Showing papers on "Propulsion published in 1994"

Hypersonic Airbreathing Propulsion

Abstract: The next great leap for jet propulsion will be to power-sustained, efficient flight through the atmosphere "Hypersonic Airbreathing Propulsion presents the first comprehensive, unified introduction to all elements of the scramjet engine that will make this feat possible The text emphasizes fundamental principles, guiding concepts, analytical derivations, and numerical examples having clear, useful, insightful results

Analytical aeropropulsive-aeroelastic hypersonic-vehicle model with dynamic analysis

Abstract: The determination of the dynamic characteristics of hypersonic vehicles requires an integrated approach since the propulsion system and airframe are so highly coupled. The forces and moments arise from both aerodynamic and propulsive sources, which are for these configurations hard to separate. Offered herein is a first step toward the development of such an approach that is intentionally generic and basic. Further, analytical expressions are developed to allow for characterization of the vehicle's dynamics early in the design cycle, so that configuration trade-offs may be performed with some cognizance of the attitude dynamics. The method of approach involves a two-dimensional hypersonic aerodynamic analysis utilizing Newtonian theory, coupled with a one-dimensional aero/thermo analysis of the flow in a SCRAMjet-type propulsion system. In addition, the airframe is considered to be elastic, and the structural dynamics are characterized in terms of a simple lumped-mass model of the in vacuo vibration modes. The vibration modes are coupled to the rigid-body modes through the aero/propulsive forces acting on the structure. The control effectors considered on a generic study configuration include aerodynamic pitch-control surfaces as well as engine fuel flow and diffuser area ratio. It is shown that the vehicle's aerodynamics and propulsive forces are both very significant in the evaluation of key stability derivatives that dictate the vehicle's dynamic characteristics. It is also shown that the vehicle model selected is highly unstable in pitch and exhibits strong airframe/engine/elastic coupling in the aeroelastic and attitude dynamics. With the use of literal expressions for both the system's poles and zeros as well as the stability derivatives, key vehicle dynamic characteristics are investigated. For small errors, or uncertainties, in either the aerodynamic or propulsive forces, significant errors in the frequency and damping of the dominant modes and zero locations will arise. AD AN b Cp g h /i h L L i

Influence of Hydrodynamic Design and Propulsive Mode on Mammalian Swimming Energetics

Abstract: Optimisation of energy by aquatic mammals requires adaptations that reduce drag, and improve thrust production and efficiency. Drag is minimised by streamlining the body and appendages. Highly derived aquatic mammals have body shapes close to the optimal hydrodynamic design for drag reduction. There is no conclusive evidence for specialised drag reduction mechanisms, although decreasing hair density is associated with reduced drag. Improvement in thrust production and efficiency is accomplished by changes in propulsive mode and appendage design. Semiaquatic mammals employ drag-based propulsion using paddles, whereas fully aquatic mammals use lift-based propulsion with hydrofoils. Because paddling generates thrust through half the stroke cycle, propulsive efficiency is low and energetic cost is high compared with that for mammals using hydrofoils. Lift-based swimming is a rapid and high-powered propulsive mode. Oscillations of the hydrofoil generate thrust throughout the stroke cycle. For cetaceans and pinnipeds, propulsive efficiency is approximately 80%, and transport cost is below that of semiaquatic mammals. Behavioural adaptations help minimise energy expenditure by swimming mammals. Submerged swimming avoids increased drag from energy lost in formation of surface waves. Porpoising and wave riding, characteristic of dolphins, can reduce the transport costs, allowing for longer-duration swimming at high speeds.

Hybrid drive system

Abstract: A propulsion system includes an internal combustion engine predominantly operating in a steady-state mode and a driving engine operating in a transient mode, which act on the output shaft of a planetary gear train by first and second drive shafts. To obtain independent speed and torque values at the driven shaft, an additional transiently operating engine is provided which has a fixed r.p.m. ratio with the first drive shaft or the driven shaft of the planetary gear train. The two transient engines are configured as hydraulic engines or electric engines connected to a control device, a unit being provided for hydraulic or electric power flow between the two transient engines, which in turn is provided with an energy storage.

Design and construction of a wheel-directly-coupled axial-flux PM motor prototype for EVs

Abstract: In electric vehicle (EV) motor drives, the use of a low-speed motor coupled directly to the wheel axle allows a reduction of the vehicle weight and an improvement in the drive efficiency. Slotless axial-flux PM motors are particularly suited for such an application, since they can be designed for high torque-to-weight ratio and efficiency. This paper deals with a 16 poles axial-flux PM motor prototype which is used in the propulsion drive of an electrical scooter. The motor prototype has 45 Nm peak torque, 6.8 kg active materials weight, and is coupled directly to the scooter rear wheel. The paper discusses design and construction of the motor prototype, and reports experimental results achieved from laboratory tests. Finally, details concerning the arrangement of the scooter motor drive are given. >

Comparison of AC drives for electric vehicles-a report on experts' opinion survey

Abstract: It is recognized that wide applications of electric vehicles (EVs) will bring tremendous social, economical and ecological benefits. With the growing interests in electric vehicles, much effort is demanded for the development of efficient, reliable and economical AC drives' for EV propulsion purpose. Both induction motor (IM) drives and permanent magnet brushless DC motor (IM) drives have been applied to EVs. Switched reluctance motor (SRM) drives have been proposed as an alternative for EV propulsion. In order to assess the suitability of IM, BDCM and SRM drives for EV applications and to provide a technical support for the development and selection of future EV propulsion systems, the existing EV AC propulsion drives were compared, and a survey of experts' opinions was conducted. Comparison of the three AC drives was made on a relative and a quantitative basis using the survey questionnaires. According to the majority of the experts, induction motor drives are best suited for EV propulsion purpose, due to their low cost, high reliability, high speed, established converter and manufacturing technology, low torque ripple/noise and absence of position sensors. BDCM drives feature compactness, low weight and high efficiency and therefore provide an alternative for EV propulsion. The experts regard insulated gate bipolar transistors (IGBTs) as the most suited power semiconductor devices for AC drive converters at the present stage. >

The design and development of an axial flux permanent magnet brushless DC motor for wheel drive in a solar powered vehicle

Abstract: This paper presents the development of a "weight-power trade-off" applicable to high-performance, power limited vehicles. The theory is then applied to the electric vehicle case to justify the pursuit of an "in the wheel" motor design. The singular benefits of axial flux geometry are discussed with reference to the particular requirements of electric motors for vehicular applications. The basic design process, construction, and test results for a motor fitted in a 26 inch wheel to drive a 260 kg all up weight vehicle are presented. At an output power of 1 kW, the attainable vehicle speed is 72 km/h, corresponding to a motor/wheel speed of 578 r/min and torque of 16.5 Nm, at an estimated motor efficiency of 94%. >

Lighter than air sphere or spheroid having an aperture and pathway

Abstract: A lighter than air apparatus is provided with a gas impermeable sheeting material having a pathway either extending through the apparatus itself or adjacent to the apparatus. One or more control surfaces are provided proximately to an aperture in the pathway for deflecting air passing through the pathway. A propulsion unit with the pathway propels air through pathway. The pathway, the control surfaces, and the control unit allow the lighter than air apparatus to control its bearing and efficiently maintain its position over the Earth.

Toward an improved understanding of thruster dynamics for underwater vehicles

Abstract: This paper proposes a novel approach to modeling the four quadrant dynamic response of thrusters as used for the motion control of ROV and AUV underwater vehicles. The significance is that these vehicles are small in size and respond quickly to commands. Precision in motion control will require further understanding of thruster performance than is currently available. The model includes a four quadrant mapping of the propeller blades lift and drag forces and is coupled with motor and fluid system dynamics. A series of experiments is described for both long and short period triangular, as well as square wave inputs. The model is compared favorably with experimental data for a variety of differing conditions and predicts that force overshoots are observed under conditions of rapid command changes. Use of the model will improve the control of dynamic thrust on these vehicles.

Small satellite propulsion options

Abstract: Advanced chemical and low power electric propulsion offer attractive options for small satellite propulsion. Applications include orbit raising, orbit maintenance, attitude control, repositioning, and deorbit of both Earth-space and planetary spacecraft. Potential propulsion technologies for these functions include high pressure Ir/Re bipropellant engines, very low power arcjets, Hall thrusters, and pulsed plasma thrusters, all of which have been shown to operate in manners consistent with currently planned small satellites. Mission analyses show that insertion of advanced propulsion technologies enables and/or greatly enhances many planned small satellite missions. Examples of commercial, DoD, and NASA missions are provided to illustrate the potential benefits of using advanced propulsion options on small satellites.

Basic principle and design criteria of axial-flux PM machines having counter-rotating rotors

Abstract: Axial-flux PM machines are particularly suitable for application in electrical drives devoted to ship propulsion, since they allow the elimination of the large-power gearbox used in conventional systems. In consideration of that, this paper deals with a novel slotless axial-flux PM machine topology which is characterized by the synchronous counterrotation of the two machine rotors. Such a new machine topology can find application in the direct driving of two counterrotating propellers, which may be used in ship propulsion systems to recover energy from the rotational flow of the main propeller slip stream. In this case, the use of an axial-flux machine having counter-rotating rotors allows an improvement in terms of weight and efficiency, since the epicyclic gear otherwise required for the motion reversal can be avoided. The paper discusses the stator winding arrangement which allows the opposite motion of the machine rotors and reports experimental results taken from a small-size machine prototype. >

Toy aircraft and method for remotely controlling same

Abstract: A toy aircraft includes a main body portion having a central hub member and a plurality of wings. Each wing of the plurality of wings is equally spaced about a central axis of rotation. The toy aircraft further includes a power source carried by the aircraft, at least one motorized propulsion unit interconnected with the power source, and at least first and second propeller assemblies interconnected to the at least one motorized propulsion unit. The first and second propeller assemblies each include a plurality of blades arranged for rotation within a substantially horizontal plane. A preferred construction of the propellers includes a propeller shaft and a plurality of blade portions equally spaced about an axis of rotation defined by the propeller shaft. Each blade portion is formed from foamed polystyrene. A preferred construction of a control system for controlling the flight of the toy aircraft includes a handheld remote control unit and a receiver circuit positioned on the toy aircraft.

Control device for hydraulically propelled work vehicle

Abstract: The current operational condition is discriminated as being the vehicle propulsion condition or the performing work condition. When the vehicle propulsion operational condition is discriminated, the maximum engine revolution speed is limited to a first revolution speed and the maximum displacement is limited to a first displacement value. When the performing work condition is discriminated, the maximum engine revolution speed is limited to a second revolution speed equal to or lower than the first revolution speed and the maximum displacement is limited to a second displacement value higher than the first displacement value. The first and second revolution speeds and the first and second displacement values are so determined that the first revolution speed multiplied by the first displacement value at least as relating to pressure for vehicle propulsion on level ground is less than the second revolution speed multiplied by the second displacement value as relating to the pressure for below the range of torque limitation control. By this, the pump output flow during vehicle propulsion on level ground is made lower than while performing work and, during vehicle propulsion, reduction of the pressure loss is made possible. Even with the identical pump pressure, the effective motor pressure is increased, so that its output torque can be increased. Because also the maximum displacement of the motor can be reduced according to the reduction of the maximum pump output flow amount, the construction of the hydraulic circuit can be made more compact.

Non-railbound vehicle with an electric motor

Abstract: The invention relates to a non-railbound vehicle with an electric motor. To modify such vehicles in such a way that the specific fuel consumption remains as low as possible and the maximum possible power of the internal combustion engine is fully available to the vehicle drive in case of need without the sacrifice of any convenience relating to the electrical operation of subsidiary functions, it is proposed that the control system (FST) provide the on-board low-voltage system with part of the power produced by the generator and that, during operational phases in which the full power of the engine (1) is required for propulsion, a program in the electronic control system (FST) provide for the temporary interruption (interrupter 11) of the electric power supply from the generator (2) to the low-voltage system, the subsidiary electric consumers (10) then being powered from the vehicle battery (10).

Dual-motor electric drive system for vehicles

Abstract: A dual-motor electric drive system is particularly suited for driving track-laying vehicles. The propulsion motors of the drive system are each individually selected to provide the speed and torque for selected portions of the operational requirements of the vehicle. The electric drive system utilizes a primary motor to provide the maximum speed requirements and a secondary motor to provide the high torque requirements for low speed operation. The primary and secondary propulsion motors are interconnected by a predetermined drive ratio so that the secondary motor provides torque until it attains a maximum predetermined speed whereupon it is disconnected from the primary motor.

Basic principle and design criteria of axial-flux PM machines having counter-rotating rotors

Abstract: Axial-flux PM machines are particularly suitable for application in electrical drives devoted to ship propulsion, since they allow the elimination of the large-power gearbox used in conventional systems. In consideration of that, this paper deals with a novel slotless axial-flux PM machine topology which is characterized by the synchronous counterrotation of the two machine rotors. Such a new machine topology can find application in the direct driving of two counterrotating propellers, which may be used in ship propulsion systems to recover energy from the rotational flow of the main propeller slip stream. In this case, the use of an axial-flux machine having counter-rotating rotors allows an improvement in terms of weight and efficiency, since the epicyclic gear otherwise required for the motion reversal can be avoided. The paper discusses the stator winding arrangement which allows the opposite motion of the machine rotors and reports experimental results taken from a small-size machine prototype. >

A Large Hemi-anechoic Enclosure for Community-Compatible Aeroacoustic Testing of Aircraft Propulsion Systems

Abstract: A large hemi-anechoic (absorptive walls and acoustically hard floor) noise control enclosure has been erected around a complex of test stands at the NASA Lewis Research Center in Cleveland, Ohio. This new state-of-the-art Aeroacoustic Propulsion Laboratory (APL) provides an all-weather, semisecure test environment while limiting noise to acceptable levels in surrounding residential neighborhoods. The 39.6 m (130 ft) diameter geodesic dome structure houses the new Nozzle Aeroacoustic Test Rig (NATR), an ejector-powered M = 0.3 free jet facility for acoustic testing of supersonic aircraft exhaust nozzles and turbomachinery. A multi-axis, force-measuring Powered Lift Facility (PLF) stand for testing of Short Takeoff Vertical Landing (STOVL) vehicles is also located within the dome. The design of the Aeroacoustic Propulsion Laboratory efficiently accomodates the research functions of two separate test rigs, one of which (NATR) requires a specialized environment for taking acoustic measurements. Absorptive fiberglass wedge treatment on the interior surface of the dome provides a hemi-anechoic interior environment for obtaining the accurate acoustic measurements required to meet research program goals. The APL is the first known geodesic dome structure to incorporate transmission-loss properties as well as interior absorption into a free-standing, community-compatible, hemi-anechoic test facility.

Hypersonic vehicle model and control law development using H(infinity) and micron synthesis

Abstract: The control system design for a Single Stage To Orbit (SSTO) air breathing vehicle will be central to a successful mission because a precise ascent trajectory will preserve narrow payload margins. The air breathing propulsion system requires the vehicle to fly roughly halfway around the Earth through atmospheric turbulence. The turbulence, the high sensitivity of the propulsion system to inlet flow conditions, the relatively large uncertainty of the parameters characterizing the vehicle, and continuous acceleration make the problem especially challenging. Adequate stability margins must be provided without sacrificing payload mass since payload margins are critical. Therefore, a multivariable control theory capable of explicitly including both uncertainty and performance is needed. The H(infinity) controller in general provides good robustness but can result in conservative solutions for practical problems involving structured uncertainty. Structured singular value mu framework for analysis and synthesis is potentially much less conservative and hence more appropriate for problems with tight margins. An SSTO control system requires: highly accurate tracking of velocity and altitude commands while limiting angle-of-attack oscillations, minimized control power usage, and a stabilized vehicle when atmospheric turbulence and system uncertainty are present. The controller designs using H(infinity) and mu-synthesis procedures were compared. An integrated flight/propulsion dynamic mathematical model of a conical accelerator vehicle was linearized as the vehicle accelerated through Mach 8. Vehicle acceleration through the selected flight condition gives rise to parametric variation that was modeled as a structured uncertainty. The mu-analysis approach was used in the frequency domain to conduct controller analysis and was confirmed by time history plots. Results demonstrate the inherent advantages of the mu framework for this class of problems.

Oscillating foils for marine propulsion

Abstract: The use of oscillating fins by aquatic animals for propulsion has inspired the design of corresponding propulsors for ships. Rigid and partly flexible oscillating propulsor designs were analyzed for a large ship based on two-dimensional linear and nonlinear theories. Open water efficiencies of the oscillating propulsors were 17-25% higher than those of an optimal screw propeller. Behind the ship, quasi- propulsive efficiency of the partly chordwise flexible foil was 72%, i.e. 5% higher than that of the screw propeller. The efficiency increase produced by the oscillating propulsor was attributed to the considerable increase in the propeller working area due to the wide span of the foil.

Lunar missions using advanced chemical propulsion: System design issues

Abstract: To provide the transportation of lunar base elements to the moon, large high-energy propulsion systems will be required. Advanced propulsion systems for lunar missions can provide significant launch mass reductions and payload increases. These mass reductions and added payload masses can be translated into significant launch cost savings for the lunar base missions. The masses in low Earth orbit (LEO) were compared for several propulsion systems: nitrogen tetroxide/monomethyl hydrazine (NTO/MMH), oxygen/methane (O2/CH4), oxygen/hydrogen (O2/H2), and metallized O2/H2/Al propellants. Also, the payload mass increases enabled with O2/H2 and O2/H2/Al systems were addressed. In addition, many system design issues involving the engine thrust levels, engine commonality between the transfer vehicle and the excursion vehicle, and the number of launches to place the lunar mission vehicles into LEO will be discussed. Analyses of small lunar missions launched from a single STS-C flight are also presented.

Optimal trajectories for hypersonic launch vehicles

Abstract: In this paper, we derive a near-optimal guidance law for the ascent trajectory from Earth surface to Earth orbit of a hypersonic, dual-mode propulsion, lifting vehicle. Of interest are both the optimal flight path and the optimal operation of the propulsion system. The guidance law is developed from the energy-state approximation of the equations of motion. The performance objective is a weighted sum of fuel mass and volume, with the weighting factor selected to give minimum gross take-off weight for a specific payload mass and volume.

Launch vehicle performance using metallized propellants

Abstract: Metallized propellant propulsion systems are considered as replacements for the solid rocket boosters and liquid sustainer stages on the current launch vehicles: both the Space Transportation System (STS) and the Titan 4. Liquid rocket boosters for the STS were analyzed as replacements for current solid rocket boosters. These boosters can provide a liquid propulsion system within the volume constraints of a solid rocket booster. A replacement for the Space Shuttle Main Engines using metallized O2/H2/Al was studied. The liquid stages of the Titan 4 were also investigated; the Aerozine-50 (A-50) fuel was replaced with metallized storable A-50/Al. A metallized propellant is similar to a traditional liquid propellant. However, it has metal particles, such as aluminum, that are suspended in a gelled fuel, such as hydrogen, RP-1, A-50 or monomethyl hydrazine (MMH). The fuels then undergo combustion with liquid oxygen or nitrogen tetroxide (NTO). These propellants provide options for increasing the performance of existing launch vehicle chemical propulsion systems by increasing fuel density or specific impulse or both. These increases in density and specific impulse can significantly reduce the propulsion system liftoff weight and allow a liquid rocket booster to fit into the same volume as an existing solid rocket booster. Also, because gelled fuels are akin to liquid propellants, metallized systems can provide enhanced controllability over solid propulsion systems. Gelling of the propellant also reduces the sensitivity to impacts and consequently reduces the propellant explosion hazard.

The rationale/benefits of nuclear thermal rocket propulsion for NASA's lunar space transportation system

Abstract: The solid core nuclear thermal rocket (NTR) represents the next major evolutionary step in propulsion technology With its attractive operating characteristics, which include high specific impulse (approximately 850-1000 s) and engine thrust-to-weight (approximately 4-20), the NTR can form the basis for an efficient lunar space transportation system (LTS) capable of supporting both piloted and cargo missions Studies conducted at the NASA Lewis Research Center indicate that an NTR-based LTS could transport a fully-fueled, cargo-laden, lunar excursion vehicle to the Moon, and return it to low Earth orbit (LEO) after mission completion, for less initial mass in LEO than an aerobraked chemical system of the type studied by NASA during its '90-Day Study' The all-propulsive NTR-powered LTS would also be 'fully reusable' and would have a 'return payload' mass fraction of approximately 23 percent--twice that of the 'partially reusable' aerobraked chemical system Two NTR technology options are examined--one derived from the graphite-moderated reactor concept developed by NASA and the AEC under the Rover/NERVA (Nuclear Engine for Rocket Vehicle Application) programs, and a second concept, the Particle Bed Reactor (PBR) The paper also summarizes NASA's lunar outpost scenario, compares relative performance provided by different LTS concepts, and discusses important operational issues (eg, reusability, engine 'end-of life' disposal, etc) associated with using this important propulsion technology

Nuclear rockets: High-performance propulsion for Mars

Abstract: A new impetus to manned Mars exploration was introduced by President Bush in his Space Exploration Initiative. This has led, in turn, to a renewed interest in high-thrust nuclear thermal rocket propulsion (NTP). The purpose of this report is to give a brief tutorial introduction to NTP and provide a basic understanding of some of the technical issues in the realization of an operational NTP engine. Fundamental physical principles are outlined from which a variety of qualitative advantages of NTP over chemical propulsion systems derive, and quantitative performance comparisons are presented for illustrative Mars missions. Key technologies are described for a representative solid-core heat-exchanger class of engine, based on the extensive development work in the Rover and NERVA nuclear rocket programs (1955 to 1973). The most driving technology, fuel development, is discussed in some detail for these systems. Essential highlights are presented for the 19 full-scale reactor and engine tests performed in these programs. On the basis of these tests, the practicality of graphite-based nuclear rocket engines was established. Finally, several higher-performance advanced concepts are discussed. These have received considerable attention, but have not, as yet, developed enough credibility to receive large-scale development.

Advanced electric propulsion, power generation, and power distribution

Abstract: Investigations into the development of electric drive systems for both submarines and surface ships have been ongoing for several years. These studies led us to the conclusion that accepted contemporary concepts did not offer the full potential envisioned for electric drive. These concepts did not fully consider non-developmental (existing) technology, and the evolutionary approach to system development did not adequately address ship system interface, cost and other shipbuilder concerns. A “clean sheet” approach was taken to designing advanced electric propulsion, generation and power distribution systems and equipment. Primary objectives were reduced cost, weight, and volume with improved arrangement flexibility, operation, power allocation, growth potential, reliability, maintainability, survivability and efficiency. This paper focuses on the technologies involved with component development, the installation of the system on a typical submarine, and the resulting benefits.

NASA's Hypersonic Research Engine Project: A review

Abstract: The goals of the NASA Hypersonic Research Engine (HRE) Project, which began in 1964, were to design, develop, and construct a high-performance hypersonic research ramjet/scramjet engine for flight tests of the developed concept over the speed range of Mach 4 to 8. The project was planned to be accomplished in three phases: project definition, research engine development, and flight test using the X-15A-2 research airplane, which was modified to carry hydrogen fuel for the research engine. The project goal of an engine flight test was eliminated when the X-15 program was canceled in 1968. Ground tests of full-scale engine models then became the focus of the project. Two axisymmetric full-scale engine models, having 18-inch-diameter cowls, were fabricated and tested: a structural model and combustion/propulsion model. A brief historical review of the project, with salient features, typical data results, and lessons learned, is presented. An extensive number of documents were generated during the HRE Project and are listed.

Double row loop-coil configuration for high-speed electrodynamic maglev suspension, guidance, propulsion and guideway directional switching

Abstract: A stabilization and propulsion system comprising a series of loop-coils arranged in parallel rows wherein two rows combine to form one of two magnetic rails. Levitation and lateral stability are provided when the induced field in the magnetic rails interacts with the superconducting magnets mounted on the magnetic levitation vehicle. The loop-coils forming the magnetic rails have specified dimensions and a specified number of turns and by constructing differently these specifications, for one rail with respect to the other, the angle of tilt of the vehicle can be controlled during directional switching. Propulsion is provided by the interaction of a traveling magnetic wave associated with the coils forming the rails and the super conducting magnets on the vehicle.

Supersonic flight test results of a performance seeking control algorithm on a NASA-15 spacecraft

Abstract: A model-based, adaptive control algorithm called Performance Seeking Control (PSC) has been flight tested on an F-15 aircraft. The algorithm attempts to optimize performance of the integrated propulsion system during steady-state engine operation. The final phase of a 3-year PSC flight test program is described in this paper. Previous studies of use of PSC on the F-15 airplane show improvement in propulsion system performance. Because these studies were conducted using one of two F-15 engines, the full effect on aircraft performance was not measured. During the most recent studies, both engines were optimized to demonstrate the full effect of PSC propulsion system optimization on aircraft performance. Results were gathered over the 1-g supersonic envelope demonstrating benefits of the integrated control approach. Quantitative flight results illustrating the PSC method for deriving benefits from the F-15 integrated propulsion system for Mach numbers up to 2 are also presented.