1、MSFC-STD-3676National Aeronautics and REVISION ASpace Administration EFFECTIVE DATE: January 10, 2013George C. Marshall Space Flight CenterMarshall Space Flight Center, Alabama 35812ER41MSFC TECHNICAL STANDARDDEVELOPMENT OF VIBROACOUSTIC AND SHOCK DESIGN AND TEST CRITERIANOT MEASUREMENT SENSITIVEApp
2、roved for Public Release; Distribution is Unlimited)CHECK THE MASTER LISTVERIFY THAT THIS IS THE CORRECT VERSION BEFORE USE at https:/repository.msfc.nasa.gov/docs/multiprogram/MSFC-STD-3676.pdfProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MSFC Tec
3、hnical StandardER41DEVELOPMENT OF VIBROACOUSTIC AND SHOCK DESIGN AND TEST CRITERIADocument No.: MSFC-STD-3676 Revision: Revision AEffective Date: January 10, 2013 Page 2 of 37DOCUMENT HISTORY LOGStatus(Baseline/Revision/Canceled)DocumentRevisionEffectiveDate DescriptionBaseline 4/19/2012 Baseline re
4、lease; document is authorized through MPDMS.RevisionA 1/10/2013Revision A release; document is authorized through MPDMS. Changed only the standard status from ITAR to Approved for Public Release; Distribution is Unlimited. CHECK THE MASTER LIST - VERIFY THAT THIS IS THE CORRECT VERSION BEFORE USE at
5、 https:/repository.msfc.nasa.gov/docs/multiprogram/MSFC-STD-3676.pdf Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MSFC Technical StandardER41DEVELOPMENT OF VIBROACOUSTIC AND SHOCK DESIGN AND TEST CRITERIADocument No.: MSFC-STD-3676 Revision: Revis
6、ion AEffective Date: January 10, 2013 Page 3 of 37FOREWORDThis Standard describes the methodology used by the Marshall Space Flight Center to calculate random vibration, acoustic, and shock design and test criteria and subsequent design loads. In addition, the rationale for using these methods for l
7、aunch vehicle components and payloads is described. Also included are guidelines and requirements for selection of appropriate criteria for qualification and acceptance testing and guidelines and requirements for their application in testing spaceflight hardware.The major requirements detailed in th
8、is standard are:g120 Section 6. Random vibration, acoustic and shock qualification test criteria shall be based on the P97.5/50 statistical basis. No margin is required above the maximum predicted environment.g120 Section 6. Acceptance testing shall be conducted 6 dB below the qualification test lev
9、els.g120 Section 6. Qualification test duration shall encompass flight environments as well as the fatigue induced by multiple acceptance tests.g120 Requirements to be implemented during vibroacoustic and shock qualification and acceptance testing are described in section 7.g120 Test tolerances are
10、defined in section 7.CHECK THE MASTER LIST - VERIFY THAT THIS IS THE CORRECT VERSION BEFORE USE at https:/repository.msfc.nasa.gov/docs/multiprogram/MSFC-STD-3676.pdf Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MSFC Technical StandardER41DEVELOPM
11、ENT OF VIBROACOUSTIC AND SHOCK DESIGN AND TEST CRITERIADocument No.: MSFC-STD-3676 Revision: Revision AEffective Date: January 10, 2013 Page 4 of 37CONTENTSSECTION PAGE1. SCOPE71.1 Scope.71.2 Authority.71.3 Responsibility72. APPLICABLE DOCUMENTS72.1 Government Documents.72.2 Reference Documents.72.2
12、.1 Government Documents.72.2.2 Non-government Documents. 83. DEFINITIONS.83.1 Acronyms used in this standard84. INTRODUCTION.104.1 MSFC Approach/Experience Base105. ENVIRONMENT DEFINITION115.1 Acoustic and Aerodynamically Induced Fluctuating Pressure Environments.115.1.1 Engine Generated Acoustics11
13、5.1.2 Aerodynamically Generated Fluctuating Pressures.125.1.3 Internal Compartment Acoustics.125.2 Random Vibration Environment.125.2.1 Acoustically Induced Random Vibration125.2.2 Mechanically Induced Random Vibration.135.3 Transient Environments.145.3.1 Low and Mid Frequency Transients.145.3.2 Hig
14、h Frequency Transients146. DESIGN AND VERIFICATION CRITERIA.156.1 Maximum Predicted Environment.16CHECK THE MASTER LIST - VERIFY THAT THIS IS THE CORRECT VERSION BEFORE USE at https:/repository.msfc.nasa.gov/docs/multiprogram/MSFC-STD-3676.pdf Provided by IHSNot for ResaleNo reproduction or networki
15、ng permitted without license from IHS-,-,-MSFC Technical StandardER41DEVELOPMENT OF VIBROACOUSTIC AND SHOCK DESIGN AND TEST CRITERIADocument No.: MSFC-STD-3676 Revision: Revision AEffective Date: January 10, 2013 Page 5 of 376.2 Qualification and Acceptance Test Margin.166.3 Acceptance Tests.166.4 R
16、ationale and Consideration of Other NASA Standards176.5 Acoustic Criteria196.5.1 Insensitive Components.196.5.2 Sensitive Components.206.5.3 Engine Generated Acoustic Criteria206.5.4 Aerodynamically Generated Acoustic Criteria206.5.5 Payload Compartment Acoustic Criteria.206.6 Random Vibration Crite
17、ria216.6.1 Power Spectral Density (PSD) Calculation.216.6.2 Acoustically Induced Random Vibration Criteria.216.6.3 Mechanically Induced Random Vibration Criteria226.6.4 Payload Compartment Random Vibration Criteria.226.7 Transient Criteria.226.7.1 Low and Mid Frequency Transient Criteria.226.7.2 Hig
18、h Frequency Transient Criteria227. VIBRATION AND SHOCK QUALIFICATION TEST REQUIREMENTS AND PROCEDURES237.1 General Vibration and Shock Testing Requirements237.1.1 Specimen.237.1.2 Fixture.247.1.3 Test Specimen and Fixture Resonance Survey.247.1.4 Test Amplitude.257.1.5 Test Sequence.257.1.6 Function
19、al Performance267.2 Random Vibration Tests.267.2.1 Random Vibration Test Procedure.267.3 Transient (Shock) Tests27CHECK THE MASTER LIST - VERIFY THAT THIS IS THE CORRECT VERSION BEFORE USE at https:/repository.msfc.nasa.gov/docs/multiprogram/MSFC-STD-3676.pdf Provided by IHSNot for ResaleNo reproduc
20、tion or networking permitted without license from IHS-,-,-MSFC Technical StandardER41DEVELOPMENT OF VIBROACOUSTIC AND SHOCK DESIGN AND TEST CRITERIADocument No.: MSFC-STD-3676 Revision: Revision AEffective Date: January 10, 2013 Page 6 of 377.3.1 Vehicle Dynamics Test Procedure277.3.2 Shock Test Req
21、uirements.287.3.3 Test Instrumentation287.3.4 Shock Test Procedure287.4 Acoustic Test Requirements and Procedures.297.4.1 General Requirements297.4.2 Reverberation Chamber Facilities297.4.3 Progressive Wave Facilities.307.4.4 Tolerances307.4.5 Acoustic Test Procedure307.4.6 Acoustic Test Reports317.
22、5 Combined Environments317.6 Test Tolerances.317.7 Failure Determination.327.8 Deviations from Specifications.327.9 Test Reports328. DESIGN LOADS METHODOLOGY.338.1 Acoustic and Fluctuating Pressure Loads338.2 Random Vibration Loads.348.3 Transient Loads358.4 Dynamic Load Combination.369. SUMMARY AND
23、 CONCLUSIONS37TABLE. PAGETable I. Rayleigh Distribution35FIGURE PAGEFigure 1. Relationship Between Acceptance and Qualification Tests When a Minimum Test is Applied .17Figure 2.Comparison of Criteria Drawn on 5 Hz Versus 1/6 Octave Bandwidth Data 19CHECK THE MASTER LIST - VERIFY THAT THIS IS THE COR
24、RECT VERSION BEFORE USE at https:/repository.msfc.nasa.gov/docs/multiprogram/MSFC-STD-3676.pdf Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MSFC Technical StandardER41DEVELOPMENT OF VIBROACOUSTIC AND SHOCK DESIGN AND TEST CRITERIADocument No.: MSF
25、C-STD-3676 Revision: Revision AEffective Date: January 10, 2013 Page 7 of 371. SCOPE1.1 Scope.This document presents the methodology for the development and application of the vibroacoustic and transient design and verification criteria for Marshall Space Flight Center (MSFC) managed launch vehicle
26、and payload hardware. The following are included:a. Environment definitionb. Design and verification criteriac. Vibration and shock qualification test requirements and proceduresd. Design loads methodology1.2 Authority.This standard is to be used to aid in the development of random vibration, acoust
27、ic, and shock design and test criteria. It meets the intent of higher level NASA standards such as NASA-STD-7001 and NASA-STD-7003.1.3 Responsibility.The Marshall Space Flight Center is responsible for implementation of this standard. Contractors fulfilling contracts that levy this standard shall ad
28、here to the requirements included herein. Any deviation to the requirements in this standard shall require approval by the OPR.2. APPLICABLE DOCUMENTS2.1 Government Documents.NASANASA-STD-7003 Pyroshock Test CriteriaNASA-STD-7001 Payload Vibroacoustic Test Criteria2.2 Reference Documents.Documents l
29、isted below are provided as background or supplemental information for the users of this standard. The listing in this section does not levy any new or relieve any specific requirements that are imposed by this standard or by other contractual documents. 2.2.1 Government Documents.NASANASA TM-86538
30、Design and Verification Guidelines for Vibroacoustic and Transient Environments NASA-HDBK-7005 Dynamic Environmental CriteriaCHECK THE MASTER LIST - VERIFY THAT THIS IS THE CORRECT VERSION BEFORE USE at https:/repository.msfc.nasa.gov/docs/multiprogram/MSFC-STD-3676.pdf Provided by IHSNot for Resale
31、No reproduction or networking permitted without license from IHS-,-,-MSFC Technical StandardER41DEVELOPMENT OF VIBROACOUSTIC AND SHOCK DESIGN AND TEST CRITERIADocument No.: MSFC-STD-3676 Revision: Revision AEffective Date: January 10, 2013 Page 8 of 37NASA TN D-1836 Techniques for Predicting Localiz
32、ed Vibratory Environments of Rocket VehiclesNASA TN D-2158 Statistical Techniques for Describing Localized Vibratory Environments of Rocket Vehicles NASA TN D-7159 Development and Application of Vibroacoustic Structural Data Banks in Predicting Vibration Design and Test Criteria for Rocket Vehicle S
33、tructuresNASA/TM-2009-215902 Using the Saturn V and Titan III Vibroacoustic Databanks for Random Vibration Criteria Development2.2.2 Non-government Documents.NASA-CR-116437 “Aerospace Systems Pyrotechnic Shock Data - Ground Test and Flight, Volumes 1 through 6”, Martin Marietta Corp., March 7, 1970,
34、 Contract No: NAS5-15208.Gaberson, Howard A.: “Shock Severity Estimation”, Sound Karen Oliver and Andrew Smith, EV31; David Parsons, ES22; Bruce LaVerde with ERC, Inc. and David Teague with Jacobs Engineering.4.1 MSFC Approach/Experience Base.The MSFC approach presented in this standard is based on
35、more than 40 years of experience in developing large launch vehicles and payloads, many of which were man-rated. The launch vehicle programs include the Redstone; Jupiter; Saturn I, IB, and V; and the Solid Rocket Booster (SRB), External Tank (ET), and Space Shuttle Main Engine (SSME) elements of th
36、e Space Shuttle. The payload programs include the Skylab, Spacelab, Hubble Space Telescope and numerous Space Shuttle payloads. MSFC has been extremely successful in the vibroacoustic design and verification of the flight hardware for these programs. Vibration and acoustic data acquired from these p
37、rograms during static firings, ground-based acoustic tests, and flights have been evaluated and folded into a computerized structural data bank. This data bank serves as the empirical base for the formulation ofthe vibroacoustic design and verification criteria for all MSFC managed launch vehicle an
38、d payload programs. The data bank also provides a basis for evaluation of predictions from analytical tools. All analyses are simulations which are not complete (limited), which attempt to predict trends of what will happen. The same is true of test. All these partial attempts to model or test reali
39、ty are melded together. How these many pieces are put together determines the validity of the design. This principle must be fully understood so that everything is constantly challenged for applicability. The major problem we deal with is how this less-than-reality information is meshed together to
40、get verified, reliable systems. Obviously, this can only be done in some probabilistic sense. In addition CHECK THE MASTER LIST - VERIFY THAT THIS IS THE CORRECT VERSION BEFORE USE at https:/repository.msfc.nasa.gov/docs/multiprogram/MSFC-STD-3676.pdf Provided by IHSNot for ResaleNo reproduction or
41、networking permitted without license from IHS-,-,-MSFC Technical StandardER41DEVELOPMENT OF VIBROACOUSTIC AND SHOCK DESIGN AND TEST CRITERIADocument No.: MSFC-STD-3676 Revision: Revision AEffective Date: January 10, 2013 Page 11 of 37to the use of robust statistical approaches, how the limitations o
42、f model, tests, etc. are dealt with determines the design outcome. There are many ways of approaching the question; however, the fundamental approach appears to be a building block approach using a combination of analysis and test. Fundamental to this approach are the following steps: (1) formulate
43、model, (2) perform pretest analysis and sensitivity studies to guide test, etc., (3) perform test with proper instrumentation, (4) correlate predictions and test, and (5) update model to produce verified model.One of the most important general principles in the development of vibroacoustic design an
44、d test criteria is to make simplified hand analyses to understand the phenomenon and guide all more in-depth computer evaluations. A fundamental part of this approach is the determination of the extreme or limiting cases. By establishing the physical understanding of a problem and its bounds, greate
45、r insight and more efficiency are established.MSFC has also developed a capability for using vibroacoustic models. The focus of this development has been critical evaluation and verification of analytical response results by comparison to flight and ground test measurements. Exploring the strengths
46、and identifying the limitations of each analytical approach is important.5. ENVIRONMENT DEFINITIONThe critical nature of todays launch vehicles and payloads results in stringent vibroacoustic and transient design requirements on systems and components. The stringent cost controls and critical schedu
47、les are an additional consideration. Precise definition of the vibroacoustic and transient environments is an essential design requirement. This section briefly discusses the sources of these environments and methods of predicting their magnitudes.5.1 Acoustic and Aerodynamically Induced Fluctuating
48、 Pressure Environments.The acoustic environment is the maximum fluctuating pressure acting on the surface of the launch vehicle or payload structure. The two primary sources for the acoustic environment are the engine generated noise during static firing and liftoff and the aerodynamically generated
49、 fluctuating pressure levels (FPL) during the transonic and maximum dynamic pressure periods of ascent and reentry flight.5.1.1 Engine Generated Acoustics.The primary source of the acoustic field is the fluctuating turbulence in the mixing region of the rocket exhaust flow. Engine generated noise is a function of the exhaust flow parameters, launch stand
