Explosive Jet Patents (Class 244/74)
-
Patent number: 12253049Abstract: The present invention provides a hypersonic large internal contraction ratio air inlet channel having stepless adjustable air release valve, including an air inlet channel front body, an air-discharging slit cover plate, sidewalls, a lip cover, air-discharging cavities, valve plates, partition plates, a rotatable shaft, an expansion section and a driver. The valve plates are rotated through the driver according to the actual working conditions of air inlet channel, the minimum cross-section of the air discharging flow path is thus changed, and a stepless dynamic adjustment of the air discharging flow of the air inlet channel can be realized, so that the aerodynamic performance of the air inlet channel is improved, and the air discharging resistance of the air vehicle is reduced.Type: GrantFiled: March 21, 2022Date of Patent: March 18, 2025Assignees: NANJING UNIVERSITY OF AERONAUTICS AND ASTRONAUTICS, BEIJING AEROSPACE TECHNOLOGY INSTITUTEInventors: Hexia Huang, Zhengkang Lin, Xuebin Tang, Yuan Qin, Huijun Tan, Hang Zhang, Ziren Wang, Chao Li, Xiru Xu
-
Patent number: 11485506Abstract: An aircraft including a fuselage and a propulsion assembly. The propulsion assembly includes at least one fan rotor placed behind the fuselage as an extension thereof along a longitudinal axis, and a nacelle which forms a fairing of the at least one fan rotor through which at least one air flow passes. The aircraft comprises a plurality of stator radial arms mounted upstream of the at least one fan rotor and extending between the fuselage and the nacelle. The radial arms comprise at least one variable-pitch movable portion configured to axially divert the air flow.Type: GrantFiled: July 21, 2016Date of Patent: November 1, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventor: Nicolas Jérôme Jean Tantot
-
Patent number: 11338927Abstract: An aircraft including a fuselage extending along a longitudinal axis; forward swept wings extending from the fuselage; at least one horizontal stabilizer secured to the fuselage; and a distributed electrical propulsion system operatively connected to an electrical power source. The distributed electrical propulsion system have an air intake located rearward of an intersection between the forward swept wings and the fuselage open to a boundary layer region on a surface of the fuselage.Type: GrantFiled: December 10, 2019Date of Patent: May 24, 2022Assignee: BOMBARDIER INC.Inventor: Martin Abramian
-
Patent number: 11162416Abstract: A vehicle structure with unitary casing for an attritable gas turbine engine comprising a vehicle structure forming a unitary casing having a casing wall opposite the vehicle structure; a bypass duct formed between the casing wall and the vehicle structure, wherein the unitary casing is configured to receive a core of the attritable gas turbine engine.Type: GrantFiled: December 17, 2018Date of Patent: November 2, 2021Assignee: Raytheon Technologies CorporationInventors: Evan Butcher, Jesse R. Boyer, Om P. Sharma, Lawrence Binek, Bryan G. Dods, Vijay Narayan Jagdale
-
Patent number: 11136937Abstract: An aircraft propulsion assembly, including a turbine engine comprising at least one gas generator configured to generate a main flow, which is supplied by a central jet to at least one power turbine, the central jet being surrounded by an outer fairing, and the power turbine driving, on the periphery thereof, at least one fan rotor. The aircraft propulsion assembly comprises first movable means which are arranged so as to divert at least some of the main flow from the central jet to the outside of the outer fairing and preferably upstream of the turbine engine so as to generate thrust reversal. An aircraft which uses the propulsion assembly, particularly on the rear tip of the fuselage of the aircraft.Type: GrantFiled: July 21, 2016Date of Patent: October 5, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventors: Nicolas Jérôme Jean Tantot, Antoine Jean-Philippe Beaujard, Pascal Coat, Didier Jean-Louis Yvon
-
Patent number: 11105297Abstract: A turbofan having a nacelle comprising a slider translatable between an advanced position and a retracted position to open a window between a duct and the exterior, a plurality of blades, each one rotatable on the slider between a stowed position and a deployed position, and a maneuvering system that moves each blade and comprises, for each blade, a shaft rotatable on the slider and on which the blade is fixed, and a toothed sector fixed to the shaft, and a toothed arc rotatable on the slider about a longitudinal axis, where the teeth of the toothed arc mesh with the teeth of each toothed sector, a cam, as one with the toothed arc, and a groove, as one with a fixed structure, which receives the cam and where, when the slider moves, the cam follows the groove and rotates the toothed arc.Type: GrantFiled: January 17, 2020Date of Patent: August 31, 2021Assignee: AIRBUS OPERATIONS SASInventors: Pascal Gardes, Guillaume Seguin, Laurent Tizac, Fabien Menou, Frédéric Ridray, Benoit Orteu, Romain Cusset
-
Patent number: 10710745Abstract: A multi-stage, intercooled centrifugal compressor with integral power generator system for a mobile, ground-based aviation support cart is disclosed. A bootstrap-type turbo compressor module which can supply cooled air. The system may be operated in one of several modes: high pressure “bleed air” (e.g., 35-50 psig) for jet engine start, conditioned or cooled air (e.g., 2-5 psig) for aircraft cooling purposes, or electrical ground power. Electrical ground power and conditioned air may also be supplied simultaneously if desired.Type: GrantFiled: September 7, 2017Date of Patent: July 14, 2020Assignee: VOLTAIRE INCORPORATEDInventors: Robert B. Anderson, Brian K. Dalton
-
Patent number: 10106265Abstract: An aerodynamic stabilizer assembly for stabilizing an aft fan mounted to a fuselage of an aircraft is presented. The stabilizer assembly includes one or more generally horizontal stabilizers for mounting to a nacelle of the aft fan and the fuselage so as to stabilize the aft fan. Each of the generally horizontal stabilizers includes an inner portion and an outer portion. The inner portions are mounted to a nacelle of the aft fan and the fuselage at a predetermined downward angle with respect to a central axis of the aft fan so as to direct airflow upwards and into the aft fan, the outer portion being mounted to the inner portion.Type: GrantFiled: June 24, 2016Date of Patent: October 23, 2018Assignee: General Electric CompanyInventors: Jixian Yao, Andrew Breeze-Stringfellow
-
Patent number: 9815560Abstract: An aircraft including a fuselage and an aft engine is provided. The fuselage extends from a forward end of the aircraft towards an aft end of the aircraft. The aft engine is mounted to the fuselage proximate the aft end of the aircraft and includes a fan and a nacelle. The fan is rotatable about a central axis of the aft engine and includes a plurality of fan blades. The nacelle of the aft engine surrounds the plurality of fan blades and defines a bottom portion having a forward end. Additionally, the nacelle defines a curved surface at the forward end of the bottom portion, the curved surface including a reference point where the curved surface defines the smallest radius of curvature. The nacelle further defines a normal reference line extending normal from the reference point. The normal reference line defines an angle with the central axis of the aft engine greater than zero to, e.g., allow for a maximum amount of airflow into the aft engine.Type: GrantFiled: September 21, 2015Date of Patent: November 14, 2017Assignee: General Electric CompanyInventors: Patrick Michael Marrinan, Thomas Lee Becker, Kurt David Murrow, Jixian Yao
-
Patent number: 9540113Abstract: A turbofan engine includes a core engine section including a compressor section feeding air to a combustor to generate high speed exhaust gases that drive a turbine section all disposed about an engine axis, a geartrain driven by the core engine section, a fan section driven by the geartrain about a fan axis spaced apart from the engine axis, and an accessory gearbox driven by the geartrain and mounted apart from the core engine section and the fan section.Type: GrantFiled: February 25, 2014Date of Patent: January 10, 2017Assignee: United Technologies CorporationInventor: Robert L. Gukeisen
-
Patent number: 9157368Abstract: The disclosed turbine engine includes a fan nacelle surrounding a fan and including an inlet arranged upstream from the fan. The inlet includes an inlet surface having a boundary layer flow. A flow control actuator is in fluid communication with the inlet surface. A boundary layer sensing device is associated with the inlet surface for detecting a boundary layer condition at the inlet surface. A controller is in communication with the flow control actuator and the boundary layer sensing device. The controller is programmed to command the flow control actuator in response to the boundary layer sensing device detecting an undesired boundary layer condition. In this manner, the flow control actuator generates a desired boundary layer condition.Type: GrantFiled: September 5, 2007Date of Patent: October 13, 2015Assignee: UNITED TECHNOLOGIES CORPORATIONInventors: Wayne Hurwitz, Stuart S. Ochs
-
Patent number: 9056670Abstract: A hybrid air intake system and method for air-breathing missiles and aircraft comprising providing to an airborne vehicle fuselage an air intake opening comprising at least a pair of side walls and at least an upper wall and a lower wall extending between the side walls, wherein the lower wall extends below a plane defined by the vehicle fuselage, and not employing a boundary layer diverter between the fuselage and the upper wall.Type: GrantFiled: November 30, 2007Date of Patent: June 16, 2015Assignee: Lockheed Martin CorporationInventors: Carlos G. Ruiz, Glenn A. Gebert
-
Patent number: 8662441Abstract: A system for launching an unmanned aerial vehicle (UAV) payload includes a launch tube, liquid rocket, and launch control assembly. The rocket is positioned in the launch tube and contains the UAV payload. A booster assembly may include a canister partially filled with liquid. A gas cylinder is filled with compressed gas. The liquid is pre-pressurized by the gas or mixed with the gas right before launch such that, upon launch, liquid and gaseous thrust stages launch the rocket to a threshold altitude. The UAV payload deploys after reaching the threshold altitude. Optional stability tubes may be connected to the launch tube, which may be buoyant for water-based operations. An optional tether may be connected to the liquid rocket for arresting its flight prior to reaching apogee. The UAV payload is not launched directly by the gas/liquid mix. A method of launching the UAV payload is also disclosed.Type: GrantFiled: February 7, 2012Date of Patent: March 4, 2014Assignee: Sparton CorporationInventors: David Powell, Earl Mark, John T. Houck, Keith Huber
-
Patent number: 8338768Abstract: An actuation assembly is provided. The actuation assembly includes a casing, a plurality of linear actuators coupled to the casing, each of the linear actuators having first and second components and being configured to move the second component thereof relative to the first component thereof along a respective first axis, and a plurality of translational member sets, each being coupled to the second component of a respective one of the linear actuators and the casing and being configured such that when the second component of the respective linear actuator moves along the respective first axis, a selected portion of the translational member set moves substantially along a respective second axis.Type: GrantFiled: October 15, 2008Date of Patent: December 25, 2012Assignee: Honeywell International Inc.Inventors: Casey Hanlon, Kellan Geck, Andrew T. Johnson
-
Patent number: 7828243Abstract: Hypersonic aircraft having a lateral arrangement of turbojet and SCRAMjet engines are disclosed. The SCRAMjet engines may be positioned laterally outboard of the turbojet engines. In one embodiment, the turbojet inlet and outlet openings may be covered during use of the SCRAMjets in order to provide compression and expansion ramps for the laterally adjacent SCRAMjet engines. The side-by-side arrangement of the turbojet and SCRAMjet engines reduces the vertical thickness of the aircraft, thereby reducing drag and potentially increasing performance.Type: GrantFiled: August 3, 2005Date of Patent: November 9, 2010Assignee: Northrop Grumman Systems CorporationInventor: Allen A. Arata
-
Patent number: 7753315Abstract: An un-manned multi-stage payload delivery vehicle and methods of deployment therefore are disclosed. According to various embodiments, the payload delivery vehicle includes first stage and a second stage. At least one of the first and second stages comprises a jet engine. According to various embodiments, methods of deploying the payload delivery vehicle include the steps of launching the payload delivery vehicle from a launch site, controlling the flight of the payload delivery vehicle in accordance with one or more deployment parameters, deploying a payload attached to the payload delivery vehicle, and controlling the flight of the payload delivery vehicle subsequent to payload deployment such that the payload delivery vehicle is flown to a pre-determined location for recovery and reuse.Type: GrantFiled: April 18, 2005Date of Patent: July 13, 2010Assignee: Teledyne Solutions, Inc.Inventor: John R. Troy
-
Patent number: 7581383Abstract: A pulsejet is provided that includes an inlet, an exhaust nozzle, and a combustion chamber between the inlet and the exhaust nozzle. The pulsejet additionally includes a flow-turning device positioned over an end of the inlet. The flow turning device forms an air flow pathway (AFP) having a substantially 180° turn. The 180° turn aligns a direction of exhaust exiting the combustion chamber through the inlet along a positive axial thrust line and substantially parallel with exhaust exiting the combustion chamber through the nozzle.Type: GrantFiled: July 27, 2005Date of Patent: September 1, 2009Assignee: The Boeing CompanyInventor: Richard P Ouellette
-
Patent number: 7427048Abstract: A linear acoustic pulsejet (LAP) including a body having a first side panel and an opposing substantially parallel second side panel. A plurality of substantially parallel intercostals are orthogonally connected to each of the first and second side panels to create a plurality of pulsejet cells within an interior of the body. The LAP additionally includes a linear inlet cap over a top of the body that forms an air flow pathway (AFP) between the linear inlet cap and an exterior of an inlet section of the body. The linear inlet cap forms the AFP to have a substantially 180° turn between an exterior of the body and an interior of the pulsejet cells.Type: GrantFiled: July 27, 2005Date of Patent: September 23, 2008Assignee: The Boeing CompanyInventor: Richard P Ouellette
-
Publication number: 20040084566Abstract: A jet propulsion outlet device is disclosed that has a grid plate having a plurality of densely clustered nozzlettes, the nozzlettes of the grid plate being configured to operably couple to a pressurized gas source to efficiently expand the pressurized gas.Type: ApplicationFiled: November 6, 2002Publication date: May 6, 2004Inventor: Daniel Chasman
-
Publication number: 20030201363Abstract: An aircraft designed with three wings located on either side of the fuselage. The forward wing has a downward angle with a curved top and bottom surface. The upper wing is located towards the rear of the aircraft and above the forward wing. The lower wing is located below the upper wing and slightly forward. It is also located to the rear and below of the forward wing. The outer ends of all three wings come into contact at one point. The forward wing uses the Coanda effect to increase the airflow across the top surface of the bottom wing. The aircraft can be designed so that it is large enough to carry people and/or cargo, or to be small enough to be flown as a toy aircraft. The like design can use any type of aircraft engine commonly used today. One embodiment of the aircraft has two turbines, shaft-coupled to a power source, located on either side of the forward end of the fuselage.Type: ApplicationFiled: January 14, 2002Publication date: October 30, 2003Inventor: Robert Jonathan Carr
-
Patent number: 6632378Abstract: A nitrate ester plasticized energetic composition in which the binder is made of, prior to curing, lower alkylene glycol prepolymer blocks end-capped with ethylene glycol monomers and/or oligomers. The end-capped prepolymer blocks are preferably difunctional or trifunctional. The lower alkylene glycol are preferably propylene glycol, butylene glycol, and/or copolymers thereof. The difunctional end-capped alkylene glycol prepolymer blocks are cured with a diisocyanate or polyisocyanate. In the case of a trifunctional (or higher functional) end-capped alkylene glycol prepolymer block, preferably a diisocyanate is used to effect crosslinking.Type: GrantFiled: March 2, 2001Date of Patent: October 14, 2003Assignee: Alliant Techsystems Inc.Inventors: Ingvar A. Wallace, II, Jeffery Oyler
-
Publication number: 20020190159Abstract: A variable cycle propulsion system for a supersonic airplane, the system comprising at least one engine having at least one compressor and capable of generating thrust for supersonic flight speeds, and at least one auxiliary propulsion assembly separate from said engine, and capable of generating additional thrust for takeoff, landing, and subsonic cruising speeds, at least one pipe connecting the engine to the auxiliary propulsion assembly to convey thereto compressed air produced by the compressor so as to enable the auxiliary propulsion assembly to generate additional thrust for takeoff, landing, and subsonic cruising flight, there being at least one valve enabling the pipe to be closed off for supersonic cruising flight.Type: ApplicationFiled: June 13, 2002Publication date: December 19, 2002Applicant: SNECMA MOTEURSInventors: Michel Franchet, Yann Laugier, Jean Loisy
-
Patent number: 6367739Abstract: A compound exhaust system including two or more stages, preferably three, uses the force of exhaust gases traveling from a thrust generating source through the exhaust system to maximize thrust and minimize wasted energy consumption. In particular, the compound exhaust system for a thrust generating source comprises at least a first stage exhaust and a smaller, second stage exhaust. Various reflections of high speed traveling gases are provided and the resultant pressures induced during this travel supplement the thrust provided by the thrust generating source, which can be a jet engine. The invention also relates to a novel airframe that uses multiple engines having the inventive compound exhaust system.Type: GrantFiled: September 29, 2000Date of Patent: April 9, 2002Inventor: Von Friedrich C. Paterro
-
Patent number: 6227486Abstract: A single-stage earth-to-orbit launch vehicle employs a combination of rocket engines and turbojet engines to propel a device into orbit. The vehicle is driven through a unique set of operating conditions of the engines to conserve oxidizer and optimize acceleration. Cooling effects of fuel used by both types of engines is employed to maintain operating temperature of the turbojet engines within limits of lightweight materials. The rocket engines are used during initial acceleration and then permitted to remain deeply throttled or idle until the vehicle reaches a speed of about Mach 6. The rocket engine, with most of its oxidizer intact, is then used to accelerate the vehicle into orbit.Type: GrantFiled: May 28, 1999Date of Patent: May 8, 2001Assignee: MSE Technology Applications, INC.Inventor: Vladimir Balepin
-
Patent number: 6119985Abstract: A reusable rocket airplane which may be utilized to launch satellites and other payloads into space. The airplane may also be used for rapid surface to surface flight. The reusable rocket airplane may be safely supplied with oxidizer in mid-air, achieve an altitude outside the Earth's atmosphere, and return safely to be used again. The rocket airplane utilizes unique concepts to secure its gas turbine engines for high speed flight, minimize fluid spillage during mid-air oxidizer transfer, as well as employs design features advantageous to the economical building and reuse of the rocket airplane.Type: GrantFiled: March 7, 1997Date of Patent: September 19, 2000Assignee: Pioneer Rocketplane CorporationInventors: Mitchell B. Clapp, Robert M. Zubrin
-
Patent number: 5836542Abstract: A flying craft (14) has a dish shaped body (18, 20, 21) with a convex upper surface (18) to provide lift. Engine means (1) in the form of a jet or rocket engine is housed in the body at the rear, while a duct (15) extends through the body from an air opening (15A) at the front of the craft (14) so as to direct air to the engine means (1) for example to serve as cooling and/or combustion air for the engine means. Additional thruster jets (16A, 16B) can be located on the bottom of the body for directional control. In a further embodiment (FIG. 12), an electric motor driven fan (37) is located in the duct (15) to form a ducted fan propulsion and unit for forward, slightly descending, movement of the craft (14A), while a more powerful jet or rocket engine (35) is located vertically in the craft to effect vertical ascent of the craft to an elevation where forward motion by the ducted fan propulsion unit can commence. A turbine fan driven alternator (27) can also be located in the ducting (15).Type: GrantFiled: April 28, 1995Date of Patent: November 17, 1998Inventor: David Johnston Burns
-
Patent number: 5799902Abstract: A low-cost, liquid-propellant rocket launch vehicle having a central pod that carries an optional final-stage rocket engine cluster, and having additional engine clusters arranged in diametrically opposed pairs of clusters. The pairs of clusters are burned and separated in a staging sequence until the final stage is reached. In the presently preferred embodiment, there are three pairs of engine clusters arranged in a hexagonal configuration about the central pod and each engine cluster contains seven identical engines. The engines are made from light-weight, low-cost materials, without gimbals or other moving parts. Steering of the vehicle is effected by differential control of the engine thrusts of selected engines, using duty-cycle modulation of a plurality of on/off propellant supply valves and, additionally, control of other on/off valves controlling the supply of an inert cryogenic fluid to secondary injection ports on the engine.Type: GrantFiled: July 28, 1997Date of Patent: September 1, 1998Assignee: Microcosm, Inc.Inventors: Edward L. Keith, Thomas P. Bauer
-
Patent number: 5727382Abstract: The present invention relates to an aircraft ram jet engine for supersonic and/or hypersonic flight, intended to operate over a wide range of speeds.According to the invention, the ram jet engine comprises a ram jet engine body (5) including a combustion cheer portion (6) and a jet pipe portion (7), and, in the vicinity of the transition region (8) between the combustion chamber (6) and the jet pipe (7), having a changing geometry passing progressively from a convergent then divergent longitudinal section, for speeds corresponding to a low Mach number, to an at least substantially constant then divergent longitudinal section for speeds corresponding to a high Mach number.Type: GrantFiled: June 27, 1996Date of Patent: March 17, 1998Assignee: Aerospatiale Societe Nationale IndustrielleInventors: Alain Chevalier, Marc Bouchez, Vadim Levine, Valery Avrachkov, Dimitri Davidenko
-
Patent number: 5456429Abstract: A thrust maneuver system for steerable vehicles comprising a plurality of thrusters of varying impulsive force, some of which provide a base force, and others varying multiples of the base force. The forces may be used additively or subtractively to obtain a desired force for any given maneuver.Type: GrantFiled: August 2, 1993Date of Patent: October 10, 1995Assignee: Loral Corp.Inventor: Joseph R. Mayersak
-
Patent number: 5058826Abstract: A method of operating a scramjet engine having an improved low pressure combustion cycle is disclosed. Apparatus for carrying out the method is also disclosed. The method includes the steps of providing supersonic compressed airflow to a combustor and supplying fuel to the combustor for generating a fuel/air mixture having a predetermined temperature less than a temperature required for spontaneous ignition of the fuel/air mixture. The method also includes igniting the fuel/air mixture for sustaining recombination reactions of the fuel/air mixture for generating combustion gases. In the preferred embodiment, the fuel/air mixture is ignited by generating a boundary layer of airflow having atomic oxygen and channeling the boundary layer into the combustor for mixing with a portion of the fuel for generating a boundary layer fuel/oxygen mixture subject to spontaneous ignition.Type: GrantFiled: January 29, 1990Date of Patent: October 22, 1991Assignee: General Electric CompanyInventor: George A. Coffinberry
-
Patent number: 4817892Abstract: An engine suitable for use in an aerospace plane is a composite engine comprising, in combination, a turbo jet engine, a ram jet engine, and a rocket engine, all arranged co-axially. An aerospace plane comprises such an engine mounted in a body defining, toward a rear thereof, in association with said engine, a nozzle surface which extends rearwardly in curved, concave manner, and which is part-round in cross-section, said or each nozzle surface being arranged in relation to a nozzle of said engine to be an extension of the nozzle.Type: GrantFiled: April 28, 1987Date of Patent: April 4, 1989Inventor: Charl E. Janeke
-
Patent number: 4723736Abstract: An improved rocket staging system for missiles and the like wherein a carriage borne rocket engine assembly is sequentially employed within separate, generally aligned oxidizer stages which are generally coaxially disposed about the central rocket engine and its associated carriage. A central fuel tank is surrounded by several separate, cooperating, generally ring-shaped oxidizer tanks generally coaxially disposed about the rocket periphery. A plurality of oxidizer delivery lines run through each of the outer tanks and up to the top of the fuel tank, where a flexible hose brings oxidizer down to the engine carriage. As fuel is consumed, the rocket motor carriage slides upwardly inside the fuel tank in response to thrust. When the carriage is firmly seated inside the next higher oxidizer tank and all of the propellant has been removed from the lowest tank, the lowest tank is jettisoned to discard unnecessary mass.Type: GrantFiled: August 18, 1986Date of Patent: February 9, 1988Inventor: Todd Rider