30results about "Gliders" patented technology

The application discloses a design method of a high-maneuverability control characteristic gliding wave-riding aircraft, and the design method comprises the following steps: step one, selecting a conical wave-riding body as a basic configuration of the aircraft, wherein the wave-riding body comprises a fixed section aircraft body and variable side front edges located on the left and right sides of the fixed section aircraft body, the variable side front edges can be rotated into the fixed section aircraft body, the left and right variable side front edges are respectively denoted as a left variable side front edge and a right variable side front edge; step two, determining a front edge line of the wave-riding body; step three, determining the height and curvature of the upper surface of the wave-riding body; step four, determining the maximum distance from the upper surface of the wave-riding body to the lower surface of the fixed section aircraft body; and step five, designing the variable side front edges; the application greatly adjusts the lift-drag ratio of the wave-riding aircraft body, improves the utilization rate of the internal volume of the aircraft, and makes the wave-riding aircraft have comprehensive maneuvering characteristics of pitching, yawing and rolling by using a simple rotating deformation mechanism.

The steam ejection device applied to the glider comprises a flying runway, a steam tank and an ejection system, two sliding grooves are formed in the flying runway, the ejection system is arranged below the flying runway, the ejection system comprises a sliding shuttle and two guide steel pipes arranged in parallel, and the sliding shuttle is connected with the steam tank. A guide groove is formed in the guide steel pipe, an open groove is formed in the pipe wall of the guide steel pipe, one end of the guide steel pipe is connected with the steam tank through an air pipe, a hydraulic buffer groove is formed in the other end of the guide steel pipe, a steam valve is arranged on the air pipe, and a piston is arranged at the lower end of the sliding shuttle. The piston is in sliding fit with the guide groove, a connecting plate is arranged at the upper end of the sliding shuttle, and the connecting plate penetrates through the sliding groove and is connected with a front wheel of the glider through a connecting rod. The utility model relates to the technical field of space flight and aviation.

The application discloses a kind of aircraft structures with repeatable jumping and gliding function, it is related to the field of jumping glider aircraft.The application reduces the additional mass caused by increasing the jumping structure and effectively improves the jumping height of the glider.The aircraft includes a fuselage, a pair of wings and a wing membrane connected to the wings.The fuselage includes a head shell, a base shell and a plurality of carbon fiber rods connected between the two, a jumping drive assembly is provided between the head shell and the base shell for bending the carbon fiber rods, and a folding drive assembly is provided in the base shell for folding the wings.The application effectively improves the movement range of the glider and expands its application range.

The aircraft wing comprises a wing main body, an air door device is installed on the upper surface of the wing main body, the air door device is installed at the front end of the wing main body and extends in the length direction of the wing main body, and the air door device has an open state and a closed state. An exhaust air door is formed between the air door device and the wing main body when the air door device is in an open state. According to the utility model, enough lift force can be generated in the takeoff and landing stage of the airplane, so that vertical takeoff and landing or short-distance takeoff and landing of the airplane are realized.

The embodiment of the invention provides an aircraft and a design method thereof, and relates to the technical field of aircrafts, the aircraft comprises an aircraft body, an air inlet channel and two hang gliders, the air inlet channel penetrates through the bottom of the aircraft body, the two hang gliders are arranged on the two sides of the aircraft body respectively, when the aircraft flies in the forward direction, the aircraft is in a cruise mode, and when the aircraft flies in the forward direction, the aircraft is in a cruise mode; and when the aircraft flies reversely, the aircraft is in a gliding mode. The aircraft body is provided with the air inlet channel and the two hang gliders, when the aircraft flies in the forward direction, air enters the air inlet channel in the bottom of the aircraft body, cruising flight is conducted through stamping power, and the aircraft is in a cruising mode; after the aircraft rotates around the center shaft to a reverse rotation state, the aircraft glides in a high lift-drag ratio unpowered mode and is in a gliding mode. In the flight state of the aircraft, the cruising mode and the gliding mode can be switched at any time through attitude switching, the defects of weak carrying capacity of the cruising mode and the dynamic defect of the gliding mode are overcome, and the dynamic advantage of the cruising mode and the carrying advantage of the gliding mode are considered.

A heavy payload, autonomous UAV able to deliver supply by way of airdrop with more precision and at a lower cost. The UAV is equipped with two movable wing systems that rotate from a stowed position to a deployed position upon jettison of the UAV from a mothership. The UAV can be controlled remotely or it can operate autonomously and the movable wings can include ailerons to effectuate flight control of the UAV. The UAV can be reusable or can be an expendable UAV.

The invention provides a foldable vertical expansion out-of-phase airfoil coupling tandem wing device, and belongs to the technical field of gliders, the foldable vertical expansion out-of-phase airfoil coupling tandem wing device comprises an adjusting part, the adjusting part comprises a vertical cylinder and a wing, the outer part of the vertical cylinder is fixedly connected with a limiting sleeve, and the outer part of the vertical cylinder is fixedly connected with a fan-shaped guide plate; a folding assembly used for storing the wings is arranged outside the vertical cylinder, and a rotating assembly is arranged outside the wings. Through the arranged adjusting part, under the cooperation of the rotating frame, the rotating plate and the spring positioning pin, the wing can stably rotate to the storage or working position around the vertical cylinder, and accurate adjustment of the attack angle of the trailing edge adjusting plate is achieved by starting the driving motor. The problem that a traditional tandem wing is inconvenient to transport is solved, the space adaptability of equipment is improved, and the overall aerodynamic performance of the aircraft can be remarkably enhanced by actively adjusting the aerodynamic surface and optimizing the ratio of lift force to resistance in different flight states.

Aerial delivery systems are described including a propulsion unit, a deployable parafoil attached to the propulsion unit, a control / navigation unit operably connected to the parafoil, and a support truss connected to the propulsion unit. The system may be configured to attach to and transport a payload. The propulsion unit may be configured to provide thrust to the aerial delivery system while the parafoil is deployed and the control / navigation unit may be configured to steer the parafoil while deployed.

Aircraft system and launching method and apparatus A method of controlling the altitude and / or velocity of a tethered aircraft, the method comprising the steps of: a charging phase, in which the energy of the aircraft is increased, a conversion phase following the charging phase, in which the increased energy is utilised to increase the altitude and / or velocity of the aircraft; a gliding phase, in which the aircraft is positioned for a further charging phase and conversion phase; and repeating the charging phase and conversion phase at least once.

A supply glider is disclosed herein. The supply glider includes a body having a first end and a second end, the body being configured to be coupled to a host aircraft, a container disposed between the first end and the second end of the body, wings coupled to the body between the first end and the second end, and stabilators coupled to the body adjacent the second end.

Relates to an apparatus, system and method for a fire fighting robot capable of extinguishing fires such as fires, wildfires, forest fires, building and / or house fires, general fires, etc. by accurately directing water and / or fire extinguishing agents towards the flames. 【Solution means】The fire fighting robot uses sensors to pinpoint the direction, range and temperature of the fire in order to accurately direct the nozzle of the hose towards the fire. This can be a skydiving robot that dives into a wildfire in a rocky area, a drone, a helicopter, or in the case of a fire truck, a robot arm or robot nozzle with at least two degrees of freedom, and can reliably and optimally use water and / or fire extinguishing agents using sensors and a network capable of transmitting the fire location, range and temperature to the robot.

To provide a firefighting robotic device, system, and method capable of extinguishing fires, wildfires, forest fires, building and home fires, general fires, and the like, by precisely directing water and / or fire extinguishing agents at the flames.SOLUTION: A firefighting robot uses sensors to pinpoint the direction, extent, and temperature of a fire in order to accurately aim a hose nozzle at the fire. This could be a skydiving robot diving into a remote wildfire, or in the case of a drone, helicopter, or fire engine, a robotic arm or nozzle with at least two degrees of freedom. Using sensors and a network that can transmit the fire's location, extent, and temperature to the robot, it can ensure optimal use of water and / or extinguishing agents.SELECTED DRAWING: Figure 9

The utility model discloses a glider full-motion horizontal tail amplification steerage control mechanism, which comprises horizontal tails, side plates and a special-shaped rocker arm, the two horizontal tails are arranged at the tail part of a glider body, the special-shaped rocker arm is arranged between the two horizontal tails, the special-shaped rocker arm is clamped between the two side plates, and the special-shaped rocker arm is provided with a spar groove, a rotating shaft hole, a rocker arm limiting groove and a steel wire hole. The steel wire hole is connected with a servo steering engine through a push-pull steel wire. The horizontal tail is reasonable and ingenious in structural design, the servo steering engine is used for controlling rotation of the special-shaped rocker arm, so that the turnover angle of the horizontal tail is changed, the flight angle range of the horizontal tail is enlarged, the controllability of the glider is enhanced, the horizontal tail can be close to the vertical state, the glider vertically descends, and the flight space needed by landing of the glider is reduced.

An aircraft structural component, for example, a wing spar that has an I-beam shape having upper and lower spar caps coupled by a web therebetween and that provides structural support for an aircraft wing. The wing spar may be fabricated as a graphite composite that is thermally cured to have a certain stiffness. In one embodiment, the wing spar is fabricated so that the upper spar cap has a higher CTE than the web, which creates tension forces in the spar cap when the spar is thermally cured and then cooled. Therefore, when the wing spar is mounted to the wing and the aircraft is in flight, compression forces on the wing skin act to relieve the tension forces in the spar cap, which reduces the compression buckling load on the wing.

The utility model discloses a novel gliding parachute traction device, including the shell body, install rotatable electric cylinder in the shell body, and electric cylinder is used for winding up the traction rope, install the corresponding lead screw in the shell body with electric cylinder, install the lead screw nut on the lead screw, install the corresponding slide bar in the shell body with the lead screw nut, one end of lead screw nut and slide bar slidingly connected, install the corresponding traction rope guide mechanism with electric cylinder between the lead screw nut and slide bar. The utility model has the advantages of: through setting up electric cylinder to replace traditional motor, with good sealing performance, can protect the electrical device in electric cylinder, thereby effectively dustproof waterproof, avoid the risk of electric cylinder in the humid environment such as sea or lake water short circuit, guarantee the stability of electric cylinder work, improve the safety of equipment.

A glider system capable of sustained long-term flight includes a fixed-wing glider having a dual fuselage system. The top surface of the glider is covered with a plurality of photovoltaic cells capable of powering onboard sensors, propeller systems, and / or onboard processers. The glider includes wing spars with a composite material covering an inner foam core, with the type of foam core or use of reinforcement materials differs along the length or width of the wing spars. The glider is able to downward facing sacrificial winglets to provide a landing system without the need for bulkier landing gear.

A computer implemented method of acquiring and processing autonomous aerial vehicle data comprising obtaining past flight data from an autonomous aerial vehicle; storing the data in a database; conducting netto-variometer calculations to obtain equations to normalize the data; using a filtering technique to normalize the data; storing the equations obtained from the netto-variometer calculations into the database; and using the stored equations and live flight data to generate an optimized sink polar estimate for the autonomous aerial vehicle, wherein the optimized sink polar estimate is to be used in computing netto-variometer during flight.

A solar powered plane, such as a plane configured to operate in the stratosphere, that includes a descent control system arranged such that, in the event of loss of control or airframe failure or flight termination, a transferred energy to an impacted object and / or a kinetic energy imparted on impact by any item of the plane that reaches the ground is reduced to less than a predetermined energy or a regulatory or legal safety threshold.

This application discloses a combined aircraft system and control method, relating to the field of aircraft technology. A paraglider unit is foldably stored on the fuselage; a release mechanism is located on the fuselage for releasing the paraglider unit from the fuselage; the paraglider unit is connected to a multi-rotor flight unit via multiple parachute lines on both sides; limiting components are provided on both sides of the fuselage arms, and at least one parachute line on each side is threaded through or connected to the corresponding limiting component; the multi-rotor flight unit is configured to generate differential force by controlling at least one set of rotors corresponding to the limiting components. This differential force is transmitted to the parachute lines through the limiting components, creating a lift difference between the two sides of the paraglider unit, thereby controlling the flight attitude of the combined aircraft system. Therefore, this application ultimately achieves the technical effect of "combining the vertical takeoff and landing and high maneuverability of a multi-rotor flight unit with the long endurance advantages of a paraglider unit," becoming an integrated and efficient flight platform.

A glider system capable of sustained long-term flight includes a fixed-wing glider having a dual fuselage system. The top surface of the glider is covered with a plurality of photovoltaic cells capable of powering onboard sensors, propeller systems, and / or onboard processers. The glider includes wing spars with a composite material covering an inner foam core, with the type of foam core or use of reinforcement materials differs along the length or width of the wing spars. The glider is able to downward facing sacrificial winglets to provide a landing system without the need for bulkier landing gear.

The invention relates to a pipe rail gas supply infinite endurance hydrogen-oxygen explosion pushing all-weather galloping platform (glider and car), which is characterized in that two sides of an elevated flyway are respectively provided with an iron pipe gas supply rail capable of conveying high-pressure hydrogen through side gas leakage holes; according to the iron pipe air supply rail, a plurality of small galloping vehicles with grabbing lugs can slide on the outer surface of the iron pipe air supply rail in the mode that the side sliding plate face of the sliding rail with the flat cavity defined by the plate pipes is attached to the outer surface of the iron pipe air supply rail, and the side air leakage hole is provided with a half-exposed leakage-proof plug which can exert pressure on the hole through a spring in the pipe. When the sliding head attached to the rail of the flat cavity impacts the inclined face of the half-exposed leakage-proof plug, the half-exposed leakage-proof plug can leak air in a full-hidden mode, and the leaked hydrogen can generate reverse thrust when the flat cavity with a backward opening explodes when encountering oxygen, so that the small aerodyne drives the manned glider to slide forwards. The grabbing lugs can be used for the glider to grab the galloping trolley by means of the grabs at the legs of the glider to slide on the rail by means of hydrogen-oxygen power or to fly off the rail singly after the grabs are loosened. The invention can be used for providing a whole vehicle transportation and ejection platform for military and civilian dual-purpose vehicles and airplanes.

Devices, such as aerodynamic kites used in kiteboarding (also known as kitesurfing), handheld aerodynamic wings used in wing foiling and wing surfing, and paddles used in paddleboarding, for generating a force for powering a user on an appropriately configured vehicle, such as a kiteboard, kitesurfing foilboard, hydrofoil board, surfboard, wing board, wing foil board, stand up paddleboard, stand up paddleboard with hydrofoil, roller skates, rollerblades, skateboards, snowboards, skis, or ice skates, to traverse across a body of water, sand, earth, paved area, snow, or ice, are provided with a thrust generating device (e.g., an electric ducted fan system) to assist in generating said force.

This invention discloses a bird-like aircraft with adjustable wing lift, comprising a fuselage, a flight controller, a tail fin, and at least one pair of wings. Each wing includes a wingplate and several damper flaps. The wingplates have several air intakes, and the damper flaps are rotatably mounted on the air intakes via pivots. The invention also includes a first drive mechanism for driving the wingplates to swing and simultaneously driving the damper flaps to rotate and open / close. The tail fin is either a first tail fin or a second tail fin. The first tail fin is connected to a second drive mechanism that drives its rotation and extension / retraction to deploy / retract. The second tail fin is connected to a third drive mechanism that drives its rotation and swing. The second or third drive mechanism is mounted on the fuselage and operates through the flight controller. This invention, through wing swing and damper opening / closing control, combined with the adjustment of the multi-functional tail fin, significantly improves the aerodynamic efficiency and attitude control precision of the aircraft, achieving multiple flight modes such as vertical takeoff and landing, hovering, forward flight, roll, yaw, and gliding.

Aerial delivery systems are described including a propulsion unit, a deployable parafoil attached to the propulsion unit, a control / navigation unit operably connected to the parafoil, and a support truss connected to the propulsion unit. The system may be configured to attach to and transport a payload. The propulsion unit may be configured to provide thrust to the aerial delivery system while the parafoil is deployed and the control / navigation unit may be configured to steer the parafoil while deployed.

The paraglider traction equipment suitable for the regional tourism industry development comprises a machine body (1) and a control device (7), a servo driving device (2), a winch (3) and a wire guiding device (4) are installed in the machine body (1), the servo driving device (2) is connected with the winch (3) through a transmission device (5), and the winch (3) is connected with the wire guiding device (4) through a speed changing device (6). The wire guiding device (4) comprises a movably-installed ground wire guiding gauge (41), one end of a pulling rope is fixed to the winch (3) and then wound from one end of the winch to the other end of the winch in a reciprocating mode, and the index end of the pulling rope on the winch (3) penetrates through the wire guiding gauge (41). By means of the mode, the problem that an unpowered paraglider cannot take off from the ground can be solved, the industry threshold is lowered, and meanwhile the wing folding risk caused by mountain turbulence to the paraglider during traditional mountain top take-off is lowered.

The invention discloses a combined aircraft system and a control method, and relates to the technical field of aircrafts. The paraglider unit is accommodated on the fuselage in a foldable manner; the release mechanism is arranged on the fuselage and used for releasing the paraglider unit from the fuselage; the paraglider unit is connected to the multi-rotor flight unit through a plurality of parachute cords on the two sides of the paraglider unit. Limiting components are arranged on the vehicle arms on the two sides of the vehicle body, and at least one parachute cord on each side penetrates through or is connected to the corresponding limiting component. The multi-rotor flight unit is configured to generate differential power by controlling at least one group of rotors corresponding to the limiting parts, and the differential power is transmitted to the parachute cords through the limiting parts, so that a lift force difference is generated on the two sides of the paraglider unit, and the flight attitude of the combined aircraft system is further controlled. Therefore, the technical effect of integrating the vertical take-off and landing and high maneuverability of the multi-rotor flight unit and the long endurance advantage of the paraglider unit is finally achieved, and the integrated efficient flight platform is formed.

A flow deflector for an aerial vehicle system has a flow deflector body, a clip arranged in an interior of the flow deflector body, and a spring within the clip. The flow deflector body includes a first portion at a forward end shaped to engage a surface of an aerial vehicle body and a second portion at an aft end shaped to engage a surface of a booster engine. The flow deflector body can include a plurality of body segments arranged to form the flow deflector body. The clip may be configured to fit around and engage a portion of an aft flange of the aerial vehicle body. The spring can be preloaded and arranged to press on the aft flange when the clip engages the portion of the aft flange.

The safe paraglider convenient to fold and unfold comprises a back seat, the inner bottom wall of the back seat is fixedly connected with a servo motor, the output end of the servo motor is fixedly connected with a third gear, the inner wall of the back seat is fixedly connected with a second mounting seat, the inner wall of the second mounting seat is rotationally connected with a second rotating shaft, and the second rotating shaft is fixedly connected with a second rotating shaft. According to the safe paraglider convenient to fold and unfold, the paraglider body is firstly placed on the ground, then a servo motor is started, a third gear is driven to rotate, the meshed second gear rotates, then the meshed first gear is driven to rotate, the first rotating shaft synchronously rotates while rotating, the paraglider body is driven to rotate, the paraglider body is driven to rotate, and the paraglider body is driven to rotate. When the paraglider body is folded, the two take-up wheels are driven to rotate, the paraglider rope is wound, in the process, under the action of the supporting rotary drum and the two limiting rotary drums, the paraglider rope is in a straightened state during winding, the flatness during winding is guaranteed, and after the paraglider rope is wound, the paraglider body is folded.

A launch system and method for orbital or suborbital air-launch of a payload involving releasably coupling a launch vehicle with a towed aircraft via an articulatable carriage to form an air-launch assembly, towing the air-launch assembly via a tow aircraft and interconnected tow cable to a first altitude, releasing the air-launch assembly from tow at or above the first altitude, activating the towed aircraft propulsion system and initiating a pull-up and climb maneuver of the towed aircraft to a second altitude, articulating the articulatable carriage to shift the air-launch assembly from a stowed position to a deployed position with the launch vehicle spaced from the towed aircraft, releasing the launch vehicle from the articulatable carriage and thus from the towed aircraft, and activating the launch vehicle propulsion system for further altitude gain or to meet specific mission requirements.