SAE ARP 5724-2013 Aerospace - Testing of Electromechanical Actuators General Guidelines For《航空航天 机电制动器测试通用导则》.pdf

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5、ctromechanical Actuators, General Guidelines For RATIONALEThe test methodologies applicable to Electromechanical Actuators (EMAs) require considerations unique to EMAs for certain requirements and tests, as compared to conventional hydraulic servoactuators or electrohydrostatic actuators. This ARP s

6、atisfies the need for such a document which discusses such tests specific to EMAs, and recommends test methodologies unique to EMAs.TABLE OF CONTENTS 1. SCOPE 31.1 Purpose . 31.2 Field of Application 32. REFERENCES 32.1 Applicable Documents 32.1.1 SAE Publications . 42.1.2 ASTM Publications 42.1.3 R

7、TCA Publications 42.1.4 Military Specifications . 42.2 Definitions . 43. ELECTROMECHANICAL ACTUATORS - TEST CONSIDERATIONS 63.1 System Considerations . 63.2 Component Considerations 63.2.1 Power Drive Electronics (PDE) . 63.2.2 EMA Mechanical Components 73.3 Test Fixture and Setup Considerations 73.

8、3.1 Instrumentation . 73.3.2 Electric Power Supply . 84. ELECTROMECHANICAL ACTUATORS - TESTS, THEIR SCOPE, AND METHODOLOGY . 84.1 Unit Integration Tests 84.1.1 Performance Tests 94.1.2 Thermal Tests . 94.1.3 Failure Transients . 94.2 Acceptance Tests . 94.2.1 Examination of Product . 94.2.2 Software

9、/Firmware Version Verification 94.2.3 Weight . 94.2.4 Performance Tests 94.2.5 Electrical Tests 164.2.6 Environmental Stress Screening. 17SAE INTERNATIONAL ARP5724 Page 2 of 25 4.2.7 Secondary Load Path Tests 174.2.8 Electric Brake Tests 184.2.9 Other Device and Function Tests . 194.3 Qualification

10、Tests. 194.3.1 High Temperature Performance . 194.3.2 Low Temperature Performance 194.3.3 Dynamic Characteristics . 204.3.4 Dynamic Stiffness . 204.3.5 Static Structural Stiffness 204.3.6 Failure Transients . 204.3.7 Functional Tests 204.3.8 Duty Cycle Tests . 204.3.9 Endurance Test . 214.3.10 Fatig

11、ue Test 224.3.11 Electrical Power Up Endurance 224.3.12 Limit Load 234.3.13 Ultimate Load 234.3.14 Environmental Tests . 234.3.15 Electrical Tests 244.3.16 Magnetic Effects 254.3.17 Highly Accelerated Life Test (HALT) 255. NOTES 25SAE INTERNATIONAL ARP5724 Page 3 of 25 1. SCOPE This document provide

12、s an overview of the tests, and issues related to testing, that are unique to Electromechanical Actuators (EMAs). The tests, and issues documented, are not necessarily all-inclusive. This document discusses both the tests applicable to EMAs and the test methodologies to accomplish the test objective

13、s. EMAs may be used in a wide variety of applications such as utility, secondary flight controls and primary flight controls, in a wide variety of markets including manned and unmanned civil and military aircraft, small missile fin and thrust vector control applications up to high powered utility an

14、d flight controls. EMAs may also have either a rotary or a linear output, be servo controlled or use simple open loop point-to-point or other control topologies. As such this document covers a wide range of potential applications, the application of any given test requirement is determined by the ap

15、plication and the user. This document attempts to provide basic guidance on which tests should be considered for various applications. This document also lists tests that are not unique to EMAs, but are still applicable to EMAs. In these instances a discussion of such tests is not contained in this

16、document, and as applicable, the reader may reference the appropriate documents as indicated in the text. While many EMA configurations include digital power drive electronics (PDE), the specific tests required for the electronic hardware, software, or firmware are outside the scope of this document

17、. 1.1 Purpose The purpose of this document is to facilitate the generation of test specifications, plans and procedures for EMAs. It covers unit integration tests, acceptance tests, and qualification tests.The tests and test methodologies discussed in this document, while not necessarily all inclusi

18、ve, are also not to be construed as mandatory. They are advisory, with the user bearing the responsibility to ensure that all relevant specification requirements for the users equipment are met by the test specifications and procedures generated, and that they preclude any undesirable over testing.

19、1.2 Field of Application This document focuses on EMA issues irrespective of the application of the EMA - whether military or commercial. It shall be the procuring agencies responsibility to ensure that particular qualification or certification requirements, or applicable specifications, standards o

20、r regulations for the intended application are satisfied by the EMA design, and the tests and test methods that are developed. 2. REFERENCES 2.1 Applicable Documents The following publications form a part of this document to the extent specified herein. The latest issue of SAE publications shall app

21、ly. The applicable issue of other publications shall be the issue in effect on the date of the purchase order. In the event of conflict between the text of this document and references cited herein, the text of this document takes precedence. Nothing in this document, however, supersedes applicable

22、laws and regulations unless a specific exemption has been obtained. SAE INTERNATIONAL ARP5724 Page 4 of 25 2.1.1 SAE Publications Available from SAE International, 400 Commonwealth Drive, Warrendale, PA 15096-0001, Tel: 877-606-7323 (inside USA and Canada) or 724-776-4970 (outside USA), www.sae.org.

23、ARP1281 Actuators: Aircraft Flight Controls, Power Operated, Hydraulic, General Specification For ARP4058 Actuators: Mechanical, Geared Rotary, General Specification For ARP4255 Electrical Actuation Systems for Aerospace and Other Applications ARP4386 Terminology and Definitions for Aerospace Fluid

24、Power, Actuation and Control Technologies ARP5007 Development Process - Aerospace Fly-By-Wire Actuation System ARP5311 Aerospace-Interface Definition for Mechanical Actuation Subsystems 2.1.2 ASTM Publications Available from ASTM International, 100 Barr Harbor Drive, P.O. Box C700, West Conshohocken

25、, PA 19428-2959, Tel: 610-832-9585, www.astm.org.ASTM D149 Standard Test Method for Dielectric Breakdown Voltage and Dielectric Strength of Solid Electrical Insulating Materials at Commercial Power Frequencies 2.1.3 RTCA Publications Available from RTCA, Inc., 1150 18th Street, NW, Suite 910, Washin

26、gton, DC 20036, Tel: 202-833-9339, www.rtca.org.RTCA DO-160 Environmental Conditions and Test Procedures for Airborne Equipment 2.1.4 Military Specifications Available from DLA Document Services, Building 4/D, 700 Robbins Avenue, Philadelphia, PA 19111-5094, Tel: 215-697-6396, http:/quicksearch.dla.

27、mil/.MIL-STD-810 Environmental Engineering Considerations and Laboratory Tests2.2 Definitions The primary source for terminology and definitions used herein is ARP4386. LOAD: Is defined as force applied to the output of a linear actuator or as the torque applied to the output of a rotary actuator. S

28、ince EMAs may have either linear or rotary outputs the term load shall be used throughout this document to represent either force or torque as applicable to the application. FREEPLAY: Is defined as either the axial unrestrained motion of a linear output device or the rotational unrestrained motion o

29、f a rotary output device. ENDPLAY: Is defined as the output axial unrestrained motion of a linear output device measured between two equal and opposite force loads of sufficient magnitude to seat all bearings within the load path, but sufficiently low to allow elastic deformations of the actuator st

30、ructure and bearings to be ignored. In some cases endplay requirements are applied to the output of a rotary device, these loads shall be applied axially as defined above. ROTARY BACKLASH: Is defined as the output rotational unrestrained motion of a rotary output device measured between two equal an

31、d opposite torque loads of sufficient magnitude to take up all transmission freeplay within the load path, but sufficiently low to allow elastic deformations of the actuator structure and bearings to be ignored.SAE INTERNATIONAL ARP5724 Page 5 of 25 UNIT INTEGRATION TESTS: These tests are designed t

32、o subject the EMA to a series of tests to verify that the EMA and PDE sub-system functions per its design requirements. These tests may be limited to functional verification at a relatively higher level, or could include lower level performance verification. These tests generally precede formal qual

33、ification tests, and are not counted as a part of the formal qualification. These tests are performed in accordance with a specific test procedure, typically referred to as the Integration Test Procedure or ITP. These tests are typically performed once on each design, they may be repeated if determi

34、ned to be needed based on changes to the hardware or to the requirements during the test program. ACCEPTANCE TESTS: These tests are designed to subject the EMA to a series of examinations, inspections and tests to verify that a subset of key physical and performance parameters meets the EMA design r

35、equirements and that they are consistent with the performance characteristics of the qualification and integration units providing evidence the unit is acceptable for use. These tests are generally conducted at laboratory ambient conditions though other environmental conditions may be specified. The

36、se tests are performed in accordance with an approved specific test procedure, typically referred to as the Acceptance Test Procedure or ATP. These tests may be defined in the detail specification or developed during the detail design phase. These tests are performed on each assembly, new or repaire

37、d, prior to shipment to the customer. The terms Factory Acceptance Test (FAT), Production Acceptance Test (PAT) and Performance and Acceptance Test (PAT), are sometimes used to describe the acceptance tests QUALIFICATION TESTS: These tests, designed to verify flight worthiness of the EMA design and

38、construction, subject the EMA to a series of tests to verify that the EMA meets all its performance and life requirements, over all extremes of ambient and other requirements. These tests constitute a verification of the entire set of design requirements. The term Verification tests is also used som

39、etimes to describe the Qualification tests. These tests are performed in accordance with an approved specific test procedure, typically referred to as the Qualification Test Procedure or QTP. These tests are typically performed once on each design, they may be repeated if determined to be needed bas

40、ed on changes to the hardware or to the requirements during the test program. Note that the procuring agency may define a specific portion of the qualification tests and part of the endurance test as a “Flight Worthiness“ or “Safety-of-Flight” tests. This is done when test schedules preclude complet

41、ion of the qualification test prior to first flight in the intended platform. Successful completion of the tests allow the actuator to be flown on the platform prior to the completion of the qualification test. Depending on the criticality of the actuator, ten to twenty-five percent of the endurance

42、 tests may be specified by the procuring activity along with other tests such as proof and ultimate tests. The description of these tests is the same as for the associated qualification tests except for duration. SYSTEM INTEGRATION TESTS: These tests include control system integration and aircraft s

43、ystem integration. Control system integration tests are usually performed by the equipment manufacturer and include all tests required to verify the EMA, PDE, and Control Electronics (CE) perform properly as a control actuation sub-system. Aircraft system integration tests are usually performed by t

44、he aircraft manufacturer and include all tests required to verify the control actuation sub-system performs properly with the rest of the aircraft structure, flight control system, power generation system, etc. Specifics of system integration tests are outside the scope of this document. These tests

45、 are typically performed once on each design, they may be repeated if determined to be needed based on changes to the hardware or to the requirements during the test program. FUNCTIONAL PERFORMANCE TESTS: Throughout all qualification testing, similar to a conventional flight control servoactuator, i

46、t is important that the operation of the EMA be periodically verified for acceptable operation and performance, to preclude the possibility of unacceptable degradation or failure. These tests are frequently referred to as Functional Performance Tests or FPT and are typically a sub-set of the ATP, th

47、ough in some cases may include additional tests if required. These tests are typically repeated many times during the course of Integration and/or Qualification Testing. SAE INTERNATIONAL ARP5724 Page 6 of 25 3. ELECTROMECHANICAL ACTUATORS - TEST CONSIDERATIONS 3.1 System Considerations The performa

48、nce of many EMA configurations is heavily dependent upon the associated electronics, both the power drivers for the electric motor, as well as the various control loop closures. Some applications employ either brush DC motors or AC induction motors and, therefore, may not include electronics. For ap

49、plications where power drive electronics and loop closure electronics are required, the EMA by definition includes the power drive electronics (PDE), whether mounted locally on the actuator itself, or at a remote location, reference ARP4386. The control electronics (CE) by definition are not a part of the EMA. While this definition of an EMA facilitates isolation of the discussion of the critical EMA elements involved in power transmission, p