1、i- cr cg 03 3 SUPE HStD ING MIL- C - I8244 (AER I - 16 MARCH 1955 P MILITARY SPECIFICATION CONTROL AND STABILIZATION SYSTEMS: AUTOMATIC, 7 PILOTED AIRCRAFT, GENERAL SPECIFICATION FOR r( # This specification has been approved by the Bureau of Naval Weapons, Department of the Navy. 1. SCOPE Scope - Th
2、is specification covers design, test and performance requirements for either GFE or CFE automatic control and stabilization systems for ail U. S. Navy piloted aircraft. In the event of conflict between this specification and other referenced documents the requirements of this specifica- tion shall g
3、overn. The detail requirements for aparticular system shall be as specified in the detailed specification, contract or purchase order for that system. 2. APPLICABLE DOCUMENTS 1.1 (See 6.2) 2.1 General - The following documents, of the issue in effect on the date of invitation for bids, shall be us-r
4、ever applicable in the design, installation and operation of the automatic control and stabilization system. SPECIFICATIONS Military JAN-1-225 JAN- T- 781 MIL- F- 3541 MIL - S - 3 950 MIL - E -4682 MIL -W - 5088 MIL- E - 5272 MIL -E - 5400 MIL-H-5440 MIL-1-61 15 MIL-1-6181 MIL-L-6880 MIL-E-7080 MIL-
5、M-7969 MIL-A-8064 Interference Measurements, Radio, Methods of, 150 Kilocycles to 20 Megacycles (For Components and Complete Assemblies) Terminal; Cable, Steel (For Swaging) Fittings, Lubrication Switches, Toggle Electron Tubes and Transistors, Choice and Application of Wiring, Aircraft, Instailatio
6、n of Environmental Testing, Aeronautical and Associated Equipment, General Specification for Electronic Equipment, Aircraft, General Specification for Hydraulic System; Aircraft Type I and II, Installation and Data Requirements for Instrument Systems, Pitot Tube and Flush Static Port Operated, Insta
7、llation of Interference Control Requirements, Aircraft Equipment Lubrication of Aircraft, General Specification for Electrical Equipment, Piloted Aircraft Installation and Selection of, General Specification for Motors, Alternating Current, 400-Cycle, 115/200 Volt System, Aircraft, General Specifica
8、tion for Actuators and Actuating Systems, Aircraft, Class A and B, Electro- I Mechanical, General Requirements for 1 Obtained From GLOBAL ENGINEERING DOCUMENTS 2625 So.Hickory St. Santa Ana, CA 92707 (714)540-9870: (21 3)624-1216: (800)854-7 179 Provided by IHSNot for ResaleNo reproduction or networ
9、king permitted without license from IHS-,-,-hIIL-6-18244A (WEB) hgL-M-7793 MIL-PL-8501 MIL-S-8512 MIL-Mo8609 MIL-Il-8708 MIL- P-8785 MIL-I9-18300 MIL-N-18307 MIL-E- 19600 MIL-R-22256 MIL-R-23094 8TANBATIDS Military MIL-STD-203 MIL-STD- 704 MS15001 MS15002 Meter, Time Totalizing Helicopter Flying Qua
10、lities, Requirements for Support Equipment Aeronautical, Special, General Specification for Design of Motors, Direct Current, 28-Volt System, Aircraft, General Specificationfor Class A and B Data, Design; Contract Requirement for Aircraft Flying Qualities of Piloted Airplanes Design Data Requirement
11、s for Contracts Covering Airborne Electronic Equipment Nomenclature and Nameplates for Aeronautical Electronic and Associated Equipment Electronic Modules, General Aircraft Requirements tor Reliability Requirements for Design of Electronic Equipment or Systems Reliabllity Assurance for Production Ac
12、ceptance of Avionic Equipment, General specification for Cockpit Controls; Location and Actuation of For Fixed Wing Aircraft Electric Power, Aircraft, Characteristics and Utilizatlon of Fittings, Lubrication (Hydraulic) Surface Check, 1/4 - 28 Taper Threads, Steel, Type 1 Fittings, Lubrication (Hydr
13、aulic) Surface Check, Straight Threads, Steel, Type 2.2 Availability of Documents (1) When requesting specifications, standards, drawings, and publications refer to both title and number. Copies of this specification and applicable specifications required by contractors in connection with specific p
14、rocurement functions may be obtained upon application to the Commanding Officer, Naval Supply Depot, Code DCS, 5801 Tabor Avenue, Philadelphia 20, Pennsylvania, 3. REQUIREMENTS 3.1 System Desigr-Requirements - Automatic Flight Control Systems (AFCS) slilill bo as smpIo, diroccfoolproof as possibIow?
15、th respect to design, operation and maintenance. 2 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-C-L244A NI 9977906 ClLi25223 2 MIL-C-18244A (MEP) 3.1.1 3.1.1.1 Automatic Flight Control Systems (A FCS) Categories of Operation - The control func
16、tion or functions to be performed by automatic flight control systems or components shall be determined from the military character- istics or the requirements of the aircraft ar class of aircraft in which the equipment shaU be used. By definition, the automatic control functions shall fall within t
17、he following categories: 3.1.1.1.1 Augmentation - The augmentation category shall include those control functions which are required to improve the stability and handling characteristics of the vehicle, The damping of the longitudinal or direction-lateral oscillatory mode shall be governed by the re
18、quirements specified in Specification IMIL- F-8785. 3.1.1.1.2 Pilot Assist or Pilot Relief - The pilot assist or pilot relief category shall include those automatic control functions which simplify or ease the control of the flight path of the aircraft. These functions include but shall riot necessa
19、rily be limited to the following: (a) Attitude Hold (Pitch and Roll) (b) Heading Hold (c) Heading Select (d) Automatic Turn Coordination (e) Side Slip Limiting (f) Aititude Hold (g) Mach Hold (h) Return to Level (i) Control Stick Maneuvering Guidance - The guidance category shall include those contr
20、ol functions 3.1.1.1.3 which provide automatic flight path control in accordance with steering signals generated by guidance and control systems external to the flight control system. types of control functions: The category shall include the following (a) Enroute navigation (b) Rendevous and statio
21、n keeping (c) Terminal guidance for bomb delivery (d) Search and tracking for fire control (e) Automatic takeoff, approach and landing 6) Inertial Flight Path Control (g) Automatic Terrain Avoidance Choice of Components - Systems, subsystems and components shaii be 3.1.1.2 selected from the followin
22、g categories in the order listed, consistent with the applicable requirements and specifications: (a) In operational use, or under procurement for operational use, by the same service. 3 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-in operational
23、use, or under procurement for operational use, by other branches of the service. Modification of category a. Modification. of category b. Certified by a competent government agency for commercial aircraft use. Beveloped under contract to the services and approved in principle. Under development on c
24、oncurrent programs having more stringent requirements or scheduled for earlier completion. Designed and developed specifically for the requirements on hand, Complimco with the aime listed order of categories shall be a major criterion in the selection of an automatic flight control system subcontrac
25、tor. The proposed use of systems, subsystems and com- ponents from a category lower than category b shall be justified macle cluring the development phase which necessitate the use of systems, subsystems or components in a lower category must be approved by tho procuring activity. Requests for appro
26、val supported by studies showlng the necessity for the use of the system, subsystem or component shall be submitted prior to the appropriate design review, at which tfme the procuring activity shall decide upon approval or disapproval. and any changes 3.1.1 2.1 3.1.1.2.1.1 System Design - The AFCS s
27、hall be designed for minimum weight and volume Avoidance of Duplication - Automatic flight control systems, subsystems consistent with the designofthe aircraft for which it is intended. tuid components shall be so clSmma maximum of integration is accomplished, consistent with system reliability, ope
28、ration and safety between: (a) Those components providing the automatic control function and components or parts comprising or providing any other function of a weapon system, and b) The components providing the different functions of the automatic flight control system itself. Detailed requirements
29、 of each integration situation shall be as specified in the procurement document or in tho system or component specification, 3. I. 1.2.2 following requirements: Additional qesign Requirements - The AFCS shall be designed to meet the (a) The electronic control amplifier shall consist of separate ass
30、emblies for each major channel. b) Channels having higher reliability requirements than other channels shall be electrically isolated and have their own power supply, circuit breakers, etc, (c) A control panel switch shall be provided so that the AFCS can be isolated before ground power is applied o
31、r removed. 4 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-4 NIL-C-18244A NI m 7779906 0425225 b MIL- C- 18244AwEP) 3.1.1.2.3 Interchangeability - All assemblies having the same manufacturers part number shail be directly and completely interchange
32、able with respect to installation and performance without adjustment. 3.1.1.2.3.1 Reordered Equipment or Second Source Procurement - Where models or drawings of components of systems are furnished by the procuring activity on a contract to facilitate inter- changeable construction, or where procurem
33、ent is for equipment to provide interchangeable use with equipment previously procured, and the requirements for interchangeability contradict the current requirements of one or more MIL specifications, the contract requirements for interchangeability shall govern without additional approval by the
34、procuring activity. I 3.1.1.2.4 Repairability - No assembly or subassembly shall be encapsulated or permanently sealed without written approval of the procuring activity. access whenever necessary to repairable parts in components and/or assemblies. This requirement is established to insure 3.1.1.3
35、Functional Design Requirements 3.1.1.3.1 Conditions for Engagement - Unless the automatic flight control system and integrated portions of other systems are properly energized and synchronized, it shall not be. possible to engage the system or to switch from one functional category or mode of operat
36、ion to another. It shall be possible to engage the augmentation mode independently of any other function or mode of the automatic flight control system. No control transients, which exceed the limits of 3.1.1.4. 3, shall occur when switching from one functional mode of operation to another or when d
37、isengaging the system. Unless otherwise specified in the system specification, all control axes shail be engaged and disen- gaged simultaneously. Means shall be provided so that the pilot can visually determine the operation status of the system. not more than 90 seconds for fighter or attack type a
38、ircraft and not more than 3 minutes for other types of aircraft. 3.1.1.3.2 Warm-up - After the application of power, the warm-up time required shall be 3.1.1.3.3 Synchronization - The system design shall be such that, upon engagement, the aircrafts attitude or other control mode will be maintained,
39、or the aircraft will be displaced at a predetermined rate to a predetermined attitude as defined in the system specification covering the particular automatic flight control system. Synchronization indication, if required, shall be as specified in the system specification. The synchronization rate s
40、hall be such that no transients exceeding the limits of 3.1.1.4.3 shall occur due to system engagement or mode switching after the completion of any maneuver up to the maneuver limits of the aircraft. 3.1.1.3.4 Disengagement - Provisions shall be made for inflight disengagement and reengage- ment of
41、 the automatic flight control system. Disengagement shall be positive under any and all load conditions. Disengagement switches shall be normally closed and shall be located in accordance with the requirements d MIL-STD-203. A disengagement not initiated by the pilot shall be indicated by means whic
42、h shall be approved by the procuring activity. In the event that servo disengagement should result from action of the structural protective means, the circuitry shall provide for immediate re-engagement at the pilots discretion. Series Actuators - The series actuators shall, after deactivating, be p
43、ositively centered and capable of transmitting fuil control system load without creep. The rate of centering shall be such that no undesirable transients will be introduced. Unless a dual cross monitoring system, including dual separate actuators with a common output is used, series actuators having
44、 more than 40 percent primary control authority shall not be used. Overpower - With the automatic flight control system engaged and operating. it shall be possible to manually overpower or countermand the control action of the system on all axes. its design limits about all axes, subsequent to overp
45、owering or countermanding control system action shall not exceed the values specified in Sections 3.3 and 3.4 of Specification MIL-F-8585; in addition the maximum instantaneous forces shall not exceed 120 percent of the maximum steady force. 3.1.1.3.5 3.1.1.3.6 For fixed-wing aircraft the maximum st
46、eady forces required to maneuver the aircraft within 5 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-HIL-C-18244A MI W 4999906 0425226 B bIL-C-l8244A(REP) 3.1.1.3.7 Cockpit Control Motion- The control surface motion required to zccomplish augmentat
47、ion functions shll not be reflected rit the aircrafts cockpit control. In addition there shall b9 no random spurious stick motion aeeociated with any automatic flight control motle. control system trlm erro-lTzero. Such a means shall operate at a rate which does not significantly affect the transien
48、t performance of the automatic flight control system, Automatic trim $ha! be oparational during the guidance and pilot assist niodes only. Manual Trim - Powered manual trim shall be made inoperative when the automatic flight control system is eng%ged. The circuitry shall be arranged so as to mirlimi
49、ze the eficct of a failure in the automatic flight control system on the manual trim operation after the auto- matic flight control systerr is disengaged. Control Stick (or Wheel) Maneuvering - Where control stick maneuvering is 8 system requirement, poviclions stZl be made solhat the pilot shall have ftll capability to maneuver tho aircraft withn cortrol forces and maneuver limits specified in Specification M1L-F-8785 or the applicable system speciflcation. This
