Control (TC) message format. TABLE B-XVIII. Instruction word. TABLE B-XIX. Allowable instruction type field states. TABLE B-XX. Subaddress select. TABLE B-XXI. Dual binary number. TABLE B-XXII. Transfer Monitor (TM) message format. TABLE B-XXIII. Transfer mode status. TABLE B-XXIV. Transfer Data (TD) message format. (Note TABLE B-XXV. Allowable mode status field states. TABLE B-XXVI. Data entity list. TABLE B-XXVII. Linear data entities. TABLE B-XXVIII. complement format. TABLE B-XXIX. Unsigned format. TABLE B-XXX. Binary scientific notation format. TABLE B-XXXI. Invalidity word. TABLE B-XXXII. Critical control TABLE B-XXXIII. Critical control TABLE B-XXXIV. Critical authority. TABLE B-XXXV. Critical monitor TABLE B-XXXVI. Critical monitor TABLE B-XXXVII. Fuzing mode TABLE B-XXXVIII. Fuzing/arming mode status TABLE B-XXXIX. Protocol status. TABLE B-XL. ASCII packed. TABLE B-XLI. Discriminator description. TABLE B-XLII. Header word definition. TABLE B-XLIII. Fuzing mode TABLE B-XLIV. Fuzing/arming mode status TABLE B-XLV. Dispersion data word. TABLE B-XLVI. zone format.
MIL-STD-1760C CONTENTS PARAGRAPH PAGE
FIGURE Aircraft-store configuration examples. FIGURE Primary interface signal set. FIGURE Auxiliary power signal set. FIGURE Conceptual interface configurations. FIGURE Cosine-squared signal requirements. FIGURE Cosine-squared signal requirements. FIGURE signal requirements (1.0V). FIGURE signal requirements (1.3V). FIGURE Gain misequalization envelope. FIGURE Random noise weighting function. FIGURE Periodic noise weighting function. FIGURE Common mode noise weighting function. FIGURE Equivalent circuits interfaces. FIGURE output waveform envelope. FIGURE Gain misequalization envelope (aircraft, LB). FIGURE Equivalent circuits interfaces. FIGURE Primary interface current level. FIGURE Auxiliary interface current level. FIGURE Stabilization time. FIGURE Power factor limits. FIGURE Equivalent circuits carriage store Type signal paths. FIGURE Maximum gain misequalization envelope (LB, carriage store). FIGURE Equivalent circuits carriage store signal paths. FIGURE Carriage store voltage drop diagram. FIGURE Connector orientation. FIGURE B-1. Examples general form service request protocol. FIGURE B-2. Aircraft body axis system. FIGURE B-3. Earth axis systems. FIGURE B-4. Aircraft, target waypoint position fixed point. FIGURE B-5. Earth aircraft alignment. FIGURE B-6. Aircraft-store alignment. FIGURE B-7. Store body axis system. FIGURE B-8. Target waypoint position from current position. FIGURE B-9. Target position/store trajectory (polar). FIGURE B-10. Target sector segment position. APPENDIX Deleted APPENDIX Digital Data Communication Rules Message Requirements APPENDIX Annotations Explaining Differences From Revision CONCLUDING MATERIAL.
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MIL-STD-1760C
SCOPE Scope.
This standard defines implementation requirements Aircraft/Store Electrical (and fiber optic) Interconnection System (AEIS) aircraft stores. This interconnection system provides common interfacing capability operation employment stores aircraft, includes: electrical (and fiber optic) interfaces aircraft store stations, interface mission stores, interface carriage stores, characteristics umbilical cables. Interrelationships between aircraft store interfaces. Interrelationships between interfaces different store stations aircraft.
Purpose.
purpose this standard minimize proliferation electrical optical interfacing variations required aircraft operating stores minimize proliferation electrical optical interfacing variations required stores interface with aircraft. implementation this standard should [Note6]enhance interoperability stores aircraft defining specific electrical/optical, logical, physical requirements AEIS.
Application.
This standard applies aircraft stores that electrically interface with each other. This coverage encompasses stores aircraft presently concept development stages future aircraft store development. This standard also applies existing aircraft which required carry MIL-STD-1760 compatible stores.
MIL-STD-1760C
APPLICABLE DOCUMENTS General.
documents listed this section specified sections this standard. This section does include documents cited other sections this standard recommended additional information examples. While every effort been made ensure completeness this list, document users cautioned that they must meet specified requirements documents cited sections this standard, whether they listed.
Government documents.
2.2.1 Specifications, standards, handbooks. following specifications, standards, handbooks form part this document extent specified herein. Unless otherwise specified, issues these documents those listed issue Department Defense Index Specifications Standards (DoDISS) supplement thereto, cited solicitation (see 6.2). SPECIFICATIONS Department Defense MIL-C-17/94 MIL-C-17/113 MIL-A-8591 MIL-C-38999 Cable, Radio Frequency Flexible Coaxial Ohms M17/094 RG179 Cable Radio Frequency, Flexible, Coaxial, Ohms, M17/113-RG316 Airborne Stores, Suspension Equipment Aircraft-Store Interface (Carriage Phase); General Design Criteria Connectors, Electrical, Circular, Miniature, High Density, Quick Disconnect (Bayonet, Threaded Breech Coupling), Environment Resistant, Removable Crimp Hermetic Solder Contacts, General Specification Contacts, Electrical Connector, General Specification Contacts, Electrical Connector, Pin, Crimp Removable, Shielded, Size (For MIL-C-38999 Series III, Connectors) Contacts, Electrical Connector, Socket, Crimp Removable, (For MIL-C-38999 Series Connectors) Contacts, Electrical Connector, Pin, Crimp Removable, (For MIL-C-24308, MIL-C-38999 Series III, MIL-C-55302/69 MIL-C-83733 Connectors Contacts, Electrical Connector, Socket, Crimp Removable, Shielded, Size (For MIL-C-38999 Series III, Connectors) Contact, Electrical Connector, Concentric Twinax, Pin, Size Contact, Electrical Connector, Concentric Twinax, Socket, Size Contacts, Electrical Connector, Pin, Crimp Removable, Coaxial, Size (For MIL-C-38999 Series Connectors) Contacts, Electrical Connector, Socket, Crimp Removable, Coaxial, Size (For MIL-C-38999 Series Connectors) Connectors Accessories, Electrical, Circular, Umbilical, Environment Resistant, Removable Crimp Contacts, MIL-STD-1760 Applications (Metric), General Specification Connector Accessories, Electrical, General Specification
MIL-C-39029 MIL-C-39029/28 MIL-C-39029/56 MIL-C-39029/58
MIL-C-39029/75 MIL-C-39029/90 MIL-C-39029/91 MIL-C-39029/102 MIL-C-39029/103 MIL-C-83538
MIL-C-85049
MIL-STD-1760C MS27488 STANDARDS Department Defense MIL-STD-704 MIL-STD-1553B Not. MIL-STD-1560 Aircraft Electric Power Characteristics Digital Time Division Command/Response Multiplex Data NOTE: Revision Notice specifically required. Insert Arrangements MIL-C-38999 MIL-C-27599 Electrical, Circular Connectors Plug, Seal, Electrical Connector
(Unless otherwise indicated, copies above specifications, standards, handbooks available from Standardization Document Order Desk, Robbins Avenue, Building Philadelphia, 19111-5094.) 2.2.2 Other government documents, drawings, publications. following other Government documents, drawings, publications form part this document extent specified herein. Unless otherwise specified, issues those cited solicitation. NATO STANAG 3350 Analogue Video Standard Aircraft System Applications (Copies NATO standards available from Standardization Document Order Desk, Robbins Avenue, Building Philadelphia, 19111-5094, phone (215) 697-2179.)
Non-Government publications.
following documents form part this document extent specified herein. Unless otherwise specified, issues documents which adopted those listed issue DoDISS cited solicitation. Unless otherwise specified, issues documents listed DoDISS issues documents cited solicitation (see 6.2). SOCIETY AUTOMOTIVE ENGINEERS, INC. SAE-AS15531 Digital Time Division Command/Response Multiplex Data (Copies documents obtained from: Society Automotive Engineers, Inc., Commonwealth Dr., Warrendale, 15096-0001, phone (412) 776-4841.)
Order precedence.
event conflict between text this document references cited herein, text this document takes precedence. Nothing this document, however, supersedes applicable laws regulations unless specific exemption been obtained.
MIL-STD-1760C
DEFINITIONS Definitions.
Definitions applicable this standard follows. 3.1.1 Aircraft. vehicle designed supported air, being borne either dynamic action upon surfaces vehicle, buoyancy. term includes fixed movable wing airplanes, helicopters, gliders, airships, excludes air-launched missiles, target drones, flying bombs. 3.1.2 Aircraft/store Electrical Interconnection System (AEIS). AEIS system composed collection electrical (and fiber optic) interfaces aircraft stores through which aircraft energize, control, employ stores. AEIS consists electrical interfaces interrelationships between interfaces necessary transfer electrical power data between aircraft stores from store another store aircraft. 3.1.3 Electrical interface types. five electrical interface types aircraft/store electrical interconnection system shall specified below. 3.1.3.1 Aircraft Station Interface (ASI). electrical interface(s) aircraft structure where mission carriage store(s) electrically connected. connection usually aircraft side aircraft-to-store umbilical cable. aircraft station interface locations include, limited pylons, conformal fuselage hard points, internal weapon bays, wing tips (see 4.1).[Note7] 3.1.3.2 Carriage Store Interface (CSI). electrical interface carriage store structure where aircraft electrically connected. This connection usually store side aircraft-to-store umbilical cable (see 4.1) [Note8] 3.1.3.3 Carriage Store Station Interface (CSSI). electrical interface(s) carriage store structure where mission store(s) electrically connected. This connection usually carriage store side umbilical cable (see 4.1). 3.1.3.4 Mission Store Interface (MSI). electrical interface mission store external structure where aircraft carriage store electrically connected. This connection usually mission store side umbilical cable (see 4.1). 3.1.3.5 Routing Network Aircraft Subsystem Port (RNASP). electrical interface between high bandwidth network bandwidth network other subsystems within aircraft. This interface point defined order identify "aircraft" high bandwidth bandwidth networks allow network performance specified two-port network terms. 3.1.4 Provisions. Space feed-through connections wire runs that will allow future incorporation aircraft store without modification other than addition changes connectors, cables, hardware/software necessary control added functions. 3.1.5 Store. device intended internal external carriage mounted aircraft suspension release equipment, whether item intended separated flight from aircraft. Stores classified categories specified below. 3.1.5.1 Carriage stores. Suspension release equipment that mounted aircraft non-permanent basis store shall classified carriage store. Carriage store includes both single adapters multiple store carriers. Pylons primary racks (such MAU-12 BRU-10) shall considered carriage stores.
MIL-STD-1760C 3.1.5.2 Mission stores. stores excluding suspension release equipment (carriage stores) classified mission stores. general, these stores directly support specific mission aircraft. Mission stores include, limited missiles, rockets, bombs, torpedoes, buoys, flares, pods, fuel tanks. 3.1.6 Stores management system. avionics subsystem which controls monitors operational state aircraft installed stores provides manages communications between aircraft stores other aircraft subsystems. 3.1.7 Suspension release equipment (S&RE). airborne devices used carriage, suspension, employment, jettison stores, such limited racks, adapters, launchers, pylons. 3.1.8 Random noise. Randomly occurring noise which distributed over large bandwidth (sometimes known white pink noise). Random noise which keyed from time time (sometimes known burst noise) included. 3.1.9 Periodic noise. Noise made discrete frequency components. Periodic noise includes effects crosstalk from aircraft store signal sources. 3.1.10 Impulse noise. Spurious spikes which occur randomly fixed intervals. 3.1.11 Stimulated noise. Additional noise which induced presence input signal. 3.1.12 Common mode noise. interfaces, common mode noise potential difference between signal return (shield) connection local structure ground. interfaces, common mode noise potential differences between non-inverting connection local structure ground, (ii) inverting connection local structure ground. 3.1.13 Latency. Signal data latency time difference between signal data output system time which signal data valid. 3.1.14 Delay. Signal data delay elapsed time between input stimulus output response particular signal data path. 3.1.15 Power interruption. excursion aircraft power outside specified normal steady state limits established this standard.
MIL-STD-1760C
Acronyms abbreviations.
following acronyms abbreviations applicable. AEIS Aircraft/Store Electrical Interconnection System ANSI American National Standards Institute required ASCII American Standard Code Information Interchange Aircraft Station Interface Controller Bose-Chaudhuri Hocquenghem (codes) Built-In-Test Carriage Store Interface CSSI Carriage Store Station Interface decibel decibels above milliwatt DoDISS Department Defense Index Specifications Standards Electronic Industries Association Electromagnetic Compatibility Electromagnetic Interference gigahertz High Bandwidth hertz Interface Control Document International Standards Organization kilohertz kilovolt-ampere Bandwidth LLSP Lower Least Significant Part Least Significant Least Significant Part megahertz millisecond Mission Store Interface Most Significant Most Significant Part Multiplex (Digital Data Interface) NATO North Atlantic Treaty Organization peak-to-peak Pulse Repetition Frequency Root Mean Squared RNASP Routing Network Aircraft System Port Remote Terminal S&RE Suspension Release Equipment Stores Management System STANAG NATO Standardization Agreement Transfer Control Transfer Data Transfer Monitor volt
MIL-STD-1760C
GENERAL REQUIREMENTS Aircraft/store configurations.
This standard provides variety aircraft/store configurations, depicted figure specifying requirements measurable Aircraft Station Interface (ASI), Mission Store Interface (MSI), Carriage Store Interface (CSI), Carriage Store Station Interface (CSSI), Routing Network Aircraft System Port (RNASP). depicted figure requirements allow possible installation carriage store between MSI.
Interface classes.
functions AEIS shall allocated between separate signal sets; primary interface signal (figure auxiliary power signal (figure Separate connectors shall required each set. shall implement, shall compatible with, following interface classes. Class Class shall full primary interface. Class Class shall consist class plus auxiliary power interface. Class Class shall full primary interface without high bandwidth fiber optic power return. Class IIA. Class shall consist class plus auxiliary power interface. carriage stores, CSSI(s) shall implement either class class interface.[Note9]
4.3. Primary interface signal set.
primary interface signal set, shown figure shall comprised interfaces high bandwidth signals, redundant data signals, bandwidth signals, specified number dedicated discrete signals, aircraft power fiber optic signals. [Note10] Detailed electrical requirements each these functions ASI, MSI, CSI, CSSI shall comply with requirements section herein. [Note11]Equipment shall functionally damaged removal termination interface. 4.3.1. [Note12] High bandwidth (HB) interfaces. interfaces shall support transfer general signal types (type type sourced either internal aircraft subsystems mission stores. Type signals shall compatible with transmission passband MHz. Type signals shall compatible with transmission passband GHz. nominal source sink impedance interfaces shall ohms ohms HB4. Each interface shall include signal connection signal return (shield) connection. requirements 4.3.1 paragraphs apply RNASP signals originating aircraft signals originating mission store. [Note13] transmission scheme used between RNASP (e.g., signal RNASP purposely modulated amplitude-adjusted digitized form signal ASI). aircraft requirements herein, however, expressed terms deviations from ideal linear, unity-gain noninverting transmission system. Where different transmission scheme implemented between RNASP MSI, equivalent signal fidelity shall achieved each stated requirement. These requirements apply with interfaces terminated proper nominal impedance include effect applicable mating contacts. Figure shows number possible interface configurations.
MIL-STD-1760C
AIRCRAFT/PYLON DISCONNECT
AIRCRAFT WING
PYLON PARENT RACK
STORE STATION EQUIPMENT
UMBILICAL
MISSION STORE
FIXED RACK/ADAPTOR AIRCRAFT WING AIRCRAFT STATION STORE STATION EQUIPMENT UMBILICAL CARRIAGE STORE EQUIPMENT RACK CSSI
AIRCRAFT STATION
MISSION STORE
PYLON
PARENT RACK RACK CSSI
MISSION STORES
AIRCRAFT STATION INTERFACE CARRIAGE STORE INTERFACE CSSI CARRIAGE STORE STATION INTERFACE MISSION STORE INTERFACE
ONLY THESE INTERFACES CONTROLLED THIS STANDARD
FIGURE Aircraft-store configuration examples.
MIL-STD-1760C
AIRCRAFT
SIGNAL LINES HIGH BANDWIDTH HIGH BANDWIDTH HIGH BANDWIDTH HIGH BANDWIDTH BANDWIDTH FIBER OPTIC FIBER OPTIC DISCRETE LINES RELEASE CONSENT INTERLOCK INTERLOCK RETURN ADDRESS ADDRESS ADDRESS ADDRESS ADDRESS PARITY ADDRESS RETURN STRUCTURE GROUND POWER LINES POWER POWER RETURN POWER POWER RETURN 115V 115V 115V 115V NEUTRAL 270V POWER* 270V RETURN*
STORE
APPLICABLE CLASS INTERFACE
FIGURE Primary interface signal set.
MIL-STD-1760C
AIRCRAFT AUXILIARY POWER RETURN 115V 115V 115V 115V NEUTRAL 270V 270V RETURN STORE
DISCRETE LINES INTERLOCK INTERLOCK RETURN STRUCTURE GROUND
FIGURE Auxiliary power signal set.
4.3.1.1 Type signal requirements. Type signals shall limited within range ±1.55 under steady state conditions within range ±2.0 under transient conditions. signal peak voltage shall return within percent steady state voltage limits less than following transient change component signal. power spectral components above shall exceed limit line which decreases rate dB/octave. limit line shall equal largest power spectral component determined over nominal transmission passband 4.3.1. requirement shall apply until MHz. slew rate shall exceed volts/microsecond.
4.3.1.2 Type signal requirements. Type signal peak envelope power shall exceed dBmRMS. This requirement applies individual peak envelope power values more than signal simultaneously present. 4.3.1.3 Signal assignment. Signals interfaces shall limited following: Signals which comply with type signal characteristics shall only transferred HB1. Time correlation (synchronization, clocking blanking) signals which comply with type signal characteristics shall only transferred both. Monochrome raster composite video shall only transferred both. Raster composite video shall comply with STANAG 3350. [Note14]
MIL-STD-1760C
RNASP
ROUTING NETWORK
RNASP
ROUTING NETWORK
AIRCRAFT
AIRCRAFT
AIRCRAFT UMBILICAL
UMBILICAL STORE
UMBILICAL STORE
STORE
FIGURE Store aircraft aircraft store direct.
FIGURE Store store direct.
RNASP
AIRCRAFT
RNASP
AIRCRAFT
ROUTING NETWORK
ROUTING NETWORK
AIRCRAFT
UMBILICAL CARRIAGE STORE
ROUTING NETWORK
UMBILICAL CSSI CARRIAGE STORE CARRIAGE STORE
ROUTING NETWORK
UMBILICAL CSSI STORE
CSSI UMBILICAL STORE
CSSI UMBILICAL STORE
FIGURE Store aircraft aircraft store carriage store.
FIGURE Store store carriage store.
FIGURE Conceptual interface configurations. (continues following page)
MIL-STD-1760C
RNASP
AIRCRAFT
RNASP
AIRCRAFT AIRCRAFT
ROUTING NETWORK
ROUTING NETWORK
AIRCRAFT
UMBILICAL STORE CSSI
UMBILICAL
ROUTING NETWORK
UMBILICAL CSSI
UMBILICAL
CARRIAGE STORE
CARRIAGE ROUTING STORE NETWORK CSSI CSSI
ROUTING CARRIAGE NETWORK STORE
UMBILICAL STORE
CSSI UMBILICAL
UMBILICAL STORE
STORE
FIGURE Store store carriage store.
FIGURE Store store carriage stores
FIGURE Conceptual interface configurations. (Continued) 4.3.2 Digital multiplex data interface. [Note15] digital time division command/response multiplex data interface shall provide redundant channels (Mux transferring digital information, store control store status data between aircraft stores. signals crossing interface shall comply with requirements MIL-STD-1553 augmented requirements section herein. SAE-AS-15531 used lieu MIL-STD1553.[Note16] case carriage store, S&RE functions shall monitored controlled digital data interface. 4.3.3 bandwidth (LB) interface. [Note17] interface shall support transfer signals sourced either mission stores (measurable MSI) internal aircraft systems (measurable RNASP). interface shall include noninverting signal connection, inverting signal connection shield connection. nominal source impedance shall ohms nominal sink impedance shall ohms. following requirements apply signal source output (MSI RNASP) when output terminated with ohms.[Note18] transmission scheme used between RNASP (e.g., signal RNASP purposely modulated amplitude-adjusted digitized form signal ASI). aircraft requirements herein, however, expressed terms deviations from ideal linear, unity-gain non-inverting transmission system. Where different transmission scheme implemented between RNASP MSI, equivalent signal fidelity shall achieved each stated requirement. These requirements include effect applicable mating contacts. Figure shows number possible configurations. 4.3.3.1 signal requirements. maximum instantaneous signal voltage (between non-inverting connection inverting connection) shall peak peak signal voltage shall maximum. maximum instantaneous common mode voltage (the voltage between non-inverting connection reference ground added voltage between inverting connection reference ground) shall signals shall compatible with transmission passband kHz.
MIL-STD-1760C 4.3.3.2 Signal assignment. Signals interface shall limited tones voice grade audio. interface shall capable supporting transfer signal with signal characteristics between mission stores aircraft subsystems.[Note19][Note20] 4.3.4 Release consent interface. release consent interface shall power discrete used only enable, inhibit, safety critical store functions which commanded aircraft over data interface (see 4.3.2).
CAUTION release consent interface provided satisfy aircraft safety function. Consent shall enabled only when aircraft determines that safety criteria store employment sequence have been met.
4.3.5 Primary interlock interface. interlock interface shall available aircraft monitor electrically mated status primary interface connector between stores aircraft. CSSI interlock interface shall available carriage store monitor electrically mated status primary interface connector between stores carriage store.
CAUTION interlock interface shall used sole criterion functions which could result unsafe condition interlock circuit fails open.
4.3.6 Address interface. address interface shall used assign unique MIL-STD-1553 remote terminal address connected store. address interface shall contain discretes (five binary weighted address discretes through parity discrete) common address return. Stores monitor address discretes determine mated status connector. [Note21] 4.3.7 Primary structure ground. dedicated circuit shall provided between aircraft store structure grounds. shall provide electrical connection between aircraft store structures minimize shock hazards personnel. This circuit shall used signal power return path. 4.3.8 Primary power. aircraft shall supply control power stores through ASI. ASIs shall provide sources source three phase, four wire, wye-connected, 115/200 addition, provisions shall included source dedicated power return shall provided through AEIS each power source. Stores utilize combination 115/200 power available interface. activation power shall used discrete functions. 4.3.9 Fiber optic (FO) interfaces. Installation fiber optics required this standard this time. Provisions shall included Class interface connectors fiber optic interfaces, fiber optic path (FO1) fiber optic path (FO2). anticipated that these interfaces will used transferring bi-directional signals between aircraft
MIL-STD-1760C stores within wavelength windows: nominally nanometer (nm) 1300 nm.[Note22] [Note23] Auxiliary power interface signal set. [Note24]The auxiliary power signal set, shown figure shall include interfaces aircraft power, structure ground, interlock discrete. Detailed electrical requirements ASI, CSI, CSSI, shall accordance with section herein. 4.4.1 Auxiliary power. aircraft shall supply control auxiliary power stores through ASI. auxiliary power interface shall include power source source three phase, four wire, wyeconnected, 115/200 addition, provisions shall included source dedicated power return shall provided through AEIS each power source. Stores utilize combination 115/200 power available interface. activation power shall used discrete functions. 4.4.2 Auxiliary interlock interface. auxiliary interlock interface shall available aircraft monitor electrically mated status auxiliary power interface connector between stores aircraft. auxiliary CSSI interlock interface shall available carriage store monitor electrically mated status auxiliary power interface connector between stores carriage stores.
CAUTION interlock interface shall used sole criterion functions which could result unsafe condition interlock circuit fails open.
4.4.3 Auxiliary structure ground. dedicated circuit shall provided between aircraft store structure grounds. shall provide electrical connection between aircraft store structures minimize shock hazards personnel. This circuit shall used signal power return path.
Interface connectors.
[Note25]The standard primary interface connector contact functional assignments paragraph 5.6.1 shall used. standard auxiliary interface connector contact functional assignment requirements paragraph 5.6.2 shall used auxiliary power signal implemented.
MIL-STD-1760C
DETAILED REQUIREMENTS Aircraft requirements.
aircraft shall meet following requirements each ASI. Requirements shall measurable (looking into aircraft) except where indicated. 5.1.1 Aircraft interfaces. [Note26][Note27]The aircraft shall provide interfaces each minimum) bi-directional simplex transfer type type signals. aircraft shall assign, control, route signals their proper destinations means signal routing network. Each implemented routing network signal path shall meet following electrical requirements between RNASP between ASIs applicable. following requirements cover four interfaces, however, interface classes requirements associated with apply. 5.1.1.1 Minimum transfer capacity. aircraft shall support transfer type signal type signal HB1, simultaneously with transfer type signals HB2, HB3, through ASI.[Note28] 5.1.1.2 Type signal path requirements. 5.1.1.2.1 Return loss. input return loss each signal path shall less than over frequency band when output terminated with nominal impedance. output return loss each signal path shall less than over frequency band when input terminated with nominal impedance. 5.1.1.2.2 Transient response. transient response characteristics each signal path shall meet following requirements. When each signals figures applied input, output signal shall meet requirements figures response envelope figure V'1.0 defined figure response envelope figure V'1.3 defined figure 5.1.1.2.3 Insertion gain. signal path insertion gain between input output shall +0.5/-4.0 where insertion gain (V'1.3 V'1.3 defined figures respectively. 5.1.1.2.4 Representative pulse delay. representative pulse delay signal path shall exceed microseconds shall vary more than nanoseconds from nominal value. nominal value signal path representative pulse delay current routing path configuration shall retained made available computing signal latency. When signal figure applied input, representative pulse delay time difference between voltage being reached input signal rising edge voltage V'1.3 being reached output signal rising edge where V'1.3 defined figure 5.1.1.2.5 Equalization. gain misequalization signal path shall exceed limits shown figure zero gain reference shall gain kHz. maximum gain between shall exceed with respect zero-dB gain reference. 5.1.1.2.6 Dynamic range. When sine wave peak-to-peak voltage added voltage ±0.5 then applied signal path input, signal output shall compressed clipped more than percent. 5.1.1.2.7 Signal path offset. maximum voltage output each signal path shall exceed ±250 millivolts with input terminated.
MIL-STD-1760C 5.1.1.2.8 Noise requirements. Noise type signal path outputs shall meet following requirements over frequency band MHz. 5.1.1.2.8.1 Random noise. Using weighting function figure weighted random noise power each signal path output with input terminated shall exceed dBmRMS. 5.1.1.2.8.2 Periodic noise. calculated periodic noise voltage each signal path output with input terminated shall exceed mVRMS each valid state routing network. noise voltage shall determined stimulating each interface AEIS associated with signal path turn in-band, maximum amplitude sinusoidal signal which produces maximum weighted crosstalk voltage signal path output. weighting function given figure frequency stimulus signal different each interface. calculated periodic noise voltage shall root squares individual crosstalk voltages plus unstimulated weighted periodic noise voltage signal path output when interfaces terminated. 5.1.1.2.8.3 Impulse noise. peak-to-peak impulse noise voltage signal path output with input terminated shall exceed 5.1.1.2.8.4 Stimulated noise. more than (HB1 HB2) (HB3 HB4) noise shall added signal path noise output when sinusoidal excitation signal frequency between applied signal path input. 5.1.1.2.8.5 Common mode noise. Using weighting function figure common mode noise voltage output each signal path shall exceed with respect output structure ground when input terminated input signal return connected input structure ground. 5.1.1.3 Type signal path requirements. (None specified this time) 5.1.1.4 Ground reference. When interface sending type type signal, signal return shall connected aircraft structure ground shown figure 13a. When interface receiving type signal, signal return shall isolated from aircraft structure ground shown figure 13b. When interface receiving type signal, signal return shall connected aircraft structure ground shown figure 13c.
MIL-STD-1760C
v(t)
v(t) cos2
v(t) volts elsewhere where nanoseconds, volt
FIGURE Cosine-squared signal.
73%V'1.0 minimum Waveform shall fall above this line times between -100 Waveform shall fall below this line times between -100 Peak value shall greater than V'1.0 occur time between Waveform shall fall below this line times between
18%V'1.0 10%V'1.0 5%V'1.0 -5%V'1.0 -10%V'1.0
-18%V'1.0 -100 NOTE waveform shall completely contained within envelope, time reference arbitrary. NOTE sampled systems, response envelope shall apply alignment input signal with respect sample clock.
FIGURE Allowed response envelope cosine-squared signal. FIGURE Cosine-squared signal requirements.
MIL-STD-1760C
v(t)
v(t) cos2
v(t) volts elsewhere where nanoseconds, volt
FIGURE Cosine-squared signal.
112%V'1.3
88%V'1.3 Waveform shall fall above this line times between -200 Waveform shall fall below this line times between -200 Peak value shall between 112% V'1.3 occur time between Waveform shall fall below this line times between
12%V'1.3 6%V'1.3 3%V'1.3 -3%V'1.3 -6%V'1.3
-12%V'1.3 -200 -100 referenc
NOTE: waveform shall completely contained within envelope, time arbitrary.
FIGURE Allowed response envelope cosine-squared signal. FIGURE Cosine-squared signal requirements.
MIL-STD-1760C
where: denotes convolution v(t) g(t) 25µs g(t) volts elsewhere
-12.5 25µs elsewhere 12.5
where volt
FIGURE signal 1.0V).
Response (Typical)
v(t)
V'1.0 (see note
V'1.0
V'1.0
NOTE V'1.0 value measured midpoint between V'1.0 points.
FIGURE Allowed response envelope signal (referenced ±1.0V). FIGURE signal requirements (1.0V).
MIL-STD-1760C
v(t)
(where: denotes convolution) v(t) g(t) 25µs g(t) volts elsewhere
-12.5 25µs elsewhere 12.5 where nanoseconds, volts
FIGURE signal 1.3V).
Response (Typical)
v(t)
1.015 V'1.3 0.985V'1.3 V'1.3
V'1.3 (see note
NOTE exact shape Response waveform important. only requirement that within shaded box. NOTE V'1.3 value measured midpoint between V'1.3 points.
FIGURE Allowed response envelope signal (referenced ±1.3V). FIGURE signal requirements (1.3V).
MIL-STD-1760C
GAIN (dB)
0.25 -0.25
100k 1.25M
FREQUENCY (Hz)
FIGURE Gain misequalization envelope.
WEIGHTING FUNCTION (dB)
random noise weighting function defined
1+(4.70*10 +(8.55*10-8
FREQUENCY (MHz)
FIGURE Random noise weighting function.
MIL-STD-1760C Weighting function (dB)
100k Frequency (Hz)
periodic noise weighting function defined 1150
FIGURE Periodic noise weighting function.
WEIGHTING FUNCTION (dB)
100k FREQUENCY (Hz)
FIGURE Common mode noise weighting function.
MIL-STD-1760C
Equivalent source impedance
Signal connection
Equivalent voltage source
Signal return (shield) connection
FIGURE 13a. Equivalent circuit interface when sending Type Type signal.
Signal connection
Equivalent sink impedance
Signal return (Shield) connection
FIGURE 13b. Equivalent circuit interface when receiving Type signal.
Signal connection
Equivalent sink impedance
Signal return (Shield) connection
FIGURE 13c. Equivalent circuit interface when receiving Type signal. FIGURE Equivalent circuits interfaces.
MIL-STD-1760C
5.1.2 Aircraft digital data interface. aircraft shall provide data interfaces (Mux each primary signal transfer digital messages through MIL-STD-1553 compliant remote terminal connected store. Each data interface shall contain data high connection, data connection shield connection. 5.1.2.1 Functional characteristics. [Note29]The aircraft shall responsible controller function defined MIL-STD1553. interfaces each shall operated dual standby redundant mode described MIL-STD-1553. aircraft shall also control digital information transfer from remote terminal below remote terminal below other ASIs. aircraft shall communicate with remote terminal (connected ASI) with: messages whose terminal address corresponds address encoded address interface (see 5.1.6) ASI, MIL-STD-1553 broadcast messages. Subaddress fields (10011 11011 binary) shall only used communications with nuclear stores. This restriction applies messages detectable ASI. Subaddress (0111 binary) shall only used data routing through carriage stores "peeling". This restriction applies messages detectable ASI. [Note30] aircraft shall communicate with stores through interfaces accordance with requirements appendix 5.1.2.2 Electrical characteristics. aircraft shall comply with electrical characteristics defined herein ASI. characteristics defined apply when measured data high connection referenced data connection. Data high that connection which positive referenced data connection first part MILSTD-1553 command status word sync waveform. 5.1.2.2.1 Output characteristics. aircraft shall deliver, each ASI, MIL-STD-1553 compatible digital data waveforms except that peak-to-peak, line-to-line voltage shall within envelope figure maximum zero crossing deviation from ideal (with respect previous zero crossing) shall exceed nanoseconds. 5.1.2.2.2 Input characteristics. aircraft shall receive, operate with, input signal waveforms which comply with output characteristics MIL-STD-1553 transformer coupled stub terminal. 5.1.2.2.3 Shield grounding. aircraft shall connect data stub shields both aircraft structure ground.
MIL-STD-1760C
VALID WAVEFORM ENVELOPE
SQUARE WAVE SINE WAVE
1MICROSECOND (REF)
FIGURE output waveform envelope.
5.1.3 Aircraft interface. aircraft shall provide interface each bi-directional simplex transfer signals. aircraft shall assign, control, route signals their proper destinations. following requirements apply aircraft network including cables. When connected source sink equipment with impedances defined 4.3.3, signal paths shall have following characteristics. 5.1.3.1 Minimum transfer capacity. aircraft shall support transfer signal between applicable aircraft equipment applications where signal source located either aircraft connected store. aircraft shall capable rerouting signals between aircraft equipment each ASI. Specific transfer capacity beyond this minimum controlled this standard. 5.1.3.2 Input/output impedance. input impedance (line-to-line) each signal path shall ohms ohms, over frequency band kHz, when output terminated with nominal sink impedance defined 4.3.3. output impedance (line-to-line) each signal path shall less than ohms, over frequency band kHz, when input terminated with nominal source impedance defined 4.3.3. 5.1.3.3 Insertion gain. signal path insertion gain between input output shall sine wave input. 5.1.3.4 Equalization requirements. gain misequalization signal path shall exceed limits shown figure reference shall gain kHz.
MIL-STD-1760C
Gain (dB)
3.4k Frequency (Hz)
FIGURE Gain misequalization envelope (aircraft, LB).
5.1.3.5 Signal path offset. maximum voltage output each signal path shall exceed line-to-line lineto-ground with input terminated. 5.1.3.6 Noise. signal path noise shall meet following requirements over frequency band except where otherwise specified. 5.1.3.6.1 Periodic random noise. calculated periodic random noise voltage each signal path output with input terminated shall exceed 12.5 mVRMS each valid state routing network. noise voltage shall determined stimulating each interface AEIS associated with signal path turn in-band (150 kHz), maximum amplitude sinusoidal signal which produces maximum crosstalk voltage signal path output. frequency stimulus signal different each interface. calculated noise voltage shall root squares individual crosstalk voltages plus unstimulated periodic random noise voltage signal path output when interfaces terminated. 5.1.3.6.2 Impulse noise. With input signal path terminated, there shall standard deviation) more than occurrences impulse noise exceeding peak over three minute period. impulse noise voltage shall apply when band-limited pass. 5.1.3.6.3 Stimulated noise. frequency between kHz, application sinusoidal excitation signal signal path input shall more than noise output over frequency range kHz. 5.1.3.6.4 Common mode noise. peak common mode noise voltage output each signal path shall exceed when input terminated input shield same potential local structure ground. This requirement shall apply over band kHz. 5.1.3.7 Ground reference. When interface sending signal, inverting non-inverting signals shall referenced ground shown figure 16a. When interface receiving signal,
MIL-STD-1760C signal shall represented difference between non-inverting signal inverting signal shown figure 16b. shield shall connected ground.
Notes: V1-V2 Thevenin equivalent voltage source (balanced with respect ground). R1+R2 Thevenin equivalent source impedance.
non-inverting signal connection
inverting signal connection shield
FIGURE 16a. Equivalent circuit when sending signal.
non-inverting signal connection inverting signal connection shield
FIGURE 16b. Equivalent circuit when receiving signal. FIGURE Equivalent circuits interfaces.
5.1.4 Aircraft release consent interface. aircraft shall provide release consent interface each primary signal transferring enable/inhibit signal connected store. Release consent, when enabled state, shall indicate aircraft consent stores perform safety-critical functions (such store release from carriage store, missile launch from rail launcher rocket firing from pod) when commanded over data interface (see 4.3.4). [Note31] aircraft shall require positive crew action generate enabled state release consent signal. When inhibited state, release consent interface shall electrically isolated from release consent interface other ASIs. isolation shall kilohms minimum 5.1.4.1 Voltage level. voltage level measured between release consent connection power return connection shall Steady State Conditions Enable: Minimum voltage 19.0 Maximum voltage, accordance with MIL-STD-704 Inhibit: 1.50 (maximum)
Voltage transients shall comply with MIL-STD-704 limits applications.[Note32]
MIL-STD-1760C 5.1.4.2 Current level. Mission carriage stores require milliamperes steady state through during enable state aircraft shall able supply that current. aircraft not, however, required supply current excess milliamperes. [Note33] aircraft shall comply with requirements herein store imposed load currents milliamperes minimum through ASI. 5.1.4.3 Stabilization time. With resistive load between ohms kilohms connected between release consent power return, voltage shall reach steady state levels (see 5.1.4.1.a) within milliseconds during transition between enable inhibit states. 5.1.4.4 Enable lead time. release consent required store, release consent signal shall attain enable state least milliseconds prior transferring safety critical command over data interface prior firing signal parent S&RE, applicable. 5.1.4.5 Inhibit delay. release consent been enabled, aircraft shall operate under assumption that store(s) connected that remain enable state milliseconds after release consent signal been returned inhibit state. 5.1.4.6 Ground reference. power return connection shall ground reference release consent. 5.1.5 Aircraft interlock interface. aircraft shall provide interlock interface each primary signal auxiliary power signal monitoring mated status associated connectors. interlock interface each primary auxiliary consists interlock connection interlock return connection. aircraft monitors interlock interface, then aircraft shall comply with following requirements. These requirements apply interlock connection referenced interlock return connection. Open circuit voltage Minimum voltage Maximum voltage, accordance with MIL-STD-704 Voltage transients shall exceed upper limit defined MIL-STD-704 Excitation current Minimum current milliamperes Maximum current milliamperes Impedance detection threshold. interface disconnected condition shall detected impedance level kilohms greater. interface connected condition shall detected impedance level ohms less. These impedance values apply over frequency range kHz. 5.1.6 Aircraft address interface. aircraft shall provide address interface each primary signal assigning data address MIL-STD-1553 remote terminal store mated ASI. Each address interface shall include five binary encoded address connections (A0, A4), address parity connection common address return connection. aircraft shall this interface only assigning address remote terminal associated with directly connected carriage store mission store. 5.1.6.1 Address assignment. aircraft shall supply logic state logic state each five binary weighted address connections each ASI. remote terminal address assigned shall defined follows:
MIL-STD-1760C Remote terminal address (A4) (A3) (A2) (A1) (A0) aircraft shall supply logic state logic state address parity connection such that number logic states exist five address connections plus address parity connection. aircraft shall modify address assigned whenever power (see 5.1.8, 5.1.9, 5.1.10) applied that ASI. 5.1.6.2 Address signal. aircraft shall comply with requirements herein when signals with following characteristics applied address interface connected store. characteristics defined apply address parity connections referenced address return connection. Open circuit (logic voltage Minimum voltage Maximum voltage 31.5 Rise fall times applied voltage less than milliseconds Logic current Minimum current milliamperes Maximum current milliamperes through each address parity connection Maximum current milliamperes through address return connection Rise fall times applied current less than milliseconds 5.1.6.3 Logic thresholds. aircraft shall provide following logic states under voltage current conditions 5.1.6.2: Logic state characteristics. aircraft shall maintain sufficient open circuit conditions between each logic address parity) connection return connection such that when voltages 5.1.6.2 applied across connections, current flow shall exceed microamperes. Logic state characteristics. aircraft shall limit voltage drop between each logic address parity) connection return connection volts maximum when current levels specified 5.1.6.2 applied. This maximum voltage drop applies when logic states exist address parity connections. 5.1.6.4 Response characteristics. aircraft shall produce valid address characteristics within milliseconds excitation signal application from store. aircraft shall require continuous application excitation signal. 5.1.6.5 Address isolation. aircraft shall electrically isolate address connections (including address return) each from address connections other ASIs, from power returns from aircraft structure. isolation shall kilohms minimum over frequency range kHz. 5.1.7 Aircraft structure ground. aircraft shall provide connection each primary signal each auxiliary signal which terminated aircraft structure capable carrying overcurrent levels defined figures primary auxiliary ASIs respectively. structure ground interface shall used signal return power return path. [Note34]
MIL-STD-1760C 5.1.8 Aircraft power interface. aircraft shall provide power interfaces each ASI. primary signal shall contain power (and power return) connections power (and power return) connections. auxiliary power signal shall contain power (and power return) connections. 5.1.8.1 Independent control. aircraft shall capable sourcing independently controlling each power interface through each primary signal through each auxiliary power signal ASI. [Note35] 5.1.8.2 Voltage level. voltages between each power connection associated power return connection shall comply with normal abnormal operation characteristics utilization equipment defined MIL-STD-704 with following addition: normal steady state lower voltage limit shall 22.0 current full rated load primary, auxiliary).[Note36] Voltage transients shall comply with MIL-STD-704. These voltage requirements shall apply valid load conditions. 5.1.8.3 Current capacity. 5.1.8.3.1 Primary signal set. aircraft shall capable sourcing maximum load current levels figure through power interface maximum load current levels figure through power interface ASI. aircraft shall capable sourcing total amperes, continuously through combination power power interfaces ASI. 5.1.8.3.2 Auxiliary power signal set. interface classes IIA, aircraft shall capable sourcing maximum load current levels figure through power interface auxiliary ASI. 5.1.8.3.3 Simultaneous current. total current available simultaneously from ASIs controlled this standard. total continuous current provided simultaneously through both primary auxiliary interfaces class need exceed amperes. 5.1.8.4 Overcurrent protection. aircraft shall ensure that current flow through power connection does exceed maximum overcurrent limits figures primary auxiliary ASIs, respectively. aircraft achieve this current limit operation deactivation appropriate power interface other power interface associated ASI. 5.1.8.5 Off-state leakage current. off-state leakage current between each power respective return shall exceed milliampere with valid load impedance. off-state leakage current between auxiliary power auxiliary power return shall exceed 2.50 milliamperes with valid load impedance.
MIL-STD-1760C
MAXIMUM OVERCURRENT
CURRENT
Circuit protection "always trip" zone MAXIMUM LOAD CURRENT Circuit protection "never trip" zone 1000 Circuit protection "may trip" zone
CURRENT DURATION (SEC)
FIGURE Primary interface current level.
1000 MAXIMUM OVERCURRENT
CURRENT
MAXIMUM LOAD CURRENT
Circuit protection "may trip" zone
Circuit protection "always trip" zone
Circuit protection "never trip" zone 1000
CURRENT DURATION (sec)
FIGURE Auxiliary interface current level.[Note37] NOTE: curves figures define locus discrete current-time points (such amperes seconds duration) intended represent continuous profile current versus time. [Note38]
MIL-STD-1760C
5.1.8.6 Stabilization time. When tested with valid resistive load connected ASI, voltage shall reach steady state levels (see 5.1.8.2) within milliseconds power turn-on turn-off (see figure 19).
VOLTAGE SPECIFIED INTERFACE VOLTAGE LEVEL VMIN
POWER POWEROFF POWER
VMIN TIME STABILIZATION TIME
FIGURE Stabilization time.
5.1.8.7 Ground reference. power return connections primary auxiliary ASIs shall reference each associated power connection. 5.1.8.8 Power application. aircraft shall only energize power auxiliary when aircraft determined that safe aircraft operation shall consider that some stores utilize power auxiliary powering safety critical functions such that store safety degraded with activation these power interfaces. aircraft energize power time under assumption that store functions powered either safety critical that multiple safety interlocks exist within store such that store safety significantly degraded activation power [Note39] 5.1.9 Aircraft 115/200 power interface. aircraft shall provide three phase, four wire, wye-connected, 115/200 power interfaces each ASI. primary signal shall contain phase phase phase neutral connections. auxiliary power signal shall contain phase phase phase neutral connections. 5.1.9.1 Independent control dead facing. aircraft shall capable sourcing independently controlling 115/200 power interface through each primary interface signal through each auxiliary power signal ASI. aircraft shall ensure that power applied until indication available that store mated, such interlock circuit complete. aircraft shall also ensure that power removed from prior store separation connector disconnect.
MIL-STD-1760C 5.1.9.2 Voltage level. voltage between each phase connection associated neutral connection shall comply with normal abnormal operation characteristics utilization equipment defined MIL-STD-704 with following addition: normal steady state lower voltage limit shall 108.0 current full rated load primary, auxiliary). Voltage transients shall comply with MIL-STD-704. These voltage requirements apply valid load conditions. 5.1.9.3 Current capacity. 5.1.9.3.1 Primary signal set. aircraft shall capable sourcing maximum load current levels figure simultaneously through each three phases primary signal ASI. 5.1.9.3.2 Auxiliary power signal set. interface classes IIA, aircraft shall capable sourcing maximum load current levels figure simultaneously through each three power phases auxiliary ASI. 5.1.9.3.3 Simultaneous current. total current available simultaneously from ASIs controlled this standard. total continuous current provided simultaneously through both primary auxiliary interfaces class need exceed amperes phase. 5.1.9.4 Overcurrent protection. aircraft shall ensure that current flow through power phase connection does exceed maximum overcurrent limits figures primary auxiliary ASIs, respectively. aircraft achieve this current limit operation deactivation appropriate power interface other power interface associated ASI. 5.1.9.5 Off-state leakage current. off-state leakage current between phase associated neutral shall less than milliamperes primary signal shall less than milliamperes auxiliary power signal with valid load impedance. 5.1.9.6 Stabilization time. When tested with valid resistive load connected ASI, voltage shall reach steady state levels within milliseconds power turn-on turn-off (see figure 19). 5.1.9.7 Phase rotation. three power phases shall comply with phase sequence voltage phase difference requirements MIL-STD-704. power phase assigned contact location auxiliary connector shall identical phase assigned contact location primary connector same location. 5.1.9.8 Load power factor. electrical characteristics shall comply with requirements herein when loads with power factor within limits figure applied ASI.[Note40]
MIL-STD-1760C 10.0 TOTAL RATED LOAD, LAGGING POWER FACTOR LEADING POWER FACTOR
ALLOWED LOAD POWER FACTOR
FIGURE Power factor limits.
5.1.9.9 Phase power unbalance. electrical characteristics shall comply with requirements herein when loads with phase power unbalance within limits MIL-STD-704 applied ASI. 5.1.9.10 Ground reference. Each neutral connection primary signal auxiliary power signal shall reference respective power phase. 5.1.9.11 Power application. aircraft energize 115/200 power interface (primary auxiliary) time under assumption that store functions powered either safety critical that multiple safety interlocks exist within store such that store safety significantly degraded activation 115/200 power. [Note41] 5.1.10 Aircraft power interface. power interface growth provision future applications power interfaces shall activated until characteristics performance details added this standard. class interface connectors ASIs shall include contacts plugged cavities) power power return. general electrical characteristics will defined MIL-STD-704 continuous current levels amperes primary amperes auxiliary ASI. Independent control deadfacing will also required, power. 5.1.11 Aircraft fiber optic interface. [Note42]The fiber optic interfaces growth provisions future applications. fiber optic interfaces shall activated until characteristics performance details added this standard. class interface connectors ASIs shall include size cavities fiber optic channel channel fiber optic termini installed, connector shall employ plugs that compatible with umbilical which populated with fiber optic termini.
MIL-STD-1760C 5.1.12 Initialization. aircraft shall comply with following default procedure sequence presented) initializing stores connected ASIs. aircraft initialize stores using other procedures, provided aircraft: knows (prior power application) identity connected store, prior established alternate procedure safely initializing that store. 5.1.12.1 Pre-initialization conditions. aircraft shall provide following pre-initialization conditions ASI: power interfaces shall deactivated. Release consent interface shall inhibit state. Address interface shall valid address.
NOTE: Data interface, interlock interface, high bandwidth interfaces, bandwidth interface fiber optic interface active. 5.1.12.2 Power application. aircraft shall apply primary power primary 115/200 power within milliseconds each other without required predetermined sequence. other power interfaces shall remain deactivated. 5.1.12.3 First communication. aircraft shall send store (over data interface) transmit command(s) store description message defined appendix aircraft shall require valid store response (see appendix these transmit commands sent within milliseconds after both power application. aircraft shall require "not busy" response (see appendix these transmit commands sent within milliseconds after both power application. [Note43][Note44]
Mission store requirements (measured MSI).
Mission stores shall provide Mission Store Interfaces (MSIs) with following characteristics. [Note45] 5.2.1 Mission store interfaces. mission store required interface. interface used, mission store shall comply with requirements below. interface used, resistance between signal signal return connection shall greater than ohms greater than ohms HB4. Hierarchical order selection type signal utilization shall over over HB4. 5.2.1.2 Electrical characteristics (type 5.2.1.2.1 Return loss. return loss mission store shall less than over frequency band when operating either sourcing sinking mode. 5.2.1.2.2 Dynamic range. When acting sink, mission store shall compatible with input voltage within range ±3.0 5.2.1.3 Electrical characteristics (type (None specified this time.) 5.2.1.4 Ground reference. When interface sending type type signal, signal return shall connected mission store structure ground shown figure 13a. When interface receiving type signal, signal return shall isolated from ground shown figure 13b. When interface
MIL-STD-1760C receiving type signal, signal return shall connected mission store structure ground shown figure 13c. 5.2.2 Mission store data interface. mission store shall provide connections data interface (Mux primary signal MSI. Each connections shall include data high, data low, shield connection. mission store required interface. However, interface used, mission store shall comply with requirements below. interface used, impedance between data high data connections shall greater than 1000 ohms from MHz. 5.2.2.1 Functional characteristics. mission store shall provide remote terminal function defined MIL-STD-1553. This remote terminal shall accessible through data interface (Mux dual standby redundant, [NOTE46] MIL-STD-1553 communication link with aircraft carriage store. mission store shall respond accordance with MIL-STD-1553 those messages whose MIL-STD-1553 command word terminal address corresponds address encoded address interface (see 5.2.6) monitored MSI; broadcast address implemented mission store. Subaddress fields (10011 11011 binary) shall only used communications with nuclear stores. This restriction applies messages detectable MSI. mission store shall respond commands received interfaces accordance with requirements appendix 5.2.2.2 Electrical characteristics. mission store shall comply with electrical characteristics defined herein MSI. characteristics defined apply when measured data high connection referenced data connection. Data high that connection that positive referenced data connection first part MIL-STD-1553 command status sync waveform. 5.2.2.2.1 Output characteristics. mission store shall provide output characteristics defined here which comply with output characteristics MIL-STD-1553 transformer coupled stub terminal except terminal output voltage shall 20.0 27.0 Vpp, line-to-line. 5.2.2.2.2 Input characteristics. mission store shall capable receiving operating with input signals which comply with input waveform compatibility, common mode rejection noise rejection requirements MILSTD-1553 transformer coupled stub terminals. magnitude line-to-line input impedance MSI, when mission store terminal transmitting power removed, shall minimum ohms within frequency range MHz. remote terminal contained within mission store shall comply with 1000 minimum terminal input impedance required MIL-STD1553. 5.2.2.2.3 Shield grounding. mission store shall connect data stub shields both mission store structure ground. 5.2.3 Mission store interface. interface shall include non-inverting, inverting, shield connection. mission store required interface. However, interface used, mission store shall comply with requirements below. interface used, impedance between non-inverting inverting connections shall greater than ohms. mission store provide signal source signal sink applicable.
MIL-STD-1760C 5.2.3.1 Input/output impedance. When interface acting source, shall have total source impedance exceeding ohms. When interface acting sink, input impedance shall ohms. These requirements apply over frequency band kHz. 5.2.3.2 Ground reference. When interface acting source, inverting non-inverting signals shall referenced ground shown figure 16a. When interface acting sink, signal shall represented difference between non-inverting signal inverting signal shown figure 16b. shield shall connected mission store ground. 5.2.4 Mission store release consent interface. mission store shall provide connections release consent interface primary signal MSI. [NOTE47] mission store shall release consent interface Commit Separate Store Submunition function (bit Fire, Launch Release function (bit D10) Critical Control data word Mission Store Control message (see appendix implemented. store shall these safety critical commands received over data interface only release consent signal enabled state. [Note48] mission store required release consent interface other instances. However, release consent interface used, mission store shall comply with requirements below. release consent used, impedance between release consent connection power return connection shall greater than kilohms dc).
CAUTION release consent interface provided satisfy aircraft safety function. Consent enabled whenever aircraft determines that safety criteria store employment sequence have been met.
5.2.4.1 Voltage level. mission store shall establish appropriate enable inhibit state when following voltage levels applied release consent connection (referenced power return connection) MSI: Steady-state conditions: Enable: Inhibit: Minimum voltage 15.0 Maximum voltage defined MIL-STD-704 1.50 (maximum applied)
Voltage transients limits MIL-STD-704 applications. 5.2.4.2 Current level. mission store shall limit load current range milliamperes when steady state enable voltages (see 5.2.4.1a) applied MSI. 5.2.4.3 Stabilization time. mission store shall compatible with aircraft carriage stores which deliver signal with transition time (between enable inhibit states) milliseconds. 5.2.4.4 Enable lead time. mission store shall capable accepting safety critical commands over data interface within milliseconds after valid enable signal applied MSI.
MIL-STD-1760C 5.2.4.5 Inhibit lead time. mission store shall functionally reject safety critical commands over data interface within milliseconds after valid inhibit signal applied MSI. 5.2.4.6 Ground reference. power return connection shall ground reference release consent signal. 5.2.5 Mission store interlock interface. mission store shall provide connections interlock interface primary signal (primary MSI) auxiliary power signal (auxiliary MSI). interlock interface both primary auxiliary shall include interlock connection interlock return connection. path between interlock interlock return primary auxiliary connectors shall have impedance milliohms maximum over frequency range when measured MSI. This impedance applies excitation current within range milliamperes. excitation current from connected aircraft carriage store continuously applied periodically pulsed. mission store shall comply with requirements herein when excitation signal open circuit voltage applied between MIL-STD-704 upper voltage limits. mission store shall electrically isolate both interlock interlock return connections from mission store circuits grounds. isolation shall kilohms minimum over frequency range kHz. 5.2.6 Mission store address interface. mission store shall include connections address interface primary signal detecting assigned store data address. mission store needs determine mated status MSI, shall also address interface this purpose. address interface shall include five binary encoded address connections (A0, A4), address parity connection common address return connection. characteristics defined below shall apply address parity connections when referenced address return connection. Mission stores which implement data interface (5.2.2) shall energize address interface monitor data address assigned mission store connected aircraft carriage store. [Note49] Mission stores which implement data interface required address interface. 5.2.6.1 Address assignment. mission store shall monitor five binary encoded address connections logic logic states. remote terminal address assigned shall defined follows: Remote terminal address (A4) (A3) (A2) (A1) (A0) mission store shall monitor address parity connection logic logic states. mission store shall accept assigned address valid remote terminal address address parity connection logic state indicates parity. parity defined number logic states six-bit composed five address connections plus address parity connection. mission store shall, minimum, determine assigned address during initialization sequence 5.2.12. [Note50] 5.2.6.2 Address signal. mission store shall provide excitation signals with following characteristics: Open circuit (logic voltage: Minimum voltage Maximum voltage 31.5 Rise fall times applied voltage shall exceed milliseconds when measured with resistive load.
MIL-STD-1760C Logic current: Minimum current milliamperes Maximum current milliamperes through each address parity connection Maximum current milliamperes through address return connection Rise fall times applied current shall exceed milliseconds when measured with resistive load. 5.2.6.3 Logic threshold. mission store shall detect logic logic states under following conditions. logic state detection conditions apply valid invalid address assignment combinations. Logic current level microamperes less address address parity connection when excitation voltage 5.2.6.2 applied store shall interpreted logic state. Logic voltage level 1.50 less between address parity) connection address return connection when excitation current 5.2.6.2 sourced store shall interpreted logic state. 5.2.6.4 Response characteristics. store shall allow milliseconds minimum logic state stabilization after application excitation signal. 5.2.7 Mission store structure ground. mission store shall provide connection primary signal auxiliary power signal which terminated mission store structure capable carrying overcurrent levels defined figures primary auxiliary MSI, respectively. structure ground interface shall used signal return power return path. [Note51] 5.2.8 Mission store power interface. mission store shall provide connections power interface primary signal (primary MSI) auxiliary power signal (auxiliary MSI). primary shall contain power power return connections power power return connections. auxiliary shall contain power connection power return connection. mission store required power interfaces. However, power interface used, mission store shall comply with requirements below. power interface used, impedance between unused power connection associated return connection shall greater than kilohms dc). [Note52] 5.2.8.1 Voltage level. mission store shall compatible with voltages which comply with normal abnormal characteristics voltage transients utilization equipment defined MIL-STD-704 with following addition. mission store shall compatible with normal steady state lower voltage limit 20.0 [Note53]. 5.2.8.2 Load current. mission store shall comply with following load current requirements when voltage within range 20.0 29.0 5.2.8.2.1 Primary signal set. Under fault free conditions, mission store load applied primary each power power connections shall exceed maximum load current level figure 5.2.8.2.2 Auxiliary power signal set. Under fault free conditions, mission store load applied auxiliary shall exceed maximum load current level figure
MIL-STD-1760C 5.2.8.2.3 Simultaneous load. Under fault free conditions, mission stores with class shall limit total simultaneous current power interfaces primary auxiliary maximum load current level figure 5.2.8.3 Load isolation. mission store shall provide minimum isolation kilohms between primary power connection, primary power connection auxiliary power connection. mission store provide continuity between associated power return connections. 5.2.8.4 Overcurrent compatibility. mission store shall become unsafe fault currents maximum overcurrent levels figures sourced into primary auxiliary MSIs, respectively. 5.2.8.5 Off-state leakage current. mission store shall compatible with off-state leakage currents supplied primary milliampere between each power respective return. mission store shall compatible with off-state leakage currents supplied auxiliary 2.50 milliamperes between auxiliary power associated power return. 5.2.8.6 Stabilization time. mission store shall compatible with voltages which below levels 5.2.8.1 herein milliseconds during power turn-on turn-off (see figure 19). 5.2.8.7 Ground reference. power return connections primary auxiliary MSIs shall reference each associated power connection. mission store shall compatible with aircraft carriage stores which connect returns aircraft structure ground. mission store shall also compatible with aircraft carriage stores which isolate returns from aircraft structure grounds. [Note54] 5.2.8.8 Power utilization. Mission stores shall utilize power auxiliary power those safety critical functions which insufficient interlocks exist store assuring that required level store safety achieved once associated power interface activated. store shall execute safety critical functions (e.g., employ) solely result activation power auxiliary power. Mission stores utilize power auxiliary powering non-safety critical store functions with understanding that aircraft will energize these power interfaces until aircraft determined that safe Mission stores shall utilize power only powering those store functions which safety critical which have sufficient safety interlocks such that store safety significantly degraded with activation power Mission stores shall withstand without functional damage, activation power interfaces prior needed activation. [Note55] 5.2.9 Mission store 115/200 power interface. mission store shall provide connections 115/200 power interface primary signal (primary MSI) auxiliary power signal (auxiliary MSI). Both primary auxiliary shall contain phase phase phase neutral connections. mission store required phases. However, phase used, mission store shall comply with requirements below. phase used, impedance between unused phase connection associated neutral connection shall greater than kilohms Hz). mission store shall require presence power during actual store separation from aircraft carriage store, during connector disconnect.
MIL-STD-1760C 5.2.9.1 Voltage level. mission store shall compatible with voltages which comply with normal abnormal characteristics voltage transients utilization equipment defined MIL-STD-704 with following addition. mission store shall compatible with normal steady state lower voltage limit 105.0 RMS. [Note56] 5.2.9.2 Load current. mission store shall comply with following load current requirements when voltage within range volts RMS. 5.2.9.2.1 Primary signal set. Under fault free conditions, mission store load applied each phase connection shall exceed maximum load current level figure Mission stores designed operation through carriage stores shall limit phase load percent maximum load current level figure 5.2.9.2.2 Auxiliary power signal set. Under fault free conditions, mission store load applied each phase connection shall exceed maximum load current level figure 5.2.9.2.3 Simultaneous load. Under fault free conditions, mission stores with class shall limit total simultaneous phase current phase connections primary auxiliary maximum load current level figure Mission stores designed operation through carriage stores, shall exceed ampere continuous phase load. 5.2.9.3 Load isolation. mission store shall provide minimum isolation kilohms between primary phase connections auxiliary phase connections. mission store provide continuity between associated neutral connections. 5.2.9.4 Overcurrent compatibility. mission store shall become unsafe fault currents maximum overcurrent levels figures sourced into primary auxiliary MSI, respectively. 5.2.9.5 Off-state leakage current. mission store shall compatible with off-state leakage currents applied primary milliamperes between each power phase neutral. mission store shall compatible with off-state leakage currents supplied auxiliary milliamperes between each auxiliary power phase associated neutral. 5.2.9.6 Stabilization time. mission store shall compatible with voltages which below levels 5.2.9.1 herein milliseconds during power turn-on turn-off (see figure 19). 5.2.9.7 Load power factor. mission store load each phase shall have power factor within limits figure 5.2.9.8 Phase unbalance. mission store load shall comply with phase power utilization requirements MILSTD-704. 5.2.9.9 Ground reference. neutral connections primary auxiliary MSIs shall reference each associated phase connection. mission store connect neutrals routed through mission store structure. mission store shall compatible with aircraft carriage stores which connect isolate) neutrals from) aircraft structure grounds. [Note57]
MIL-STD-1760C 5.2.9.10 Power utilization. Mission stores shall utilize 115/200 power (primary auxiliary) only powering those store functions which safety critical which have sufficient safety interlocks such that store safety significantly degraded with activation 115/200 mission store shall withstand without damage, activation loss power phase time. [Note58] 5.2.10 Mission store power interface. power interface growth provision future application power interfaces shall utilized until characteristics performance details added this standard. class interface connectors MSIs shall include contacts plugged cavities) power power return. general electrical characteristics will defined MIL-STD-704 (except voltage drop) continuous current levels amperes primary amperes auxiliary MSI. 5.2.11 Mission store fiber optic interface. store uses fiber optic interfaces, fiber optic interfaces shall comply with requirements specified 5.1.11 subparagraphs. fiber optic interfaces mission store shall occur until optical logical (protocol) characteristics fiber optic interfaces added this standard.[Note59] fiber optic interfaces used, connector shall employ plugs that compatible with umbilical which populated with fiber optic termini. [NOTE60] 5.2.12 Store initialization. Stores shall comply with following initialization requirements sequence presented. 5.2.12.1 Pre-initialization conditions. following pre-initialization conditions shall provided store (see 5.1.12.1): power interfaces deactivated. Release consent interface inhibit state. Address interface stabilized.
NOTE: Data interface, interlock interface, high bandwidth interfaces, bandwidth interface, fiber optic interfaces active. 5.2.12.2 Power application. store shall compatible with simultaneous (within milliseconds) application primary power primary 115/200 power non-predetermined sequence. store shall require application other interface power completing initialization requirements specified herein. 5.2.12.3 Address determination. Within milliseconds interface power application (ac, both, required store), store shall interrogate address discretes (see 5.2.6.2) accept assigned address store's data interface address. 5.2.12.4 First response. Within milliseconds interface power application (ac, both, required store), store shall capable responding valid commands received over data interface. required store response shall either: valid status word indicating busy condition, valid status word indicating non-busy condition plus appropriate valid data words. store receives commands before transpired, store shall either respond defined above shall respond all.
MIL-STD-1760C 5.2.12.5 First required non-busy response. Within interface power application (ac, both, required store), store shall capable responding valid store description message transmit command. This response shall valid status word indicating non-busy condition plus appropriate valid data words defined appendix B.[Note61] [Note62] [Note63]
Carriage store requirements.
Carriage stores shall provide Carriage Store Interfaces (CSIs) Carriage Store Station Interfaces (CSSIs) with following characteristics. [Note64] 5.3.1 Carriage store interfaces. carriage store shall provide interfaces each primary signal CSSI bi-directional simplex transfer type type signals. CSSI shall contain four interfaces (HB1, HB2, HB3, HB4). 5.3.1.1 Minimum transfer capacity. carriage store shall support minimum CSSI time) transfer type signal type signal (but simultaneously) simultaneously with transfer signals HB2, HB3, accordance with table carriage store shall also support unidirectional broadcast signals from multiple CSSIs accordance with table minimum, only CSSI need supported with signal transfers time. Routing configurations will defined aircraft data bus. TABLE Carriage store signal transfer.
Interface Applicability either Type -orPoint-to-point, bi-directional simplex, CSSI transfer. Type -simultaneously withHB2 Type Type Type Broadcast, uni-directional, CSSI(s) transfer. Type Type 5.3.1.2 Type signal path characteristics. 5.3.1.2.1 Return loss. input return loss each signal path shall less than over frequency band when output terminated with nominal impedance. output return loss each signal path shall less than over frequency band when input terminated with nominal impedance. 5.3.1.2.2 Transient response. carriage store network transient response shall such that when each signals figures applied input, output signal shall meet requirements figures output response envelope figure V'1.0 defined figure response envelope figure V'1.3 defined figure
MIL-STD-1760C 5.3.1.2.3 Insertion gain. signal path insertion gain between input output shall +0.5/-1.0 where insertion gain (V'1.3 V'1.3 defined figures respectively. 5.3.1.2.4 Representative pulse delay. representative pulse delay signal path shall exceed microsecond shall vary more than nanoseconds from nominal value. nominal value signal path representative pulse delay current routing path configuration shall retained made available transmission aircraft required. When signal figure applied input, representative pulse delay time difference between voltage being reached input signal rising edge voltage V'1.3/2 being reached output signal rising edge where V'1.3 defined figure 5.3.1.2.5 Equalization. gain misequalization signal path shall exceed limits shown figure zero gain reference shall gain kHz. maximum gain between shall exceed with respect zero-dB gain reference. 5.3.1.2.6 Dynamic range. When kHz, sine wave added voltage ±0.25 then applied CSSI input, signal output signal path shall compressed clipped more than percent. When kHz, sine wave added voltage ±0.75 then applied input, signal output signal path shall compressed clipped more than percent. 5.3.1.2.7 Signal path offset. maximum voltage output each signal path shall exceed ±250 with input terminated. 5.3.1.2.8 Noise. Noise type signal path outputs shall meet following requirements over frequency band MHz. 5.3.1.2.8.1 Random noise. Using weighting function figure weighted noise power each signal path output with input terminated shall exceed RMS. 5.3.1.2.8.2 Periodic noise. calculated periodic noise voltage each signal path output with input terminated shall exceed 0.52 mVRMS each valid state routing network. noise voltage shall determined stimulating each interface AEIS associated with signal path turn in-band, maximum amplitude sinusoidal signal which produces maximum weighted crosstalk voltage signal path output. weighting function given figure frequency stimulus signal different each interface. calculated periodic noise voltage shall root squares individual crosstalk voltages plus unstimulated weighted periodic noise voltage signal path output when interfaces terminated. 5.3.1.2.8.3 Impulse noise. impulse noise voltage signal path output with input terminated shall exceed 5.3.1.2.8.4 Stimulated noise. more than noise shall added signal path noise output when sinusoidal excitation signal frequency between applied input. 5.3.1.2.8.5 Common mode noise. Using weighting function figure common mode noise voltage output each signal path shall exceed with respect output structure ground when input terminated input signal return connected input structure ground. 5.3.1.3 Signal path electrical characteristics (type None specified this time.
MIL-STD-1760C 5.3.1.4 Ground reference (type When configured carry type signals, signal paths through carriage store shall either: Passive, with signal return (shield) electrically isolated from carriage store structure ground, shown figure 21a, Active, with output signal return (shield) connected carriage store structure ground input signal return (shield) isolated from carriage store structure ground, shown figure 21b. signal connection signal return (shield) connection INPUT SIGNAL PATH signal connection signal return (shield) connection
OUTPUT
FIGURE 21a. Equivalent circuit Type passive signal path.
signal connection equivalent sink impedance signal return (shield) connection
equivalent source impedence equivalent source voltage
signal connection
signal return (shield) connection
INPUT
SIGNAL PATH
OUTPUT
FIGURE 21b. Equivalent circuit Type active signal path.
FIGURE Equivalent circuits carriage store Type signal paths. 5.3.1.5 Ground reference (type When configured carry type signals, signal return (shield) shall electrically connected carriage store structure ground both signal path input output. 5.3.2 Carriage store data interface. carriage store shall transfer data between CSSI(s) commanded aircraft. 5.3.2.1 CSI. carriage store shall provide data interfaces (Mux primary signal CSI. Each connections shall include data high, data low, shield connection. data interfaces shall meet same functional electrical characteristics data interfaces MSI, specified 5.2.2.1 5.2.2.2. 5.3.2.2 CSSI. carriage store shall provide data interfaces (Mux each primary signal CSSI. Each data interface shall include data high, data low, shield connection. data interfaces CSSI shall meet same functional electrical characteristics data interfaces ASI, specified 5.1.2.1 5.1.2.2, except zero crossing deviation shall limited
MIL-STD-1760C 5.3.3 Carriage store interface. carriage store shall provide interface each CSSI bi-directional simplex transfer signals. Routing configurations will defined aircraft data interface. When connected source sink equipment with impedances defined 4.3.3, signal paths shall have following characteristics. 5.3.3.1 Minimum transfer capacity. carriage store shall support transfer signals between CSSI. minimum, only CSSI need supported with signal transfers time. Specific transfer capacity beyond this minimum controlled this standard. 5.3.3.2 Input/output impedance. input impedance (line-to-line) each signal path shall ohms ohms, over frequency band kHz, when output terminated with nominal sink impedance defined 4.3.3. output impedance (line-to-line) each signal path shall less than ohms, over frequency band kHz, when input terminated with nominal source impedance defined 4.3.3. 5.3.3.3 Insertion gain. signal path insertion gain between input output shall sine wave input. 5.3.3.4 Equalization. gain misequalization signal path shall exceed limits shown figure zero gain reference shall kHz. Gain +1dB -1dB
150Hz
300Hz
1kHz
3.4kHz
8kHz
Frequency FIGURE Maximum gain misequalization envelope (LB, carriage store). 5.3.3.5 Signal path offset. maximum voltage output each signal path shall exceed line-to-line lineto-ground with input terminated. 5.3.3.6 Noise. signal path noise shall meet following requirements over frequency band except where otherwise specified. 5.3.3.6.1 Periodic random noise. calculated periodic random noise voltage each signal path output with input terminated shall exceed mVRMS each valid state routing network. noise voltage shall determined stimulating each interface AEIS associated with signal path turn in-band (150 kHz), maximum amplitude sinusoidal signal which produces maximum
MIL-STD-1760C crosstalk voltage signal path output. frequency stimulus signal different each interface. calculated noise voltage shall root squares individual crosstalk voltages plus unstimulated periodic random noise voltage signal path output when interfaces terminated. 5.3.3.6.2 Impulse noise. With input signal path terminated, there shall standard deviation) more than occurrence impulse noise exceeding peak over three minute period. impulse noise voltage shall apply when band-limited pass. 5.3.3.6.3 Stimulated noise. frequency between kHz, application sinusoidal excitation signal signal path input shall more than noise output over frequency band kHz. 5.3.3.6.4 Common mode noise. peak common mode noise voltage output each signal path (CSI CSSI) shall exceed X0.5 when input terminated input shield same potential local structure ground. This requirement shall apply over band kHz. 5.3.3.7 Ground reference. signal paths through carriage store shall either: Passive, shown figure 23a, Active, with outputs referenced carriage store ground, shown figure 23b.
MIL-STD-1760C
non-inverting signal connection inverting signal connection shield INPUT SIGNAL PATH non-inverting signal connection
inverting signal connection shield OUTPUT
FIGURE Equivalent circuit passive signal path.
non-inverting signal connection inverting signal connection shield
non-inverting signal connection
inverting signal connection shield
INPUT
SIGNAL PATH
OUTPUT
Notes: V1-V2 Thevenin equivalent voltage source (balanced with respect ground). R1+R2 Thevenin equivalent source impedance. FIGURE 23b. Equivalent circuit active signal path. FIGURE Equivalent circuits carriage store signal paths.
5.3.4 Carriage store release consent interface. carriage store shall provide connections release consent interface each CSSI. 5.3.4.1 CSI. carriage store shall release consent signal from aircraft enable/inhibit fire, launch, release, jettison functions. carriage store shall release consent-interlocked safety critical commands received over data interface only release consent signal enabled state. Release consent shall meet same requirements release consent MSI, stated paragraphs 5.2.4.1 through 5.2.4.6. 5.3.4.2 CSSI. carriage store shall provide release consent interface each primary signal CSSI transferring enable/inhibit signal connected store(s). Release consent, when enabled state, shall indicate consent stores perform safety critical functions (such missile launch from rail launcher rocket firing from pod) when commanded over data interface. When inhibited state, release consent interface CSSI shall electrically isolated from release consent interface other CSSIs. isolation shall kilohms minimum Release consent
MIL-STD-1760C CSSI shall meet same requirements release consent ASI, stated paragraphs 5.1.4.1 through 5.1.4.6, with following clarifications exceptions: release consent required store, release consent signal shall attain enable state least milliseconds prior transferring safety critical command over data interface prior firing signal. release consent CSSI been enabled, carriage store shall operate under assumption that store connected CSSI remain enable state milliseconds after release consent signal returned inhibit state. 5.3.4.3 CSSI transfer. Release consent shall enable state before release consent enable state CSSI. When release consent inhibit state CSI, release consent shall inhibit state CSSIs. 5.3.5 Carriage store interlock interface. carriage store shall provide connections interlock interface primary signal primary CSSI locations also auxiliary power signal auxiliary CSSI locations. 5.3.5.1 CSI. interlock interface each primary auxiliary shall meet same requirements interlock interface, stated 5.2.5. 5.3.5.2 CSSI. carriage store shall monitor interlock shall provide information aircraft (via data interface) mated status each CSSI connector. interlock interface each primary auxiliary CSSI shall meet same open circuit voltage, excitation current, impedance detection threshold requirements interlock interface, stated 5.1.5. 5.3.5.3 Isolation. carriage store shall electrically isolate both interlock interlock return connections from carriage store circuits grounds. interlock signal each CSSI connector shall isolated from interlock signal other CSSI connectors. isolation shall kilohms greater from kHz. 5.3.6 Carriage store address interface. carriage store shall provide connections address interface CSSI. Each address interface shall include five binary encoded address connections (A0, A4), address parity connection common address return connection. 5.3.6.1 CSI. carriage store shall address interface from aircraft detecting assigned store data address determining mated status CSI. address interface shall meet same requirements address interface MSI, stated paragraphs 5.2.6.1 through 5.2.6.4. 5.3.6.2 CSSI. carriage store shall provide address interface each primary signal CSSI assigning data address MIL-STD-1553 remote terminal mission store mated CSSI. carriage store shall this interface only assigning address remote terminal associated with directly connected mission store. address interface CSSI shall meet same requirements address interface ASI, stated paragraphs 5.1.6.1 through 5.1.6.4. 5.3.7 Carriage store structure ground. carriage store shall provide connections primary signal CSSI(s) auxiliary power signal CSSI(s) which terminated carriage store structure ground capable carrying overcurrent levels defined figures primary CSSI(s)
MIL-STD-1760C auxiliary CSSI(s), respectively. structure ground interfaces shall used signal return paths power return paths. 5.3.8 Carriage store power interface. carriage store shall provide connections power interfaces power interfaces CSSI(s). aircraft shall control power. primary signal CSSI(s) shall contain power power return connections power power return connections. auxiliary power signal CSSI(s) shall contain power connection power return connection. 5.3.8.1 CSI. power interfaces shall meet same requirements power interfaces MSI, stated paragraphs 5.2.8.1 through 5.2.8.8, except following: shall compatible with normal steady state lower voltage limit 22.0
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