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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 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.

This paper reviews a recent internal study by Pratt & Whitney to define the optimum propulsion system characteristics for a commercial transport designed to fly at Mach 0.95. The impact on aircraft gross weight of propulsion cycle characteristics such as bypass ratio, overall pressure ratio, turbine temperature, nacelle weight, and drag as well as the important criteria of noise is reviewed. ...The impact on aircraft gross weight of propulsion cycle characteristics such as bypass ratio, overall pressure ratio, turbine temperature, nacelle weight, and drag as well as the important criteria of noise is reviewed.

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

This paper presents the results achieved during the first year of this Atlas Propulsion Diagnostics Program and discusses the goals, approach, and accomplishments of the effort.

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

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.

Experimental data on performance and cooling from sea level and altitude firing tests of fluorine/oxygen mixtures with light-hydrocarbon fuels are presented. The majority of the work has been oriented toward pressure-fed rocket applications, with testing at 5000-lb vacuum thrust and 100-psia chamber pressure. Work in progress is at chamber pressures of 250 and 500 psia, being oriented toward pump-fed rocket applications. High delivered specific impulse levels have been demonstrated. One problem, apparently unique to these propellants, is that performance at the optimum mixture ratio is extremely sensitive to incomplete mixing.

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.

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).

SAE Aerospace Information Report AIR1871 provides valuable insight into lessons learned in the development, implementation, and operation of various health monitoring systems for propulsion engines and drive train systems. This document provides an overview of the lessons learned for ground-based systems, oil debris monitoring systems, lubrication systems, and Health and Usage Monitoring Systems (HUMS) for military and commercial programs. ...The lessons learned presented in this document represent a fragment of the knowledge gained through experience when developing and implementing a propulsion health management system. Previous versions of this document contain additional lessons learned during the 1980’s and 1990’s that may be of additional value to the reader.

Optimization of a Prop-Fan propulsion system for a Mach 0.8, 120 passenger commercial transport has shown the need for relatively high levels of overall pressure ratio, combustor exit temperature, propeller tip speed and propeller disk loading to achieve lowest fuel burn and direct operating costs. ...Comparison of this optimized Prop-Fan propulsion system with an equivalent technology turbofan showed it to have significant mission fuel burn and direct operating cost advantages.

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).

This ARP outlines recommended practices to quantify the concentrations of a subset of bleed air contaminant marker compounds on an aircraft propulsion engine or APU prior to delivery and installation on civil and military aircraft. Testing is specified during steady state (non-transient) operation only, in a ground level test bed.