4results about How to "Increase flight speed" patented technology

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 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.