58results about "Skis/runners" patented technology

The present invention provides landing gear that reduces the effects of wind from a predetermined direction on the landing gear during flight, thereby improving fuel efficiency and stability, and reducing the impact during landing. [Solution] The aircraft in the present invention is equipped with landing gear having a contact surface, wherein the contact surface has a shape that reduces drag during travel compared to when landing. The shape of the contact surface is substantially airfoil in the longitudinal direction of the aircraft, and the angle of attack of the contact surface decreases during travel compared to when landing. The shape of the contact surface is inverted airfoil in the longitudinal direction of the aircraft, and the angle of attack of the contact surface decreases during travel compared to when landing. Multiple landing gears are provided, and the contact surface of the above shape is provided only on the landing gear on the front side of the aircraft. The landing gear is connected to the contact surface and is equipped with an intermediate member that extends at least vertically, and the structure of the contact surface is more fragile than the intermediate member.

An unmanned aerial vehicle (UAV) includes a UAV body constructed and arranged to carry a payload, a set of UAV wings coupled with the UAV body, and a set of undercarriage apparatus coupled with at least one of the UAV body and the set of UAV wings. The set of UAV wings is constructed and arranged to provide lift to the UAV. At least one undercarriage apparatus of the set of undercarriage apparatus includes an elastomeric vehicle mount, a leg, and a coupling constructed and arranged to couple the leg with the elastomeric vehicle mount. The elastomeric vehicle mount is constructed and arranged to absorb energy provided from the leg through the coupling.

A sled landing gear and a method for using same. The sled landing gear comprises a main landing gear (100), a front steel cable (200), a rear steel cable (300), a retractable steel cable (400), a main gear sled (500), and a retraction / extension device. The main gear sled (500) is a double-board structure with an opening. An end of the front steel cable (200) is connected to the main landing gear (100). Another end of the front steel cable (200) is connected to a front end of the main gear sled (500). An end of the rear steel cable (300) is connected to the main landing gear (100). Another end of the rear steel cable (300) is connected to a rear end of the main gear sled (500). An end of the retractable steel cable (400) is connected to a middle section of the rear steel cable (300). Another end of the retractable steel cable (400) is connected to the retraction / extension device. The retraction / extension device controls retraction and extension of the sled via the retractable steel cable.

The invention related to a Landing gear (10) for a vertical take-off and landing aircraft (100), comprising a wheel (20), a shock absorber (30) with an absorber connection (32) to connect to a fuselage (110) of the aircraft (100) and at least one attachment lever (40) with a lever connection (42) to connect to the fuselage (110) of the aircraft (100) spaced apart from the absorber connection (32), the wheel (20) being attached to the attachment lever (40) spaced apart from the lever connection (42), wherein the shock absorber (30) is connected to the wheel (20) directly or indirectly via a wheel connection (34) to provide a load path (LP) for vertical load from the wheel (20) to the absorber connection (32), and wherein the shock absorber (30) comprises a fuse pin (36) at the absorber connection (32) and / or the wheel connection (34) having a predetermined breaking load to break and release the connection at the absorber connection (32) and / or the wheel connection (34), and wherein the attachment lever (40) comprises a rotary bearing (41) providing a folding movement for the wheel (20) from an extended landing position (ELP) into a crash position (CP) when the fuse pin (36) breaks.

The utility model relates to a skid undercarriage counterweight structure and a skid undercarriage, belongs to the technical field of aerospace, and solves the problem that the undercarriage resonates in ground experiments and test flight processes due to actual skid undercarriage products and design deviations. The device comprises a central shaft and a balancing weight, the number of the balancing weights is multiple, and the balancing weights are arranged on the center shaft in a sleeving mode. And the counterweight structure is arranged in the undercarriage second pipe. According to the skid undercarriage, the structure of the undercarriage is not changed, the counterweight structure is arranged in the first pipe of the skid undercarriage, and the resonance phenomenon of the undercarriage is weakened or avoided.

The application provides a landing gear sled pull rod device, and belongs to the technical field of helicopter landing gear design. The device comprises an outer cylinder, a piston rod, a spring and a limiting joint. The outer cylinder is arranged on a landing gear buffer, the piston rod is arranged on a landing gear sled, one end of the piston rod extends into a hole in the outer cylinder, the limiting joint is arranged at the connection between the outer cylinder and the piston rod, the limiting joint, the inner wall of the outer cylinder and the outer wall of the piston rod jointly form a closed space, and the spring is sleeved on the outer side of the piston rod body and located in the closed space. The device can keep the posture of the helicopter sled. Meanwhile, the design of the pull rod device can keep the sled in an upward posture at all times, which is beneficial to the helicopter landing on snow or sliding, so that the sled cannot be inserted into the snow, and the helicopter can smoothly slide above the snow.

The present disclosure relates to a skid device for aircraft and a method for controlling the same that may implement an optimal soft landing even under varied landing conditions in various environments, and the skid device may include: at least one support leg (10) having a hollow portion and fixed to a lower portion of a fuselage; a skid (20) connected to an end of the support leg; a magnetic field generator (30) installed in the hollow portion; and a magnetorheological material (40) accommodated in the hollow portion.

The invention discloses a multi-stage multi-phase buffering skid type landing gear, which belongs to the technical field of aircraft landing buffering, and comprises a skid plate, a strut mechanism, a buffering bent plate mechanism, an aluminum honeycomb buffering mechanism and a sliding mechanism. The upper end of the supporting column mechanism is fixed to the aircraft, an oil-gas buffer is arranged in the supporting column mechanism to form first-stage buffering, and impact energy is preliminarily absorbed and dissipated through the synergistic effect of compressed gas and hydraulic oil. The buffering bent plate mechanism is composed of an arc-shaped bent plate and a connecting piece of the arc-shaped bent plate and can convert impact loads into elastic deformation energy. The aluminum honeycomb buffering mechanism is arranged between the skid plate and the arc-shaped bent plate, generates plastic deformation when being pressed, and forms secondary buffering together with the buffering bent plate mechanism. The sliding mechanism is used for guiding the two ends of the arc-shaped bent plate to synchronously slide outwards in the length direction of the skid plate, and uniform compression of the aluminum honeycomb buffering mechanism is guaranteed. Through the synergistic effect of a multi-stage buffering mechanism, the impact load peak value is effectively reduced, and the buffering stability and the structural reliability are improved.

The invention relates to the technical field of aviation aircraft takeoff and landing systems, in particular to an aircraft takeoff and landing supporting system and a light-weight sleigh plate composite structure adopted by the aircraft takeoff and landing supporting system, and the aircraft takeoff and landing supporting system is of a combined structure of a front sleigh plate, a front composite restraining assembly, a main sleigh plate and a main composite restraining assembly. The problem that an existing aircraft takeoff and landing system cannot have the takeoff and landing capacity on land and ice and snow road surfaces at the same time is solved, adaptability and stability are good, meanwhile, the defects that an existing sled plate is heavy, poor in low temperature resistance and insufficient in impact resistance are overcome through a light-weight sled plate composite structure, the light-weight and high-strength structural design is achieved, and the service life of the sled plate is prolonged.

The utility model discloses an undercarriage and an aircraft, and relates to the technical field of equipment. The frame body is used for being installed at the bottom of the aircraft, the frame body comprises an arch-shaped beam used for being connected with the aircraft and skid pipes connected with the two ends of the arch-shaped beam, the skid pipes are used for making contact with a supporting face, and a boosting assembly is arranged on the frame body and used for applying thrust in the direction opposite to the descending direction of the aircraft so as to reduce the descending speed of the aircraft. According to the undercarriage provided by the invention, the boosting assembly is arranged on the frame body of the undercarriage, and the thrust can be applied in the direction opposite to the descending direction of the aircraft through the boosting assembly, so that the descending speed of the aircraft is reduced, and the risk that the aircraft is damaged when falling to the ground can be reduced.

This application belongs to the field of aircraft landing gear technology, and specifically relates to a novel skid-type landing gear structure, comprising: skid tubes, including two arranged at different tilt angles; a front crossbeam connected to the front end of the two skid tubes; a rear crossbeam connected to the rear end of the two skid tubes; and a fuselage joint installed on the front and rear crossbeams for connecting the front and rear crossbeams to the fuselage; wherein both the front and rear crossbeams are curved upwards to form an arc-shaped bow. This application reduces the load on the landing gear and aircraft; reduces the weight of the skid-type landing gear and aircraft; improves the cushioning performance of the skid-type landing gear; and reduces the manufacturing cost of the aircraft.

A landing gear assembly for an unmanned aerial vehicle (UAV) includes a shock tower, a pair of leg members, and suspension assemblies. The shock tower is adapted to mount to a frame of a fuselage of the UAV and includes upper and lower end mounts. The leg members are adapted to extend out from opposing sides of the lower end mounts. The leg members are flexible and each include an upper leg section pivotally mounted to the lower end mount and a lower leg section adapted to connect to a ground gear. The suspension assemblies are each mounted to and extend between the upper end mount and a corresponding one of the leg members. The suspension assemblies each include a damper and a spring.

This invention provides a skid-type landing gear for helicopter takeoff and landing at high altitudes and its control method. The landing gear includes a strut, a brushless DC motor, a universal joint, a worm gear mechanism, a main skid, and a skid for correction. The main skid and the skid for correction can effectively adapt to soft and undulating surfaces such as snow, sand, and swamp at high altitudes. The brushless DC motor, through the force transmission of the universal joint and the worm gear mechanism, ensures that one skid for correction contacts the ground while the other skid remains initially off the ground. The difference in ground friction between the two sides generates a yaw torque on the aircraft, which is the correction torque. This effectively solves the problem of difficult correction during takeoff and landing for helicopters equipped with skid-type landing gear. Through the self-locking principle of the worm gear mechanism, the motor is protected from counter-torque and structural damage when the skid for correction is subjected to a large impact force from an uneven road surface.

The invention relates to a manoeuvring device (100) for ground movements of an aeroplane with landing gear skids (10), such as an aircraft, which does not require removing a lateral nacelle or a work platform when the aeroplane is equipped with same. To this end, the inventor proposes a ground manoeuvring device which comprises pivoting arms (140) that are connected to wheels (50), the pivoting arms being pushed so as to be rotated with respect to the body (110) of the ground manoeuvring device, in a direction from top to bottom until the wheels come into contact with the ground and the landing gear skid is lifted off the ground.

A vertical take-off and landing (VTOL) aircraft designed for both vertical and horizontal flight features a fuselage that houses essential stability and propulsion components. The aircraft includes a main rotor (2) and wide-chord blades (1) with a fully proportional cross-section, enabling high lift in both VTOL and fixed-wing modes. The flight control system facilitates smooth transitions between flight modes by adjusting the orientation of the blades (1), switching between the main rotor (2) and a rear pusher propeller (5) driven by a gas engine (16). Stability in VTOL mode is maintained by front and rear duct fans (6, 6') and ailerons (4, 4'), while in horizontal mode, stability is provided by front and rear skids (3, 3'). The aircraft is further enhanced by solar panels (14) on the fuselage, allowing for battery recharging during horizontal flight, extending operational endurance. A payload compartment (10) maintains the aircraft's center of gravity across flight modes.

The invention belongs to the technical field of aircraft ground taxiing, and particularly relates to a self-adaptive unfolding type sleigh type landing gear and a working method thereof.When the device is used, the snow depth is detected through a snow depth detector, whether the snow depth exceeds a set value or not is judged through a control system of an aircraft, and when the snow depth does not exceed the set value, the aircraft is started; when the snow depth exceeds a set value, the extension front sledge plate mechanism and the extension rear sledge plate mechanism do not act, and when the snow depth exceeds the set value, the extension front sledge plate mechanism and the extension rear sledge plate mechanism are unfolded; the extension front sledge plate mechanism and the extension rear sledge plate mechanism are unfolded so that the stress area of the main sledge plate can be increased, resistance borne by the main sledge plate can be reduced, meanwhile, whether the extension front sledge plate mechanism and the extension rear sledge plate mechanism need to be unfolded or not can be judged according to the snow depth, and therefore the self-adaption effect is achieved.

A solar powered plane configured to operate in the stratosphere includes a hinged vertical stabiliser that that pivots about a hinge; the stabiliser extends both above the fuselage and also below the fuselage, and the base of the vertical stabiliser includes a skid. The hinged vertical stabiliser is configured such that when the skid contacts the ground on landing, the top of the vertical stabiliser pivots forwards around the hinge point, minimising damage to the aircraft on landing. the skid includes a lightweight, replaceable sacrificial layer.

[Problem] To provide landing gears that reduce the influence of wind blowing the landing gears in a prescribed direction during the flight of a flight vehicle and improve fuel consumption and stability, and that make it possible to reduce an impact during a landing. [Solution] A flight vehicle according to the present invention is provided with landing gears having ground contact parts that are each shaped so as to reduce drag during an advance as compared with during a landing. The ground contact parts are each shaped substantially like an airfoil in the front-back direction of the fuselage. In the ground contact parts, the angle of attack decreases during an advance as compared with during a landing. The ground contact parts are each shaped substantially like a reverse airfoil in the front-back direction of the fuselage. In the ground contact parts, the angle of attack decreases during an advance as compared with during a landing. A plurality of the landing gears are provided, and the ground contact parts having the shapes are provided to only the landing gears on the front side of the fuselage. The landing gears are each provided with an intermediate member that is connected to the ground contact part and that extends at least in the vertical direction. The ground contact part is so structured as to be more prone to breakage than the intermediate member.

The invention relates to a common interface quick interchange dual-mode undercarriage system which is applied to an unmanned aerial vehicle and comprises a front undercarriage common interface module and a main undercarriage common interface module which are arranged at the front part and the middle rear part of a fuselage of the unmanned aerial vehicle; a first force bearing device of the nose landing gear common interface module is connected with the front part of a fuselage of the unmanned aerial vehicle; a first connecting device is connected with the first force bearing device and a wheel type nose landing gear assembly or a skid nose landing gear assembly; a second force bearing device arranged on the main undercarriage common interface module is connected with the middle rear part of the fuselage of the unmanned aerial vehicle; and a second connecting device is connected with the second force bearing device and the wheel type main undercarriage assembly or the skid main undercarriage assembly. Through the front common interface module and the main undercarriage common interface module, core bearing structures and actuating mechanisms of two modes are reused, redundant weight caused by designing complete and independent structures for the two modes is thoroughly avoided, and the structural weight of the whole undercarriage system is remarkably reduced.

A solar powered plane configured to operate in the stratosphere includes a hinged vertical stabiliser that that pivots about a hinge; the stabiliser extends both above the fuselage and also below the fuselage, and the base of the vertical stabiliser includes a skid. The hinged vertical stabiliser is configured such that when the skid contacts the ground on landing, the top of the vertical stabiliser pivots forwards around the hinge point, minimising damage to the aircraft on landing. the skid includes a lightweight, replaceable sacrificial layer.

The utility model discloses an undercarriage and aircraft relates to undercarriage technical field, wherein the undercarriage includes at least two sled, at least two buffer beam and mounting bracket, the two sled is arranged opposite to each other, the buffer beam connects the two sled, the mounting bracket is mounted on the mounting bracket, and the mounting bracket is mounted on the mounting bracket. The at least two buffer beams are convexly arranged upwards and are distributed at intervals in the extension direction of the skid; the mounting bracket is arranged on the buffer beam and is used for connecting an aircraft body; at least two buffer beams comprise front beams, bent beam sections are arranged at the ends of the front beams, the bent beam sections bend and extend outwards towards the rear side, the front ends of the skids extend towards the front side to form front warping sections, and the front warping sections protrude outwards and are connected with the bent beam sections. According to the technical scheme, the buffering and energy absorbing effects of the undercarriage can be improved.

A long-range heavy-lift turbojet-powered manned vertical take-off and landing aircraft layout, comprising: a riding cockpit, telescopic variable-span wings, landing gears, turbojet thrust vectoring lift engine compartments, and a turbojet thrust engine. The riding cockpit, as a structural body, is located at the center of the aircraft; the bottom of the riding cockpit is connected to the telescopic variable-span wings; four turbojet thrust vectoring lift engine compartments are vertically arranged at the front, rear, left and right corners of the cockpit connected to the telescopic variable-span wings; the turbojet thrust engine and an air intake / exhaust duct thereof are horizontally embedded in the middle area between the wings in the front-back direction; and the landing gears are arranged on two sides of the turbojet thrust engine. The telescopic variable-span wings consider the take-off and landing stability and the cruise economy requirements by means of telescopic change; in addition, by additionally providing end plates at wing tips, the cruise flight induced resistance can be reduced, and the wing tips can be prevented from being scratched. The present invention considers heavy-lift / long-range flight capability, controllability and stability, and achieves pilot-aircraft attitude decoupling; and a pilot can control the aircraft attitude on the basis of body sensing, such that the operation requirement for the pilot is low.

The invention discloses a vehicle-mounted flight stretcher which is composed of a rescue vehicle platform and a vehicle-mounted rescue aircraft, the vehicle-mounted rescue aircraft comprises a rescue aircraft body and a ground rescue vehicle platform, and a special lifting type take-off and landing cabin is arranged on the ground rescue vehicle platform; the vehicle-mounted rescue aircraft body adopts a double-row serial heterogeneous duct layout, a streamline battery cabin is fixedly connected right below a main body frame of the aircraft body through hanging points, and an energy module is packaged in the streamline battery cabin; a load management system is integrated on the abdomen of the vehicle body main body frame, namely between the energy module and the vehicle body main body frame, and a medical stretcher is arranged under the load management system. A specially-designed large-load, compact and disassembly-free ducted aircraft serves as a connection aircraft to achieve the function similar to a stretcher, and the problem that vehicles cannot pass through and cannot be driven in harsh rescue environments such as dense forest mountains, traffic jam highways and urban blocked streets is solved.

The present invention relates to a restraint (20) for an aircraft (1). The restraint (20) comprises a cylinder (50) including a housing (51) and a head (70) movable in translation relative to the housing (51) along an elevation axis (AXALT), said head (70) having three degrees of freedom in rotation respectively along a longitudinal axis (AXL) as well as a transverse axis (AXT) and the elevation axis (AXALT), said restraint (20) comprising a force-retaining element (40) surrounding the cylinder (50) and provided with a fixing (42) suitable for being secured to the aircraft (1).

The utility model relates to the technical field of airplanes, in particular to an airplane capable of landing on a snowfield. The snowboard comprises a machine body, a damping mechanism and two snowboards, the bottom of the machine body is connected with the tops of the two snowboards through a damping mechanism, the damping mechanism is used for damping when the machine body lands, and the two snowboards are flush with each other and are arranged at an interval; the snowboard comprises a first inclined section, a transverse section and a second inclined section which are sequentially connected from front to back, the joint of the first inclined section and the transverse section and the joint of the second inclined section and the transverse section are of an arc-shaped structure, the first inclined section inclines upwards towards the front end of the machine body, and the second inclined section inclines upwards towards the rear end of the machine body. The width of the snowboard is sequentially increased from front to back. By arranging the snowboard, the pressure during landing of the airplane can be effectively dispersed, the sinking problem caused by the loose and soft accumulated snow is avoided, and therefore the airplane can land on the snowfield.