NAVY MIL-STD-5522-2000 TEST REQUIREMENTS AND METHODS FOR AIRCRAFT HYDRAULIC AND EMERGENCY PNEUMATIC SYSTEMS《飞机液压和气压应急系统的试验要求和方法》.pdf
《NAVY MIL-STD-5522-2000 TEST REQUIREMENTS AND METHODS FOR AIRCRAFT HYDRAULIC AND EMERGENCY PNEUMATIC SYSTEMS《飞机液压和气压应急系统的试验要求和方法》.pdf》由会员分享,可在线阅读,更多相关《NAVY MIL-STD-5522-2000 TEST REQUIREMENTS AND METHODS FOR AIRCRAFT HYDRAULIC AND EMERGENCY PNEUMATIC SYSTEMS《飞机液压和气压应急系统的试验要求和方法》.pdf(46页珍藏版)》请在麦多课文档分享上搜索。
1、NOT MEASUREMENT I SENSITIVE MIL-STD-5522 17 March 2000 SUPERSEDING 30 September 1975 MIL-T-5522D DEPARTMENT OF DEFENSE TEST METHOD STANDARD TEST REQUIREMENTS AND METHODS FOR AIRCRAFT HYDRAULIC AND EMERGENCY PNEUMATIC SYSTEMS AMSC NIA FSC 1650 Provided by IHSNot for ResaleNo reproduction or networkin
2、g permitted without license from IHS-,-,-MIL-STD-5522 FOREWORD 1. This standard is approved for use by all Departments and Agencies of the Department of Defense (DoD). 2. This standard established in determining methods for testing aircraft hydraulic and emergency pneumatic systems. This standard co
3、vers test methods for aircraft subsystems, weapon system and support equipment. This standard provides contractor for preparation of a detail test procedure for hydraulic and emergency pneumatic systems of a specific aircraft. 3. Beneficial comments (recommendations, additions, deletions) and any pe
4、rtinent data which may be of use in improving this document should be addressed to: Commander, Naval Air Warfare Center Aircraft Division, Code 414100B120-3, Highway 547, Lakehurst, NJ 08733-5100, by using the Standardization Document Improvement Proposal (DD Form 1426) appearing at the end of this
5、document or by letter. 11 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-STD-5522 1. SCOPE l. 1 Scope. This standard establishes test and test method requirements for aircraft and weapons hydraulic and emergency pneumatic systems design and inst
6、allation with operating pressure ranges from 3,000 psi to 8,000 psi and temperature ranges from -65 “F to + 450 “F. 2. APPLICABLE DOCUMENTS 2.1 General. The documents listed in this section are specified in sections 3, 4, and 5 of this standard. This section does not include documents cited in other
7、 sections of this standard or recommended for additional information or as examples. While every effort has been made to ensure the completeness of this list, document users are cautioned that they must meet all specified requirements documents cited in sections 3,4, and 5 of this standard, whether
8、or not they are listed. 2.2 Government documents. 2.2.1 Specifications, standards, and handbooks. The following specifications and standard form a part of this document to the extent specified herein. Unless otherwise specified, the issues of these documents are those listed in the issue of the Depa
9、rtment of Defense Index of Specifications and Standards (DoDISS) and supplement thereto, cited in the solicitation (see 6.3). SPECIFICATIONS DEPARTMENT OF DEFENSE MIL-F-8785 - Flying Qualities of Piloted Airplanes. STANDARDS DEPARTMENT OF DEFENSE MIL-STD-8 10 - Environmental Engineering Consideratio
10、ns and Laboratory Tests. (Unless otherwise indicated, copies of the above specification and standard are available from the Standardization Document Order Desk, 700 Robbins Avenue, Building 4D, Philadelphia, PA 191 11-5094.) 2.2.2 Other Government documents, drawings and publications. The following
11、other Government publication forms a part of this document to the extent specified herein. Unless otherwise specified, the issues are those cited in the solicitation. 1 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-STD-5522 United States Govern
12、ment Printing Office GPO Style Manual (Copies of the GPO Style Manual are available from the Superintendent of Documents. U.S. Government Printing Office, North Capitol and H street, N. W., Washington, DC 20402-0001.) 2.3 Order of precedence. In the event of a conflict between the text of this stand
13、ard and the references cited herein, the text of this document takes precedence. Nothing in this document, however, supersedes applicable laws and regulations unless a specific exemption has been obtained. 3. DEFINITION 3.1 Aircraft varidrive operation. A demonstration of normal operation of the air
14、craft hydraulic and pneumatic systems with the use of varidrive motor inplace of engine. 3.2 Cycle. A cycle is a full travel of service from down to up and return to original down. An illustration of a full cycle would be a landing gear down when valve closed and up when valve opened and return to o
15、riginal down when valve closed. 3.3 Emergency operation. A hydraulic and pneumatic power system reverts from normal system pressure to emergency system pressure when normal system pressure is reduced in detrimental manner. 3.4 Elapse time. Time duration taken to complete a prescribed operation from
16、start to finish. 3.5 Fatigue life. Anticipated life of component expected to last prior to fail due to repeated stress. 3.6 Functional test. A test performed on systems or system components to ensure components and systems are in proper working order and their performance conforms to the specificati
17、on. 3.7 Half cycle. A half cycle is a selector valve and control valve operates one complete cycle. It is illustrated as a landing gear from down to up. 3.8 Mission profile. Demonstration of all satisfactory functions of hydraulic and pneumatic systems and components during a mission. A mission incl
18、udes satisfactory completion of tasks mission from startup to shutdown. 3.9 Normal system. Hydraulic and pneumatic systems and components are functioning properly under the specified condition. 2 Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-MIL-ST
19、D-5522 3.10 Post test inspection. Examination of components inspected after actual test. 3.1 1 Power braking system. A control unit generated pressure by manual actuation and a manually generated pressure is boosted by pressure from a power generating system. 3.12 Pump ripple. Pressure variance prod
20、uced by the pump. 3.13 Resonant condition. A condition when components are exposed to resonant frequencies. 3.14 Resonance ripple freauencies. Vibration frequencies at a resonant stage transmitted from hydraulic pump. 3.15 Simulator tests. Tests conducted in a simulator where installation of compone
21、nts and tubing are identical to actual aircraft. 3.16 Unsymmetrical loading. Uneven or unbalance loading subjected to the control surface of the aircraft. 4. GENERAL REQUIREMENTS 4.1 Recycled, recovered, or environmentally preferable materials. Recycled, recovered, or environmentally preferable mate
22、rials shall be used to the maximum extent possible provided that the material meets or exceeds the operational and maintenance requirements, and promotes economically advantageous life cycle costs. 4.2 Acronym use. The use of acronym shall be in accordance with GPO style manual. 4.3 Test requirement
23、s. new aircraft. One or more of a new series of aircraft shall complete the tests specified in this standard before first flight. If an aircraft simulator is not available, the simulator tests shall be performed on the aircraft. Test requirements versus test methods are tabulated in table I. 4.4 Sim
24、ulator. All simulator tubing and component installations shall be identical to those in the first flight aircraft. All tubing flatness greater than 5 percent for 3,000 PSI and above, and 10 percent for less than 3,000 PSI operating pressure shall be pre-stressed. 4.4.1 Proof pressure. Proof pressure
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