Patents
Literature
775results about "Undercarriages" patented technology
Efficacy Topic
Property
Owner
Technical Advancement
Application Domain
Technology Topic
Technology Field Word
Patent Country/Region
Patent Type
Patent Status
Application Year
Inventor
Cryogenic fuel distribution systems including heat exchangers and related methods
Heat exchangers for cryogenic fuel distribution systems and related methods are disclosed herein. An example aircraft disclosed herein includes a cryogenic fuel system including a cryogenic fuel, a hydraulic system including a hydraulic fluid, a gas turbine engine fluidly coupled to the cryogenic fuel system, and a heat exchanger fluidly coupled to the cryogenic fuel system, the heat exchanger is used to exchange heat between the cryogenic fuel and at least one of (1) hydraulic fluid or (2) working fluid thermally coupled to the hydraulic system.
Owner:GE AVIO SRL +1
Broadband sound absorption structure suitable for undercarriage cabin door noise reduction and design method
The invention provides a broadband sound absorption structure suitable for undercarriage cabin door noise reduction and a design method, and belongs to the field of aircraft noise reduction. The sound absorption structure comprises a plurality of perforated plate type Helmholtz cavity unit cells and a plurality of embedded pipe type Helmholtz cavity unit cells. In the perforated plate type unit cells, one or more first through holes are formed in the perforated plate. And in the embedded pipe type unit cells, the embedded pipes penetrate through the perforated holes in the perforated plates and extend into the cavities. Cavities of the two single cells face the same direction, and the perforated plate forms a curved surface conformal with an undercarriage cabin door. The effective length of the neck of the perforated plate is increased by using the embedded pipe, the low-frequency sound absorption performance is improved, the sound absorption performance and the sound absorption bandwidth of the middle-frequency band are improved by using the perforated plate type Helmholtz cavity, meanwhile, the curved surface conformal design is highly matched with the special-shaped cabin door structure, and the sound absorption performance is improved. The low-frequency and medium-frequency sound absorption performance can be guaranteed, and meanwhile the light and thin requirements of an aircraft can be met; and a pure passive mechanical structure is adopted, so that the control complexity and stability risks of an active noise reduction system can be avoided.
Owner:NORTHWESTERN POLYTECHNICAL UNIV +1
Locking system for aircraft landing gear bay doors
A locking system for doors of a deployable aircraft landing gear system includes a spring-biased swing arm configured to be pivotally attached to a body of an aircraft and including a roller at a distal end of the swing arm. The swing arm is configured to engage with a portion of a first landing gear bay door to prevent the first landing gear bay door from opening.
Owner:AMERICAN HONDA MOTOR CO INC
Aircraft landing gear support fixtures
PendingUS20250362196A1Aircraft components testingForce/torque/work measurement apparatus calibration/testingAircraft landingMechanical engineering
Disclosed here is a landing gear support fixture for an aircraft under test having a landing gear. The disclosed landing gear support fixture includes: an axle attachment assembly that is compatibly shaped, sized, and configured to mate with and attach to at least one axle of the landing gear of the aircraft under test; a support platform to support the axle attachment assembly, wherein the support platform is in a fixed position relative to a stationary reference foundation; and a force sensor couplable between the axle attachment assembly and the support platform to provide sensor output associated with load imparted by the landing gear of the aircraft under test.
Owner:GULFSTREAM AEROSPACE CORP
Undercarriage and aircraft
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.
Owner:SICHUAN AEROFUGIA TECH DEV CO LTD
Airplane pneumatic electromagnetic valve sealing structure and machining method thereof
The invention relates to the field of valve sealing structures, and particularly discloses an aircraft pneumatic electromagnetic valve sealing structure and a machining method thereof.The aircraft pneumatic electromagnetic valve sealing structure comprises a sealing structure body, a side wall groove is formed in one end of the sealing structure body, and the sealing structure body comprises any one of a first sealing structure and a second sealing structure; according to the first sealing structure, a plurality of annular bionic grooves which are arranged up and down are formed in the inner circumferential face of the side wall groove, and a plurality of concentrically-distributed annular bionic grooves are formed in the bottom end face of the side wall groove. According to the second sealing structure, a plurality of linear bionic grooves which are distributed in a circumferential array mode are formed in the inner circumferential face of the side wall groove, and a plurality of divergently-distributed linear bionic grooves are formed in the bottom end face of the side wall groove. According to the method, the micro-nano bionic sealing structure is machined on the electromagnetic valve sealing surface through the femtosecond laser micro-nano machining technology, the roughness consistency and the bonding strength of the rubber bonding surface of the pneumatic sealing element are improved, the sealing performance of the pneumatic element is guaranteed, and the reliability of an airplane emergency control system is guaranteed.
Owner:WUHU STATE-OWNED FACTORY OF MACHINING
A processing method for emergency disconnection safety pin of aircraft main landing gear
ActiveCN118833386BMaterial strength using tensile/compressive forcesMaterial strength using steady shearing forcesMechanical engineeringAirplane
The present invention discloses a processing method for an emergency breakaway pin for an aircraft main landing gear. The pin is hollow and cylindrical, with two breakaway slots provided in the inner bore corresponding to two locations bearing shear force. A thickened section is provided between the two breakaway slots, and the inner bore diameter corresponding to the thickened section is smaller than that at other locations. The bottom of the breakaway slot is connected to the straight stepped surfaces on both sides by a rounded transition. The emergency breakaway pin of this solution has a breakaway slot design that not only controls precise breakaway but also limits the breakaway area. The rounded transition between the bottom of the breakaway slot and the straight stepped surfaces on both sides improves fatigue strength, and the thickened section between the two breakaway slots improves static strength. The measured breakaway value can be controlled within a range of ±4% of the set threshold, achieving precise breakaway.
Owner:ORIENTAL BLUE SKY TITANIUM TECH CO LTD
Novel aircraft auxiliary landing stabilizing device and control system thereof
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.
Owner:马云昌 +1
Locking device for movable components, in particular aircraft components such as an aircraft landing gear
The disclosure proposes a locking device for movable components, in particular aircraft components such as an aircraft landing gear, which comprises a hook rotatable about an axis of rotation for receiving a pin portion fixedly arranged on the landing gear, wherein the hook has a U-shaped, C-shaped or V-shaped opening, which is designed receive the pin portion in a locked state in a first rotational position and to release the pin portion in an unlocked state in a second rotational position. The disclosure is characterised in that at least one of the two legs of the U-shaped, C-shaped or V-shaped opening has a non-constant contour in the width direction.
Owner:LIEBHERR AEROSPACE LINDENBERG GMBH
Flying robot
ActiveUS12479607B2Aircraft convertible vehiclesAircraft indicatorsClassical mechanicsMechanical engineering
A flying robot includes a body portion, a propulsion portion including a plurality of propulsion units configured to generate propulsion force by driving rotor blades, the plurality of propulsion units being provided at the body portion, a plurality of leg portions configured to support the body portion, each leg portion of the plurality of leg portions including at least one joint and being configured to be able to change a posture of the leg portion, and a controller configured to control the plurality of leg portions when landing on a landing surface from a flying state, and the controller controls part or all of at least one leg portion among the plurality of leg portions to adjust a tilt of the body portion from when the at least one leg portion comes into contact with the landing surface until when landing on the landing surface is completed.
Owner:THK CO LTD
Seaplane with attachable float frame comprising auxiliary fuel tanks
A seaplane float frame apparatus with extra fuel storage, and a method of installing, comprising: 1) a middle section housing at least one auxiliary fuel storage tank; and 2) two opposing side panels affixed to the middle section, extending outward from about 45-60-degrees from the parallel, each of the two opposing side panels comprising a bottom flat edge fit-able to a float (e.g., carbon composite). The middle section further comprises a fuel pump and a fuel line attached to the auxiliary fuel storage tank(s) and to a main fuel tank within an airplane fuselage-engine. Electrical components enable the pilot, or automatedly as needed, to pump fuel from the frame's tanks. The two opposing side panels comprise triangular shaped cutouts to reduce the float frame's weight and drag, and a built-in steps, a bar, and non-skid coating on the floats to assist in climbing safely into / out of the cockpit.
Owner:CUB CRAFTERS INC
Aircraft system
An aircraft system is disclosed including a hydraulic actuator, an inlet line for supplying hydraulic fluid to the hydraulic actuator, an outlet line for removing hydraulic fluid from the hydraulic actuator, a first one-way valve configured to allow fluid flow along the inlet line in a direction toward the hydraulic actuator, and a second one-way valve configured to allow fluid flow along the outlet line in a direction away from the hydraulic actuator.
Owner:AIRBUS OPERATIONS LTD
All-electric retractable actuator cylinder for aircraft landing gear
The utility model discloses an all-electric retractable actuator cylinder for an aircraft landing gear, which belongs to the technical field of actuator cylinders and comprises an actuator cylinder body and a transmission shaft, the transmission shaft is hermetically mounted on the outer side of the actuator cylinder body in a penetrating and sliding manner, top plates are mounted at two ends of the interior of a connecting piece in a penetrating and sliding manner, and the two top plates are T-shaped. The tops of the two top plates are connected with limiting blocks in an attached mode. According to the all-electric folding and unfolding actuator cylinder for the aircraft landing gear, the top plates are arranged, the top plates are arranged in grooves in the two ends of the interior of the connecting piece in a penetrating and sliding mode through reset springs, then limiting blocks are connected to the top ends of the two top plates in an attached mode, and after a transmission shaft and the connecting piece are disassembled and assembled, the two reset springs can unload force and rebound; therefore, the two top plates can be driven to push the transmission shaft connected with the inner ends of the two limiting blocks to automatically pop out to the outer side of the connecting piece, and auxiliary disassembly and replacement of the connecting piece can be achieved.
Owner:XIAN CHUANGXINSHENGHE LANDING GEAR EQUIP CO LTD
Retractable body mounted landing gear with secondary crash attenuation
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.
Owner:SAFRAN LANDING SYST CANADA INC
Rotary toggle mechanism for landing gear system
ActiveUS20250382050A1Limiting/preventing/returning movement of partsManual control with single controlling memberGear systemControl theory
Systems for activating and deactivating an emergency landing gear system in an aircraft include a rotary toggle mechanism that actuates a switch. When the switch is actuated, the emergency landing gear system is activated and the operation of one or more other aircraft systems may be modified accordingly. The rotary toggle mechanism may be placed in three different states: a ready state, an active state, and a reset state. In the ready state, the switch is not actuated and the emergency landing gear system is not activated. In the active state the switch is actuated and the emergency landing gear system is activated. While the mechanism is in the active state the mechanism cannot be returned to the ready state without first passing through the reset state.
Owner:AMERICAN HONDA MOTOR CO INC
Method and system for comprehensive control of electric pump operation
The application belongs to the field of electromechanical control, and relates to electric pump working control technology, and discloses an electric pump working comprehensive control method and system.The working comprehensive control method comprises the following steps: collecting machine state signals, flight control system state signals and hydraulic pressure of each sub-hydraulic system in a hydraulic system in real time; controlling the opening and closing of the electric pump connected to the sub-hydraulic system according to the machine state signals through a first electric pump control logic and an error prevention working mechanism; and automatically controlling the electric pump connected to each sub-hydraulic system according to the flight control system state signals, the hydraulic pressure and the rest of the electric pump control instructions through a second electric pump control logic, the error prevention working mechanism and a staggered working mechanism.The application can ensure the accuracy of the electric pump working, avoid system damage caused by simultaneous starting of the electric pump, and improve system safety.
Owner:XIAN AVIATION COMPUTING TECH RES INST OF AVIATION IND CORP OF CHINA
aircraft
The application provides an aircraft, comprising a fuselage, a bumper, a connecting mechanism and a landing gear, the cylinder body of the bumper is assembled to the fuselage; the connecting mechanism is hinged to the movable rod of the bumper and the fuselage; and the landing gear is foldably connected to the connecting mechanism. In this way, when the landing gear vibrates, the landing gear can transmit the vibration to the connecting mechanism to drive the connecting mechanism to rotate relative to the fuselage, and then drive the movable rod to slide in the cylinder body to achieve the effect of energy absorption and vibration reduction through the bumper. In addition, compared with the technical solution in the prior art that the bumper is synchronously folded with the landing gear, the aircraft provided by the embodiment of the application does not need to consider the influence of the weight of the bumper on the folding of the landing gear, the weight of the folding part is reduced, and no folding space needs to be reserved for the bumper after the landing gear is folded, which helps to reduce the volume of the aircraft.
Owner:GUANGDONG HUITIAN AEROSPACE TECH CO LTD
Landing gear actuator control device and landing gear
The application relates to the field of aircraft control, and discloses a landing gear actuating cylinder control device and a landing gear, which comprise a controller, a main control circuit and at least one standby control circuit, wherein the main control circuit comprises a detection circuit; the detection circuit is arranged at the landing gear actuating cylinder to generate a detection signal; the controller is used for generating an action instruction according to state information of an airplane and sending the action instruction to the main control circuit, so that the main control circuit controls the landing gear actuating cylinder according to the action instruction; the controller is also connected with the detection unit to acquire the detection signal, and when the detection signal does not satisfy a preset condition, the controller controls the standby control circuit to work and sends the action instruction to the standby control circuit. When the main control circuit fails, the standby control circuit is started to work, so that the stability of the landing gear actuating cylinder control system and the safety of the airplane are improved on the basis of preventing multiple controller interference and motor power disputes, so as to prevent the airplane from being unable to take off or land safely due to the failure of the actuating cylinder.
Owner:SICHUAN AEROSPACE FENGHUO SERVO CONTROL TECH CO LTD
HYDRAULIC SYSTEMS
Owner:AIRBUS OPERATIONS LTD
Durable mechanical undercarriage structure of unmanned aerial vehicle
Owner:HUNAN HAOTIANYI AERO-TECH CO LTD
Aircraft hydraulic system and method for controlling aircraft hydraulic system
PCT designated stageWO2026105785A1Fluid-pressure actuator safetyWith power amplificationThermodynamicsPressure reduction
An aircraft hydraulic system 100 comprises common hydraulic pressure sources 11 and 12 and pressure reduction valves 21 and 22. The common hydraulic pressure sources 11 and 12 supply a shared hydraulic pressure to a low pressure operation unit 103 that is disposed in an aircraft 101 and that operates by a relatively low operating hydraulic pressure and to a high pressure operation unit 102 that is disposed separately from the low pressure operation unit 103 in the aircraft 101 and that operates by a relatively high operating hydraulic pressure. The pressure reduction valves 21 and 22 reduce the hydraulic pressure that is supplied to the low pressure operation unit 103.
Owner:SUMITOMO PRECISION PRODUCTS CO LTD
AIRCRAFT CHASSIS SYSTEM
Owner:AIRBUS OPERATIONS LTD
A crossover machine landing gear and crossover machine
This invention discloses a landing gear and a racing drone, belonging to the field of racing drones. It includes two mounting beams positioned front and rear at the bottom of the drone's fuselage; two support rods symmetrically mounted on one of the mounting beams; two telescopic components symmetrically mounted on the other mounting beam; and two base plates symmetrically mounted at the bottom ends of the support rods and telescopic components. The support rods and telescopic components are arranged in pairs, with each base plate simultaneously universally connected to the bottom end of one pair of support rods and telescopic components. The telescopic components extend and retract to adjust their axial length, changing the tilt angle of the base plate relative to the plane of the two mounting beams. This invention adjusts the forward tilt angle of the racing drone by extending and retracting the length of the rear support legs, enabling optimal launch at the forward tilt angle under different load conditions. After the racing drone leaves the ground, as the load on the landing gear is released, the landing gear automatically returns to a state of uniform front-to-back height in the air, ensuring a safe landing of the racing drone in a horizontal attitude.
Owner:RISING SUN & BLUE SKY (WUHAN) TECH CO LTD
Driving control device and aircraft landing gear folding and unfolding system
The invention discloses a drive control device and an aircraft landing gear extension and retraction system.The drive control device comprises an outer cylinder, a first pipe joint and a second pipe joint, the first pipe joint and the second pipe joint are connected with the outer cylinder, a first cavity is formed in the outer cylinder, and the first pipe joint and the second pipe joint are arranged in the length direction of the outer cylinder; a piston rod is arranged in the first cavity, one end of the piston rod is slidably connected with the inner wall of the first cavity, and the outer end of the piston rod and the second pipe connector are located on the same side of the first pipe connector. A first channel is arranged in the first pipe connector, a first connector is arranged on the first channel, and the first channel is communicated with the first cavity. A pressure relief assembly is arranged on the first pipe joint, and one end of the pressure relief assembly is communicated with the first channel; a second channel is arranged in the second pipe joint, and a second interface and a third interface are arranged on the second channel; a moving assembly and a first elastic element are arranged in the second channel. The driving control device solves the technical problems that in the prior art, an undercarriage folding and unfolding system is large in weight and complex.
Owner:LANDING GEAR ADVANCED MFG
On-line configuration system and method for landing gear control redundancy
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.
Owner:LANDING GEAR ADVANCED MFG
A retractable trolley-type landing gear with a rotating frame
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.
Owner:CHENGDU AIRCRAFT DESIGN INST OF AVIATION IND CORP OF CHINA
Aircraft landing gear assembly
An aircraft landing gear assembly comprising: a ground contacting assembly; a main strut; a mounting bearing arranged for coupling the landing gear assembly to an aircraft such that the main strut supports the aircraft on the ground when the ground contacting assembly is in contact with the ground; a noise-inducing component which, in use, with the landing gear assembly deployed, has a front region and a back region separated by a pair of side regions, such that flight motion of the aircraft causes airflow to encounter the front region followed by the side regions, followed by the back region; and a first flow deflector mounted adjacent to and spaced from a first side region, the first flow deflector having a leading edge and a trailing edge separated by first and second sides and being shaped with a curved profile between the leading edge and trailing edge that is curved towards the back region of the noise-inducing component so as to redirect airflow adjacent the first side region at an angle between 30 to 90 degrees relative to a free stream flow.
Owner:MESSIER DOWTY
Rotary-wing aircraft
This invention provides a technology that allows the main rotor and shaft to be tilted relative to the landing plane in a rotary-wing aircraft using a simple configuration. [Solution] The rotary-wing aircraft comprises a fuselage having a base located at the bottom, a shaft connected to the fuselage so as to rotate around a rotation axis that is inclined at a predetermined first angle with respect to the base, a main rotor connected to the shaft, and a landing gear that contacts the object to be landed on when the rotary-wing aircraft lands. The landing gear includes a pair of skid tubes that define a landing plane, and a pair of cross tubes connecting the pair of skid tubes, each having a first portion extending along the landing plane and a pair of second portions connecting the first portion and the pair of skid tubes. The base is inclined at a predetermined second angle with respect to the first portion and connected directly or indirectly to the first portion so as to the rotation axis inclined with respect to the landing plane.
Owner:KAWASAKI JUKOGYO KK
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
Multi-rotor aircraft with lift-enhanced wings
PendingCN121822799AReduce the tension componentLow energy consumption in flightWing adjustmentsRotocraftFly controlFlight vehicle
The invention discloses a multi-rotor aircraft with lift-enhanced wings, which comprises rotor power devices, a fuselage for mounting airborne equipment and connecting the rotor power devices, and a pair of independent and controllable lift-enhanced wings, the high-lift wings are mounted on the fuselage; when the multi-rotor aircraft with the high-lift wings flies, a flight control algorithm controls the tilting angles of the high-lift wings according to the attitude and the flight speed of the aircraft, so that the high-lift wings are in a proper attack angle state, and proper lift force can be provided for the aircraft. The flying speed can be increased, the cruising ability is improved, and transportation and storage are convenient.
Owner:HANGZHOU YUNJIAN ZHIRONG INFORMATION TECHNOLOGY CO LTD