1、 - - K -3?i-(5 - - i - (5- is . I i . MTT 1-J-8 Cifi7AlAS) 5 Jauuary 1970 Sup er seding of 2 November 1953 I-. i UL . .- MIL-J-8667(Aer) 5 =. MILITARY SP E CE ICATION JET ASSISTED TAKE-OFF SYSTEMS-DESIGN AND INSTALLATION OF; IN NAVAL AIRCRAFT This specification has been approved by the Naval Air Sys
2、tems Command, Department of the Navy 1. SCOPE 1.1 installation, test and data requirements for Jet Assisted Take-off Systems for Naval aircraft. This specification establishes the requirements for the design, 1.2 - Classification. JATO unit systems covered by this specification shall be of the follo
3、wing types: Type I - 100G pound thhiust unit installation Type II - 45GO pound thrust unit instaliation 2. APPLICABLE DOCUMENTS 2.1 - Government docxments normallj iurnished. _ The following documents of the iss.ie in effect on dxce of iwitation for bids, or request for proposal, form a phr! o: thee
4、peci5cation to the extmr specified herein. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Specifications (Cont) Militg MIL-A-8591 MIL-D- 8706 MIL-D- 8 7 O 8 MIL- F-8785 MIL-A -88 60 Thru MIL-A-88 7 O MIL-R-18136 MIL-H- 216 6 O MIL-H-21722 MIL-P-2401
5、4 Other Departmental Documents SD-24 4 - Standards MIL- STD -143 MIL-STD- 7 04 MILSTD-885 Airborne Stores and Associated Suspension Equipment, General Design Criteria for Contract Design Data Requirements for Aircraft Demonstration of Piloted Airplanes Flying Qualities of Piloted Airplanes Airplane
6、Strength and Rigidity Research and Engineering Repwt, For- mat and General Requirements Hooks, Thrust, JATO 1000 Pounds Nominal Thrust Hooks, Thrust and Stabilizing, JATO 4500 Pounds Nominal Thrust Preclusion of hazards from Electro- magnetic radiation to ordnance General Specification for the Desig
7、n and Construction of Naval Aircraft Specifications and Standards, Order of Precedence for the Selection of Electric Power, Aircraft, Characteristics and Utilization of Dissimilar Metais (When requesting appilcahe aocumects. refer to both title and number. Copies of unclassified docw:ent,s r-a) e ob
8、tained from tiit CommandiEg Officer, Naval Publicatips and Forris Ce:.- Y 53L: Ilabur -Avenue. nhladelphia, Pennsylvania 19IZU. ReqKes.5 io1 . q Lb CASS ed ciocunis-nts should be 2 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,- MIL-J-Bbh7A 28 77777
9、0b OL87418 7 W addrcssed to the Naval Publications and Forms Center, via thc cognizant GOVerMient representative. ) Drawings NAF GO3894 Hook, Thrust, JATO, Retractable, 4500 Pound Thrust NAF 603922 Hook, S.tabiliz standard i- =-.=-. ri ? Provided by IHSNot for ResaleNo reproduction or networking per
10、mitted without license from IHS-,-,-parts available, commercial parts may be used provided they conform to all requirements of this speciication. 3.5 Design. The design of the JATO Systems shall be such as to assure satisfactory instaliation, firing and jettisoning of the JATO units, 3.5.1 Aerodynam
11、 ic considerations. 3.5.1.1 JATO weight and thrust. The weight of the JATO installation acting separately and in combination with the thrust of the JATO units shall not result in an inability of the aircraft to comply with the requirements of MIL-D-8708 and MIL-F-8785, 3.5.1.2 Center of gravity effe
12、ctive movement. The thrust moment about the mass center of gravity shall not result in movement of the center of gravity beyond the allowable limits. The effective center of gravity movement shall be determined by the following equation, Mt X= wA - t where x = effective center of gravity movement Mt
13、 = thrust moment about the mass center of gravity based on the thrust of the JATO unit when at a temperature of 140“ F W = aircraft gross weight A V = vertical component of the thrust of the JATO units when at t a temperature of 140“ F. 3.5.1.3 Asymmetric thrustL The JATO instdlation shall be design
14、ed to minimize the effects of asymmetric thrust due to JATO unit misfire (no ignition or delayed ignition) or blowoff (safety diaphragm operation). 3.5.1.4 Suspension system drag. The JATO installation shall be as aerodynamically clean as is feasible. Type II JATO installations shall be designed to
15、take full advantage of the retractable feature of the JATO hooks. 3.5.2 Blast cone clearance. The JATO units shall be installed so as to provide cone clearance as shown in figure 1. 3.5.3 Structural aeslgn. Those portions of the JATO System and aircraft structure which are subjected to loads resulti
16、ng from the installation and operation of the JATO units shall be designed to withstand the loads as specified herein. The above structure shall also Se adequate for flight, take-off, 5 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-6 P E El X E z O
17、 _-I- % . Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-landing, and handling, consistent with the strength requirements of the airplane, when carrying the maximum number of loaded JATO units, as specified in the airplane detail specification and S
18、pocifications MIL-A-8860 through MIT,-A-8870 and 81-21, 58 applicable. 3,5.3.1 Definition of terms. 3.5.3.1.1 Normal rated thrust. Normal rated thrust of a JATO unit is the thrust of the unit when at a temperature of 60 degrees Fahrenheit, 3.5.3.1.2 Design limit thrust load. The design limit thrust
19、load shall equal two times the normal rated thrust of the JATO unit, acting along the center line of the JATO unit nozzle throat. 3.5.3.1.3 JATO unit weight, Wj. The weight in pounds of a fully loaded JATO unit. 3.5.3.2 Magnitude and direction of design limit loads. 3.5.3.2.1 Landplane installations
20、. The design limit thrust load shall be considered to be acting separately and in any combination with the following loads: a downward load equal to 3Wj, an upward load equal to 1.5Wj, and a lateral load to the right or to the left equal to LOWj. For JATO installations on aircraft designed for catap
21、ulting, in addition to the above loads, a load of 5.5W. shall be considered to act aft on the unit, with or without thrust load. J 3.5.3.3 Location of loads. The thrust load component which is parallel to a line through the centers of the JATO unit mounting lugs shall be applied to the thrust hook.
22、The remaining compments of the design limit loads shall be applied to the thrust and stabilizing hooks in the proportions determined by the geometry of the JATO installation. 3.5.3.4 Factors of safety. The minimum yield and ultimate factors of s (b) The optimum techniques for firing JATOS for optimu
23、m take-off performance; ignition) ; (c) The effect of JATO unit misfire (non-ignition or delayed (d) That the rocket motor jet blast causes no structural fatigue or overtemperature, or any other unacceptable adverse conditions resulting from the jet blast, to any part of the aircraft. During the abo
24、ve tests, flight procedures shall be established by the contractor which will insure satisfactory control of the aircraft during JATO unit misfire. 5. PREPAATIOI; FOR DEUVERY 5.1 This section not applicable to this specification. Provided by IHSNot for ResaleNo reproduction or networking permitted w
25、ithout license from IHS-,-,-6. NOTES 6.1 intended use. This specification is intended for use in the design, installation and testing of JATO systems for naval aircraft. The fol- lowing specific paragraphs of this specification apply as noted: -. (a) Design and installation. Paragraphs 1 through 3.
26、(b) Inspection. Paragraphs 4.1 and 4.2. (c) Testing. Paragraphs 4.3, 4.4, 4.5, 4.6 and 4.7. (d) Data requirements. Drawings and data shall be submitted in accordance with MIL-D-8706A, and the requirements of paragraphs 3.3.6.8, 3.4 and 4.3 herein. A letter report of highlights during the tests shall
27、 be submitted monthly to the procuring activity. A detailed summary report, in accordance with MIL-R-l8136C, shall be submitted for the structural test (para 4.3). -. Preparing Activity Navy - AS Project No. 2845-NO18 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-
