| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 060233000 | Condition responsive thrust varying means | 11 |
| 20090107110 | Fan control apparatus - When a FADEC detects an abnormality in any of engine+compressor combinations, a FCC controls the amount of air for driving the fan to a level that is lower than that before the abnormality has been detected, until a state is assumed in which the normally operating engine+compressor combination can supply the air at a flow rate necessary for a fan to generate a propulsion force that has been attained before the abnormality has been detected. As a result, the normally operating engine+compressor combination can be prevented from the occurrence of a surge and a resultant overload state. Therefore, when some drive sources from a plurality of drive sources fail, normally operating drive sources can be prevented from being in an overload state. | 04-30-2009 |
| 20110179768 | ROCKET THRUSTER ASSEMBLY COMPRISING LOAD-BALANCED PINTLE VALVE - A rocket thruster of this invention includes a nozzle and a valve assembly. The valve subassembly includes a pintle with a head portion, which has a truncated substantially conical surface region facing and concentric with converging and throat regions of the nozzle to provide a variable effective throat area therebetween. The truncated portion of the head portion has an outer edge defining a bleed passageway opening communicating with a primary bleed passage leading through the head portion to a bleed cavity located on an opposite side of the head portion. During activation of a rocket motor to which the rocket thruster is coupled, gases imparting a load on the head portion pass through the primary bleed passage to the opposite side of the head portion for counterbalancing loads acting on the head portion. A thrust control subassembly moves the pintle axially for changing the effective throat area. | 07-28-2011 |
| 060235000 | Motive fluid outlet area and fuel flow control | 1 |
| 20100107600 | Gas turbine engine variable area exhaust nozzle - A turbofan gas turbine engine ( | 05-06-2010 |
| 060240000 | Oxidizer and fuel flow control | 2 |
| 20100170222 | MECHANICAL SIGNAL PROCESSING ACCUMULATOR ATTENUATION DEVICE AND METHOD - A liquid/gas interface pressure accumulator and mechanical filter device is especially adapted for use within a propellant utilization monitoring system of a space launch vehicle. The device provides a retrofit solution for overcoming problems associated with liquid entering a pressure sensing lines and pressure noises that collectively harm the ability to accurately measure fuel and oxidizer levels. One device is attached to each fuel and oxidizer tank of the launch vehicle. Each device includes a housing and an internal sensing chamber that is used to accumulate liquid before it can enter a pressure sensing communication line connected to a pressure sensing transducer. The construction of the device also allows filtering of undesirable pressure noises due to vibration, pressure pulsations, and other vibratory events that occur during operation of the space vehicle. The device is also selectively tunable to filter out certain frequencies and frequency ranges/bands. The invention in other aspects includes methods of improving pressure sensing applications in a propellant utilization monitoring system. | 07-08-2010 |
| 20100269487 | Thermally-integrated fluid storage and pressurization system - An oxygen-hydrogen pressurization system includes a cryogenic oxygen tank, cryogenic hydrogen tank, thermal switch, supercritical oxygen bottle, supercritical hydrogen bottle, and pressure management system and a thermodynamic vent system. The thermal switch permits heat to flow between hot and cool areas within the space vehicle to help facilitate pressure management within the cryogenic liquid oxygen tank and the cryogenic liquid hydrogen tank in conjunction with the higher pressure fluid from the supercritical oxygen tank and the fluid from the supercritical hydrogen tank and the added cooling from the pressure management system. | 10-28-2010 |
| 060242000 | Outlet area control | 3 |
| 20090100823 | Gas turbine engine reheat fuel system - A gas turbine propulsion engine reheat system having a variable area exhaust nozzle comprising a nozzle area control system including means for accelerating increases of nozzle area | 04-23-2009 |
| 20090211225 | Systems and methods for varying the thrust of rocket motors and engines while maintaining higher efficiency using moveable plug nozzles - The thrust of a rocket motor can be varied to optimize Nozzle Pressure Ratio (NPR) using a design that allows for adjusting the relative position of a plug and a combustion chamber exit. The plug or the exit may be attached to an adaptive control system for position modification. The relative position of the plug and exit may be adjusted to optimize NPR to account for changing propellant flow and/or changing ambient pressure. | 08-27-2009 |
| 20120186224 | AIRCRAFT JET ENGINE COMPRISING A SYSTEM FOR REDUCING THE NOISE GENERATED BY THE EJECTION OF THE GASES - The invention relates to an aircraft jet engine comprising a nozzle ( | 07-26-2012 |
| 060243000 | Fuel flow control | 3 |
| 20110005194 | FLASHBACK SHUT-OFF - A flashback-arresting shut-off valve is disclosed herein. Propellant is moved from a propellant reservoir, through the shut-off valve in an open configuration to a point of combustion in a normal propellant flow direction. During a flashback, the propellant is ignited within the propellant line and substantial physical/thermal energy caused by the flashback travels in the direction opposite to the normal propellant flow direction back to the shut-off valve. A burst member within the shut-off valve fails because of the flashback. Failure of the burst member causes compression on a spring-loaded portion of the shut-off valve to be released, thereby closing the shut-off valve and sealing the propellant reservoir from the flashback. Failure of the burst member also causes one or more pressure relief outlets to open that direct the physical/thermal energy and/or un-combusted/combusted propellant out and away from the shut-off valve. | 01-13-2011 |
| 20110146231 | Tiered Porosity Flashback Suppressing Elements for Monopropellant or Pre-Mixed Bipropellant Systems - Monopropellant and pre-mixed bipropellant storage and supply systems for rocket engines and other work producing systems are subject to damage when detonation progresses upstream from a combustion chamber to and through supply lines. Interposing one or more micro porous or micro fluidic elements into the supply conduit can limit the flame front that accompanies such unintended detonation, but inevitably restrict the flow of the propellant to the combustion chamber. A tiered micro fluidic element where a bulk of the element has relatively large pores but forms a structurally robust supports a second, relatively thin region having appropriately small mean pore diameter provides an effective flashback barrier that can resist catastrophic failure during such detonations. Such elements can be used in isolation, or they can be incorporated into detonation wave arrestors or pressure wave-triggered cut-off valves or the like to decrease the incidence of unintended detonations. | 06-23-2011 |
| 20130019586 | PROPULSION METHOD AND DEVICE COMPRISING A LIQUID OXIDANT AND A SOLID COMPOUND - One subject of the present invention is a propulsion method comprising:
| 01-24-2013 |
