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Monitoring a mechanism or a component thereof
A system for detecting a state of a mechanism includes processing circuitry. The mechanism includes multiple components, at least some of which are capable of moving relative to each other. At least one state is specified for the mechanism, based on the alignment of the mechanism components. The processing circuitry identifies, within image data of the mechanism, reference points on at least two of the components. Based on respective locations of the reference points, it determines whether the components of mechanism are in one of the specified alignments (i.e. states), and outputs an indicator.
Owner:ODYSIGHT AI LTD
Bipedal robot with integrated thruster-assisted locomotion
A bipedal robot having a legged assembly and an aerial assembly is described. The legged assembly includes two legs, each leg having a hip frontal joint, a hip sagittal joint, and a knee joint. The aerial assembly includes two thrusters mounted on a carbon fiber-aluminum composite mount. Actuators for the joints include 3D printed housings with embedded components. A controller generates walking trajectories and controls the thrusters to assist with stabilization and obstacle traversal. The robot is capable of dynamic multimodal locomotion, combining legged movement with thruster-assisted stabilization and jumping to navigate challenging terrain.
Owner:NORTHEASTERN UNIV (US) +1
Aircraft landing gear noise reduction device and method with miniature metal wire wound on surface
The invention relates to the field of aviation noise control, and provides an aircraft landing gear noise reduction device and method based on micro metal wire spiral winding. The device part comprises a metal wire and a metal wire fixing buckle, the metal wire is fixed through the metal wire fixing buckle, and meanwhile the size and material parameters of the metal wire are designed in a targeted mode. In the method part, the designed metal wire is wound on a cylindrical bluff body part, possibly generating vortex shedding and vortex-fixing interference, on the nose gear in a spiral winding manner, and the two ends and the axial interval position of the metal wire are fixed through the metal wire fixing buckles, so that the metal wire is ensured to be fastened. Therefore, through the wound metal wires, single-frequency noise in the over-top direction caused by falling of a towing rod vortex can be effectively eliminated, broadband noise is reduced, and the noise control capability of an airplane is improved. The method is suitable for various civil aircraft types, and has the advantages of being simple in structure, remarkable in noise reduction effect, high in practicability, high in adaptability and the like.
Owner:BEIHANG UNIV
A flapping-wing aircraft capable of ejection and taking off and having a sweep-twist mechanism
The present invention discloses a flapping-wing aircraft capable of catapult takeoff and having a sweep-torsion mechanism, belonging to the field of aircraft technology. The aircraft comprises: a fuselage frame, left and right flapping wings, a passive torsion mechanism, a sweep mechanism, a catapult takeoff mechanism, a transmission flapping mechanism, and a tail rudder, wherein: a passive torsion mechanism and a sweep mechanism are provided at the roots of the left and right flapping wings, the catapult takeoff mechanism is provided in the middle of the fuselage, and a hip joint, thigh, ankle joint, calf, foot, and toe joint are provided from top to bottom, the inner and outer sides of the hip joint are controlled by a servo motor for relative rotation, the ankle joint and toe joint are provided with elastic energy storage torsion springs, a synchronous pulley and its drive mechanism are provided between the outer side of the hip joint and the outer side of the ankle joint to control the relative rotation between the thigh and the calf, and perform energy storage for catapult takeoff. In summary, the aircraft can perform catapult takeoff flight, and can perform passive torsion and sweeping motions during the flapping of the wings, which helps to increase the flapping wing lift and the overall payload of the aircraft.
Owner:JILIN UNIVERSITY
Undercarriage system scheme design method based on heterogeneous design simulation data management
The invention provides an undercarriage system scheme design method based on heterogeneous design simulation data management, which comprises the following steps of: firstly, analyzing, abstracting and standardizing different types of heterogeneous design and simulation data in a development process of an undercarriage system, and constructing a uniform abstract data model; secondly, according to the defined semantic rules, an undercarriage semantic ontology model is constructed, then the semantic rules are loaded through a semantic reasoning engine, and processed data are associated; according to the research and development process of the undercarriage system and the semantic association relationship between the data, data storage and display are realized; after data abstract analysis, semantic association and unified storage are completed, functional information, design information and simulation information are further derived based on an undercarriage semantic ontology and a reasoning result, so that an undercarriage system development scheme driven by requirements is constructed. According to the method, multi-source heterogeneous design and simulation data generated in the research and development process of the undercarriage system can be effectively managed, and a design scheme of the undercarriage system is constructed on the basis of the multi-source heterogeneous design and simulation data.
Owner:NORTHWESTERN POLYTECHNICAL UNIV +1
Interactive strategic and tactical guidance system for aircraft ground operations
An aircraft-based strategic and tactical interactive guidance system for ground operations includes position sensors for determining position information of an aircraft engaged in taxi operations (e.g., gate to takeoff, touchdown to gate) at an airport. The guidance system stores airport database information about runways, taxiways, hazards, gates, and other airport features. The guidance system analyzes and parses verbal taxi instructions from the airport control facility, into a navigation path. The guidance system fuses the navigation path with the airport database information and the aircraft's position information to present, via an interactive display surface, a strategic display, e.g., providing an overhead view of the current aircraft position, its assigned gate or destination, and the navigation path incorporating the prescribed runways and / or taxiways via which the aircraft will reach said destination. The pilot may modify the displayed navigation path via the interactive display surface.
Owner:ROCKWELL COLLINS INC
Electromagnet electromagnetic ultrasonic thickness measuring method and system based on anti-collision unmanned aerial vehicle
PendingCN121540096AAnalysing solids using sonic/ultrasonic/infrasonic wavesUsing subsonic/sonic/ultrasonic vibration meansUltrasonic thickness measurementFrequency modulation
The invention discloses an electromagnet electromagnetic ultrasonic thickness measurement method and system based on an anti-collision unmanned aerial vehicle, and relates to the field of nondestructive testing, and the method comprises the steps: obtaining the coordinates of a preset detection point, controlling the flight path of the unmanned aerial vehicle, and determining the safety position information of the unmanned aerial vehicle located near the preset detection point; the motion of the multi-degree-of-freedom mechanical arm is controlled through a servo motor and an encoder, contact impact is reduced through a buffer mechanism, and attitude information of the electromagnetic ultrasonic sensor unit aligned with the surface of the to-be-detected object is determined; the magnetic attraction force is adjusted in real time through a closed-loop feedback system, and a linear frequency modulation pulse is adopted as an excitation signal to obtain an echo signal containing acoustic-electromagnetic coupling interference; acoustic-electromagnetic coupling interference is corrected and processed in an auxiliary mode through a multi-mode signal separation algorithm and machine learning, and final thickness data is obtained; and transmitting the final thickness data to a cloud platform, and providing a data visualization interface and an alarm function on the cloud platform. According to the invention, accurate thickness detection and remote monitoring of a complex structure material can be realized.
Owner:CHINA SPECIAL EQUIP INSPECTION & RES INST
Unmanned aerial vehicle inspection equipment and method for electric power inspection
The invention discloses an unmanned aerial vehicle inspection device and method for electric power inspection, and relates to the technical field of electric power inspection. A mounting base is fixed to the front side of the unmanned aerial vehicle body, a second camera is mounted on the front side of the mounting base, a buffer assembly is mounted on the lower side of the unmanned aerial vehicle body, and the cable is shot by arranging the second camera; the moving assembly comprises fixing frames, a T-shaped block, a threaded rod, a limiting rod and a first motor, the two corresponding fixing frames are fixed to the lower side of the unmanned aerial vehicle body, the T-shaped block is arranged between the two fixing frames, a threaded hole is formed in the edge of the right side of the T-shaped block, and the threaded rod is in threaded connection with the interior of the threaded hole; and the threaded rod is rotationally connected to the interior of the fixing frame on the right side, a first motor is installed on the lower side of the fixing frame on the right side, residues attached to the surface of the cable can be cleaned, and meanwhile damage points of the cable can be marked.
Owner:SHADAI (ZHEJIANG) DIGITAL TECHNOLOGY CO LTD
Self-lubricating pin
A pin for a pinned joint includes a hollow body with a first and second end caps coupled to first and second ends, respectively. The body and the end caps at least partially define a cavity within the body, wherein at least one aperture extends through the hollow body. A main piston is slidably disposed within the cavity and divides the cavity into a first chamber proximate to the first end and a second chamber proximate to the second end and fluidly isolated from an environment around the body. A lubricant is disposed within the first chamber. The main piston moves toward the first end of the body when a pressure in the second chamber is greater than a pressure of the environment. Movement of the main piston toward the first end of the body discharges lubricant through the at least one aperture.
Owner:SAFRAN LANDING SYSTEMS +1
Inspection unmanned aerial vehicle with good damping effect
The invention discloses an inspection unmanned aerial vehicle with a good damping effect, and relates to the technical field of damping of unmanned aerial vehicles. The unmanned aerial vehicle comprises an unmanned aerial vehicle body, two supporting frames are fixedly connected to the two sides of the unmanned aerial vehicle body correspondingly, connecting plates are fixedly connected to the bottom ends of the supporting frames correspondingly, supporting plates are arranged below the two supporting frames correspondingly, and buffering assemblies are arranged between the connecting plates and the supporting plates and used for damping the unmanned aerial vehicle body; when impact force vertically acts on the top end of the connecting plate, the first damping spring rapidly absorbs the impact force by means of the elastic deformation characteristic of the first damping spring, high-frequency vibration generated by impact of the unmanned aerial vehicle body is effectively reduced, meanwhile, the residual impact force is stably transmitted to the first mounting base, and the second damping spring is promoted to be compressed; the impact energy is secondarily absorbed through elastic deformation of the two-stage spring, the double damping effect is achieved through the linkage damping mechanism of the two-stage spring, the protection performance of the unmanned aerial vehicle is further enhanced, and the overall damping efficiency is remarkably improved.
Owner:HEFEI KEKONG HUIXIANG TECHNOLOGY CO LTD
Aircraft ground steering system and aircraft ground steering control method
The invention provides an aircraft ground steering system and an aircraft ground steering control method, which can realize steering and runway separation of an aircraft under a low-speed condition even if a front wheel turning system cannot work normally, and can inhibit or avoid additional weight increase. The aircraft ground steering system comprises a turning hand wheel assembly used for controlling a front wheel turning system to achieve steering of an aircraft when the aircraft slides on the ground at a low speed; the brake system comprises a brake control part, and the brake control part is used for controlling the brake pressure of the left main undercarriage wheel and the brake pressure of the right main undercarriage wheel; and a standby turning control unit capable of switching to a standby mode in which the brake pressure of the left main landing gear wheel and the brake pressure of the right main landing gear wheel are controlled via a brake control unit according to the angle of the hand wheel of the turning hand wheel assembly operated by a pilot.
Owner:COMMERCIAL AIRCRAFT CORP OF CHINA LTD +1
Landing chassis structure of surveying unmanned aerial vehicle
The landing chassis structure of the surveying unmanned aerial vehicle comprises an installation base, an unmanned aerial vehicle body is connected to the top of the installation base in an inserted mode, and supporting rods are fixedly connected to the front sides and the rear sides of the left side wall and the right side wall of the installation base. Top plates are arranged on the left side and the right side of the lower portion of the mounting base, connecting bases are fixedly connected to the front sides and the rear sides of the tops of the top plates on the left side and the right side, and the connecting bases on the left side and the right side are fixedly connected with the supporting rods on the left side and the right side; the unmanned aerial vehicle connecting mechanism comprises a mounting bin, a gear driven screw rod, a threaded sleeve, a mounting plate, a clamping tenon and a gear driving rod, the landing chassis structure for surveying the unmanned aerial vehicle is reasonable in structural design, the unmanned aerial vehicle can be quickly and conveniently mounted on the landing chassis, time and labor are saved, and the buffering performance of the landing chassis on landing impact force can be effectively improved; and the landing stability of the unmanned aerial vehicle is improved.
Owner:GUANGDONG JINGMA INFORMATION TECHNOLOGY CO LTD
Unmanned aerial vehicle hoisting device
The utility model provides an unmanned aerial vehicle hoisting device, which relates to the technical field of unmanned aerial vehicle transportation, and comprises an unmanned aerial vehicle main body, the bottom of the unmanned aerial vehicle main body is fixedly connected with a frame, two clamping plates are arranged in the frame, the bottoms of the two clamping plates are respectively provided with grabbing plates and adjusting assemblies which are symmetrically arranged, and the adjusting assemblies are respectively arranged on the two clamping plates. The height position of the grabbing plate is adjusted. According to the device, the size of the goods loading shelf can be adjusted according to the actual size of goods through the adjusting assembly, so that the goods of different sizes can be loaded and fixed, the practical performance of the device is improved, manual secondary fixing is not needed, the stability is high, and the safety risk of high-altitude object throwing is avoided; buffering can be provided during landing through the buffering assembly, the situation that the unmanned aerial vehicle body is damaged due to the fact that large impact is generated during landing due to the influence of the self weight is avoided, and the situation that goods are damaged and extra damage is caused due to the fact that ground protrusions collide with the goods is avoided.
Owner:JIANGSU ZHIYIHANG TECHNOLOGY CO LTD
Multi-lens surveying and mapping unmanned aerial vehicle
Owner:GUANGXI ZHUANG AUTONOMOUS REGION TOBACCO CO LIUZHOU TOBACCO CO
Ground support equipment for a high altitude long endurance aircraft
Systems, devices, and methods for a ground support system for an unmanned aerial vehicle (UAV) including: at least one handling fixture, where each handling fixture is configured to support at least one wing panel of the UAV; and at least one dolly, where each dolly is configured to receive at least one landing pod of the UAV, and where each landing pod supports at least one wing panel of the UAV; where the at least one handling fixture and the at least one dolly are configured to move and rotate two or more wing panels to align the two or more wing panels with each other for assembly of the UAV; and where the at least one dolly further allows for transportation of the UAV over uneven terrain.
Owner:AEROVIRONMENT INC
Unmanned aerial vehicle for pesticide spraying in agriculture and forestry
The invention relates to the technical field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle for pesticide spraying in agriculture and forestry, which comprises an unmanned aerial vehicle frame provided with a plurality of groups of arms, each arm is provided with a wing, and the unmanned aerial vehicle further comprises a controller for controlling the rotation of the wings; the rack is used for supporting the unmanned aerial vehicle rack, the rack comprises supporting legs connected with the unmanned aerial vehicle rack, and adjusting assemblies are arranged in the supporting legs; the fixing assembly is used for fixing the adjusting rod arranged in a sliding mode; when the unmanned aerial vehicle lands on a slope, the base making contact with the slope firstly is squeezed by the gravity of the unmanned aerial vehicle frame, the adjusting rods move upwards, the first air bags are squeezed, internal air is exhausted into the first air bags corresponding to the other adjusting rods, the other first air bags are expanded, and the adjusting rods not making contact with the slope are pushed to stretch out to make contact with the slope; after all the adjusting rods make contact with the slope through the base, the base extrudes the second air bag, air in the second air bag pushes the fixing block into the fixing groove, and the adjusting rods and the supporting legs are fixed in a limited mode.
Owner:JIANGSU HONGXIANG AVIATION TECH CO LTD
Slow descent device for surveying unmanned aerial vehicle
Owner:LANGFANG INTEGRATED NATURAL RESOURCES SURVEY CENTER CHINA GEOLOGICAL SURVEY
Unmanned aerial vehicle equipment for electric power engineering investigation
The utility model discloses unmanned aerial vehicle equipment for electric power engineering investigation, which comprises an unmanned aerial vehicle lower body, a buffer mounting assembly is arranged at one end of the lower part of the unmanned aerial vehicle lower body, and a support frame assembly is arranged at one end of the buffer mounting assembly; according to the utility model, the mounting clamping ring groove at one end of the support frame body is aligned with the open arc-shaped clamping ring and is jacked in, and the fixing bolt penetrates through the locking through hole to lock the open arc-shaped clamping ring, so that the support frame assembly can be flexibly and conveniently disassembled and assembled, and the support frame assembly can be conveniently adjusted and adaptively used according to different use scene environments; a damping telescopic rod and a buffering elastic piece are arranged during landing, the good buffering effect can be achieved, and the length of the portion, screwed into a threaded connection adjusting base, of an adjusting threaded rod body can be conveniently adjusted by arranging an inserting rod assembly screwed into an adjusting threaded hole and rotating a hexagonal rotating head; in this way, the unmanned aerial vehicle can take off and land in some environments with poor ground, so that the unmanned aerial vehicle can stably stand on the ground.
Owner:HUBEI CAICHENG ELECTRIC POWER ENG DESIGN CO LTD
Folding undercarriage device of low-altitude aircraft
The invention relates to the technical field of undercarriages, in particular to a folding undercarriage device of a low-altitude aircraft, which comprises an aircraft body, a pesticide spraying mechanism for crop fertilization is arranged on the aircraft body, a height-adjustable undercarriage mechanism is arranged at the lower end of the aircraft body, and a landing buffer mechanism is arranged on the undercarriage mechanism. The landing buffering mechanism is used for reducing impact on the undercarriage mechanism at the moment of landing, a linkage auxiliary mechanism is arranged on the aircraft body, the undercarriage mechanism comprises a fixing plate body, and the fixing plate body is detachably installed on the aircraft body. By arranging the undercarriage mechanism and adopting a dynamic folding design, after taking off, the second-stage frame body retracts to drive the telescopic joint to be shortened, so that the overall height is reduced, air turbulence during flight can be effectively reduced, meanwhile, the first-stage frame body rotates to be parallel to the fuselage, the cross sectional area of the undercarriage mechanism is greatly reduced, and the overall height is reduced. And the wind resistance loss during high-speed flight can be obviously reduced.
Owner:YANGTZE DELTA REGION INST OF TSINGHUA UNIV ZHEJIANG
Insulator antifouling cleaning device carried by unmanned aerial vehicle
The invention relates to the technical field of electric power inspection, in particular to an unmanned aerial vehicle carried insulator antifouling cleaning device which comprises an unmanned aerial vehicle body, the bottom of the unmanned aerial vehicle body is fixedly connected with a fixing frame, and the front end and the rear end of the top of the fixing frame are fixedly connected with the unmanned aerial vehicle body through quick release mechanisms. A water tank is fixedly mounted on the inner side of the fixing frame, a water distribution pipe is fixedly connected to the inner side of the fixing frame, adjusting arms are rotationally connected to the front and rear sides of the left and right ends of the fixing frame, and first electric push rods are mounted on the inner side of the fixing frame and located between the two adjusting arms at the same end; compared with an existing insulator anti-fouling cleaning mode, the insulator anti-fouling cleaning device is convenient to disassemble, assemble and maintain through the design, the outer side of an insulator can be subjected to anti-fouling cleaning, and the anti-fouling cleaning effect is good. And the antifouling cleaning effect and efficiency of the insulator and the operation safety are greatly improved.
Owner:STATE GRID FUJIAN ELECTRIC POWER CO LTD +2
Vertical takeoff and landing tilting fuselage winged frame multirotor aircraft
VTOL aircraft that takeoff and land as a multirotor and cruises as airplane. The aircraft comprises two major parts: First; winged carrier frame comprises wings, engines, propellers and landing gears. Second; tilting fuselage comprises cockpit, cabin and tail. Winged carrier frame is basically X / H frame multirotor that its thruster carrying arms are wing shaped. Aircraft vertically takeoff as multirotor after gaining safe altitude and forward airspeed then changes its flying axis that wings and thrust direction parallel to horizon. Lift generated by wings and thrust generated by thrusters that aircraft has basic airplane flying characteristics. Fuselage tilted to keep payload parallel to the horizon. Speed reduced, winged carrier frame and fuselage returned to multirotor for landing. It is easier to rotate fuselage than thrusters or wings. It is better to adjust thrust levels than vectoring to reduce the moving parts and aerodynamic effects.
Owner:ACIKEL GURKAN
Unmanned aerial vehicle vibration reduction support for geographic surveying and mapping
An unmanned aerial vehicle vibration reduction support for geographical surveying and mapping relates to the technical field of geographical surveying and mapping unmanned aerial vehicles and comprises an unmanned aerial vehicle body, a surveying and mapping assembly is arranged on the unmanned aerial vehicle body, four connecting arms are evenly arranged on the side face, propellers are arranged at the tops of the connecting arms, and supporting legs are arranged at the bottoms of the connecting arms; the lower bottoms of the supporting legs are fixedly connected with a buffering support. The buffering support comprises an outer cylinder, a supporting rod and a footstand. The top of the outer cylinder is fixedly connected with the supporting leg, the lower portion of the outer cylinder is provided with an opening, the upper end of the supporting rod extends into the outer cylinder along the opening, the lower end of the supporting rod is connected with the footstand, the portion, extending into the outer cylinder, of the supporting rod is sleeved with a piston, the outer ring of the piston is in sliding fit with the inner wall of the outer cylinder, and the space between the top face of the piston and the outer cylinder is filled with hydraulic oil. The hydraulic oil communicates with a hydraulic oil tank located on the unmanned aerial vehicle body through the oil hole. A compression spring is arranged between the top face of the piston and the top of the inner cavity of the outer cylinder. And the speed that the compression spring is extruded or rebounded is reduced under the action of the hydraulic oil, so that the effect of stabilizing vibration reduction is achieved.
Owner:惠民县自然资源和规划局石庙管理所
Unmanned aerial vehicle protection device and method
The invention relates to the technical field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle protection device and method. The unmanned aerial vehicle comprises an unmanned aerial vehicle body, and an undercarriage is fixedly connected to the bottom of the unmanned aerial vehicle body and comprises a supporting assembly; the two supporting assemblies are fixedly connected to the bottom of the unmanned aerial vehicle body, a transportation assembly is slidably connected between the interiors of the two supporting assemblies, the supporting assemblies are used for supporting the unmanned aerial vehicle body, and the transportation assembly is used for storing and supporting goods needing to be transported; when goods are placed in the transportation assembly, the transportation assembly is stretched to the proper storage size, meanwhile, the supporting assembly is driven to be stretched, and the goods in the transportation assembly are clamped and protected through the clamping resilience force of the supporting assembly; when the unmanned aerial vehicle body takes off, the supporting length of the supporting assembly is increased to exceed the conveying assembly, and when the unmanned aerial vehicle body lands, the supporting length of the supporting assembly retracts, so that the vibration amplitude of landing of the unmanned aerial vehicle body is reduced.
Owner:SHANTOU FEILIITE MODEL AIRCRAFT IND CO LTD
A multi-functional drone
This invention relates to the field of unmanned aerial vehicle (UAV) technology and discloses a multi-functional UAV. The UAV includes a stabilizing support mechanism installed at the bottom of each of its four rotor arms. This stabilizing support mechanism can stably support the UAV in soft sand. An auxiliary mechanism is rotatably connected to the top of each stabilizing support mechanism. This auxiliary mechanism assists in supporting the stabilizing support mechanism and improves its cushioning capacity. A secondary support mechanism is detachably connected to the bottom of the UAV. This secondary support mechanism protects the bottom of the UAV and prevents it from tipping over on uneven ground. Through the cooperation of the stabilizing support mechanism and the auxiliary mechanism, the UAV can utilize its own gravity to stabilize itself in sandy or soft soil terrain, preventing it from sinking or tipping over. Furthermore, the structure is purely mechanical, simple, and low-cost, and is relatively reliable in extreme environments.
Owner:SHENZHEN XINJIASHENG PRECISION TECHNOLOGY CO LTD
Special unpowered landing device for disc-shaped flying device
The invention discloses an unpowered landing device special for a saucer-shaped aircraft, belongs to the technical field of saucer-shaped aircrafts, and aims to solve the problems that a traditional landing device is large in occupied space, complex to operate and free of autonomous speed and direction control. The device comprises an annular umbrella cloth storage container, cylindrical umbrella cloth, a rotatable ring, a hanging ring, a flexible hanging wire, a supporting pulley, a limiting device, an air leakage opening and an arc-shaped plate. The annular umbrella cloth storage container and the outer edge of the saucer-shaped aircraft are fixed or integrally designed, the upper edge of cylindrical umbrella cloth is bonded with a rotatable ring, the lower edge is bonded with the outer side of a hanging ring, and a flexible hanging wire is connected with the rotatable ring and the inner side of the hanging ring through a limiting device; the rotatable ring is supported by more than three supporting pulleys, is connected with an external power device through a clutch mechanism, and can drive the cylindrical umbrella cloth to be spirally stored; after the external power is cancelled, the gravity of the hanging ring drives the cylindrical umbrella cloth to unfold without jamming, and the opening and closing degree of the air outlet are adjusted in cooperation with the arc-shaped plate, so that the falling speed and the drifting direction are autonomously controlled. The device is high in adaptability, high in reliability and suitable for unpowered safe landing of the saucer-shaped aircraft in the vertical non-straight-through airflow state of the saucer body.
Owner:周耀瑜
Wheel suspension for a vehicle
A wheel suspension for a vehicle includes: - a guide tube (10) that can be mounted on or is mounted on a vehicle chassis in an operating position or is permanently connected to or belonging to a vehicle chassis and assumes the operating position, which in its operating position has a guide tube axis extending vertically or inclined relative to a vertical direction according to a nominal guide tube angle with respect to a vehicle standing on a horizontal flat surface; - a wheel fork (3) having two fork legs (4), which is mounted on the vehicle chassis at least at one bearing area at least by means of the guide tube (10) in its operating position; - Bearing devices at free end areas of the fork legs for the rotary bearing of a wheel (2) between them. It is proposed that the wheel fork (3) is or can be mounted in a relatively movable manner radially outside on the guide tube (10) by means of its bearing area (5, 6).
Owner:GURU TECHNOLOGIES GMBH
Unmanned aerial vehicle for topographic surveying and mapping
The invention relates to an unmanned aerial vehicle for topographic surveying and mapping, and relates to the field of unmanned aerial vehicles, the unmanned aerial vehicle comprises a flight main body, a flight mechanism, a stabilizing mechanism and a shooting mechanism, the flight mechanism is arranged on the flight main body and used for flight, the stabilizing mechanism is arranged on the flight main body, and the shooting mechanism is arranged on the stabilizing mechanism. The stabilizing mechanism drives the shooting mechanism to rotate. The method has the effect that the terrain surveying and mapping quality of the unmanned aerial vehicle is better.
Owner:SHANXI URBAN PLANNING & DEV RES CO LTD
Device for rotating an aircraft wheel
A landing gear for an aircraft having an axle carried by a strut, the axle including a rotatably-mounted wheel and a drive device for rotating the wheel about a rotation axis. The drive device can have a motor mounted at one end of the axle for transmitting a rotational torque to the wheel, a body projecting out of the motor and snugly received in the axle, and at least a first harness extending along the body and connecting the motor to at least a first coupler carried by a free end of the body to cooperate with a second coupler of the landing gear to supply the motor with power. The second coupler received in an opening formed in the axle at the junction between the strut and the axle, the opening extending along an axis perpendicular to the axis of rotation of the wheel.
Owner:SAFRAN LANDING SYSTEMS +1
Vertical Takeoff and Landing Aircraft
ActiveUS20250256841A1Power plant arrangements/mountingAircraft stabilisationCruise speedClassical mechanics
A vertical takeoff and landing (VTOL) aircraft includes a maximum takeoff weight (MTOW) of about 1700-kg, a cruising speed of about 80-knots equivalent airspeed (EAS) to about 100-knots EAS, a nominal range of about 300-km, a nominal flight time of about 4-hours, and at least one pair of rotors configured to provide vertical thrust. Each rotor of the at least one pair includes an about 2-meter propeller diameter, a disk loading of about 67-kg / m2 to about 110-kg / m2, and an operating speed of about 1800 rotations-per-minute (RPM) to about 2700-RPM.
Owner:PIPISTREL D O O
Long-service-life and high-reliability sealing structure of aircraft undercarriage
The invention belongs to the technical field of aircraft hydraulic systems, and relates to a long-life and high-reliability sealing structure of an aircraft undercarriage, which realizes oil-gas mixed sealing of an aircraft undercarriage buffer under multiple working conditions through the structural design of fluorinated silicone rubber, nitrile rubber and modified polytetrafluoroethylene materials. Modified polytetrafluoroethylene and nitrile rubber are used on a dynamic sealing surface for combined action, and meanwhile, the wear resistance of the modified polytetrafluoroethylene and the high elasticity of the nitrile rubber are fully utilized, so that the service life of the sealing device under a high-pressure and high-speed dynamic sealing working condition and zero leakage of air seal under a low-temperature and low-pressure static sealing working condition are ensured. The elastic body on the movable sealing surface adopts a T-shaped structure, so that the elastic body torsion failure possibly caused by the undercarriage buffer under a long-stroke working condition and the extrusion failure under high pressure are prevented; and the elastomer for the static sealing surface is made of fluorosilicone rubber, so that the low-temperature performance of the sealing device is ensured. The sealing device can achieve a good sealing effect under the working conditions of oil-gas mixing, long stroke, high pressure, wide temperature range and the like confronted by the sealing of the undercarriage buffer of the aircraft.
Owner:JINCHENG NANJING ELECTROMECHANICAL HYDRAULIC PRESSURE ENG RES CENT AVIATION IND OF CHINA