65results about "Convertible alighting gear" patented technology

An unmanned aerial vehicle includes a fuselage, a power device connected to the fuselage, and a control device disposed at the fuselage and electrically connected with the power device. The control device is configured to control the power device to switch an operating mode of the power device to cause the unmanned aerial vehicle to fly in air or navigate on a water surface.

A propulsion system for an aerial vehicle or toy aerial vehicle is disclosed. The system comprises a ducted fan or shrouded propeller drive system for driving the vehicle along ground, the ducted fan or shrouded propeller drive system operating in a plane and having a peripheral ground-engagement part or hubless wheel. The system further comprises a ducted fan or shrouded propeller comprising one or more blades rotatable about a ducted fan or shrouded propeller axis for producing thrust, wherein the ducted fan or shrouded propeller is mounted as such that it may tilt or rotate so that during ground travel it may be in the same plane as the hubless wheel and during operation of the ducted fan or shrouded propeller for flight the blades pass through the plane and inside the hubless wheel. In this way, the ducted fan or shrouded propeller blades of the drive system are protected from blade strikes on obstacles and personnel operating around the ducted fan or shrouded propeller drive system are protected from harm from exposed rotors or blades with no duct or shroud surrounding them.

The invention relates to a slide-wheel composite type small and medium sized UAV (unmanned aerial vehicle) landing gear system. The system is characterized in that: each taxiing vehicle wheel assembly located on slide plates is equipped with a base for installing vehicle wheels, a clamping slot is arranged above the base, a clamp hole for placing a compression spring is disposed at the center of the clamping slot, a threaded hole is coaxially disposed at the clamping hole center, and slideway holes are arranged on landing gear supporting arms and the slide plates coaxially toward the direction of the threaded hole. The landing gear system also includes a pair of automatic release control assemblies able to control timely separation of each taxiing vehicle wheel assembly. Each automatic release control assembly comprises: a sliding pin equipped with a small hole at the upper end, a fastening rope able to pass through the small hole at the upper end of the sliding pin so as to prevent the sliding pin from slipping off from the slideway holes, and a cutter that passes through and is in connection with the fastening rope and can cut off the fastening rope. The cutter cut off the fastening rope timely under the control instruction of a control circuit board so as to complete automatic separation release actions of the taxiing vehicle wheel assembles, thus realizing the functions of rapid taxiing takeoff and short-range braking landing.

The invention discloses a low-altitude flight operation unmanned aerial vehicle and a control system and application thereof. Buffer mechanisms of a main undercarriage supporting column and a front undercarriage supporting column are designed and mounted on a force bearing structure on the outer side of a fuselage (1), the lower ends of the main undercarriage supporting column and the front undercarriage supporting column are connected into a slide-type undercarriage (2) structure, and the gliding ratio is increased through the high lift-drag ratio aerodynamic force design. A low-altitude crash prevention technology, a low-altitude link communication technology and an unmanned aerial vehicle system technology are integrated, the pneumatic and dynamic overall layout design of the fixed wingunmanned aerial vehicle suitable for low-altitude operation is adopted, and the new-layout unmanned aerial vehicle is suitable for low-altitude operation such as agricultural aviation plant protection and safety flight.

A retractable helicopter landing gear has a suspension structure supporting one wheel, and is movable between a withdrawn position, to reduce drag on the helicopter, and a lowered position for landing and takeoff of the helicopter. The landing gear also has a skid, which is located between the axis of rotation of the wheel and the periphery of the wheel, is diametrically opposite the suspension structure, and is connected to the suspension structure by a connecting device having a torsion bar.

A system for controlling landing gear of an aircraft is disclosed. The apparatus includes a sensor for sensing water, wherein the sensor is coupled to the landing gear and a retracting device for retracting the landing gear when the sensor senses a body of water. In one alternative, the aircraft is an amphibious aircraft and the sensor senses electrical conductivity. In another alternative, the retracting device comprises a hydraulic system for deploying and retracting the landing gear, wherein the hydraulic system retracts the landing gear when the sensor senses a body of water. In yet another alternative, the retracting device comprises a locking mechanism that locks the landing gear to the aircraft, wherein the locking mechanism unlocks the landing gear so as to detach it from the aircraft when the sensor senses a body of water.

A twin float aircraft (1) which has a retractable float (4 and 5) for each side of a fuselage (3) providing buoyancy for the aircraft during take off and landing and reduced air resistance during flight with each of the floats (4 and 5) being articulated (12 and 13) to assist streamline alignment when retracted.

The invention is to an optionally piloted aircraft that can takeoff and land conventionally or vertically, and can convert between the two. The aircraft is immune to one or more engine failures during vertical flight through multiple engines and the use of a virtual nozzle. Aerodynamic controls are similarly redundant. Hovering flight is enabled with a novel stabilization system. Long range efficient cruise is achieved by turning off some engines in flight and sealing them into an aerodynamic fairing to achieve low drag. The resulting aircraft is capable of CTOL and VTOL, and is capable of converting between the two modes while in the air or on the ground. The aircraft can also be easily taxied on the ground in the conventional manner. Automatic controls considerably reduce the amount of training a pilot needs to fly and land the aircraft in either VTOL or CTOL mode.

The invention relates to manufacture of airplanes and performance improvement, taking off and landing, and parking of the airplanes. 1, a rubber air bag (4) is arranged on an airplane body (7) or wings (5) of an airplane (battleplane) used on land, and the airplane can take off and land on the surfaces of rivers, lakes and sea by utilization of buoyancy generated when the rubber air bag filled with compressed air is placed on water surface, so as to become an amphibious aircraft. And 2, fixed devices such as a small front wing (3), a rudder wing (6) and a tail-pipe nozzle (9) of the most advanced battleplane made in China are improved to be movable and adjustable devices, so that the operation of the airplane is more flexible and the performance of the airplane is perfect.

An amphibious aircraft has a tricycle landing gear that is movable between a retracted, or up, position and an extended, or down, position. Each member of the landing gear is protected in the forward direction by a hydrodynamic protector, or vane, or shoe, such as may tend to create lift when brought into engagement with water, as during landing. The landing gear protector vanes may be mounted to move with extension and retraction of the landing gear. The landing gear wheels may protrude to extend partially downwardly proud of the sole of the shoe. The landing gear actuator and transmission may operate all gear in concert. The shoes may include sacrificial wear members for ground engagement in the event of an inadvertent gear-up landing on terrain.

The invention discloses an implementation method for an aerial photography aircraft. The aircraft comprises a support (12), a rotor wing, a bottom plate (9), a tripod head (13), supporting legs (8) and a camera (7). The rotor wing and the tripod head are arranged on the support. The bottom plate is fixed to the bottom of the support. The camera is mounted on the tripod head. The supporting legs are fixed to the bottom of the bottom plate. The camera comprises a camera body (77) and a compound lens (72). A charge coupled device (CCD) sensor (76) is arranged in the camera body which is provided with a photoelectric emission and receiving device (75) for lens alignment. According to the implementation method for the aerial photography aircraft, the integration level is high, and the structure is compact; the aircraft is provided with not only a flying mechanism with excellent performance but also the supporting legs with a unique buffering function, moreover, the aircraft is provided with the creative camera, and therefore the aerial photography aircraft is abundant in function, high in safety, ingenious in structure, large in lift force, smooth and steady in flight, and easy to implement.

The invention discloses an unmanned aerial vehicle and a lifting undercarriage thereof. The lifting undercarriage comprises a wing plate (3) and undercarriage supporting legs (22) used for making contact with the ground, one end of the wing plate (3) is connected with the undercarriage supporting legs (22), the other end of the wing plate (3) is used for being connected with an aircraft body (1),and when the lifting undercarriage rises, the wing plate (3) serves as a fixed wing and is used for improving the lifting force of the aircraft. According to the unmanned aerial vehicle undercarriage,the cruise economy of an aerial vehicle can be improved; and meanwhile, the whole unmanned aerial vehicle is compact in structure, and the weight is kept at a low level.

The invention discloses an air vehicle capable of achieving transformation recycling and a recycling method, and belongs to the fields of rocket overall design technologies and reusability technologies. The air vehicle capable of achieving transformation recycling comprises a rocket body, a large-area wing used for providing lifting force and achieving high supersonic speed section decelerating, retractable canards for wide speed range trimming, a parachute system for subsonic speed section decelerating, a reverse thrust engine system for decelerating before landing and an undercarriage systemfor landing. The air vehicle capable of achieving transformation recycling can adapt to the whole-course flying working condition from the high supersonic speed stage to the subsonic speed stage, nomain power is consumed in the decelerating process, and the landing environment adaptability is higher in the recycling process. Compared with a wing transformation scheme, pressure center configuration of the low supersonic speed stage is completed by adopting the pop-up canards, a transformation mechanism is simple, power dissipation is low, and the effects are significant; and compared with a vertical recycling scheme, lateral wind disturbance can be resisted better in a horizontal recycling process.

The safety tripod includes a tripod, a flight driving machine mounted on the tripod to enable the tripod to fly, a landing base for seating the tripod on the ground when the tripod lands, and a standing guide mounted on the tripod to enable the tripod to stand up.

The invention provides a variant aircraft, which comprises an aircraft body, folding wing sections, wing tail vertical fins, folding mechanisms, a tail rotor, a power inclination rotation wing and a reconnaissance communication equipment cabin, wherein the aircraft body is provided with the reconnaissance communication equipment cabin at the front end of the flight direction in the center axis direction of the variant aircraft; the back end is provided with the tail rotor; the folding wing sections are symmetrically arranged at the two sides; the two wing tail vertical fins are respectively and correspondingly arranged at the tail ends of the two folding wing sections; the wing tail vertical fins are vertical to the folding wing sections; each folding mechanism is provided with a rotatingshaft which is parallel to the center axial line of the variant aircraft; the two folding wing sections are arranged at the two sides of the aircraft body through the folding mechanisms; the folding wing sections can realize 90-degree folding around the rotating shafts of the folding mechanisms. The variant aircraft is based on inclination rotation power and realize the vertical takeoff and landing; the vertical takeoff and landing can be realized in the space limited region; after the variation of the variant aircraft, the fixed wing mode cruising flight can be realized; a vertical takeoff and landing function, a high-speed cruising function, and a target staring function can be realized.

The invention discloses a multi-position undercarriage for aircraft, the multi-position undercarriage may comprise a first aircraft landing skid disposed on the bottom side of the aircraft, and a second one landing skid disposed on the top side or on the bottom side of the aircraft, wherein the first landing skid and second landing skid are rotatable with respect to the aircraft.

The invention belongs to the technical field of unmanned aerial vehicles, and particularly relates to an amphibious landing gear for an unmanned aerial vehicle. The problems of small application rangeof an existing landing gear for an unmanned aerial vehicle and poor protection effect on the unmanned aerial vehicle are solved. According to the following scheme, the amphibious landing gear for theunmanned aerial vehicle comprises a base. Sleeves are fixed to both sides of the inner wall of the top of the base through screws, and a first sliding groove and a second sliding groove are formed inthe inner walls of the two sleeves separately. A first sliding rod and a second sliding rod are slidably connected to the inner wall of the first sliding groove and the inner wall of the second sliding groove separately. A supporting wheel is connected with the inner wall of the second sliding rod in a sleeving mode. A rotating frame is connected to the outer wall of the bottom of the first sliding rod through a hinge, and universal wheels are fixed to two sides of the outer wall of the bottom of the rotating frame through screws. According to the amphibious landing gear for the unmanned aerial vehicle, the stability of the base on the water surface can be improved, the possibility of tilting and rolling over of the base can be reduced, the tilting angle of a fixing plate can be effectively reduced, the stability of the unmanned aerial vehicle can be improved, and the protection effect on the unmanned aerial vehicle is improved.

The invention discloses a replaceable foot structure for a legged landing gear. The replaceable foot structure comprises a mechanical connection interface, a force sensor and a replaceable foot end, wherein the upper end of the replaceable foot end is detachably connected to the lower end of the force sensor; the upper end of the force sensor is connected to the mechanical connection interface; and the form of the replaceable foot end comprises, but not limited to, a buffer type foot end, a disk type foot end, an electromagnetic absorption type foot end and a spiny hemisphere type foot end. The replaceable foot structure designed by the invention can be used in cooperation with the legged landing gear, so that an aircraft can satisfy landing and parking requirements under the condition ofdifferent geology, topography and terrain.

The invention relates to a novel automobile, belonging to the technical field of flying automobiles, which comprises a vehicle body, a chassis and a wheel device. The vehicle body comprises a controller. The controller is installed inside the vehicle body and connected by electric wires. The chassis comprises a frame, a swivel arm and a take-off and landing seat; the frame is arranged under the vehicle body in a square shape, and swivel arms are mounted on the four corners of the frame, and the take-off and landing seat is mounted on the central part of the chassis. The wheel device comprisesa wheel, a hub, a motor, a bearing, a pinion, a hollow gear, a support frame, a propeller, an electronic governor and a clutch. The wheel is provided with a hub on one side close to the vehicle body by a toothed structure inside the wheel. The motor is an internal and external two-axis motor, and the motor shaft on the inner side is connected with the pinion. The hollow gear meshes with the pinionand the wheel; one side of the support frame is fixed on the swivel arm, and the other side is fixed on the motor and the hollow gear. The electronic governor is mounted on the support frame and connected to the motor. The clutch is mounted on the motor shaft. The invention has the advantages of simple structure, easy maintenance, and can be used as an air-land amphibian.

An aircraft having a retractable landing gear assembly configured to support some of the weight of the aircraft via one or more wheels, and another retractable non-wheeled landing gear assembly or device configured to support some of the weight of the aircraft via one or more “low-friction” supports such as an air cushion is disclosed. The aircraft may have a maximum take-off weight between 100 and 150 tonnes. There may be two main landing gears each carrying two wheels, a nose landing gear, and a central non-wheeled landing gear providing the low friction vertical support when the aircraft is moving on the ground / operating surface.

The invention relates to an aircraft for takeoff and landing on water or on land. The aircraft comprises a fuselage and a spring-mounted landing gear. Landing gear wheels are mountable on the landing gear for takeoff and landing on land. Furthermore, the aircraft comprises a floating device coupleable to the landing gear of the aircraft via a connecting device. The floating device is configured such that the hydrostatic lifting force of the floating device is greater than the maximum takeoff weight of the aircraft.

The invention discloses a leg and sledge combined landing gear of a vertical-takeoff-and-landing aircraft. The leg and sledge combined landing gear comprises two landing gear main bodies; each landinggear main body comprises a supporting device, driving devices, a sliding sledge and a control system, the supporting device comprises a connecting seat and a supporting leg, the supporting leg comprises at least two leg bodies separated from each other, the connecting seat, the supporting leg and the sliding sledge are sequentially and rotationally connected, bearings are arranged at all rotationally-connected parts, and the driving devices are arranged in all the rotationally-connected positions. The landing gear has the advantages of a leg type landing gear and the advantages of a sliding sledge type landing gear, the postures of the supporting legs and the angle of the sliding sledge are adjustable, the landing gear can be applied to slope landing and step landing of the vertical-takeoff-and-landing aircraft, the leg postures can be adjusted in real time according to the terrain after being landed so as to guarantee the horizontal posture of the fuselage of the vertical-takeoff-and-landing aircraft, change of the gravity center of the fuselage of the aircraft due to the terrain can be prevented effectively, and thus the aircraft can be effectively prevented from rolling over.

This invention relates to an improved float for use with an aircraft having water landing capabilities comprising at least one float capable of increasing / decreasing its volume arranged to at least substantially support said aircraft in a floating on water status so that the fuselage of the aircraft is substantially above the water.