1、AECMA STANDARD NORME AECMA AECMA NORM prEN 2285 Edition P 1 March 2002 PUBLISHED BY THE EUROPEAN ASSOCIATION OF AEROSPACE INDUSTRIES - STANDARDIZATION (AECMA-STAN) Gulledelle 94 - 6-1200 BRUXELLES - Tel. (+32) 2 775 81 1 O - Fax. (+32) 2 775 81 11 ICs: ENGLISH VERSION Aerospace series Bushes, plain
2、aluminium alloy with self-lubricating liner Dimensions and loads Will supersede EN 2285: 1989 Srie arospatiale Luft- und Raumfahrt Bagues cylindriques en alliage daluminium garniture autolubrifiante Dimensions et charges Buchsen ohne Flansch aus Aluminiumlegierung mit selbstschmierender Beschichtung
3、 MaRe und Belastungen This Herospace Series” frestandard has been drawn up under the responsibility of AECMA-STAN (The European Association of Aerospace industries - Standardization). It is published on green paper for the needs of the European Aerospace Industry. It has been technically approved by
4、 the experts of the concerned Domain following member comments. Subsequent to the publication of this Prestandard, the technical content shall not be changed to an extent that interchangeability is affected, physically or functionally, without re-identification of the standard. Affer examination and
5、 review by users and formal agreement of AECMA-STAN it will be submitted as a draft European Standard to CEN (European Committee for Standardization) for formal vote. I Nota - Extra copies can be supplied by B.N.A.E. - Technopolis 54 - 199, nie Jean-Jacques Rousseau - 92138 ISSY-LES-MOULINEAUX CEDEX
6、 I Edition approved for publication I Comments should be sent within six months I Mechanical Domain 2002-03-29 after the date of publication to Gulledelle 94 AECMA-STAN Mr Feltham B-1200 BRUXELLES aecma 20( Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS und
7、er license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Page 2 prEN 2285: 2002 Contents Page 3 Normative references . 3 Required characteristics . . 3 Designation . 6 6 Technical specification 6 7 Copyright Association Europeene des Constructeurs de Ma
8、teriel Aerospatial Provided by IHS under license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Page 3 prEN 2285: 2002 1 Scope This standard specifies the characteristics of plain bushes in aluminium alloy with self-lubricating liner and the design recom
9、mendation of shafts and housings. The bushes are intended for operation within the temperature range of - 55 OC to 163 OC and assembly with an interference fit into fixed and moving aerospace parts. 2 Normative references This European Standard incorporates by dated or undated reference, provisions
10、from other publications. These normative references are cited at the appropriate places in the text and the publications are listed hereafter. For dated references, subsequent amendments to or revisions of any of these publications apply to this European Standard only when incorporated in it by amen
11、dment or revision. For undated references the latest edition of the publication referred to applies. EN 2086 EN 2101 EN 2284 EN 2311 EN 2701 EN 2704 3 3.1 Aerospace series - Aluminium alloy AL-P2618A - T851 - Hand forgings - a I 150 mm 1) Aerospace series - Chromic acid anodizing of aluminium and wr
12、ought aluminium alloys Aerospace series - Sulphuric acid anodizing of aluminium and wrought aluminium alloys Aerospace series - Bushes with self-lubricating liner - Technical specification Aerospace series - Aluminium alloy (2024) - Solution treated, water quench, cold worked and naturally aged (T3)
13、 - Drawn tube for structures - 0,6 I a I 12,5 mm 2) Aerospace series - Aluminium alloy 2024-T3511 drawn bar a I 75 mm 2) Required characteristics Configuration - Dimensions - Masses Configuration: according to figure 1. Dimensions, masses: according to figure 1 and table 1. Dimensions apply after su
14、rface treatment. 3.2 Surface roughness According to figure 1. 3.3 Materials Bush: Aluminium alloy according to EN 2086, EN 2701 or EN 2704. Liner: Self-lubricating wear resistant material consistent with the requirements of EN 231 1. 3.4 Chromic acid anodizing according to EN2101A or Sulphuric acid
15、anodizing according to EN2284A. S u rfa c e treatment 1) Published as AECMA Prestandard at the date of publication of this standard 2) Published as AECMA Standard at the date of publication of this standard Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS und
16、er license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Page 4 prEN 2285: 2002 II I -L- Dimensions in millimetres 0,5max. 0,8max. - d ln m8m8 .c al c z- io g.; $5 a 0,50 to0,75 Chamfer machined before bonding I - 0,4 D - 0,l ln 6 8 10 12 15 16 18 20 22
17、 25 28 30 32 35 40 45 50 .G al c =io 5.9 ln z= mE Mass in kgll O00 pieces X x e 0,Bmax. Chamfer or radius at manufacturers option Chamfer machined after bonding Figure I Table 1 Dimensions in millimetres Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under
18、license with AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Page 5 prEN 2285: 2002 dI nm 10 12 15 16 18 *O Table 2 mm 66 6 8- 8 6 8 10 6 8 10 12 8 10 - 12 15 8 10 12 15 16 10 12 - 15 18 10 - - - - - - - - - - - - - 12 Permissible radial load d Static Dynamic
19、cs“ I C2!b 11 kN kN IF 82 12.4 10.3 I -II 9.9 I 8.3 II 19.8 I 16.5 II 25 15,4 24,7 18,5 27,5 22to t- 26,4 33,O 357 42,5 45,l 38,4 1 30 II 27.5 41,2 I 34,3 II I I Permissible radial load 11 d Static Dynamic 1 cs“ 1 C25b 11 mm kN 81,6 68,O 22 90,6 753 I II 12 513 42,9 15 67,O 55,8 I II II 86,5 6215 t-
20、 15 75,O 20 103,8 22 115,4 25 132,7 II 92,7 103,O 28 150,O 15 80,3 20 111,2 22 123,6 -1 144,2 50 II I Permissible radial load 22 I 144.2 I 120.2 I 25 165,8 138,2 30 201,9 168,3 I 40 313,l 260,9 25 213,2 177,7 I 40 352,3 293,6 45 398,5 332,l I 25 236,9 197,4 30 288,4 240,3 I I a C, = 0,206 d (I - 2)
21、kN - Based on a unit pressure of 206 MPa. C C25 = kNl 12 b Definitions of all loads are given in EN 231 1. 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-
22、,-,-Page 6 prEN 2285: 2002 Description block Identity block EN2285-12- ! Without code NOTE 1 The number of characters is constant, Zero (O) is inserted to the lefi of the figure when the diameter d or length I is less than 1 O. NOTE 2 If necessary, the code 19005 shall be placed between the descript
23、ion block and the identity block NOTE 3 Parts manufactured before the issue of this standard shall be accepted without technology code. Both technologies can be used at users convenience Table 3 Technology I code Technology I A I Bonded fabric liner I B Injection moulded liner 5 Marking In addition
24、to the manufacturers own marking, each bush and its package shall be marked with the identity block specified in clause 4 of this standard. The technology used by the manufacturer shall be stated within the identity block. Marking position and method are at manufacturers option and shall not have an
25、y detrimental effect on the bush. Bushes which are too small to be marked with the full information required shall have this on the package only. 6 Technical specification According to EN 231 1. Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license w
26、ith AECMANot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Page 7 prEN 2285: 2002 7 Design recommendation Bushes defined by this standard are intended to be installed by interference fit methods (see figure2). Therefore, the loads given in table 2 can only be ensured
27、 if the following mounting is applied. 3 Key I Shaft 2 Bush 3 Housing a Housing diameter D H7 Sha diameter d f6 Figure 2 Hardness of the shaft: 50 HRC min. Surface roughness of the shaft: according to figure 2. The reduction in bore diameter d (see figure I), due to interference fit of the bush in t
28、he housing, has been taken into account when selecting tolerances for the shaft: f6 (clearance fit). When applied in actual usage, the coefficient of friction under load could be different from that defined in EN 231 I, since it depends on the following shaft definitions: Material, hardness, surface finish, surface treatment and installation conditions. 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-,-,-
