1、BRITISH STANDARD BS 2G 143: 1965 Incorporating Amendment No. 1 Specification for A.C. and D.C. rotary and linear actuators for aircraft UDC 629.13.066:621-54:621.313.13:621.833BS2G 143:1965 This British Standard, having been approved by the AircraftIndustry Standards Committeeand endorsed by theChai
2、rman of the EngineeringDivisional Council,was published undertheauthority of the GeneralCouncil of the Institutionon 14 April 1965 BSI 12-1999 The following BSI references relate to the work on this standard: Committee reference ACE/42 Draft for comment A(ACE)3019 ISBN 0 580 34090 2 Amendments issue
3、d since publication Amd. No. Date of issue Comments 5773 February 1966 Indicated by a sideline in the marginBS2G 143:1965 BSI 12-1999 i Contents Page Foreword iii 1 Scope 1 2 Definitions 1 Section 1. General requirements 3 Types of actuator 1 4 General construction 1 Section 2. Particular requiremen
4、ts 5 Arrangement and construction 1 6 Rating 2 7 Enclosure 2 8 Fixing attachments 2 9 Motor 2 10 Brake 2 11 Clutch 3 12 Gears 3 13 Ram 3 14 Limit switches 3 15 Limit stops 3 16 Special features 3 17 Jamming 3 18 Over-run, and variations of stroke 3 19 Static load 3 20 Limits of temperature and press
5、ure 3 21 Terminal arrangement 4 22 Vibration, acceleration, climatic proofing flame-proofing and resistance to fluids 4 23 Fire resistance 4 24 Waterproofing 4 25 Radio interference 4 26 Compass interference 4 27 Declaration of performance 4 28 Name plate 4 Section 3. Tests 29 General 4 30 Initial c
6、heck 5 31 High voltage test 5 32 Insulation resistance test 5 33 Performance tests on complete unit 5 34 Over-run and variations in stroke 6 35 Endurance tests 6 36 Vibration test 7 37 Climatic test 7 38 Heating tests 7 39 High temperature functioning tests 7 40 Static load tests 7 41 Stalling test
7、8 42 Low temperature functioning test 8 43 High altitude test 8BS2G 143:1965 ii BSI 12-1999 Page 44 Operation without limit switches 8 45 Acceleration test 8 46 Waterproof test 9 47 Explosion-proofness test 9 48 Fire-resistance test 9 49 Radio interference test 9 50 Compass interference test 9 51 Pe
8、rformance tests on motors 9 52 Dimensional check for wear 9 53 Component check 9 54 Dimensional check 9 55 Short endurance test 9 56 High voltage test 9 57 Performance tests 10 58 Travel tolerance test 10 59 Clutch setting test 10 60 Selection of samples 10 61 Performance tests 10 62 Text deleted 11
9、 63 Insulation resistance test 11 64 Overtravel test 11 65 Endurance test 11 66 Vibration test 11 67 Low temperature functioning test 11 68 Dimensional check for wear 11BS2G 143:1965 BSI 12-1999 iii Foreword The major change in this revision of BSG143:1953, is the introduction of requirements for ac
10、tuators operating on an a.c. supply. The other changes occur principally in the details of the test procedure. These result from the removal of arbitrary differences between the requirements of the British Standard and those of the Ministry of Aviation Specification EL. 1618 to achieve, as far as pr
11、acticable having regard to their different applications, common requirements between the two specifications. Reference is made in the standard to the following British Standards: BS 2G 100, General requirements for electrical equipment and indicating instruments for aircraft. BS G., General requirem
12、ents for rotating electrical machines for aircraft 1) . BS G 146, D.C. motors for aircraft. BS G 147, A.C. motors for aircraft. BS 436, Machine cut gears. A. Helical and straight spur. BS 545, Bevel gears (machine cut). BS 721, Worm gearing. BS 2059, Straight-sided splines and serrations. NOTEWhere
13、metric equivalents are stated, the figures in British units are to be regarded as the standard. The metric conversions are approximate. More accurate conversions should be based on the tables in BS350, “Conversion factors and tables”. A British Standard does not purport to include all the necessary
14、provisions of a contract. Users of British Standards are responsible for their correct application. Compliance with a British Standard does not of itself confer immunity from legal obligations. Summary of pages This document comprises a front cover, an inside front cover, pages i to iv, pages1to 11
15、and a back cover. This standard has been updated (see copyright date) and may have had amendments incorporated. This will be indicated in the amendment table on the inside front cover. 1) In course of preparation.iv blankBS2G 143:1965 BSI 12-1999 1 1 Scope This British Standard covers the general de
16、sign and test procedure for electrically-operated a.c. and d.c. rotary and linear actuators for use in aircraft. It is intended to be read in conjunction with BS2G100 and G. 2) . 2 Definitions For the purposes of this British Standard the following definitions apply: 2.1 linear actuator a device pro
17、viding linear motion over a distance determined by limit switches mounted either in the actuator or on the actuator device, against tensile or compressive loads and consisting basically of an electric motor and reduction gearing, together with a screw jack or rack and pinion 2.2 rotary actuator a de
18、vice providing rotary motion over a distance determined by limit switches mounted either in the actuator or on the actuated device, and consisting basically of an electric motor and reduction gearing 2.3 cycle of operation travel of the actuator in one direction followed by equal travel in the oppos
19、ite direction 2.4 stroke full travel of the actuator in either direction 2.5 load either the force in pounds on a linear actuator or the torque in pound inches on a rotary actuator 2.6 rated load the working load of the actuator at its rated speed 2.7 maximum load the maximum working load of the act
20、uator irrespective of speed 2.8 stalling load the maximum load at which the actuator motor will start 2.9 static load the maximum permissible loading of the actuator as a stressed member NOTEMinimum stalling load is not less than twice rated load. Maximum load is not more than one and a half times r
21、ated load. Minimum clutch slipping load is not less than 1 7 / 8rated load. Section 1. General requirements 3 Types of actuator Four types of actuator are covered by this BritishStandard, as follows: Type A, with a performance as declared over a terminal voltage range of23.5 to28.5 volts d.c. on a n
22、ominal28V d.c. supply, but capable of operation at reduced speed at rated load down to 22volts. Type B, suitable for operating over a terminal voltage range of18 to28.5 volts d.c. on a nominal28V d.c. supply. (This covers additionally the conditions of battery operation, including those of heavy dis
23、charge.) Type C, suitable for operation on a three-phase a.c. supply with a frequency of 400 c/s 5 per cent over a terminal voltage range of 185 to 205 volts. Type D, suitable for operation on a single-phase a.c. supply with a frequency of 400 c/s 5 per cent over a terminal voltage range of 105 to 1
24、19 volts. 4 General construction The design and construction of the actuator shall be in accordance with the relevant requirements of BS 2G 100 and G. 3) . The number and frequency of operations shall be stated in the individual specification. Section 2. Particular requirements 5 Arrangement and con
25、struction a) The overall dimensions and offset weight of the actuator shall be kept to a minimum. b) Linear actuators shall preferably be designed with the motor and screw jack axes in line or with the motor offset, i.e. with the motor axis to the side of, and parallel with, the line of motion of th
26、e ram. NOTEThe in-line type of actuator has been found to be preferable for use under conditions of severe vibration, e.g.power plants. c) All parts of the actuator, i.e. brake, clutch, gears, screw, etc., shall be capable of being dismantled for maintenance. 2) In course of preparation 3) “General
27、requirements for rotating electrical machines for aircraft” (in course of preparation).BS2G 143:1965 2 BSI 12-1999 d) For actuators the continuous functioning of which is vital to the safety of the aircraft and for which more than one motor is provided, the design shall be such that in the event of
28、one motor failing the other will take up the drive without the operation of contactors. Both motors may normally share the load, but each of them shall be capable of continuing to drive the load at an appropriate reduced speed when the other fails. 6 Rating a) The rated speed of the actuator at 20 5
29、 C and nominal voltage and rated load shall be as required by the individual specification. b) The rated load at the nominal voltage, and the time rating of the actuator at this load for the declared maximum ambient temperature and minimum pressure, shall be as required by the individual specificati
30、on. Any limitation of the frequency of operation shall be stated. c) At rated load and at nominal voltage, and with all parts of the actuator at the declared maximum ambient temperature, it shall be possible: i) for actuators used on manual control to perform, at a steady speed, three full stroke cy
31、cles of operation consecutively; ii) for actuators used on automatic control to perform one full stroke followed by one hour of continuous inching cycling at the declared operating frequency, without damage or overheating, whether the load applied during each cycle puts the actuator in tension or co
32、mpression. d) The stalling load of the actuator at nominal voltage and at an ambient temperature of 20 5 C, with the clutch, if any, inoperative, shall be not less than twice the rated load. e) At maximum load and at nominal voltage at the declared maximum ambient temperature and with all parts of t
33、he actuator at that temperature, the actuator shall be capable of performing one full stroke cycle of operation without damage or over-heating. The maximum load shall be not more than75per cent of the stalling load. The speed during these operations is not stipulated, but it shall be steady. f) The
34、maximum and minimum times taken by the actuator in making a stroke shall be declared by the manufacturer. The time shall be within this range under all conditions of load from rated load opposing to rated load assisting with nominal voltage and at20 5 C. 7 Enclosure a) The actuator shall be enclosed
35、 to prevent the ingress of foreign matter, and provided with drain holes when necessary. b) All joints shall be sealed. NOTE 1Sealing does not obviate the necessity for using climate-proof components. NOTE 2Unless specifically required, electrical bonding of the various parts of the actuator is not
36、necessary. 8 Fixing attachments a) Rotary actuators. Rotary actuators shall be provided with means to take up torque reaction, preferably by flange mounting the actuator at the driving end. The output shaft, if serrated, shall be in accordance with BS 2059. b) Linear actuators. i) To prevent undesir
37、able couples and bending moments being applied, the means of attachment shall be so arranged that the line of application of the load always coincides with the axis of the ram. ii) Any end attachments fitted to the actuator shall embody a joint permitting an angular movement of not less than three d
38、egrees at right angles to the working plane to allow of misalignment between the anchorage and the axis of the actuator. At the moving end the working pivot, if provided, shall have a self-aligning bearing. iii) Unless otherwise specified, provision shall be made for adjusting the length between the
39、 centres of the actuator, without alteration of limit switch settings, to ensure correct matching of the relative parts. NOTEThe recommended amount of the adjustment is ! in(6.35mm). 9 Motor The motor shall comply with the requirements of BS2G 100 and G. 4) . The actuator should also preferably be d
40、esigned to incorporate a motor complying with BS G 146 or BS G 147, as appropriate. 10 Brake If a brake is fitted, it shall not engage when the motor is energized under any condition of operation of the actuator, unless specifically designed and approved for such operation. 4) “General requirements
41、for rotating electrical machines for aircraft” (in course of preparation).BS2G 143:1965 BSI 12-1999 3 11 Clutch If an overload clutch is fitted, it shall, unless otherwise specified, be set to slip at a suitable value of load between maximum load and stalling load under any working condition of term
42、inal voltage and ambient temperature. The clutch shall be capable of operating at the slipping load for a period of20seconds, or such other period as may be approved, without over-heating or damage. 12 Gears The design of the gear train shall be such that backlash between gears and the effects of vi
43、bration due to tooth impact are reduced to a minimum. The gears should preferably conform to the Class A limits and tolerances of BS 436, BS 545 or BS 721. 13 Ram In a linear actuator the ram shall generally be designed to eliminate torque reaction from the end mountings. In exceptional cases, howev
44、er, when torque reaction on the structure is acceptable, the maximum reaction of the actuator shall be declared. 14 Limit switches a) Limit switches shall be of robust construction and of snap action and should be so arranged that they are positively operated by the ram, operating shaft or the actua
45、ted device. They shall be pre-set and sealed against unauthorized adjustment. Facilities shall be provided for easy access to the switches for inspection. b) Limit switches associated with three-phase a.c. actuators shall open two lines simultaneously. Limit switches for actuators whose function is
46、vital to the safety of the aircraft should preferably interrupt the supply directly. c) The design of the switches and of their mounting shall be such that there is no possibility of the switches being set outside the mechanical limits of movement of the ram or shaft. 15 Limit stops Means shall be p
47、rovided, either in the actuator or actuated device, to prevent mechanical damage or malfunctioning in the event of limit switch failure. This protection may be in the form of additional limit switches connected electrically in series with the normal ones or of built-in mechanical stops. 16 Special f
48、eatures Any special features or devices incorporated in the actuator shall be the subject of an approved specification. Special features or devices shall be declared by the manufacturer. 17 Jamming When required by the individual specification, the actuator shall be capable of freeing itself and sha
49、ll not become inoperative, other than temporarily, when driven to a mechanical stop in either direction with rated load assisting and at maximum test voltage (and frequency). For actuators which must necessarily operate in an emergency, e.g. fuel cock actuators, it is essential that the actuator shall be capable of performing its normal operation without delay, even at the risk of becoming permanently inoperative. It shall be demonstrated that under the most adverse conditions such actuators would not constitute a risk of fire or explosion in the aircraft. 18 Ov
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