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An aircraft propulsion system for Mach .6 flight is being developed which utilizes two turboshaft engines driving a pusher propeller through driveshafts and a combining gearbox.

The paper gives an overview of the propulsion content of the programs at the undergraduate and postgraduate levels, as offered to students in both Mechanical and Aerospace Engineering.

The program is being conducted at Rocketdyne, a division of North American Rockwell Corporation, under the sponsorship of the Air Force Rocket Propulsion Laboratory under Contract F04611-67-C-0116. This paper summarizes the accomplishments of the program to date, and describes the engine system and its possible application to the orbit-to-orbit shuttle (OOS).

Several ramjet propulsion systems are evaluated for future Earth-to-orbit transportation designed for reduced operational cost, reduced loads on payloads, and increased flexibility of launch site and schedule.

The C-5A propulsion system installation is described and discussed. Induction system, exhaust system, and thrust reverser configurations define the general nacelle concepts.

These crew safety requirements impose many unusual constraints that are not required in launch vehicle or unmanned propulsion system designs. These requirements and their effects on design and operation are discussed and the systems operational experience on Apollo models are presented.

General Electric is conducting a Propulsion Study for NASA as part of the Small Transport Advanced Technology (STAT) program. The General Electric CT7 is used as the current modern turboprop engine baseline.

The prop-fan propulsion system is being investigated as part of the NASA Aircraft Energy Efficiency program which includes both analytical studies and experimental tests.

A unique propulsion system is being developed for the Space Shuttle Orbiter utilizing airbreathing engines to provide a means for horizontal flight testing and ferrying the Orbiter within the contiguous United States. ...The airbreathing engine arrangement which has resulted, while employing conventional propulsion subsystems, still possesses installation problems because of the low ground clearance.

Because of its high overall propulsion system efficiency, the turbofan engine is now being chosen for most military and commercial airplanes.

There are future military and commercial propulsion requirements, however, where the anticipated market may not be sufficiently large or firm to provide the basis for a new development, for example, a medium size commercial or military STOL aircraft.

A method that exploits certain properties of a recirculating gas has been investigated as a means of achieving a sustained accelerative vector force without either the expulsion of mass from or a reaction against an external mass by the accelerated body. A theory of operation is presented that defines the capabilities and limitations of the method, and which has resulted in functioning prototypes. The prototype devices require only a source of electric power and a means of cooling to achieve an internally generated, externally measurable accelerative vector force that is sustained for as long as power is supplied to the device.

Studies recently completed for NASA show significant improvements in duct heating turbofans and low-bypass turbojets for an advanced supersonic transport. Dual-valve variable-cycle engines (VCE) prove to be noncompetitive; however, an emerging double-bypass dual-cycle VCE concept is reviewed which does indicate range improvements that are possible. It is 1985 technology and would require extensive development. Engine availability in the United States,as important to program success as technology or economics,is discussed. A fan derivative of an improved-technology Rolls Royce Olympus engine is also considered. An interesting case is developed showing that an Olympus fan derivative on a Douglas AST design offers an earlier U.S. SST possibility than heretofore thought possible. This might be important if airline pressure should mount as a result of overwhelming public demand for Concorde supersonic travel.

Continued performance demands make interceding attractive on single-engine turbosupar-charged applications. Intercooling permits power increases which yield significant speed improvements particularly at altitude. Attention paid to ducting as well as cooler sizing results in very effective installations.

The requirements of engine test cells and propulsion laboratories for propulsion education will be discussed. A typical versatile propulsion laboratory set-up for testing full-scale aircraft reciprocating engines, gas turbines, as well as small-scale rocket motors will also be presented. ...There are a variety of propulsion packages available for general aviation aircraft including reciprocating engines, small gas turbines, and rotary engines. ...In future, electrical propulsion will be a major contender in this market. The importance of general aviation propulsion education for aeronautical engineers will be addressed.

The author discusses the ADAM II (Air Deflection and Modulation) propulsion system as it is applied to LTV propulsive wing airplane configurations which house all or part of their propulsion system within the wing surface. ...The author discusses the ADAM II (Air Deflection and Modulation) propulsion system as it is applied to LTV propulsive wing airplane configurations which house all or part of their propulsion system within the wing surface. Briefly mentioned are the original ADAM I configuration and its subsequent development to the present ADAM II, together with a discussion of the characteristics currently used for each of its components such as fan turbine set, gas generator, hot gas ducting, wing mounted turbofans, and mechanical cross shafting. ...The ADAM II concept is applicable to a full spectrum of subsonic aircraft and the propulsion system uses present day state-of-the-art technology which makes the feasibility of its development quite real.

The steps involved in design and development of the L-1011 propulsion system, with emphasis on maintenance aspects of the program, are summarized. System requirements, including maintainability and reliability, performance, and noise are reviewed. ...Major factors leading to determination of the propulsion system configuration are summarized and the rationale for meeting requirements of the various components leading to a well balanced propulsion system is presented. ...Major factors leading to determination of the propulsion system configuration are summarized and the rationale for meeting requirements of the various components leading to a well balanced propulsion system is presented. It is shown that the three-spool RB.211 engine satisfies requirements for minimum maintenance of the basic engine.

The characteristics of current space propulsion systems are reviewed, including performance, storability, restart, and throttling. Their limitations are discussed with emphasis in the area of long-term storage coupled with high performance.

This paper describes propulsion systems under consideration for orbital maneuvering stages (Space Tug or Orbit-to-Orbit Shuttle). ...It describes the Space Tug/Orbit-to-Orbit Shuttle (OOS) configurations, and the missions to be performed by the Space Tug/OOS. The propulsion system requirements for the Space Tug/OOS main engine and the attitude control systems are described. ...A listing of the propulsion system candidates for this application is provided. Briefly described are existing systems such as Delta, Agena, Centaur, and Transtage.

Apollo 17 ended the most successful application of rocket propulsion systems in man's history. A total of 23 developmental and manned operational flights were made. ...Over 6 h of manned rocket flights were logged by the spacecraft propulsion systems and approximately one million rocket engine firings were made. One engine failure was encountered on an early unmanned flight as a result of a failure in the guidance programmer which caused the engine to operate in a manner known to cause failures. ...This paper will present some highlights of Apollo propulsion performance and will provide a bibliography of all flight results.