AIR FORCE MIL-STD-1540 D-1999 PRODUCT VERIFICATION REQUIREMENTS FOR LAUNCH UPPER STAGE AND SPACE VEHICLES《航天器上层级发射的生产验证要求》.pdf

《AIR FORCE MIL-STD-1540 D-1999 PRODUCT VERIFICATION REQUIREMENTS FOR LAUNCH UPPER STAGE AND SPACE VEHICLES《航天器上层级发射的生产验证要求》.pdf》由会员分享，可在线阅读，更多相关《AIR FORCE MIL-STD-1540 D-1999 PRODUCT VERIFICATION REQUIREMENTS FOR LAUNCH UPPER STAGE AND SPACE VEHICLES《航天器上层级发射的生产验证要求》.pdf（28页珍藏版）》请在麦多课文档分享上搜索。

1、AMSC N/A FSC 1810MIL-STD-1540D15 January 1999_SUPERSEDINGMIL-STD-1540C15 SEPTEMBER 1994DEPARTMENT OF DEFENSESTANDARD PRACTICEPRODUCT VERIFICATIONREQUIREMENTSFORLAUNCH, UPPER STAGE, AND SPACEVEHICLESNOTMEASUREMENTSENSITIVEProvided by IHSNot for ResaleNo reproduction or networking permitted without li

2、cense from IHS-,-,-iiFOREWORD1. This Military Standard is approved for use by all Departments and Agencies ofthe Department of Defense.2. Beneficial comments (recommendations, additions, or deletions) and anypertinent data which may be of use in improving this document should beprovided by letter ad

3、dressed to:Space and Missile Systems Center, SMC/AXM160 Skynet Street, Suite 2315El Segundo, CA 90245-46833. A verification process is required by this document. The verification process isfundamental in the development of a successful launch or space system. Theprocess involves various tasks perfor

4、med in different program phases applyinga coherent bottom-up building block concept.4. The fact that most launch and space systems involve flight equipment that isnot recoverable and not repairable means that risk management is essential.The cost of a failure may be extremely high due to the loss of

5、 missioncapability and the loss of equipment. The large number of independentorganizations involved and the complexity of equipment and software meansthat extensive verification of launch and space systems is necessary to reducethe risk of failure. A combination of different verification methodologi

6、es (e.g.,Test, Analysis, Inspection) at several assembly levels (from units to the overallsystem) through the various program verification phases (e.g. Qualification,Acceptance, Pre-launch, On-orbit) is cost effective in assuring successfulequipment and software design and operation.Provided by IHSN

7、ot for ResaleNo reproduction or networking permitted without license from IHS-,-,-iiiCONTENTSPARGRAPHpageFOREWORD ii1. SCOPE . 11.1 Scope 12. APPLICABLE DOCUMENTS 12.1 General 12.2 Government Documents . 12.2.1 Specifications, standards and handbooks . 12.3 Non Government Publications . 22.4 Order o

8、f precedence . 23. DEFINITIONS . 33.1 Part. 33.2 Subassembly . 33.3 Unit 33.4 Subsystem 33.5 Vehicle 33.5.1 Launch Vehicle 33.5.2 Upper-stage Vehicle . 33.5.3 Space Experiment 33.5.4 Space Vehicle . 33.5.5 Flight Vehicle 43.6 System . 43.7 Combined Systems 43.7.1 Launch Systems 43.7.2 On-orbit Syste

9、m 43.8 Airborne Support Equipment (ASE) 43.9 Critical Unit . 43.10 Development Test Article . 43.11 Reusable Item 54. GENERAL REQUIREMENTS . 64.1 Objectives of Verification . 64.2 Verification Activities 64.3 Risk Management . 7Provided by IHSNot for ResaleNo reproduction or networking permitted wit

10、hout license from IHS-,-,-ivTABLE OF CONTENTS(continued)5. DETAILED REQUIREMENTS 85.1 Requirements Allocation . 85.2 Service Life Cycle Profile . 85.3 Environmental Design Requirements . 85.4 V erification Methods . 95.4.1 Analysis 105.4.2 Test . . 105.4.2.1 Hardware Qualification . 105.4.2.1.1 Qual

11、ification Techniques . 105.4.2.1.2 Qualification Test Requirements . 105.4.2.1.3 Test for Risk Mitigation 115.4.2.2 Hardware Acceptance 115.4.2.2.1 Acceptance Test Requirements . 115.4.2.2.2 Acceptance Methods 125.4.2.2.3 Test for Risk Mitigation 125.4.3 Inspection . 135.4.4 Demonstration 135.4.5 Si

12、milarity . 135.5 Integrated Test Plan . 135.6 Preparation for Verification Activities 145.6.1 Preparation for Analysis 145.6.2 Preparation for Test Activities . 145.6.3 Preparation for Inspections . 145.6.4 Preparation for Demonstrations . 155.6.5 Documentation for Demonstrations . 155.6.6 Process I

13、mprov ement 155.7 Conduct Verification Activities 155.8 Evaluate Verification Results . 156.0 NOTES . 166.1 Shared Database . 166.2 Guidance Tables . 16TABLEST-1 Factors to Consider When Establishing Test Requirements. 17T-2 Type of Subsystem 18-21T-3 Primary Qualification Tests to Identify Failure

14、Mechanism . 22T-4 Primary Acceptance Test to Precipitate Failure Mechanism . 23CONCLUDING MATERIAL . 24Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-STD-1540D11. SCOPE1.1 Scope. This document requires that a process be established todevelop and

15、 manage verification requirements to assure that launch and spaceequipment can function correctly and withstand stresses it may encounter during itslife cycle including end-of-life performance requirements. This document isintended for use in developing the detailed verification requirements for a p

16、articularproject. The application of these requirements should result in an effectiveverification process and consequently high confidence in achieving successfulspace missions.2. APPLICABLE DOCUMENTS2.1 General. The documents listed in this section are specified in sections 3, 4,and 5 of this stand

17、ard. This section does not include documents cited in othersections of this standard or recommended for additional information or as examples.While every effort has been made to ensure the completeness of this list, documentusers are cautioned that they must meet all specified requirements documents

18、 citedin sections 3, 4, and 5 of this standard, whether or not they are listed.2.2 Government Documents .2.2.1 Specifications, standards, and handbooks . The following standards andspecifications form a part of this document to the extent specified herein. Unlessotherwise specified, the issues of th

19、ese documents are those listed in the issue ofthe Department of Defense Index of Specifications and Standards (DODISS) andsupplement thereto, cited in the solicitation.DEPARTMENT OF DEFENSE STANDARDSMIL -STD -810 Environmental Test Methods andEngineering Guidelines.MIL -STD -1522 (USAF) Standard Gen

20、eral Requirements for Safe Design and Operation of Pressurized Missile and Space Systems.MIL -STD -1541 (USAF) Electromagnetic Compatibility Requirements forSpace Systems.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-STD-1540D2MIL -STD -1833 (U

21、SAF) Test Requirements for Ground Equipmentand Associated Computer Software Supporting Space Vehicles. (Cancele d)MIL-HDBK-340A (USAF) Volume 1 Test Requirements For Launch, Upper Stage i.e., the launch vehicle(s), the upper -stage vehicle(s),and the space vehicle(s) to be sent to orbit.3.6 System .

22、 A system is a composite of equipment, skills, and techniquescapable of performing or supporting an operational role. A system includes alloperational equipment, related facilities, material, software, services, and personnelrequired for its operation. A system is typically defined by the System Pro

23、gramOffice or the procurement agency responsible for its acquisition.3.7 Combined Systems . Combined systems are interconnected systems thatare required for program level operations or operational tests. The combinedsystems of interest are typically the launch system and the on -orbit system.3.7.1 L

24、aunch System . A launch system is the composite of equipment, skills,and techniques capable of launching and boosting one or more space vehicles intoorbit. The launch system includes the flight vehicle and related facilities, groundequipment, material, software, procedures, services, and personnel r

25、equired fortheir operation.3.7.2 On -orbit System . An on -orbit syst em is the composite of equipment,skills, and techniques permitting on -orbit operation of the space vehicle(s). Theon -orbit system includes the space vehicle(s), the command and control network,and related facilities, ground equi

26、pment, material, software, procedures, services,and personnel required for their operation.3.8 Airborne Support Equipment (ASE) . Airborne support equipment is theequipment installed in a flight vehicle to provide support functions and interfaces forthe space or upper -stage vehicle during launch an

27、d orbital operations of the flightvehicle. This includes the hardware and software that provides the structural,electrical, electronic, and mechanical interfaces with the flight vehicle.3.9 Critical Unit . A critical unit is one whose failure can affect the systemoperation sufficiently to cause the

28、loss of the stated vehicle objectives, a partial lossof the mission, or is a unit whose proper performance is essential from a rangesafety standpoint.3.10 Development Test Article . A development test article is arepresentative vehicle, subsystem, or unit dedicated to provide design and testinformat

29、ion. The information may be used to check the validity of analytictechniques and assumed design parameters, to uncover unexpected responsecharacteristics, to evaluate design changes, to determine interface compatibility, toprove qualification and acceptance test procedures and techniques, or to dete

30、rmineif the equipment meets its performance specifications. Development test articlesProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-STD-1540D5include engineering test models, thermal models, and structural static and dynamicmodels.3.11 Reusable

31、Item . A reusable item is a unit, subsystem, or vehicle that is tobe used for multiple missions. The service life (3.5.6) of reusable hardwareincludes all planned reuses, refurbishment, and retesting.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MI

32、L-STD-1540D64. GENERAL REQUIREMENTS4.1 OBJECTIVES OF VERIFICATIONThis document outlines requirements for a verification process that shall bedeveloped and used for launch vehicles, upper stage vehicles and space vehicles.During development of a launch vehicle, upper stage vehicle or space vehicle,ve

33、rification is a fundamental process used to demonstrate that the system designmeets applicable requirements and is capable of sustaining its operational roleduring the life cycle. Verification may be by analysis, test, inspection,demonstration, similarity, or a combination of these methods The verif

34、icationobjectives are primarily:a. To qualify the design through an analysis, demonstration and testprogram that verifies that it meets performance and interfacerequirements when exposed to applicable environments.b. To verify that the manufacturing process produces products that meetspecified desig

35、n requirements.c. To ensure that flight hardware and software are free of workmanshipand latent defects and are acceptable for flight.d. To validate equipment and procedures necessary to support groundand flight operations.e. To predict and confirm vehicle and system integrity and performanceduring

36、all phases and that it completes its design life cycle includingend-of-life performance requirements.4.2 VERIFICATION ACTIVITIESTo reach the objectives stated in 4.1, verification activities shall be conceivedand documented during the design and requirements definition phase. Therequirements to be v

37、erified shall be analyzed taking into account designpeculiarities, candidate solutions, qualification status of heritage units andsubsystems, test and analysis methodologies, programmatic constraints, riskmanagement process, cost, schedule, and allowable performance dispersions.The verification acti

38、vities are incrementally performed at different hardwareand software assembly levels from units to the overall system, utilizing a suitablecombination of verification methods. They apply to all project phases through thefollowing main steps of the verification process:Provided by IHSNot for ResaleNo

39、 reproduction or networking permitted without license from IHS-,-,-MIL-STD-1540D7a. Establish all system requirements and allocate to subtier levels.b. Establish the service life cycle profile.c. Derive the environmental design requirements.d. Establish methods for design and process verification (Q

40、ualification)and product verification (Acceptance).e. Prepare for verification activities: e.g.; prepare models, software anddatabases needed for analyses, prepare plans and procedures fortests, and develop tools and methodologies for inspections.f. Conduct the verification activities.g. Evaluate re

41、sults to confirm verification.Details of other verification activities required such as for software and forintegrated system level requirements are too extensive for inclusion in thisdocument. These omissions should not be interpreted to mean that theseverification activities are less effective or

42、less important.4.3 Risk Management The risk management process is a life cycle process,which periodically reassesses the risk elements; to ensure the programsability to meet its cost, performance and schedule goals. The followingguidelines shall apply:a. Design margins shall be a Risk Management Dec

43、ision,b. Ensure that risk management decisions do not invalidate the verificationobjectives,c. Because space systems / subsystems and launch vehicles are notmanaged to the same levels of risk. Space risk classification for eitherhardware class or program class or both should be agreed by the custome

44、r,d. The risk classification of space programs, space vehicles and spaceexperience are defined in MIL-HDBK-343.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-STD-1540D85. DETAILED REQUIREMENTS5.1 REQUIREMENTS ALLOCATIONThe system requirements in

45、cluding performance requirements and externalinterfaces, shall be documented. The allocation of these system requirements tosubtier hardware and software shall also be documented as subtier requirements.These system and subtier requirements establish the list of requirements thatgovern the design pr

46、ocess and establish the need for subsequent verification of thehardware and software.5.2 SERVICE LIFE CYCLE PROFILEA projection of life cycle events, performance requirements, interfaces,configuration, and associated environmental conditions for an item (unit throughvehicle level of assembly) from i

47、ts completion in manufacturing, through assemblyand integration into a flight system, prelaunch, launch and orbital operation shall bedocumented. The life cycle shall include the various phases an item may encounterin its life, such as: testing, handling, shipping, storage, launch, ascent and on-orb

48、itoperations. The combination of environments each item of equipment mayencounter at each phase of its life cycle through end-of-life shall be determined.The following factors should be taken into account:a. Exposure and duration, to launch vehicle, operational and naturalenvironments.b. Probability of environmental condition.c. Configuration of the hardware and applicable software.d. Interfaces with other equipment or software.e. Other information which helps identi