SAE AS 8581-2000 Engine Rocket Solid Propellant 5 Second Duration 4500 Pounds Thrust《发动机 5秒固体推进剂4500英镑推力火箭》.pdf

1、SAE-AS8581ADOPTION NOTICESAE-AS8581, “ENGINE; ROCKET, SOLID PROPELLANT 5 SECOND DURATION,4500 POUNDS THRUST“, was adopted on 26-MAY-00 for use by theDepartment of Defense (DoD). Proposed changes by DoDactivities must be submitted to the DoD Adopting Activity:Commander, Naval Air Warfare Center, Airc

2、raft Division, Code414100B120-3, Highway 547, Lakehurst, NJ 08733-5100. Copies ofthis document may be purchased from the Society of AutomotiveEngineers 400 Commonwealth Drive Warrendale, Pennsylvania, UnitedStates, 15096-0001. http:/www.sae.org/_Custodians: Adopting Activity:Navy - ASNavy - ASFSC 28

3、45DISTRIBUTION STATEMENT A: Approved for public release; distributionis unlimited.SAE Technical Standards Board Rules provide that: “This report is published by SAE to advance the state of technical and engineering sciences. The use of this report is entirelyvoluntary, and its applicability and suit

4、ability for any particular use, including any patent infringement arising therefrom, is the sole responsibility of the user.”SAE reviews each technical report at least every five years at which time it may be reaffirmed, revised, or cancelled. SAE invites your written comments and suggestions.Copyri

5、ght 2000 Society of Automotive Engineers, Inc.All rights reserved. Printed in U.S.A.TO PLACE A DOCUMENT ORDER: (724) 776-4970 FAX: (724) 776-0790SAE WEB ADDRESS: http:/www.sae.org400 Commonwealth Drive, Warrendale, PA 15096-0001AEROSPACE STANDARDAS8581Issued 2000-03Engine; Rocket, Solid Propellant5

6、Second Duration, 4500 Pounds ThrustFSC 2845NOTICEThis document has been taken directly from U.S. Military Specification MIL-E-8581A(AS) and contains only minor editorial and format changes required to bring it into conformance with the publishing requirements of SAE technical standards. The initial

7、release of this document is intended to replace MIL-E-8581A(AS). Any part numbers established by the original specification remain unchanged.The original Military Specification was adopted as an SAE standard under the provisions of the SAE Technical Standards Board (TSB) Rules and Regulations (TSB 0

8、01) pertaining to accelerated adoption of government specifications and standards. TSB rules provide for (a) the publication of portions of unrevised government specifications and standards without consensus voting at the SAE Committee level, and (b) the use of the existing government specification

9、or standard format.Under Department of Defense policies and procedures, any qualification requirements and associated qualified products lists are mandatory for DOD contracts. Any requirement relating to qualified products lists (QPLs) has not been adopted by SAE and is not part of this SAE technica

10、l document.SAE AS8581 - 2 -1. SCOPE:1.1 This specification established the requirements for a 5 second duration, 4500 pound thrust (when determined at 60F) solid propellant rocket engine hereinafter specified as 5 S-4500.1.2 Classification:The 5 S-4500 rocket engine is a moderate duration, low-thrus

11、t, self-contained power plant employing a solid propellant. The engine is designed specifically for jet assist take-off (JATO) of aircraft, and to deliver a nominal thrust of 4500 pounds for 5 seconds duration at 60F and sea level. The engine contains aircraft attachment fittings and an ignition sys

12、tem.2. APPLICABLE DOCUMENTS:2.1 Government documents:2.1.1 Specifications, standards and handbooks: Unless otherwise specified, the following specifications, standards and handbooks of the issue listed in the issue of the Department of Defense Index of Specifications and Standards (DoDISS) specified

13、 in the solicitation form a part of this specification to the extent specified herein.SPECIFICATIONSMILITARYMIL-P-116 Preservation, Methods ofDoD-D-1000 Drawings, Engineering and Associated ListMIL-S-5002 Surface Treatments and Inorganic Coatings for Metal Surfaces of Weapons SystemsMIL-D-5480 Data,

14、 Engineering and Technical, Reproduction Requirements forMIL-I-6867 Magnetic Inspection UnitsMIL-I-6868 Inspection Process, Magnetic ParticleMIL-I-6870 Inspection Program Requirements, Non-Destructive for Aircraft and Missile Materials and PartsMIL-F-7179 Finishes and Coatings, Protection of Aerospa

15、ce Weapon Systems, Structures and Parts, General Specification ForMIL-J-8667 Jet Assisted Take-Off Systems - Design and Installation of, in Naval AircraftMIL-C-16173 Corrosion Prevention Compound, Solvent Cutback, Cold ApplicationMIL-S-28786 Switches, Preparation For Delivery OfSAE AS8581 - 3 -2.1.1

16、 (Continued):STANDARDSMILITARYDoD-STD-100 Engineering Drawing PracticesMIL-STD-105 Sampling Procedures and Tables for Inspection by AttributesMIL-STD-109 Quality Assurance Terms and DefinitionsMIL-STD-129 Marking for Shipment and StorageMIL-STD-320 Fuse Explosive Component Terminology, Dimensions an

17、d MaterialsMIL-STD-410 Non-Destructive Testing Personnel Qualification and Certification (Eddy Current, Liquid Penetrant, Magnetic Particle, Radiographic and Ultrasonic)MIL-STD-480 Configuration Control - Engineering Changes, Deviations and WaiversMIL-STD-481 Configuration Control - Engineering Chan

18、ges, Deviations and Waivers (Short Form)MIL-STD-810 Environmental Test MethodsMIL-STD-889 Dissimilar MetalsMIL-STD-1595 Qualification of Aircraft, Missile and Aerospace Fusion WeldersCopies of specifications, standards, handbooks, drawings and publications required by manufacturers in connection wit

19、h specific acquisition functions should be obtained from the contracting activity or as directed by the contracting officer.2.1.2 Other government documents, drawings, and publications: The following other Government documents, drawings, and publications form a part of this specifications to the ext

20、ent specified herein.DoD ManualDoD 4145.26M Safety Manual for Ammunition, Explosives and Related Dangerous MaterialDoD 5154.4S DoD Ammunition and Explosives Safety StandardsNaval Air Systems DrawingsNAF Dwg. 502706 JATO Unit, 30 Canted Nozzle, 4500 lb. Thrust Envelope DimensionsNaval Sea Publication

21、sNAVSEA S9086-AA-STM-000 Naval Ships Technical Manual Chapter 700OP-5 Ammunition and Explosives AshoreFEDERAL TEST METHOD 151 Test Methods MetalsSAE AS8581 - 4 -2.1.3 Order of precedence: When the requirements of the contract, this military specification, or applicable subsidiary specifications are

22、in conflict, the following precedence shall apply:2.1.3.1 Contract: The contract shall have precedence over any specification.2.1.3.2 Military Specification: This specification shall have precedence over all applicable subsidiary specifications. Any deviations from this specification, or from subsid

23、iary specifications where applicable, shall be specifically approved by the procuring agency.2.1.3.3 Model Specification: A specification shall be prepared by the contractor in which the particular characteristics of his rocket engine model shall be defined. The model specification shall contain inf

24、ormation which is supplementary to the military specification and shall state specifically any deviations from the requirements of the latter. The model specification shall be incorporated as a part of the procurement contract.3. REQUIREMENTS:3.1 Engine performance characteristics:The performance of

25、 the rocket engine shall be reliable and uniform throughout the storage and operating limits specified herein. Performance curves shown in the attached figures shall constitute the performance part of this specification. Variation in average thrust, thrust duration and total impulse shall be kept at

26、 a minimum by the best methods of quality and process control. The performance ratings of the rocket engine shall be as shown in Figures 1, 2 and 3.3.1.1 Operating temperature range: The engine performance shall be reliable and consistent throughout the temperature range of -30F to +140F. To demonst

27、rate this performance requirement, test firings shall be made at -40F and +150F, respectively.3.1.2 Duration of thrust variation: Variation in duration of thrust of the rocket engine fired at any temperature within the operating temperature shall not exceed that specified in Figure 1.3.1.2.1 Thrust

28、duration measurement: Thrust duration shall be measured on the thrust-time curve (see Figure 4, sample) between the point at which the tangent to the initial rise of the curve crosses the zero thrust ordinate and the point at which the tangent to the final decline of the curve crosses the zero thrus

29、t ordinate.3.1.3 Average thrust variation: Variation of the average thrust of the rocket engine fired at sea level and at any temperature within the firing temperature range shall not exceed that specified in Figure 2.3.1.3.1 Average thrust: Average thrust shall be obtained by dividing the total imp

30、ulse (3.1.3.2) by the duration of thrust (3.1.2.1).SAE AS8581 - 5 -3.1.3.2 Total impulse: Total impulse shall be determined by integration of the thrust-time curve from the point where a line tangent to the initial rise of the thrust curve intersects the line of zero thrust, to the point where a lin

31、e tangent to the final decline of the thrust curve intersects the line of zero thrust.3.1.4 Total impulse variation: Variations in total impulse (3.1.3.2) of the rocket engine within the operating temperature range of -30F to +140F shall not exceed that specified in Figure 3.3.1.5 Ignition interval

32、limit: The ignition interval at any temperature within the operating temperature range (3.1.1) shall not exceed 0.230 seconds.3.1.5.1 Ignition interval: Ignition interval is defined as the time from switch operation to the time when a minimum continuous thrust of 3000 lb. at -40F, 3500 lb. at 60F, a

33、nd 4500 lb. at +150F is obtained during the initial three seconds of thrust duration.3.2 Qualification Inspection:When specified, a sample shall be subjected to qualification inspection (see 4.2).3.3 Material:Material used shall conform to applicable government specifications or contractors specific

34、ations. Materials conforming only to contractors specifications may be used to provided the specifications are approved by the cognizant customer representative. The use of contractors specifications will not constitute waiver of customer inspection.3.4 Parts:3.4.1 Standard parts: Army-Navy Standard

35、 parts and references to their AN part numbers shall be used whenever possible.3.4.2 Dissimiliar metals: Contact between dissimiliar metals, especially brass, copper or steel, in contact with aluminum or its alloys shall be insulated in the best practicable manner. Refer toMIL-STD-889 for the compat

36、ibility for the metals.3.4.3 Interchangeability: Design of components shall be such as to insure interchangeability of parts and assemblies wherever possible. Quality control of components shall be exercised to assure such interchangeability. Exceptions to this specifications shall be limited to the

37、 following:(a) Nozzle throat diameters shall be assigned specifically for a batch of propellant when throat resizing is required to bring performance within allowable limits.(b) Safety diaphragms shall be assembled per applicable drawings and specifications, and shall be interchangeable as assemblie

38、s only.SAE AS8581 - 6 -3.5 Design and Construction:All drawings shall be prepared in accordance with DoD-D-1000 (Level Established by Contracting Officer) and MIL-D-5480; and shall be reviewed and approved by the customer or its duly authorized representative before being issued for production purpo

39、ses. Drawing changes shall be made in accordance with the procedure outlined in MIL-STD-480 and MIL-STD-481.A complete stress analysis for the rocket engine design shall be prepared and submitted to the customer for approval before manufacturing begins.3.5.1 Engine: The rocket engine shall be compos

40、ed of the following major components which shall be specified in detail in the applicable Model Specification.Chamber AssemblyAttachment fittingsAft Cap Assembly including:Nozzle and weather sealSafety release diaphragmIgniter AssemblyPropellant Grain AssemblyShipping Cap - Fore End3.5.2 Chamber ass

41、embly: The chamber, when fitted with igniter assembly and aft cap assembly (including nozzle and safety diaphragm assemblies), constitutes a pressure vessel, which shall be constructed in accordance with the best engineering practice to protect the enclosed propellant grain from all foreign matter i

42、ncluding moisture and to satisfy operating pressure requirements.3.5.2.1. Fittings: The attachment fittings shall satisfy installation under MIL-J-8667. The over-all envelope shall be within the outline established by NAF Drawing 502706, except that envelope deviations not violating the satisfaction

43、 of attachment fittings shall be permitted by contractual agreement between customer and contractor.3.5.2.2 Proof test: Hydrostatic proof test of each pressure vessel assembly as composed of aft cap assembly, chamber and nozzle shall be made of sufficient magnitude to demonstrate that, at the temper

44、ature to be encountered in these parts, adequate strength has been provided for the highest predictable operating pressure and the estimated acceleration loads during JATO operation as set forth in the stress analysis (3.5).3.5.2.3 Welding: All welding on the chamber shall be done by operators certi

45、fied in accordance with MIL-T-5021.3.5.3 Aft Cap Assembly: The aft cap assembly shall form the aft and closure of the chamber and retain the propellant grain in position within the chamber. The aft cap assembly shall incorporate the nozzle and safety diaphragm sub-assembly.SAE AS8581 - 7 -3.5.3.1 No

46、zzle assembly: The nozzle assembly shall be designed for the intended application and pressures.3.5.3.2 Safety diagram assembly: The safety diaphragm assembly shall be incorporated into the nozzle assembly to afford protection to the chamber against excessive pressure and shall be so designed that i

47、f actuated, pieces of the diaphragm are not ejected.3.5.4 Igniter assembly: A suitable igniter assembly shall be provided which can be shipped separately and easily inserted into the forward boss of the chamber assembly. The igniter assembly shall be capable of producing proper ignition of the main

48、propellant charge, and shall be equipped with a glow plug, containing dual filaments in parallel, which will set off the igniter charge when a minimum current of 10 amperes is applied. The electrical circuit shall consist of a suitable single lead wire, with a cable type protective covering, from th

49、e glow plug, and shall terminate with a standard electrical connector for attachment to the aircraft firing circuit. The ground connection shall be provided through the unit and its aircraft attachment fittings.3.5.4.1 Ignition: Ignition shall in no case take place with 0.04 (or less) amperes current flowing through the igniter circuit for any length of time.3.5.4.2 Wiring: Wiring on and around terminals shall be protected from moisture and spray to prevent corrosion and shorting of circuits. The igniter shall be protected from moisture a