19results about How to "Reduce flight resistance" patented technology

The invention discloses an aircraft folding type propeller mechanism and an aircraft, the aircraft folding type propeller mechanism comprises a rotating shaft, a driving part, a first propeller and a second propeller; the driving piece is connected with one end of the rotating shaft; the first propeller comprises a first propeller hub and a first propeller blade which are connected with each other, the first propeller hub is fixedly connected to the rotating shaft, a thrust groove is formed in the side, away from the driving part, of the first propeller hub, and a first thrust surface which is obliquely arranged is arranged at the bottom of the thrust groove; the second propeller comprises a second propeller hub and a second propeller blade which are connected, the second propeller hub is movably arranged on the rotating shaft in a sleeving mode and located on the side, away from the driving piece, of the first propeller hub, and a thrust block extending into the thrust groove is arranged on the side, facing the first propeller hub, of the second propeller hub in a protruding mode; and the thrust blocks are matched with the thrust grooves, so that the second paddles are in a folded state or an unfolded state relative to the first paddles. According to the folding propeller mechanism of the aircraft, the resistance of the aircraft in the flight process is reduced, and the flight performance of the aircraft is improved.

The invention belongs to the technical field of design of turbo-ramjet combination engines, and particularly relates to a turbo-ramjet combination engine and a control method thereof. According to the design, a complex outer turbine channel is separated from a smooth ramjet channel, and an afterburner and a ramjet combustion chamber are designed to share the space; the designed center stamping channel has multiple functions of a turbine engine stator force bearing frame, a center deflation channel, a subsonic combustion stamping rectification channel, a scramjet channel and the like. Self-adaptive switching of four working modes including a turbine engine conventional working mode, a turbine engine center deflation working mode, a subsonic combustion stamping working mode and a scramjet working mode is achieved, the space of a center stamping channel is utilized to the maximum extent, the working speed range of the turbine modes is widened, the cross sectional area is greatly reduced, the flight resistance is effectively reduced, and the service life of the turbine engine is prolonged. And wide-speed-range work with the Mach number of 0-7 is realized.

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.

An aircraft fuel tank inerting system comprises: an inerting gas separation device (100), the inerting gas separation device (100) comprising a to-be-separated gas inlet (110) and an inerting gas outlet (120); the aircraft fuel tank inerting system comprises an inerting gas separation device (100), an inerting gas outlet (120) and an inerting gas conveying pipeline (200), the inerting gas conveying pipeline (200) is in fluid connection with the inerting gas outlet (120) and used for introducing the inerting gas produced by the inerting gas separation device (100) into an aircraft fuel tank (300), and the aircraft fuel tank inerting system further comprises an injection device and a control device, and the injection device is configured to inject the cabin bleed air (420) by taking the engine bleed air (410) as an active flow and then convey the obtained air to the to-be-separated air inlet (110). According to the aircraft fuel tank inerting system, two strands of gas are introduced from the passenger cabin and the engine, and the jet pump is arranged on the upstream of the system, so that the temperature / pressure adjustment of engine bleed gas and passenger cabin bleed gas is realized at lower cost.

The invention relates to the technical field of unmanned aerial vehicle structure design, in particular to an unmanned aerial vehicle self-adaptive undercarriage and adjusting system. The undercarriage assembly is arranged at the end of the unmanned aerial vehicle and comprises a storage box fixed to the end of the unmanned aerial vehicle, and a servo motor and a turnover plate are arranged in the storage box; comprehensive information is provided for the control module through the sensor module, the control module accurately controls a servo motor, a driving motor and an adjusting motor through a strategy based on feedback of the sensor module, the turnover plate is controlled to move in the storage box, the turnover plate is stored in the storage box during take-off, flight resistance is reduced, the overall size is reduced during transportation, and transportation is facilitated. The height of a driving motor and supporting legs in the supporting component can be adjusted, stability is guaranteed through cooperation with a limiting structure, and an adjusting piece can enable a disc to adapt to concave-convex ground and is matched with the supporting legs to keep the horizontal state of the unmanned aerial vehicle.

The present invention discloses a detachment device for an external hydrogen storage tank of a drone, a drone and a detachment method. The detachment device for an external hydrogen storage tank of a drone comprises a mounting seat, a disconnection assembly and a pipeline lock subassembly; the disconnection assembly comprises the disconnection drive connected to the mounting seat and a disconnection piece connected to the output end of the disconnection drive, and the disconnection drive can drive the disconnection piece to connect and disconnect from the external hydrogen storage tank; the pipeline lock subassembly comprises a lock sub-drive connected to the mounting seat and a lock sub-device connected to the output end of the lock sub-drive, and the lock sub-drive can drive the lock sub-device to lock and separate the pipeline joint of the external hydrogen storage tank. The disconnection assembly and pipeline lock subassembly of the present invention thus realize the loosening of the freedom of the external hydrogen storage tank in the front and back and up and down directions, and the external hydrogen storage tank can be dropped in a free fall manner under the action of its own gravity, which greatly reduces the overall deadweight and flight resistance of the drone.

The invention discloses a traffic infrastructure inspection unmanned aerial vehicle and a system thereof, and relates to the technical field of inspection unmanned aerial vehicles, the traffic infrastructure inspection unmanned aerial vehicle comprises a driving integrated machine body, a regulation and control assembly is installed in the driving integrated machine body, and the side end of the regulation and control assembly is fixedly connected with a side wing regulation and control assembly; according to the unmanned aerial vehicle, under the cooperation of the side wing regulation and control assembly and the regulation and control assembly, the light high-strength auxiliary wing structure capable of reducing wind resistance is adopted, so that the unmanned aerial vehicle is effectively kept in a more stable flight attitude, the image stability and the data accuracy during inspection are improved, the flight performance of the unmanned aerial vehicle is adjusted according to actual requirements in the flight process, and the unmanned aerial vehicle is more stable in flight. When long-distance inspection is carried out in an open zone, the regulation and control assembly can drive the side wing regulation and control assembly to retract, so that the overall flight resistance is reduced, energy is saved, the flight efficiency is improved, the situation that the unmanned aerial vehicle is limited due to the fact that the state of the unmanned aerial vehicle is affected by the construction operation environment is reduced, and the detection effect of the unmanned aerial vehicle is guaranteed.

The invention provides a stealth patch capable of reducing resistance and removing ice, a preparation method of the stealth patch and an aircraft. The stealth patch capable of reducing resistance and removing ice comprises a base body layer, a heating layer and a super-smooth resistance reducing layer which are sequentially arranged in a stacked mode from bottom to top. Wherein the heating layer is composed of a glass fiber cloth layer connected to the base body layer and a graphene layer distributed on the glass fiber cloth layer in a network-shaped island mode, the super-slippery resistance reduction layer is composed of a polydimethylsiloxane coating and silicone oil injected into the polydimethylsiloxane coating, and a plurality of resistance reduction micro grooves are formed in the super-slippery resistance reduction layer at intervals. According to the invention, the functions of radar wave penetration, ice prevention / removal and resistance reduction can be realized, the device can be used in a severe environment, and the use requirements of civil and military aircrafts are met.

The invention discloses a stern room gas vane transmission system and a control method thereof, and relates to the technical field of aircraft flight, and the gas vane transmission system comprises an air vane and a gas vane which are arranged on a cabin section shell; an air rudder shaft of the air rudder penetrates through one end of the cabin section shell and is connected with a driving end of the steering engine; the air rudder is in transmission connection with the gas rudder through a transmission assembly; the gas vane is connected with the bottom of the cabin section shell through at least two separation pieces; the separating part has a first working state and a second working state; in the first working state, the separation piece keeps the connection between the gas vane and the cabin section shell; and in the second working state, the separation piece cuts off the connection between the gas vane and the cabin section shell, so that the gas vane is separated from the cabin section shell. The system can abandon the unnecessary weight of the gas vane for the aircraft after the solid engine of the aircraft finishes working, so that the range or other flight indexes of the aircraft are improved.

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 present application belongs to the field of air flow, and relates to a blowing flap of a fixed-axle sub flap adaptive spoiler. The blowing flap comprises a fixed wing surface, a fixed rotating shaft, a main flap, a sub flap, a main flap blowing gap, a sub flap blowing gap, a spoiler rotating shaft and a spoiler. The main flap and the sub flap are downwardly deflected at a large angle, the spoiler is downwardly deflected to be attached to the upper surface of the sub flap, the blowing gaps on the sub flap and the main flap work in a certain blowing momentum coefficient matching relationship, the maximum lift coefficient of the aircraft is greatly improved, the lift-drag ratio is very high, and the super-circulation effect is realized.

The invention relates to an aviation dynamic differential pressure all-wing aircraft. An airfoil profile of the aircraft comprises an upper airfoil surface and a lower airfoil surface. The section lines of the airfoils are all composed of curves of a monotonically decreasing function from the front edge to the rear edge. The structure is simple, and when the lower wing surface does work on windward airflow, the flow speed is reduced, the static pressure intensity is increased, and upward thrust is generated; the upper airfoil does not do work, airflow flows back, static pressure is reduced, upward pulling force is generated by the airfoils, and therefore the double-airfoil lift airfoil profile with the upper airfoil and the lower airfoil simultaneously and consistently upward lift force is formed, the sum of the lift force of the two surfaces is larger than that of an existing single-face lift airfoil profile, and the airfoil efficiency is further improved by optimizing the lift-drag ratio. By adopting the wing section line and the spanwise line rear corner, shock waves are weakened to be low-sound-velocity object plane static pressure, damage of the shock waves is avoided, and the strong resistance effect is reduced.

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.