AECMA PREN 2591-D2-1992 Aerospace Series Elements of Electrical and Optical Connection Test Methods Part D2 - Shock Issue P 1《航空航天系列.光电连接元件 试验方法 D2部分 冲击》.pdf

1、ENGLISH VERSION Edition approved for publication Comments should be sent within six months after the date of publication decision A.E.C.M.A. Technopolis - 175, rue Jean-Jacques Rousseau 921 38 Issy-les-Moulineaux Cdex FRANCE 1992-06-05 Aerospace series Elements of electrical and optical connection T

2、est methods Part D2 -Shock C2 Chairinan M. J. LE CUNFF Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-CEN PREN*259L (PART*D2) 92 m 3404589 0027033 5 m

3、 ! Q prEN 2591-D2 Page 3 1 Scope and field of application This standard specifies a method of assessing the ability of an element of connection to withstand mechanical shock of a specified severity. It shall be used together with EN 2591. 2 References EN 259 EN 259 EN 2591 Aerospace series - Element

4、s of electrical and optical connection - Test methods - General Aerospace series - Elements of electrical and optical connection - Test methods - Part AI - Visual examination 2) Aerospace series - Elements of electrical and optical connection - Test methods - Part B4 - Discontinuity of contacts in t

5、he microsecond range 1) Aerospace series - Elements of electrical and optical connection - Test methods - Part D8 - Mating and unmating forces 2) -Al -B4 EN 259 1-08 3 Preparation of specimens 3.1 The specimens shall be fitted with their standard accessories and wired as specified by the technical s

6、pecification. 3.2 Unless indicated in the technical specification, the following details shall be specified : - method of mounting and specimen wiring, - initial measurements and requirements, - pulse shape (method A or B), - test severity, - requirements for final measurements, - number of axes, if

7、 other than three, - number of shocks for each direction. 4 Apparatus The characteristics of the shock machine and mounting fixtures shall comply with the following requirements when loaded for conditioning. 4.1 Shock characteristics The shock machine shall be capable of generating a half sinusoidal

8、 pulse (method A) or a final peak saw-tooth pulse (method 6) as shown in figures 1 and 2 within tolerances as defined by the area shown within solid lines. The true value of the velocity change shall be within f 10 % of the value corresponding to the nominal pulse. To determine the velocity change,

9、the actual pulse shall be integrated from 0,4 D before the ideal pulse start to 0,l D beyond the end of this pulse where D is the duration of the ideal pulse. 1) In preparation at the date of publication of the present standard. 2) Published,as AECMA we-standard at the date of publication of the pre

10、sent standard. Previous page is blank Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-CEN PREN82591 (PARTmD2) 92 m 340Y589 00270LY 7 E prEN 2591-D2 Pag

11、e 4 0.2 -0,2 Time during which speed variation is measured I 4 Minimum time during which the pulse should be monitored -.I_ Reference line corresponding to prepulse conditions -_-_-_. Ideal pulse Limits of tolerances 0 = Duration of ideal pulse A = Peak acceleration of ideal pulse The reference line

12、 shall not differ more than i 0.05 a or? 9,8 rnls2 (equivalent to f 1 g), whlchever is the greater, from zero acceleration ,2 A“ .0,2 A Figure 1 - Half sinusoidal pulse - Method A Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot fo

13、r ResaleNo reproduction or networking permitted without license from IHS-,-,-CEN PREN*K2593 (PART*D2) 92 W 3484589 0027035 9 prEN 2591-D2 Page 5 -0.2 A O& I 1,15 A .85 +-I? Time during which speed variation is measured -0,4 D-r D Minimum time during which the pulse should be monitored - -.- Referenc

14、e line corresponding to prepulse conditions _ Ideal pulse Limits of tolerances Peak acceleration of ideal puise D = Duration of ideal puise A The reference line shall not differ more than 2 0.05 Aor +_ 9.8 m/s2 (equivalent to I 1 gl, whichever is the greater, from zero acceleration 1,2 A -0.2 A Figu

15、re 2 - Final peak saw-tooth pulse - Method B Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-prEN 2591-D2 Page 6 4.2 Mounting The specimen shall be mou

16、nted as specified by the technical specification so that all mechanical features shall be fully utilised (mounting, locking system . ). 5 Method 5.1 Initial measurements (if applicable) They shall be carried out according to the technical specification. 5.2 Levels They are given by a combination of

17、following parameters : wave form, acceleration, duration and velocity change. Table 1 - Levels Acceleration 5.3 Procedure Unless otherwise specified by the technical specification, monitoring of contact discontinuities in the microsecond range (test EN 259 1 -B4) shall be provided for contacts being

18、 connected in series (and shielding, if any) during test. There shall not be any discontinuity greater than 1 ps. The specimen shall be subjected to successive shocks for the number of shocks defined by the technical specification along the three axes and in each of the three directions, unless othe

19、rwise specified by the product standard. 5.4 Final measurements (if applicable) The specimens shall be submitted to the following tests - EN 2591-A1 - Visual examination, - EN 259 1 -D8 - Mating and unmating forces. Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-