V38 液压、冷气系统及其附件 标准查询与下载

DLA MS51854 REV C NOTICE 1-1999 液压非扩口式三通管接头

This notice should be filed in front of MS51854C, dated 30 July 1987.

TEE, TUBE TO SWIVEL, SWIVEL ON RUN, FLARELESS TYPE, HYDRAULIC [Refer To: SAE J514, SAE J514, SAE J514, SAE J514, SAE J514]

DLA MS51822 REV E NOTICE 1-1999 液压非扩口式管子承头三岔管

This notice should be filed in front of MS51822E, dated 30 July 1987.

TEE, PIPE TO TUBE, FEMALE PIPE ON RUN, FLARELESS TYPE, HYDRAULIC [Refer To: SAE J514, SAE J514, SAE J514, SAE J514, SAE J514]

DLA MS51853 REV C NOTICE 1-1999 液压非扩口式三通管接头

This notice should be filed in front of MS518536, dated 30 July 19

TEE, TUBE TO SWIVEL, SWIVEL ON BRANCH, FLARELESS TYPE, HYDRAULIC [Refer To: SAE J514, SAE J514, SAE J514, SAE J514, SAE J514]

DLA MS51852 REV C NOTICE 1-1999 液压非扩口式直角三通管接头

This notice should be filed in front of MS51852C, dated 30 July 1987.

ELBOW, TUBE TO SWIVEL, 90 DEGREE, FLARELESS TYPE, HYDRAULIC [Refer To: SAE J514, SAE J514, SAE J514, SAE J514, SAE J514]

SAE AS19692A-1999 变速流液压泵通用规范

This specification and a detail pump specification establish the requirements for variable flow hydraulic pumps, for use in aircraft hydraulic systems conforming to and as defined in MIL-H-5440 and MIL-H-8891, as applicable. The general requirements for type I and type II hydraulic systems pumps are specified in MIL-H-8775 and for type III system pumps in MIL-H-8890.

Pumps, Hydraulic, Variable Flow, General Specification for

DLA QPL-1339-6-1999 400华氏度3000 PSI轻量级液压 四氟乙烯软管组件

This list has been prepared for use by or for the Government in the acquisiüor of products mered by SAE-AS1339. Listing of a product is not intended to and does not cannote endorsement of the produd by the Department of Defense.

HOSE ASSEMBLY, TETRAFLUOROETHYLENE, 400 DEG. F, 3000 PSI, HYDRAULIC LIGHTWEIGHT

SAE AS7997-1999 飞行器用液压定量马达总规范

This specification covers constant displacement hydraulic motors, generally remotely mounted, using hydraulic fluid under pressure as the energy transfer medium for driving various accessories. Hydraulic motors shall be suitable for use in aircraft hydraulic systems conforming to and as defined in MIL-H- 5440 and MIL-H-8891 as applicable.

Motors, Aircraft Hydraulic, Constant Displacement General Specification for FSC 1650

ISO 7169:1998 航空航天 液压系统用24°锥度孔可拆卸管接头 一般规范

This International Standard specifies performance and quality requirements for the qualification and manufacture of standard 24°cone fittings to ensure reliable performance in aircraft hydraulic systems. This International Standard specifies baseline criteria for the design and manufacture of system fittings that are qualification tested on engines. This International Standard covers fittings of the temperature types and pressure classes specified in ISO 6771. note: 1) The geometrical definition of a 24°cone fitting will be given in a future International Standard.

Aerospace - Separable tube fittings for fluid systems, 24 degrees cone - General specification

SAE AMS3021C-1998 流体，参考，用于测试耐二酯（多元醇）材料

This specification covers a neopentyl polyol ester in the form of a fluid. This fluid has been used typically to evaluate the ability of elastomeric and other polymeric compounds to conform to designated requirements after immersion in the fluid at a specific temperature and time, as required by an applicable specification, and its use is limited to such applications. This fluid is not intended for operational use in gas turbine engines. Each application should be considered separately.

Fluid, Reference, For Testing Di-Ester (Polyol) Resistant Material

DLA MS51855 REV C (1)-1998 液压非扩口式舱壁90度弯管

This amendment forms a part of MS51855C, dated 30 July 1987, and is approved for use by all Departments and Agencies of the Department of Defense.

ELBOW, TUBE, 90 DEGREE, BULKHEAD, FLARELESS TYPE, HYDRAULIC [Refer To: SAE J514, SAE J514, SAE J514, SAE J514, SAE J514]

DIN ISO 10583:1998 航空航天流体系统.管/管接头组件的试验方法

The test methods specified apply to fitting assemblies used in aircraft fluid systems in the pressure and temperature ranges covered by pressure classes B, D and E, and temperature types I, II and III of ISO 6771. Applies each time that it is referred to in a procurement specification or other definition document which contain the pass/fail criteria for these tests.#,,#

Aerospace fluid systems - Test methods for tube/fitting assemblies (ISO 10583:1993)

SAE AIR4281-1998 直升机动力装置的润滑油系统

Turbine engines installed in helicopters require a highly sophisticated oil system to fulfill two tasks: a. Cooling/oil supply b. Lubrication. While lubrication is an engine internal procedure, cooling and oil supply require more or less design activity on the aircraft side of the engine/airframe interface for proper engine function, depending on the engine type. The necessity for engine cooling and oil supply provisions on the airframe can lead to interface problems because the helicopter manufacturer can influence engine related functions due to the design of corresponding oil system components. This SAE Aerospace Information Report (AIR) deals with integration of engine oil systems with the airframe and gives information for both helicopter and engine manufacturers for a better understanding of interface requirements.

Oil Systems for Helicopter Powerplants

BS 2M 49:1997 航空器.液压组件.已校准组件液体指示标记

This International Standard establishes a scheme for the mark-ing of components (other than pipelines, hoses and fittings) used in aircraft hydraulic systems, so that the correct type of fluid is readily apparent during any assembly or testing opera-tions in workshops. The marking is not intended to serve any purpose when a component is installed in an aircraft. NOTE — The requirements for the marking of pipelines and hoses in aerospace vehicles to indicate the type of fluid for which they are ap-proved are given in ISO 12.

Aircraft. Hydraulic components. Marking to indicate fluid for which component is approved

BS 2M 53:1997 飞机 流体系统 管道和配件的热冲击测试

This International Standard provides an environmental test method for thermal shock testing of fluid system piping and fittings, excluding hose and hose as-semblies.

Aircraft. Fluid systems. Thermal shock testing of piping and fittings

HB 7493-1997 液压传感器通用规范

本规范规定了航空液压系统用液压传感器的技术要求、试验方法、检验规则及标志、包装、运输和贮存的通用要求。 　　本规范适用于液压传感器（以下简称“传感器”）的设计、制造与验收。

General specification for hydraulic pressure sensors

HB/Z 300-1997 飞机液压功率转换装置设计指南

本标准规定了飞机液压功率转换装置各种类型的工作特性及设计要求，并给出了飞机液压功率转换装置原理图和典型应用实例。 　　本标准适用于飞机液压系统中由泵、马达组成的功率转换装置。

Design Guidelines for Aircraft Hydraulic Power Conversion Units

SAE AIR1811A-1997 液体冷却系统

This publication is applicable to liquid cooling systems of the closed loop type and the expendable coolant type in which the primary function is transporting of heat from its source to a heat sink. Most liquid cooling system applications are oriented toward the cooling of electronics. Liquid cooling techniques, heat sinks, design features, selection of coolants, corrosion control, and servicing requirements for these systems are presented. Information on vapor compression refrigeration systems, which are a type of cooling system, is found in Reference 1. The purpose of this Aerospace Information Report (AIR) is to provide guidelines for the selection and design of airborne liquid cooling systems.

Liquid Cooling Systems

SAE ARP699E-1997 飞机高温气动管道系统

This Recommended Practice is intended to outline the design, installation, testing, and field maintenance criteria for a high temperature metal pneumatic duct system, for use as a guide in the aircraft industry. These recommendations are to be considered as currently applicable and necessarily subject to revision from time to time, as a result of the rapid development of the industry.

High Temperature Pneumatic Duct Systems for Aircraft

SAE AMS3159E-1996 泄露试验溶液液态氧兼容

This specification has been declared "NONCURRENT" by the Aerospace Materials Division, SAE, as of February, 2005. It is recommended, therefore, that this specification not be specified for new designs. "NONCURRENT" refers to those specifications which have previously been widely used and which may be required on some existing designs in the future. The Aerospace Materials Division, however, does not recommend these specifications for future use in new designs. This specification covers a liquid oxygen compatible gas-leak deteching compound in the form of a liquid. This solution has been used typically in detecting leaks in liquid oxygen propulsion systems where a leak test solution (bubble fluid) is desirable, but usage is not limited to such applications.

Leak Test Solution Liquid Oxygen Compatible

SAE AIR4922-1996(R2008) 主飞行控制液压驱动系统接口定义

This SAE Aerospace Information Report (AIR) provides a description of the interfaces and their requirements for generic and specific hydraulic actuation systems used in the flight control systems of manned aircraft.Included are the basic control system characteristics and functional requirements, and the essential interfaces (structural, mechanical, hydraulic power, control input, status monitoring, and environment). Major design issues, requirements, and other considerations are presented and discussed.

Primary Flight Control Hydraulic Actuation System Interface Definition