17results 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 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.

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 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.

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 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.