SAE ARP 6154-2017 Aerospace Fluid Power Electrohydrostatic Module Design Performance and Test Recommendations.pdf

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4、0 (outside USA) Fax: 724-776-0790 Email: CustomerServicesae.org SAE WEB ADDRESS: http:/www.sae.org SAE values your input. To provide feedback on this Technical Report, please visit http:/standards.sae.org/ARP6154 AEROSPACE RECOMMENDED PRACTICE ARP6154 Issued 2017-03 Aerospace Fluid Power Electrohydr

5、ostatic Module, Design, Performance and Test Recommendations RATIONALE There is a need for a document that provided design, performance and test requirements for an Electrostatic Module (EHM) that is comparable to existing documents for an Electrohydraulic Servo Valve (ARP490) or a Direct Drive Valv

6、e (ARP4493). This document meets this need. FOREWORD The key component of the existing regular Fly By Wire servo controls are the Electrohydraulic Servovalves (EHSV) which are designed in compliance with ARP490 which defines standard characteristics and interfaces to a level which makes possible to

7、define families of components with significant commonality and to ensure the interchangeability of products from different manufacturers. This level of standardization, while still providing a lot of flexibility, has made possible to keep the cost of EHSV within certain limits. An Electrohydrostatic

8、 Module (EHM) is a key component of an Electrohydrostatic Actuator (EHA) that is comparable to an Electrohydraulic Servovalve (EHSV) or a Direct Drive Valve (DDV) of an Electrohydraulic Servo Actuator (EHSA). UUUEHSVUUMELECTRONICSEHMElectrohydraulic Servo Actuator hydraulic diagram (typical) EHA hyd

9、raulic diagram (typical) Figure 1 - EHSV and EHM hydraulic function comparison SAE INTERNATIONAL ARP6154 Page 2 of 40 TABLE OF CONTENTS 1. SCOPE 4 1.1 Purpose . 4 1.2 Field of Application 4 2. REFERENCES 4 2.1 Applicable Documents 4 2.1.1 SAE Publications . 5 2.1.2 ISO Publications 5 2.1.3 Radio Tec

10、hnical Commission for Aeronautics Documents . 5 2.1.4 U.S Government . 6 2.2 Definitions . 6 2.3 Symbols and Abbreviations 6 3. PROCUREMENT SPECIFICATIONS . 8 3.1 Description and Interfaces 8 3.1.1 Item Definition . 8 3.1.2 Item Functions . 9 3.1.3 EHM Key Design Drivers 9 3.1.4 Interface Definition

11、 10 3.1.5 Hydraulic Requirements 16 3.2 Performance 18 3.2.1 Open Loop Performance . 18 3.2.2 Close Loop Performance 21 3.2.3 Airborne Noise 22 3.2.4 Thermal Performance . 22 3.2.5 Electrical Performance 23 3.3 Stressing and Life . 27 3.3.1 Static Strength . 27 3.3.2 Fatigue Life . 27 3.3.3 Wear Lif

12、e . 28 3.4 Built In Test . 28 3.5 Endurance Spectrum 28 3.6 Corrosion Protection . 29 3.7 Identification and Marking . 29 3.7.1 Identification 29 3.7.2 Marking and Serialization 29 3.8 Lubrication . 30 3.9 Standardized Components . 30 3.10 Maintainability . 30 3.11 Reliability and Safety Requirement

13、s . 31 3.11.1 Reliability . 31 3.11.2 Safety 31 3.12 Electronic Module Hardware, Software / Firmware Requirements . 31 3.13 Weight . 31 4. ENVIRONMENTAL REQUIREMENTS . 32 4.1 General 32 4.2 Hydraulic Fluid Temperature . 32 4.3 Altitude / Pressure . 32 4.4 Vibration 32 4.4.1 Normal Operating Conditio

14、ns 33 4.4.2 Failure Conditions . 33 4.5 Constant Acceleration . 33 4.6 Operational Shocks . 33 4.7 Humidity 34 4.8 Icing . 34 4.9 Salt Spray 34 4.10 Fungus Resistance . 34 SAE INTERNATIONAL ARP6154 Page 3 of 40 4.11 Fluids Susceptibility . 34 4.12 Hydraulic Fluid Contamination 34 4.13 Water Proofnes

15、s . 34 4.14 Sand and Dust 35 4.15 Electromagnetic Environmental Requirements . 35 4.15.1 Lightning Protection 35 4.15.2 High Intensity Radio Frequency (HIRF) 35 4.16 Magnetic Effect . 36 4.17 Electrostatic Discharge Susceptibility (ESD) 36 4.18 Atmospheric Radiation 36 5. TEST REQUIREMENTS . 36 5.1

16、Development Tests . 36 5.1.1 Highly Accelerated Life Tests . 36 5.2 Acceptance Tests 38 5.2.1 Highly Accelerated Stress Screening 38 5.2.2 EHM Acceptance Tests (AT) 39 5.3 Qualification Tests . 40 6. NOTES 40 6.1 Revision Indicator 40 FIGURE 1 EHSV AND EHM HYDRAULIC FUNCTION COMPARISON . 1 FIGURE 2

17、RUN-UP TIME DEFINITION . 18 TABLE 1 EHM TYPICAL RATIONALIZED AND ACCELERATED ENDURANCE SPECTRUM . 29 SAE INTERNATIONAL ARP6154 Page 4 of 40 1. SCOPE This Aerospace Recommended Practice provides general requirements for Electrohydrostatic Module (EHM) that is used in Electrohydrostatic Actuator (EHA)

18、 for aerospace applications. This document includes design, performance and test (production and qualification) requirements. 1.1 Purpose This document is intended to be used as a guide by the EHA manufacturer in preparing a detail specification for a specific EHM application. This document may be r

19、ead in conjunction with ISO 22072 which defines the general characteristics, requirements and design data for an Electrohydrostatic Actuator (EHA). The requirements contained in this document are confined to interface definition and input/output characteristics of an EHM. The information presented s

20、hould be useful in standardizing: x The terminology x The specification of design and performance parameters, and x The test procedures used in conjunction of these components. The requirements do not restrict nor attempt to define the internal design characteristics of an EHM. As such the material

21、is equally applicable to an EHM having: x Different internal functioning x Different ratings x Different physical sizes, etc. In certain instances, standards for an EHM design are recommended to achieve component interchangeability, for example, command signal polarity, mounting bolts and fluid port

22、s location. 1.2 Field of Application This document applies to both balanced and unbalanced area EHA and EBHA applications. The specification information is directed towards an EHM for use in aircraft flight control systems. However, it shall be recognized that it may also be applicable to many other

23、 control systems, for example, landing gear actuation and steering systems. Unless otherwise indicated in the rest of this document, EHA term is used to describe actuators using EHM concept. 2. REFERENCES 2.1 Applicable Documents The following publications form a part of this document to the extent

24、specified herein. The latest issue of SAE publications shall apply. 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 prece

25、dence. Nothing in this document, however, supersedes applicable laws and regulations unless a specific exemption has been obtained. SAE INTERNATIONAL ARP6154 Page 5 of 40 2.1.1 SAE Publications Available from SAE International, 400 Commonwealth Drive, Warrendale, PA 15096-0001, Tel: 877-606-7323 (in

26、side USA and Canada) or +1 724-776-4970 (outside USA), www.sae.org. ARP490 Electrohydraulic Servovalves AS595 Aerospace Civil Type Variable Delivery, Pressure Compensated, Hydraulic Pump AS1241 Fire Resistant Phosphate Ester Hydraulic Fluid for Aircraft ARP1383 Aerospace - Impulse Testing of Hydraul

27、ic Components AIR1922 Aerospace - System Integration Factors That Affect Hydraulic Pump Life AS4059 Aerospace Fluid Power - Contamination Classification for Hydraulic Fluids ARP4386 Terminology and Definitions for Aerospace Fluid Power, Actuation and Control Technologies ARP4493 Aerospace - Direct D

28、rive Servovalves AS4941 Aerospace - General Requirements for Commercial Aircraft Hydraulic Components ARP5879 Aerospace Test Methodology for Electrohydrostatic Actuators AS5994 Pump Units, Hydraulic, Electric Motor Driven, Variable Delivery AS8775 Hydraulic System Components, Aircraft and Missiles,

29、General Specification For 2.1.2 ISO Publications Copies of these documents are available online at http:/webstore.ansi.org/ or available from International Organization for Standardization, ISO Central Secretariat, 1, ch. de la Voie-Creuse, CP 56, CH-1211 Geneva 20, Switzerland, Tel: +41 22 749 01 1

30、1, www.iso.org. ISO2669 Steady-State Acceleration ISO2678 Insulation Resistance and High Voltage Tests for Electrical Equipment ISO22072 Aerospace Electrohydrostatic Actuator (EHA) Characteristics to be defined in procurement specifications 2.1.3 Radio Technical Commission for Aeronautics Documents

31、Available from Radio Technical Commission for Aeronautics Inc., 1828 L Street, NW, Suite 805, Washington, DC 20036, Tel: 202-833-9339, www.rtca.org. RTCA/DO-160 Environmental Conditions and Test Procedures for Airborne Equipment RTCA/DO-178 Software Considerations in Airborne Systems and Equipment C

32、ertification RTCA/DO-254 Design assurance Guidance for Airborne Electronic Hardware Considerations in Airborne Systems and Equipment Certification SAE INTERNATIONAL ARP6154 Page 6 of 40 2.1.4 U.S Government Copies of these documents are available online at http:/quicksearch.dla.mil. MIL-PRF-83282 Hy

33、draulic Fluid, Fire Resistant Synthetic Hydrocarbon Base, Aircraft, Metric, NATO Code Number H 537 MIL-PRF-87257 Hydraulic Fluid, Fire Resistant; Low Temperature, Synthetic Hydrocarbon Base, Aircraft therefore, a good level of fluid cleanliness shall be insured within the EHA hydraulic circuit. This

34、 is a key factor to maintain and/or improve EHM pump reliability. Contamination can enter a hydraulic system from external sources (actuator) as well as being generated internally (inside the EHM). Contamination of the system from external causes can occur when a component of the actuator is replace

35、d, new fluid is being added or personnel awareness is lacking. Contaminants which require attention are solid particles, water, free and dissolved air, other gases and chemicals such as chlorine solvents and acids. The contamination level of the fluid supplied to the EHM shall be specified. AS4059 C

36、lass 8 maximum is an appropriate reference for the contamination level in new conditions. As part of the EHA acceptance test, the EHM case-drain flow shall be sampled and measured for particulate contamination; the recommended maximum contamination level shall be less than Class 6 per AS4059. The ou

37、tlet cleanliness level at case drain shall not be more than one class greater compared to the supplied fluid. 3.1.5.8 Filtration Requirements Internally, contamination can be generated by: x Wear or failure of the EHM components x Residual particles from the fabrication of components x EHM operation

38、 at temperatures higher than rated for components and fluid SAE INTERNATIONAL ARP6154 Page 18 of 40 x Chemical reaction of fluid with other actuator components or particulates x Formation of fluid deposits and localized hot spots that cause component wear or fluid breakdown To ensure the required fl

39、uid cleanliness requirements (see 3.1.5.7), the EHA design shall include appropriate filtration to protect the EHM from fluid-borne contaminants. The filtration device shall be installed outside the EHM in the case drain line as close as possible to the unit as is practical. The in-service fluid cle

40、anliness limits shall be determined jointly between EHM and the EHA manufacturers. 3.2 Performance The requirements defined in this paragraph shall be met at any time of the flight, during the whole specified service life and under the operating conditions specified in Section 4. In extreme operatin

41、g conditions, the functions shall be ensured. However, deviations on the performance may occur and shall be agreed between EHM and the EHA manufacturer. 3.2.1 Open Loop Performance 3.2.1.1 Flow Limit The flow limit is defined as the maximum flow that can be provided by the EHM at the Design Operatin

42、g Pressure. The EHM flow limit shall be specified and its tolerance is generally 10 %. It is not essential that these maximum ratings be rigidly followed since the maximum speed of the electric motor may be adapted within certain limit to cover the maximum flow requirement. 3.2.1.2 Flow versus Press

43、ure Characteristics The EHM output flow at a given pump speed may vary with operating conditions such as fluid temperature, load pressure drop and life. A set of power points which are flow requirements at specific speeds with corresponding pressure drops is generally specified in worst case conditi

44、ons (low temperature, minimum supply voltage, end of life) to define EHM hydraulic output requirements and is derived from corresponding hinge moments, the EHA pressure drops and slew rates. 3.2.1.3 Run Up Time Refer to Figure 2. When the EHA main mode is the stand-by mode (the EHA used as a back-up

45、 system), it can be useful to specify the run-up time of the EHM as the time from activation of the EHM (power up) to being able to achieve the required speed or flow under the specified load pressure drop. Figure 2 - Run-up time definition Run up Time Flow demand, Mode signal, Power supply curve Ti

46、me EHM speed curve Specified Speed or Flow SAE INTERNATIONAL ARP6154 Page 19 of 40 The run-up time is used to define the EHM acceleration capability, and is usually minimized to improve the EHM cold start capability. The run-up time may be measured by using motor speed sensor information instead of

47、the EHM output flow. The fluid and ambient temperature conditions shall be specified. The initial conditions for run-up time characterizations (simultaneously at t = 0) shall be specified as follows: x Flow demand: 0 to max flow or Input current: 0 to 8 mA (both polarities shall be tested) x Mode si

48、gnal: OFF to ON x Power supply OFF to ON 3.2.1.4 Efficiency (Power Losses) 3.2.1.4.1 EHM Stall Speed The EHM Stall speed is a measure of EHM internal leakage. It is the speed of the EHM (measured in rpm) that is required to maintain the stall pressure differential across the EHM output ports, with z

49、ero discharge flow. 3.2.1.4.2 Volumetric Efficiency The volumetric efficiency is the efficiency associated with converting pump shaft speed into flow. Volumetric efficiency shall be accounted for over the full operation range of flow, pressure and temperature to determine the motor rpm at the required speeds to deliver the flow requirements specified in the procurement specification. 3.2.1.4.3 Torque Ef