511results about "Wheel arrangements" patented technology

The utility model relates to a variable-configuration tilting quad-rotor unmanned aerial vehicle which comprises rotors (1), motors (2), main wings (3), a fuselage (4), a vertical fin (7), a power supply unit (8), a control unit (9), tilting steering engines (10), driving rocker arms (11), tilting connecting rods (13), tilting rod supports (16), front tilting rods (17), rear tilting rods, front driven rocker arms (18) and rear driven rocker arms. The tilting mechanism is simple in configuration form, the appearance of the whole tilting mechanism is not greatly changed in the tilting process, and the pneumatic influence in the tilting process is relatively small. When the rotors tilt forwards, a conventional rotor fixed wing aircraft mode is adopted, when the rotors tilt upwards, a conventional four-rotor unmanned aerial vehicle mode is adopted, and various modes and modes such as vertical take-off and landing, hovering and forward flying can be achieved.

A convertible ducted fan engine and mounting system. The convertible ducted fan engine has a shroud encircling a mechanical fan. The convertible ducted fan engine includes a fluid-propulsion configuration in which the mechanical fan rotates freely with respect to the shroud to produce thrust through fluid flow, and a drive-wheel configuration in which the shroud rotates about the rotational axis.

The invention discloses an all-electric turning execution mechanism and a turning anti-swing control method for a front wheel of an unmanned aerial vehicle, the all-electric turning execution mechanism comprises a motor, an electromagnetic clutch, a parallel gear box and an output gear, the electromagnetic clutch comprises a stator, a rotor and an armature, the stator is fixedly connected with a shell of the motor, and the rotor is connected with an output shaft of the motor; the armature is connected with a high-speed shaft of the parallel gearbox, and the output gear is fixedly connected with a low-speed shaft of the parallel gearbox. The motor, the electromagnetic clutch, the parallel gear box and the output gear are designed in an integrated mode, double optimization of the structure and functions is achieved, the number of parts and the connecting complexity are greatly reduced, and the requirements of the unmanned aerial vehicle for light weight and compact layout are met; by means of the connection and disconnection characteristics of the electromagnetic clutch, accurate active anti-swing and front wheel turning control can be achieved through linkage of the motor and the parallel gear box during power-on, and passive anti-swing can be achieved through a mechanical structure during power-off.

The invention provides a front wheel steering mechanism for a miniature ship-borne fixed-wing unmanned aerial vehicle, and relates to the technical field of unmanned aerial vehicle rotation mechanisms, the front wheel steering mechanism comprises a front wheel assembly, a front starting mounting frame assembly is mounted above the front wheel assembly, a front starting steering engine assembly is mounted on the side wall of the front starting mounting frame assembly, and the front wheel assembly comprises a damping column body; a shock absorption column is fixedly installed on an output shaft of the shock absorption column body, the lower end of the shock absorption column body is fixedly connected with a front supporting frame, and a front lifting tire is installed below the front supporting frame, so that output of a front lifting steering engine is more efficient, and front wheel steering is correspondingly faster. The rotation output of the front steering engine drives the front wheel to rotate through the front rocker arm, the two ball head connecting rods and the steering engine rocker arm, accurate control over front wheel steering during autonomous take-off and landing of the unmanned aerial vehicle is guaranteed, meanwhile, it is guaranteed that front wheel steering can be manually and remotely controlled, and compared with a single-connecting-rod front wheel steering mechanism, the front wheel steering mechanism is simple in structure, high in precision, high in torsion resistance and high in efficiency, and can be widely applied to the field of unmanned aerial vehicles. The maintenance is convenient.

The invention relates to the technical field of unmanned aerial vehicle loads, in particular to an unmanned aerial vehicle load structure which comprises a concave supporting seat, supporting legs are symmetrically and fixedly mounted on the left side and the right side of the concave supporting seat, a clamping driving mechanism is mounted on the inner side of the concave supporting seat, and an opening of the concave supporting seat is designed downwards. T-shaped connecting plates are symmetrically mounted on the left side and the right side of the clamping driving mechanism, and clamping parts are detachably mounted at the lower ends of the two T-shaped connecting plates. The unmanned aerial vehicle has the beneficial effects that when the load body needs to be clamped, the unmanned aerial vehicle drives the load structure to sleeve the load body, and meanwhile, the clamping parts are distributed on the left side and the right side of the load body; and in the downward landing process of the unmanned aerial vehicle, the lower end of the anti-falling mechanism rotates outwards to be opened, and meanwhile, the anti-falling mechanism drives the transmission mechanism to move close to the first locking mechanism, so that the first locking mechanism loosens locking of the clamping driving mechanism.

A rotorcraft with at least one non-retractable wheel-type landing gear and a fuselage comprising a lower shell, an inner floor, and at least one lower fuselage compartment arranged between the inner floor and the lower shell, wherein the at least one non-retractable wheel-type landing gear is rigidly attached in the at least one lower fuselage compartment and comprises: at least one wheel; a shock absorber connected to the at least one wheel and comprising a shock absorber tube and a shock absorber rod telescopically mounted to the shock absorber tube; at least two mounting arms extending laterally from the shock absorber tube; and a mounting pin extending from the shock absorber tube toward a floor fitting provided at the inner floor, wherein the mounting pin is connected to the floor fitting.

The undercarriage comprises a front undercarriage and two main undercarriages, the front undercarriage is arranged on the front side of the bottom of an aircraft body and comprises a front aircraft wheel and a front buffering supporting column, one end of the front buffering supporting column is connected with the aircraft body and arranged in the aircraft body, and the other end of the front buffering supporting column is connected with the aircraft body. The other end penetrates out of the machine body and is elastically connected with the front machine wheel; the two main undercarriages are arranged on the two opposite sides of the bottom of the aircraft body respectively, each main undercarriage comprises a buffer frame body, the two ends of each buffer frame body are a hinged end and a free end respectively, the hinged ends are hinged to the inner side of the aircraft body, and the free ends are connected with main aircraft wheels. Part of the structure of the front undercarriage is arranged in the aircraft body, and the rocker arm of the main undercarriage is directly hinged with the aircraft body, so that the overall windward area of the undercarriage is reduced, the aerodynamic resistance and the overall weight of the aircraft are reduced, the overall performance and the endurance of the aircraft are improved, and meanwhile, the aircraft is suitable for the aircraft with a shorter aircraft body.

A rotorcraft comprising a fuselage forming at least one lower lateral fuselage compartment with at least a first fitting, a second fitting, and a third fitting; and at least one non-retractable wheel-type landing gear that comprises: at least one wheel; a shock absorber with a shock absorber tube having an open end and an axially opposed closed end, and a shock absorber rod telescopically mounted to the shock absorber tube via the open end; a first fixation provided close to the open end on the shock absorber tube and connected to the first fitting; a second fixation provided close to the closed end on the shock absorber tube and connected to the second fitting; and a third fixation provided close to the closed end on the shock absorber tube and connected to the third fitting.

The invention discloses an unmanned aerial vehicle with an anti-impact function, and relates to the technical field of unmanned aerial vehicles, the unmanned aerial vehicle comprises an unmanned aerial vehicle body, anti-impact mechanisms, a fixing rod, a detection mechanism and an adjusting mechanism, the anti-impact mechanisms are fixedly connected to the periphery of the outer wall of the unmanned aerial vehicle body, and the fixing rod is fixedly connected to the center of the top of the unmanned aerial vehicle body; a detection mechanism is fixedly connected to the top of the fixing rod, two adjusting mechanisms are fixedly connected to the bottom of the unmanned aerial vehicle body, an anti-impact mechanism is arranged, the shock resistance and impact resistance of a fuselage and propellers of the unmanned aerial vehicle body are improved, the influence of shock on internal precise elements is reduced, and stable operation of equipment is guaranteed; meanwhile, damage to the machine body and parts is reduced through deformation buffering and energy absorption, and the safety and survivability of the equipment are improved; the detection mechanism is arranged, the obstacles are detected in multiple directions through rotation of the four laser range finders, distance information is transmitted to an external display screen, data support is provided for obstacle avoidance decision making, and collision accidents are avoided.

A landing gear includes a supporting structure, and a damping cylinder connected to a lever which is hinged to the supporting structure about a hinge axis. The lever is movable between a towards end position, in which the wheel is moved towards the hinge axis, and an away end position, in which the wheel is moved away from the hinge axis. The towards and away end positions are on either side of an intermediate position, in which the lever and the cylinder are aligned. The end away position is defined by a stop secured to the supporting structure and against which the lever in the away position is applied to take up the landing forces.

The utility model discloses a landing buffering device of a single-body type hovercar and the single-body type hovercar, the single-body type hovercar is provided with an integrated power device, the integrated power device can be switched between a first position and a second position, and the landing buffering device is fixedly connected with the integrated power device. The landing buffer device comprises an undercarriage and damping wheels; wherein the damping wheels can be supported on the ground in a rolling mode when the integrated power device is located at the first position, and the landing buffering device and the ground can be arranged in a spaced mode when the integrated power device is located at the second position. Therefore, when the single-body type hovercar lands on the ground, the landing buffer device can reduce impact on the single-body type hovercar when the single-body type hovercar makes contact with the ground, and can prevent the integrated power device from colliding with the ground; the landing buffer device and the ground are arranged at an interval, so that the smoothness of the single-body type hovercar walking on the ground is guaranteed.

An aircraft landing gear has a suspension mechanism which has a four-bar linkage that comprises four links rigidly extending between a corresponding four pivots. A lower link of the four-bar linkage supports front and rear wheels, and is movable relative to an upper link between lengthened and shortened positions. A shock absorber urges the four-bar linkage towards the lengthened position. A length of the upper link of the four-bar linkage is adjustable.

A case for carrying loads by an Unmanned Aerial Vehicle (UAV) comprises a first end comprising a first cap and a first opening and a second end comprising a second cap and a second opening, the second opening being smaller than the first opening. The case also comprises a rechargeable battery pack that, when the case is secured to the UAV, is configured to provide a power source for the UAV and the first cap and the second cap each comprising at least one metal connector for providing power to the UAV.

The invention relates to the technical field of aerospace, and discloses a novel aircraft auxiliary landing stabilizing device and a control system thereof.The novel aircraft auxiliary landing stabilizing device comprises an aircraft body, an undercarriage is rotatably connected to the interior of the aircraft body, a fixing plate is arranged in the undercarriage, and a control center is fixedly connected to the outer wall of one side of the fixing plate; a fixing assembly is fixedly connected to the outer wall of the other side of the fixing plate, an adjusting assembly is fixed in the fixing assembly, an air inlet assembly is fixedly connected to the lower surface of the adjusting assembly, an airflow rotating assembly is fixedly connected to the interior of the air inlet assembly, and a transmission assembly is arranged in the fixing shell. And the outer wall of the transmission assembly is fixedly connected with a machine wheel. In the invention, the electric push rod is controlled by the control center, the rotation angle of the guide plate is finally controlled, and the airplane wheels are finally driven to rotate, so that the friction force at the landing moment can be obviously reduced, and the tire wear and overload risk can be reduced.

The invention discloses a linkage mechanism of an undercarriage and a cabin door of an unmanned aerial vehicle, and particularly relates to the field of unmanned aerial vehicles. Comprising a driving rod fixed on a driving cylinder body of the undercarriage; the two ends of the driving rod are movably connected with follow-up connecting rods correspondingly, and the follow-up connecting rods can rotate around the driving rod by a preset angle. The free ends of the two follow-up connecting rods are movably connected to the surfaces of the corresponding cabin doors respectively, and the follow-up connecting rods can move around the cabin doors in a multi-degree-of-freedom mode. Wherein the length of the follow-up connecting rod is determined according to the rotation angle of the undercarriage, the rotation angle of the cabin door, the position of a rotating shaft bearing of the undercarriage, the distance between the driving rod and the rotating shaft bearing of the undercarriage, the distance between the follow-up connecting rod and a cabin door rotating shaft and the position of the rotating shaft bearing of the cabin door. The undercarriage and the cabin door are connected through the driving rod and the follow-up connecting rod, linkage of the undercarriage and the cabin door can be achieved, a complex multi-connecting-rod mechanism is avoided, and the space between the undercarriage and the cabin door can be fully utilized.

The utility model discloses an unmanned aerial vehicle undercarriage, and relates to the technical field of undercarriages. The device comprises a fixing plate and a mounting frame, the top of the mounting frame is fixed to the bottom of the fixing plate, an adjustable supporting assembly is rotatably mounted in the mounting frame, a buffer rod is fixedly mounted at the top of the fixing plate, a lifting plate is fixedly mounted at the top of the buffer rod, a groove is formed in the top of the lifting plate, and a rotary clamping assembly is fixedly mounted in the groove. The top of the lifting plate is provided with a buffer foam plate, and the bottom is fixed with a drawer. Through the adjustable supporting assembly, the ground supporting mode can be changed according to the actual use condition, the height of the base can be adjusted, the undercarriage can be conveniently used on the uneven ground, the stability is better, meanwhile, the unmanned aerial vehicle can be clamped and fixed through the rotary clamping assembly, and the unmanned aerial vehicle can be conveniently and rapidly fixed. And the protection plate can be rotated to protect the top of the unmanned aerial vehicle.

A landing gear assembly for a vehicle, such as a helicopter, includes a linkage coupled to the vehicle and configured to reciprocate between a stowed position and a deployed position. A shock strut forms a part of the linkage. The landing gear assembly further includes a side brace having a first end coupled to the linkage and a second end coupled to the vehicle. The side brace provides a driving force that reciprocates the linkage between the stowed and deployed position. The side brace includes an energy attenuation system that dissipates energy when a compressive load on the side brace exceeds a predetermined threshold.

Disclosed is a method of communicating configuration data of a tire pressure monitoring device configured to be affixed to a wheel in use. The method includes, at the tire pressure monitoring device, receiving (102) a request to confirm configuration data, and responsive to receipt of the request to confirm configuration data, transmitting (104) a configuration data signal which encodes the configuration data. The configuration data signal is configured to be received and understood by a human.

A pneumatic tire (10) is disclosed comprising a carcass (22) and a belt structure (40). The belt structure (40) comprises a plurality of belt layers that include at least one spiral belt layer (60) and at least one zigzag belt layer (70). Each of the at least one spiral belt layers (60) has cords arranged at an angle of 5° or less with respect to an equatorial plane of the pneumatic tire (10) and each of the at least one zigzag belt layers (70) has cords arranged at an angle in a range of from of 2° to 40°, alternatively from 5° to 30°, with respect to the equatorial plane of the pneumatic tire (10) and extending in alternation to turnaround points at each lateral edge of the belt structure (40). A first belt layer of the plurality of belt layers located radially outward of the carcass (22) is one of the at least one spiral belt layers (60). The first belt layer has an axial width less than the axially widest belt layer of the plurality of belt layers. The pneumatic tire (10) further comprises a tread (20) comprising two or more main grooves (17a, 19a, 17b, 19b) extending circumferentially continuously around the pneumatic tire (10) and defining a plurality of ribs (25a, 23a, 21, 23b, 25b) that include an axially outermost rib (25a, 25b) on each lateral side of the tread (20). At 10% to 100% of the rated inflation pressure of the pneumatic tire (10) and no load, each of the two axially outermost ribs (25a, 25b) is radially raised in relation to a respective next nearest rib (23a, 23b) located axially inward of the respective axially outermost rib (25a, 25b).

Landing gear system (5) for an aircraft (1), the landing gear system comprising a nose landing gear (2) and at least one tail landing gear, the tail landing gear being a bogie balancer and comprising at least two wheels, the landing gear system being further equipped with a hybrid braking system comprising at least one friction brake and at least one auxiliary brake providing energy dissipation by means other than friction, at least one of the wheels of the tail landing gear being equipped only with one or more auxiliary brakes and at least one of the wheels of the tail landing gear being equipped only with one or more friction brakes, all the wheels of the tail landing gear being equipped with at least one auxiliary brake or one friction brake. Aircraft equipped with such a landing gear system. FIGURE OF THE ABSTRACT: Fig.1

The invention provides an air-ground combined mobile robot which comprises a flying module, a ground moving module, a platform rack and a control system, the flying module is fixedly connected to one end of the platform rack, and the ground moving module is fixedly connected to the other end of the platform rack; the flight module comprises a multi-rotor structure, and the ground moving module has an advancing mode and a crossing mode; the control system comprises a master controller, a flight control system, a land motion control system, a sensor system and a power supply system, and adopts a master-slave control mode; a multi-rotor structure, a ground moving module with wheel type advancing and foot type obstacle crossing capabilities and a unified control system are highly integrated on a platform rack to form a real single-body land-air amphibious robot, the problems of complexity and reliability of multi-system collaboration are solved, all core function modules are clear in design, interfaces are clear, and the cost is low. And maintenance and upgrading are facilitated.

The rotary shimmy damper comprises an inner cylinder and an outer cylinder rotationally arranged outside the inner cylinder in a sleeving mode, the portion between the inner cylinder and the outer cylinder is divided into a first outer cavity and a second outer cavity which are independent of each other, and a first one-way elastic damping valve set is arranged on the portion, between the first cavity and the second cavity, of the outer cylinder; an inner cavity communicating with the first outer cavity and the second outer cavity is formed in the inner cylinder, and a torsion damping assembly is rotationally arranged in the inner cavity. The first one-way elastic damping valve set comprises conical damping valve bodies and reset springs, a middle cavity is formed in the position, between the first cavity and the second cavity, of the outer cylinder, the conical damping valve bodies are arranged at the left end and the right end of the middle cavity in a sliding mode, and the conical surfaces of the conical damping valve bodies at the left end and the right end are arranged oppositely. A reset spring is arranged at one end of the conical damping valve body, and a center hole with the diameter smaller than the drift diameter of the middle cavity is formed in the center of the conical damping valve body. Circumferential rotation type damping shimmy reduction can be carried out on an external load, and the size of the shimmy damper is effectively reduced while the shimmy reduction effect is guaranteed.

The invention relates to unmanned aerial vehicle equipment, in particular to an unmanned aerial vehicle turning device which comprises a motor, a clutch, a speed reducer, an angle sensor, an electric connector, an output gear, a first protective cover and a second protective cover. The motor is connected with a motor wire harness, the clutch is connected with a clutch wire harness, the angle sensor is connected with an angle sensor wire harness, and the motor, the clutch, the speed reducer, the angle sensor, the motor wire harness, the clutch wire harness and the angle sensor wire harness are sleeved with the first protection cover. The second protection cover is arranged outside the output gear in a sleeved mode, a shell of the speed reducer is provided with a first protruding edge, a second protruding edge and a third protruding edge on the outer edge of the first supporting lug and the outer edge of the second supporting lug, and the first edge, the second edge and the third edge of the notch in the second containing body abut against the first protruding edge, the second protruding edge and the third protruding edge respectively. The protection level is high, and the installation process is more convenient and safer.

The present invention relates to a trolley-type landing gear with a retractable rotating frame, comprising a strut buffer, a frame, wheels, shock absorber cylinders, a double parallelogram mechanism, a retractable actuator cylinder, and a strut coordination rod; the frame is equipped with wheels at the front and rear. By utilizing the inherent characteristics of the motion adder of the double parallelogram mechanism, the present invention isolates the translational and rotational motions of the frame from each other, so that the translational motion of the frame only drives the strut buffers, and the rotational motion of the frame only drives the shock absorbers. The rigid body rotation of the frame is transmitted to the shock absorber via the double parallelogram mechanism and does not affect the strut buffer. In other words, the shock absorber not only performs the function of shock absorption but also performs the function of retracting and extending the landing gear, achieving both functions using a single mechanism.

An aircraft assist system described herein includes an aircraft coupling counterpart attached to a strut of a landing gear of an aircraft, and an assist vehicle. The assist vehicle includes a frame, ground-engaging wheels mounted to the frame, a power source for driving one or more of the ground-engaging wheels, and a vehicle coupling counterpart for engagement with the aircraft coupling counterpart. The aircraft coupling counterpart and the vehicle coupling counterpart define a swivel connection for transferring a propulsive force from the takeoff assist vehicle to the aircraft. The aircraft coupling counterpart is disengageable from the vehicle coupling counterpart by upward movement of the aircraft coupling counterpart relative to the vehicle coupling counterpart.

An aircraft landing gear damping device belongs to the technical field of aircraft damping. The problems that a traditional undercarriage damping structure is poor in damping effect, complex in structure and high in maintenance cost are solved. The mounting frame comprises a mounting plate and two L-shaped plates, the damping mechanism comprises a first damping unit and a second damping unit, the two L-shaped plates are oppositely arranged on the left side and the right side of the lower end face of the mounting plate, the first damping unit comprises two first damping assemblies, and the two first damping assemblies are arranged between the undercarriage and the lower end faces of the corresponding L-shaped plates correspondingly. The second damping unit is arranged in a space defined by the lower end face of the mounting plate and the two L-shaped plates, the left and right ends of the second damping unit are slidably connected with the inner side walls of vertical plates of the two L-shaped plates correspondingly, and the left and right sides of the lower end of the second damping unit are slidably connected with the upper end faces of transverse plates of the two L-shaped plates correspondingly; the upper end of the undercarriage is fixedly connected with the lower end of the second damping unit. The shock absorber can efficiently absorb shock, and is stable in structure, easy to maintain and high in adaptability.

Retaining element (20) comprising elastic support elements configured to secure rotating assembly members (4). Aircraft landing gear wheel equipped with such a retaining element (20). Method for manufacturing such a retaining element (20). Figure for the abstract: Fig. 2

The invention discloses a gyroscope stable hub and an unmanned aerial vehicle, and belongs to the field of balance control of aircrafts. The hub comprises a wheel disc type motor, a first motor cover and a second motor cover, wherein the first motor cover and the second motor cover are packaged at two ends of the wheel disc type motor; the outer end of the first motor cover is connected with the rack through a hub flange plate seat; the wheel disc type motor comprises a hub permanent magnet motor unit and a disc type permanent magnet motor unit which are coaxially arranged, and the hub permanent magnet motor unit and the disc type permanent magnet motor unit share a shaft disc motor stator; a rotor of the hub permanent magnet motor unit is a rim of a sleeve structure and sleeves the periphery of a shaft disc motor stator, and the two ends of the rotor are coaxially and fixedly connected with a first motor cover and a second motor cover respectively. A rotor of the disc type permanent magnet motor unit is a disc type magnetic rotor of a disc structure, is opposite to the end face of one side of the shaft disc motor stator and is rotationally connected between the first motor cover and the second motor cover through a gyro shaft. The problem that in the prior art, the take-off and landing stage of the heavy fixed-wing unmanned aerial vehicle cannot be stably controlled is solved.

The utility model relates to the technical field of undercarriages, in particular to a modular undercarriage with a strong stability mechanism, which comprises a bearing frame, two adjusting plates are fixedly connected to one side of the bearing frame and are symmetrically arranged, an auxiliary bearing frame is fixedly mounted at one end of the bearing frame, and a plurality of auxiliary bearing frames are fixedly mounted at the other end of the bearing frame. The surface of the adjusting plate is rotatably connected with a mounting plate, the surface of the mounting plate is fixedly connected with a first shock absorption supporting column, the first shock absorption supporting column is hollow, and the inner wall of the first shock absorption supporting column is slidably connected with a vertical rod. Kinetic energy generated when the aircraft lands on the runway is converted into electric energy to be transmitted to the super-capacitor module to be stored, so that energy which is originally consumed and wasted in the braking process is recycled, cyclic utilization of the energy is achieved, the overall energy utilization efficiency of the aircraft is improved, dependence on external energy is reduced to a certain degree, and the operation cost is reduced.