1、- MIL-G-2308LC 66 W 9997706 OL3L205 9 mfl C-1581 MIL-G-23081 C( AS) 2 October, 1972 Superseding 13 January 1967 MIL-G-23081 B( AS) MILITARY SPEC1 FICATION GYROSCOPE INDICATOR SYSTEM, VERTICAL This specification has been approved by the Naval Air Systems Command, Department of the Navy. 1. SCOPE 1.1
2、Scope .- The equipment covered by this specifiiation is a 400 Hertz, 3-phase, 4-wire wye power supply. System shall consist of the items listed in 6.7. The Gyroscope System shall be of the following types: Vertical Gyroscope Indicator System operated by 11 5/200 vol t + Classification - The Vertical
3、 Gyroscope In Aircraft, Installation of MI L-E- 5272 Environmental .Testing, Aeronautical and Associated Equipment, General Specification For Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,- -I _- - - MLL-G-E30BLC bb W 99999Ob 013120b O W MIL-G-23081
4、 C( AS) MIL-E-5400 Electronic Equipment, Aircraft, General MI L-T- 5422 MI L-C-5541 Chemical Films for Aluminum and Aluminum MIL-L-6085 MI L-M-7793 Meter, Time Totalizing MIL-C-14806 Coating Reflection Reducing for Instrument Cover Glasses and Light Wedges MIL-T-18303 Test Procedures: Preproduction
5、and Acceptance For Aircraft Electronic Equipment, Format For MI L-N- 18307 Nomenclature and Namepl ates for Aeronautical Electronic and Associated Equipment MI L-G-23083 Gyroscope, Rate Switching MS17399 MIL-L- 25467 Light, Integral, Aircraft Instrument, General Specification For MIL-C-26482 Connect
6、ors, Electric, Circular, Miniature, Quick Disconnect MIL-G-81322 Lubricating Grease, Bal 1 Bearing MIL-G-81559 Gyroscopic Assemblies , Atti tude and Directional Reference Instrument For Aircraft Preservation and Packagi ng , Procedures For Speci fi cati on For Tes ti ng , Environmental , Ai rcraft E
7、l ec tron i c Equ i pment Al 1 oys Lubricati ng Of 1 , Aircraft Instrument, Low Vol ati 1 i ty Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-G-2308LC 66 = O6 0331207 2 MIL-G-2308lC( AS) Barrier Film Solvents and Solutions Ni trog en Glasses, Fl
8、at and Corrugated, for Glazing, Mirrors and Other Uses Clean Room and Work Station Requirements, Controlled Environment Colors Electromagnetic Interference Characteristics, Requirements for Equipments Maintainability Demonstration Flectric Power, Aircraft, Characteristics and Utilization of Reliabil
9、ity Tests Exponential Distribution Reliability Program for Sys tems and Equipment Development and Production Barrier Coating Process for Anti-Friction Bearing Connector, Plug, Electric, Straight Connectors, Plug, Electric Solder Type, Straight Bayonet Coupling Meter, Time Totalizing Miniature, Digit
10、al 115 Volt 400 Cycle Gyroscope, Displacement, Roll and Pitch Hardmoun t Gyroscope, Rate Switching Indicator+ Attitude, Remote - 3-inch Case Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,- fl I L - G- 2 3 O IC b 6-i 77 9 9 7 Ob c3 1708 MIL-G-23081C(
11、AS) MS 17 40 1 Indicator,Attitu,d, Remote- MS 2 43 6 7 MS25237 MS 33 5 5 8 Naval Air Systems Command AR- 5 AR-10 AR-34 Lamp, Incandescent, Miniature Integral Lighting Lamp, Incandescent, Single Contact Midget Flanged Base Numerals and Letters, Aircraft Instrument Dial, Standard Form of Microelec Iro
12、nic Device8 Used in Avionics1 I Equipment, Procedures for Selection and Approval of I Maintainability of Avionics Equipment and Systems, General Requirements for Failure Classification for Reliability Testing, General Requirements for Lubricant, Instrument Ball Bearing High Flash Point d AS- 2 844 s
13、pecifications standards, drawings, and publications, refer to both title and number. by contractors in connection with specific procurement functions may be obtained upon application to the Commanding Offfcer, Publications and Forms Center (1051), 5801 Tabor Avenue, Philadelphia, Pennsylvania 19120.
14、 Copies of this specificaeion and applicable specifications required 3.mQUIWMENTS 3.1 Preproduction - This specification makes provision or preproduction testing, Parts and Materials - In the selection of parts and materials, fdffllmen% of major design objectives shall be the prime consideration. In
15、 so doing, the following shall govern: (1) Parts and materials requirements shall conform to MIL-E-5400. 4 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,- MIL-G-23083C 66 7779706 0333207 b MI L-G- (2) Nonrepairable subassemblies, as outlined in MIL-
16、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. Nonrepairable subassemblies must be reliable. (See 6.4.) (3) When previously produced models of this equipment do not use nonr
17、epairable subassemblies, the design shall not be changed to employ nonrepairable assemblies without the approval of the procuring acti vi ty . . * 3.2.1 Nonstandard Parts and Materials Approval - Approval for the use of nonstandard parts and materials (including tubes, transistors and diodes) shall
18、be obtained as outlined in MIL-E-5400. Microelectronic devices shall be approved as outlined in AR-5. * 3.2.1.1 Final approval of all nonstandard parts and materials shall be completed before Preproduction approval can be granted. Microelectronic Modular Assemblies - When used, Micro- (I)elec:o%*oul
19、ar Assembli es shall meet the requirements of Specification AR-5. Conformal coatings encapsulants, embedments or potting materials used wi th modul ar assemblies contai ni ng i ntegrated circui ts and discrete parts shall be easily removable without damage to the assembly. wl th an anodic conforming
20、 to MIL-t-5400. * 3.2.3 Aluninun Alloy Parts - Alminun parts shall be covered * 3.2.4 Nonmagnetic Materials - Nonmagnetic materials shall be used for all parts of the Indicators, except where nonmagnetic materials 5 Provided by IHSNot for ResaleNo reproduction or networking permitted without license
21、 from IHS-,-,-Mounting Base I Remote Attitude Indicator 7.0 lbs. 7.0 lbs. 3.8 lbs. 5.0 lbs. I * 3.3,2 Reliabilit - The contractor shall conduct a Reliability Program us1 ng MIL-STD-7 / has previously produced the eqpment, the program previously used nqy be continued unless otherwise indicated in the
22、 contract or order. satisfactory. performance, continuously or intermittently, for a period of at least 2000 hours without the necessity for readjustment of any controls which are inaccessible to the operator during normal use. life of 10,000 hours wit reasona e servicing and replacement of parts. P
23、arts On a reorder from a supplier, who * 3.3.2.1 Operational Stabil i ty - The equi ment chal 1 operate with O eratin Life - The equipment shall have total operatind I -+%l- 3.3.2.2 I requiring scheduled replacement shall be specified by the contractor. I the Rate Switching Gyroscope shall be in acc
24、ordance with MIL-G-23083. I Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-G-23081C (AS) 3.3.3 Cabling and Connections - 3.3-3.1 Cables and Connectors - The system shall provide for the use of cables and connectors in accordance with MIGE.5400.
25、3.3.3.2 interconnection Cabling- Ihe system shall be capable of satisfactory operation using external wiring in accordance with the applic- able requirements of MIGW-5088 and Figure 1 or Figure 2 of this specifica- tion. of the.individual wires my be shielded when demnstrated, as necessary, to metin
26、terference control requirements and provided the assembly of the cable to its plugs my be easily accomplished. External cables and that portion of the connectors attached to the cables shall not be supplied as part of the system. * The external Wiring shall be unshielded, except that a minkmmnurher
27、3.3.4 equipmnt, interchanppabilitg shd1 edst between units and between all Interchangeability of Reordered Quipmnt - For reordered replaceable assenblis, subassemblies, and parts of a desigpated mdel of any previously mufactwed equipment or system supplied or desigated by the procuring activity. * 3
28、.3.5 Interfei.ence Control - The generation of radio interference by the equipment and the vulnerability of the equipmnt to radio interference hail neet the requiremnts of MIGSTD-461. * 3.3.6 Provisions for Maintainability - The Phintainability Program, e built-in test features, construction and.Lpa
29、ckaging, provisions for test points, and other maintainability parameters shall be as specifled in Requiremant m-10. 3.3.7 Nameplates - Nanieplates approval for equipmnt identification! shall be in accordance with MIL-N-18307. 3.3.8 Standard Conditions - The following conditions shall be used to est
30、ablish normal performance characteristics under standard conditions and-for making laboratory Bench !EstS. Room ambient (25+5OC) Temperature - Altitude NOrlmum. 3.5 Detai 1 Requirements - 3.5.1 Displacement Gyroscope - The reference for the Vartical Gyroscope Indicator System is the Displacement Gyr
31、oscope. The Displacdnt Gyroscope shall be constructed in accordance with E14114 and the require- ments of this specification. It shall develop continuous electrical signals representative of aircraft attitude through 366 degrees roll and f 82 degrees of pitch, The Displacement Gyroscope shall operat
32、e with all the components of the Vertical Gyroscope Indicator System. It shall be built to withstand the normal strains, jars, vibrations, and such other conditions as are incident to shipping, storage, installation, and service. I to 01 I Provided by IHSNot for ResaleNo reproduction or networking p
33、ermitted without license from IHS-,-,-. MIL-G-230LC bb m 7797706 0131215 1 m *3.5.1.1 Case - The outline dimensions of the Displacement Gyroscope and its shockmount shall be in accordance with MS14114-2. * 3.5.1.2 Gyroscopes Mount - The Gyroscope shall have inter vi brati on is01 ators and shall be
34、hard-mounted in accordance with MS14114-3. * 3.5.1.2.1 Cable and Connector - With the Displacement Gyroscope properly mounted on the Gyroscope Mount, the assembly shall meet the re- qui rements of MS14114. a mans of rapidly clamping the feet of the Displacement Gyroscope in place. One end of the mou
35、nt shall hold the Gyroscope firmly by the feet when the case 1s placed on the mount and slid along its long axis toward that end for a dqqtance not greater than 5/8 inch. The other end of the mount shall permit the quick release of the Displacement Gyroscope Case from the mount by means of a thumbsc
36、rew quick release mechanism on the mount. Normally the cable end of the Displacement Gyroscope Case shall be on the quick release end of the mount. * 3.5.1.2.2 Attaching Method - The Gyroscope Mount shall incorporate Replacement of the Gyro shall not require realignment in the airframe. Gimbalin - T
37、he Displacement Gyroscope shall be mounted + * 3.5.1.3 torque motor on each axis. The pitch axis shall be the pivot axis of the two gimbals and shal have two axes of freedom. There shall be a synchro e er gimbal (gyro wheel housing) and shall be perpendicular to the roll axis which is the pivot axis
38、 of the outer gimbal. The roll axis shall be parallel to the longitudinal axis or long centerline of the case as shown on MS94114. 3.5.1.4 Gimbal Freedom - The Displacement Gyroscope shall have unlimited freedom in rol1 and a minimum of plus or minus 82 degrees of freedom in pitch. Pitch stops shall
39、 be incorporated which produce a roll precession when the pitch freedom is exceeded. The pitch stops shall be so designed that no parts of the Gyroscope will be damaged by a loop at the rate of 90 degrees per second. The plus or minus three degrees error shall result from loops of 15 degrees per sec
40、ond plus or minus one degree per second. Errors induced by roll maneuvers at ratesplu or minus three degrees of error to not exceed one degree. 3.5.1.5 Gyroscope shall be so desied that the maximum free drift, noted after compensation for the earths rotation, shall not be greater than 0.25 degree pe
41、r minute. This requirement applies over the entire temperature range specified herein, and with the spin axis either tilted 20 degres or vertical. Drift - Unless otherwise specified, the Displacement Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-I
42、- I MIL-G-23081 C( AS) 3.5.1.6 Erection - The erection mechanism shall incorporate separate systems for pitchroll. Erection shall be accomplished by electrolytic swttches and torque motors on the gimbals. When the vertical is displaced in one axis, it shall not deviate by more than one degree in the
43、 other axis while it is erecting. The erection system shall provide both Initial and Final Erection and shall erect the Displacement Gyroscope, from any attitude to the vertical, as determined by the Vertical Sensing Electro- lytic Switches. The above shall also be accomplished with the Gyroscope ha
44、rdmounted and without Vibration. 3.5.1.6,l Initial Erection - The Displacement Gyroscope shall have fast Initial Erect3on such that it assumes a position wlthfn one degree of vertical in pitch and roll within a maximum of 68 seconds after power i s appl i ed 3.5.1,6.2 Final Erection - The Displaceme
45、nt Gyroscope shall align its spin axis with the direction of gravity within plus or minus 1/2 degree in two minutes, or less, after the Initial Erection period. 3.5.1.6.3 Erection Rate - 3,5,1.6.3.1 High (Fast) Erection - Means shall be provided to apply a fast erection simultaneously to both axes o
46、f the Gyroscope to the apparent vertical. This fast erection shall be obtained by externally closing the circuit between Pins N and C of the Electrical Connector. The fast erection rate shall not be less than 15 degrees per minute in either axis. about the roll axis sham be nominally twp degree per
47、minute and shall fall between the limits plotted on Figure 3 throughout all environments and all roll attitudes of the Displacement Gyroscope Case. Roll erection shall not be affected appreciably by displacement of the Gyroscope from vertical about the pitch axis through plus or minus 82 degrees. Th
48、e rate of normal erection about the pitch axis shall be nominally one degree per minute and shall fall between the limits plotted on Figure 3 throughout a11 environments and pitch attitudes of plus or minus 40 degrees. for greater pitch attitudes, the erection rate shall be held to a minimum but sha
49、ll not be less than that permitted by Figure 3, Pitch erection shall not be affected appreciably by displacements of the Gyroscope in the roll axis of plus or minus 85 degrees or less, Internal provisions shall also be made for Internal Roll Cut-out without change to exirtfng connector. 3.5.1.6.3,3 such that when Pins L and G are connected externally, roll erection shall be cut out and when Pin
