21 results about "Thrust vectoring" patented technology

This invention discloses an aerodynamic optimization design method for scaled-down model blades of large vertical axis wind turbines based on DMST theory. The method includes: determining scaled-down parameters according to wind tunnel similarity criteria; selecting an optimized airfoil for aerodynamic characteristic matching at low Reynolds numbers based on the lift-to-drag ratio characteristics of the prototype blades; constructing an aerodynamic performance model based on dual-disk multi-flow theory, calculating and verifying the theoretical thrust coefficients of the prototype and optimized airfoils; conducting force-pressure tests in a wind tunnel, extracting the pure thrust of the blades by subtracting the total thrust of the turbine from the tower thrust vector; and comparing the measured thrust coefficients with the theoretical thrust coefficients to verify the aerodynamic load matching degree. This invention effectively eliminates the Reynolds number effect in scaled-down tests by combining airfoil optimization, DMST theory verification, and wind tunnel test verification, achieving high-precision matching of aerodynamic loads on scaled-down model blades of vertical axis wind turbines and improving the reliability of wind tunnel test data.

A heat exchanger configured to perform heat exchange for a heat source of a fuselage and provide thrust or thrust vectoring to the fuselage, and an aircraft including the same are disclosed. The aircraft includes a fuselage, at least one inlet provided at a side of the fuselage, at least one outlet provided at a bottom of the fuselage, and a fan unit having at least one fan disposed between the inlet and the outlet along a fluid flow direction and drawing air inward through the at least one inlet to discharge through the at least one outlet.

The application relates to a force couple balance and longitudinal array push-pull vertical take-off and landing high-speed aircraft, belonging to the technical field of aircrafts, which comprises a fuselage, a rotor, a fixed wing, a steering controller and a propeller. The rotor is installed at the top of the middle part of the fuselage through a rotor shaft, and a clutch is arranged between the rotor and a power system and / or a transmission system matched with the fuselage, so as to be controlled to be disconnected or to transmit power to the rotor. The steering controller comprises a fixed base and a rotating base, and each of the nose and the tail has a set of the rotating base. The propeller is provided with two propellers which are respectively installed on the rotating bases of the nose and the tail, and are controlled to rotate with the rotating bases relative to the fixed base. The force couple formed by the front and rear thrust vectors is used to balance the reverse torque brought by the rotor. When the propeller is coaxial with the middle axis of the fuselage, the wind area of the single propeller obtains double thrust. The application can improve the energy utilization rate, improve the carrying capacity, improve the flight safety performance and obtain a longer hovering time.

The application discloses a vertical take-off and landing fixed-wing aircraft based on thrust vector nozzles, which comprises four engines, four thrust vector nozzles, a wing, a fuselage, a T-shaped tail wing and a support; four sets of power devices adopt a four-point isosceles trapezoidal symmetrical layout, and front and rear power devices are symmetrically arranged about the gravity center of the whole machine. The transverse spacing of the front power device is 2.5-3 times that of the rear power device, the spanwise projection is located at 40%-60% of the wing span length, and the height is matched with the wing leading edge to realize jet flow lift increase; the height and horizontal position of the rear power device are optimized to ensure stable air intake. The thrust vector nozzle takes the horizontal axis of the fuselage as the 0° reference, the vector angle adjustment range is not less than -95°-+15°, and the hovering, mode transition and steady switching of the flat flight are realized through differential adjustment. The application cancels the tilting mechanism, reduces the structural dead weight, reduces the aerodynamic interference, and improves the cruising speed and flight safety.

This invention relates to a dual-duct area independently adjustable circular-to-square two-dimensional vector nozzle, belonging to the field of aero-engine technology. The nozzle includes a circular-to-square cylindrical body, a main duct and a second duct adjustment vane system, a heat shield assembly, and an actuation mechanism. The second duct airflow channel, formed by the circular-to-square cylindrical body and the heat shield, has a circular-to-square cross-section transition. The main duct airflow passes through the central cavity enclosed by the heat shield. A rocker arm-actuator mechanism independently drives the outer duct adjustment vanes to adjust the second duct area, while the main duct adjustment vanes control the throat area, exit area, and thrust vector. The low-temperature airflow from the second duct cools the heat shield. This invention integrates independently adjustable dual duct area, circular-to-square cross-section transition, and two-dimensional vector function, offering advantages such as compact structure, good thermal protection performance, and high adjustment precision.

The application discloses a large vertical axis fan wind tunnel scale model blade aerodynamic optimization design method based on a DMST theory, and comprises the following steps: determining scale parameters according to wind tunnel test similarity criteria; selecting an optimized airfoil with matched aerodynamic characteristics under low Reynolds number based on the lift-drag ratio characteristics of a prototype blade; constructing an aerodynamic performance model based on a double disk multi-flow management theory, calculating the theoretical thrust coefficient of the prototype and the optimized airfoil, and performing matching verification; carrying out a force-measuring and pressure-measuring test in a wind tunnel, stripping the pure thrust of the blade by subtracting the total thrust of the whole machine from the thrust vector of the tower column; and comparing and verifying the aerodynamic load matching degree by comparing the measured thrust coefficient with the theoretical thrust coefficient. The application combines airfoil optimization, DMST theory verification and wind tunnel test stripping verification, effectively eliminates the Reynolds number effect in the scale test, realizes high-precision matching of the aerodynamic load of the vertical axis fan scale model blade, and improves the reliability of the wind tunnel test data.

This invention discloses a method for measuring the vector angle of a thrust vector nozzle, comprising the following steps: S1, acquiring a high-speed schlieren image of the thrust vector nozzle wake to obtain an original grayscale image; S2, obtaining a preprocessed image and a set of coordinate points representing the main boundary of the wake; S3, obtaining the coordinate range of a first selected region and a second selected region; S4, filtering out a first set of edge points located within the coordinate range of the first selected region and a second set of edge points located within the coordinate range of the second selected region; S5, performing linear fitting on the first set of edge points to obtain a first fitted line, and performing linear fitting on the second set of edge points to obtain a second fitted line; S6, calculating the angle bisector of the two lines to obtain the equation of the angle bisector; S7, outputting the thrust vector angle. This invention enables the direct acquisition of the nozzle wake deflection angle based on a high-speed schlieren image in the measurement of the thrust vector nozzle wake deflection angle.

The jet-based ducted fan fluid thrust vector propulsion system belongs to the field of aviation power technology, and the system comprises an air inlet, a rotor, a stator and a tail nozzle arranged in series along an axis, and a duct flow channel is formed inside; a plurality of jet exciters in annular array distribution are embedded in the inner wall surface of the tail nozzle expansion section. The jet exciter is composed of a vibrating diaphragm and a resonance cavity, and an external control system outputs a high-frequency alternating signal to drive the vibrating diaphragm to vibrate at a high frequency, so that the gas in the cavity is periodically sucked and sprayed, forming a high-speed jet with zero net mass flow. The jet injects energy into the main flow boundary layer, induces the main flow to deflect based on the Coanda effect, and realizes omnidirectional thrust vector control. The present application does not need a mechanical deflection rudder surface and an external air source pipeline, has the advantages of compact structure, light weight, response without delay, low energy loss, and is suitable for electric vertical take-off and landing aircraft and tilting ducted fan propulsion systems.

The application discloses a gas path assembly for a thrust vector adjusting mechanism, comprising: fixed flanges, two of which are arranged, wherein the upper fixed flange is connected with the upper framework of the thrust vector adjusting mechanism, and the lower fixed flange is connected with the lower framework of the thrust vector adjusting mechanism; an inner pipeline and an outer pipeline, wherein the inner pipeline and the outer pipeline penetrate through the two fixed flanges, the region between the fixed flanges is designed in a coaxial spiral shape, and the inner pipeline is arranged on the inner side of the outer pipeline; a fixed terminal, which is arranged between the outermost spiral segment and the fixed flange, one end of the fixed terminal is connected with the fixed flange, and the other end of the fixed terminal is connected with the inner pipeline and the outer pipeline; and a fixed clamp, which is clamped on the inner pipeline and the outer pipeline of each spiral segment and is arranged in a plurality of intervals along the circumference of each spiral segment. The gas path assembly has the characteristics of large flexibility and small deformation resistance, and can effectively avoid the pipeline resonance phenomenon.

This invention relates to the field of space electric propulsion technology, and particularly to a method for refined thruster allocation in an electric propulsion system based on thrust vector parameters. The method includes: for each electric thruster, determining the first and second angles between the thrust vector of the current electric thruster and the coordinate system of the entire satellite when the thrust vector points towards the center of mass of the entire satellite, based on the thrust vector parameters of the current electric thruster and the transformation model between the thrust vector of the electric thruster and the coordinate system of the entire satellite; determining the propellant consumption for maintaining north-south position using the current electric thruster, based on the specific impulse of the current electric thruster and the first and second angles between the thrust vector of the current electric thruster and the coordinate system of the entire satellite when the thrust vector points towards the center of mass of the entire satellite; and sorting all the electric thrusters to be allocated according to their propellant consumption based on the propellant consumption of each electric thruster to identify and allocate the target electric thrusters, thereby reducing the propellant load of the electric propulsion system and improving the overall payload capacity of the satellite.

This invention relates to a vector-hybrid multi-rotor unmanned aerial vehicle (UAV) and its energy management and control method, belonging to the field of UAV technology. It includes: main rotor power systems and thrust vectoring power systems mounted on the left and right wings of the fuselage; a vertical tail on the rear of the fuselage; main rotor power systems mounted aft and forward on the wings; and thrust vectoring power systems mounted on the outer ends of the wings. It adopts a controlless design. The main rotors of the main rotor power systems directly generate pitch and roll control torques using a differential lift control mechanism. The thrust vectoring power system provides vector thrust through differential tilt, forming a redundant control system of "four rotors + thrust vectoring". Combined with a full-cycle intelligent energy dynamic optimization and control system, it achieves a minimalist configuration and ultra-high reliability, breakthrough energy efficiency and balanced performance across all operating conditions, intelligent integrated control, and strong anti-interference capabilities.

A two-dimensional gimbaled propeller produces a vector thrust. A directional propeller produces a two-dimensional propulsion thrust vector without producing adverse moments or translational forces. By directing the vector through the aerodynamic center of the propeller, the forces required to control the propulsion vector are minimized, decoupled from the power source that is delivered to the propeller through a drive shaft with a fixed orientation.

The patent is a kind of ring cluster plug engine layout scheme fusing multiple unit solid-liquid combustion chamber, which uses liquid propellant supply system to adjust the flow of multiple unit combustion chamber, has thrust regulation, thrust vector and multiple starting ability, and comprises liquid propellant, storage tank, storage tank valve, storage tank pipeline, electric pump, power supply and control module, plug cone, post-pump pipeline, flange, inner nozzle, combustion chamber, solid charge, injector, ignition device, combustion chamber pipeline, combustion chamber pipeline valve and liquid collecting ring. The electric pump, post-pump valve and combustion chamber pipeline valve work cooperatively to adjust the valve opening, change the liquid propellant flow into the combustion chamber, and realize the nozzle thrust regulation; the inner nozzles are uniformly arranged along the plug cone in a ring direction, each inner nozzle corresponds to a combustion chamber and a combustion chamber pipeline, the combustion chamber pipeline valve controls the opening, adjusts the combustion chamber pipeline valve to change the flow field of the plug nozzle engine, generates lateral force, and realizes the engine thrust vector; the liquid propellant is injected into the combustion chamber multiple times, the mixed solid-liquid propellant is ignited by the ignition device, and the nozzle realizes multiple start.

The application provides a satellite attitude control method and device, electronic equipment and readable storage medium. The method comprises the following steps: establishing a center-of-mass offset calculation model of the system center-of-mass position changing with the residual fuel mass of different tanks according to the comprehensive center-of-mass position obtained by superimposing the dry mass center-of-mass position and the initial center-of-mass deviation; establishing a fuel uneven discharge model of different tanks according to different initial fuel masses, nominal flow rates and uneven discharge influence factors of different tanks; identifying a target working condition from a plurality of preset working conditions according to a target initial center-of-mass deviation and target uneven discharge influence factors of different tanks; establishing a coupling disturbance torque model of the 490N engine, and substituting the thrust vector detection data into the coupling disturbance torque model to obtain the current orbit disturbance torque in real time; and dynamically controlling at least one thruster group for attitude control during on-orbit control according to the target working condition and the current orbit disturbance torque.

This invention provides a ducted passive air bleed structure and aircraft based on a micro-pore array, relating to the field of aircraft technology. The ducted passive air bleed structure includes a duct body and a downstream nozzle section; an air bleed channel is provided within the duct wall, connecting an array of inlet micro-pores at the lip to an array of outlet micro-pores offset towards the inner side of the nozzle in the nozzle junction area. This structure is purely passive, with no moving parts and zero power consumption, relying on the natural airflow redistribution driven by the pressure difference inside and outside the duct under flight conditions: during hovering / takeoff, it enhances lip suction to suppress backflow and separation; during cruise, it improves boundary layer control and jet mixing inside the nozzle, enhancing thrust vector efficiency and total pressure recovery. The micro-pore array design significantly enhances pressure difference response sensitivity, stress dispersion, acoustic vibration suppression, and improves tolerance tolerance and mass production consistency; the fully rigid structure completely avoids jamming risks, significantly improving long-term reliability and flight safety margins, and achieving a balanced optimization between propulsion efficiency, aerodynamic stability, lightweight design, and operational economy.

A dynamic modeling method for a quadrotor-turbojet hybrid unmanned aerial vehicle (UAV) is presented, belonging to the field of UAV dynamic modeling technology. The method includes establishing coordinate systems: an inertial coordinate system, a body coordinate system, and a turbojet engine coordinate system; defining the turbojet engine attitude angles; establishing coordinate transformation relationships; calculating the system's time-varying moment of inertia; establishing a quadrotor dynamic model, calculating the force and torque vectors generated by the four rotors based on their positions and dynamic parameters; establishing a turbojet engine dynamic model, calculating the turbojet engine's thrust vector, eccentric torque, anti-torque, and gyroscopic torque; establishing complete time-varying dynamic equations, including translational and rotational dynamic equations; establishing incremental comparative analysis, defining the increments of moment of inertia, torque, and thrust; and establishing an incremental comparison relationship between the hybrid power system and the original quadrotor system. Experiments verify the necessity of establishing the complete time-varying dynamic model presented in this paper.

The application provides a small ship anchoring positioning device, comprising a jet device, the jet device comprises at least three nozzle assemblies, the nozzle assembly comprises a motor, a motor shaft, a flow guide cover arranged on the motor for guiding water flow, a nozzle opening arranged at the end of the flow guide cover, a plurality of openings arranged on the flow guide cover, a flow guide core arranged on the motor shaft and a propeller; when the propeller rotates forward, water flows into the nozzle opening from the plurality of openings and is sprayed out in the form of a water column to form a reverse thrust vector; when the propeller reverses, water is sucked into the nozzle opening and sprayed out from the plurality of openings to form a pulling force vector, and the resultant force vector formed by the reverse thrust vector and the pulling force vector is used for controlling the ship; the jet device is fixedly connected with the ship and does not have relative rotation. The application uses the resultant force vector of the thrust or pulling force of the jet water column to control the anchoring and positioning of the ship, and the speed of responding to and executing instructions and obtaining results is fast.

The application belongs to the field of aircraft air intake and exhaust system design, and particularly relates to a multi-degree-of-freedom aerodynamic vector nozzle integrated design structure with an aircraft rear body. The structure comprises: a double-throat aerodynamic thrust vector nozzle, and the double-throat aerodynamic thrust vector nozzle is arranged on the aircraft rear body through a tail cover. The double-throat aerodynamic thrust vector nozzle comprises an inlet converging section, an expansion section and an outlet converging section connected in sequence. The inlet converging section is arranged with a plurality of secondary flow channels, each of which is provided with a valve for controlling the opening and closing of the channel. The attitude control of the aircraft is realized by differential control of the secondary flow channels. The outlet converging section is in an elliptical shape, and the outlet converging section is provided with a driving mechanism for adjusting the outlet area. The driving mechanism is used to adjust the size of the outlet area to match the flight working state. The tail end of the tail cover is in an elliptical shape, and the tail cover and the outlet converging section are designed in a transition and fusion manner.

The application discloses a binary plug nozzle with a two-stage adjusting plate structure and an adjusting method thereof, and belongs to the technical field of space propulsion systems, and aims to solve the problem of strong coupling of the flow rate and the area ratio of an existing adjusting mechanism. The nozzle comprises a first exhaust passage and a second exhaust passage, and a common plug cone is arranged between the two exhaust passages. An adjusting system is independently arranged in each exhaust passage and comprises a converging adjusting plate and a diverging adjusting plate. The converging adjusting plate is used for adjusting the throat cross-sectional area. In the flow direction, the gas inlet end of the diverging adjusting plate is rotationally connected with the gas outlet end of the converging adjusting plate. The diverging adjusting plate is configured to move in linkage with the converging adjusting plate and can independently rotate around the rotation shaft of the gas inlet end of the diverging adjusting plate relative to the converging adjusting plate, so as to independently adjust the outlet cross-sectional area. The application realizes mechanical decoupling of the flow rate and the nozzle area ratio, and improves the wide-working-condition propulsion efficiency and the thrust vector control capability.

This invention discloses a passive fluid thrust vectoring nozzle and a method for real-time sensing of jet vector characteristics. The passive fluid thrust vectoring nozzle includes an engine exhaust outlet, sidewalls, a Coanda wall, a wall pressure sensor, a jet total pressure sensor, a jet static pressure sensor, a temperature sensor, an ambient pressure sensor, and a force vector angle calculation device. The sidewalls are fixedly installed on both sides of the engine exhaust outlet. The Coanda wall includes a first Coanda wall and a second Coanda wall, both fixedly connected to the sidewalls. The cross-section of the first Coanda wall and the engine exhaust outlet has a certain angle, and the first and second Coanda walls are mirror images of each other. The passive fluid thrust vectoring nozzle and the method for real-time sensing of jet vector characteristics disclosed in this invention improve the vector control performance of aircraft, enhance flight stability and safety, and can further promote the practical application of fluid thrust vectoring nozzles.