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Field deployable resonant sensors
ActiveUS20250076154A1Aircraft health monitoring devicesWithout separate inflatable insertsHealth riskEmergency medicine
Resonant sensors for environmental health risk detection are disclosed. A mechanical member may include at least one meso-scale or micro-scale resonator disposed on a surface of the mechanical member. Additionally, the at least one meso-scale or micro-scale resonator may include a plurality of first carbon particles configured to uniquely resonate in response to an electromagnetic ping based at least in part on a concentration level of the first carbon particles within the at least one meso-scale or micro-scale resonator. Further, the at least one meso-scale or micro-scale resonator may be configured to resonate at a first frequency in response to the electromagnetic ping when the mechanical member is in a first state, and may be configured to resonate at a second frequency in response to the electromagnetic ping when the mechanical member is in a second state.
Owner:LYTEN INC
Variable-configuration tilting quad-rotor unmanned aerial vehicle
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.
Owner:哈尔滨哈飞航空工业有限责任公司
Landing gear assemblies, rotorcraft and rotorcraft methods
A landing gear assembly for rotorcraft includes a shock absorber, a ground support assembly and an airframe linkage assembly. The shock absorber includes a force sensor to detect a pressure of an incompressible fluid within the shock absorber and a temperature sensor to detect a temperature of the fluid. The ground support assembly is linked to the shock absorber and includes an axle and a ground contact element movable in relation to the axle. The linkage assembly is linked to the shock absorber and / or the ground support assembly and includes a position sensor to detect movement of the axle between compressed and uncompressed conditions of the shock absorber. Various rotorcraft include one, two, three or more landing gear assemblies and an attitude control system. Various rotorcraft methods process sensor signals from one, two, three or more landing gear assemblies at the attitude control system to provide various rotorcraft functions.
Owner:THE BOEING CO
Convertible drive system
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.
Owner:HYALTA AERONAUTICS INC
Ducted unmanned aerial vehicle structure
PendingCN119389486Areduce widthImprove structural stabilityWheel arrangementsUncrewed vehicleElectric machinery
The invention discloses a ducted unmanned aerial vehicle structure. The device comprises a machine body supporting beam, fixed ducted fans and movable ducted fans are arranged on the left side and the right side of the machine body supporting beam, the fixed ducted fans are arranged on the front side and the rear side of the movable ducted fans, a fixed frame and a telescopic frame are arranged on the machine body supporting beam, and the fixed ducted fans and the machine body supporting beam are fixed. The movable ducted fan and the machine body supporting beam are movably connected left and right, the fixed ducted fan and the movable ducted fan each comprise a ducted body, a motor base is arranged on the inner side of each ducted body, the motor bases and the ducted bodies are fixed through a plurality of guide vanes, motors are fixed to the motor bases, water cooling cavities are formed in the motor bases, and the water cooling cavities are formed in the outer sides of the motors. A cooling water channel is arranged on the inner side of the guide vane. The folding unmanned aerial vehicle has the beneficial effects that the folded unmanned aerial vehicle is of an H-shaped structure, and the trafficability of road transportation or road driving can be met; and the extended unmanned aerial vehicle is of a *-shaped structure, so that the yaw control capability is improved.
Owner:ZHEJIANG CHANGKONG POWER TECH CO LTD
All-electric turning executing mechanism of front wheel of unmanned aerial vehicle and turning anti-swing control method
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.
Owner:BEIJING INST OF SPECIALIZED MACHINERY
Front wheel steering mechanism for miniature ship-borne fixed-wing unmanned aerial vehicle
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.
Owner:LUFEI AVIATION TECHNOLOGY (SUZHOU) CO LTD
Load structure for unmanned aerial vehicle
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.
Owner:JIANGSU FEI RUIDE TECH CO LTD
Rotorcraft with a non-retractable wheel-type landing gear
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.
Owner:AIRBUS HELICOPTERS DEUT GMBH +1
Vertical take-off and landing fixed-wing aircraft
PendingCN119389431Aextended sailing distancestable handlingSupports/holding devicesParachutesFlight vehicleControl theory
The invention discloses a vertical take-off and landing fixed-wing aircraft, and relates to the technical field of aircrafts. According to the invention, the conversion from a multi-rotor flight mode to a fixed-wing flight mode and from the fixed-wing flight mode to the multi-rotor flight mode can be easily realized. Due to the structural layout characteristics of the aircraft, the safety of the aircraft is guaranteed, and the aircraft can be safely and reliably landed according to the fault degree and urgency of the aircraft even if the aircraft breaks down seriously and only forced landing can be selected. Through multi-rotor-wing assisting control, the forced landing buffering function of the telescopic empennage assembly and the safety protection measure of a protection sponge lining in the manned cabin, various safety modes and measures such as an internal safety protection air bag, an external safety protection air bag and a forced landing parachute of the manned cabin can be selectively used according to the fault degree and urgency of the aircraft; and safe or low-damage forced landing of the aircraft is realized.
Owner:CHENGDU RENTIANXING TECHNOLOGY CO LTD
Aircraft brake control system
An aircraft brake control system for controlling anti-skid braking of at least first and second wheels in a wheel set of an aircraft is disclosed. The system includes a control assembly having wheel speed inputs including an input of an indication of the wheel speed of the first wheel, and an input of an indication of the wheel speed of the second wheel, a wheel speed comparator for determining which of the wheel speeds indicated is a lowest wheel speed, and an output for indicating a wheel speed other than the lowest wheel speed. An aircraft landing gear, an aircraft, and methods of braking an aircraft are also disclosed.
Owner:AIRBUS OPERATIONS LTD
Swing reducing device, undercarriage and aircraft
The invention relates to a shimmy damping device, an undercarriage and an aircraft. The shimmy damping device comprises a movable module, a sleeve, a friction piece and an adjusting module, and the movable module is rotatably arranged on a first supporting piece; the sleeve is rotatably arranged on the second supporting piece, the sleeve is arranged outside the movable module in a sleeving mode, and the movable module can reciprocate in the axis direction of the sleeve; the friction piece is arranged on the outer wall of the movable module and is in sliding fit with the inner wall of the sleeve; the adjusting module is arranged on the movable module and used for adjusting the friction force of the friction piece acting on the inner wall of the sleeve. Compared with the prior art, the shimmy damping device can prevent the rolling wheel from shimmy through friction damping generated by the friction piece and the inner wall of the sleeve, the overall weight and size of the structure are small, and therefore the flight safety of the small and light aircraft is guaranteed.
Owner:HUANGPU INST OF MATERIALS
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
Undercarriage and aircraft
ActiveCN119527538AReduce the windward areareduce aerodynamic dragGeometric CADSpecial data processing applicationsFlight vehicleRocker arm
The invention discloses an undercarriage and an aircraft, and relates to the technical field of aircraft structural parts, the undercarriage comprises a front undercarriage and two main undercarriages, the front undercarriage is arranged on the front side of an aircraft body, the front undercarriage comprises a front aircraft wheel and a front buffer supporting column, one end of the front buffer supporting column is connected with the aircraft body and arranged in the aircraft body, and the other end of the front buffer 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 aircraft body respectively, each main undercarriage comprises a rocker arm, a main buffer and a main wheel, the two ends of each rocker arm are a hinged end and a free end respectively, the hinged ends are hinged to the inner side of the aircraft body so that the rocker arms can only swing in the course of the aircraft, and the free ends are connected with the main wheels. A 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 to 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, and the overall performance and endurance of the aircraft are improved.
Owner:SICHUAN AEROFUGIA TECH DEV CO LTD
A multi-rotor wall-climbing robot
ActiveCN114084346BImprove stabilityHigh precisionAnalysing solids using sonic/ultrasonic/infrasonic wavesWheel arrangementsClassical mechanicsMachine
The present application relates to the field of robot technology, and in particular to a multi-rotor wall-climbing robot, including a robot body, a flight component and a wall-climbing component arranged on the body, the robot body is also provided with a rotating structure, the wall-climbing component is arranged at one end of the rotating structure, a pressure propeller is arranged at the other end of the rotating structure away from the wall-climbing component, and the wall-climbing component and the flight component are connected through the rotating structure. The embodiments of the present application aim at the deficiencies of the prior art, effectively solve the problems that the hovering positioning of drones is difficult, they are easily disturbed by environmental factors, and the wall-climbing robots are greatly affected by the wall materials used and the roughness, so that the robot can realize the functions of drone inspection, wall inspection, non-destructive flaw detection, etc.
Owner:HANGZHOU SHENHAO TECH
Rotorcraft with a non-retractable wheel-type landing gear
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.
Owner:AIRBUS HELICOPTERS DEUT GMBH
Multifunctional unmanned aerial vehicle undercarriage
InactiveCN119590662Aincrease the anglereduce blockingAircraft braking arrangementsWheel arrangementsUncrewed vehicleStructural engineering
Owner:TIBET YINGHAN INFORMATION TECHNOLOGY CO LTD
Vertical take-off and landing aircraft landing system, control method and aircraft
ActiveCN119408701Areduce loadreduce plastic deformationAircraft braking arrangementsWheel arrangementsEnergy absorptionAircraft landing
The invention belongs to the technical field of aircrafts, and particularly discloses a vertical take-off and landing aircraft landing system, a control method and an aircraft. The landing system of the vertical take-off and landing aircraft comprises a take-off and landing mechanism, an energy absorption mechanism and a braking mechanism. The landing gear comprises a rack, a supporting frame and aircraft wheels arranged at the lower end of the supporting frame, the energy absorption mechanism is arranged on the rack and used for absorbing kinetic energy generated when the supporting frame is turned outwards, the braking mechanism is used for adjusting braking force of the aircraft wheels so as to adjust the turning amplitude of the supporting frame, and when the aircraft lands, the braking mechanism actively adjusts the friction coefficient between the landing gear and the ground so as to adjust the turning amplitude of the supporting frame. The size of friction acting of the undercarriage and the ground and acting of an undercarriage energy absorption system is adjusted, so that the vertical acceleration of the fuselage of the aircraft is reduced, the fuselage load is reduced, the risk that the fuselage and airborne equipment are damaged due to plastic deformation is reduced, the load transmitted to passengers is reduced, the safety and reliability of the whole aircraft are improved, and safe landing of the aircraft is guaranteed. And the risk that the aircraft is damaged due to hard landing is reduced.
Owner:GUANGDONG HUITIAN AEROSPACE TECH CO LTD
Unmanned aerial vehicle with anti-impact function
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.
Owner:QUANZHOU NORMAL UNIV
Aircraft wheel and brake assembly
ActiveUS12221081B2Braking element arrangementsAircraft brake actuating mechanismsActuatorControl theory
An aircraft wheel and brake assembly includes a wheel, a brake configured to brake the wheel, and a measurement device configured to measure the speed of rotation of the wheel. The brake includes at least one friction member, an actuator support, and at least one brake actuator carried by the actuator support and configured to exert a braking force selectively on the friction member. The measurement device includes a target and a sensing component for producing a measurement signal representative of the speed of rotation of the target. The aircraft wheel and brake assembly is configured in such a manner that, when assembled, the target is constrained to rotate with the wheel and the sensing component is mounted on the actuator support. The target and the sensing component is configured in such a manner that the sensing component detects rotation of the target.
Owner:SAFRAN LANDING SYSTEMS
Landing gear system with magnetorheological damper
A landing gear system may include: a casing coupled to a fuselage of an aircraft, such as an urban air mobility vehicle; a steering, one side of which is inserted into the casing and the other side of which is connected to a tire; a magnetorheological (MR) damper including a cylinder coupled to the casing and a piston coupled to the steering rod; a sensor unit configured to measure a condition of the urban air mobility vehicle; and a controller configured to control damping force of the MR damper based on measurement data of the sensor unit. The sensor unit may include a first sensor for measuring a stroke of the MR damper and a second sensor for measuring an acceleration of the casing.
Owner:HYUNDAI MOTOR CO LTD +1
Variable-length landing gear and aircraft equipped with such a landing gear
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.
Owner:SAFRAN LANDING SYSTEMS
Unmanned aerial vehicle driving module with switchable water propeller and air propeller, unmanned aerial vehicle and switching method
The invention relates to the technical field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle driving module capable of switching a water propeller and an air propeller, an unmanned aerial vehicle and a switching method.The driving module capable of switching the water propeller and the air propeller comprises the water propeller, the air propeller, a motor, a motor mounting base, a first one-way bearing and a second one-way bearing, and the motor is provided with double output shafts and is mounted on the motor mounting base; inner and outer rings of the first one-way bearing are fixedly connected with an output shaft on one side of the motor and the empty paddle respectively, inner and outer rings of the second one-way bearing are fixedly connected with an output shaft on the other side of the motor and the water paddle respectively, and the water paddle is fixedly connected with the walking wheel; speed reducers with different reduction ratios can be arranged for empty propellers or water propellers according to needs. According to the scheme, the motors are controlled to rotate forwards or backwards to drive the empty propellers or the water propellers / the walking wheels to rotate, air flight, underwater sneaking, land movement and cross-domain movement switching are achieved in cooperation with the variable structure design of the unmanned aerial vehicle, and the integration and control complexity of the triphibian unmanned aerial vehicle is reduced.
Owner:GUANGDONG UNIV OF TECH
Tail airplane wheel anti-deflection mechanism capable of being manually unlocked and automatically locked
A tail airplane wheel anti-deflection mechanism capable of being manually unlocked and automatically locked comprises a shell, a piston, a lock pin assembly, a touch rod, a lock washer, a limiting nut, a spring, a manual rod and a wheel fork hole, the piston penetrates through an inner hole of the shell, the manual rod is located in the piston and coaxially arranged with the piston, the manual rod extends out of the end of the piston, the manual rod can slide in the piston, and the lock pin assembly is located in the shell. The position, extending out of the piston, of the manual rod is sleeved with a spring and a limiting nut, the spring is located in an inner hole of the limiting nut, the lock pin assembly comprises a U-shaped connector, a self-locking nut, a pin rod, a knuckle bearing and a lock pin, the U-shaped connector is provided with a through hole, the lock pin is provided with the knuckle bearing, and the pin rod penetrates through the knuckle bearing and the through hole of the U-shaped connector to connect the lock pin with the U-shaped connector. The U-shaped connector is connected with the manual rod through threads, the touch rod is arranged between the U-shaped connector and the limiting nut in a sleeved mode, a lock washer is arranged between the touch rod and the limiting nut, and the end, away from the U-shaped connector, of the lock pin extends into a wheel fork hole.
Owner:GUIZHOU XINAN AVIATION MACHINING CO LTD
Landing buffering device of single-body type hovercar and single-body type hovercar
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.
Owner:TSINGHUA UNIVERSITY
Aircraft notification system for a blended wing body aircraft and method of use
An aircraft notification system, the aircraft notification system having a processor and a memory communicatively connected to the processor, the memory containing instructions configuring the processor to receive aircraft angle data from a blended wing body aircraft (BWB) having a main body and a wing with no clear demarcation between the wings and the main body along a leading edge of the aircraft, determine an aircraft orientation as a function of the aircraft angle data, wherein the aircraft orientation comprises at least a pitch angle of the BWB while the BWB is in contact with a ground surface, transmit the aircraft orientation to an aircraft display system and visually display the aircraft orientation through the aircraft display system.
Owner:JETZERO INC
Aircraft landing gear
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.
Owner:AIRBUS OPERATIONS LTD
Axial locking device for a first tubular element received for adjustment in a second tubular element
Axial locking device (100) of a first tubular element (20) received to fit in a second tubular element (E), the locking device comprising a tubular body (101) having an external annular groove (101.2) in which a ring (102) is mounted to slide along a longitudinal axis (Y101) of the body between a locking position and a release position, the ring comprising a crown (102.1) having a front face from which extend in axial projection external elastically deformable gripping claws (102.2) between a radially projecting state of the body and a retracted state towards the interior of the body, and the groove of the body comprising a bottom (101.7) shaped to maintain the claws in their projecting state when the ring is in the locking position, and to allow the claws to move from the projecting state to the retracted state when the ring is in the release position. FIGURE FROM THE ABRIDGED: Fig. 5
Owner:SAFRAN LANDING SYSTEMS
Strut and landing gear including strut
The present disclosure relates to a strut and a landing gear including the strut, and more particularly, to an disclosure in which a strut is formed of a curved pipe formed of a flexible body to reduce a weight of a component, and at the same time, an impact load of the strut and the landing gear is alleviated through a design of the physical properties and shape of the strut.
Owner:KOREA AEROSPACE RES INST
Payload container with power supply for unmanned systems
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.
Owner:UNITED PARCEL SERVICE OF AMERICAN INC