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This document is intended to serve as suitable guidance for propulsion system manufacturers and applicants for propulsion system type certification. It is also intended to provide guidance for subsequent propulsion system integration into aircraft systems for aircraft certification and operational use. ...The purpose of this SAE Aerospace Information Report (AIR) is to provide guidance for aircraft engine and propeller systems (hereafter referred to as propulsion systems) certification for cybersecurity. Compliance for cybersecurity requires that the engine control, propeller control, monitoring system, and all auxiliary equipment systems and networks associated with the propulsion system (such as nacelle systems, overspeed governors, and thrust reversers) be protected from intentional unauthorized electronic interactions (IUEI) that may result in an adverse effect on the safety of the propulsion system or the airplane. ...Compliance for cybersecurity requires that the engine control, propeller control, monitoring system, and all auxiliary equipment systems and networks associated with the propulsion system (such as nacelle systems, overspeed governors, and thrust reversers) be protected from intentional unauthorized electronic interactions (IUEI) that may result in an adverse effect on the safety of the propulsion system or the airplane.

This document applies to prognostics of aerospace propulsion systems. Its purpose is to define the meaning of prognostics in this context, explain their potential and limitations, and to provide guidelines for potential approaches for use in existing condition monitoring environments.

This SAE Aerospace Standard (AS) provides classical propulsion system performance parameter names for aircraft propulsion systems and their derivatives, and describes the logical framework by which new names can be constructed.

While providing these example architectures, this document will develop common definitions for the elements of the architectures by defining: 1 The elements of electrified propulsion architectures, including any dedicated power generation and distribution systems as well as energy storage elements. 2 The interfaces to/from the electrified propulsion system. 3 The interfaces within the electrified propulsion system. 4 Electrical energy management and storage architecture of an electrified propulsion system. ...The application of electric power for aircraft propulsion can take a variety of forms, ranging from partial electric to full electric. The introduction of electric engines to drive propulsors, along with the variety of available methods to generate electricity and store energy offers great degree of new design freedom for next-generation aircraft and aircraft architectures. ...This newfound design freedom exposes a need within the aviation industry to establish a common design language for electrified propulsion. While this need for a common design language is recognized, the intent of this document is to encourage innovation, providing reference architectures as a launching point for future work in this area.

Create and publish a list of terms relevant to electrified propulsion aircraft with summary text descriptions. The terms and descriptions will not provide full explanations, diagrams, and other detailed technical descriptions. ...This document defines the relevant terms and abbreviations related to the design, development, and use of electrified propulsion in aircraft. This definition is provided to enable a consistent use of technical language throughout the standards developed by the E-40 committee.

This document lists recommended noun titles for drawings of support equipment and provides definitions for each. The use of secondary modifiers to distinguish a part from similar parts is also covered.

This Aerospace Information Report (AIR) presents metrics for assessing the performance of diagnostic and prognostic algorithms and systems delivering propulsion health management functions.

Aviation propulsion development continues to rely upon fossil fuels for the vast majority of commercial and military applications. ...With those challenges in mind, research and development of more efficient and electric propulsion systems will expand. Fuel-cell technology is but one example that addresses such emission and resource challenges, and others, including negligible acoustic emissions and the potential to leverage current infrastructure models. ...Requirements for greater flight time, stealth characteristics, and thrust-to-power ratios adds urgency to the development of efficient propulsion methods for applications such as UAVs, which looks to technologies such as asymmetrical capacitors to enhance electric propulsion efficiency.

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.

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.

This SAE Aerospace Information Report (AIR) provides guidelines to document the functional and physical interface requirements for the electrical systems (including an Electronic Engine Control System (EECS) and its components) between a given propulsion system and the aircraft on which the system is installed. The Interface Control Document (ICD) is considered to be a subset of the Engine Installation Manual, with interface considerations between the Airframer and Engine manufacturer.

Measurements of the gas state properties in hypersonic propulsion system research present unique problems demanding unconventional diagnostic measurement system design solutions.

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.

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.

To achieve this goal, NASA has analyzed a hybrid body wing aircraft with a turboelectric distributed propulsion system. The propulsion system must be designed to operate at the highest possible efficiency in order to meet the reduced fuel burn goal. ...High density components are required to minimize the weight of the electric propulsion system while meeting the high power demand. Minimizing the electric propulsion system weight helps to reduce the amount of fuel required for propulsion. ...NASA's N3-X aircraft design under the Research and Technology for Aerospace Propulsion Systems (RTAPS) study is being designed to meet the N+3 goals, one of which is the reduction of aircraft fuel burn by 70% or better.