249 results about "Landing gear" patented technology

This invention discloses a landing buffer device for unmanned aerial vehicles (UAVs), relating to the field of aviation equipment technology. By integrating the roller body and the sliding plate as two grounding structures onto the landing gear, the device can quickly switch operating modes according to ground conditions through the linkage of the piston cylinder and piston rod. On flat ground, the roller is used first to reduce gliding resistance, while on muddy or slippery ground, the sliding plate is used for grounding, effectively preventing roller jamming and enhancing all-terrain adaptability and landing safety. Simultaneously, the mechanical buffer composed of a second and third spring, combined with the hydraulic damping buffer composed of buffer components, forms a highly efficient double-layer energy-absorbing buffer structure, which to a certain extent alleviates the damage to the aircraft and equipment caused by landing impact, thus improving the landing safety of the UAV.

The utility model relates to the technical field of aircraft, and disclose a kind of movable landing gear fairing, including landing gear and upper fairing, the one end of landing gear is provided with mounting hole, mounting hole is provided with multiple, and pass through upper fairing and enter aircraft, by the mounting hole and aircraft fixed connection, can be fixed by bolt or bolt etc. detachable fixed mode, the upper fairing is fixedly connected with aircraft. By adopting the structure form of one end without connection, the deformation of landing gear can be better absorbed, the inside is filled with foaming material with good compression, effectively supporting fairing, thereby improving stability, solving the problem that fairing is prone to deformation damage, and internal support is insufficient, and stability is poor.

A kind of airplane nose landing gear turning performance test bench and test method contain nose landing gear test piece, rigid support frame and jacking device, the body of nose landing gear test piece is fixed on rigid support frame, wheel is supported on jacking device, turning mechanism drives the top plate of jacking device top by fixed shaft along with wheel rotation, the fixed shaft is connected with a loading actuator, the telescopic end of loading actuator is hinged with one end of fixed shaft, the other end of loading actuator is hinged on support frame by connecting seat, the loading actuator is controlled by torque loading controller, when carrying out turning performance test, nose inner cylinder and wheel are compressed using jacking device, so that wheel is in turnable state;According to the turning angle of wheel, predetermined torque is applied to fixed shaft using torque loading actuator.

The application discloses an online configuration system and method for landing gear control redundancy, wherein a comprehensive control system publishes a redundancy scheme according to system working states and application scene requirements; a redundancy monitoring module analyzes redundancy configuration and scheduling strategy information according to the received redundancy scheme, realizes online redundancy configuration and recombination of a control module, carries out redundancy management on the control module according to the redundancy strategy, monitors the health state of the control module and reports the comprehensive control system, and outputs an effective driving signal to an element driving module; a landing gear control signal is provided for the control module by a landing gear control device; and the control module outputs a driving signal to the element driving module after logical calculation according to the received landing gear control signal. The application realizes online on-demand configuration of control redundancy and dynamic management of redundancy scheduling strategy.

An aircraft dolly includes a plate having opposing mirror-imaged longitudinal sides. Each side includes a continuous first portion and a second portion of spaced-apart fingers contiguous with the first portion. A support disposed at each side of the plate includes a tube of triangular cross-section. The tube has a first leg, a second leg inboard of the first leg and coupled thereto, and a third leg consisting of the first portion of the plate extending between the first and second legs. Each support also includes a horizontal member coupled to the tube and extending over the plate's fingers, and a set of bracing members coupled to the fingers and the horizontal member. Casters are coupled to each horizontal member with each caster disposed between two adjacent fingers. One caster at each side is spring-biased away from its horizontal member. A ramp engages the plate and a ground surface.

The application relates to the technical field of unmanned aerial vehicle structure design and optimization, and discloses a layout optimization method based on an unmanned aerial vehicle landing gear system. The method comprises the following steps: a three-dimensional design model of the landing gear is constructed; real flight attitude data and a load spectrum are imported; stress nephograms and displacement fields under multiple working conditions are dynamically generated to accurately identify a region to be optimized; preset layout rule library is used for iterative adjustment; component layout is optimized until mechanical indexes are met; the optimized model is compared with a historical failure case database; a risk component list with geometric or mechanical similarity is extracted; and local reinforcement or topological reconstruction is carried out according to the risk component list to generate a final scheme. The method fuses dynamic load analysis and historical failure data, improves the accuracy of layout design, and identifies and prevents potential structural failure risks.

The application provides an airplane main landing gear simulation test device, a test load vehicle and a control method, relates to the technical field of flight test devices, and solves the technical problem that the main landing gear of the test load vehicle cannot be lifted with the change of the load, resulting in errors in the test results and low precision. The airplane main landing gear simulation test device and the test load vehicle comprise a main landing gear body, a left wheel assembly and a right wheel assembly, a wheel frame upper joint, a wheel frame lower joint and a hydraulic drive mechanism are arranged between the left wheel assembly and the main landing gear body and between the right wheel assembly and the main landing gear body, the wheel frame upper joint is rotationally connected to both ends of the main landing gear body, one end of the wheel frame lower joint is rotationally connected to the wheel frame upper joint, the other end of the wheel frame lower joint is connected to the left wheel assembly or the right wheel assembly, and the hydraulic drive mechanism is connected between the wheel frame upper joint and the wheel frame lower joint. The application is used for providing an airplane main landing gear simulation test device and a test load vehicle for improving the accuracy of test results.

The application provides a three-stage throttle valve for an anti-crash landing gear, which comprises a valve body, a first plane, a second plane, an upper circumferential surface and an upper counterbore; the upper circumferential surface is arranged between the first plane and the second plane, and the upper counterbore is arranged on the second plane; a first oil hole is arranged on the first plane; a second oil hole is arranged on the upper circumferential surface; and a third oil hole is arranged on the circumferential surface of the upper counterbore; the first plane and the second plane are both circular ring surfaces, and the outer diameter of the first plane is larger than that of the second plane; the three-stage throttle valve can meet the load control requirements in the large-span sinking speed range, has a low installation space, controllable damping effect, no strict requirement on the buffer assembly and can be used for the design of the anti-crash landing gear.

This utility model discloses a pluggable roller connector for aircraft landing gear that avoids the impact of harsh environments. It includes a connector with a roller inserted at its lower end. The outer sides of the bolts and nuts are respectively provided with spiral grooves on the connector, and protective covers are spirally wound within each spiral groove. Each protective cover has a rubber plate on its outer wall. The protective covers of this pluggable roller connector for aircraft landing gear, which avoids the impact of harsh environments, form a spiral locking structure with the connector through the spiral grooves. This spirally installed protective cover protects the bolts and related components, thus preventing the connecting parts between the connectors from being affected by harsh external environments. The rubber pads of this device, through locking blocks and spiral blocks, form a spiral locking structure with the protective covers. This spirally installed rubber pad further limits the movement of the bolts and nuts and provides shock absorption protection, thereby increasing the stability of the connector connecting parts.

A drone flight collision avoidance device, belonging to the field of aircraft technology, addresses the problem that existing drone landing gears are mostly fixed rigid support structures, only suitable for flat, hard ground, and prone to tipping over or sinking on inclined, soft, or gravel surfaces. The invention includes an aircraft shell, with a first camera and a second camera fixedly installed on the side wall of the shell. A lifting structure is fixedly installed in the inner cavity at the bottom of the shell, and a sponge anti-slip plate is fixedly installed at the bottom of the lifting structure. This invention uses the second camera to identify ground conditions, and in conjunction with a retractable landing structure and balancing components, relies on a balance sensor to calibrate the levelness of the balancing platform in real time. This allows for the creation of a horizontal landing reference surface on uneven ground, significantly overcoming landing site limitations and effectively avoiding drone tipping and fuselage damage caused by tilted landings. It significantly improves landing adaptability and safety in complex outdoor environments.

The utility model relates to a kind of promotion performance unmanned aerial vehicle with shell that can be quickly replaced, to solve the unmanned aerial vehicle performance or promotion problem in small range scene. The unmanned aerial vehicle is mainly composed of rotor unmanned aerial vehicle, upper shell and lower shell. Upper shell is connected with the upper end of the middle part of rotor unmanned aerial vehicle by fixed column, and the power box of lower shell supplies power for it, and the two are fixedly connected by upper guide column and lower guide column. Upper shell and lower shell are provided with air guide opening composed of air guide groove in relative position with rotor. Lower shell is provided with switch and power supply port with one-way insertion device outside, and landing gear is mounted on the bottom. When using, shell can be quickly replaced, power supply is connected and started, and promotion performance is carried out by using its flexible flight characteristics in small range. The utility model has the advantages of stable structure, convenient use, adaptability to various scenes, etc., effectively improves the applicability and effect of unmanned aerial vehicle promotion performance.

Aircraft landing gear system (100, 200, 300), comprising actuators associated with the landing gear and supplied with pressurized hydraulic fluid by a hydraulic circuit (10; 15), including at least hatch and landing gear attachment boxes (106, 109, 206, 209, 306, 309), the aircraft comprising emergency extension means (20) capable of ensuring the release of the hatches and landing gear to cause the landing gear to extend under the effect of gravity in the event of failure of the hydraulic circuit. According to the invention, the emergency extension means comprise a pyrotechnic device (50) adapted to generate, in a controlled manner, pressurized gas acting on a first face of a piston (40) sliding with a seal in a chamber (30) such that a second face of the piston, in contact with the hydraulic fluid, transmits the pressure of the gas thus produced to at least the attachment boxes via the hydraulic fluid. FIGURE IN ABRIDGED FORM: Fig. 2

The utility model discloses a kind of front landing gear torsion arm dismounting practical operation rack, it includes fixed support, operating plate, torsion arm practical operation model and torsion arm pin assembly on the torsion arm of aircraft front landing gear, the upper surface of fixed support is fixed with two operating plates, the lower of operating plate is equipped with fixed tray, torsion arm practical operation model is respectively equipped in the front of operating plate, the connection between torsion arm practical operation model and operating plate can be disassembled, the front end of torsion arm practical operation model is equipped with left and right torsion arm, torsion arm pin assembly is connected on each torsion arm practical operation model left and right torsion arm. Through the utility model, the entire dismounting process of torsion arm pin assembly of aircraft front landing gear torsion arm can be carried out practical operation training.

An aircraft having a landing gear provided with a stand and a pivoting assembly, the landing gear having a pivot locking system comprising a movable locking finger and a passage provided in a base. A monitoring system is configured to determine the presence of a risk of sudden yaw movement of the aircraft in the event of a take-off or an unlocking of the landing gear when the locking finger is in the locked mode on the ground, the monitoring system being configured to emit a risk signal to a processing system following a determination of the presence of the risk of sudden yaw movement.

This invention discloses a camera gimbal based on a multi-rotor drone, belonging to the field of drone technology. The drone part includes a center plate main body, a center plate upper plate mounted on top of the center plate main body, landing gear mounted below the center plate main body, and an onboard computer and camera mounted on the center plate upper plate. Sensors are mounted between the center plate main body and the center plate upper plate, and an optical flow meter is mounted below the center plate main body. A 4000mAh 4S large battery is mounted between the landing gear and the center plate main body. The camera of the drone is fixed by a dedicated camera gimbal. A pressure sensor is placed in the center of the camera gimbal's groove. For most monocular and binocular camera models on the market, when placed on the gimbal, the pressure sensor senses the weight and controls the fixing clamps on both sides of the gimbal to automatically clamp the camera. The fixing clamps have a certain angle of change in all directions, allowing the camera to adjust the field of view in all directions (up, down, left, and right).

This invention discloses a hybrid configuration high-payload unmanned helicopter, belonging to the field of unmanned aerial vehicle (UAV) technology. It includes a fuselage with symmetrically detachable wings on both sides. Two rotor systems are mounted on the top of the fuselage along its longitudinal axis, a tail thrust system is mounted at the rear, and landing gear is mounted at the bottom. Internally, the fuselage houses a synchronous transmission system, a power system, and a control system. The power system provides power and transmits it to the two rotor systems and the tail thrust system via the synchronous transmission system. The control system controls flight attitude, transmits and receives commands, and processes data. This invention utilizes tandem rotors to provide primary lift, combined with the auxiliary lift from the detachable wings to reduce cruise power consumption. The tail thrust system enhances forward speed and attitude control. The modular, quick-release structure significantly improves transportation and maintenance convenience, effectively addressing the limitations of existing single-configuration UAV helicopters in simultaneously achieving high payload, long endurance, and high maneuverability.

The application provides a precise alignment device for unmanned aerial vehicle, and relates to the technical field of aircraft landing gear, which comprises an unmanned aerial vehicle body, a landing gear and a charging rod, a plurality of adaptive buffer assemblies are installed on the edge of the landing gear, each assembly comprises a hinged seat, a supporting leg and an adjusting arm driven by a motor, forms a multi-bionic leg structure, can be independently adjusted according to the topography, realizes stable and horizontal landing, and the landing gear is also provided with an alignment assembly, which comprises a fixed seat, a floating seat and a lifting seat, the floating seat realizes horizontal universal movement through a connecting rod mechanism driven by a motor, the lifting seat realizes vertical lifting through an electric telescopic rod, and finally drives the charging rod at the bottom to make position fine adjustment, the application solves the problem that the traditional fixed landing gear cannot adapt to the terrain, leading to inaccurate docking, realizes stable landing of the unmanned aerial vehicle on the complex ground and high-precision automatic alignment of the charging rod, and improves the operation efficiency and reliability.

This invention discloses a nose landing gear assembly structure, comprising: a nose landing gear body with a first connecting member thereon; a wheel mounting bracket with a first connecting lug, a second connecting lug, and a second connecting member thereon, the first connecting lug being used to connect a wheel; a buffer joint, one end of which is hinged to the second connecting lug and the other end of which is connected to the nose landing gear body; a spring, both ends of which are respectively connected to the first connecting member and the second connecting member; and a load transfer assembly detachably connected to the fuselage, the end of the nose landing gear body being assembled in the load transfer assembly; the load transfer assembly comprising: a force transmission frame detachably connected to the fuselage for transmitting loads perpendicular to the fuselage, the end of the nose landing gear body being assembled in the force transmission frame; a force transmission beam detachably connected to the fuselage, the force transmission beam also being connected to the force transmission frame for transmitting directional loads; and a longitudinal beam detachably connected to the fuselage, the longitudinal beam also being connected to the force transmission beam for transmitting directional loads.

This invention pertains to the field of drone landing pads, specifically a universal drone landing pad and its control method. The landing pad's upper surface features two long and two short mechanical rods, which position and fix the drone in the upper left corner after landing. One of the short and one long mechanical rods can move longitudinally and laterally, respectively, and each rod contains an embedded magnet. Below the landing pad, at corresponding positions, is a short and one long electromagnetic drive device, containing an electromagnet with opposite polarity to the upper rod and a multi-axis accelerometer. The sensor detects the drone's landing status through longitudinal acceleration and calculates the movement distance through horizontal acceleration to determine whether the landing gear is securely fastened. The electromagnetic drive device uses magnetic attraction to move the upper mechanical rod horizontally, and the lateral drive device also integrates a wireless charging coil. This invention is compatible with multiple drone models and various charging power levels, eliminating the need for complex mechanical alignment and structures such as hangar covers and lifting platforms, significantly reducing costs while maintaining protection levels and reliability.

The present application relates to the technical field of aircraft landing gears, and provides an aircraft landing gear stay lock. The landing gear stay lock comprises: a front lock stay, a rear lock stay, an unlocking rocker arm, an unlocking actuator cylinder, locking damping actuator cylinders, and locking springs. One end of the front lock stay is connected to a landing gear stay, and the other end of the front lock stay is hingedly connected to the rear lock stay. The other end of the rear lock stay is hingedly connected to a landing gear strut and is hingedly connected to the locking damping actuator cylinders. The unlocking rocker arm is arranged at the position where the front lock stay is hingedly connected to the rear lock stay. One end of the unlocking actuator cylinder is connected to the front lock stay, and the other end thereof is connected to the unlocking rocker arm. One end of each locking damping actuator cylinder is hingedly connected to the rear lock stay, and the other end thereof is connected to the corresponding locking spring. The other end of the locking spring is connected to the front lock stay. Respective ends of each locking spring and the corresponding locking damping actuator cylinder which are connected are arranged on the landing gear strut.

The application discloses a simulation analysis method for an aircraft landing gear tire under heavy landing impact load, and relates to the technical field of aeronautical engineering and computational mechanics. First, in the tread and sidewall rubber area, the micro-heterogeneity of the rubber material in the tire is equivalent to the super-elastic mechanical behavior of the macro-continuous medium based on the homogenization theory. This process avoids the extremely dense mesh and complex constitutive relationship required for depicting the micro-features such as filler distribution and interface effect in the traditional model. Then, the rebar element representing force transmission under impact load is created in the pre-constructed rubber matrix grid, and the rebar element is coupled with the rubber matrix. The simplified coupled model can accurately capture the anisotropic stiffness, main force transmission path and reinforcement effect of the cord-rubber composite structure, so as to finally stably and accurately simulate the transient impact process of the tire under heavy landing impact load, which includes the triple nonlinearity of geometry, material and contact.

The present application relates to the technical field of aircrafts, and discloses an aircraft ground towing trailer. The aircraft ground towing trailer of the present application is used for lifting and towing an aircraft, and comprises a towing portion and a frame portion capable of moving horizontally and up and down by means of the towing portion. The frame portion can enter and exit an area below the aircraft under the action of the towing portion, and a plurality of connecting devices on two sides of the frame portion can individually move close to and connect to a landing gear of the aircraft. The aircraft ground towing trailer of the present application can conveniently enter the area below the aircraft, especially in the case where the ground area is uneven, the landing gear of the aircraft is supported and connected by means of the movable connecting devices, so as to complete the towing work of the aircraft.

An electrohydraulic system for controlling a landing gear of an aircraft, said landing gear comprising a plurality of retractable landing gear units each provided with at least one wheel. Said system comprises two braking devices for braking said wheel of two landing gear units, one movement device per landing gear unit for moving a landing gear unit relative to a housing of said aircraft, and two hydraulic units, hydraulically connected to said movement devices and to at least one of said braking devices. Each hydraulic unit comprises a reservoir containing a fluid, a pump driven by an electric pump motor and a distributor configured to distribute said fluid to said at least one braking device and to said movement devices, by means of braking, extension, retraction and discharge valves.

This invention discloses a low-power wireless temperature and pressure sensor for aircraft, belonging to the field of aircraft temperature and pressure monitoring. It includes a temperature and pressure core, a control component, a battery component, and an antenna installed within the battery component. The outer shell of the temperature and pressure core connects to an interface corresponding to an aircraft wheel or landing gear buffer, used to sense the temperature and pressure data of the medium within the interface and transmit the data to the control component. The control component, installed inside the outer shell of the temperature and pressure core, processes the temperature and pressure data and transmits it to the battery component. The battery component, installed at the end of the temperature and pressure core furthest from the interface, supplies power to the control component and the temperature and pressure core, and transmits the processed temperature and pressure data to the antenna. The antenna transmits the temperature and pressure data radio frequency to a host computer. This invention enables temperature and pressure monitoring of aircraft wheels or landing gear buffers and wireless transmission to a host computer, solving the problems of existing wired pressure monitoring devices being complex to install, easily damaged, and unable to simultaneously monitor temperature information.

The utility model belongs to the technical field of unmanned plane, concretely relates to a retractable landing gear, including containing frame, landing support, limiting component and telescopic push rod. The utility model discloses the rotation direction adjustment is toward the advancing direction of unmanned plane when the landing support is stored in the internal storage cavity of containing frame, and when the landing support rotates to the vertical state, limiting support is realized by utilizing limiting component, so that in the ground taxiing stage of unmanned plane, the reverse torque borne by the landing support will not be transmitted to the telescopic push rod, effectively reduces the abrasion and fatigue damage of telescopic push rod, guarantees its stability in the long -term use process, and then prolongs the service life, and reduces maintenance cost and replacement frequency.

The present application relates to the field of aviation brake wheel, in particular to a novel single-web aircraft brake master wheel, comprising: a brake assembly and a wheel assembly arranged on the landing gear shaft, the wheel assembly and the brake assembly are installed on the landing gear shaft to form the single-web aircraft brake master wheel, wherein the outer ring of the heat sink assembly and the inner wall of the outer cylinder of the hub assembly form a first heat dissipation channel, the inner ring of the brake shell assembly and the outer wall of the inner cylinder of the hub assembly form a second heat dissipation channel, the second heat dissipation channel is communicated with the through hole arranged on the end surface of the brake shell assembly, the airflow output by the cooling fan assembly in the air collecting cavity passes through the heat dissipation holes arranged on the hub web, the first heat dissipation channel and the second heat dissipation channel to take the heat of the heat sink assembly to the outside of the brake assembly. The present application can dissipate the radiation heat of the heat sink assembly to the atmosphere outside the aviation wheel, greatly improving the cooling efficiency of the cooling fan on the heat sink assembly.

The application belongs to the field of comprehensive strength, and relates to a load calculation method and device of a helicopter auxiliary landing device. After the helicopter is stopped on the deck, the deck device fixes the lower end of the probe rod, and the external load borne by the helicopter includes gravity, inertia load caused by ship movement and wind load; the support reaction force is provided by the tire and the auxiliary landing device; all the friction forces are borne by the main wheel, and the tail wheel is a steering wheel and does not bear the friction force; the method comprises the following steps: stress analysis is carried out on the fixed helicopter, and a load balance equation is established; and the load of the helicopter auxiliary landing device is solved according to the load balance equation.

The utility model relates to a skid -type undercarriage drop test device, including gantry, electric hoist, electromagnet, metal section tool rest, counterweight, the metal section tool rest is used for installing counterweight, and still include the undercarriage installation tool of skid -type undercarriage, electric hoist fixed mounting is below the gantry, is used for driving the lift of electromagnet, the electromagnet can adsorb the metal section tool rest when electrification.

The application belongs to the technical field of aircraft hoisting design, and particularly relates to an aircraft hoisting tool based on a main landing gear support and a main bearing frame, which comprises a hoisting frame, a top hoisting ring, a bottom front bearing crossbeam, and a bottom main landing gear connecting clamp. The hoisting frame is isosceles triangular and horizontally arranged. The top hoisting ring is above the hoisting frame and above the gravity center of the hoisting frame, and is connected to three corner parts of the hoisting frame through a diagonal cable. The bottom front bearing crossbeam is below the hoisting frame and is connected to the top corner of the hoisting frame through a front hoisting cable to bear below the main bearing front frame part of the aircraft. The bottom landing gear connecting clamp has two and is used to be clamped to two main landing gear supports of the aircraft. The two bottom landing gear connecting clamps are below the hoisting frame and are connected to the bottom edges of the hoisting frame through rear hoisting cables.