18 results about "Turbojet" patented technology

The unmanned wheeled vehicle, the control method and the control system thereof can assist the unmanned wheeled vehicle to overcome the obstacle and get rid of the predicament when the unmanned wheeled vehicle is trapped by the obstacle, thereby improving the adaptability of the unmanned wheeled vehicle to the complex terrain and improving the maneuverability of the unmanned wheeled vehicle. The unmanned wheeled vehicle comprises an unmanned vehicle main body structure, an auxiliary power system connected with the unmanned vehicle main body structure and configured to assist the unmanned vehicle main body structure to overcome the obstacle, wherein the auxiliary power system comprises a turbojet system, an unmanned vehicle state detection system configured to detect the state of the unmanned vehicle main body structure, and a control system electrically connected with the unmanned vehicle state detection system and the auxiliary power system and configured to control the auxiliary power system according to the state detection result of the unmanned vehicle state detection system.

This invention relates to the field of underground coal mining technology and discloses an explosion-proof high-energy dynamic current power generation device for underground coal mines based on non-contact turbojet technology. The device includes a pipeline, with a support frame fixedly connected to the inner ring of the pipeline. A transmission rod is rotatably connected to the inner ring of the support frame, with one end fixedly connected to a housing. A main rotor is mounted on the other end of the transmission rod. A support plate is fixedly connected to one side of the inner ring of the pipeline, and a generator is fixedly connected to one side of the outer wall of the support plate. An active bevel gear is connected and fixedly attached to the input end of the generator. Based on wind power meter readings, an electric push rod is used to disengage the corresponding main rotor from the slave rotor. Compressed air inside the pipeline then drives the housing to rotate, generating electricity. If the wind power meter reading is insufficient, a branch pipe is opened to output water from a power waterwheel, which then drives the waterwheel to rotate, generating electricity. This allows for flexible switching based on actual conditions.

The application discloses a hyperplane climbing track group intelligent optimization method, which comprises the following steps: constructing a hyperplane climbing section dynamics equation, and obtaining to-be-optimized parameters in the hyperplane climbing section dynamics equation; designing a hierarchical cost function considering multiple constraints and turbojet, subsonic ramjet and supersonic ramjet three power mode switching Mach numbers; and optimizing the cost function through a chicken swarm algorithm, thereby completing the hyperplane climbing track group optimization. The hyperplane climbing track parameter optimization is performed through the improved chicken swarm algorithm, the suitable power mode switching Mach number is selected while the complex constraints of the hyperplane climbing section are met, the climbing scheme capable of significantly shortening the climbing time and total fuel consumption is obtained, and the problem that the track is difficult to optimize under the hyperplane cross-power mode and long-time window climbing condition is solved.

1. Name of the product in this design: Thrust Test Platform for Turbojet and EDF Engines. 2. Purpose of this design: This design is used to measure the thrust ratio of the EDF engine thrust test platform. 3. The key design feature of this product is its shape. 4. The image or photograph that best illustrates the design's key points: 3D view 1.

The application relates to the field of general structure design of an aero-engine, and discloses an aero-engine duct airflow distribution mechanism and a control method thereof. The bleed air structure and the flow path control structure are integrated in the rotating casing and the support plate structure of the inner and outer ducts. In the turbofan mode, the leading edge and the trailing edge of the corresponding support plate of the outer duct and the inner duct are matched, so that the duct flow is smooth. In the turbojet mode, the inner and outer duct flow passages are blocked, and the outer duct airflow is guided into the inner duct. The application can support the demand that the variable flow path aero-engine works in the turbofan engine mode at low flight speed and works in the turbojet mode at high flight speed, widen the flight speed domain of the conventional turbofan engine, realize the consideration of high economy at low speed and large thrust at high speed, and effectively reduce the structural complexity of the engine.

The invention discloses a hybrid electric engine using electric supercharging and indirect cooling. The engine is based on a turbojet or turbofan core engine. An electric supercharging indirect cooling device and a turbine power generation device are additionally arranged on a core engine and are installed at the front end and the rear end of the engine respectively. The electric supercharging intercooling device comprises an electric supercharging channel with a contracted flow channel, an electric driving fan is used in the channel for supercharging, the fan is a wide-pressure-ratio working fan, a motor for driving the fan is located in the center of the flow channel at the rear end of the fan, the flow channel is narrowed after the motor passes through the electric supercharging fan, and a compact intercooler is installed on the rear portion of the flow channel. A flange is arranged at the casing behind the intercooler and is connected with a shell of the core engine; the rear-end turbine power generation device is connected with an outlet of the core engine through a flange, the rear-end device is provided with an adjusting device and divides a duct into an inner duct and an outer duct, the inner duct is provided with a turbine, the turbine is connected with a power generator through a force transmission shaft perpendicular to the direction of a flow channel after passing through a direction changing device, and the power generator is installed outside the flow channel of the device.

The application discloses an aero-engine hot-end component full-life-cycle management method and system, and belongs to the technical field of aero-engines.The system constructs a full-life-cycle closed loop system of material gene optimization-precision forming process-service health monitoring-life prediction and active repair, can realize service life improvement of more than 200% of the aero-engine hot-end component, and improves the production yield rate from the conventional 60% in the industry to more than 90%.The application fills the core short board of short life, poor reliability and low yield rate of the aero-engine hot-end component in China, breaks through the core technical bottleneck of the "industrial crown pearl" of the aero-engine, and is 100% domestically produced and controllable in material and process, and can be widely applied to scenes such as army armed helicopter turboshaft engines, military unmanned aircraft turbojet / turbofan engines and the like.

1. Name of the product in this design: Central Controller. 2. Purpose of this design: To control the operation of a turbojet snowplow and to display real-time dynamic information feedback from the turbojet snowplow. 3. The key design feature of this product is its shape. 4. The image or photograph that best illustrates the design's key points: a 3D model.

1. Name of the designed product: propeller (turbojet). 2. Use of the designed product: hand propeller for toy kayak. 3. Design points of the designed product: in shape. 4. Picture or photo best indicating the design points: perspective view.

The invention provides a deep learning-based turbojet manned aircraft visual positioning method and system, and belongs to the field of aircraft visual positioning. The invention aims to solve the problems of motion blurring of a visual camera and IMU noise time-varying caused by vibration of dozens of or hundreds of Hertz and strong maneuverability of a turbojet aircraft due to acceleration and deceleration and jet coupling of the turbojet aircraft. The method comprises the following steps: extracting point-line features from a left-eye visual image based on a neural network model of point-line joint feature detection, carrying out inter-frame point-line feature matching, judging whether the left-eye visual image is a key frame or not, if so, inputting a right-eye image, and carrying out binocular feature stereo matching; and if not, carrying out position and attitude calculation on the turbojet manned aircraft, and then constructing a factor graph for optimization. According to the method, the binocular image is only adopted in the key frame for estimation so as to ensure the algorithm real-time performance of the turbojet manned aircraft, and estimation is carried out based on the point-line features so as to ensure the high-speed robustness of the turbojet manned aircraft.

1. Name of the designed product: toy (turbojet fire engine 8693). 2. Use of the designed product: for toys. 3. Design points of the designed product: in shape. 4. Picture or photo best indicating the design points: perspective view.

The invention relates to a turbomachine turbine comprising a casing (12) carrying a distributor (13) extending circumferentially around an axial direction, in which: – this distributor is formed of several bladed sectors (22, 23, 24) each comprising a radially external platform (26, 27, 28) and a radially internal platform with several blades (14) extending radially from the internal platform to the external platform (26, 27, 28); – the casing (12) has an internal groove (29) of revolution, with several distinct ring sectors (32, 33, 34) each engaged in this internal groove (29) and extending radially towards the interior of the casing (12); – each ring sector (32, 33, 34) axially blocks at least one bladed sector (22, 23, 24). Figure for the summary: Figure 5

A propulsion system comprising a turbojet with a fan casing and a central casing, a pylon with an upper spar, a front wall and on either side of a vertical median plane, a fitting rigidly fixed to the rigid structure, a cylindrical pin as one with the fan casing and inserted in a hole of the upper spar, a shackle with at the vertical median plane, an upper articulation between the shackle and the front wall and on either side of the vertical median plane, a lower articulation between the shackle and the central casing, and two reaction rods disposed on either side of the median plane, where each rod is articulated, at a front end, on the central casing, and, at rear end, on the fitting.

An injector for a de-icing device for an air intake of an aircraft turbojet nacelle. The injector including a peripheral member internally defining a passage duct. The peripheral member including a peripheral mouth configured to inject a peripheral hot air flow so as to circulate a flow of fresh air in the passage duct from upstream to downstream. The peripheral member including an inner guide wall located downstream of the peripheral mouth. The peripheral member including a plurality of members for rotating the hot air flow during the injection thereof.

The invention provides a high-speed starter generator rotating shaft structure with an energy storage and self-starting structure, which belongs to the field of thermal power devices and comprises a controllable power coupler, a magnetic suspension bearing, a high-speed permanent magnet motor, a turbojet, a heat exchanger and a controller system. The turbojet drives the permanent magnet motor through the transmission shaft, and the motor outputs electric energy. When the control system is switched to an energy storage state, the controllable power coupler is rapidly disconnected, the driving shaft is not connected with the transmission shaft any more, a high-speed motor rotor maintains short-time high-speed idling by means of original kinetic energy, next-time rapid connection and self-starting are facilitated, a magnetic suspension bearing is used in the high-speed motor to rotate a rotating shaft, axial and radial active adjustment of the motor can be achieved, and the service life of the motor is prolonged. And the heat exchanger is arranged at the tail part of the turbojet, so that the heat of the combustion tail gas can be fully utilized, and the power generation efficiency of the high-speed starting generator is improved.

1. The name of the design product: multifunctional turbojet snowplow. 2. The use of the design product: for snow removal work on roads. 3. The design points of the design product: in shape. 4. The picture or photo that best shows the design points: perspective view.

This invention relates to the field of aircraft testing technology and discloses a turbojet aircraft testing platform, comprising a testing platform, a connecting plate fixedly connected to the upper surface of the testing platform, a rotating shaft rotatably connected to the outer surface of the connecting plate, a rotating plate fixedly connected to the end of the rotating shaft away from the connecting plate, a reduction gearbox fixedly connected to the upper surface of the testing platform, an input shaft of the reduction gearbox fixedly connected to the rotating plate, an output shaft of the reduction gearbox fixedly connected to a central shaft, a mounting frame fixedly connected to the outer circumference of the central shaft, a six-axis force gauge fixedly connected to the top of the mounting frame, and an aircraft support fixedly connected to the top of the six-axis force gauge. This turbojet aircraft testing platform effectively solves the problem in existing technologies where, after the fuel pipe is bent, the fuel flow resistance increases, directly affecting the engine's fuel supply stability and power output characteristics, and reducing the accuracy of performance testing.

The application provides graphene heat-conducting fiber and intelligent flight clothing powered by micro turbojet cluster, and relates to the field of flight clothing.The graphene heat-conducting fiber and intelligent flight clothing powered by micro turbojet cluster include flight clothing, the upper end of the flight clothing is provided with a flight helmet, the rear end of the flight clothing is provided with a back power backpack, the lower end of the flight clothing is provided with flight trousers, the lower end of the flight trousers is provided with flight protective boots, the two sides of the back power backpack are provided with arm-mounted vector thrusters, the middle part of the front end of the flight clothing is provided with an intelligent flight control display panel, and the outer sides of the two sides of the flight clothing are provided with arm-mounted controls.In the application, the whole integration of protection, power, intelligent control and ergonomics is realized, the components form an organic linkage flight system, the full-dimension coverage design from the head to the feet eliminates the function breakpoints of traditional flight equipment, the protection, control and power supply in the flight process form a closed loop, and the overall use safety and adaptability are improved.