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To establish recommended hole sizes for use with protruding head metric threaded fasteners primarily used on propulsion equipment, and provide the recommended positional tolerance for use with these holes.

This recommended practice covers design requirements for silver, copper and nickel brazed joints, primarily for tube connections, for aerospace propulsion systems. The environmental conditions stated herein, and those given in the applicable AMS specifications, provide the limitations of this ARP.

This recommended practice covers a series of stands that may be used for assembly, disassembly and maintenance; incorporating the following design criteria: a collapsible frame construction, envelope dimensions, attachment shear pad configuration and gear box and caster specifications.

A landmark study of Synerjet propulsion for fully-reusable Earth/orbit transport missions was conducted for NASA in 1965-67 by a study team of Marquardt, Rocketdyne, and Lockheed (the present author led this effort). ...Synerjet propulsion systems are fully integrated aerospace vehicle power-plants, comprising both airbreathing and rocket hardware subsystems and technologies.

This SAE Aerospace Information Report (AIR) reviews performance testing parameters for non-cleanable (often referred to as disposable) filter elements utilized in aircraft power and propulsion lubrication systems, including gas turbine engines and auxiliary power units (APUs), propulsion and transmission gear boxes, and constant speed drives and integrated drive generators (IDGs). ...This SAE Aerospace Information Report (AIR) reviews performance testing parameters for non-cleanable (often referred to as disposable) filter elements utilized in aircraft power and propulsion lubrication systems, including gas turbine engines and auxiliary power units (APUs), propulsion and transmission gear boxes, and constant speed drives and integrated drive generators (IDGs).

Propulsion system hardware has steadily increased in complexity which has placed even greater demands on the propulsion control hardware. ...Propulsion system hardware has steadily increased in complexity which has placed even greater demands on the propulsion control hardware. With the engine and inlet operating at higher levels of performance, the need for improvements in control system technology has become more evident. ...In addition to increased sensing and computation, it is required that the various inlet and engine control functions be integrated to achieve maximum propulsion system stability and performance during all flight conditions. This paper describes a three year exploratory research program for the design, development, and flight evaluation of an Integrated Propulsion Control System (IPCS).

A critical evaluation of spacecraft propulsion requirements for the 1970 decade is presented. The anticipated types of this time period are surveyed to identify future applications of present hardware and areas requiring new propulsive media.

Integration of propulsion controls can simplify the task of aircraft power management. Not only can integration ease the pilot's problem of adjusting engine power settings according to the flight mode, but it also enables improved propulsion system performance to be achieved and extends the regions of safe and stable operation. ...Not only can integration ease the pilot's problem of adjusting engine power settings according to the flight mode, but it also enables improved propulsion system performance to be achieved and extends the regions of safe and stable operation.

Propulsion system controls have been steadily increasing in complexity to meet the regulation and limiting requirements of current and future turbine engines. ...This requirement further increases the sensing, computational and regulation functions of the propulsion system control. In the past, electronic controls have played a subordinate role because of the severe turbine engine flight environment and the computational needs of the engine could usually be met by hydromechanical components. ...With this insight, more timely planning and execution of state-of-the-art advances in propulsion system control technology can be accomplished to meet the functionability, performance, and confidence goals of future propulsion system hardware.

Two propulsion related drag correlation parameters have been developed. Existing or planned parametric jet aftbody drag data can therefore be reduced into a simple prediction technique for aircraft preliminary design studies. ...The drag due to the external nozzle geometry correlates with the average slope of the aftbody's area distribution (Integral Mean Slope), and the drag influence of the internal nozzle geometry/exhaust plume correlates with an effective plume inclination angle (Plume Correlation Parameter). The propulsion related drags of single, twin, and two-dimensional jet installations, and convergent, convergent-divergent, and plug nozzles are shown to correlate with the two parameters.

A multimode propulsion control system concept has been developed for the remotely piloted research vehicle of the NASA Highly Maneuverable Aircraft Technology program.

The technology of waterjet propulsion has reached a state of development where discussion of all technical aspects is beyond the scope and intent of this paper.

Current activities in seals for space propulsion turbomachinery that the NASA Lewis Research Center sponsors are surveyed. The overall objective is to provide the designer and the researcher with the concepts and the data to control seal dynamics and leakage.

A decentralized, multivariable controls methodology is being developed for the functional integration of a fighter's aerodynamic controls with those of its propulsion system (inlet, engine, and thrust vectoring/reversing nozzle). Integrated controls account for, and take advantage of the significant cross-coupling between these system elements.

This paper describes the status of the compact multimission aircraft propulsion simulator (CMAPS) technology. Three CMAPS units have accumulated a total of 340 hr during approximately 1-1/2 yr of static and wind-tunnel testing.

This SAE Aerospace Standard (AS) covers devices whose primary function is the retention of fasteners, except for such devices that are integral with the item being retained.

Vertical landing/takeoff candidate aircraft will require some type of Reaction Control System (RCS) for aircraft balance, control, and maneuver during jet-boume flight. Typically these systems require high pressure compressor bleed air to be discharged through nozzles located on the wing tips, nose and tail of the aircraft for hover stability. Bleed rates on the order of 10 to 20 lbs/sec could be required with the source of air from compressor interstage, compression discharge or a combination from both locations.

This recommended practice covers a stand that may be used for assembly, disassembly, and maintenance. The stand incorporates the following design criteria: complete interchangeability of any and all components, collapsible frame construction, envelope dimensions (marked with an asterisk on the attached drawings), attachment pad configuration, and gearbox and caster specifications.

Two decades of turboprop technology advances are discussed along with their application to a Prop-Fan propulsion system for modern high-speed commercial aircraft. The Prop-Fan propulsion system features a small diameter, multibladed propulsor geared to an advanced gas turbine engine. ...Several advanced technologies in the airframe and propulsion disciplines have been identified by NASA, with the turboprop being one of these. Two decades of turboprop technology advances are discussed along with their application to a Prop-Fan propulsion system for modern high-speed commercial aircraft.