NAVY MIL-N-81497 A-1970 NAVIGATION SET INERTIAL AN ASN-84《AN ASN-84型惯性航海装备》.pdf

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1、MIL-N-81q97A 58 7797706 0170793 2 W z _. MILN-814.97A ( AS 1 15 March 1979 Superseding MILK431 497 (AS) 1 by 1968 MILITARY SPECIFICATION NAVIGATION SET, INERTIAL AN/ASN- 8 4 This specification has been approved by the Naval Air Systems Command, Department of the Navy 1, SCOPE 1.1 Scope - The equipme

2、nt covered by this specification shall attitude, velocity and position outputs. covered by this specirication shall consist of the following items: by means of inertial instruments, provide aircraft azimuth 1.2 Classification - The Inertial Navigation Set (INS) I tem Control, Navigation Con tro 1 ,

3、Gyros cope Assembly Indicator, Position Gyros cope. Assembly Compute r, N avi g a t i on Power Supply Rack Electrical Equipment . - Applicable Type Designation Paragraph C -7561/ASN-84 3.5.1 C -7560/ASN-84 .3.5*2 ID-1542/ASN-84 CN-1231/ASN-84 CP- 924/ASN-84 PP-4964/ASN-84 MT-3947/ASN-84 3.5.3 3.5.04

4、 3.5.5 3.566 3.5.7 1.3 Associated Equipment - “he equipment ehall operate with the associated equipment listed in 6.8; Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-flIL-N-BLY97A 58 7999706 0370794 Y - M -_ - 2. APPLICABLE DOCUMENTS 2.1. General -

5、The following documents of the issue in effect on the date of invitation for bids form a part of the specification to the extent specified herein. Specifications Military MIL-W-5088 MIL-E-5400 MIL-T-5422 MIL-1-6181 MIL-C-6781 MI L-P- 7 7 8 8 MIL-M-7793 MIL-E-17555 MIL-T- 18 3 O 3 MIL-N- 18 3 O7 MIL-

6、T- 19 57 6 MIL-S-20708 Wiring, Aircraft, Installation of Electronic Equipment, Aircraft, General Specification For Testing, Environmental, Aircraft Electronic Equipment Interference Control Requirements, Aircraft Equipment Control Panel: Aircraft Equipment, Rack or Console Mounted Plate, Plastic, Li

7、ghting Meter, Time Totalizins . Electronic And Electrical Equipment and Associated Repair Parts, Preparation for Delivery of Test Procedures: Preproduction and Inspection, for Aircraft Electronic Equipment, Format for Nomenclature and Nameplates for Aeronautical Electronic and Associated Equipment T

8、ransmitter, Remote Comwss Thin Wins Type ML-1 (Unstabilized,) Synchros, 60 and 400 cycles, General Specification for 2 O Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-N-L497A 58 99799Ob 0370795 b m -. MIL-N-81497A (AS) 2.1 (Continued) Specifica

9、tions Naval Air Systems Command AR- 5 Standards Military MSI7322 MS91403 MIL-STD-454 MIL-STD-704 MIL-STD-781 MIL-STD-794 Federal FED- STD- 5 9s Other ARINC 407 ARINC 407-1 Publications Naval Air Systems Command EI-554 2.1;l- Availability of Documents Microelectronic Devices Used in Avionics Equipmen

10、t, Procedures for Selection and Approval of Meter, Time Totalizing, Miniature Digital, 115 volt 400 cycle Cases, Large Size (For Use with Electronic Equipment in Arcraf t) Standard General Requirements for Electronic Equipment Electric Power, Aircraft , Character- istics and Utilization of Reliabili

11、ty Tests, Expotential Dis tribut ion Parts and Equipment, Procedures for Packaging and Packing of Colors Synchro Standard Manual, Aeronautical Radio, Inc. Avionics Installation instructions for Navigation Set, Inertial, ANjASN-84 (1) When requesting specifications, standards, drawings and publi- cat

12、ions refer to both title and number. cation and applicable specifications required by contractors in connection with specific procurement functions may be obtained upon application to the Covanding Officer,Naval Supply Depot, Code 105,5801 Tabor Avenue, Philadelphia , Pennsylvania. Copies of this cp

13、ecifi- o Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. MIL-N-81Li77A 58 W 7799706 0370796 I MIL-N- 8 14 9 7A (AS 3. REQUIREMENTS 3.1 Preproduction - This specification aakes provision for preproduction testing. zaterials, fulfillzent of major des

14、ign objectives shall be the prhe consideration. In so doing the following shall govern: 3.2 Parts and Materials - In the selection of parts and I Microelectronic technology shall be considered ard microelectronic items shall conform to the require- ments specified herein. Other parts and materials r

15、equirements shall conforz to MIL-E-5400, Non-repairable subassemblies, as outlined in KL-E-5400, shall be used when practicable. The general size of the subassembly and the amount of circuitry to be included therein shall be approved by the procuring activity. Non-repairable subassemblies must be re

16、liable (See 6.4). When previously produced models of this equipment did not use non-repairable subassemblies, the design shall not be changed to employ non-repairable subassemblies without the approval of the procuring activity. t 3.2.1 Nonstandard Parts and - Materials Approval - Approval for the u

17、se of non-standard parts and materiais (including electron tubes, transistors, and diodes) other than micro-electronic devices shall be obtained as outlined in MIL-E-5400. shall be approved as outlined in AR-5. Microelectronic devices 3.2.2 Microelectronic Module Assemblies - When used, micro- elect

18、ronic modularassemblies shall meet the requirements of AR-5. 3.2.3 Modules, Maintenance - The electronic portions of the equipment shall be divided into maintenance modules. zodulec shall normally be considered repairable. Maintenance t 3.3 Design and Construction - The equipment shall conform with

19、all the.applicable requirements of MfL-E-5400 for design, con- straction, and workmanship, except as otherwise specified herein. 4 O Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-14- 814971 (AS) 3.3.1 Total Weight - The total weight of t.his eq

20、uipment excluding cables, shall be a minimum consistent with good design and shall not exceed 85.0 pounds. 3.3.2 Reliability - 3.3.2.1 Operational Stability - The eqsipment shall be designed to operate with Satisfactory performance, continuously or intermittently for a period 0.f at least 500-operat

21、ing hours or 6 months whichever ccurs first, without the necessity for readjustment of any controls which are inaccessible to the operator during normal use. - - 3.3.2.2 Operating Life - The equipment shall have a total operating life of 25,000 hours with reasonable servicing and replace- ment of pa

22、rts. Parts requiring scheduled replacement shall be specified by the contractor. 3.3.2.3 Reliability in Mean Time Between Failure (MTBF) - The eauiDment shall h ave 750 hours or mean (operating) time between - failures when tested and accepted as outlined under the requirements of 4.4.3. 3.3.2.4 Tim

23、e Totalizing Meter - The equipment shall contain time totalizing meters in accordance with MIL-M-7793. Meters shall have a range of 9999 hours, and shall be included in the following units : Unit Type of Meter Gyroscope Assembly - MS17 3 2 2 Computer, Navigation MC17 3 22 Power Supply MC 17 3 2 2 3.

24、3.3 Cabling and Connections - 3.3.3.1 Cables and Connectors - The equipment shall provide for the use of cables and connectors Ifi accordance with MIL-E-5400. 3.3.3.2 Interconnection Cabling - The equipment shall be capable of satisfactory operation using external wiring in accordance with the appli

25、cable requirements of MIL-W-5088. shall be unshielded, except that a minimum number of the individual wires may be shielded when demonstrated a8 necessary to,meet inter- ference control requirements and provided the assembly of the cable to its plugs may be easily accomplished. portion of the connec

26、tors attached to the as Part of the equipment. The external wiring External cables and that cables shall not be 8upplied f 5 O Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-3 3 3.2.1 External Wiring - External wiring shall be in accordance with EI-

27、554. 3.3.4 Control Panels .- All rack or console mounted con- trol panels shall conform to the applicable requirements of MIL-C-6781 Type I except as specified herein. 3.3.4.1 Control Panel Front Panels - All control panel front panel details shall conform to MIL-C-6781 (Type I), MIL-P-7788 (Class I

28、) except as specified herein. must be approved by the procuring activity prior to pre-production testing. t I The configuration of all panels 3.3.4.1.1 Panel #Front; Control, Gyroscope Assembly - In accordance with Figure 1. 3.3.4.1.2 Panel, Front: Control, Navigation - In accordance with Figure 2.

29、3.3.4.1.3 Panel, -Front: Indicator, Position - In accordance Interchangeability - The equipment shall meet the with Figure 3. interchangeability requirements specified in MIL-E-5400. 3.3.5 3.3.6 Interference Control - The generation of radio inter- ference-by the equipment and the vulnerability of t

30、he equipment to radio interference shall be controlled within the limits of MIL-1-6181. Short duration interference levels shall be in accordance with 3.3.2 Of MIL-1-6181. 3.3.7 Maintainability - The equipment shall meet the main- tainability requirements specified herein. 3.3.7.1 In Flight Maintena

31、nce - In flight maintenance shall not be a requirement for the equipment. provide both visual and electrical failure Indications in the event of malfunction. However, the equipment shall 3.3.7.2 Flight Line Maintenance - The equipment shall be designed to permit corrective maintenance to be performe

32、d within a mean time of 30 minutes (MIN) for 95 percent of all detected system failures. Corrective maintenance shall consist of fault isolation to an individual unit (LRU), unit replacement, and equipment checkout. The 30 MIN shall not include equipment warm-up and alignment time, LRU malfunction d

33、isplays shall be provided on the Contro1,Gyroscope Assembly. submode. Flight line maintenance shall be accomplished in a Self Test 6 o Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-_ MIL-N-61477A 58 7779706 0370979 3 MIL-N- 81 49 7 A (AS) 3.3.7.2.1

34、 Definition of Line Replaceable Units (LRU) - The LRUs shall be defined as follows: Gyroscope Assembly Computer, Navigation Power Supply Indicator, Position Control, Navigation Control, Gyroscope Assembly Battery 3.3.7.2.2 Flght Line,Maintenance - Additional Capability - The Power Supply and Compute

35、r, Navigation shall contain external test connectors which when coupled with standard test equipment can be used to identify and isolate malfunctioning modules or groups of modules while mounted in the aircraft. Computer, Navigation shall be provided to permit rapid removal and replacement of select

36、ed mobules or groups of modules without the removal of the equipment from its mounted position, ability shall be provided for in-aircraft fault isolation to the module level of each unit, module replacement and equipment.checkout within a maximum elapsed time of 90 MIN. have exposed test points to f

37、acilitate unit checkout. Access doors on the Power Supply and Where possible, the cap- The Power Supply shall,in addition, 3.3.7.3 Removable Cam Compensator - The equipment shall be designed to permit removal and replacement ot the magnetic heading cam compensator from the Control, Gyroscope Assembl

38、y when installed in the aircraft. 3.3.7.4 Control Panel Covers - All control panels shall have quick disconnect removable covers to facilitate unit repair. . 3.3.7.5 Intermediate Maintenance - The equipment shall be such that shop repair actions can be accomplished to include module removal and rpai

39、; to the component level. 3.3.8 Nomenclature and Nameplptes - Nomenclature assignment and nameplate approval tor equipment identification shall be in accord- ance with MIL-N-18307. 3.3.9 Standard Conditions - The following conditions shall be used to establish normal performance characteristics unde

40、r standard conditions and for making laboratory bench tests. Temperatures Altitude : Vibration; Room ambient (25 f 5 degrees Centigrade (DCG Cl Normal Ground None , Room ambient up to 90 percent relative humidity t Humidi ty : O Provided by IHSNot for ResaleNo reproduction or networking permitted wi

41、thout license from IHS-,-,-MIL-N- 81 49 74 (AS) 3.3.9 (Continued) Input Power Voltage: 115f1.0 volts (VI; 40055 hertz (Hz), 3 phase, Y connect 26+:4V, 4004.5 Hz, 1 phase (Synchro excitation) 5 to 28V, 400f5 Hz, 1 phase (variable) (Control Panel edge 1 igh t i ng vol tag e ) t27.5k0.5 V DC +18k0.5 V

42、DC(Advisory lamp exci ta tion) +27.5 fd.5 V DC or +9 f 0.5 V DC (Control, Naviqation Advisory lamp excitation) 3.3.10 Service Conditions - The equipment shall operate satisfactorily under any of the environmental service conditions or reasonable combination of these conditions as specified in MILE-5

43、400, ciass i, except as mciified herein; 3.3.10.1 Vibration - The equipment shall operate satisfactorily when subjected to the vibration requirements of Curves I and II of MIL-E-5400. Maximum vibration for the Power Supply and Navigation Com- yter shall be 5G. 3.3.10.2 factorily when subjecte to t e

44、 continuous temperature requirements 03 MIL-E-5400for Class 1 equipment except as specified herein, Degraded performance shall-be permitted for ambient temperatures in excess of 46.1 DEG C. Minimum operating temperature for the Position Indicator shall be limited to -25 DEG C. Tem erature - The equi

45、pment shall operate satis- + 3.3.10.3 Cooling Alr - Circulating cabin air with maximum temperature of +55 DEG C shall be available for cooling the equipment specified herein. align prior to operation shall not exceed the values tabulated below. 3.3.11 Alignment Time - The time required to warmup and

46、 Time 20 MIN 30 NIN Irlode - v Temperature Ranqe (T) - T * -18 DEG C -54 DEG C T C-18 DEG C T 2 -54 DEG C 3.5 MIN Inertial -*Ground Align Inertial -*Damping On (Inf light Align) Slave Free T 2 =54, DEG i3 3.5 MIN f I *For latitudes below f75 DEG # Provided by IHSNot for ResaleNo reproduction or netw

47、orking permitted without license from IHS-,-,-3.3.12 Primary Input Power Requirements - The equipment s!iall nieet all applicable requi.rements of MIL-STD-704 and shall give specified performance from the following power sources with charact- eristics as defined in PIIL-STD-704 having limits as spec

48、ified therein. The power required shall not exceed the specified amounts, (1) AC Power (three phase); 115/200V, 400 Hz, Category B, 660 Voltamperes (VA) operating power (maximum) Category B, 1000 VA heater power (maximum) , phase (load) balance shall be within 400 VA (3) AC Power (single phase): 26:

49、 VI 400 Hz, 27 volt amperes synchro power4maximum) (4) DC Power, 28 VI Category %; 2 amperes (maxi- mum) (2) AC Power (three phase); 115/200Vl 400 Hz, (5) DC Power, 18 V, Category B, 1.2 ampere (maxi- mum) advisory lamp excitation for Control, Gyroscope Assembly and Indicator, Position Category A, 400 Hz for control panel edge lighting; 25 VA (maximum) (7) DC Power, 28 V DC, Category B, 0.3. ampere (