1、1. SCOPE MIL-C-85247 AS) 23 June 198 h MILITARY SPECIFICATION COMPUTERy AIR DATA CP-l005A/A This specification is approved for use by the Naval Air Systems Command y Department of the Navy and is available for use by al 1 Departments and Agencies of the Department of Defense. 1.1 Scope. The Computer
2、, Air Bata, CP-l105A/A covered by this specifi- cation will supply impact pressure, static pressure, barometric altitude, Mach number, and true airspeed information to cockpit indicators and flight control systems for aircraft control. 1.2 Associated equipment. This equipment shall operate with the
3、associa- ted equipment listed in 6.7. 2. APPLICABLE DOCUMENTS 2.1 Issues of documents. The following documents of the issue in effect on the date of invitation for bids or request for proposal y form a part of this specification to the extent specified herein. c 1 Beneficial comnents (recommendation
4、s, additions, deletions) and any pertinent data which may be of use in improving this document should be addressed to: Comnanding Officer, Naval Air Engineering Center, Engineering Specifications and Standards Department (ESSD) Code 93, Lakehurst, NJ 08733, by using the self-addressed Standardizatio
5、n Document Improvement Proposal (DD Form 1426) appearing at the end of this document or by letter. t, THIS DOCUMENT CONTAINS 37 PAGES. FSC 661 O B Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-SPECIFICATIONS Federal PPP -B-636 TT-L-20 Mi 1 i tary M
6、IL-P-116 MIL-T-152 MIL-C-172 MIL-W-5088 MIL-E-5400 M I L -T-5422 MIL-M-7793 MIL-E-17555 Boxes, Fi berboard Lacquer, Camoufl age Preservation-Packaging, Methods of Treatment, Moi sture and Fungus Resistant, of Communications, Electronic and Associated Electrical Equipment , General Process for Cases;
7、 Bases, and Mounts, Vibration (For Use with Electronic Equipment in Aircraft) Wiring Aerospace Vehicle El ectroni c Equi pment , Ai rborne , General Speci fi cat i on for Testing Envi ronmental Airborne Electronic and Associated Equipment Meter, Time Total i zing Electronic and Electrical Equipment,
8、 Accessories, and Repai r Parts ; Packaging and Packing of. MIL-T-18303 Test Procedures; Preproduction, Acceptance and Life For Aircraft El ectroni c Equi pment , Format for MIL-N-18307 MIL-S-19500 Nomcl ature and Ident i fi cat i on for Electronic, Aeronautical , and Aero- nauti cal Support Equi pm
9、ent Incl udi ng Ground Support Equipment Semiconductor Devices, General Specification for MIL-S-20708/8 Synchro Control Transmitter, Type 26V-llCX4C 2 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-STANDARDS Mi 1 i tary MIL-STD-129 Marking for Shipm
10、ent and Storage MIL-STD-461 Electromagnetic Emission and Suscepti- bility Requirements for the Control of Electromagnetic Interference MIL-STD-701 List of Standard Semiconductor Devices MIL-STD-704 Aircraft Electric Power Characteristics MIL-STD-781 MIL-STD-785 MIL-STD-2074 MS33656 Re1 i abi 1 i ty
11、Design Qual if i cati on and Production Acceptance Tests: Exponenti al Di stri buti on Reliability Program for Systems and Equi pment Devel opment and Product i on Failure Classification for Reliability Testing Fitting, End, Standard Dimensions for Flared Tube Connection and Gasket Seal (Copies of s
12、pecifications, standards, drawings, and publications required by contractors in connection with specific procurement functions should be ob- tained from the procuring activity or as directed by the contracting officer.) 2.2 Other publications. The following documents form a part of this specificatio
13、n to the extent specified herein. Unless otherwise indicated the issue in effect on date of invitation for bids or request for proposal shall aPPl Y CONRAC CORPORATION DOCUMENTS 7102432 7102530 Acceptance Test Procedure for Air Data Computer, P/N 560T58-1 Burn-In Procedure for Air Data Com- puter, P
14、/N 560T58-1 DRAWINGS 560T58-1 Ai r Data Computer 7603729 Static Fitting 66442 Connector (Application for copies of CONRAC Corporation documents should be. addressed to CONRAC Corporation, Systems-East Division, 32 Fairfield Pl ace, West Caldwell , New Jersey 07006.) 3 Provided by IHSNot for ResaleNo
15、 reproduction or networking permitted without license from IHS-,-,-AFCRC-TR-59-267 Ai r Research and Deve1 opment command (ARDC) Model Atmosphere, 1959 (Application for Copi es of AFCRC-TR-59-267 should be addressed to the Air Force Geophysics Research Directorate, Cambridge Research Center, Bedford
16、, Massachusetts .) 3. REQUIREMENTS 3.1 First article. When specified (see 6.2), the contractor shall furnish equipment samples for first article inspection and approval (see 4.4 and 6.3). 3.2 Parts and materials. In the selection of parts and materials, ful- fillment of major design objectives shall
17、 be the prime consideration. In so doing the following shall govern: a. Parts and materials requirements shall conform to MIL-E-5400. b. Nonrepairable subassemblies, as outlined in MIL-E-5400, shall be used when practicable. The general size of the subassembly, and the amount of circuitry to be incl
18、uded therein shall be approved by the procuring activity. Nonrepairable subassemblies must be re1 i ab1 e. c. When previously produced models of this equipment did not use nonrepai rable subassemblies, the design shall not be changed to employ nonrepairable assemblies without the approval of the pro
19、curing activity. 3.2.1 Nonstandard parts and material approval. Approval for the use of nonstandard parts and materials shall be obtained as out1 ined in MIL-E-5400. 3.2.2 Electron devices. Integrated circuits, transistors, and diodes shall be chosen and appl ied. Complements reports shall be prepar
20、ed as out- lined in MIL-STD-701 for procuring activity review and approval prior to pre- production testing. Diodes shall be selected in accordance with MIL-STD-701. Transistors shall be selected in accordance with MIL-S-19500. 3.3 Design and construction. The equipment shall conform with all the ap
21、plicable requirements of MIL-E-5400 for design, construction, and workman- ship, unless otherwise specified herein. The following air data tables shall be used in the functional design of the air data computer: AFCRC-TR-59-267, ARDC Model Atmosphere, 1959 Air Force Surveys in Geophysics No. 115. 3.3
22、.1 Total weight. The total weight of the equipment excluding cables shall be a minimum consistent with good design. The weight shall not be greater than 25 pounds. 3.3.2 Reliability. The contractor shall conduct a reliability program in accordance with MIL-STD-785. On a reorder from a supplier who i
23、s producing the equipment, the program previously approved may be continued unless other- wise indicated in the contract or purchase order (see 6.2.ld). 4 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-3.3.2.1 Operational stability. The equipment sh
24、all operate with satis- factory performance, continuously or intermittently for a period of not 1 ess than 2000 hours 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 li
25、fe of 3000 hours with minimal servicing and repl acement of. parts. A 1 i st of parts requiring scheduled repl acement due to wear during the 1 ife of the equipment, and the wearout life of such parts, shall be made available for the procuring activity review and approval (6.2.2). 3.3.2.3 Reliabilit
26、y in mean time between failure (MTBF). The equipment, incl uding any Bui 1 t-in-Test provisions , shall have 2000 hours of mean (operating) time between failures (0, as defined in MIL-STD-781) when tested and accepted as outlined under the requirements of 4.4.3. 3.3.2.4 Time totalizing meter. The eq
27、uipment shall contain a 10,000 hour time totalizing meter in accordance with MIL-M-7793. The location of the time totalizing meter shall be on the front chassis plate. 3.3.3 Cabling and connectors. 3.3.3.1 Cables and connectors. The equipment shall provide for use of cables and connectors in accorda
28、nce wjth MIL-E-5400. 3.3.3.2 Interconnecting cabling. The equipment shall be capable of satisfactory operation using external wiring in accordance with the applicable requirements of MIL-W-5088. The external wiring shall be unshielded, except that a minimum number of the individual wires may be shie
29、lded when demon- strated as necessary to meet interference control requirements and provided the assembly of the cable to its plug may be easily accomplished. Cables and that portion of the connectors which are to be attached to the cables shall not be suppl ied as part of the equipment. Type 66442
30、connectors shall be used 3.3.4 Cases, bases, and mountings. The case sizes and mount loading shall be in accordance with MIL-C-172. 3.3.5 Interchangeability. The equipment shall meet the interchange- ability requirements as defined in MIL-E-5400. 3.3.6 Interference control. The generation of radio i
31、nterference by the equipment and the vulnerability of the equipment to radio interference shall be controlled within the limits of MIL-STD-461. 3.3.7 Maintenance and field testing. Provisions for maintenance shall be as specified in MIL-E-5400. Specific test points, built-in testing capability as sp
32、ecified in 3.3.15 and test facilities shall be-provided for ease of field testing and maintenance. The test points shall be used to is01 ate a fai 1 Ure to the module level and shall be wired to the external connectors. 3.3.8 Nomenclature and nameplates. Nomenclature assignment and nameplate approva
33、l for equipment identification shall be in accordance with MIL-N-18307. 5 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-3.3.9 Standard conditions. The following standard conditions shall be used to establish normal performance characteristics and f
34、or making laboratory bench test s. Room Ambient -( 25 -50 a . Temperature c +15“ b. Altitude Normal ground c. Vi brat i on No ne d. Humidity Room ambient up to 90% re1 ati ve humidity e. Input Power Vol tage 115 f 2 vac, 400 Hz O VR at O Mach; 1 VR at 1.3 Mach k. Output 19 Mach Number (A/D Converter
35、). (2) Range Control Transmitter MIL-S-20708/8B (26V - 11CX4) 0.13 to 1.3 Mach O degrees at O Mac h (3) Scale Factor 257.1 degrees/Mach Electrical zero at O Mach (see Figure 3) (4) Excitation Voltage 26 vac, 400 Hz (suppl ied by A/D Converter) (5) Phase Shift O +5 degrees (6) Null Voltage 19 MV max
36、Total, 12 MV max Fundamental (7) Electrical Error O +7 minutes max 1 Output 20 Mach Control C( Incremental Mach) Autopilot. Type wire is01 ated 400 Hz clutched synchro output proportional to the deviation from the “engage“ Mach with phase reversing to indicate direction of departure. (2) Range k0.05
37、 Mach (3) Scale Factor 0.079 Volts/0.001 Mach (4) Sensitivity 0.001 Mach (5) Excitation Voltage 26V 400 Hz (suppl ied by autopi 1 ot) (6) Phase Shift oo k loo (7) Linearity The linearity deviation of the synchro within k6Oo of nul 1 shall not be greater than +1%. 14 Provided by IHSNot for ResaleNo r
38、eproduction or networking permitted without license from IHS-,-,-(8) Engage Cl utch The cl utch shall be engaged by the appl i cati on of 28 t 2 volts dc from a remote source for Mach hold .operation. When the voltage is removed, a mechanism shall return the output device to its null position. -7 (9
39、) Null 0.045 volts total or less before and after clutch engagement. m. Output 21 Fault Is01 ation (Course Logqc). (2) Scale Factor Synchro, control transmitter , Bendix Type No. AY 503-25-A7 or Equival ent. 240“ - ,O Logfc ) 0.27012 (3) Range 0.33 IN Hg to 25.46 IN Hg n. Output 22 Fault Isolation (
40、Fine Log 1. (2) Scale Factor Synchro , control transmitter Bendix Type No. AY-500-25-A7 or equivalent 240“ - 675“ Log c . (L7012l (3) Range o. Output 23 Fault Is01 ati on (Coarse Log / ) . (2) Scale Factor Synchro, differential transmitter Bendix Type No. AY-533-25-AZ or equi val ent 60“ - 75 LO;, )
41、 - 75OLOg (S 2.11778 ) (3) Range 31 242 IN Hg to 3.264 IN Hg 15 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-p. Output 24 Fault Isolation (fine Log qc/Ps). (2) Scale Factor Synchro, differential transmitter Bendix Type No. AY-533-25-A2 or equi val
42、 ent 675Lo(S -11778 1 (3) Range 31.242 IN Hg to 3.264 IN Hg q. Output 25 AAU/19A Power. (1) Vol tage 102 to 124 volts (2) Frequency 380 to 420 Hz (3) Power (I) 30 V.A. max 3.5 Detail requirements. 3.5.1 Rack assembly. The rack assembly shall be in accordance with standard Air Transport Rack .(ATR) p
43、rovisions except for the envelope size, and except that the modules (see 3.5.2) shall be mounted on a flat tray and shall meet the following requirements: 3.5.1.1 Function. The rack assembly shall provide for the following: a. Plug-in mounting of the module subassemblies on one tray. b. Interconnect
44、ing wiring between the module connectors on the tray and the external connectors on the front panel. c. Mounting of the ai r data computer in the aircraft and isolation of the equipment from external vibration. d. Mounting of the elapsed time indicator, static and pitot fittings, and electrical conn
45、ectors on the front panel. 3.5.1.2 Form factor. The form factor and outline dimensions shall not be greater than those shown in Drawing No. 560T58-1. 3.5.1.3 Contents. The rack assembly shall consist of the following: a. Mounting Rail Assembly O b. Shock Mount Assembly c. Module Mounting Assembly 16
46、 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-C-85247 (AS) d. El ectri cal connections e. Static and pitot ports f. Elasped Time Indicator g. Relay for Built-In-Test 3.5.1.3.1 Mounting rail assembly. The mounting rail shall be designed for fix
47、ed mounting in the aircraft and to provide mounting for the shock mounti ng assembly. 3.5.1.3.2 Shock mount assembly. The shock mount assembly shall mount on the mounting rail and shall provide the following: a. Mounting rack b. Shock mounts (4) c. Mounting provisions for the module mounting assembl
48、y d. Interconnection tubing between external pressure ports and the modules e. Interconnecting wi ri ng between the external electrical connectors and the modules 3.5.1.3.3 Module mounting assembly. The module mounting assembly shall mount on the shock mount assembly and shall provide the following:
49、 a. Provisions for securing the pl ug-in module. b. Provisions for mounting the internal (module) connectors of the shock mount assembly. c. Provide quick disconnect pressure connections for the altitude and impact pressure modules. 3.5.1.3.4 Electrical connections. The rack assembly shall provide external connectors. 3.5.1.3.5 Elapsed time indicators. The rack assembly shall provide a 10,000 hour num
