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An extension member is attachable to a trailer hitch and extends away from the vehicle and is connected to a seating frame supporting a toilet seat.
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| Number | Title | Issue Date |
| 7287369 | Method for extending a nozzle and extended nozzle for rocket drives A method for extending a nozzle for a rocket engine is described, in which at least one second region of the contour of the nozzle is arranged as an extension of a first region of the contour of the nozzle. This extension of the first region by the second region occ... | 10/30/2007 |
| 7251989 | Method and device for operating an internal combustion engine A method and a device are provided for diagnosing operation of an internal combustion engine having a compressor for compressing air supplied to the internal combustion engine, which method and device permit diagnosis of as many error patterns in the compressor oper... | 08/07/2007 |
| 7200999 | Arrangement for bleeding the boundary layer from an aircraft engine An aircraft engine comprising a nacelle, a first wall and fan outlet guide vanes. The fan outlet guide vanes comprises a plurality of stator vanes extending between a second wall and a third wall. The nacelle having apertures at a region of low pressure. A means to ... | 04/10/2007 |
| 7127880 | Induction coupled variable nozzle A turbofan nacelle includes forward and aft cowls adjoining at a joint, and including an exhaust duct having a main outlet for discharging exhaust. A variable nozzle surrounds the exhaust duct and includes a secondary outlet around the main outlet. A thrust reverser... | 10/31/2006 |
| 7117681 | Thrust control valve A thrust control valve includes a nozzle having a gas supply chamber, a gas jetting chamber and a connecting passage therebetween. The nozzle has an upstream inner surface defining the gas supply chamber and a downstream inner surface defining the gas jetting chambe... | 10/10/2006 |
| 7093793 | Variable cam exhaust nozzle An exhaust nozzle includes an exhaust duct with an outlet and a row of radial apertures upstream therefrom. A radial frame surrounds the duct upstream from the apertures. A row of flaps are hinged to the frame to selectively cover and uncover the apertures for contr... | 08/22/2006 |
| 7069728 | Multi-position BOV actuator A multi-position pressurized fluid actuator is mounted for movement in a casing. The actuator includes at least one selectively openable opening at a location corresponding to an intermediate position through which pressurized fluid can be selectively bled from the ... | 07/04/2006 |
| 7065468 | Methods and apparatus for assessing gas turbine engine damage A method and apparatus for assessing damage to machine components is provided. The method includes calculating an expected parameter value based on a first parameter value indicator, calculating an estimate of an actual parameter value based on a second parameter va... | 06/20/2006 |
| 7051511 | Method and arrangement for preventing encased explosives being caused to explode by an external fire This disclosure relates to a method and an arrangement for preventing explosives such as rocket engines from exploding while subjected to an external fire in an ammunition bunker. The basic principle underlying the invention is that the casing surrounding the explos... | 05/30/2006 |
| 7010906 | Gas turbine engine haveing a disconnect panel for routing pipes and harnesses between a first and a second zone A gas turbine engine (10) includes a first fire zone (Zone 3) in the region of a core of the engine and a second fire zone (Zone 1) in the region of a fan case of the engine, the first and second fire zones being separated by fire walls. The fir... | 03/14/2006 |
| 6986246 | Side thruster valve and side thruster device A side thruster valve of an aerospace craft is improved to reduce torque of a servo-motor, etc. needed for nozzle opening and closing to thereby realize a compact and light weight device. The side thruster valve comprises a valve plug having its back directed to an ... | 01/17/2006 |
| 6901740 | Engine with a central spike for a space launcher The pointed end of a central spike, used in an engine of a space launcher, may have a deformable structure that can adopt either a folded position or a deployed position. ... | 06/07/2005 |
| 6892127 | Methods and apparatus for assessing gas turbine engine damage A method and apparatus for assessing damage to machine components is provided. The method includes calculating an expected parameter value based on a first parameter value indicator, calculating an estimate of an actual parameter value based on a second parameter va... | 05/10/2005 |
| 6758032 | System of pulsed detonation injection for fluid flow control of inlets, nozzles, and lift fans According to one embodiment of the invention, a system for altering a fluid flow includes a nozzle having a fluid flow and including a converging portion, a diverging portion downstream of the converging portion, and a throat coupling the converging portion to the d... | 07/06/2004 |
| 6574952 | Apparatus for controlling the flow separation line of rocket nozzles The invention refers to an apparatus for controlling the flow separation line of rocket nozzles for reducing side loads. For obtaining this control it is suggested according to the invention that the inside of the nozzle (1) has circumferentially regular ... | 06/10/2003 |
| 6543717 | Compact optimal and modulatable thrust device for controlling aerospace vehicles The thrust device comprises a valve body (20) having a chamber (24) surrounding part of the needle, at least one gas admission opening (27) opening out into the chamber, and a gas outlet opening (25) opening out into the chamber and defined by a wall port... | 04/08/2003 |
| 6233919 | Force driven hot gas proportional thruster valve A thruster valve has a continuously positionable piston between a closed position and a maximum open position. The piston moves in response to the difference in pressure between the pressure of the valve's inlet and thruster nozzle and the pressure behind... | 05/22/2001 |
| 6220852 | Variable exit high velocity burner A method and apparatus for adjusting the flame exit velocity of a high velocity burner. The burner includes burner combustor chamber having a fluid accelerating nozzle and a burner combustor exhaust port. Fuel is delivered to the burner combustor through ... | 04/24/2001 |
| 6170257 | Variable thrust nozzle system A variable thrust nozzle system comprises a housing, a pair of nozzle skirts. attached to the outer surface of the housing so as to open in opposite directions, respectively, a pair of nozzle plugs disposed in the pair of nozzle skirts so as to define a n... | 01/09/2001 |
| 5833140 | Variable geometry exhaust nozzle for a turbine engine A variable exhaust nozzle (26) for a turbine engine nacelle (16) includes a pair of semi-cowls (58, 60) disposed about a longitudinally extending central axis (14) and a pair of corresponding shells (36, 38) each of which is spaced radially inwardly from ... | 11/10/1998 |
| 5826794 | Aircraft scoop ejector nozzle An engine exhaust nozzle (36) is provided for reducing exhaust noise in an intermediate bypass ratio turbofan engine. The nozzle (36) includes a plurality of scoop ejectors (38) placed equal distances about the circumference of a nozzle outer structure (4... | 10/27/1998 |
| 5687564 | Low rotor vibration avoidance in aircraft gas turbine engines Corrected fan speed (N1C2) and engine pressure ratio (EPR) are controlled, by controlling exhaust nozzle area (EA) according to a schedule or map so that as altitude increases (P2 decreases) the axial forces on the low rotor are sufficient to minimize low... | 11/18/1997 |
| 5664415 | After-burning turbo-fan engine with a fixed geometry exhaust nozzle having a variable flow coefficient An after-burning turbo-fan engine system (10) includes turbo-fan engine (14) for producing exhaust gas (20), and jet thrust therefrom. After-burning chamber (16) receives turbo-fan exhaust and injects a controllable amount of fuel into turbo-fan exhaust t... | 09/09/1997 |
| 5579635 | Distributed erosion region rocket motor nozzle A rocket motor nozzle has a nozzle core that defines a nozzle passage through which combustion products travel during flight. The erosive forces created by the combustion products are longitudinally distributed over the nozzle core so that the nozzle's sm... | 12/03/1996 |
| 5571262 | Supersonic nozzle for a turbojet engine Disclosed is a variable supersonic nozzle for a turbojet engine having an improved control system for varying the convergent and divergent nozzle flaps. All of the flaps are supported on several beams about the circumference of a gas passage. A control li... | 11/05/1996 |
| 5491973 | Self-actuating control for rocket motor nozzle A rocket motor is provided with a self-actuated nozzle throat control mechanism. The motor includes a casing that forms a combustion chamber and houses propellant. An exhaust nozzle extends from the motor casing and is fluidly coupled to the combustion ch... | 02/20/1996 |
| 5463866 | Supersonic jet engine installation and method with sound suppressing nozzle A supersonic jet engine having a nozzle section into which ambient air can be selectively introduced for a noise suppressing mode of operation, with this ambient air being intermixed with engine exhaust flow, through passageway segments. Flow modulating p... | 11/07/1995 |
| 5448881 | Gas turbine engine control based on inlet pressure distortion Circumferential and radial inlet pressure distortion on an aircraft gas turbine engine are detected by a plurality of static pressure sensors and a signal processor, which computes the total pressure for each sensor to determine a pressure distortion patt... | 09/12/1995 |
| 5435128 | Pyrotechnically driven nozzle restrictor A pyrotechnically driven device for restricting the area of the nozzle throat in a solid propellant rocket motor is disclosed. In one embodiment, the device includes a piston support mounted to the rocket motor in the exit cone. A restrictor is attached t... | 07/25/1995 |
| 5402963 | Acoustically shielded exhaust system for high thrust jet engines A flade exhaust nozzle for a high thrust jet engine is configured to form an acoustic shield around the core engine exhaust flowstream while supplementing engine thrust during all flight conditions, particularly during takeoff. The flade airflow is conver... | 04/04/1995 |
| 5394690 | Constant pressure, variable thrust bipropellant engine A pressure controlled pintle is employed in combination with a throttling quid, gel, or hybrid engine to provide a constant pressure and variable thrust from a single operating engine. As the propellants are throttled back and the chamber pressure drops, ... | 03/07/1995 |
| 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 |
| 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 |
| 5201800 | Method for discharging combustion gases from an exhaust nozzle A method is disclosed for discharging combustion gases from an engine powering an aircraft at subsonic and supersonic velocities. The engine includes a variable area exhaust nozzle having primary and secondary flaps defining a generally converging channel... | 04/13/1993 |
| 5197280 | Control system and method for controlling a gas turbine engine A control system for a gas turbine engine receives a signal representative of a first target engine operating condition and also receives a signal representative of an actual engine condition. The system produces an error signal representative of the diff... | 03/30/1993 |
| 5140809 | Exhaust nozzle idle thrust spoiling method A method and apparatus are disclosed for spoiling thrust from combustion gases discharged from an aircraft gas turbine engine at ground idle operating condition. The method comprises the step of positioning a secondary exhaust flap of the exhaust nozzle t... | 08/25/1992 |
| 5103639 | Exhaust nozzle having variable contour exhaust flap A method is disclosed for discharging combustion gases from an engine powering an aircraft at subsonic and supersonic velocities. The engine includes a variable area exhaust nozzle having primary and secondary flaps defining a generally converging channel... | 04/14/1992 |
| 5072580 | System for operating gas turbine jet engine with fan damage Normal high load operation automatically varies nozzle area to maintain an optimum engine pressure ratio (EPR). An error signal representing fan damage is established by comparing the actual EPR to the predicted EPR. Compressor stalls are also monitored. ... | 12/17/1991 |
| 5038559 | Method and apparatus for selectively varying an effective fluid flow area of a jet engine exhaust nozzle A method and apparatus for varying the effective area of a jet engine exhaust nozzle. The apparatus includes a center body disposed upstream of the nozzle throat and configured to form a recirculation wake extending to and through the nozzle throat. The c... | 08/13/1991 |
| 5038560 | Fluid outlet duct A cooling air outlet duct for a heat exchanger of a gas turbine engine is provided with a rotatable wall portion. The rotatable wall portion is rotatable about a pivot positioned at its upstream end so that the total flow area between the downstream end o... | 08/13/1991 |
