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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).

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.

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.

The Waste Management/Rocket Propulsion System appears capable of satisfying many propulsion requirements; for example, orbit change maneuvers, aerodynamic drag makeup, midcourse correction, terminal braking, and auxiliary and emergency propulsion. ...To date, spacecraft designers have considered life support systems and rocket propulsion systems as independent subsystems of a manned spacecraft. The Integrated Waste Management/Rocket Propulsion System concept developed by Rocket Research Corp. under NASA Contract NAS 1–6750, has demonstrated that human waste products can form a useful propellant ingredient and provide propulsion, as well as be an effective means of removing and sterilizing spacecraft waste. ...The Integrated Waste Management/Rocket Propulsion System concept developed by Rocket Research Corp. under NASA Contract NAS 1–6750, has demonstrated that human waste products can form a useful propellant ingredient and provide propulsion, as well as be an effective means of removing and sterilizing spacecraft waste.

Hydrocarbon fuels capable of meeting high performance standards in advanced supersonic propulsion systems can be produced in substantial volume at reasonable cost from petroleum streams by hydrogenating aromatic concentrates or processing certain cuts from selected crudes.

This SAE Aerospace Information Report (AIR) outlines transient measurement methods to determine engine-generated levels of relevant compressor bleed air contaminant marker compounds on a ground level test cell for aircraft propulsion engine or auxiliary power unit (APU) to be fitted on civil and military aircraft. This AIR focuses on lubrication oils that might enter the bleed air through leaking engine seals or other sources.

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.

SAE J1979-3 describes the communication between the zero emissions propulsion systems and test equipment required by government regulations. Standardization regulations require passenger cars and light-, medium-, and heavy-duty trucks to support a minimum set of diagnostic information to external (off-board) “generic” test equipment.

This document is intended to satisfy the data reporting requirements of standardization regulations in the United States and Europe, and any other market that may adopt similar requirements in the future. This document specifies: a Message formats for request and response messages. b Timing requirements between request messages from external test equipment and response messages from vehicles, and between those messages and subsequent request messages. c Behavior of both the vehicle and external test equipment if data is not available. d A set of diagnostic services, with corresponding content of request and response messages. e Standardized source and target addresses for clients and vehicle. This document includes capabilities required to satisfy OBD requirements for multiple regions, model years, engine types, and vehicle types. At the time of publication many regional regulations are not yet final and are expected to change in the future.

The significant simultaneous improvement in these areas represents a formidable technical and economic challenge in airplane and propulsion system design, and it is important to identify those propulsion system and advanced technology areas which show a high potential payoff for the next generation supersonic transport. ...This paper will cover the promising propulsion systems including variable-cycle engine concepts for long-range supersonic commercial transport application. ...The benefits of applying advanced propulsion technology to solve the economic and environmental problems will be reviewed. The advanced propulsion technologies to be covered will be in the areas of structures, materials, cooling techniques, aerodynamics, variable engine geometry, jet noise suppressors, acoustic treatment, and low-emission burners.

This concept aims to allow effective and more efficient electric aeronautic propulsion through next generation of green all electric propulsion....Today state of electric-propulsion is demonstrating a lack of performance and operative range if compared to traditional propulsion concepts. This paper presents a novel concept which has been only envisaged before based on the increase of the performance and range of electric airplanes by an effective cogeneration on board.

An evaluation was made of advanced technology engine cycles, low emissions combustors and low noise exhaust nozzles which identified payoffs for advanced propulsion technology in terms of aircraft gross weight, stratospheric cruise emissions and airport noise reduction.

This paper endeavors to identify some of the requirements for the propulsion system of the advanced technology transport. These requirements lie in the areas of design, material selections, accessibility and maintainability of the system, and noise and emission control.

However the defined targets require major improvements in existing propulsion systems, especially on the gas generator itself. Regarding small power engines for business aviation, rotorcrafts or APU, the turboshaft is today a dominant technology, despite quite high specific fuel consumption. ...The objective of this paper is therefore to perform a detailed comparison between several propulsion systems for the particular application of a rotorcraft, taking into account realistic constraints (power to weight ratio, fuel economy…).

This paper describes an ice-crystal icing experiment conducted at the NASA Propulsion System Laboratory during June 2018. This test produced ice shape data on an airfoil for different test conditions similar to those inside the compressor region of a turbo-fan jet engine.

NASA has compiled a set of research goals for five year periods starting 2015, 2020 and 2025 for three classes of future subsonic aircraft, N+1 (2015), N+2 (2020) and N+3 (2025). With the intention of progressively making reductions in noise emissions, greenhouse gas emissions, fuel burn and energy consumption at each of these points to achieve Technology Readiness Levels (TRL's) of between 4 and 6. In the last few years much progress has been made towards achieving these goals through the development of new technologies and designs. This paper assesses how the current More Electric Aircraft (MEA) design concepts are advancing to allow the near term, N+1 goals of reducing 32 dB of noise emissions, 60% of the landing and take-off (LTO) NOx emissions, 55% of cruise emissions and 33% saving of fuel burn and energy consumption, relative to single aisle B737-800, could be met and eventually surpassed.

Following the electrification trend observed in the automotive industry, the idea of an electric propulsion aircraft has also drawn attention and investments from a range of aviation industry stakeholders (including the world's largest aerospace companies) focused on both fuel burning reduction and environmental performance improvement (greenhouse gases (GHG), pollutants and noise emissions) potential of electric propulsion technology. Electric propulsion has the potential to provide more efficient, cleaner, quieter and more profitable aviation services, with potential benefits to both airlines and passengers. ...Following the electrification trend observed in the automotive industry, the idea of an electric propulsion aircraft has also drawn attention and investments from a range of aviation industry stakeholders (including the world's largest aerospace companies) focused on both fuel burning reduction and environmental performance improvement (greenhouse gases (GHG), pollutants and noise emissions) potential of electric propulsion technology. ...From a technical perspective , the aviation propulsion electrification strategy might involves the integration of electric powetrains into aircrafts into the i) all electric; ii) hybrid and iii) turboelectric approach.

In the last decades, the requirement related to the reduction of energy waste has been focused on the aeronautical field for decreasing CO2 emissions in propulsion systems, coupled with the possibility of improving their ecological sustainability. Performance of hybrid electric aircraft are affected by the sizes and weights of propulsion systems typically constituted of internal combustion engines and electric motors. ...Performance of hybrid electric aircraft are affected by the sizes and weights of propulsion systems typically constituted of internal combustion engines and electric motors. Therefore, the correct design of propulsive architectures is fundamental to ensure a desired state of charge target level of batteries compliant with the flight plan provided by a driver unit. ...The MPC, designed as a supervisor, provides the best trade-off between command torques of motors belonging to a parallel-hybrid propulsion system to guarantee the final state of charge as close as possible to the initial one.

The Diagnostics Tested Facility (DTF) at NASA's John C. Stennis Space Center (SSC) in Mississippi was designed to provide a testbed for development of rocket engine exhaust plume diagnostics instrumentation. A 1200-lb thrust liquid oxygen (LOX)/gaseous hydrogen (GH2) thruster is used as the plume source for experimentation and instrument development. Theoretical comparative studies have been performed with aero-thermodynamic codes to ensure that the DTF thruster (DTFT) has been optimized to produce a plume with pressure and temperature conditions as much like the plume of the Space Shuttle Main Engine (SSME) as possible. Operation of the DTFT is controlled by an icon-driven software program using a series of soft switches. Data acquisition is performed using the same software program. A number of plume diagnostics experiments have utilized the unique capabilities of the DTF.

Recently several researchers have proposed utilizing the DBD in various configurations to act as viable propulsion systems for micro and nano aerial vehicles. The DBD produces stable atmospheric-pressure non-thermal plasma in a thin sheet with a preferred direction of flow. ...Several researchers have utilized DBDs in an annular geometric setup as a propulsion device. Other researchers have used them to alter rectangular duct flows and directional jet devices.