1、SAE Technical Standards Board Rules provide that: “This report is published by SAE to advance the state of technical and engineering sciences. The use of this report is entirelyvoluntary, and its applicability and suitability for any particular use, including any patent infringement arising therefro
2、m, is the sole responsibility of the user.”SAE reviews each technical report at least every five years at which time it may be reaffirmed, revised, or cancelled. SAE invites your written comments and suggestions.Copyright 2002 Society of Automotive Engineers, Inc.All rights reserved. No part of this
3、 publication may be reproduced, stored in a retrieval system or transmitted, in any form or by any means, electronic, mechanical, photocopying, recording, or otherwise, without the prior written permission of SAE.TO PLACE A DOCUMENT ORDER: Tel: 877-606-7323 (inside USA and Canada)Tel: 724-776-4970 (
4、outside USA)Fax: 724-776-0790Email: custsvcsae.orgSAE WEB ADDRESS: http:/www.sae.orgAEROSPACE RECOMMENDED PRACTICEARP1281REV.CIssued 1974-01Revised 2002-09Superseding ARP1281B(R) Actuators: Aircraft Flight Controls, Power Operated, Hydraulic, General Specification ForTABLE OF CONTENTS1. SCOPE .51.1
5、Purpose51.2 Product Classification.51.3 Field of Application.52. REFERENCES .62.1 Applicable Documents .62.1.1 SAE Publications .62.1.2 ASTM Publications.72.1.3 Government Publications.72.1.4 NAS Publications .82.1.5 FAR Publications from the FAA92.1.6 Joint Aviation Authorities Committee Documents
6、92.1.7 Radio Technical Commission for Aeronautics Documents.92.1.8 American Society of Mechanical Engineers Documents92.1.9 Information References92.2 Definitions and Abbreviations.92.2.1 Definitions 92.2.2 Abbreviations .93. TECHNICAL REQUIREMENTS .103.1 General 103.2 Design103.2.1 Hydraulic Contro
7、l Valves103.2.2 Electrical Components . 113.2.3 Physical Characteristics.123.2.4 Structural Characteristics.12Copyright SAE International Provided by IHS under license with SAENot for ResaleNo reproduction or networking permitted without license from IHS-,-SAE ARP1281 Revision C- 2 -TABLE OF CONTENT
8、S (Continued)3.2.5 Design Characteristics .123.2.6 Materials 163.2.7 Parts.173.2.8 Identification and Marking 173.2.9 Safety.183.2.10 Human Performance/Engineering183.2.11 Bearings.183.3 Processes, Construction/Assembly Requirements 193.3.1 Processes 193.3.2 Construction/Assembly Requirements.193.3.
9、3 Workmanship .213.4 Performance 213.4.1 Performance, Standard Conditions 213.4.2 Leakage .233.4.3 Reliability233.4.4 Performance, Environmental Conditions233.4.5 Input and Output Limit Loads.233.4.6 Load Capability of Dual-Load-Path-Elements 243.4.7 Fatigue .243.4.8 Operating Life 253.5 Installatio
10、n/Maintenance Requirements .253.5.1 Maintainability 253.5.2 Contamination263.5.3 Electromagnetic Interference .263.5.4 Interchangeability.263.6 Documentation.263.6.1 Analysis Requirements 263.6.2 Reliability Analysis .263.6.3 Design Analysis .263.6.4 Qualification Analysis.273.6.5 Drawings 273.6.6 P
11、lastic Model274. QUALITY ASSURANCE PROVISIONS274.1 General 274.2 Test Requirements .274.2.1 Optional Procedures 274.3 Classification of Tests.274.3.1 Acceptance Tests.274.3.2 Preproduction Tests .284.3.3 Qualification Tests284.4 Test Procedures .284.4.1 Acceptance Test.284.4.2 Preproduction Test Pro
12、cedure28Copyright SAE International Provided by IHS under license with SAENot for ResaleNo reproduction or networking permitted without license from IHS-,-SAE ARP1281 Revision C- 3 -TABLE OF CONTENTS (Continued)4.4.3 Qualification Test Procedure 284.5 Test Conditions 294.5.1 Test Fluid294.5.2 Fluid
13、Temperature 294.5.3 Test Fluid Filtration.294.5.4 Hydraulic Power Supply.294.5.5 Environmental Conditions 294.5.6 Test Instruments.294.5.7 Test Fixtures.294.5.8 Steady-State Tests .304.5.9 Mission-Profile Tests 304.6 Acceptance Test Methods304.6.1 General 304.6.2 Examination of Product304.6.3 Operat
14、ion and External Leakage .304.6.4 Chatter .304.6.5 Proof Pressure .304.6.6 Internal Leakage 314.6.7 Supplementary Acceptance Tests314.6.8 Rejection and Retest314.7 Preproduction Test Methods 314.7.1 Sampling and Tests314.7.2 Pretest Inspection 324.7.3 Acceptance Tests.324.7.4 Proof Load .324.7.5 Pre
15、ssure Drop324.7.6 Cylinder Friction .324.7.7 Immersion 324.7.8 Performance Verification Tests.324.7.9 Extreme Temperature Performance.324.7.10 Altitude .334.7.11 Acceleration .334.7.12 Shock .334.7.13 Vibration.334.7.14 Endurance334.7.15 Burst Pressure .354.8 Qualification Test Methods.354.8.1 Sampl
16、ing and Tests354.8.2 Pretest Inspection 354.8.3 Acceptance Tests.354.8.4 Proof Load .354.8.5 Pressure Drop354.8.6 Cylinder Friction .354.8.7 Immersion 354.8.8 Performance Verification Tests.35Copyright SAE International Provided by IHS under license with SAENot for ResaleNo reproduction or networkin
17、g permitted without license from IHS-,-SAE ARP1281 Revision C- 4 -TABLE OF CONTENTS (Continued)4.8.9 Extreme Temperature Performance.354.8.10 Altitude .364.8.11 Humidity .364.8.12 Fungus .364.8.13 Salt Fog364.8.14 Dust364.8.15 Acceleration .364.8.16 Shock .364.8.17 Vibration.364.8.18 Endurance364.8.
18、19 Burst Pressure .364.8.20 Reliability Tests 364.8.21 Contamination Tests.364.8.22 Structural Tests.374.8.23 EMI Tests .374.9 Test Reports, Design Changes and Approval Data374.9.1 Preproduction and Qualification Test Reports374.9.2 Subsequent Design Change 374.9.3 Qualification Approval of Similar
19、Units.374.10 Preproduction and Qualification Test Failures375. PREPARATION FOR DELIVERY.375.1 Preservation and Packaging 375.1.1 Cavities 385.1.2 Servoactuator Attachment Bearings 385.1.3 Piston Rod and Input Linkage385.1.4 Servoactuator.385.2 Packing 385.2.1 Immediate Use Shipment.385.2.2 Domestic
20、Shipment385.2.3 Overseas Shipment .385.3 Marking of Shipment 386. NOTES39APPENDIX A TECHNICAL NOTES AND COMMENTS40FIGURE 1 Dimensions for End Caps and Locknuts .14TABLE 1 Dynamic Characteristics .22TABLE 2 Environmental Criteria.24TABLE 3 Acceptance Test31TABLE 4 Load Cycle Schedule Number of Cycles
21、.34Copyright SAE International Provided by IHS under license with SAENot for ResaleNo reproduction or networking permitted without license from IHS-,-SAE ARP1281 Revision C- 5 -1. SCOPE:This aerospace recommended practice provides a framework and suggested procedures or values for requirements for t
22、he design, performance, and test of hydraulically powered servoactuators for use in aircraft flight control systems.The original version of this document was intended for military usage: consequently, the requirements still often reflect such use. However, the basic requirements of this ARP may and
23、should be applicable to commercial usage as well, provided that appropriate considerations are given for the applicable FAR/JAR 25 regulations, hydraulic fluids, and environmental conditions.1.1 Purpose:This recommended practice is a guide and surrogate specification for preparing a detail specifica
24、tion for a particular servoactuator application.1.2 Product Classification:Servoactuators covered by this recommended practice are of the following classes:Class A - Power ActuatorsClass B - Signal Conversion ActuatorsClass C - Power and Signal Conversion Actuator CombinationFor military aircraft, t
25、he servoactuators covered by this recommended practice include those in the following types of hydraulic systems:a. Type I - 65 to +160 F (-54 to +71 C) fluid temperature rangeb. Type II - 65 to +275 F (-54 to +135 C) fluid temperature rangec. Type III - 65 to +390 F (-54 to +199 C) fluid temperatur
26、e rangeFor commercial aircraft, the servoactuators covered by this recommended practice include those suitable for use with type IV and type V phosphate ester fluids.1.3 Field of Application:A servoactuator in the flight control system positions an aerodynamic control surface or other force effector
27、 to produce forces and moments on the aircraft for stability and control of the vehicle. These servoactuators may be controlled by mechanical, electrical, photonic or fluidic inputs, or combinations thereof, and may be powered by one or more hydraulic systems. The complete actuator assembly may inco
28、rporate basic components such as servovalve, input linkage and electrical, optical, and/or mechanical position feedback systems, and redundancy logic in addition to the actuating cylinder. These components are usually designed as an integral package, but in some cases are physically separated. Addit
29、ional components may also be included and configured integrally or separately such as bypass valves, filters, pressure switches, motor or solenoid operated shutoff valves, thermostatic control valves, hydraulic logic, mechanical locking devices and electrical transducers.Copyright SAE International
30、Provided by IHS under license with SAENot for ResaleNo reproduction or networking permitted without license from IHS-,-SAE ARP1281 Revision C- 6 -2. REFERENCES:Following are listings of documents and pertinent definitions associated with hydraulically powered aircraft flight control actuators. These
31、 publications form a part of this document to the extent referenced herein. The latest issue of all documents shall apply.2.1 Applicable Documents:2.1.1 SAE Publications: Available from SAE, 400 Commonwealth Drive, Warrendale PA 15096-0001.AMS 2403 Plating, Nickel, General PurposeAMS 2406 Plating, C
32、hromium, Hard DepositAMS 2419 Cadmium-Titanium PlatingAMS 2426 Coating, Cadmium Vacuum DepositionAMS-A-21180 Aluminum - Alloy Castings, High StrengthAMS-A-22771 Aluminum Alloy Forgings, Heat TreatedAMS-C-8837 Coating, Cadmium (Vacuum Deposited)AMS-F-7190 Forgings, Steel, Aircraft/Aerospace Equipment
33、 and Special Ordnance ApplicationsAMS QQ-C-320 Chromium Plating (Electrodeposited)AMS-S13165 Shot Peening of Metal PartsAMS-STD-2175 Castings, Classification and Inspection ofARP490 Electrohydraulic Flow Control ServovalvesARP598 The Determination of Particulate Contamination in Hydraulic Fluids by
34、the Particle Count MethodARP926 Design Analysis Procedure for Failure Mode, Effects and Criticality Analysis (FMECA)ARP1383 Impulse Testing of Hydraulic Actuators, Valves, Pressure Containers and Similar Fluid System ComponentsAIR4066 Hydraulic Servoactuator MaterialsARP4386 Terminology and Definiti
35、ons for Aerospace Fluid Power, Actuation, and Control TechnologiesARP4493 Direct Drive ValvesARP4763 Aerospace Fluid Power Relief ValvesAIR4922 Primary Flight Control Hydraulic Actuation System Interface DefinitionARP4945 Aerospace - Solenoid Valve, Hydraulic, Three-Way, Two-Position, Direct ActingA
36、S1241 Fire Resistant Phosphate Ester Hydraulic Fluid for AircraftAS1290 Graphic Symbols for Aircraft Hydraulic and Pneumatic SystemsAS4059 Aerospace Cleanliness Classification for Hydraulic FluidsAS4088 Rod Scraper Gland Design StandardAS4716 Gland Design, O-ring and Other Elastomeric SealsAS4941 Hy
37、draulic System Components, Commercial Aircraft, General Specification ForAS5169 Fitting, Port Plug and Bleeder FSC 4730AS5440 Hydraulic Systems, Aircraft, Design and Installation Requirements forAS6038 Bearings, Ball, Bellcrank, Antifriction, AirframeCopyright SAE International Provided by IHS under
38、 license with SAENot for ResaleNo reproduction or networking permitted without license from IHS-,-SAE ARP1281 Revision C- 7 -2.1.1 (Continued):AS6039 Bearings, Ball, Rod End, Double Row, Self-AligningAS7949 Bearings, Ball, Airframe, AntifrictionAS8775 Hydraulic System Components, Military Aircraft,
39、General Specification forAS8976 Bearings, Plain Self-Aligning, All-MetalAS8879 Screw Threads - UNJ Profile, InchAS33649 Boss Fluid Connection - Internal Straight ThreadAS39901 Bearings, Roller, Needle, Airframe, Antifriction, InchJ2470 Hydraulic Fluid Power Valves Method for Assessing the Lock Sensi
40、tivity to Contaminants2.1.2 ASTM Publications: Available from ASTM, 100 Barr Harbor Drive, West Conshohocken, PA 19428-2959.ASTM B 38l Specification for Titanium and Titanium Alloy ForgingsASTM D 1974 Fiberboard Shipping Containers, Methods of Closing, Sealing, and Reinforcing, Standard Practice for
41、ASTM E 1417 Standard Practice For Liquid Penetrant ExaminationASTM E 1444 Standard Practice For Magnetic Particle Examination2.1.3 Government Publications: Available from Standardization Documents Order Desk, Building 4D, 700 Robbins Avenue, Philadelphia, PA 19111-5094.A-A-1898 Cushioning Material,
42、Cellulosic, PackagingA-A-66057 Panels, Wood/Wood Based; construction and DecorativeJSSG-2006 Aircraft Structures, General Specification ForMIL-A-8625 Anodic Coatings for Aluminum and Aluminum AlloysMIL-DTL-5015 Connectors, Electrical, Circular Threaded, An Type, General Specification forMIL-C-11796
43、Corrosion Preventive Compound, Petrolatum, Hot ApplicationMIL-C-26482 Connector, Electrical (Circular, Miniature, Quick Disconnect, Environment Resisting)/ when spanner wrench slots are used, they shall be dimensioned in accordance with Figure 1. Drilled hole-type nuts requiring the use of pin-type
44、spanner wrenches shall not be used in servoactuator designs. Positive locking methods are to be used to prevent rotation of the end caps, locknuts, and adjustment nuts.3.2.5.1.8 Rod Ends: These components shall be designed to minimize stress risers. Integral anti-rotation devices are preferred and s
45、hall be arranged to prevent excessive airframe attach fitting wear. Controlled radius root threads conforming to AS8879 or special threads with root radii greater than specified in AS8879 are required. The assembly of the rod end to the piston rod shall result in a minimum thread preload equivalent
46、to the maximum rod end load. A positive locking arrangement, positively safetied, shall be used to maintain the thread preload. Safety wiring and cotter pinning shall be in accordance with NASM 33540.Copyright SAE International Provided by IHS under license with SAENot for ResaleNo reproduction or n
47、etworking permitted without license from IHS-,-SAE ARP1281 Revision C- 14 -FIGURE 1 - Dimensions for End Caps and Locknuts3.2.5.1.9 Seals: Unless otherwise specified in the detail specification, seal design characteristics shall comply with the gland design requirements of AS4716. The seal designs w
48、hether vented or unvented (single or two stage) shall have the written approval of the procuring activity. The elastomeric seals shall be compatible with the hydraulic fluid to be used in the servoactuator. Seal operating life shall be specified in the detailed specification and may be given either
49、in terms of total hours of operation or in number of cycles of operation of specified amplitudes and rates which represent actual usage.3.2.5.1.10 Vulnerability: The detail specification shall establish the vulnerability requirements. These detail requirements shall stress rip stop designs, construction materials and proper positioning of the more critical components both electrical and hydraulic, so as to provide greater protection fr
