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With the imminent development of the United States Mach 3 Supersonic Transport (SST), aircraft hydraulic fluid state-of-the-art must take another step forward to meet system performance requirements combined with high temperature environments.

While the SST will operate in environments that are new to commercial passenger airplanes, its flight control system introduces no radical changes in operating procedures. All primary flight control surfaces are operated by triple, noninterconnected hydraulic systems. The normal mode of longitudinal and lateral control employs an electrical command system and mechanical backup is provided. Multichannel stability augmentation is introduced on all three control axes. Optimum lift/drag characteristics are assured through variable-sweep wings, direct lift control, and the secondary flight controls. Trim is accomplished by displacing the primary control surfaces. Development of flight control system components is progressing on schedule.

Aircraft which fly at supersonic speeds for long periods of time encounter conditions which require incorporation of a hydraulic fluid cooling system.

This AS covers subsonic and supersonic Mach meter instruments which, when connected to sources of static (Ps), and total (Pt), or impact (Pt-Ps), pressure provide indication of Mach number.

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.

The fluid used in hydraulic systems is one of the strongest links in this total system of safety, reliability, and maximum utilization, and may indeed be crucial in supersonic craft of the future. This paper describes the chemical properties of hydraulic fluids, how they relate to present and advanced designs, and points up maintenance problems and their solutions.

The paper discusses special problems of hydraulic system design for a supersonic transport resulting from high ambient temperatures, weight and space limitations, and the requirements of the working fluid.

The results of pump loop testing 50 candidate supersonic transport (SST) hydraulic fluids were presented to the May 1965, SAE Aerospace Fluid Power Systems and Equipment Conference in Los Angeles.

Discussion will include: Brief review of hydraulic system circuits and the redundancy for complete flight safety back up The need for operator concern over system integrity and internal leakage The periodic checks and measurements used to monitor and control the system integrity These contemporary problems and procedures give us some insight into the more sophisticated matters of the future that must concern the operation of a Supersonic Transport.

The studies addressed actuation of canard and rudder control surfaces on supersonic Navy-fighter aircraft.

The YF-23A Advanced Tactical prototype Fighter was a revolutionary statically unstable, twin engine aircraft that cruised at supersonic speeds without afterburner and was designed to out maneuver opponents at subsonic and supersonic speeds. ...The YF-23A Advanced Tactical prototype Fighter was a revolutionary statically unstable, twin engine aircraft that cruised at supersonic speeds without afterburner and was designed to out maneuver opponents at subsonic and supersonic speeds. Combining these capabilities into a chosen aircraft configuration demanded a flight control hydraulic system of unprecedented power and performance. ...The YF-23A's unique flight and maneuvering envelope required high surface rates and large actuator excursions at low flight speeds, as well as power to generate increased hinge moments at supersonic speeds. To achieve these specifications, Northrop developed a hydraulic system that utilized flow conservation and prioritization techniques.

Studies and wind tunnel tests for a supersonic interceptor were conducted at the Vultee Division of Consolidated Vultee Aircraft Corporation (Convair) in 1945. ...It will be on display for the world to see this one airplane that pioneered the development of the delta wing proving its worth as an efficient aerodynamic shape for transonic and supersonic flight.

These operational criteria will become even more critical in the supersonic transport (SST), and additional demands will be made upon the hydraulic fluid. This paper will describe the development of a new fire-resistant hydraulic fluid specifically designed for the SST.

This AS covers subsonic and supersonic Mach Meter instruments which, when connected to sources of static (Ps), and total (Pt), or impact (Pt-Ps), pressure provide indication of Mach number.

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.

The pressurization system design considerations presented in this AIR deal with human physiological requirements, characteristics of pressurization air sources, methods of controlling cabin pressure, cabin leakage control, leakage calculation methods, and methods of emergency cabin pressure release.

Hypersonic aircraft represent a radical departure from contemporary air vehicles in terms of system performance requirements and operating envirnoment. Flight control components may encounter environmental temperatures as high as 1600 F during high Mach number cruise. A basic re-evaluation of auxiliary power distribution techniques has been made to determine the type of system most suitable for use under these conditions. Five types were considered: 1. Cooled hydraulic system. 2. Liquid metal system. 3. Pneumatic system. 4. Pulsating flow hydraulic system (using conventional fluid in the moderate temperature, and liquid metal in the higher temperature portions of the vehicle). 5. Mechanical system. These systems have been evaluated for use in a high Mach number cruise aircraft on the basis of weight, power requirements, and cooling requirements.

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.

This SAE Aerospace Information Report (AIR) covers the field of civilian, commercial and military airplanes and helicopters. This summary of tail bumper design approaches may be used by design personnel as a reference and guide for future airplanes and helicopters that require tail bumpers. Those described herein will consist of simple rub strips, structural loops with a wear surface for runway contact, retractable installations with replaceable shock absorbers and wear surfaces and complicated retractable tail landing gears with shock strut, wheels and tires. The information will be presented as a general description of the installation, its components and their functions.

The pressurization system design considerations presented in this AIR deal with human physiological requirements, characteristics of pressurization air sources, methods of controlling cabin pressure, cabin leakage control, leakage calculation methods, and methods of emergency cabin pressure release.