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| Number | Title | Issue Date |
| 5444973 | Pressure-fed rocket booster system Disclosed is a space launch system having a main engine which uses turbopumps to provide fuel and oxidizer to the main engine combustion chamber, and one or more booster engines that use high pressure fuel and/or oxidizer to pressurize the fuel and oxidiz... | 08/29/1995 |
| 5442909 | Control system for limiting the vector angle in an axisymmetric vectoring exhaust nozzle A method for controlling the amount of side load experienced by a gas turbine engine and associated airframe components is provided, where the gas turbine engine includes a thrust vectoring system which deflects thrust at a vector angle away from a center... | 08/22/1995 |
| 5435127 | Method and apparatus for boosting ram airflow to an ejection nozzle An ejecting exhaust nozzle in a gas turbine engine includes a convergent section, a divergent section, extending downstream from the convergent section, and an ejector for ejecting an airflow into the core airflow is fed by a boost pump. The boost pump in... | 07/25/1995 |
| 5431010 | High speed, amplitude variable thrust control method A high speed control apparatus and method utilized in a system having a high pressure fluid supply for producing precisely controlled, amplitude and duration variable thrust are disclosed, the apparatus including a piezoelectric stack responsive to a cont... | 07/11/1995 |
| 5419116 | Miniscale ballistic motor testing method for rocket propellants A method for using a miniscale ballistic test motor for determining burn es over an operating pressure range allows the testing of a small propellant sample. The small propellant sample allows performance of an abbreviated procedure for each test of the ... | 05/30/1995 |
| 5406787 | After-burning turbo-jet engine with a fixed geometry exhaust nozzle A method and apparatus are provided for generating thrust in a turbo-fan engine (10), including generating additional thrust with after-burning. Sensors are used for monitoring a temperature in nozzle (26) of engine (10) and fan stream pressure of engine ... | 04/18/1995 |
| 5404713 | Spillage drag and infrared reducing flade engine A FLADE aircraft gas turbine engine having a FLADE duct circumscribing a preferably variable cycle inner gas turbine engine and having a FLADE fan disposed in the FLADE duct and radially outward of and drivenly connected to a first fan disposed in a first... | 04/11/1995 |
| 5402638 | Spillage drag reducing flade engine A FLADE aircraft gas turbine engine having a FLADE duct circumscribing a preferably variable cycle inner gas turbine engine. A FLADE fan is disposed in the FLADE duct radially outward of and drivenly connected to a first fan disposed in a first fan duct o... | 04/04/1995 |
| 5394689 | Gas turbine engine control system having integral flight Mach number synthesis method A gas turbine engine digital electronic control is disclosed which is capable of maintaining safe, efficient engine thrust levels in the event of loss of communication with an aircraft flight computer. Specifically, a limited number of engine sensor input... | 03/07/1995 |
| 5392597 | Jet mixer noise suppressor using acoustic feedback The present invention generally relates to providing an improved jet mixer noise suppressor for high speed jets that rapidly mixes high speed air flow with a lower speed air flow, and more particularly, relates to an improved jet mixer noise suppressor th... | 02/28/1995 |
| 5380570 | Thermoplastic para-polyphenylene sulfide, high temperature-resistant rocket motor cases Para-polyphenylene sulfide, a non-composite, ultrahigh-temperature-resist, thermoplastic resin, is employed for the manufacture of interceptor motor cases. The thermoplastic resin, para-polyphenylene sulfide, has a combination of properties which are of ... | 01/10/1995 |
| 5379585 | Hydraulic control system for a jet engine nozzle A method of controlling a system is adapted to control flow to throat nozzle and vectoring nozzle actuators. The method comprises the steps of summing a plurality of signals representative of flow to the vectoring nozzle actuators with a signal representa... | 01/10/1995 |
| 5379584 | Synthesis of critical temperature of a turbine engine A critical parameter for a device is generated as follows. The critical parameter is modeled. When the device is operated under steady-state conditions, the modeled parameter is corrected by a measured parameter known to be accurate under steady state ope... | 01/10/1995 |
| 5357748 | Compressor vane control for gas turbine engines In a gas turbine engine a method for thrust variation with reduced compressor RPM excursion is provided in two modes which includes adjusting pivotable compressor vanes mounted upstream of compressor rotor blades, ahead of the conventional vane schedule t... | 10/25/1994 |
| 5341638 | Low cost segmented structure for pressure vessels, rocket motors, piping A composite structure for rocket motors includes a longitudinal element of the composite structure, which is an assembly of segments of clamshell or barrel stave form. The element is held in place by a circumferential element, which is a composite overwra... | 08/30/1994 |
| 5341639 | Fullerene rocket fuels Solid fuel gas generator compositions for use in ducted rockets, in which fullerenes or substituted fullerenes are used. Fullerene compounds in which easily oxidizable groups, oxidizing groups, or salts of oxidizing acids are attached to the spherical car... | 08/30/1994 |
| 5329762 | Method for assembling rocket propulsion motor A method for assembling a rocket propulsion motor including a motor case and a nozzle assembly, wherein the assembling is carried out under vacuum so that air can not be presented between a silicon sealant layer and a first O-ring disposed between the mot... | 07/19/1994 |
| 5325661 | Jet mixer noise suppressor using acoustic feedback The present invention generally relates to providing an improved jet mixer noise suppressor for high speed jets that rapidly mixes high speed air flow with a lower speed air flow, and more particularly, relates to an improved jet mixer noise suppressor th... | 07/05/1994 |
| 5317866 | Free-flying tubular vehicle A relatively low drag, completely free-flying, tubular vehicle comprises a body that defines a leading edge and a trailing edge and includes an external surface and an internal surface each extending from the leading to the trailing edge. The internal sur... | 06/07/1994 |
| 5311735 | Ramjet bypass duct and preburner configuration A combined turbofan and ramjet aircraft engine includes a forward bypass duct which allows the engine to operate more efficiently during the turbofan mode of operation. By mounting a ramjet preburner in the forward duct and isolating this duct from the tu... | 05/17/1994 |
| 5282357 | High-performance dual-mode integral propulsion system A propulsion system in which pure hydrazine is used as the fuel for both a bipropellant rocket engine for high-thrust performance and in multiple monopropellant thrusters for station keeping and attitude control functions. Use of a common fuel for both mo... | 02/01/1994 |
| 5269136 | Sub-idle stability enhancement and rotating stall recovery In an aircraft gas turbine engine having a variable area exhaust, gas turbine compressor operating conditions are sensed to determine a sub-idle condition or a rotating stall. The exhaust area is increased to a maximum when a sub-idle condition is present... | 12/14/1993 |
| 5269132 | Method and apparatus for controlling infrared emissions There is described a method and apparatus for reducing the infrared emissions from a tail-pipe section of a jet engine. The apparatus consists of a plurality of overlapping hollow panels each having a truncated cone shape supplied with a liquid coolant su... | 12/14/1993 |
| 5269133 | Heat exchanger for cooling a gas turbine A heat exchanger for cooling turbine components of a gas turbofan engine in which air to be cooled is directed along a first annular, radially extending path away from the engine and cooled by bypass air. The cooled air is returned to the engine along a s... | 12/14/1993 |
| 5267435 | Thrust droop compensation method and system A control system and method provide thrust droop compensation in a gas turbine engine. A droop compensation signal is generated for increasing turbine exit temperature T5 based on a predetermined model, and is selectively reduced for limiting t... | 12/07/1993 |
| 5267436 | Vectoring nozzle control of gas turbine engines Exhaust vectoring control for gas turbine engines having an exhaust nozzle mounted on a ring that is positionally controlled by a plurality of actuators in response to pitch and yaw commands uses signal processing to convert pitch and yaw signals into act... | 12/07/1993 |
| 5259188 | Method and system to increase stall margin A method and system are provided to bias a control subsystem of a gas turbine engine having a fan and compressor. The method includes the steps of measuring an operating parameter of the engine and differentiating this parameter over time to obtain a deri... | 11/09/1993 |
| 5259187 | Method of operating an aircraft bypass turbofan engine having variable fan outlet guide vanes A method of operating an aircraft bypass turbofan engine having variable fan outlet guide vanes. In a first embodiment, an engine out condition is sensed, fan rotor speed is repeatedly measured, and vane pitch is adjusted to a predetermined value as a fun... | 11/09/1993 |
| 5255513 | Method of operating a scramjet including integrated inlet and combustor A scramjet engine is disclosed which is effective for use in a hypersonic aircraft as an aircraft-integrated scramjet engine. The engine includes a first surface having an aft facing step, and a cowl upper surface spaced from the first surface to define a... | 10/26/1993 |
| 5239820 | Electric propulsion using C60 molecules Fullerene propellants, which are stable carbon cage structures composed of even numbers of carbon atoms in the range of about 32 to 200 atoms, particularly a combination of conveniently obtainable C60 and C70, may be carried in solid... | 08/31/1993 |
| 5231825 | Method for compressor air extraction A method of obtaining extraction airflow from a compressor includes accelerating the extraction airflow to at least Mach 1 for obtaining choked airflow and decelerating the choked airflow to a speed less than Mach 1. An apparatus for carrying out the meth... | 08/03/1993 |
| 5222359 | Nozzle system and method for supersonic jet engine A supersonic jet engine for improved noise abatement and thrust augmentation. There is an intake section, an engine, a mixing section, an exhaust section, and a secondary air passageway. Ambient air is directed into the engine and into the secondary air p... | 06/29/1993 |
| 5223651 | Supersonic combustion engine and method of combustion initiation and distribution A supersonic combustion air breathing jet engine and method of igniting fuel. The engine has means for providing a spatially controlled combustion distribution of fuel with an ignitor that provides a volumetrically diffuse discharge of energy to initiate ... | 06/29/1993 |
| 5220783 | Foamed in place igniter and aft-end assembly for rocket motor comprising the same A process of forming an igniter in an aft-end assembly for a solid rocket motor, the assembly having an internal cavity and comprising at least one element selected from the group consisting of a nozzle, a blast tube and an exit cone, which process compri... | 06/22/1993 |
| 5216878 | Mixed exhaust flow supersonic jet engine and method A supersonic jet engine installation for improved noise abatement and thrust augmentation. There is an intake section, an engine, a mixing section, an exhaust section, and a secondary air passageway. Ambient air is directed into the engine and also into t... | 06/08/1993 |
| 5214914 | Translating cowl inlet with retractable propellant injection struts The invention is an inlet system for a variable geometry transatmospheric air breathing engine. It incorporates a rotatably translatable cowl provided with a rotating lip used in combination with insertable and propellant injection struts.... | 06/01/1993 |
| 5211006 | Magnetohydrodynamic propulsion system Magnetohydrodynamic methods and apparatus for propelling a vehicle including: an endless closed loop vehicle housing; a plurality of spaced pairs of positive and negative electric field plates coupled to at least one voltage source and mounted in the hous... | 05/18/1993 |
| 5211007 | Method of pressure-ratio control of gas turbine engine Control of a gas turbine engine, suitable for powering an aircraft, is accomplished by varying outlet nozzle cross section and/or a mixing of bypass air with exhaust gas at an inlet to the nozzle. The engine includes a core engine having a combustion cham... | 05/18/1993 |
| 5207760 | Multi-megawatt pulsed inductive thruster This invention discloses an engine for use in sustained space travel. The engine is of an electric type powered by a nuclear reactor. The electric engine includes a pulsed inductive magnetic thruster. A gas is discharged against an inductor comprising a s... | 05/04/1993 |
| 5201886 | Method of operating a pulse thruster A method of operating a pulse thruster comprising delivering electrically charged fuel attracted to a plate having an opposite charge where such fuel is ignited, causing an impulse force, and repeating the process.... | 04/13/1993 |
