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This SAE Aerospace Standard (AS) provides a performance station designation system for aircraft propulsion systems and their derivatives.

On the Thermodynamic Spectrum of Airbreathing Propulsion - Insights from 1958 are valid guidelines yet in 1988 - Paul Czysz. Staff Manager, McDonnell Douglas Fellow.

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.

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.

In addition, a study was performed to compare candidate lox/HC propulsion system concepts and to evaluate major system/component design options. The data generated provide quantitative substantiation of trends previously experienced with hypergolic propellants and with a lox and rocket propellant combination.

According to some, electric propulsion is already on its way down the “trough of disillusionment.” This report argues that while there are some concerns with associated technologies, such pessimism is unwarranted. ...Yes, these unsettled questions may take a little longer to solve than originally estimated, but there is full expectation within the industry that electric propulsion for commercial aircraft will succeed. In this SAE EDGE Research Report we present points of view from leading researchers in the industry who are thinking deeply about solving these problems.

An integrated, multidisciplinary environment of a tactical aircraft platform has been created by leveraging the powerful capabilities of both MATLAB/Simulink and Numerical Propulsion System Simulation (NPSS). The overall simulation includes propulsion, power, and thermal management subsystem models, which are integrated together and linked to an air vehicle model and mission profile. ...The model has the capability of tracking temperatures and performance metrics and subsequently controlling characteristics of the propulsion and thermal management subsystems. The integrated model enables system-level trade studies involving the optimization of engine bleed and power extraction and thermal management requirements to be conducted.

Hybrid electric aircraft propulsion is an emerging technology that presents a variety of potential benefits along with technical integration challenges. ...Developing these new propulsion architectures with their complex control systems, and ultimately proving their benefit, is a multistep process. ...This paper describes the NASA-developed tools and puts them in the context of control system development for hybrid electric aircraft propulsion. The three MATLAB®-based software packages are the Toolbox for the Modeling and Analysis of Thermodynamic Systems (T-MATS), the Electrical Modeling and Thermal Analysis Toolbox (EMTAT), and the Thermal Systems Analysis Toolbox (TSAT).

These advances have enhanced the usage of the code in the areas of liquid propulsion, fire suppression, and environmental control systems (ECLSS), providing for the first time a common framework for analysis and data exchange between engineers in these otherwise distinct specialties.

It analyses the heat transfer process through the wall of the combustion chamber of a pulsejet for aeronautic propulsion. The inside wall is exposed to burning gases with an average temperature of 1500 K, which oscillates with an amplitude 500 k and a frequency of 50 Hz.

Therefore, a fireproof test was conducted using 6AL-4V titanium structure for the attachment of the propulsion system on a mid-size business jet to satisfy FAA Federal Aviation Requirement 25.865. ...The fire test simulates a fire on the aircraft from the propulsion system by using a burner with jet fuel exposing the component to a 2000 °F (1093°C) flame.

This SAE Aerospace Recommended Practice (ARP) provides performance station designation and nomenclature systems for aircraft propulsion systems and their derivatives.

This SAE Aerospace Recommended Practice (ARP) provides performance station designation and nomenclature systems for aircraft propulsion systems and their derivatives.

This SAE Aerospace Standard (AS) provides performance station designation and nomenclature systems for aircraft propulsion systems and their derivatives.

This SAE Aerospace Standard (AS) provides performance station designation and nomenclature systems for aircraft propulsion systems and their derivatives.

This SAE Aerospace Standard (AS) provides a performance station designation system for aircraft propulsion systems and their derivatives. The station numbering conventions presented herein are for use in all communications concerning propulsion system performance such as computer programs, data reduction, design activities, and published documents. ...The station numbering conventions presented herein are for use in all communications concerning propulsion system performance such as computer programs, data reduction, design activities, and published documents. ...Numbering conventions for instrumentation used in testing aircraft propulsion systems are not explicitly addressed in AS755. Other industry resources, such as ARP246, AIR1419, and AGARD-AR-245, provide recommendations and guidance based on AS755 station numbering and AS6502 nomenclature principles.

Separate procurements for air vehicle, propulsion system, and avionics have contributed to the development of aircraft that are sub-optimized from a thermal management viewpoint. ...Thermal integration between the air vehicle, propulsion system, and avionics can be particularly important from a thermal management standpoint.

Modern propulsion system designers face challenges that require that aircraft and engine manufacturers improve performance as well as reduce the life-cycle cost (LCC). ...These improvements will require a more efficient, more reliable, and more advanced propulsion system. The concept of smart components is built around actively controlling the engine and the aircraft to operate optimally. ...This process involves defining, developing, and validating against requirements for key integrated propulsion, power, and thermal management system capabilities.

Some rotorcraft may use an alternate source of propulsion system power to supplement engine output shaft power delivered. If RFM performance includes the contribution of a Supplemental Power Unit (SPU), then the installed power available of the SPU should also be defined and measured, for which the power loss factors and methods described in this document may be applicable.

At the same time, propulsion systems have become increasingly complex as mission criteria push the limits of present technologies. ...At the same time, propulsion systems have become increasingly complex as mission criteria push the limits of present technologies. These propulsion system advancements require detailed understanding of engine performance and test cell interactions.