NAVY MIL-L-23822 C-1971 LIQUID PROPELLANT ROCKET ENGINE LR64 FOR AQM-37A MISSILE TARGET SYSTEM《AQM-37A型导弹瞄准系统的LR64型火箭引擎液体推进剂》.pdf

《NAVY MIL-L-23822 C-1971 LIQUID PROPELLANT ROCKET ENGINE LR64 FOR AQM-37A MISSILE TARGET SYSTEM《AQM-37A型导弹瞄准系统的LR64型火箭引擎液体推进剂》.pdf》由会员分享，可在线阅读，更多相关《NAVY MIL-L-23822 C-1971 LIQUID PROPELLANT ROCKET ENGINE LR64 FOR AQM-37A MISSILE TARGET SYSTEM《AQM-37A型导弹瞄准系统的LR64型火箭引擎液体推进剂》.pdf（29页珍藏版）》请在麦多课文档分享上搜索。

1、MIL-L- 23822C (AS) 30 April 19 71 SUPERSEDING MIL-L- 2 3 822B( AS) 18 April 1969 MILITARY SPECIFICATION LIQUID PROPELLANT ROCKET ZNGINE LR64 FOR AQM-37A MISSILE TARGET SYSTEM This specification has been approved by the Naval Air Systems Command, Department of the Navy 1. SCOPE 1.1 Scope. This specif

2、ication establishes the requirements for the performance, manufacture, testing, acceptance and packaging of the Liquid Propellant Rocket Engine LR64. 2 APPLICABLE DOCUMENTS * 2.1 Government-furnished Documents. The following documents of the issue in effect on the date of invitation for bids or requ

3、est for pro- posal, form a part of this specification to the extent specified herein, SPECIFICATIONS Federal D-D-12 71 Diethylenetriamine, Technical (Activities outside the Federal Government may obtain copies of Federal Specifications and Standards as outlined under General Information in the index

4、 of Federal Specifications and Standards and at the prices indicated in the Index. The Index, which includes cumulative monthly supplements as issued, is for sale on a subscription basis by the Superintendent of Documents, U. S. Government Printing Office, Washington, D, C., 20492, ) THIS DOCUNENT C

5、ONTAINS 29 PAGES. . K , t FSC 1430 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. , .i . :! MIL -L - 2 3 8 2 2C( AS) (Single copies of this specification and other product specifications required by activities outside the Federal Government for bi

6、dding purposes are available without charge at the General Services Adminis- tration Regional Offices in Boston, New York, Atlanta, Chicago, Kansas City, Mo., Dallas, Denver, San Francisco, Los Angeles, Seattle, and Washington, D. C. 1 (Federal Government activities may obtain copies of Federal Spec

7、ifica- tions and Standards and the Index of Federal Specifications and Stand- ards from established distribution points in their agencies.) SPECIFICATIONS Mili tarv MIL-P-116 MIL- P- 7 2 54 MIL- P49 8 34 MIL-C-23661 MIL-E - 25 366 MIL-D- 256 04 MIL- P- 27401 Weapons Specification WS-4613 STANDAR ris

8、 Military MIL - STD- J29 MIL-STD-130 2 Preservation, Methods of Propellant, Nitric Acid Plates, Identification, Metal Foil, Adhesive Backed Cartridge, Impulse, Mk 45 Mod O Electric and Electronic Equipment and Systems, Guided Missile, Installation of, General Specification for Propellant, Uns -Dimet

9、hylhydrazine Propellant, Pressurizing Agent, Nitrogen Safety Requirements, Minimum, for Target Guided Missiles Marking for Shipment and Storage Identification Marking of U. S. Military Property Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-STANDARD

10、S (Contd) Military MIL-STD-292 Ballistic Nomenclature, Rocket Static Tests I MIL-STD-721 * MIL -STD- 8 89 DRAWINGS Naval Air Systems Command BuWeps Dwg 2522505 Definitions of Effectiveness, Terms for Reliability, Maintainability, Human Factors, and Safety Dis similiar Metals Rocket Engine LR64 for A

11、QM-37A Missile Target, Coordination Control Drawing * NAVAIR Dwg 589AS100 Fitting, Propellant Valve, Shear (When requesting any of the applicable documents, refer to both title and number, All requests should be made via the cognizant Government inspector, cations and drawings required by contractor

12、s in connection with specific procurement functions should be obtained upon application to the Command- ing Officer, Naval Supply Depot (Code 1051), 5801 Tabor Avenue, Phil- adelphia, Pennsylvania, 19120. All other documents should be obtained from the procuring activity or as directed by the contra

13、cting officer. ) Copies of this specification and other unclassified specifi- 2. ? Other documents. The following documents form a part of this specification to the extent specified herein. indicated the issue in effect on the date of invitation for bids shall apply, Unless otherwise National Bureau

14、 of Standards Handbook H-28 Screw Thread Standards for Federal Services National Advisory Committee on Aeronautics Report No. 1235 Standard Atmosphere (Application for copies should be addressed to the Superintendent of Documents, Government Printing Office, Washington, D. C. 20402. ) 3 Provided by

15、IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-L-23822C 14 m 797790b 0303857 7 m MIL-L-Z3882C( AS) 3 REQUIREMENTS 3.1 Description. The LR64 Liquid Propellant Rocket Engine, consists of a propulsion unit, a cartridge actuated multipurpose nitrogen valve, a c

16、artridge actuated oxidizer valve and shear fitting, a cartridge actuated fuel valve and shear fitting, and two nitrogen check valves, 3.1.1 Propulsion Unit. The propulsion unit consists of a booster thrust chamber, a sustainer thrust chamber, a propellant flow selector valve, a cartridge actuated bo

17、oster shut-off valve, a thrust mount, and miscellaneous fittings and tubing. 3.1.2 Associated Equipment. Associated with the LE64 Rocket Engine (but not a part of it) are a fuel tank, an oxidizer tank, a nitrogen tank, ia.pulse cartridges, burst diaphragms and holders, engine section structure, air

18、launch structure, lines, and fittings. 3.1.3 Operation. The LR64 Rocket Engine is prepared for flight by installation of impulse cartridges in the nitrogen, oxidizer, fuel and booster shut-off valves. the desired engine thrust level is selected on the propellant flow selector valve. The engine start

19、 sequence is initiated shortly after launch by action of the targets programmer. The nitrogen valve is opened and the stored gas flows through the nitrogen pressure regulator to pres- surize the propellant tanks. Upon actuation of the shear fittings in the prcFcllant valves, the pressurized propella

20、nts flow from the propellant tanks through the propellant flow selector valve into the thrust chambers. The hypergolic propellants ignite on contact. thrust chamber is shut off by energizing the impulse cartridge in the booster shut-off valve as a function of missile target velocity, The nitrogen ta

21、nk is charged to 3, O00 psig and Propellant flow to the booster 3.2 Preproduction sample. Unless otherwise specified in the contract or purchase order, each contractor who has not previously been approved as a qualified producer of the rocket engine shall manufacture a sample lot of 15 rocket engine

22、s (or a greater number when a design proposed in the opinion of the Government requires a Preflight Rating Test (PFRT) and Qualification Program) using the methods, processes and equipment proposed for production. The preproduction engines shall meet the requirements of 3. 3, 3.4 and 3. 5 of this sp

23、ecification when tested in 4 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-. “ MIL-L-23822C 24 W 7979706 0303b0 3 M - MIL-L- 2 3 82 2C (AS) 3. 2 (Contd) accordance with Section 4, at an activity designated by the procuring activity for the purpose

24、of demonstrating that the production equipment methods and criteria proposed are suitable and will yield rocket engines meeting the requirements of this specification. No production equipments or lot samples shall be delivered prior to the approval of the prepro- duction samples. 3.2.1 Qualified pro

25、ducer. In the event of interruption of production by a previously qualified producer, the procuring activity shall, unless otherwise specified in the contract or purchase order, require test of additional preproduction rocket engines in number as specified in the contract prior to the resumption of

26、production. Any production by the contractor prior to the approval of the preproduction lot shall be at the contractors risk. 3.3 General requirements. * 3.3.1 Construction and dimensions. The rocket engine shall be constructed in strict conformance to Naval Air Systems Command (NAVAIR) Drawings 252

27、2505 and 589AS100. or purchase order, all materials entering into the final assembly of the rocket engine shall conform strictly to the applicable specification. Materials which are not covered by specification or which are not speci- fically designated herein shall be of the best quality, of the li

28、ghtest prac- ticable weight consistent with strength and durability, and entirely suited to the purpose for which intended under all conditions of test and service operation, 3.3.2.1 Substitute materials. Recommendations concerning the use of a superior substitute for any part OP material specified

29、herein shall be accompanied by a description of the proposed substitute and the reasons eref fore, together with evidence to substantiate any claim as to its suitability. At the discretion of NAVAIR, test samples may be required to prove the suitability of the proposed substitute, 3. 3.2.2 Magnesium

30、. The use of magnesium shall require the specific approval of NAVAIR or its appointed agency. * 3.3.2 Materials. Unless otherwise specified in the contract 5 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-* MIL-L-23 82 2C( AS) 3.3.2. 3 Flammable mat

31、erials. Materials which will support combustion or which are capable of causing an explosion, except for the propellant and cartridges, shall not be used. 3.3. 2.4 Toxic materials. Materials, except the propellant, which may produce harmful toxic or corrosive effects under condi- tions encountered i

32、n the Naval Service shall not be used. 3.3. 2. 5 be governed by the requirements of MIL-STD-889. 3.3.3 Moisture, fungus and corrosion, The rocket engine shall be moisture, fungus and corrosion resistant as required by 3.3.4 Protective coatings and surface treatments. The pro- tective coatings and su

33、rface treatments used for the protection of the rocket engine shall be suitable for the propellants and gases used and for the environmental conditions to which the rocket engine will be subjected, satisfactory both for corrosion and stress corrosion cracking behavior. Dissimilar metals. The use of

34、dissimilar metals shall MIL -E - 2 5 366. Materials and protective treatments used shall be 3.3. 5 Marking. Marking shall conform to the requirements 3.3. 5.1 Nameplates. Nameplates shall conform to the require- ments of MIL-P-19834, Type I, 3.3. 5. 2 Serial numbers, a serial number which will be as

35、signed by the Government Inspector upon request, or as specified in the contract or purchase order. of MIL-STD-13 O. Each rocket engine assembly shall bear 3.3.6 Threads. Unless otherwise specified, all threads shall be in accordance with the National Bureau of Standards Handbook H-28. The class and

36、 fit for threads shall be as specified on applicable drawiqgs, and the NOT-GO gaging practice shall be as set forth in the aforementioned Handbook H-28 and the Supplement thereto., 3.3.7 Interchangeability. The following parts of the rocket engine shall be interchangeable as defined in MIL-STD-721:

37、6 I. Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-L-23822C 14 m 7777906 0303862 7 U I MIIJ-L-23822C(RSj 3.3. 7 (Contd) Booster shutoff valve Multipurpose nitrogen valve Nitrogen check valve - oxidizer system Nitrogen check valve - fuel system

38、Oxidizer valve riririri MCU rl o MCU rl o CUCUCU MCU rl o MMMrr) rlrlrlrl 9 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-L- 23 822C( AS) niL-L-23822C 14 9 9777706 0303865 2 =_ TABLE III n G O O O c- W n G O O O Ln M n W G O O O c- v n -P k O O

39、 O t- W n -P k O O O In M W n -P k O In 0 8 W u ou .t+ M O WQ 3 wu v)v)LnD MMMM cucucucu 4-3MLn MMMM cucucucu mo c-Cu rlcurld cucucucu v)v)“ MMcu cuwcu cucucucu cucucucu LnbM cucu0 rlrlrl wm3 cucu0 drlrl %“o rirlrl rlI-lcuLn cucucucu 4-34-3 LnLnLnc- LnnLnlA cucucucu F9 Fri MLncu o O“ rlrl Inc-In 3 C

40、I“ cocucu rlcum rlrl Fria F9 Fr O Ln3 Ln or10 Ln3 . vlMMcu MMcucu cu ow Lnw c- 33 M O Lnf orlo nn3 . . . . LnlnLnul O000 al k PI 8 *p cucucucu rlrldrl ririrlrl Mcu rl o MMMM Mcu 40 Mcu rl o Mcu rl 10 cucucucu Provided by IHSNot for ResaleNo reproduction or networking permitted without license from I

41、HS-,-,-MIL-L- 23 8 22C (AS) 3.4.4 Ablation. The chamber or throat linings of the pro- pulsion unit Rhall not ablate so as to emit solid particles exceeding those efined in WS-4613. 3.4.5 Smoke emission. The rocket engine shall not emit smoke or flame from any part of the engine other than from the n

42、ozzle exits. 3.4.6 Thrust build-up. The time required to increase the rocket engine thrust from activation of the propellant feed line cart- ridge operated valves to 90 per cent (%) of rated boost thrust shall be in accordance with Figure 1. 3.4, 7 Thrust tail-off, The thrust decay time interval fro

43、m cut-off of the rocket engine booster chamber thrust to 570 of the rated booster chamber thrust shall be not greater than one and one- half (i-%) seconds when operating to the requirements of Table I. 3.4. 8 Thrust variation. The rocket engine thrust variation from any swrce at either booster or su

44、stainer thrust level shall be as specified in Table I when measured in accordance with Figure 2. 3.4.9 Operating range. 3.4.9.1 Temperature range. The rocket engine shall start, operate and stop over the temperature range from minus (-) 66 * F. to plus (+) 140 F. 3.4.9. 2 Altitude range. The rocket

45、engine shall start, operate and stop over the altitude range from sea leyel to 100, O00 feet. 3.4.10 Cartridges. The rocket engine shall be started and the booster chamber thrust shall be stopped by the activation of im- pulse cartridges Mk 45 Mod O conforming to MIL-C-23661 which will be Government

46、 -furnished equipment. 3.4.11 Leakage, The rocket engine shall not leak pro- -pellants when tested at a static pressure of 620 psig minimum. 3.5 Environmental requirements. 11 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-* MIL-L-23822C LLI m 77779

47、06 0303867 b m - - 3. 5.1 Static exposure. The rocket engine shall operate after static exposure at a temperature of +I40 O F & 3 o F when supplied with propellants at a temperature of +140 O F I 3 F, and after static exposure at a temperature of -65 O F f 3 o F when supplied with propellants at a t

48、emperature of -65 O F I3 F. engine shall meet the performance requirements of 3.4 after being subjected to the static exposure test of 4.4.3.1. 3.5.2 Temperature cycling. The rocket engine shall meet the requirements of 3.4 after being subjected to the temperature cycling test of 4.4. 3.2. The rocke

49、t 3.5. 3 V ib r at ion. 3. 5. 3.1 Vibration endurance. The rocket engine shall meet the requirements of 3.4 after being tested for a minimum of nine hours as specified in 4.4. 3. 3. 2. 3.5. 3. 2 Vibration endurance life test. The rocket engine shall be tested as specified in 4.4. 3. 3. 3. 3.6 Reliability. The probability of successful operation of the rocket engine shall be not l