AECMA PREN 2794-001-1994 Aerospace Series Circuit Breakers Single-Pole Temperature Compensated Rated Currents 20 A to 50 A Part 001 Technical Specification Edition P 1《航天系列断路器 单杆 .pdf

《AECMA PREN 2794-001-1994 Aerospace Series Circuit Breakers Single-Pole Temperature Compensated Rated Currents 20 A to 50 A Part 001 Technical Specification Edition P 1《航天系列断路器 单杆 .pdf》由会员分享，可在线阅读，更多相关《AECMA PREN 2794-001-1994 Aerospace Series Circuit Breakers Single-Pole Temperature Compensated Rated Currents 20 A to 50 A Part 001 Technical Specification Edition P 1《航天系列断路器 单杆 .pdf（6页珍藏版）》请在麦多课文档分享上搜索。

1、CEN PREN*2794- 001 94 3404587 0064272 204 M Edition approved for publication 1994-06-30 AECMA STANDARD NORME AECMA AECMA NORM C2 Chairman M. Le Cunff Comments should be sent within six months after the date of publication to AECMA Technopolis - 175, rue Jean-Jacques Rousseau 921 38 Issy-les-Moulinea

2、ux Cedex - FRANCE prEN 2794-001 Edition P 1 June 1994 DIT PAR LASSOCIATION EUROPENNE DES CONSTRUCTEURS DE MATRIEL AROSPATIAL Technopolis - 175, rue Jean-Jacques Rousseau - F-92138 Issy-les-Moulineaux Cedex - Tl. (1) 47.36.98.76 UDC : 621.31 6.57:629.7 Descriptors : Aircraft industry, aircraft equipm

3、ent, circuit breaker, manufacturing requirements, designation, marking ENGLISH VERSION Aerospace series Circuit breakers, single-pole, temperature compensated, rated currents 20 A to 50 A Part O01 : Technical specification Srie arospatiale Disjoncteurs unipolaires compenss en temprature, intensits n

4、ominales 20 A 50 A Partie O01 : Spcification technique Luft- und Raumfahrt Temperaturkompensierte einpolige Schutzschalter, Nennstrme von 20 A bis 50 A Teil O01 : Technische Lieferbedingungen This “Aerospace Series“ Prestandard has been drawn up under the responsibility of AECMA (Association Europen

5、ne des Constructeurs de Matriel Arospatial). It is published on green paper for the needs of AECMA-Members. It has been technically approved by the experts of the concerned Technical Committee following comment by the Member countries. Subsequent to the publication of this prestandard, the technical

6、 content shall not be changed 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 the Member countries it

7、will be submitted as a draft European Standard to CEN (European Cornmittee for Standardization) for formal vote. Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMA Not for ResaleNo reproduction or networking permitted without license fr

8、om IHS-,-,-CEN PREN*Z774- O03 94 m 3404587 0064373 140 m Rated currents (In) A Code Range Page 3 prEN 2794-001 : 1994 20 25 30 35 40 45 50 20A 25 A 30A 35 A 40A 45A 50A Low Medium High 1 Scope Button marking This standard specifies the required characteristics for single-pole temperature compensated

9、 circuit breakers with rated currents from 20 A to 50 A for use in aircraft electrical systems, at a temperature between - 55 OC and 125 OC and at a maximum altitude of 2 = 15 O00 m. It shall be used together with EN 2350. These circuit breakers are for use in aircraft with power supplies in accorda

10、nce with EN 2282. 20 25 30 35 40 45 50 2 Normative references IS0 7137 : 1987 Aircraft - Environmental conditions and test procedures for airborne equipment (Endorsement of EUROCAE/EDI 48 and RTCA/DO-l60B) Aerospace series - Characteristics of aircraft electrical supplies Aerospace series - Circuit

11、breakers - Technical specification procedure EN 2282 EN 2350 EN 3042 Aerospace series - Quality assurance - EN aerospace products - Qualification 3 Definitions See EN 2350. 4 Description These circuit breakers are operated by a push-pull control button with trip free release, and delayed tripping ;

12、they are explosion-proof. Their function is assured up to the short-circuit current. 5 Required characteristics Rated currents (In) and voltage See tables 1 and 2. Table 1 1) Range in accordance with 6.1 .I of EN 2350 Table 2 I 28 V d.c. 26 V a.c., frequency 400 Hz, single phase 115 V a.c., frequenc

13、y 400 Hz, Voltage of aircraft electrical system single phase Previous page is blank Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMA Not for ResaleNo reproduction or networking permitted without license from IHS-,-,-CEN PRENr2794- O01

14、 94 3404589 0064174 087 Characteristics Closing force Page 4 prEN 2794-001 : 1994 Requirements 3,5 N to 55 N If an aircraft electrical power supply of variable frequency is used, the limit values (voltage and frequency) shall be specified, in accordance with EN 2282. characteristics Vibration I): cu

15、rve R, IS0 7137 Mechanical shock 1) Centrifugai acceleration 1) Sand and dust Corrosion Humidity 6 Tests Requirements 5 Hz to 54 Hz, constant amplitude 2 a = 0,51 mm 54 Hz to 2000 Hz, constant acceleration 29,43 m/s2 (= 3 g) 245,25 m/s2 (= 25 g), 11 ms 166,8 m/s2 (= 17 g) See EN 2350 See EN 2350 See

16、 EN 2350 Category B : 10 cycles 6.1 Mechanical tests Contamination by liquids See EN 2350 Mechanical strength Opening force Transverse load Actuation component Pull direction Attachment Tensile strength Compression strength Main connections 5Nto40N I I IO N minimum I 185 N minimum along FI 90 N mini

17、mum along F2 1) See product standard Environmental tests 6.2 Explosion-proof ness Short-circuit current I Voltage 1 15/200 V, 400 Hz Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMA Not for ResaleNo reproduction or networking permitte

18、d without license from IHS-,-,-CEN PRENx2794- 001 94 = 3404589 0064175 TL3 Characteristics Voltage drop at rated current Page 5 prEN 2794-001 : 1994 Requirements See table 6 6.3 Electrical tests See tables 5 to 12 and 5.5 of EN 2350 1 500 V on ground t = (23 f 5) OC t = (- 55 * 5) oc t = (125 f 5) O

19、C Table 5 - Electrical characteristics Leakage current I 1 mA No flashover, no damage Overload tripping Trip free operation Insulation resistance See table 8 See table 8, at 23 OC only I Minimum 100 MR - 55 Ambient Dielectric strength 105 % of In _ Service life at no load and with load Service life

20、under overload trip conditions 400 V at 15 O00 m t = (23 +. 5) OC See table 10 See table 11 Upper and lower trip limits Overload test with mechanism locked See table 7 See table 12 20 25 30 35 40 45 Rated current A 50 No tripping Maxim um V voltage drop 1) 0,15 temperature 105 % of In OC 80 % of In

21、0,12 Short-circuit performance 1 Rated current A See table 9 Temperature +. 5 OC Load as % of In Minimum 1 h I Maximum 5 1 h 20 to 50 23 110 145 - 55 110 165 70 125 1) The voltage drop is not measured at minimum current 105 145 90 145 Copyright Association Europeene des Constructeurs de Materiel Aer

22、ospatial Provided by IHS under license with AECMA Not for ResaleNo reproduction or networking permitted without license from IHS-,-,-CEN PRENr2794- 001 94 3404589 0064376 95T Temperature I5 oc Page 6 prEN 2794-001 : 1994 Overload as % of rated current 200 I 5 O0 I 1 O00 Table 8 - Overload tripping t

23、imes Rated voltage 115 V a.c., frequency 400 Hz 28 V d.c. I Tripping times in s Open circuit voltage Fault current establishment time In of circuit breaker 3 to 40 to (30 t 2) V 2 ms to 10 ms 20 A to 50 A (120 I 5) v 2 ms to 5 ms 20 A to 50 A 0,045 to 0,8 Test current and circuit calibration 1) Test

24、 altitude Table 9 - Short-circuit performance Product standard Product standard Ground I 15000m Ground I 15000m L/R 1 ms 0,8 I cos cp 1 Circuit characteristics In 20 A to 50 A 11 5 V a.c., frequency 400 Hz Open circuit 28 V d.c. Close At In resistive At In inductive At In inductive open (M) 1) (MI 1

25、) 5 O00 2 500 2 500 2 500 + (M) I) L/R = 5 ms 0,6 I cos p I0,7 I t = (23=+05) OC I Number of samples per range I 1 I 1 I 1 I 1 E = 15 O00 m t = (23 f 5) OC of tests CO 2) oco 2) (28 I 1,4) V d.c. 1) See product standard 2) For CO and OCO, see EN 2350 I= 51n 15 cycles CO 20 cycles CO 1) L/R = 5 ms 15

26、 cycles OCO 1) Table 10 - Service life at no load and with load I Number of cycles to be performed 1 Z=5In frequency 400 Hz I 0,6 I cos cp I0,7 (1 15 f 5,751 V ax., 15 cycles CO 20 cycles CO 1) 15 cycles OCO 1) 1) Tests marked (M) shall be preceded by a no-load mechanical endurance test. NOTE : Tole

27、rance for voltage, current and frequency values : f 5 %. Table 11 - Service life under overload trip conditions I Test conditions I I I 1) For CO and OCO, see EN 2350. Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMA Not for ResaleNo

28、reproduction or networking permitted without license from IHS-,-,- CEN PRENu2794- 001 94 3404589 0064L77 896 Page 7 prEN 2794-001 : 1994 Table 12 - Overload test with mechanism locked The circuit breaker shall be connected to cable with section to EN 2350 with length of 0,5 m without strains Loads 1

29、 O x In and short-circuit current (Zsc) V = 115 V a.c. Opening time 10 x In 8 s zsc 1 s Opening of circuit by destruction of circuit breaker without production of flames or excessive smoking Requirement I NOTE : Test performed with mechanism locked, simulating jamming of contacts, without direct int

30、ervention on thermocouple. 7 Quality assurance See EN 3042 Sampling plan : see EN 2350 8 Designation See product standard 9 Marking See EN 2350. Copyright Association Europeene des Constructeurs de Materiel Aerospatial Provided by IHS under license with AECMA Not for ResaleNo reproduction or networking permitted without license from IHS-,-,-