The report shows how the methodology of measurement uncertainty can usefully be applied to test programs in order to optimize resources and save money. In doing so, it stresses the importance of integrating the generation of the Defined Measurement Process into more conventional project management techniques to create a Test Plan that allows accurate estimation of resources and trouble-free execution of the actual test. Finally, the report describes the need for post-test review and the importance of recycling lessons learned for the next project.
The scope of this document is limited to encompass terminology, symbols, performance criteria and certain elementary test methods reflecting the current status of the technology.
The scope of this document is limited to encompass terminology, symbols, performance criteria and certain elementary test methods reflecting the current status of the technology.
This document has been formulated as a suggested guide in assisting EIA Engineering Department Panels and JEDEC Councils in cooperating with the Defense Department and other Federal agencies in the preparation of suggested reliability requirements for various types of electronic products as part of a program designed to enhance the reliability of defense and related equipment. The document is to be followed merely as a guide and is not intended to limit technical groups in the consideration of the factors to be taken into account in the development of reliability specifications for recommendation to the Government.
Shortly after World War II, as aircraft became more sophisticated and power-assist, flight-control functions became a requirement, hydraulic system operating pressures rose from the 1000 psi level to the 3000 psi level found on most aircraft today. Since then, 4000 psi systems have been developed for the U.S. Air Force XB-70 and B-1 bombers and a number of European aircraft including the tornado multirole combat aircraft and the Concorde supersonic transport. The V-22 Osprey incorporates a 5000 psi hydraulic system. The power levels of military aircraft hydraulic systems have continued to rise. This is primarily due to higher aerodynamic loading, combined with the increased hydraulic functions and operations of each new aircraft. At the same time, aircraft structures and wings have been getting smaller and thinner as mission requirements expand. Thus, internal physical space available for plumbing and components continues to decrease.
Shortly after World War II, as aircraft became more sophisticated and power-assist, flight-control functions became a requirement, hydraulic system operating pressures rose from the 1000 psi level to the 3000 psi level found on most aircraft today. Since then, 4000 psi systems have been developed for the U.S. Air Force XB-70 and B-1 bombers and a number of European aircraft including the tornado multirole combat aircraft and the Concorde supersonic transport. The V-22 Osprey incorporates a 5000 psi hydraulic system. The power levels of military aircraft hydraulic systems have continued to rise. This is primarily due to higher aerodynamic loading, combined with the increased hydraulic functions and operations of each new aircraft. At the same time, aircraft structures and wings have been getting smaller and thinner as mission requirements expand. Thus, internal physical space available for plumbing and components continues to decrease.
This aerospace test standard establishes the requirements and procedures for evaluating and comparing the impulse fatigue performance of high pressure hydraulic fittings and tubing. This test method may be used to test similar fluid system components, if desired.
This standard establishes the requirements and the procedures for impulse testing of hose assemblies, tubing, and fittings for use in aerospace metric hydraulic systems.
This standard establishes the requirements and the procedures for impulse testing of hose assemblies, tubing, and fittings for use in aerospace metric hydraulic systems.
This standard provides an environmental performance test method for thermal shock testing of fluid system piping and fittings, excluding hose and hose assemblies.
This standard provides an environmental performance test method for thermal shock testing of fluid system piping and fittings, excluded hose and hose assemblies.
This document establishes the temperature types and pressure classes that are commonly used in aerospace fluid systems. The temperature types and pressure classes are equivalent, but not identical, to the SI units defined in MA2001 (ISO 6771). For exact conversion use NAS 10000.
This document establishes the temperature types and pressure classes that are commonly used in aerospace fluid systems. The temperature types and pressure classes are equivalent, but not identical, to the SI units defined in MA2001 (ISO 6771). For exact conversion use NAS 10000.