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Solar powered stratospheric glider
ActiveUS20250011013A1GlidersAircraft stabilisation by gravity apparatusFixed wingMechanical engineering
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.
Owner:SOLARIS SUBORBITAL INC
Anti-drag deicing structure of ice surface rescue unmanned aerial vehicle and ice surface rescue unmanned aerial vehicle
The invention relates to a drag reduction and deicing structure of an ice surface rescue unmanned aerial vehicle and the ice surface rescue unmanned aerial vehicle, and discloses a deicing structure which is used for cleaning broken ice on an ice surface or a water surface through cooperation of an ice breaking cone and snow removing sawteeth, can reduce the sliding resistance of the unmanned aerial vehicle and improves the ice surface rescue efficiency. The ice breaking machine is characterized by being composed of a machine body, a machine frame, a machine frame head, a machine frame tail, a machine frame middle part, an ice breaking plate, an ice breaking cone, a hanging plate, an air cylinder, a fixing plate and a fixing block, the machine frame comprises the machine frame head, the machine frame tail and the machine frame middle part, the two ends of the machine frame middle part are correspondingly arranged at one end of the machine frame head and one end of the machine frame tail respectively, and the machine frame is arranged on the top face of the machine body. The machine body is of a hollow structure, the length of the machine body is smaller than that of the machine frame, the width of the machine body is smaller than that of the machine frame, fixing plates are correspondingly arranged on the two side faces of the machine body respectively, fixing blocks are correspondingly arranged on the two sides of the bottom face of the tail of the machine frame respectively, and one end of a hanging plate is arranged on the bottom faces of the fixing blocks.
Owner:XUZHOU BLUE LAKE INFORMATION TECH CO LTD
Utilizing multi-directional energy-absorbing landing gear for vertical takeoff and landing
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.
Owner:TEXTRON SYSTEMS CORP
Crash load distribution structure of fuselage
A crash load distribution structure of a fuselage, includes a floor frame defining a fuselage floor, a skid member fastened to the lower portion of the floor frame, and a crash box coupled to the skid member and extending to the lower portion of the floor frame, and configured to selectively deform in a crash load direction when an oblique crash occurs thereto.
Owner:HYUNDAI MOTOR CO LTD +1
Hydraulic folding and unfolding device for airplane sled
PendingCN119527541Aeasy to useGuaranteed synchronicitySkis/runnersUndercarriagesHydraulic pumpRoad surface
The invention belongs to the technology of aircraft hydraulic systems, and relates to a hydraulic retracting and releasing device for an aircraft sled. Comprising a hydraulic oil tank, a hydraulic pump, a one-way valve, a hydraulic oil filter, a two-position three-way electromagnetic valve, a pressure sensor, a pressure regulating valve, a three-position four-way electromagnetic valve, a front sleigh throttle valve, a left sleigh throttle valve, a right sleigh throttle valve, a front sleigh actuating cylinder, a left sleigh actuating cylinder and a right sleigh actuating cylinder. And the sleigh can be retracted and released. When the airplane lands on the ice and snow covered pavement, the sleigh is put down, and the airplane lands through the sleigh. When the airplane lands on hard road surfaces such as sand and stones, the sled is folded, and the airplane lands through airplane wheel tires. A simulation model of the sled retracting and releasing system is established in simulation software, a curve of displacement and time is obtained according to loads in different flight states, the flow range of the adjustable throttling valve is determined, the range of the through-flow area of the throttling valve is calculated according to a small hole throttling formula, and the range of the through-flow area serves as the flow adjusting requirement of the adjustable throttling valve.
Owner:HARBIN
flying object
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.
Owner:AERONEXT INC
Snow accumulation prevention structure of ice surface rescue unmanned aerial vehicle and ice surface rescue unmanned aerial vehicle
The invention relates to an ice surface rescue unmanned aerial vehicle accumulated snow prevention structure and an ice surface rescue unmanned aerial vehicle, and discloses the snow prevention structure which can guide accumulated snow or crushed ice through cooperation of a conical top and an inclined-plane-shaped intercepting net, reduce attachment and accumulation of the accumulated snow or the crushed ice on the intercepting net, reduce abrasion of flying fan blades and improve the ice surface rescue efficiency. The device is characterized in that the device is composed of rack wings, air guide through holes, a conical top, inclined supporting rods, an intercepting net, a ring bottom, threads, thread grooves and fixing rings, the rack wings are correspondingly provided with the air guide through holes, the top faces of the rack wings are correspondingly provided with the fixing rings, the edges of the inner side faces of the fixing rings are connected with the edges of the air guide through holes, and the conical top is provided with the inclined supporting rods. A threaded groove is formed in the side face of the fixing ring, threads are formed in the inner side face of the ring bottom, the threads correspond to the threaded groove, the inner side face of the ring bottom is in threaded connection with the side face of the fixing ring in the mode that the threads are matched with the threaded groove, and the conical top is located over the air guide through hole.
Owner:XUZHOU BLUE LAKE INFORMATION TECH CO LTD
Single-seat electric multi-rotor ultra-light aircraft
PendingCN119527543Alow costreduce weightFuselage framesPower plant arrangements/mountingDriver/operatorUltralight aviation
The invention discloses a single-seat electric multi-rotor ultra-light aircraft, and belongs to the field of ultra-light aircraft design. The fuselage is formed by welding a fuselage main structure with light high-strength hard aluminum alloy pipe beams and taking a large-range hollow light fuselage shell as a main body, the four sets of foldable coaxial double-paddle power supporting arms are arranged on the horizontal plane in the middle of the fuselage and symmetrically arranged front and back, and the skid type undercarriage is arranged at the bottom of the fuselage. The weight of an empty aircraft meets the weight requirement of an ultra-light aircraft, meanwhile, the main body adopts an aluminum alloy pipe beam welding structure, the cost is reduced, most drivers are located in a pipe frame structure, the gravity center of the whole aircraft is close to a rotor plane, and the driving experience is better.
Owner:SHENYANG AIRCRAFT DESIGN & RES INST YANGZHOU COLLABORATIVE INNOVATION RES INST CO LTD
Ice surface rescue unmanned aerial vehicle supporting and positioning structure and ice surface rescue unmanned aerial vehicle
According to the ice surface rescue unmanned aerial vehicle supporting and positioning structure and the ice surface rescue unmanned aerial vehicle, a rotating motor drives a triangular wheel to rotate, so that the unmanned aerial vehicle can rapidly reach the water surface position where a person falling into water is located, and meanwhile slipping and rollover of the unmanned aerial vehicle on the ice surface and deviation of the unmanned aerial vehicle from a preset return route are reduced; and the ice surface rescue efficiency is improved through the position adjusting structure. The device is characterized in that the device is composed of a device body, a sliding plate, a sliding plate groove, a second screw, a motor containing groove, triangular wheels, a supporting shell, a fourth rotating shaft and a rotating motor, the sliding plate comprises two vertical sliding plates and two transverse sliding plates, the motor containing groove is formed in the middle of the device body, and the length of the motor containing groove is equal to the width of the device body; the motor containing groove is parallel to the transverse sliding plates and located between the two transverse sliding plates, one ends of supporting shells are correspondingly arranged on the two sides of the bottom of the motor containing groove respectively, and rotating motors are correspondingly arranged on the side faces of the supporting shells respectively.
Owner:XUZHOU BLUE LAKE INFORMATION TECH CO LTD
Utilizing multi-directional energy-absorbing landing gear for vertical takeoff and landing
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.
Owner:TEXTRON SYSTEMS CORP
Sled landing gear and method for using same
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.
Owner:HARBIN
Landing gear for a vertical take-off and landing aircraft
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.
Owner:ARCHER AVIATION INC
Counterweight structure of skid undercarriage and skid undercarriage
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.
Owner:芜湖联合飞机科技有限公司
Landing gear sled puller device and method of designing the same
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.
Owner:CHINA HELICOPTER RES & DEV INST
Anti-seismic enhancing structure of ice surface rescue unmanned aerial vehicle and ice surface rescue unmanned aerial vehicle
Owner:XUZHOU BLUE LAKE INFORMATION TECH CO LTD
Unmanned aerial vehicles
ActiveCN113911326Bcompact structureEasy to storeRemote controlled aircraftWing adjustmentsFlight vehicleStructural engineering
An unmanned aerial vehicle (100) comprises a fuselage (20); an arm (31) rotatably connected to the fuselage (20) so that the arm (31) can be selectively in a folded state or an unfolded state relative to the fuselage (20); and a power device (33) carried by the arm (31), the power device (33) being used to provide flight power. The arm (31) comprises a first arm and a second arm, the first arm rotates around a first rotation axis, and the second arm rotates around a second rotation axis along a conical surface, so that the second arm rotates from the folded state to enter the unfolded state.
Owner:SZ DJI TECH CO LTD
Skid device for aircraft and method for controlling the same
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.
Owner:HYUNDAI MOTOR CO LTD +1
Skid device for aircraft and method for controlling it
Owner:HYUNDAI MOTOR CO LTD +1
Multi-stage multi-phase buffering skid type landing gear
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.
Owner:NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
Aircraft takeoff and landing supporting system and light-weight sled plate composite structure adopted by same
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.
Owner:RHYXEON GENERAL AIRCRAFT CO LTD
Rotorcraft provided with a cell supported by a landing gear with skids with variable stress-relieving zones
The present invention relates to a rotary-wing aircraft (1) equipped with a rotating wing (3) and a skid landing gear (5), the landing gear (5) being equipped with a first skid (6) and a second skid (7) as well as a first cross member (20) and a second cross member (30). The first cross member (20) is connected to a fuselage (2) of the rotary-wing aircraft (1) solely by two fasteners (41, 42). The second cross member (30) is supported in flight solely by two supports (50, 60) fixed to the fuselage (2) and through which the second cross member (30) passes. Each support (50, 60) includes an opening delimited by a retaining surface, the second cross member (30) having clearance with each retaining surface at all times. A median support (70) is arranged transversely between the two supports (50, 60) and above the second cross member (30).
Owner:EUROCOPTER FRANCE SA
Undercarriage and aircraft
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.
Owner:BEIJING TSINGAERO ARMAMENT TECHNOLOGY CO LTD
A skid-type landing gear structure
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.
Owner:XIAN AIRCRAFT DESIGN INST OF AVIATION IND OF CHINA
Buffering anti-collision structure of ice surface rescue unmanned aerial vehicle and ice surface rescue unmanned aerial vehicle
According to the buffering anti-collision structure of the ice surface rescue unmanned aerial vehicle and the ice surface rescue unmanned aerial vehicle, a plurality of rubber columns are arranged between an upper supporting frame and a lower supporting frame, the impact force generated when crushed ice on the water surface and the ice surface collides with the unmanned aerial vehicle can be reduced, and abrasion of the unmanned aerial vehicle is reduced. The device is characterized in that the device is composed of a rack, a rack head, a rack tail, a rack middle part, a first handle, an upper supporting frame, a rubber column and a lower supporting frame, the rack comprises the rack head, the rack tail and the rack middle part, the two ends of the rack middle part are correspondingly arranged at one end of the rack head and one end of the rack tail respectively, and the first handle is arranged at the other end of the rack head; one side of an upper supporting frame is arranged on the side face of the machine frame, the edge of one side of the upper supporting frame is connected with the edge of the side face, except the edge where the first handle is arranged, of the machine frame, and one side of a lower supporting frame is arranged on the side face of the machine frame.
Owner:XUZHOU BLUE LAKE INFORMATION TECH CO LTD
Landing gear sled pull rod device and design method thereof
The invention provides an undercarriage sled pull rod device, which belongs to the technical field of helicopter undercarriage design, and comprises an outer cylinder, a piston rod, a spring and a limiting joint, the outer cylinder is arranged on an undercarriage buffer, the piston rod is arranged on an undercarriage sled, and one end of the piston rod extends into an inner hole of the outer cylinder; the limiting connector is arranged at the joint of the outer cylinder and the piston rod, the limiting connector, the inner wall of the outer cylinder and the outer wall of the piston rod jointly form a closed space, and the spring is connected to the outer side of a piston rod body in a sleeving mode and located in the closed space. The purpose of keeping the posture of the helicopter sled can be achieved; meanwhile, due to the design of the pull rod device, the sleigh can be always kept in an upwarp posture, so that the sleigh cannot be inserted into accumulated snow when the helicopter wears snow or slides, and the helicopter can smoothly slide to the position above the accumulated snow.
Owner:CHINA HELICOPTER RES & DEV INST
Vertical take-off and landing (VTOL) aircraft
Vertical takeoff and landing (VTOL) aircraft, especially electric VTOL (e-VTOL) aircraft include a fuselage (which may include a pair of ground-engaging skids) defining a longitudinal axis of the aircraft, forward and aft pairs of port and starboard aerodynamic wings extending laterally outwardly from the fuselage and forward and aft pairs of port and starboard rotor pods each being in substantial alignment with the longitudinal axis of the fuselage. In specific embodiments, each of the forward and aft pairs of port and starboard rotor pods comprises a forward and aft pair of rotor assemblies.
Owner:EVE UAM LLC
Multistage suspension for UAV landing gear
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.
Owner:WING AVIATION LLC
Rocker arm type undercarriage, aircraft and method
The invention provides a rocker arm type undercarriage, an aircraft and a method. The rocker arm type undercarriage comprises a supporting rod, a retractable actuating cylinder, a connecting rod, a buffer mechanism, a skid and a follow-up actuating cylinder used for locking the undercarriage at any position, one end of the supporting rod is hinged to one end of the buffer mechanism, and the other end of the buffer mechanism is hinged to the skid. One end of the folding and unfolding actuating cylinder is hinged to the supporting rod, one end of the connecting rod is hinged to and slides on the buffering mechanism, one end of the follow-up actuating cylinder is hinged to the supporting rod, and the hinge point of the follow-up actuating cylinder and the supporting rod is located below the hinge point of the folding and unfolding actuating cylinder and the supporting rod; the other end of the supporting rod, the other end of the retractable actuating cylinder, the other end of the connecting rod and the other end of the follow-up actuating cylinder are all provided with connecting points E used for being hinged to a machine body. The aircraft can stably take off and land in a complex terrain environment, and the take-off and landing capacity and the bearing capacity of small and medium-sized aircrafts in the complex terrain are improved.
Owner:LANDING GEAR ADVANCED MFG
Correctable skid landing gear for helicopter takeoffs and landings at high altitudes and its control method
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.
Owner:NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
Tapered insertion brake deceleration structure of ice surface rescue unmanned aerial vehicle and ice surface rescue unmanned aerial vehicle
According to the ice surface rescue unmanned aerial vehicle cone insertion brake deceleration structure and the ice surface rescue unmanned aerial vehicle, an air cylinder drives a telescopic rod to stretch, the telescopic rod drives a brake cone to be inserted into the ice surface, braking force can be generated on the unmanned aerial vehicle, and the sliding speed of the unmanned aerial vehicle is reduced. The device is characterized in that the device is composed of a machine body, sliding plates, second screws, sliding plate grooves, a rack, a rack head, a rack tail, a rack middle part, air cylinders, telescopic rods, a circular plate and a brake cone, the rack comprises the rack head, the rack tail and the rack middle part, the sliding plates comprise two vertical sliding plates and two transverse sliding plates, and the air cylinders are correspondingly arranged on the two sides of the bottom face of the rack middle part respectively; the air cylinder is located between the two transverse sliding plates, the air cylinder is located between the side face of the machine body and the vertical sliding plate, one end of a telescopic rod is arranged in the air cylinder in a sliding mode, the other end of the telescopic rod is arranged on the top face of a circular plate, and a brake cone is arranged on the bottom face of the circular plate.
Owner:XUZHOU BLUE LAKE INFORMATION TECH CO LTD