36results 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.

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 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 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.

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.

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.

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.

The invention relates to a multi-rotor large-load intelligent truss type undercarriage, and belongs to the technical field of undercarriages. The undercarriage comprises a force bearing unit, a locking unit, a buffer unit, a sensing unit and a control unit, each force bearing unit comprises two inverted n-shaped main beam pieces and a triangular truss piece, the triangular truss pieces are arranged in the middles of the n-shaped main beam pieces, the two n-shaped main beam pieces are connected through first connecting beams, and a mounting connector is defined between the first connecting beams through second connecting beams; the locking unit comprises a split type hoop piece and a driving piece which are arranged at the two ends of the top of the main beam piece. The buffer unit comprises a sliding shoe piece arranged at the bottom of the main beam piece; the sensing unit is integrated in the sliding shoe piece; and the control unit is electrically connected with each unit. Through cooperation of the truss structure and the intelligent control system, the problems that a traditional multi-rotor undercarriage is limited in bearing capacity, low in impact resistance and lack of dynamic regulation and control are solved, and tonnage load adaptation and active buffering stability of complex terrains can be achieved.

The invention discloses a fairing structure of an aircraft skid type undercarriage and an aircraft, and relates to the technical field of aircraft fairings, the fairing structure comprises an upper-section fairing and a lower-section fairing, the upper-section fairing and the lower-section fairing are both in a sleeve shape, the upper-section fairing is connected with a fuselage of the aircraft, the lower-section fairing is connected with an arch beam of the skid type undercarriage, and the lower-section fairing is connected with the skid type undercarriage. And the arc-shaped beam is configured to generate corresponding displacement along with the deformation of the arc-shaped beam. Wherein the outline of the cross section of the upper-section fairing is larger than that of the cross section of the lower-section fairing, and the upper end of the lower-section fairing extends into the lower end of the upper-section fairing to form nested fit. According to the fairing structure, the direct effect of undercarriage deformation on the fairing is avoided, the risk of structural interference, tearing or jamming is completely eradicated, the operation reliability and safety of an aircraft in a complex take-off and landing environment are improved, meanwhile, dust and rainwater can be effectively prevented from invading, and excellent protection is provided for an undercarriage system.

The application relates to the technical field of mobile structures, and discloses a whole mobile structure of a helicopter, which comprises a first baffle, a connecting mechanism, a second baffle and a skid pipe, the connecting mechanism is arranged on the first baffle, the first baffle is arranged on the skid pipe, the second baffle is arranged on the skid pipe, the back surface of the first baffle is provided with a carrying wheel, the connecting mechanism comprises a mandrel and a first positioning hole, and the mandrel is inserted into the first positioning hole. The whole mobile structure of the helicopter is characterized in that after the mandrel is fixed on the first baffle through fixed rivets, the components are fixed on the skid pipe through locking bolts and locking nuts, the connecting shaft is inserted into the mandrel, the carrying wheel can be quickly installed, the helicopter can be moved for a short distance after the carrying wheel is added to the device, the phenomenon that the helicopter is inconvenient to move when the skid pipe type landing gear is used is avoided, and the limitation of the site on the movement of the helicopter is reduced.

The invention discloses a low-overload skid type landing gear capable of actively augmenting stability and a control method thereof, and belongs to the technical field of aircraft landing load reduction deviation correction. The device comprises an undercarriage outer cylinder, an undercarriage piston rod coaxially and elastically connected with the undercarriage outer cylinder, a rotary joint hinged to the bottom end of the piston rod, a skid assembly comprising a first skid, a second skid and a middle skid connecting plate, and a first power buffer and a second power buffer which are respectively connected with the rotary joint and the corresponding skid. According to the working mode, overload is reduced through buffering compression of the power buffer and the piston rod during landing; during skating deviation, a single-side power buffer is regulated and controlled to stretch out so as to enhance the pressure of the skid to the ground, and active deviation correction can be achieved through generated yawing torque; and when the power buffer is folded, the power buffer contracts to drive the skid assembly to retract, so that the storage space is effectively saved. The defect that a traditional skid undercarriage is free of buffering and active deviation rectifying capacity is overcome, and the skid undercarriage is particularly suitable for the application environment of hypersonic aircrafts.

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.

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 hydraulic retraction and extension device for a ski-equipped aircraft, the hydraulic retraction and extension device comprising a hydraulic oil tank, a hydraulic pump, a one-way valve, a hydraulic oil filter, a two-position three-way solenoid valve, a pressure sensor, a pressure-regulating valve, a three-position four-way solenoid valve, a front ski throttle valve, a left ski throttle valve, a right ski throttle valve, a front ski actuating cylinder, a left ski actuating cylinder and a right ski actuating cylinder. A ski can be retracted and extended. When an aircraft lands on an icy or snowy road surface, the ski is deployed, and the aircraft lands by means of the ski. When the aircraft lands on a hard road surface such as sandstone, the ski is retracted, and the aircraft lands by means of wheels and tires.

The utility model discloses an undercarriage structure and an airplane and relates to the technical field of airplanes, the undercarriage structure comprises a hydrofoil, a supporting assembly and a first driving piece, one end of the hydrofoil is inserted into the airplane, the other end of the hydrofoil extends out of the airplane, the supporting assembly comprises a supporting rod, a supporting wheel and a first sleigh, and the supporting rod is rotatably arranged on the hydrofoil; the first driving part is used for driving the supporting rod to rotate so that the supporting assembly can be folded or unfolded, the supporting wheel is arranged on the supporting rod, the first sled is movably arranged on the supporting rod, and the first sled can move to the position below the supporting wheel when the supporting assembly is unfolded. According to the technical scheme provided by the utility model, the problem that the aircraft is greatly limited in a take-off and landing environment can be solved.

The invention relates to a versatile system for the secure handling of an aircraft (1) for vertical take-off and landing, which is provided with a skid-type landing gear comprising means (6) which form a motorized trolley for handling the aircraft (1), and further comprising means (10, 11) for gripping and lifting the landing gear of the aircraft in order to facilitate the handling thereof.

The utility model discloses a snowfield detection rescue robot which comprises a main machine and two propellers arranged on the two sides of the main machine. The bottom of the main machine is rotationally connected with two connecting plates, the bottoms of the two connecting plates are rotationally connected with sled bodies, two shock-proof rods are fixedly mounted at the bottom of the main machine, the other ends of the two shock-proof rods are rotationally connected with one sides of the two connecting plates respectively, mounting grooves are formed in the upper surfaces of the sled bodies, and telescopic bearing tires are arranged in the mounting grooves. And two searchlights are fixedly installed at the bottom of the main machine, an infrared camera is fixedly installed on one side of the main machine, through the arrangement of the connecting plate, the sleigh and the shock absorption rod, the device body can be effectively buffered when running on the snowfield, and the running stability is guaranteed. Meanwhile, the telescopic bearing tires mounted on the sleigh can be telescopically adjusted according to the actual condition of the snowfield; the tire can extend out on a flat or hard snowfield surface, and the moving efficiency is improved by utilizing the tire to roll forward.

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.