1、 - CEN PREN*i!CL (PART*D20) 92 H 3404589 0027037 2 H A. E. C. M, A. STA N D A R D NORME A.E.C.M.A. A.E.C.M.A. NORM prEN 2591 Part D20 Issue P 1 June 1992 DIT PAR LASSOCIATION EUROPENNE DES CONSTRUCTEURS DE MATRIEL AROSPATIAL Technopolis - 175, rue Jean-Jacques Rousseau - F-92138 Issy-les-Moulineaux
2、Cdex -Tl. (1) 47.36.98.76 UDC : Key words ENGLISH VERSION Aerospace series Elements of electrical and optical connection Test m et h o d s Part D20 - Mechanical strength of rear accessories Srie arospatiale Luft- und Raumfahrt Mthodes dessais Prfverfahren Organes de connexion lectrique et optique Pa
3、rtie D20 - Tenue mcanique des accessoires arrire Elektrische und optische Verbindungselernente Teil D20 - Mechanische Festigkeit der r U c ks e i t i g e n Zu be h rte i I e This .Aerospace Series. pre-standard has been drawn up under the responsibility of AECMA (Association Europenne des Constructe
4、urs de Matriel Arospatial). li is published on green paper for the needs of AECMA-Members. It has been technically approved b y the experts of the concerned Commission following comment by the Member countries. Subsequent to the publication of this pre-standard, the technical content shall not be ch
5、anged to an extent that interchangeability is affected, physically or functionally, without re-identification of the standard. After examination and signature of the AECMA Standard Checking Centre (NPS) and formal agreement of the Official Services of he Member countries it will be submitted as a dr
6、aft European Standard to GEN (European Committee for Standardization) for final vote. Noia - Extra copies can be supplied by B.N.A.E. - Technopolis 54 199. rue Jean-Jacques Rousseau - 92138 ISSY-LES-MOULINEAUX CEDEX I I Edition approved for publication Commenfc should be sent within six months after
7、 the date of publication decision A.E.C.M.A. Technopolis - 175, tue Jean-Jacques Rousseau 92138 Issy-les-Moulineaux Cdex - FRANCE 1992-06-05 C2 Chairman M. J. LE CUNFF I I 0 aecma 1992 Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMAN
8、ot for ResaleNo reproduction or networking permitted without license from IHS-,- CEN PREN*K259L (PARTUD20) 92 3404589 00270L8 4 prEN 2591-D20 Page 3 1 This standard specifies a method of verifying the ability of rear accessories to withstand bending, tensile, rotational stresses and stresses applied
9、 on the mating thread. Scope and field of application r It shall be used together with EN 2591 2 References EN 2591 Aerospace series - Elements of electrical and optical connection - Test methods - General EN 2591-A1 Aerospace series - Elements of electrical and optical connection - Test methods - P
10、art Al - Visual examination 1) 3 Preparation of specimens 3.1 The specimens shall be secured to a fixture simulating the rear part of an element of connection ; they shall be locked as specified by the technical specification. 3.2 Unless indicated in the technical specification, the following detail
11、s shall be specified : - mounting of specimens, - for phase A, value of the bending moment, - for phase B, value of the tensile force, - for phase C, value of the torsional moment and direction, - for phase D, torque value and direction, - values of tightening and untightening torques. 4 Apparatus A
12、ny equipment suitable for applying and measuring the bending, tensile, rotational stresses and torque values. 5 Method 5.1 Procedure The specimen shall remain assembled while submitted to the following tests in the order shown : L 1) In preparation at the date of publication of the present standard.
13、 - 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-,-prEN 2591-D20 Page 4 5.1.1 Phase A : bending With the specimen placed horizonta
14、lly in the test fixture, bending moments shall be applied successively to the end of the accessory as shown in figure 1 or 2. 1 Figure 1 Figure 2 The force shall be applied progressively at a rate not exceeding 20 N/s until the value specified by the technical specification is reached. It shall then
15、 be maintained for 1 min. 5:l .2 Phase B : tensile h tensile force shall be applied to the end of the accessory as shown on figure 3 or 4. Figure 3 Figure 4 This force shall be applied progressively at a rate not exceeding 20 N/s until the value specified by the technical specification is reached. I
16、t shall then be maintained for 1 inin. 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-,-4 Q - CEN PREN*259L (PARTUD20) 92 3404589 0027020 2 = prEN 259 1 -
17、D20 Page 5 5.1.3 Phase C : torsional A torsional moment shall be applied to the specimen as shown on figure 5 or 6 and as specified by the technical specification. i- Figure 5 Figure 6 This torsional force shall be applied progressively at a rate not exceeding 20 N/s until the value specified by the
18、 technical specification is reached. This value shall be maintained for 1 min. 5.1.4 Phase D The specimen shall be mounted on a rigid plate and a torque shall be applied progressively to the mating thread at a rate of (1 f 0,l) N.m/s until the value specified by the technical specification is reache
19、d. This value shall be maintained for 1 min.- 5.2 Requirements - At the end of the last phase, prior to removal, check that there is no play between assembled parts, - Measurement of the untightening torque which shall comply with the requirements of the technical specification. - After removal, the
20、 specimen shall be examined visually as per test EN 2591-Al. No deformation on any constituent part of the accessory shall be observed. 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-,-
