13 results about "Hang-glider" patented technology

This invention discloses an aerial traction propulsion system with beacon guidance function and its control method. The system includes a guidance control end carried by the towed object and a guided propulsion end serving as the aerial flight power source. The two ends are physically connected by a traction rope and transmit data through a communication link. The guidance control end generates guidance information and sends it to the guided propulsion end, which adjusts its flight state accordingly to maintain the traction configuration. The system has a manual mode and an automatic mode. In the automatic mode, the guided propulsion end performs a two-layer control of speed feedforward following and lateral deviation correction. The automatic mode includes two stages: heading hold and heading follow-up. Once heading follow-up is entered, it is irreversible. The system achieves safety protection through distance anomaly detection of the dual-end position data and communication disconnection timeout. This invention does not require complex sensors or dedicated thrust devices on the propulsion end and can be implemented using a general-purpose flight platform, making it suitable for various scenarios such as hang gliding, surfing, and skiing.

The embodiment of the invention provides a super-endurance load-bearing grabbing and clamping type logistics bird-shaped unmanned aerial vehicle and a using method thereof, and relates to the field of aviation devices. The super-endurance load-bearing grabbing and clamping type logistics bird-shaped unmanned aerial vehicle comprises a vehicle body, a transmission assembly, a driving assembly, two hang gliders, a propelling mechanism, four supporting arms, four rotor wings and a grabbing assembly. The driving assembly is installed in the fuselage, the hang glider is rotationally connected with the fuselage, the driving assembly is connected with the hang glider, the four supporting arms are rotationally connected with the fuselage, the driving assembly is connected with the four supporting arms through the transmission assembly, the four rotors are connected with the four supporting arms correspondingly, and the four rotors are connected with the four supporting arms correspondingly. The propelling mechanism is connected with the machine body, and the grabbing assembly is arranged at the bottom of the machine body. The system is efficient in energy consumption control, and is especially suitable for medium and long distance logistics distribution scenes with high requirements for endurance time.

An interface apparatus for providing a user with a hang gliding experience in a virtual space includes: a control bar which the user is to grip; a tilt mechanism which supports the control bar from above such that the control bar is tiltable; a force sensor that is provided to the tilt mechanism and that detects a force and a moment which are applied from the user to the control bar; and an input and output section that provides a signal indicative of the force and the moment to a simulation apparatus configured to generate the virtual space and that acquires, from the simulation apparatus, a control signal for controlling the tilt mechanism so as to tilt the control bar.

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.

The invention discloses a split type long-hovering airship type aircraft, relates to the technical field of airship aircrafts, and solves the technical problems of high cost and low safety in the existing technical scheme. The split type long-hovering airship type aircraft comprises a pod, an airship body frame is arranged on the upper wall surface of the pod, and an airship body is arranged on the airship body frame; sub boat bodies are arranged on the boat body frame, the sub boat bodies are connected with the boat body frame through independent mooring ropes and arranged above a pod, and the multiple sub boat bodies are arranged in a staggered mode in the vertical space; by means of the split type design and safety distance isolation of the sub boat bodies, disastrous consequences caused by explosion of a single hydrogen air bag are fundamentally avoided; in combination with a standby hull rapid deployment system, fault redundancy and online repair capability are realized; and expensive helium is replaced by cheap and easily available hydrogen, and airborne equipment can be used for preparation, so that the manufacturing cost and the operating cost of the whole life cycle are greatly reduced.

1. Name of the product in this design: Powered Suspension Glider. 2. Intended use of this design: for aviation sports, recreational flying, and flight experiences. 3. The key design feature of this product is its shape. 4. The image or photograph that best illustrates the design's key points: a 3D model. 5. The bottom surface of this product is a part that is not easily seen or cannot be seen during use, so the bottom view is omitted.

Control mechanism for RC hang gliders, characterized in that the pilot's suspension as a swivel mechanism is actively swiveled around the longitudinal axis of the kite by a servo rigidly attached to the keel tube, whereby the pilot is flexibly connected to the swivel mechanism (Fig. 1 + Fig. 2)

The invention relates to the technical field of unmanned aerial vehicles, in particular to a bionic energy-saving unmanned aerial vehicle which comprises a main body shell. The folding wing is arranged above the main body shell, one end of the folding wing is connected with a rotating arm, one end of the rotating arm is sleeved with a first fixing column, one end of the first fixing column is fixedly connected with a supporting frame, and the first fixing column is connected with the inner wall of the supporting frame. According to the bionic energy-saving unmanned aerial vehicle, when the unmanned aerial vehicle climbs to a proper height, the control system closes the propellers I, the unmanned aerial vehicle enters a sliding mode through rotation and opening of the two groups of rotating arms and adjustment of the unfolding amplitude of the folding wings, long-distance unpowered sliding is achieved through airflow, energy consumption is reduced, and the unmanned aerial vehicle flies against wind; the height is adjusted or small-range maneuvering is conducted through the second propeller or the first propeller, the unmanned aerial vehicle works cooperatively with the hang glider, the hang glider achieves efficient flight by means of aerodynamic force, maneuverability is guaranteed, energy consumption is reduced, meanwhile, the unmanned aerial vehicle provides electric energy through the solar panel, and energy is saved.

The utility model discloses a fire-fighting bomb with a hang glider suite, and relates to the field of unmanned aerial vehicle fire fighting, the fire-fighting bomb comprises a fire-extinguishing bomb head, a bomb head upper cover and a tail control rudder, the tail of the fire-extinguishing bomb head is provided with a butt joint part, and the front end of the tail control rudder is provided with a butt joint groove matched with the butt joint part in an inserted mode. The tail control rudder is arranged at the tail of the fire extinguishing bullet, the butt joint portion of the tail control rudder and the butt joint groove are assembled and connected and fixed through the bolt connecting piece, then the bullet upper cover and the U-shaped fixing ring are arranged on the fire extinguishing bullet in a surrounding and sleeving mode, the U-shaped fixing ring is tightened, and fixing of the bullet upper cover is completed. The two gliding wing plates above the bullet upper cover extend through the elastic torsion piece, at the moment, the fire extinguishing bullet can be used as a gliding fire extinguishing bullet, on the contrary, the fire extinguishing bullet can be used as a common fire extinguishing bullet after the assembly part is disassembled, variety conversion among various fire extinguishing bullets is achieved, meanwhile, old stored fire extinguishing bullets can be upgraded and reformed, and the fire extinguishing bullet can be used as a fire extinguishing bullet. And the practicability is improved.

The invention discloses a sliding dual-mode AUV (Autonomous Underwater Vehicle) and a design method thereof. The AUV comprises deformable hang gliders which are arranged on the two sides of a pressure-bearing shell and can be unfolded in a gliding mode to provide lift force and folded in a swimming mode to reduce fluid resistance; the buoyancy adjusting system comprises an outer oil bag, a front buoyancy adjusting oil tank, a rear buoyancy adjusting oil tank and a buoyancy adjusting power module and is used for dynamically adjusting the buoyancy and the gravity center position of the AUV through oil transfer; and the vector propulsion module is arranged at the tail part of the AUV, comprises a propeller of which the angle can be adjusted at two degrees of freedom and a guide plate matched with the propeller, and is used for providing direction control capability in a gliding mode. The AUV is provided with the tail vector propelling device, the two buoyancy adjusting oil tanks distributed on the front portion and the rear portion of the interior of the pressure-bearing shell and the deformable hang gliders located on the two sides of the AUV body at the same time, so that the AUV has the two operation modes of gliding depending on buoyancy and swimming depending on neutral buoyancy, and flexible switching can be achieved according to operation tasks.

1. Name of the product in this design: Amusement machine (glider). 2. Intended use of this design: animation and amusement equipment. 3. The key design feature of this product is its shape. 4. The image or photograph that best illustrates the design's key points: 3D view 1.

The utility model discloses a hang glider separating and releasing mechanism. The mechanism comprises a hoop which is arranged outside an aircraft body in a sleeving mode and comprises a left half hoop and a right half hoop, the left half hoop is connected with a left side hang glider, and the right half hoop is connected with a right side hang glider; one ends of the left half hoop and the right half hoop are fixedly connected, and the other ends of the left half hoop and the right half hoop are inserted and elastically connected through a compressed first-stage separation spring; the piston cylinder is arranged in the aircraft body and is fixedly connected with the aircraft body; a memory alloy circular ring capable of being contracted by heating is arranged in the piston cylinder; a piston is arranged on the memory alloy circular ring; a compressed secondary separation spring is arranged on the periphery of the piston; the limiting stud is used for sequentially penetrating through the hoop and the aircraft body to be fixedly connected with the piston; when the memory alloy circular ring is heated and contracted, the piston drives the limiting stud to move downwards under the action of the second-stage separation spring to release connection between the left half hoop and the right half hoop, and the left half hoop and the right half hoop are opened under the action of the first-stage separation spring to be separated from the aircraft body.