1、 AEROSPACE STANDARD Aerospace General Requirements for Hydraulic System Reservoirs 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 entirely voluntary, and its applicability and su
2、itability for any particular use, including any patent infringement arising therefrom, 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. Co
3、pyright 2005 SAE International All rights reserved. No part of this 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
4、 ORDER: Tel: 877-606-7323 (inside USA and Canada) Tel: 724-776-4970 (outside USA) Fax: 724-776-0790 Email: custsvcsae.org SAE WEB ADDRESS: http:/www.sae.org Issued 2005-02 AS5586 FOREWORD This document is based on two military specifications MIL-R-5520 and MIL-R-8931. Hydraulic reservoirs are indepe
5、ndent of the system working pressure as they are generally part of the low-pressure side of the hydraulic system. The exception to this is the hydraulically pressurized reservoir (known as the Bootstrap reservoir), which is also an integral part of the high-pressure system. AIR1899 and AIR5005 provi
6、de the following information on hydraulic reservoirs used on various Military and Commercial aircraft: a. Reservoir type b. Reservoir volume c. Pressure applied to the fluid in the reservoir SAE AS5586 - 2 - TABLE OF CONTENTS FOREWORD.1 1. SCOPE 5 1.1 Reservoir Types.5 2. REFERENCES.5 2.1 Applicable
7、 Documents .5 2.1.1 SAE Publications6 2.1.2 ASME International Publications7 2.1.3 Federal Aviation Administration (FAA) Publications.7 2.1.4 European Aviation Safety Agency (EASA) Publications 7 2.1.5 Joint Aviation Authorities Committee Publications.7 2.1.6 Radio Technical Commission for Aeronauti
8、cs Publications.8 2.1.7 Department of Defense Publications8 2.2 Definitions 8 3. REQUIREMENTS 10 3.1 Aircraft, Helicopter or Missile Requirements10 3.1.1 Operating Characteristics.10 3.1.2 Reservoir Installation10 3.2 Servicing Requirements.10 3.2.1 Filling and Refill10 3.2.2 Bleeding .14 3.2.3 Drai
9、ning14 3.3 System Requirements14 3.3.1 Reservoir Capacity.14 3.3.2 Reservoir Pressure 15 3.3.3 Operating Conditions .15 3.3.4 Negative Gravity.16 3.3.5 Interconnected Emergency Reservoirs 16 3.4 Component Requirements .16 3.4.1 General 16 3.4.2 Negative Gravity Protection (Non-separated Reservoirs)
10、17 3.4.3 Return Line Inlet.17 3.4.4 Reservoir Design Operating Pressure (RDOP)17 3.4.5 Structural Strength .18 3.4.6 Pressure Relief.20 3.4.7 Seal Design Requirements (Separated Reservoirs Only)24 3.4.8 Fluid Level Indication .25 3.4.9 Connections .25 3.4.10 Marking 25 3.4.11 Environmental Requireme
11、nts.26 SAE AS5586 - 3 - 3.4.12 Corrosion Resistance.27 3.4.13 Electro-Conductive Bonding.27 3.4.14 Filters .27 3.4.15 Other Assemblies.28 4. QUALITY ASSURANCE PROVISIONS .28 4.1 Responsibility for Inspection 28 4.2 Classification of Tests 28 4.3 Test Stand Requirements 31 4.4 First Article Inspectio
12、n31 4.4.1 First Article Samples 31 4.4.2 First Article Inspection Report31 4.4.3 Rejection 31 5. ACCEPTANCE TESTS32 5.1 Examination of the Product32 5.1.1 Packaging, Packing and Marking.32 5.2 Test Program .32 5.2.1 Proof Pressure .32 5.2.2 Functional Check .33 5.2.3 Electro-Conductive Bonding.33 5.
13、3 Preparation for Shipment .34 5.4 Storage and Packing34 6. QUALIFICATION TESTS.34 6.1 General 34 6.2 Fluid Immersion Test34 6.2.1 Electrical Components .34 6.2.2 Non Metallic Parts35 6.3 Performance Tests.35 6.3.1 Expanded Envelope Acceptance Tests .35 6.3.2 Function Tests35 6.3.3 Relief Valve Oper
14、ation .36 6.3.4 Operating Characteristics.36 6.3.5 Operation Above System Pressure Test (Type A Reservoirs Only).38 6.3.6 Negative Gravity Test (Non-Separated Reservoirs Only) 38 6.3.7 Functional Endurance Test (Separated Reservoirs Only)38 6.4 Electrical Tests.39 6.4.1 Magnetic Effect 39 6.4.2 Radi
15、o Frequency Susceptibility (Radiated and Conducted) Test.39 6.4.3 Emission of Radio Frequency Energy Test39 6.5 Environmental Tests 39 6.5.1 Extreme Temperature Functioning Tests (Separated Reservoirs Only) 39 SAE AS5586 - 4 - 6.5.2 Humidity .43 6.5.3 Fluids Susceptibility43 6.5.4 Fungus .43 6.5.5 S
16、alt Spray.43 6.5.6 Icing43 6.5.7 Fire Resistance Test (Reservoirs in Designated Fire Zones Only) 43 6.6 Structural Tests43 6.6.1 Proof Pressure Test .43 6.6.2 Pressure and Structural Test .44 6.6.3 Negative Pressure44 6.6.4 Fatigue (Pressure Impulse) Test44 6.6.5 Vibration Tests .45 6.6.6 Operationa
17、l Shock and Crash Safety Tests.45 6.6.7 Handling Loads Test 45 6.6.8 Wrench Loads Test45 6.7 Destructive Tests .46 6.7.1 Ultimate Pressure Test.46 6.7.2 Pressure and Structural Test .46 6.8 Post Qualification Tests .46 6.8.1 Acceptance Tests.46 6.8.2 Disassembly and Inspection .46 7. NOTES.47 7.1 In
18、tended Use47 7.2 Keywords .47 APPENDIX A HYDRAULIC SYSTEM FLUID REQUIREMENTS AND RESERVOIR SIZING .48 FIGURE 1 Typical Identification and Instruction Plate.12 FIGURE 2 Considerations for Fluid Level Designations on Reservoir Nameplates 13 FIGURE 3 Reservoir Operating Characteristics Test Set-up.37 T
19、ABLE 1 Test Program29 SAE AS5586 - 5 - 1. SCOPE: This SAE Aerospace Standard (AS) specifies the general requirements for hydraulic system reservoirs that are installed in commercial and military aircraft and helicopters and also in missile hydraulic systems. This document includes design, test (prod
20、uction and qualification) criteria for various types of reservoirs. Appendix A provides information on hydraulic fluid volume requirements and reservoir sizing. This document also provides a basis for the Procurement Specification to completely define individual reservoir requirements 1.1 Reservoir
21、Types: Type A Separated, hydraulically pressurized (commonly referred to as a “bootstrap reservoir”) Type B Separated, gas pressurized (commonly through an engine bleed system or by a pressurized gas charge) Type C Separated, mechanically pressurized (usually by a spring and for emergency use) Type
22、D Non-separated, gas pressurized (commonly through an engine bleed system) Type E Non-separated, non-pressurized (commonly referred to as an open reservoir) 2. REFERENCES: 2.1 Applicable Documents: The following publications form a part of this document to the extent specified herein. The latest iss
23、ue 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 precedence. Nothing in this document,
24、 however, supersedes applicable laws and regulations unless a specific exemption has been obtained. SAE AS5586 - 6 - 2.1.1 SAE Publications: Available from SAE, 400 Commonwealth Drive, Warrendale, PA 15096-0001. Telephone: 724-776-4970 Web Address: http:/www.sae.org AIR1899 Military Aircraft Hydraul
25、ic System Characteristics AIR1922 System Integration Factors that Affect Pump Life AIR4543 Aerospace Hydraulics and Actuation Lessons Learned AIR5005 Commercial Aircraft Hydraulic Systems ARP1288 Placarding of Aircraft Hydraulic Equipment to Identify Fluid Suitability ARP1383 Impulse Testing of Hydr
26、aulic Actuators, Valves, Pressure Containers and Similar Fluid System Components ARP4386 Terminology and Definitions for Aerospace Fluid Power, Actuation and Control Technologies ARP4752 Design and Installation of Commercial Transport Aircraft Hydraulic Systems ARP4925 Design and Installation of Com
27、mercial Transport Helicopter Hydraulic Systems AS1300 Boss, Ring Locked Fluid Connection Type, Standard Dimensions for AS4059 Aerospace Cleanliness Classification for Hydraulic Fluids AS4941 General Requirements for Commercial Aircraft Hydraulic Components AS5202 Port or Fitting End, Internal Straig
28、ht Tread, Design Standard AS5440 Hydraulic Systems, Aircraft, Design and Installation, Requirements for AS8775 Hydraulic System Components, Aircraft and Missiles, General Specification for SAE AS5586 - 7 - 2.1.2 ASME International Publications: Available from ASME International, 22 Law Drive, Fairfi
29、eld, NJ 07007-2900. Telephone: 973-882-1167. Web Address: http:/asme.org ASME B46.1 Surface Texture (Surface Roughness, Waviness 59 F (15 C). PURCHASER: The Purchaser is the organization that has the responsibility for the design and development of the hydraulic system that includes the reservoir. T
30、ypically, the Purchaser is an aircraft manufacturer or a modification center. The Purchaser is responsible for compiling the Procurement Specification. However, for Military applications, the Purchaser can be the applicable Government department that is responsible for the procurement of the aircraf
31、t or missile. SUPPLIER: The Supplier is the manufacturer, and who will be responsible for the design, production and qualification of the reservoir. The Purchaser shall approve the Supplier for the design, development and manufacture of aerospace hydraulic components. PROCUREMENT SPECIFICATION: The
32、Procurement Specification is the document that includes the following: a. Specific performance and technical criteria b. Acceptance and qualification test requirements c. Reliability requirements d. Quality requirements e. Packaging requirements NOTES: 1. Hydraulic reservoirs can be designed and man
33、ufactured by the Purchaser. In this case, the Procurement Specification is the Design Specification that is compiled by the Purchaser as part of the design, development and qualification process for the reservoir. 2. In certain cases where performance criteria may be marginal and are a function of b
34、oth system and detail reservoir design, the Reservoir Supplier may, through prior experience, contribute to the final Procurement Specification. SAE AS5586 - 10 - 3. REQUIREMENTS: 3.1 Aircraft, Helicopter or Missile (henceforth called flight vehicle) Requirements: 3.1.1 Operating Characteristics: Re
35、fer to ARP4752, ARP4925, or AS5440 as applicable for the requirements for the integration of the reservoir into the flight vehicle system. AIR1922 should also be consulted for guidance into the factors concerning the hydraulic reservoir design that are required to ensure that the hydraulic pump perf
36、ormance and reliability conforms to the system requirements. 3.1.2 Reservoir Installation: The design of the reservoir and its associated mounts shall be such that the reservoir shall be securely fastened in place with no weight and other structural loads carried by the fittings or fluid lines attac
37、hed thereto. The mounting, when secured, shall impose no internal stress or abrasion of the reservoir or its fittings. The mounting shall facilitate removal of the reservoir without disturbance of any adjacent components or lines. Instructions for installing the reservoir should be noted on a label
38、as worded in the Procurement Specification. 3.1.2.1 Reservoir Ambient Vent Port (Type A and C Reservoirs only): If the reservoir incorporates an ambient vent port, the port should be orientated such that any moisture can freely drain out of it. 3.2 Servicing Requirements: 3.2.1 Filling and Refill: T
39、he reservoir design shall be such that initial filling of the reservoir installed in the vehicle, and any subsequent refilling or replenishment of the fluid, shall be accomplished only through the use of a device such as a hand pump or power pump. No provision shall be incorporated which permits the
40、 transfer of hydraulic fluid into the reservoir by gravity flow from an external container. 3.2.1.1 Reservoir Identification and Instruction Plate: An identification and instruction plate (see Figure 1) shall be attached to either the reservoir itself or to the immediately adjacent vehicle structure
41、 near the fluid level indicating device, positioned so as to be easily readable. SAE AS5586 - 11 - 3.2.1.1 (Continued): This plate shall include the following information: a. Name and part number of the reservoir b. Specification number and color of fluid, as applicable c. Reservoir fluid capacity a
42、t full level d. Full level indication references e. Refill level indication references f. Position of hydraulic devices and vehicle during filling procedure g. Depressurizing procedure reference h. Pressurizing warning notice Additional full and refill levels under various conditions of system press
43、ure, temperature, vehicle, attitude, accumulator pre-charge should be added as required (see Figure 2). Any other information such as installation and/or removal instructions or dry weight may also be included. SAE AS5586 - 12 - FIGURE 1 - Typical Identification and Instruction Plate SAE AS5586 - 13
44、 - ADDITIONAL FULL LEVELS MAY BEINDICATED TO REFLECT CHANGES INRESERVOIR FLUID VOLUME OCCURRINGWITH CHANGES IN POSITIONS OF CERTAINHYDRAULIC UNITS THAT MAY HAVEALTERNATE GROUND SERVICING POSITIONS.FULL HYDRAULIC UNITS IN THEIRRESPECTIVE POSITIONS FOR GROUNDSERVICING (ACTUAL POSITIONS SHALLBE STATED)
45、 AND HYDRAULIC SYSTEMPRESSURE ZERO.FULL HYDRAULIC UNITS IN THEIRRESPECTIVE POSITIONS FOR GROUNDSERVICING (ACTUAL POSITIONS SHALLBE STATED) AND HYDRAULIC SYSTEM ATNORMAL OPERATING PRESSURE.REFILL - HYDRAULIC SYSTEM PRESSUREZERO.*EACH OF THE FULL LEVELS MAY HAVE ITSCORRESPONDING REFILL LEVEL INDICATED
46、(LEVEL TO BE DETERMINED BY DROPPINGEACH FULL LEVEL BY AN AMOUNT NOT EXCEEDING THE PROVIDED LEAKAGEALLOWANCE VOLUME).FULL HYDRAULIC UNITS IN THEIRRESPECTIVE POSITIONS FOR FLIGHT(ACTUAL POSITIONS SHALL BE STATED) AND HYDRAULIC SYSTEM AT NORMALOPERATING PRESSURE.FOR PRESSURIZED RESERVOIRS, SPECIFY THAT
47、RESERVOIR SHALL BE PRESSURIZED TO ITSNORMAL PRESSURIZATION PRESSURE AFTERFILLING AND THAT FLUID LEVEL SHALL BERECHECKED. ALSO CHECK FLUID WITH SYSTEM PRESSURIZED AS EXCESSIVE LEVEL DROPINDICATES POOR SYSTEM BLEEDING.* If only one refill level is indicated, it should be that level whichresults from l
48、owering the fluid level from the uppermost full levelby an amount not exceeding the provided leakage allowance volume.FIGURE 2 - Considerations for Fluid Level Designations on Reservoir Nameplates SAE AS5586 - 14 - 3.2.2 Bleeding: 3.2.2.1 Type A, B and C Reservoirs: The reservoir design and installa
49、tion shall be such that if entrained gas bubbles in the hydraulic fluid are allowed to accumulate in any space in the reservoir, means shall be provided for removing entrapped air in the bleeding operation (such as a manual or automatic bleed valve) without disconnecting any tubing. If possible, the angle at which the reservoir is installed in the flight vehicle should be such that any free air would migrate to the bleed point. Also, provisions shall be provided in the reservoir for either automatic or periodic manual removal of any hydraulic fluid fr
