Class / Patent application number | Description | Number of patent applications / Date published |
060228000 | With thrust direction modifying means | 34 |
20080250771 | Actuator Arrangement - An actuator arrangement comprising a motor arranged to drive an input member, an extendable actuator having a rotatable shaft, a first drive transmission operable to transmit drive between the input member and the shaft when the shaft is under compression, and a second drive transmission operable to transmit drive between the input member and the shaft when the shaft is under tension, wherein the second drive transmission includes a ratchet mechanism. | 10-16-2008 |
20090013664 | Actuator Arrangement - An actuator arrangement comprises an actuator having a rotatable drive input, a motor, and a drive transmission arrangement for transmitting rotary drive from the motor to the rotatable drive input of the actuator, wherein the transmission arrangement includes a telescopic drive coupling. | 01-15-2009 |
20090282806 | Integrated airbreathing and non-airbreathing engine system - An engine assembly includes a gas-turbine engine having a tailcone portion and a bypass duct, a rocket engine combustion assembly located at the tailcone portion of the gas-turbine engine, and a movable nozzle segment subassembly that is selectively engageable with the gas-turbine engine bypass duct in an open position and with the rocket engine combustion assembly in a closed position. | 11-19-2009 |
20090320445 | METHOD AND DEVICE FOR THE DETECTION OF A THRUST DISSYMMETRY OF AN AIRCRAFT DURING A BRAKING - According to the invention, under braking of an aircraft (AC) with reverse thrust, that (those) engine(s) (Mc) of said aircraft (AC) the associated control lever ( | 12-31-2009 |
20100089031 | SYSTEM, METHOD AND APPARATUS FOR VECTORING NOZZLE EXHAUST PLUME WITH EXTERNAL ACTUATION - A vectoring nozzle with external actuation generates thrust vectoring by applying mechanical or fluidic actuation, or both, on the nozzle deck, external sidewalls, and/or air vehicle aft body to produce changes in the aft body flowfield and/or exhaust plume. An external mechanical sidewall may be integrated into a nozzle deck or side walls without the need for engine bleed to supply fluid injectors. An external fluidic vectoring system uses injectors or plasma devices located aft of the nozzle exit to vector the exhaust plume with no external moving parts. Elements of both mechanical and fluidic systems may be combined for a given application. | 04-15-2010 |
20100212288 | Jet Engine Exhaust Nozzle and Associated System and Method of Use - A first trailing edge portion of a scarfed jet engine exhaust nozzle aft of a second trailing edge portion relative to a central axis of an associated exhaust duct causes an automatic nozzle-pressure-ratio responsive transverse deflection of the associated exhaust flow away from the first trailing edge portion. When offset from both the center of gravity (CG) and the central longitudinal axis of an aircraft, at a relatively low nozzle pressure ratio, e.g. during takeoff, the thrust vector from the exhaust flow acts relatively close to the CG, whereas at a relatively high nozzle pressure ratio, e.g. during relatively high-speed cruise, the scarfed exhaust nozzle deflects the exhaust flow so that the resulting thrust vector is relatively parallel to the path of the aircraft. With the final portion of the exhaust duct skewed, the primary axis of the jet engine can be relatively parallel to the path of the aircraft. | 08-26-2010 |
20120031071 | CONTROL SYSTEM FOR A TURBOREACTOR NACELLE - The invention relates to a system for controlling a plurality of actuators ( | 02-09-2012 |
20120186223 | PRESSURE ASSISTED DIRECT DRIVE PROPORTIONAL HOT-GAS THRUSTER - A hot-gas thruster is actuated using a relatively small electric motor. The hot-gas thruster includes a pressure assisted pilot shaft to keep electric power demand to only a few hundred watts peak and only tens of watts on average, while exhibiting relatively fast response times. | 07-26-2012 |
20150052875 | BLOCKER DOOR ACTUATION SYSTEM AND APPARATUS - A blocker door actuation system for use in an aircraft thrust reverser is provided. The blocker door actuation system may comprise a rack, a gear, a gear housing, a screw shaft, and a link. The blocker door actuation system may be mounted to a translating sleeve in an aircraft nacelle. In response to the thrust reverser being activated and the translating sleeve moving aft, the blocker door actuation system may move the blocker door from a stowed position to a deployed position in a fan air duct. | 02-26-2015 |
20150107224 | CORE COWL THRUST REVERSER SYSTEM AND APPARATUS - A thrust reverser system deployable from a core cowl is provided. The thrust reverser system may comprise one or more doors that are configured to overlap to reduce leakage and increate reverse thrust while deployed. The doors may be configured to vanes that are configured to split and/or direct airflow. | 04-23-2015 |
20150113946 | METHODS AND APPARATUS FOR PASSIVE THRUST VECTORING AND PLUME DEFLECTION - A flow vectoring turbofan engine employs a fixed geometry fan sleeve and core cowl forming a nozzle incorporating an asymmetric convergent/divergent (con-di) and/or curvature section which varies angularly from a midplane for reduced pressure in a first operating condition to induce flow turning and axially symmetric equal pressure in a second operating condition for substantially axial flow. | 04-30-2015 |
20160096604 | MICRO-SCALE VEHICLE HAVING A PROPULSION DEVICE - In one general aspect, an apparatus can include a controller and a fuel container. The apparatus can include a propulsion device including a carbon nanotube structure including a parallel array of micro-channels configured to receive the fuel. Each of the micro-channels included in the array of micro-channels can have a length:width aspect ratio greater than 40:1 and can include a catalyst. | 04-07-2016 |
060229000 | With plural selectively usable motive fluid ejecting means | 6 |
20090145107 | Propulsion system - A propulsion system may include a cylindrical support member and a tubular rotatable member rotatably mounted within the support member that may be adapted to permit fluid flow therethrough. The tubular rotatable member may extend past a down stream end of the support member. An exemplary embodiment of a propulsion system may also disclose a vane attached on an interior surface of the tubular member and may include a blade which extends in a direction toward a rotational axis of the rotatable member such that rotation of the tubular member and the vane attached thereon draws fluid into the tubular member to accelerate the fluid flow through the tubular member. Additionally, a nozzle may be attached to the down stream end of the support member and include a primary nozzle and a secondary nozzle within the primary nozzle. The secondary nozzle may be engaged with the primary nozzle by a stator. | 06-11-2009 |
20090211224 | OUTLET DEVICE FOR A JET ENGINE AND A CRAFT COMPRISING SUCH AN OUTLET DEVICE - An outlet device for a jet engine comprises a number of fixed ducts, each with a gas intake and a gas outlet for conducting a gas from the jet engine, at least two of the outlets of said gas ducts open in different directions, and a gas distribution arrangement is arranged at the gas intakes for selective distribution of the gas to the ducts. | 08-27-2009 |
20090288389 | INTEGRAL THRUST VECTOR AND ROLL CONTROL SYSTEM - An apparatus for vectoring the thrust of a motor that produces thrust along a longitudinal axis by expelling combustion gases through a nozzle may include a plurality of linearly-positionable non-rotatable thrust deflectors. The thrust deflectors may be disposed at around a perimeter of the nozzle. Each thrust deflector may be independently extended to simultaneously generate both a force transverse to the longitudinal axis and a torque about the longitudinal axis. | 11-26-2009 |
20120011828 | PROPULSION SYSTEM - A propulsion system may include a cylindrical support member and a tubular rotatable member rotatably mounted within the support member that may be adapted to permit fluid flow therethrough. The tubular rotatable member may extend past a down stream end of the support member. An exemplary embodiment of a propulsion system may also disclose a vane attached on an interior surface of the tubular member and may include a blade which extends in a direction toward a rotational axis of the rotatable member such that rotation of the tubular member and the vane attached thereon draws fluid into the tubular member to accelerate the fluid flow through the tubular member. Additionally, a nozzle may be attached to the down stream end of the support member and include a primary nozzle and a secondary nozzle within the primary nozzle. The secondary nozzle may be engaged with the primary nozzle by a stator. | 01-19-2012 |
20120233983 | Rocket Nozzles for Unconventional Vehicles - Improved rocket nozzle designs for vehicles with nozzles embedded in or protruding from surfaces remote from the desired thrust axis. The nozzle configurations are for rocket vehicles where the nozzles are not located at the optimal thrust axis of the vehicle. Two examples include nozzles located on the forward end of the vehicle (also called tractor nozzles) and attitude control nozzles located on the periphery of the vehicle. More particularly, the disclosed nozzle shapes enhance the axial thrusts and/or maneuver torques on the vehicle. These unconventional nozzle shapes improve vehicle performance. | 09-20-2012 |
20130219858 | TURBINE ENGINE WITH THRUST VECTORING EXHAUST NOZZLE - A turbine engine exhaust nozzle includes a core gas duct, a nozzle duct, and a thrust vectoring duct system having a duct valve, a first vectoring duct and a second vectoring duct. The nozzle duct directs a first portion of core gas from the core gas duct through a nozzle duct outlet along a centerline. The duct valve connects the core gas duct to the first vectoring duct during a first mode of operation, and connects the core gas duct to the second vectoring duct during a second mode of operation. The first vectoring duct directs a second portion of core gas from the core gas duct through a first vectoring duct outlet along a first trajectory. The second vectoring duct directs a third portion of core gas from the core gas duct through a second vectoring duct outlet along a second trajectory that is angularly offset to the first trajectory. | 08-29-2013 |
060230000 | Jet stream deflecting means | 10 |
20090158703 | SLIDING RAMP NOZZLE SYSTEM FOR A GAS TURBINE ENGINE - A regulator system includes a slidable ramp intermediate a secondary flow path and a primary flow path of a gas turbine engine nozzle section. | 06-25-2009 |
20100223906 | COMPONENT FOR USE IN STREAMS OF HOT GAS - The present application provides a component for use in streams of hot gas, which comprises a first region of fiber-ceramic material, a second region of fiber-ceramic material and a middle layer of fiber-ceramic material which is arranged between the first region and the second region, wherein the fiber-ceramic material of the middle layer has a lower ceramic content than the fiber-ceramic material of the first region and the second region, and wherein at least one acute-angled in-flow edge and/or away-flow edge of the component is formed on the middle layer. | 09-09-2010 |
20110030339 | Multifunctional propulsive system for an airplane - A propulsive system for aircraft that has a jet engine and a nacelle surrounding the aforementioned jet engine. The nacelle has a front section fixed relative to the jet engine, and a rear extremity behind the front section, and has a rear section with two petals hinged relative to the front section. Each of the two petals in a position called zero-setting forms an extension of the front section of the nacelle in which the inside and outside surfaces of the petals and, respectively, determine the aerodynamic forms of the rear section, which are in geometric continuity with the inside and outside surfaces and, respectively, that determine the aerodynamic forms of the front section. The petals can be set individually at a positive or negative setting angle to put into play the reverser, APU, air brake, vectorial, and taxiing modes of the propulsive system. | 02-10-2011 |
20110083418 | FLYING OBJECT - In order to provide a flying object with an engine comprising a combustion chamber with a combustion space and a nozzle with a nozzle space following the combustion chamber, the transition between combustion chamber and nozzle lying in a plane in which a cross-section of the combustion space converges, in which thrust control in terms of magnitude and/or thrust vector can be carried out in a simple manner, it is provided that a centre body adapted to have combustion products flowing around it is at least partially arranged in the nozzle space, outside of the combustion space, and at least three jet vanes are arranged at the centre body. | 04-14-2011 |
20110120084 | GAS TURBINE ENGINE AIR VALVE ASSEMBLY - A gas turbine engine air valve assembly has first and second valving elements. The second element is rotatable about a first axis relative to the first element. The rotation controls a flow of air through the first and second elements. An actuator is coupled by a linkage to the second element. The linkage includes a spindle having a first portion coupled to the actuator to rotate the spindle about a second axis. A guided spherical bearing couples a second portion of the spindle to the second element. | 05-26-2011 |
20110296813 | VARIABLE AREA FAN NOZZLE WITH BYPASS FLOW - The exit area of a nozzle assembly is varied by translating a ring assembly located at a rear of the engine nacelle. The ring may be axially translatable along the axis of the engine. As the ring translates, the trailing edge of the ring defines a variable nozzle exit area. Translation of the ring creates an upstream exit at a leading edge of the ring assembly. The upstream exit can be used to bleed or otherwise spill flow excess from the engine bypass duct. As the engine operates in various flight conditions, the ring can be translated to obtain lower fan pressure ratios and thereby increase the efficiency of the engine. Fairings partially enclose actuator components for reduced drag. | 12-08-2011 |
20120285138 | AIRCRAFT GAS-TURBINE ENGINE WITH OIL COOLER IN THE ENGINE COWLING - The present invention relates to an aircraft gas-turbine engine with a core engine surrounded by a bypass duct, with a radially outer engine cowling enclosing the bypass duct and being provided at its rear region with a thrust-reversing device which is moveable relative to the engine cowling, with at least one cooler element extending over at least part of the circumference being arranged in the intermediate area between the engine cowling and the thrust-reversing device. | 11-15-2012 |
20150308377 | THRUST-REVERSER ASSEMBLIES THAT UTILIZE ACTIVE FLOW-CONTROL AND SYSTEMS AND METHODS INCLUDING THE SAME - Thrust-reverser assemblies that utilize active flow-control and systems and methods including the same are disclosed herein. The thrust-reverser assemblies define a forward-thrust configuration and a reverse-thrust configuration. The thrust-reverser assemblies include a bullnose fairing that defines a portion of a reverser duct and an active flow-control device. The active flow-control device is located to energize a boundary layer fluid flow within a boundary layer that is adjacent to the bullnose fairing to resist separation of the boundary layer from the bullnose fairing when the thrust-reverser assembly is in the reverse-thrust configuration. The methods include flowing a thrust-reverser fluid stream through the reverser duct to generate the boundary layer and energizing a boundary layer fluid flow within the boundary layer with an active flow-control device to resist separation of the boundary layer from the bullnose fairing. | 10-29-2015 |
20160177875 | COMBUSTION GAS DISCHARGE NOZZLE FOR A ROCKET ENGINE PROVIDED WITH A SEALING DEVICE BETWEEN A STATIONARY PART AND A MOVING PART OF THE NOZZLE | 06-23-2016 |
060231000 | By secondary fluid injection | 1 |
20080295481 | Fluidic vectoring for exhaust nozzle - An exhaust nozzle assembly provides fluidic thrust vectoring of the primary stream to enhance aircraft maneuverability. The exhaust nozzle assembly includes a cooling air passage that supplies cooling air. A vector opening injects cooling airflow into the exhaust passage to the primary stream. A cover plate is movable to partially block the vector openings and adjust the location of injection of the cooling airflow into the exhaust passage. | 12-04-2008 |
060232000 | Motive fluid outlet movable relative to motor part | 6 |
20090064660 | NOZZLE WITH YAW VECTORING VANE - An exhaust vane disposed in a divergent section of an aircraft gas turbine engine exhaust nozzle is sideways pivotable about a vane pivot axis. The nozzle vane pivot axis may be centrally located at an unvectored nozzle throat. Transversely spaced apart upper and lower tips of the exhaust vane may be incorporated to sealingly engage a nozzle outer wall along upper and lower surfaces of the outer wall of the nozzle. The exhaust vane has flat or contoured vane sidewalls and contoured vane sidewalls may be concave. The exhaust vane may have transversely biased apart upper and lower vane sections extending transversely inwardly from the upper and lower tips of the exhaust vane respectively. The exhaust vane may be articulated having upstream and downstream sections separately sideways pivotable about the vane pivot axis and a second pivot axis downstream of and parallel to the vane pivot axis respectively. | 03-12-2009 |
20110131948 | Engine Exhaust System with Directional Nozzle - An exhaust system for an aircraft has a primary exhaust duct for communicating exhaust gas from an engine exhaust exit and is configured for movement with the engine. A secondary exhaust duct is in fluid communication with the primary exhaust duct and is movably mounted to the airframe. The secondary duct has a portion selectively rotatable relative to the remainder of the secondary duct for directing the exhaust gas vector. The system has means for maintaining a generally consistent relative alignment between the primary duct and the secondary duct. | 06-09-2011 |
20110232262 | RADIAL AND AXIAL COMPLIANT SLIDING SEAL INCORPORATING SPRING CAPTURING FEATURES FOR IMPROVED BEARING PLANE SEALING IN AN ARTICULATING NOZZLE - A seal assembly ( | 09-29-2011 |
20120042628 | Robotic manipulator - A controlled relative motion system that permits a controlled motion member, joined to a base member, to selectively move with respect to said base member having a base support, an output structure, and a plurality of securing links including a fixed length securing link that is rotatably connected at one end thereof to the base support and rotatably connected at an opposite end thereof to the output structure. Further included is a variable length securing link that is rotatably connected at one end thereof to the base support and rotatably connected at an opposite end thereof to the output structure and having a force distributor therewith that can be directed to vary a separation distance between said ends thereof by a force imparting member capable of directing the force distributor to vary the separation distance between the variable length securing link ends. The variable length securing link also has a rotatable capstan therewith about which a cable can be selectively wrapped or unwrapped through rotating this capstan by a force imparting member to vary the separation distance between the variable length securing link ends. The system can be used with a jet propulsion engine in a moveable vehicle that can also have therein a controlled signal processing relative motion system. | 02-23-2012 |
20120060467 | FASTENER FITTING BETWEEN THE MOVABLE PORTION OF A DEPLOYABLE DIVERGING BELL FOR A THRUSTER AND A MECHANISM FOR DEPLOYING SAID MOVABLE PORTION - The fastener fitting ( | 03-15-2012 |
20160084200 | SPACE STORABLE, THRUST-VECTORABLE ROCKET MOTOR NOZZLE AND RELATED METHODS - A thrust-vectoring rocket motor nozzle includes a forward assembly having a forward shell with a flange configured for connection to a motor and a throat portion opposite the flange. A ball joint sleeve may be disposed proximate the throat portion, and an exit cone assembly may include a ball joint socket configured to mate with the ball joint sleeve to allow movement of the exit cone assembly about one or more axes relative to the forward assembly. A thermal barrier may be disposed in a gap between the forward assembly and the exit cone assembly. The forward assembly may include a throat insulator mechanically locked within the forward shell. Related methods include forming thrust-vectorable rocket motor nozzles. Rocket motors may include such nozzles. | 03-24-2016 |