1、MIL-C-3LllE bb 9999906 0138406 T W 7 Beneficial comments (recommendations, additions, deletions, and an3 pertinent data which may be of use in improving this document) should be addressed to: Engineering Specifications and Standards Department (Code 93), Naval Air Engineering Center, Lakehurst, NJ 0
2、8733, by using the self-addressed Standardization Document improvement Proposal (DD Fom 1426) appearing at the end of this document or by letter. MIL-C-38418E(&) 30 July i981 SUPERSEDING MIL-C-38418D 4 May i970 MILITARY SPECIFICATION CONTROL ASSEMBLY, GYROSCOPE, ATTITUDE This specification has been
3、approved for use by the Naval Air Systems Command, Department of the Navy, and is available for use- by all Departments and Agencies of the Department of Defense. 1. SCOPE 1.1 This specification covers the requirements for an Attitude Gyroscope Control Assembly, designated A/A24G-39, which provides
4、pitch, roll, and heading angular displacements. 1.2 Classification - The equipment controlled by this specification shall consist of the following components in accordance with 3.2. i! Type Designation Control Assembly, Gyroscope Attitude A/A24G-39 (see 3.5) Gyroscope, Displacement (see 3.6) Amplifi
5、er, Electronic Control (see 3.6) Controller, Compass System (see 3.8) 1.3 Associated Equipment - This equipment shall operate with the associated equipment listed in 3.2.2. / . FSC 6610 THIS DOCUMENT CONTAINS 78 .- PAGES. Provided by IHSNot for ResaleNo reproduction or networking permitted without l
6、icense from IHS-,-,-MIL-C-38 41 8E (AS ) 2. APPLICABLE DOCUMENTS 2.1 Issues of Documents - The following documents of the issue in effect on date of invitation for bids or request for proposal, form a part of this specification to the extent specified herein. SPECIFICATIONS Military MIL-P-116 MIL-D-
7、1000 MI L-W- 5 08 8 MIL-E-5400 MIL-C-5541 MIL-1-6181 MIL-C-6781 MIL-S-7742 MIL-P-778 8 MI L-M- 7 7 93 MIL-T-18 303 MIL-N-18307 MIL-T-19 576 MIL-S-20708 MIL-K-2 504 9 MIL-C-2505 O MIL-F-2 517 3 MI L-L-2 54 6 7 MIL-C-2 6500 MIL-L-2 716 O MIL-D-38134 MIL-G-813 22 MIL-B-81744 MIL-L -8184 6 Pre servation
8、-Packaging , Methods of Drawings, Engineering and Associated Lists Wiring, Aerospace Vehicle. Electronic Equipment, Airborne, General Specification For Chemical Conversion Coating on Aluminum and Aluminum Alloys Interference Control Requirements, Aircraft Equipment Control Panel, Aircraft Equipment,
9、 Rack or Console Mounted Screw Threads, Standard, Optimum Selected Series: General Specif ication For Panels, Information, Integrally Illuminated Meter, Time Totalizing Test Procedures, Reproduction, Acceptance, And Life For Aircraft Electronic Equipment, Format Nomenclature And Identification for E
10、lectronic, Aeronautical, and Aeronautical Support Equipment Including Ground Support Equipment Transmitter, Remote Compass, Thin Wing Type ML-1 (Unstabilized) Synchros, General Specification For Knob, Contro 1, Equipment, Aircraft (Asg) Color, Aeronautical Lights and Lighting Equipment, General Requ
11、irements For Fastener, Control Panel, Aircraft Equipment Lighting, Integral, Red, Aircraft Instrument, General Specification For Connectors, General Purpose, Electrical Miniature, Circular Environment Resisti rig, General Specification For Lighting, Instrument, Integral, White, General Specification
12、 For Detect or, Magnetic, Azimuth DSU-4/A, High Temperature Grease, Aircraft, General Purpose, Wide Temperature Range, Barrier Coating Solution and Solvent Barrier Coating Solution, Lubricant Migration Deterring Lubricating Oil, Instrument, Ball Bearing, High Flash Point 2 Provided by IHSNot for Res
13、aleNo reproduction or networking permitted without license from IHS-,-,-MIL-C-3LILE 66 W 777770b OL3LIO 3 W MIL-C-38418E(AS) STANDARDS Federal FED-STD-595 Military C MIL-STD-143 MI L-STD-4 5 4 MIL-STD-704 - MIL-STD-781 MIL-STD-794 MIL-STD-810 MIL-STD-831 MIL-STD-889 MIL-STD-1334 MIL-STD-2074 MS17322
14、 MS21384 MS24264 MS24266 MS2 51 64 MS25169 MS33558 PUBLICATIONS Federal Standard Colors Standards and Specifications, Order of Precedence for the Selection of Standard General Requirements for Electronic Equipment Aircraft Electric Power Characteristics Reliability Tests, Exponential Distribution Pa
15、rts and Equipment, Procedures for Packaging and Packing of Environmental Test Methods Test Reports, Preparation of Dissimilar Metals Process for Barrier Coating of Anti-Friction Bearings Failure Classification for Reliability Testing Meter, Time Totalizing Miniature, Digital 115 Volt 400 Cycle Knob
16、Pointer, Illuminated and Non-illuminated Connector Receptacle, Electrical, Flange Mount, Miniature Connector, Plug, Electrical - Straight, Miniature Skirt, Control Knob Knob, Bar, Small Numerals and Letters, Aircraft Instrument Dial, Standard Form of Naval Air Systems Command ET-590 EI-590 Avionics
17、Bench, Preflight and Flight Test Instructions for Attitude Gyroscope Control Assembly A/A24G-39 Avionic Installation Instructions for Attitude Gyroscope Control Assembly A/A24G-39 Radio Technical Commission for Aeronautics Document No. DD-160 - Environmental Conditions and Test Procedures for Airbor
18、ne Electronic/Electrical Equipment and Instruments. (Application f.or copies should be addressed to the RTCA, Secretariat, Suite 655, 1717 Street N.W., Washington, D.C. 20006.) 3 ,._ - . . . Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-(Copies of
19、specifications, standards, drawings, and publications required by contractors in connection with specific procurement functions should be obtained from the procuring activity or as dir.ected by the contracting officer. ) 3. WQUIREMENTS 3.1 First Article - When specified in 6.2, the contractor shall
20、furnish sample units for first article inspection and approval (see 4.4 and 6.2). -4 3.2 Components - The Attitude Gyroscope Control Assembly shall consist of the following: a. A/A24G-39 Control Assembly (1) Gyroscope, Displacement, SBK-llA/A24G-26 (2) Amplifier, Electronic Control, ASK-32/A24G-39 (
21、fixed wing aircraft) or, .ASK-44/A24G (rotary wing aircraft) (3) Controller, Compass System, DCK-l28/A24G (white-lighted) or, DCK-l29/A24G (red-lighted) or, DCK-228/A24G (white-lighted, IPL) or, DCK-234/A24G (moisture-sealed, white-lighted) or, DCK-235/A24G (Moisture-sealed, red-lighted) or, DCK-236
22、/A24G (Moisture-sealed, white-lighted, IPL) 3.2.1 Application Considerations - The A/A24G-39 Control Assembly shall be supplied for installations requiring four heading outputs, a single roll output, a single pitch output, and azimuth rate roll erection control. The Compass System Controller is avai
23、lable in different configurations to meet various flight deck lighting requirements and installation considerations (see 6.2). The Electronic Control Amplifier is to be selected to meet the performance criteria of the applicable aircraft (see 6.2). 3.2.2 Associated Equipment - The equipment shall op
24、erate properly with the following associated equipment in accordance with 3.7: 4 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-C-38418E (AS) - Item Type Designation Specification Magnetic Azimuth Detector, DSU-4A/A MIL-D-38134 Transmitter, Comp
25、ass Remote ML-1 UIL-T-19 57 6 3.3 Selection of Standards and Specifications - Standards and specifications for necessary commoditieg and services not specified herein shall be selected in accordance with MIL-STD-143. s - 3.4 Materials 3.4.1 Fungus-proof Materials - Materials that are nutrients for f
26、ungi shall not be used where it is practical to avoid them. Where used and not hermetically sealed, they shall be treated with a fungicidal agent acceptable to the procuring activity. If used within a hermetically sealed enclosure, fungicidal treatment shall not be required. 3.4.2 -Metals - Metals s
27、hall be.of the corrosion-resistant type or shall be suitably treated to resist corrosion due to conditions likely to be encountered in. storage or normal service. 3.4.2.1 Dissimilar Metals - Unless suitably protected against electrolytic corrosion, dissimilar metals shall not be used in intimate con
28、tact with each other. Dissimilar metals are defined in MIL-STD-889. 3.4.3 Nonmagnetic Materials - Non-magnetic materials shall be used for all parts of the control assembly except where magnetic materials are essential. 3.4.4 Corrosive Fumes - Materials, as installed .and used in the control assembl
29、y and under the service conditions specified herein, shall not liberate deleterious fumes. 3.4.5 Protective Treatment - When materials are used in the construction of the control assembly that are subject to deterioration when exposed to climatic and environmental conditions likely to occur during s
30、ervice usage, they shall be protected against such deterioratiod in a manner that will in no way prevent compliance with the requirements of this specification. The use of apy protective coating which will crack, chip, or scale with age or extremes f climatic and environmental conditions shall be av
31、oided. 3.5 Design and Construction - The control assembly shall be designed to accept and provide input and output signals as specified herein, and shall be so constructed as to withstand the strains, jars, vibrations, and other conditions incident to shipping, storage, installation, and service. 5
32、Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,- Corresponding components of all contro 1 assemblies procured shall be interchangeable between control assemblies. No gimbal binding under differential pressure conditions shall occur as a result of int
33、erference between case and gimbal should a leak develop in service. 3.5.1 Plug-in Cards - The electronic control amplifier circuitry and electromechanical modules shall be placed on plug-in cards which shall be removable without the use of special tools. The plug-in cards shall be keyed and color-co
34、ded to prevent being installed in the wrong location and shall have test points for easy maintenance. 3.5.2 Maintainability - The following maintainability requirements shall be considered in the design of the control assembly: a. Minimization of the complexity of maintenance tasks (for example: cal
35、ibration, adjustments, inspection, et cetera) by maximum use o simple design which includes optimum interchangeability and use of s t a nda rdi ze d e qui pme nt o r comme rci a 1 it em s. be Rapid and positive recognition of equipment malfunction or marginal performance. c Rapid and positive identi
36、fication of the replaceable defective part, assembly, or components. d. Minimum numbers and types of tools and test equipment (special and standard) needed to perform maintenance. em Optimum accessibility in all systems, equipments, and components requiring maintenance, inspections, removal, or repl
37、acement. 3.5.3 Reliability - The contract specified mean-time-between-failures (MTBF) for the control assemblies and their components shall be as follows based on a discrimination ratio of 2.0 at a confidence level of 80 percent: a. 1,3 50 hours b. SBK-llA/A24G-26 Displacement Gyroscope: 2,2 40 hour
38、 s AIA2 46-3 9 Cont ro 1 Assembly : c. ASK-32/A246-39 Electronic Control Amplifier: 3,440 hours d. ASK-441A246 Electronic Control Amplifier: 3,440 hours 6 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-c - i MIL-C-3qLE 66 m 9777706 033Lt32 5 m MIL-C
39、-38418E(AS) e. DCK-l28/A24G Compass System Controller: 10,000 hours f DCK-l29/A24G Compass System Controller: 10,000 hours g. DCK-228/A4G Compass System Controller : 10,000 hours h. DCK-234/A24G Compass System Controller: 10,000 hours i. DCK-235/A24G Compass System Controller: 10,000 hours j. DCK-23
40、6/A24G Compass System Controller: - 10,000 hours 3.5.3.1 Longevity - The control assembly and components shall each have an operating life span (equipment longevity as defined in MIL-STD-781) of not less than 2,000 hours before they consistently fail to meet the MTBF index. Those components that are
41、 subjected to reliability tests and have individually accumulated 2,000 hours or longer shall not be subjected to a longevity test. 3.6 SBK-llA/A24G-26 Displacement Gyroscope - The displacement gyroscope, including associated electronics, shall consist of a vertical and a directional gyro mounted in
42、 multiple gimbals as described in the following paragraphs. This gimbal arrangement is used in order to avoid a gimbal lock position. 3.6.1 Vertical Gyro - The vertical gyro shall have sufficient angular momentum and be so designed as to meet the performance specified herein when operated throughout
43、 the temperature, vi bration, and acceleration range s. 3.6.2 Directional Gyro - The directional gyro shall have sufficient angular momentum and be of such design as to provide the performance specified herein when operated throughout the temperature, vibration, and acceleration range s. 3.6.3 Gimba
44、l System - The displacement gyroscope configuration shall consist of a two-axis directional gyro vertically stabilized by a two-axis vertical gyro. 7 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,- MIL-C-38418E bb 777770b 0138413 7 1 MIL-C-38418E(AS
45、) 3.6.3.1 Inner Directional Gyro Gimbal - The first (inner) directional gyro gimbal (gyro wheel housing) shall be stabilized by the angular momentum of the gyro. Its pivot axis shall be the first directional-gyro axis of freedom, shall be perpendicular to the spin axis of the gyro, and normally shal
46、l lie in the horizontal plane. The slaving torquer shall act about this axis. The gimbal shall have a minimum of +30 of freedom about its axis. - 3.6.3.2 Directional Gyro Azimuth Gimbal - The second directional gyro gimbal shall be stabilized by the angular momentum of the gyro. Its pivot axis shall
47、 be the second directional gyro axis of freedom and shall be aligned with the vertical. The azimuth output synchro and the leveling torquer shall act about this axis. The gimbal shall be capable w of continuous rotation about its axis. * - 3.6.3.3 Third Gimbal - The third gimbal shall be the pitch g
48、imbal of the vertical gyro. 3.6.3.3.1 Pitch Gimbal - The first vertical gyro axis of freedom shall be stabilized by the angular momentum of the vertical gyro, shall be normally the pitch axis, and shall normally lie in a horizontal plane. The roll erection torquer shall act about this axis. The gimb
49、al shall incorporate gimbal stops for controlled precession during maneuvers through the vertical. A linear acceleration sensor shall be provided per 3.7.4.2. 3.6.3.4 Fourth (Outer) Gimbal - The fourth gimbal shall be the roll gimbal of the vertical gyro. 3.6.3.4.1 Roll Gimbal - The second vertical gyro axis of freedom shall be stabilized by the angular momentum of the vertical gyro, shall be the roll axis and shall be align
