9results about How to "Reduce flight resistance" patented technology

The utility model belongs to the technical field of flexible structure design, and particularly relates to a perimeter-variable fuselage frame structure which comprises sliding groove sections, sliding key sections, corrugated beams, height-variable supporting columns and length-variable supporting rods. The corrugated beams are arranged on the outer sides of the sliding key sections and the sliding groove sections and are provided with wave crest and wave trough structures; the sliding key sections and the sliding groove sections are located on the inner sides of the corrugated beams, arranged at intervals and distributed in a staggered mode. The corrugated beams, the sliding key sections and the sliding groove sections are all of arc-shaped structures, and wave crests and wave troughs of the corrugated beams are arranged in the radial direction of the arc-shaped structures; the sliding key section and the sliding groove section are mutually nested to form an arc-shaped supporting sliding way, and the wave trough of the corrugated beam slides on the arc-shaped supporting sliding way; the height-variable supporting column and the length-variable supporting rod are hinged to the two ends of the sliding key section respectively. The shape of the fuselage can be greatly changed, the large-size fuselage can provide a large space to carry more fuel, and the small-size fuselage is beneficial for reducing flight resistance and improving the fuel utilization rate.

This invention discloses a landing buffer device for unmanned aerial vehicles (UAVs), relating to the field of aviation equipment technology. By integrating the roller body and the sliding plate as two grounding structures onto the landing gear, the device can quickly switch operating modes according to ground conditions through the linkage of the piston cylinder and piston rod. On flat ground, the roller is used first to reduce gliding resistance, while on muddy or slippery ground, the sliding plate is used for grounding, effectively preventing roller jamming and enhancing all-terrain adaptability and landing safety. Simultaneously, the mechanical buffer composed of a second and third spring, combined with the hydraulic damping buffer composed of buffer components, forms a highly efficient double-layer energy-absorbing buffer structure, which to a certain extent alleviates the damage to the aircraft and equipment caused by landing impact, thus improving the landing safety of the UAV.

This invention discloses a variable center of gravity twin-arm aircraft with a rectified wing and its control method, belonging to the field of low-altitude unmanned aerial vehicle (UAV) technology. The aircraft has only two supporting arms, front and rear. The ends of the arms are equipped with fixed-pitch propeller power units without variable pitch structures. Each arm has an independently driven, fully movable rectified wing hinged below it. The aircraft has no external tail or various independent control surfaces. The rectified wing integrates multiple functions, including airflow rectification, counteracting propeller anti-torque, dynamically adjusting the aircraft's center of gravity, and outputting attitude torque. The hardware of this invention relies on the lift difference between the two propellers and the synchronous or differential deflection of the two wings to coordinate and control the flight attitude. The control method enables vertical takeoff and landing, forward and backward level flight, lateral translation, and stationary spin flight in all attitudes. This invention features fewer structural components and lower manufacturing costs. The streamlined wing effectively reduces aerodynamic drag and increases cruising speed. It avoids the drawbacks of complex pitch control mechanisms in helicopters and redundant frames in multi-rotor aircraft. It offers flexible vertical takeoff and landing capabilities and can be widely used in various fields such as aerial photography, plant protection, surveying and mapping, and low-altitude inspection. It solves the technical pain points of existing aircraft in achieving low cost, high speed, and omnidirectional maneuverability.

This invention provides an embedded electric tiltrotor drone laser power supply device, including a groove on the bottom surface of the drone. A laser charging plate is embedded in the groove and connected to the drone's battery. One end of the laser charging plate is the front end, the other end is the rear end, and the lower surface is the laser receiving end. The front end of the laser charging plate is rotatably mounted in the groove via a horizontal shaft perpendicular to the central axis of the tiltrotor drone. The rear end of the laser charging plate is mounted to the drone via a linkage structure driven by a motor, which rotates the laser charging plate downwards around the shaft. In this invention, the laser charging plate at any position can be adjusted to face the laser beam from the ground, improving the laser receiving effect of the laser charging plate, thereby improving the photoelectric conversion efficiency and the charging effect of the drone battery.

The utility model discloses an aircraft capable of being telescopically deformed, which comprises an aircraft and is characterized in that a telescopic bracket assembly is arranged on the aircraft, the telescopic bracket assembly comprises a carbon plate, a connecting rod, a steering engine assembly, a gear assembly, a fixed seat and a two-way connecting rod, the steering engine assembly is connected with the gear assembly, the fixed seat is arranged above the gear assembly, and the two-way connecting rod is connected with the carbon plate. The gear assembly is connected with the four two-way connecting rods, the four two-way connecting rods are arranged above the fixing base and are arranged in an equidistant and crossed mode, the ends of every two adjacent two-way connecting rods are connected with the carbon plates, and the gear assembly rotates to drive the two-way connecting rods to rotate, unfold or fold the connecting rods and the carbon plates at the ends of the connecting rods. The appearance structure of the aircraft is variable, when the aircraft is unfolded, the overall balance of the aircraft is kept, when the aircraft is completely unfolded, a stable protection frame is formed, flying paddles are protected against being impacted by foreign matter and damaged to a certain degree, when the aircraft is folded, the structural face is attached to the aircraft body to keep the streamline appearance, and flight resistance is reduced.

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.

The invention discloses an unmanned aerial vehicle with a camera assembly convenient to replace, and relates to the technical field of unmanned aerial vehicles, and the unmanned aerial vehicle comprises foot stools which are installed on the two sides of the lower portion of an unmanned aerial vehicle body and used for supporting. According to the unmanned aerial vehicle with the camera assembly convenient to replace, a bolt dismounting opening in the bottom faces the front of the unmanned aerial vehicle body through an electric push rod and a bearing frame, an operator can make direct contact with the dismounting opening from the front face conveniently, the sight of the operator is clearer through the position, the operation space is more sufficient, and the operator does not need to wind around other angles for dismounting; and meanwhile, the auxiliary mechanism and the traction mechanism operate at the same time, the supporting wings are adjusted to be in a downwards-inclined state from the horizontal position, the two sides of the unmanned aerial vehicle body are supported, the overturning risk caused by the unstable gravity center in the disassembling process is prevented, and the safety of the unmanned aerial vehicle is improved. Workers can conveniently and quickly disassemble and replace the camera assembly, and the replacement time is shortened.

The application discloses a non-rotation body warhead drag reduction method based on a von Karman curve, and comprises the following steps: S1, determining a non-rotation body warhead, a warhead section and a warhead vertex according to a flight speed, wherein a projection point of the warhead vertex at the warhead section falls on an intersection of the warhead section and a warhead symmetry plane; S2, selecting a key point located at an edge of the warhead section; S3, generating a von Karman curve on the warhead symmetry plane as a warhead contour generatrix, obtaining parameters required by a von Karman curve of a key point of a warhead connection section, and generating a von Karman curve group connecting the warhead vertex and the key point of the section; and S4, creating a plurality of planes perpendicular to the warhead symmetry plane, truncating the von Karman curve group, generating a multi-section curved surface, and closing the multi-section curved surfaces to form a solid warhead contour. The non-rotation body warhead drag reduction method based on the von Karman curve has the beneficial effects of reducing flight drag and improving flight stability.