Product
Patsnap Eureka
For R&D, Patsnap Eureka makes reading and utilizing patents & technical documents easy.
Patsnap Eureka AIR
Designed for self-driven R&D workflows. Generate viable solutions, solve complex R&D challenges, empower your innovation with AI.
Patsnap Eureka Materials
Designed for material experts only. Revolutionize your material R&D, from search, analyze, to developing new materials.
Feature
TechResearch
Generate reliable direction feasibility study reports for your R&D in just a few steps.
TechSeek
Discover and master advanced knowledge NOW. Basics, ideas, possibilities, all at once.
TechMind
As an expert in R&D Theories, TechMind can generates customized viable solutions instantly.
TechRisk
Analyze your overall solution with one click, know your potential R&D risks in advance.
TechMonitor
Get weekly tech updates, stay abreast of the latest tech innovations and key insights.
Patents
Literature
Hiro is an intelligent assistant for R&D personnel, combined with Patent DNA, to facilitate innovative research.
42results about "Rocket type power plants" patented technology
Efficacy Topic
Property
Owner
Technical Advancement
Application Domain
Technology Topic
Technology Field Word
Patent Country/Region
Patent Type
Patent Status
Application Year
Inventor
Rocket-powered entertainment vehicle
InactiveUS20100096491A1Aircraft navigation controlRocket type power plantsRocketAutomotive engineering
A rocket-powered vehicle used for entertainment, namely races, exhibitions, competitions, and revenue-generating events.
Owner:ROCKET RACING
Collection and distribution system
InactiveUS20080221745A1Rocket type power plantsDigital data processing detailsDistribution systemEngineering
A collection and distribution system wherein information is collected from one or more aerial vehicles and from one or more ground-based sources before being processed and provided to an end-user.
Owner:ROCKET RACING
Rocket-powered vehicle racing information system
InactiveUS20070194171A1Improving pilot performanceImprove performanceRocket type power plantsSpace shuttlesRocketComputer-generated imagery
A rocket-powered race for entertaining spectators wherein computer-generated images are optionally provided to at-least partially define a race-course.
Owner:ROCKET RACING
Rankline-Brayton engine powered solar thermal aircraft
InactiveUS8132412B2Significant pressure dropHigh thermal efficiencyRocket type power plantsFrom solar energyThermal energyWorking fluid
Owner:LAWRENCE LIVERMORE NAT SECURITY LLC
In-flight transfer of reactant from a towing or carrying airplane to an attached rocket or rocketplane
ActiveUS20180265211A1Dry weight increaseSmall payloadRocket type power plantsLaunch systemsJet aeroplaneLine tubing
A high altitude vehicle is brought to a desired altitude above sea-level prior to the transfer of fuel and / or oxidant from an airplane to the high altitude vehicle. The high altitude vehicle may be towed to the desired altitude by a tow airplane or may reach the desired altitude under its own power. At the desired altitude, the high altitude vehicle is connected to the tow airplane via a tow cable. Alternatively, the high altitude vehicle may be mechanically carried by the tow airplane. Fuel and / or oxidant is transferred to the high altitude vehicle from the tow airplane via respective fuel and / or oxidant lines. The high altitude vehicle then separates from the tow airplane and proceeds to high altitude under its own power.
Owner:BURGENER JOHN A +2
Rankline-Brayton Engine Powered Solar Thermal Aircraft
InactiveUS20100162702A1Significant pressure dropHigh thermal efficiencyRocket type power plantsFrom solar energyThermal energyWorking fluid
A solar thermal powered aircraft powered by heat energy from the sun. A Rankine-Brayton hybrid cycle heat engine is carried by the aircraft body for producing power for a propulsion mechanism, such as a propeller or other mechanism for enabling sustained free flight. The Rankine-Brayton engine has a thermal battery, preferably containing a lithium-hydride and lithium mixture, operably connected to it so that heat is supplied from the thermal battery to a working fluid. A solar concentrator, such as reflective parabolic trough, is movably connected to an optically transparent section of the aircraft body for receiving and concentrating solar energy from within the aircraft. Concentrated solar energy is collected by a heat collection and transport conduit, and heat transported to the thermal battery. A solar tracker includes a heliostat for determining optimal alignment with the sun, and a drive motor actuating the solar concentrator into optimal alignment with the sun based on a determination by the heliostat.
Owner:LAWRENCE LIVERMORE NAT SECURITY LLC
Fire fighting system using drone
PendingUS20210138281A1Restriction flight timeTimely controlRocket type power plantsTethered aircraftStructural engineeringElectric cables
The present invention relates to a fire fighting system for transporting a nozzle of a fire hose coupled to a drone to a high place. The fire fighting system includes a fire hose (10) having a fire hose (10) having a nozzle (11) for injecting a fire extinguishing liquid; a fire-extinguishing-liquid supply source (2) which is coupled to the fire hose (10), and supplies the fire extinguishing liquid to the fire hose (10); a top drone (1) coupled to the nozzle (11); a wired cable (4) coupled to the top drone (1); and a power supply unit (3) which supplies power or fuel for flying the top drone (1) through the wired cable (4).
Owner:EBARA CORP
Vertical takeoff and landing aircraft
InactiveUS20050109875A1Reduce vulnerabilityReduced Radar Cross SectionRocket type power plantsPower installationsFlight vehicleFixed wing
A method is provided for reducing vulnerability to hostile detection of and aggression towards an aircraft. The method includes adapting an aircraft fuselage to form an armored payload bay, wherein the armored payload bay includes a pair of sidewalls and a bottom. The method additionally includes adapting wings of the aircraft to allow the aircraft to be transported within a larger aircraft. For example, the wings could have a fixed wing span that allows the aircraft to transported within a larger aircraft or the wings could be adapted to fold so that the aircraft can transported within a larger aircraft. The method further includes disposing at least one pulse ejector thrust augmentor (PETA) bank within each sidewall. Each PETA bank is oriented such that a thrust exhaust produced is directed down and away from a centerline of the payload bay. Still further, the method includes adapting the bottom of payload bay to allow ingress and egress of cargo.
Owner:THE BOEING CO
Four high-speed air vehicles adopting novel engine
InactiveCN106494626AHigh combined powerMeet the requirement of shortening the intercontinental flight time by 1-2 timesRocket type power plantsCosmonautic vehiclesAviationJet aeroplane
The invention relates to four high-speed air vehicles adopting a novel engine. For the flying height and speed limit of an existing airplane, by adopting a novel turbofan engine and a combination of the novel turbofan engine and a novel rocket engine, the flying height of a supersonic airliner can reach 20-35 km, the Mach number of the supersonic airliner can reach 2-4, the flying height of a hypersonic unmanned aerial vehicle can reach 35-50 km, and the Mach number of the hypersonic unmanned aerial vehicle can reach 5-7. For single use of an existing carrier rocket, a horizontal rising-falling combined dynamic double-body rocket releases a hanging rocket when the flying height reaches 28-50 km and the Mach number reaches 4-7 and then returns to land, and therefore repeated use of the carrier rocket is achieved. For the problem that the research difficulty of a heavy carrier rocket is high, an economical and applicable carrier rocket is constructed by adopting three novel rocket engines. The four high-speed air vehicles have the advantage that aviation and spaceflight are combined integrally and are wide in application range.
Owner:葛明龙
In-flight transfer of reactant from a towing or carrying airplane to an attached rocket or rocketplane
ActiveUS10384797B2Reduce disadvantagesRocket type power plantsConvertible aircraftsJet aeroplaneFlight vehicle
A high altitude vehicle is brought to a desired altitude above sea-level prior to the transfer of fuel and / or oxidant from an airplane to the high altitude vehicle. The high altitude vehicle may be towed to the desired altitude by a tow airplane or may reach the desired altitude under its own power. At the desired altitude, the high altitude vehicle is connected to the tow airplane via a tow cable. Alternatively, the high altitude vehicle may be mechanically carried by the tow airplane. Fuel and / or oxidant is transferred to the high altitude vehicle from the tow airplane via respective fuel and / or oxidant lines. The high altitude vehicle then separates from the tow airplane and proceeds to high altitude under its own power. The high altitude vehicle weighs less and may have smaller wings than a comparable vehicle configured for self-powered, fully fueled flight from takeoff.
Owner:BURGENER JOHN A +2
Rocket propelled drone
PendingUS20210031913A1Comparable and good performanceGood power to weight ratio power to ratioRocket type power plantsConvertible aircraftsFlight vehicleUncrewed vehicle
Disclosed is a remotely controlled wireless drone which employs a solid fuel rocket engine to propel it quickly to a desired or location. More specifically, an unmanned vehicle including a fuselage and a propulsion unit engaged with the fuselage, the propulsion unit being operable to bring the unmanned vehicle to a desired altitude or location, generally during a launch stage. The fuselage also includes multiple rotors pivotally engaged with the fuselage and a rotor positioning system operable to pivot the multiple rotors between stowed and deployed positions. The stowed position of the propellers minimizes drag and instability during the launch stage, and the deployed position allows the multiple rotors to control the position and altitude of the unmanned vehicle after the fuel of the rocket engine is spent. Submersible / amphibious and other embodiments are also described.
Owner:MARTEL RANDY
Novel Mars spacecraft combined propulsion system
The invention relates to a novel Mars spacecraft combined propulsion system, and relates to the technical field of Mars exploration and Mars spacecraft power. The invention aims to solve the problem that the existing propulsion system needs to carry a large amount of fuel from the earth and cannot meet the full-phase flight mission of a Mars spacecraft. The output ends of an oxidant storage tank and a fuel storage tank are correspondingly connected with the input ends of an oxidant pump and a fuel pump respectively; flow regulating valves are arranged on a pipeline for connecting the oxidant storage tank with the oxidant pump and a pipeline for connecting the fuel storage tank with the fuel pump; the fuels in the oxidant storage tank and the fuel storage tank are delivered to a combustionchamber for combustion through the oxidant pump and the fuel pump respectively, and the tail end of the combustion chamber is connected with the head end of an exhaust nozzle. According to the novel Mars spacecraft combined propulsion system provided by the invention, a propellant required by a spacecraft can be directly prepared by utilizing available resources of Mars.
Owner:HARBIN INST OF TECH
In-flight transfer of reactant from a towing or carrying airplane to an attached rocket or rocketplane
ActiveUS20190168887A1Dry weight increaseSmall payloadRocket type power plantsConvertible aircraftsJet aeroplaneFlight vehicle
A high altitude vehicle is brought to a desired altitude above sea-level prior to the transfer of fuel and / or oxidant from an airplane to the high altitude vehicle. The high altitude vehicle may be towed to the desired altitude by a tow airplane or may reach the desired altitude under its own power. At the desired altitude, the high altitude vehicle is connected to the tow airplane via a tow cable. Alternatively, the high altitude vehicle may be mechanically carried by the tow airplane. Fuel and / or oxidant is transferred to the high altitude vehicle from the tow airplane via respective fuel and / or oxidant lines. The high altitude vehicle then separates from the tow airplane and proceeds to high altitude under its own power. The high altitude vehicle weighs less and may have smaller wings than a comparable vehicle configured for self-powered, fully fueled flight from takeoff.
Owner:BURGENER JOHN A +2
Rocket-powered vehicle racing reality system
InactiveUS20080217472A1Cosmonautic condition simulationsRocket type power plantsFlight vehicleEngineering
An aerial vehicle race and reality system for entertaining spectators wherein computer-generated images are optionally provided to at-least partially define a race-course.
Owner:ROCKET RACING
Propulsion system with integrated rocket accelerator
ActiveUS20090057494A1Lower performance requirementsIncrease thrustAircraft navigation controlRocket type power plantsRamjetJet engine
The present invention relates to a propulsion system for a vehicle. The propulsion system has an airframe integrated hydrocarbon fueled airbreathing engine, such as a ramjet or a scramjet. The propulsion system further has at least one rocket positioned so as to use the aft body contour of the vehicle directly for flow expansion. In a preferred embodiment, a plurality of rockets are arrayed across the width of the engine nozzle.
Owner:AEROJET ROCKETDYNE INC
Superconductive hypersonic liquefaction nosecone
ActiveUS9193457B2Maximizing the suprecooling and liquefaction potentialRocket type power plantsFuselagesEvaporationShock front
Owner:JANEKE CHARL EMELIO
Superconductive Hypersonic Liquefaction Nosecone
ActiveUS20150048208A1Maximizing the suprecooling and liquefaction potentialRocket type power plantsFuselagesAviationChemical element
An apparatus and method for mitigating the shock front of a rocket or aerospace plane flying at hypersonic speeds while simultaneously distilling liquid chemical elements from the ambient air. The invention employs supercooling (through a combination of superconductivity and / or superemissivity) driven by the cryogenic power of liquid hydrogen and / or regenerative evaporation of liquid hydrogen and / or liquid nitrogen to drive isothermal compression and consequentially usurp the shock front in totality at Mach 1. The ensuing supercool / chilled air that is rendered as a consequence of supercooling may hence be compressed, regeneratively intercooled & flashed into liquid air. By means of extension liquid air may be rendered as a direct result of said supercooling throughout the hypersonic regime into space. Under conditions of optimality the incipient air stream may be compressed in accord with the stagnation pressure of the Mach number and liquefacted in one-step via the power of supercooling and isothermal compression
Owner:JANEKE CHARL EMELIO
Aircraft with hybrid aerodynamic and space flight, and associated flight control method
InactiveCN101522525AContribute to carrying capacityFully navigableRocket type power plantsLaunch systemsJet aeroplaneFlight vehicle
This aircraft comprises both thrusters (7, 16, 17) for conventional aircraft flight through the atmosphere and for high-altitude use as a rocket. It is divided into a payload compartment (8) and a compartment (13) chiefly containing the rocket motor propellants. It comprises a long, low-backsweep transverse wing (3) near the rear to provide better wing lift in the dense strata of the atmosphere and allow the aircraft to climb to high altitudes at subsonic speed before the rocket motors are used. Return to earth is in gliding flight or flight controlled in the same way as a conventional aircraft.
Owner:ASTRIUM GMBH
Umbrella-shaped boosting solar aircraft
InactiveCN110481779AIncrease stiffnessImprove stabilityPhotovoltaic supportsRocket type power plantsEnergy storageHelicopter rotor
The invention provides an umbrella-shaped boosting solar aircraft. The aircraft comprises an aircraft body, a rocket engine, a solar film, a coaxial double-rotor mechanism, an energy storage battery and an umbrella-shaped retractable structure; the coaxial double-rotor mechanism is installed at the upper end of the aircraft body, the rocket engine is installed at the lower end of the aircraft body, the umbrella-shaped retractable structure is installed outside the middle section, and the energy storage battery is installed inside the aircraft body; the umbrella-shaped retractable structure isclung to the outer wall of the aircraft body when being folded, is conical when being unfolded and is coaxial with the aircraft body; and the solar film covers the upper surface of the umbrella-shapedretractable structure and supplies power to the energy storage battery. The launching initial speed can be increased, the initial loss energy is reduced, the variable structure design of the aircraftis realized, and the aircraft is more convenient to launch, recover and store.
Owner:西安长峰机电研究所
War zone camera shooting bulletproof unmanned plane
ActiveCN106394903AImprove survivabilityImprove securityRocket type power plantsAircraft indicatorsSurvivabilityMarine engineering
The invention provides a war zone camera shooting bulletproof unmanned plane. The war zone camera shooting bulletproof unmanned plane comprises a camera shooting module, a main protection module, side protection modules and a main plane body, and the rear end surface of the main pedestal of the camera shooting module is fixedly arranged in the very center of the front end surface of the main plane body; the main protection module is arranged on two first supports on the front end surface of the camera shooting pedestal through two second joints; and the side protection modules are arranged on second supports on the side surface of the plane body through third joints, and the third joints are directly driven by steering engines. The unmanned plane is pushed by a rocket engine, and shields are respectively arranged in the front, back, left and right directions, so the unmanned plane has certain bulletproof ability and high survivability, can fly in a war zone, acquires video and audio information, and greatly improves the safety of the interview process.
Owner:博申科技发展有限公司
Vertical takeoff and landing aircraft
ActiveUS20050151004A1Reduce vulnerabilityAircraft navigation controlRocket type power plantsWingspanFuselage
A flight capable mobile platform adapted for covert deployment is provided. The mobile platform is additionally adapted to have a reduced vulnerability to hostile detection and aggression. The mobile platform includes a fuselage having a pair of sidewalls and a bottom. The sidewalls and bottom form an armored payload bay. The mobile platform additionally includes a pair of wings connected to the fuselage. The wings have a fixed wingspan constructed such that the mobile platform can be transported by a larger second mobile platform. This allows for the mobile platform to be aerial deployed from the larger second mobile platform. Each of the sidewalls include at least one pulse ejector thrust augmentor (PETA) bank that is canted outward. Therefore, thrust exhaust produced by each PETA bank is directed down and away from a centerline of the payload bay. Furthermore, the bottom of the mobile platform is adapted to allow ingress and egress of cargo, e.g. military troops, from the payload bay.
Owner:THE BOEING CO
Propulsion system with integrated rocket accelerator
ActiveUS7849670B2Lower performance requirementsIncrease thrustRocket type power plantsContinuous jet plantsRamjetJet engine
The present invention relates to a propulsion system for a vehicle. The propulsion system has an airframe integrated hydrocarbon fueled airbreathing engine, such as a ramjet or a scramjet. The propulsion system further has at least one rocket positioned so as to use the aft body contour of the vehicle directly for flow expansion. In a preferred embodiment, a plurality of rockets are arrayed across the width of the engine nozzle.
Owner:AEROJET ROCKETDYNE INC
In-flight transfer of reactant from a towing or carrying airplane to an attached rocket or rocketplane
ActiveUS10106273B2Reduce disadvantagesRocket type power plantsLaunch systemsJet aeroplaneLine tubing
A high altitude vehicle is brought to a desired altitude above sea-level prior to the transfer of fuel and / or oxidant from an airplane to the high altitude vehicle. The high altitude vehicle may be towed to the desired altitude by a tow airplane or may reach the desired altitude under its own power. At the desired altitude, the high altitude vehicle is connected to the tow airplane via a tow cable. Alternatively, the high altitude vehicle may be mechanically carried by the tow airplane. Fuel and / or oxidant is transferred to the high altitude vehicle from the tow airplane via respective fuel and / or oxidant lines. The high altitude vehicle then separates from the tow airplane and proceeds to high altitude under its own power.
Owner:BURGENER JOHN A +2
Fixed-wing unmanned aerial vehicle and takeoff and landing methods thereof
PendingCN108394560AAdaptableLow environmental requirements for takeoff and landingRocket type power plantsAircraftsTakeoffLevel flight
The invention provides a fixed-wing unmanned aerial vehicle and takeoff and landing methods thereof. A multi-engine combined power form is adopted. The takeoff method of the unmanned aerial vehicle comprises the steps before takeoff, in a takeoff process, in a level flight process and the like. The landing method of the unmanned aerial vehicle comprises the steps of gliding and landing, stalling and descending, touching the ground and landing and the like. The fixed-wing unmanned aerial vehicle provided by the invention has the advantages that hand throwing takeoff of the unmanned aerial vehicle with relatively great takeoff weight can be realized, and auxiliary power in the takeoff process can be used for assisting the takeoff and also can be used for assisting landing; the system is simple; the performance of the unmanned aerial vehicle is improved; a takeoff and landing manner has strong adaptability; the scheme has relatively low requirements on a takeoff and landing environment and almost can realize takeoff and landing on any field.
Owner:成鑫
Electrically operated propellant thrust assist for supplementing airplane takeoff, landing or in-flight maneuverability
InactiveUS20180273193A1Well formedRocket type power plantsCosmonautic vehiclesJet aeroplaneSingle pair
Electrically operated propellant thrust assist supplements an airplane's takeoff, landing or inflight maneuvers. Unlike conventional SRM propellants, the burn rate of the electrically operated propellant can be varied via an electrical input and even extinguished by interrupting the electrical to control a secondary thrust profile (e.g., amplitude, transition rates) to fulfill the needs of a given takeoff, inflight or landing maneuver and provide a smooth transition in and out of the maneuver. Multiple pairs of fixed thrusters (opposite sides of the fuselage), a single pair of gimbaled thrusters or a hybrid of fixed and gimbaled thrusters may be configured to provide all such maneuvers. Flight control inputs are passed back and forth through an interface to enable the thrust assist.
Owner:RAYTHEON CO
Device for reducing aerodynamic drag
The invention relates to a device for reducing the aerodynamic drag of a vehicle (1) provided with at least one engine (2) including a gas ejection nozzle (3) protruding from the rear of the vehicle fuselage (4) and flaring away from the rear of the vehicle fuselage, characterised in that it comprises at least one member (5) for masking at least a portion of the nozzle, made of a resorptive material (6) that can be eliminated in the nozzle flow once the engine is operating. The invention also relates to a spacecraft including the same.
Owner:ASTRIUM GMBH
Intercontinental quick arrival transportation system based on rocket power
InactiveCN113335526AFlying fastShorter intercontinental shipping timesRocket type power plantsAircraftsFlight vehicleTransit system
The embodiment of the invention provides an intercontinental quick arrival transportation system based on rocket power, which is characterized in that the intercontinental quick arrival transportation system adopts a two-stage wing lift type structure and comprises a boosting-stage aircraft and a load-stage aircraft, the booster-level aircraft and the load-level aircraft are powered by liquid rocket engines, and the intercontinental quick arrival transportation system adopts a mode of horizontal takeoff and landing on an airport runway. The boosting-stage aircraft is used for sending the load-stage aircraft to a preset height at a certain speed; the load-level aircraft is loaded with an effective load to carry out intercontinental flight tasks; and the boosting-stage aircraft and the load-stage aircraft independently execute tasks.
Owner:SHANGHAI AEROSPACE SYST ENG INST
Method of flying an aircraft
InactiveUS20160144968A1Duration of flight is reducedReduce fuel consumptionRocket type power plantsGas turbine type power plantsFlight vehicleHigh velocity
Provided is a fuel-efficient method of flying an aircraft for flying an aircraft. The present invention relates to a method of flying an aircraft 1 having a fuselage 2, primary wings 3, and high-power engines 6 serving as driving units for generating a thrust. The method of flying an aircraft comprising: determining a combination of said primary wings 3 and high-power engines 6 so that a total wing area of said primary wings 2 is proportionally correlated to an power output of said high-power engines 6, generating a comparatively large lifting power using said primary wings 3 having large wing areas, elevating said aircraft 1 to a high altitude, and flying said aircraft 1 at high speeds and altitudes using said high-power engine 6.
Owner:KIKUCHI NAOMI
Emergency landing apparatus deployment for emergency landing of aircraft
ActiveUS11279494B2Reduce upwards thrustAircraft navigation controlRocket type power plantsFlight vehicleControl circuit
An emergency landing apparatus for an aircraft and a method of operating the emergency landing apparatus is provided. The emergency landing apparatus comprises: one or more rocket motors arranged to eject efflux in order to provide upwards thrust to control descent of the aircraft during emergency landing of the aircraft; and control circuitry configured to: cause the one or more rocket motors to eject efflux and provide upwards thrust to control descent of the aircraft during emergency landing of the aircraft; and cause redirection of the efflux ejected by the one or more rocket motors, during the emergency landing of the aircraft, in order to reduce the upwards thrust provided by the one or more rocket motors.
Owner:ACTIVE VTOL CRASH PREVENTION LTD
Center of gravity propulsion space launch vehicles
An aerospace vehicle that permits horizontal launch and subsequent orbital deployment of a second stage. The vehicle can be returned to Earth for subsequent re-use. Both land-based and water-based launch is disclosed. A rocket propulsion engine is located at the center of gravity of the vehicle and rotates to provide vertical and horizontal thrust.
Owner:SHEERIN GEOFFREY T
Who we serve
- R&D Engineer
- R&D Manager
- IP Professional
Why Patsnap Eureka
- Industry Leading Data Capabilities
- Powerful AI technology
- Patent DNA Extraction
Social media
Patsnap Eureka Blog
Learn More Browse by: Latest US Patents, China's latest patents, Technical Efficacy Thesaurus, Application Domain, Technology Topic, Popular Technical Reports.
© 2024 PatSnap. All rights reserved.Legal|Privacy policy|Modern Slavery Act Transparency Statement|Sitemap|About US| Contact US: help@patsnap.com