AECMA PREN 4662-2009 Aerospace series Test specification for vibration control components Edition P 1《航空航天系列.防震元件的测试规范.版本P1》.pdf

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1、ASD STANDARD NORME ASD ASD NORM prEN 4662 Edition P 1 March 2009 PUBLISHED BY THE AEROSPACE AND DEFENCE INDUSTRIES ASSOCIATION OF EUROPE - STANDARDIZATIONAvenue de Tervuren, 270 - B-1150 Brussels - Tel. + 32 2 775 8126 - Fax. + 32 2 775 8131 - www.asd-stan.orgICS: Descriptors: ENGLISH VERSION Aerosp

2、ace series Test specification for vibration control components Srie arospatiale Spcification dessais pour des composants de contrle en vibration Luft- und Raumfahrt Prfspezifikation fr Bauteile zur Schwingungsminderung This “Aerospace Series“ Prestandard has been drawn up under the responsibility of

3、 ASD-STAN (The AeroSpace and Defence Industries Association of Europe - Standardization). It is published for the needs of the European Aerospace Industry. It has been technically approved by the experts of the concerned Domain following member comments. Subsequent to the publication of this Prestan

4、dard, the technical content shall not be changed to an extent that interchangeability is affected, physically or functionally, without re-identification of the standard. After examination and review by users and formal agreement of ASD-STAN, it will be submitted as a draft European Standard (prEN) t

5、o CEN (European Committee for Standardization) for formal vote and transformation to full European Standard (EN). The CEN national members have then to implement the EN at national level by giving the EN the status of a national standard and by withdrawing any national standards conflicting with the

6、 EN. Edition approved for publication 31 March 2009 Comments should be sent within six months after the date of publication to ASD-STAN Mechanical Domain Copyright 2009 by ASD-STAN Copyright ASD-STAN Provided by IHS under license with AECMA Not for ResaleNo reproduction or networking permitted witho

7、ut license from IHS-,-,-prEN 4662:2009 2 Contents Page Foreword2 1 Scope 3 2 Definition and symbols .3 3 Test set up7 4 Static stiffness .7 5 Dynamic stiffness 9 Foreword This standard was reviewed by the Domain Technical Coordinator of ASD-STANs Mechanical Domain. After inquiries and votes carried

8、out in accordance with the rules of ASD-STAN defined in ASD-STANs General Process Manual, this standard has received approval for Publication. Copyright ASD-STAN Provided by IHS under license with AECMA Not for ResaleNo reproduction or networking permitted without license from IHS-,-,-prEN 4662:2009

9、 3 1 Scope This standard specifies the procedure and the parameter for testing static and dynamic stiffness of vibration control components (e.g. shockmounts with bushes). This standard applies to vibration control components all installed for aircraft applications. It may be applied when referred t

10、o in the product standard or in a design specification. 2 Definition and symbols For the purposes of this document, the following definition and symbols apply. 2.1 Coordinate system The functional requirements shall be defined in a Cartesian coordinate system. The directions for translation and rota

11、tion shall be defined in the specifications of the relevant product standards. 2.2 Symbols 2.2.1 Static stiffness Due to the material damping vibration control components can have a hysteresis load versus displacement curve as shown exemplary in Figure 1. Copyright ASD-STAN Provided by IHS under lic

12、ense with AECMA Not for ResaleNo reproduction or networking permitted without license from IHS-,-,-prEN 4662:2009 4 SpuSplFpuUpper load FplLower load SpuUpper displacement SplLower displacement F1Load value 1 F2Load value 2 F5Load value 5 F6Load value 6 S1Displacement value 1 S2 Displacement value 2

13、 S5Displacement value 5 S6Displacement value 6 Figure 1 Load and displacement symbols for translation direction The symbols and parameters for the translation directions can be analogy adapted to the rotational data (see Table 1). Copyright ASD-STAN Provided by IHS under license with AECMA Not for R

14、esaleNo reproduction or networking permitted without license from IHS-,-,-prEN 4662:2009 5 Table 1 Torque and angle symbols for rotation direction Symbols for Translation direction Rotation direction FpuMpuUpper torque FplMplLower torque SpupuUpper angle SplplLower angle F1M1Torque value 1 F2 2Torqu

15、e value 2 F5M5Torque value 5 F6 6Torque value 6 S11Angle value 1 S22Angle value 2 S55Angle value 5 S66Angle value 6 Further symbols are defined in Table 2. Table 2 General symbols for static test Symbols Static test FpreStatic constant load MpreStatic constant torque SpreStatic constant displacement

16、 preStatic constant angle N Number of load cycles V Test speed C1/2Secant stiffness (see Figure 1) C5/6Secant stiffness (see Figure 1) C1-6Resulting stiffness CkCorrection stiffness CstatResulting static stiffness T Environmental test temperature 2.2.2 Dynamic stiffness An exemplary curve for dynami

17、c stiffness and loss angle is shown in Figure 2. Copyright ASD-STAN Provided by IHS under license with AECMA Not for ResaleNo reproduction or networking permitted without license from IHS-,-,-prEN 4662:2009 6 CdyndynFrequencyLoss angleDynamic stiffnessf1fmaxCdyn-1dyn-1Key 1 Loss angle 2 Dynamic stif

18、fness 3 Frequency fmax. Limit test frequency CdynDynamic stiffness dynLoss angle f1Frequency value 1 Cdyn-1Stiffness value 1 dyn-1Loss angle value 1 Figure 2 General symbols for dynamic test Further symbols are defined in Table 3. Table 3 General symbols for dynamic test Symbols Dynamic test FpreSta

19、tic constant load A Amplitude T Environmental test temperature 123Copyright ASD-STAN Provided by IHS under license with AECMA Not for ResaleNo reproduction or networking permitted without license from IHS-,-,-prEN 4662:2009 7 3 Test set up The test set up shall be designed and manufactured ready to

20、install and measure the specimens due to the specified stiffness directions. The test device shall reproduce the real aircraft installation as exact as possible and needed. If necessary surrounding original aircraft parts has to be integrated in the test set up. The test set up shall be as rigid as

21、possible and support the maximum test loads without significant deformation (specimen and original aircraft parts excluded) or failure. For the measure of the dynamic values the test set up shall be resonance free at minimum factor 2 over the maximum test frequency. The test set up including type of

22、 testing machine shall be in accordance with the specifications of the relevant product standards and documented by pictures and drawings. 4 Static stiffness 4.1 Test parameters See Table 4 Table 4 Parameter setting Control type Default parameters Requirements pre-load cycle Requirements test cycle

23、Measurement data FpreFplFuuN Force V Load versus displacement Sample rate 100 MpreMplMuuN Torque V Torque versus angle Sample rate 100 SpreSplSuuN Displacement V Load versus displacement Sample rate 100 prepluuN Angle V In accordance with the specifications of the relevant product standards In accor

24、dance with the specifications of the relevant product standards Torque versus angle Sample rate 100 NOTE Temperature T in accordance with the specifications of the relevant product standards. Copyright ASD-STAN Provided by IHS under license with AECMA Not for ResaleNo reproduction or networking perm

25、itted without license from IHS-,-,-prEN 4662:2009 8 4.2 Stiffness evaluation See Table 5. Table 5 Measurement values Control type Default parameters Evaluation data Requirements F1S1F2 2F5S5Force F6 6M11M22M55Torque M66S1F1S2 2S5F5Displacement S6 61M12M2 5M5 Angle 6M6 Parameters and evaluation data

26、in accordance with the specifications of the relevant product standards Nominal values and tolerances for stiffness Cstatin accordance with the specifications of the relevant product standards The formulae to calculate the stiffness are: 12122/1SSFFC= 65656/5SSFFC= 26/52/161CCC+=kstatCCC =61where Ck

27、 is the parasitic or correction stiffness as defined in 4.3. Copyright ASD-STAN Provided by IHS under license with AECMA Not for ResaleNo reproduction or networking permitted without license from IHS-,-,-prEN 4662:20099 4.3 Parasitic stiffness Before testing the specimen the correction factor for th

28、e test set up shall be determined. This parasitic stiffness depends on the test machine itself and on the test set up. The correction factor shall be measured by substitution of the specimen including the original aircraft parts with a rigid dummy. The same test parameters shall be applied as for th

29、e test cycle (see Table 4) and the stiffness Ckshall be calculated analogue to C1-6. 5 Dynamic stiffness 5.1 Parameters See Table 6. Table 6 Parameter setting Default parameters Measurement data Requirements test cycle Dynamic stiffness versus frequency Sample rate 100 Fpre fmax. A Loss angle versus

30、 frequency Sample rate 100 In accordance with the specifications of the relevant product standards NOTE Temperature T in accordance with the specifications of the relevant product standards 5.2 Stiffness evaluation See Table 7. Table 7 Parameter setting Default parameters Measurement data Requirements test cycle CdynfdynlossIn accordance with the specifications of the relevant product standards Copyright ASD-STAN Provided by IHS under license with AECMA Not for ResaleNo reproduction or networking permitted without license from IHS-,-,-