8results about How to "Increase flight speed" patented technology

The invention aims to provide an aircraft propulsion system which comprises an energy storage unit and a tail fan assembly, the energy storage unit is arranged in an aircraft body, the tail fan assembly is arranged at the tail of an aircraft, and the tail fan assembly comprises a first driving unit, a tail fan rotor and a tail fan stator. The first driving unit is electrically connected with the energy storage unit, the tail fan rotor is arranged on the periphery of the tail of the aircraft and is in transmission connection with the first driving unit, and the tail fan stator is arranged on the periphery of the tail of the aircraft. The tail fan stator is closer to the rear end of the aircraft than the tail fan rotor. By adopting the aircraft propulsion system, the propulsion efficiency of the existing aircraft can be improved, and the fuel consumption of the aircraft in the whole voyage can be reduced.

The propaganda display device belongs to the technical field of propaganda display, not only can passively display propaganda materials, but also can display learning conditions through the status bar arranged on the edge of the propaganda column, so that the learning conditions displayed in the status bar can be obtained, learning objects can select learning time and content, and the learning efficiency is improved. The display rack can send a learning site to the display rack, after receiving learning related information, the display rack can send a propaganda unmanned aerial vehicle to convey related learning materials and a projector with propaganda content in place for learning, and after learning is completed, the display rack can report the learning situation back to the display rack; and then the corresponding learning condition is updated through the status bar, so that the functions of supervising and conveying learning materials are added.

The embodiment of the application discloses a kind of wisdom morphing aircraft and morphing control method, including cabin body base and the skin structure covered in the outer surface of the cabin body base;The cabin body base includes first cabin body base and second cabin body base, and the second cabin body base is combined and fixed to the first cabin body base away from the vertex of the aircraft one end;Multiple first driving members are included between the skin structure and first cabin body base, and the first driving member is configured to drive the skin mechanism to change the shape of the wisdom morphing aircraft;Multiple second driving members are included between the skin structure and the second cabin body base, and the second driving member is configured to drive the skin structure to change the shape of the wisdom morphing aircraft.By corresponding setting skin structure in different cabin section of aircraft, the segmented regulation and control of the shape of aircraft body is realized, and the aerodynamic shape of aircraft is optimized, so that it can adapt to the flight requirements of different flight tasks.

The utility model discloses a kind of unmanned aerial vehicle for realizing vertical take-off and attitude control using small turbojet engine, small turbojet engine is installed at wing tip of wing, small turbojet engine is installed at the back of fuselage (or in front of fuselage) two sides;Small turbojet engine is made to produce upward thrust by vertical rotation 90 ° using turbine worm drive mechanism or motor with self-locking holding torque, and unmanned aerial vehicle vertical take-off is realized;Unmanned aerial vehicle has aileron installed at the trailing edge of left and right wing tips, and the differential deflection of aileron makes unmanned aerial vehicle tilt rotation around longitudinal axis, and the direction of thrust of small turbojet engine is deflected using turbine worm drive mechanism, to realize the flight state stabilization and flight attitude control of unmanned aerial vehicle, so that unmanned aerial vehicle has good maneuverability;Horizontal stabilizer and elevator are omitted, vertical stabilizer and rudder are omitted, so as to reduce flight resistance, which is conducive to improving the flight speed and effective load of unmanned aerial vehicle.

This disclosure provides an explosive spraying apparatus for boundary fluxing, including a spray gun, a powder channel, a main fuel and oxidizer channel, a secondary fuel channel, a secondary oxidizer channel, multiple secondary fuel supply holes, a secondary fuel supply pipe, and micro-flame holes. The second end of the spray gun is provided with a powder channel and a main fuel and oxidizer channel coaxially therewith. The secondary fuel channel and the secondary oxidizer channel are coaxially arranged around the side wall of the spray gun. Multiple secondary fuel supply holes penetrate and are arranged in an array on the wall between the secondary fuel channel and the secondary oxidizer channel, each secondary fuel supply hole correspondingly connected to the inlet of a secondary fuel supply pipe. Multiple micro-flame holes penetrate and are arranged in an array on the side wall of the spray gun, used to connect the spray gun and the secondary oxidizer channel. The outlet of each secondary fuel supply pipe extends into a corresponding micro-flame hole. By continuously heating the sprayed powder at the edge, the uniformity of the powder parameter distribution at the outlet is improved, thereby improving the coating quality.

The present application relates to a corrosion-resistant material and its preparation method and application. Among them, the preparation method of the corrosion-resistant material comprises: in a protective gas atmosphere, using plasma spraying, spraying NbMoTaW-based refractory high entropy alloy powder on the surface of the substrate to prepare a coating; the temperature of the substrate is 180°C to 200°C; the spraying distance of the plasma spraying is 80mm to 100mm, the spraying voltage is 78V to 80V, and the spraying current is 500A to 550A. Under the above-mentioned spraying parameters, the flying speed and temperature distribution of the high entropy alloy particles are relatively uniform, and the temperature of the flying particles is relatively high, ensuring the full melting of the high entropy alloy powder. During the spraying process, the temperature and flying speed of the flying particles are relatively high, which ensures that the particles hit the surface of the substrate at a high speed in a molten or semi-molten state, and evenly spread, cool and solidify on the surface of the substrate, stacking layer by layer, and then forming a refractory high entropy alloy coating with a thicker thickness and better corrosion resistance, so as to obtain a corrosion-resistant material with better corrosion resistance.

The application discloses a variable fixed-wing aircraft for an air-land hybrid robot and belongs to the technical field of air-land hybrid robots. The variable fixed-wing aircraft comprises an air-land hybrid robot intermediate body, a pair of front engine control devices and a variable back wing device. The front engine control device comprises a two-degree-of-freedom control mechanism and a front aero-engine. The variable back wing device comprises a foldable wing, a wing control lever and a rear aero-engine. The foldable wing comprises a main wing, a left aileron and a right aileron. The rear aero-engine is installed in the middle of the main wing. The front end of the wing control lever is connected with the air-land hybrid robot intermediate body through an X-axis rotary control lever front end servo motor. The rear end of the wing control lever is connected with the main wing through an X-axis rotary control lever rear end servo motor. The aircraft can be assembled and coupled with a humanoid robot body to form an air-land hybrid robot, and has the characteristics of high flight efficiency, low energy consumption and wide application scenarios.

The invention relates to the field of aerospace, and particularly discloses a spacecraft ejection launching system. By arranging the launching track, the three sealing valves, the vacuum pump, the ultra-fast sealing valve and the catapult vehicle, an operator can place a rocket on the catapult vehicle, the catapult vehicle transports the rocket into the double-sealing door section, the vacuum pump is operated to enable the interior of the double-sealing door section to be vacuum, and the second sealing valve is opened; the driving module drives the catapult vehicle and the rocket to accelerate in the linear acceleration track section, the launching angle is adjusted through the turning track section, then the catapult vehicle and the rocket are separated in the separation track section, the rocket enters the free flight track section to do free flight motion due to inertia, and the ultra-fast sealing valve is controlled to be fast opened and closed. The high vacuum degree in the launching track is maintained, it is guaranteed that the rocket can conduct vacuum flight in the launching track, the rocket has the flight speed large enough, the rocket launching quality is reduced, and meanwhile the carrying capacity of the rocket is improved.