NAVY MIL-L-22589 D-1991 LAUNCHING SYSTEM NOSE GEAR TYPE AIRCRAFT《飞机前起落架型发射系统 飞机噪音》.pdf

1、- MIL-L-22589D 17 W 9999706 O488079 b W Benef i ci al comments (recommendations, addi t ions, del et ions) and any pert i nent data which may be of use in improving this document should be addressed to: Commanding Officer, Naval Air Engineering Center, Systems Engineering and Standardization Departm

2、ent (SESD), Code 53, Lakehurst, NJ 08733-5100, by using the Standardization Document Improvement Proposal (DD Form 1426) appearing at the end of this doc ument or by letter. !INCH-POUND! MIL-L-22589D(AS) 10 September 1991 SUPERSEDING 8 August 1979 MIL-L-22589C(AS) i- MILITARY SPECIFICATION LAUNCHING

3、 SYSTEM, NOSE GEAR TYPE, AIRCRAFT This specification is 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 .l. SCOPE 1.1 Scope. This specification covers the design, development, constructio

4、n, analysis, test and documentation requirements for aircraft nose gear launching systems on carrier-type aircraft for which detail specifications or other pertinent contractual documents require nose gear launching systems on aircraft. 2. APPLICABLE DOCUMENTS 2.1 Government documents. * 2.1.1 Spe c

5、ifications and standards. The following specifications and standards form a part of this specification to the extent specified herein. Unless otherwise specified, the issues of these documents are those listed in the issue of the Department of Defense Index of Specifications and Standards (DODISS) a

6、nd supplement thereto, cited in the solicitation (see 6.2) SPECIFICATIONS Mi 1 i tary MIL-D-8708 Demonstration Requirements for Airplanes MIL-A-8860 Airplane Strength and Rigidity; General Specification for / AMSC NIA FSC 1720 DISTRIBUTION STATEMENT A. Approved for pub1 ic release; distribution is u

7、n1 imi ted, Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-L-22589D 17 9979906 O488080 2 MIL-L-22589D(AS) SPECIFICATIONS (Contd) MIL-A-8863 MI L-P-15024 MIL-T-81259 Tie-down, Airframe Design, Requirements for MIL-B-85110 Bar, Repeatable Release

8、Holdback, Aircraft Launching Airplane Strength and Rigidity Ground Loads for Navy Acquired Airplanes Plates, Tags and Bands for Identification of Equipment General Design Requirements for STAN DARDS Mi 1 i tary MI L-STD-130 Identification Marking of U.S. Military Property MIL-STD-203 Aircrew Station

9、 Controls and Displays; Assignment, Location and Actuation of, for Fixed Wing Aircraft MIL-STD-411 Aircrew Station Signals MI L-STD-889 Dissimilar Metals MI L-STD-970 Standards and Specifications, Order of Precedence for the Selection of (Unless otherwise indicated, copies of federal and military sp

10、ecifications, and standards are available from the Standardization Documents Order Desk, Building 4D, 700 Robbins Avenue, Philadelphia, PA 19111-5094.) 2.1.2 Other Government documents, drawinus, and publications, The following other Government documents, drawings, and publications form a part of th

11、is document to the extent specified herein. cited in the solicitation. Unless otherwise specified, the issues are those DRAWINGS Naval Air Enaineering Center (NAVAIRENGCEN) 504633 607770 Design Requirements, Catapulting Arrangements, Nose Gear Catapulting Arrangement Drawing Requirements for Type La

12、unch (Copies are available from the Naval Air Technical Services Facility (NATSF) (Code 312), 700 Robbins Avenue, Philadelphia, PA 19111-5097.) REPORTS Naval Air Enuineerinq Center CNAVAIRENGCEN) NAEC-ENG-7481 Numerical Index (Drawing List) for Mk 2 Nose Gear Launch Equipment 2 Provided by IHSNot fo

13、r ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-L-22589D 17 W 999990b 048808L 4 W , - - MIL-L-22589D(AS) 4 -2 PUBLICATIONS Naval Air Systems Command AD-1 350 Engineering Drawings and Associated Data (Copies are available from the Standardization Section, (Code 51122E

14、1, Washington, DC 20361-51 10.) (Copies of documents required by contractors in connection with specific procurement functions should be obtained from the procuring activity or as directed by the contracting officer.) * 2.3 Order of precedence. document and the references cited herein (except for re

15、lated associated details specifications), the text of this document takes precedence. document, however, supersedes applicable laws and regulations unless a specific exemption has been obtained. In the event of a conflict between the text of this Nothing in this * 2.4 Streamlininu. This document has

16、 been streamlined. Appendix A to MIL-L-22589(AS) lists those documents required for acquisition and is a mandatory part of MIL-L-22589(AS). All other documents, referenced through tiering, may be used as guidance and information to supplement MIL-L-22589(AS). 3. REQUIREMENTS 3.1 Materials. Materials

17、 shall conform to applicable specifications and shall be as specified herein and on applicable drawings. Materials which are not covered by specifications, or which are not specifically described herein, shall be of the best quality, of the lightest practicable weight, and suitable for the purpose i

18、 ntended. * 3.1.1 Protective treatment. Materials exposed to environmental conditions during service use shall be protected against deterioration in a manner that will in no way prevent compliance with the performance requirements of this specification. dissimilar materials, as defined in MIL-STD-88

19、9, shall not be used in contact with each other. The protective system shall be in accordance with the aircraft detail spec i fi cat i on. * 3.2 Selection of specifications and standards. Specifications and standards for necessary commodities and services not specified herein shall be selected in ac

20、cordance with MIL-STD-970 or as specified in the detail specification. Parts which are not covered by specifications or military standards, or which are not specifically described herein, shall be completely described on manufacturers drawings submitted for approval (see 3.4). Unless suitably protec

21、ted against electrolytic corrosion, 3.2.1 Sta ndard parts. MS and AN standard parts shall be used where they suit the purpose. They shall be identified on the drawings by their part numbers. 3 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-L-225

22、8D 17 = 0b 0488082 b W 3.3 Desiun, construction and installation. The design, construction and installation of the launching system shall permit satisfactory operation of the aircraft with all specified stores with the catapults specified in the detail specification for the aircraft. this specificat

23、ion and applicable drawings shall be permitted unless specifically authorized in writing by NAVAIR. No deviation from any part of the requirements of 3.3.1 Launchinu system. The aircraft nose gear launch system shall meet the requirements of this specification and any amendments thereto specified in

24、 the detail specification for the aircraft. The launching system shall consist of a launch bar installation, cockpit controls and components, and a holdback and release installation. The aircraft launch system shall conform to the design requirements of NAVAIRENGCEN Drawing 607770 while loads and st

25、rengths must meet the requirements of MIL-A-8860 and MIL-A-8863. 3.3.1.1 Mk 2 compatibility. The aircraft nose gear launch system shall be compatible with the Mk 2 Nose Gear Launch System as shown on the drawings listed in the report NAEC-ENG-7481, 3.3.1.2 Hookup operation. The launching system shal

26、l be designed to preclude the need for manual assistance by the deck crew during tracking, hookup, tensioning, suspend, and abort operations. * 3.3.1.3 Enaagement speed. The launching system shall be designed to permit hookup with the nose gear launch deck hardware at a maximum speed, which shall be

27、 the smaller of: (a) Four knots, or (b) That speed which will cause a maximum load in the holdback bar, during buffing, equal to the minimum release load specified in MIL-A-8863. can be obtained from Naval Air Engineering Center (NAEC) Buffer load vs displacement curves for Mk 2 the system * 3.3.1.4

28、 Launchinu criteria. The launching system shall be such that the a rcraft will be capable of being launched satisfactorily from any applicable catapult, through the full range of launching weights and critical center of gravity positions specified in MIL-A-8860 under the following conditions or as s

29、pecified in the aircraft detail specification: (a) The main gear off-center location at the time of holdback release shall be the lesser of (also see Figure 1). (1) 24 inches from either side of the centerline of the catapult or, (2) The final main gear location that results when the aircraft initia

30、lly enters the wye-section of the catapult at a maximum angle of 15“ (Between Aircraft and Catapult Centerline) with the Launch Bar aligned with the longitudinal axis of the aircraft . 4 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-x: i I MIL-L-22

31、589D(AS) 3.3.1.5 Clearance * 3.3.1.5.1 Minimum clearance. The aircraft and its specified external stores shall be designed to clear the catapult tow fitting shuttle spreader, catapult deck hardware, and the holdback bar from the beginning of tracking at the entry wye to the end of the launching run

32、for the following conditions simultaneously: (a The most critical tire and strut flat: the remaining struts and tires in accordance with MIL-A-8863 and under the most critical dynamic 1 oad . (b) The aircraft and store deflection corresponding to (a above. Note: For clearance purposes, it will be as

33、sumed that the holdback bar (see 3.3.4.2.1) has no recoil and will come to rest on top of the nose gear launch deck hardware (see 3.3.11) after release. * 3.3.1.5.2 Launch bar clearance. The launch bar may contact the deck, the catapult deck hardware and the catapult shuttle spreader as required dur

34、ing normal tracking, hookup, tensioning, release, power run, suspend or abort procedures (see 3.3.2.1, 3.3.2.2.1 through 3.3.2.2.4). The launch bar shall not strike the flight deck after it has moved out of the catapult tow fitting at the end of the power run. The launch bar installation design shal

35、l not restrict 360“ nose gear swiveling with the launch bar in the up or retracted position for deck handling with a minimum clearance of 1 inch between the launch bar and all aircraft structure, stores, and attached ground handling equipment for all strut and tire conditions. * 3.3.1.5.3 Nose wheel

36、 tires and structure. The nose gear tires shall clear the catapult deck hardware and the catapult tow fitting in the maximum flat tire condition. There shall be a minimum of 118 inch clearance between the aircraft nose gear structure and catapult deck hardware and the catapult shuttle spreader in th

37、e maximum flat tire condition during all phases of catapult operations. 3.3.1.5.4 Holdback bar. Sufficient clearance shall be provided to permit the holdback bar to be attached readily to the aircraft holdback fitting with the most critical store loading. 3.3.1.6 Dvnamic analvsis. A dynamic analysis

38、 shall be made to show the interaction of the launch bar and the catapult tow fitting for the condition specified in 3.3.1.4. conditions of launch bar loadings as approved by the procuring activity: The analysis shall show the following for critical (a Resisting moments and side reactions developed

39、at the catapult tow fitting to react launch bar torsional and bending loads. (b) Attitude of the aircraft. (c) Launch bar axial load. (d) Maximum misalignment between the launch bar and the catapult shuttle spreader slot. 5 Provided by IHSNot for ResaleNo reproduction or networking permitted without

40、 license from IHS-,-,-MIL-L-22589D 17 m 9999906 O488084 T m c MIL-L-22589D(AS) * 3.3.2 Launch bar installation. The launch bar installation consists of the launch bar; launch bar extension, holddown and retraction device; launch bar uplock; launch bar control circuit and such auxiliary equipment as

41、is necessary to functionally integrate it into the launching system. wheel steering must be inoperative when entering, tracking and hooking up to the catapult shuttle spreader except that the design logic shall permit the pilot to select nose wheel steering upon command. Nose wheel centering and nos

42、e * 3.3.2.1 Launch bar. The launch bar shall provide the means of steering the nose gear during tracking and shall couple the aircraft to the catapult during the power run. The design of the launch bar shall conform to the requirements of.NAEC Drawing 607770 or as approved by NAVAIRENGCEN. NAVAIRENG

43、CEN personnel should be contacted to ascertain a proper design for optimum interface of launch bar and spreader 3.3.2.2 Launch bar holddown and retraction device * 3.3.2.2.1 Holddown. The holddown device shall provide and.maintain a positive downward force on the launch bar to keep the launch bar in

44、 contact with the guide track during tracking and buffing. The force shall be maintained until the tensioning operation is completed. result in a vertical deck contact load of 30 to 50 pounds at the end of the launch bar. Application of intermediate or maximum takeoff power shall not cause mispositi

45、oning or disengagement of the launch bar from the catapult shuttle spreader. The effect of this force plus gravity shall * 3.3.2.2.2 Automatic retraction. When the end of the power run has been reached and the launch bar has been moved out of the catapult shuttle spreader, the launch bar shall autom

46、atically retract rapidly without striking the flight deck and shall effect locking in the up position. retraction. The stowed position of the launch bar when the nose gear is fully retracted need not be the same as the up or retracted position. This shall not be dependent on landing gear * 3.3.2.2.3

47、 Emergencv retraction. Independent means, separate from the automatic retraction system, shall be provided for emergency retraction and locking of the launch bar in the up position should the automatic retraction system fail, emergency retraction system shall be automatic. The 3.3.2.2.4 Suspend or a

48、bort retraction. The retraction device shall allow retraction of the launch bar by the pilot from its on-the-deck position to the up position to permit taxiing or removal of the aircraft from the launching area without damage to the launch system and without deck crewman assistance. In the up positi

49、on, the bar shall clear deck obstructions up to 8 inches in height. Compliance with this requirement shall not require a change in aircraft power or any specific power setting and shall not result in damage to the aircraft launching system or to the deck hardware. 6 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-L-22589D 17 m 9799906 0488085 L E 3.3.2.2.5 Damaae. If retraction is initiated while the l