280results about "Convertible aircrafts" patented technology

A land to air vehicle with lower extendable wings and upper extendible wings, a body, a front hood fan, a rear fan and wheels. The wheels include wheel bases, exterior tires circumscribing the wheel bases, and a fan wheel assembly within each wheel base. The wheel assembly includes extendible fans, a rotor outer rim with teeth for holding a stator inner rim, a propeller shroud configured to house a variety of fan blades, at least one fan within the propeller shroud, a hinge fixedly attached to the outer rotor rim and the propeller shroud, a wheel motor platform and a wheel motor. The hinge is structured to allow the propeller shroud with fans to extend distally from the wheel base interior to navigate the land to air vehicle.

A quadrotor is proposed than can both fly and roll. The proposed robot employs passively reconfigurable structures to enable the rolling, tightly coupling the attitude of the robot to the rolling cage. The benefits are precise rolling and turning control as well as improved rolling efficiency. The passively reconfigurable structures are enabled by pre-stretched elastic springs to generate a nonlinear restoring torque. The robot leveraged the superior maneuverability in the rolling mode to take photos of the surroundings at different tilting and panning angles to construct a panoramic image. Besides, the results of the power measurements show a significant reduction in the cost of transport brought by at low speed, equating to a 15-fold extension in the operational range.

A hybrid system for drones and other modes of transport. A combustion engine provides range and / or lifting capacity for drones while electric motors / generators provide both control and maneuverability. One or more combustion engines, in conjunction with one or more electric motors / generators form a propulsion system whereby each is connected to and drives its own driving pinion in one or more planetary gear sets, and provide continuously variable transmission for driving propellers or driveshafts. The combustion engine may be connected directly to one of the planetary gear's driving pinions, or can drive one of the planetary gear's driving pinions. If the propellers are only driven by either a combustion engine, or an electric motor / generator, the other engine / motor will be kept at rest by a braking device for a combustion engine or a braking device for an electric motor / generator.

A payload including a housing provided with one or more toothed guides or with one or more docking mechanisms, each of which is configured to detachably toothedly interact with an unmanned aircraft apparatus being docked so as to enable the movement of said docked unmanned aircraft apparatus with respect to the housing of the payload, wherein the housing of the payload is further configured to detachably toothedly interact with yet another (other) unmanned aircraft apparatus so as to enable the action of said yet another unmanned aircraft apparatus onto said docked unmanned aircraft apparatus for withdrawal of the latter from interaction with the housing of the payload. Furthermore, embodiments of an air transport system include two or more unmanned aircraft apparatuses and one of the payload.

A quadrotor is proposed than can both fly and roll. The proposed robot employs passively reconfigurable structures to enable the rolling, tightly coupling the attitude of the robot to the rolling cage. The benefits are precise rolling and turning control as well as improved rolling efficiency. The passively reconfigurable structures are enabled by pre-stretched elastic springs to generate a nonlinear restoring torque. The robot leveraged the superior maneuverability in the rolling mode to take photos of the surroundings at different tilting and panning angles to construct a panoramic image. Besides, the results of the power measurements show a significant reduction in the cost of transport brought by at low speed, equating to a 15-fold extension in the operational range.

The invention discloses a functional gradient buffer structure suitable for a high-speed water entry process of a cross-medium navigation body, and aims to effectively improve the structural safety and integrity of the navigation body when the navigation body bears a high impact load. The structure mainly comprises a pointed arch-cylinder combined housing, a functional gradient buffer layer and a locking device. Wherein the functional gradient buffer layer is formed by sequentially and tightly attaching high-density (200kg / m < 3 >) rigid polyurethane foam, medium-density (100kg / m < 3 >) rigid polyurethane foam and low-density (50kg / m < 3 >) rigid polyurethane foam, a filling structure with gradually-decreased density is formed in the axial direction, the functional gradient buffer layer is arranged in a cavity between the housing and the navigation body, and the low-density layer is close to the head of the navigation body. The locking device achieves axial limiting and anti-falling fixing of the housing through an annular structure. Under the condition of 100 m / s vertical entry water impact, numerical simulation analysis shows that the structure can reduce the peak value of the impact load coefficient borne by the navigation body to 0.88, and compared with a single-layer buffer structure with the same volume density (100 kg / m < 3 >), the impact load coefficient of the structure is reduced by 27.3%.

An aircraft has a boom, a propulsion assembly coupled to a first end of the boom, and a first wing coupled to a second end of the boom. The propulsion assembly is coupled to the boom by a rotating joint. A second wing is optionally coupled to the rotating joint. The first wing is coupled to the boom by a rotating joint. The first wing is coupled to the rotating joint by a hinge. A vehicle with roll, pitch, and yaw maneuverability able to mirror the aircraft movements may be coupled to the second end of the boom. The vehicle body may be picked up with a vehicle chassis disconnected from the vehicle body. The boom houses an energy source to power the propulsion assembly. A rudder is coupled to the second end of the boom. A paddle is disposed between the propulsion assembly and the boom.

In some embodiments, a multi-modal robot can be capable of aerial mobility and ground mobility, and can switch between configuration. The multi-modal robot can include a chassis, and a leg attached to the chassis. The leg can include a frontal hip joint. The frontal hip joint can rotate around a frontal hip axis of rotation. The frontal hip axis of rotation can be parallel to a longitudinal axis of the chassis. The leg can further include a sagittal hip joint, wherein the sagittal hip joint is coupled to the first distal end of a first link. The sagittal hip joint can rotate around a sagittal hip axis of rotation. The leg can include a wheel. The wheel can be configured to rotate around a wheel axis of rotation. The leg can further include a propeller. The propeller can be co-axial with the wheel.

The invention relates to a self-adaptive energy-absorbing conformal head cap of an air-water cross-medium aircraft, which is mainly applied to aircrafts capable of switching motion between two media of air and water. The head cap comprises a top cover, a skin combination, an energy absorption mechanism, a shape preserving mechanism and a modular adaptive interface, wherein the skin combination comprises an outer-layer skin and an inner-layer skin; the energy absorption mechanism is arranged in the inner-layer skin; the conformal structure is arranged between the inner-layer skin and the outer-layer skin; the modular adaptive interface comprises a base and a switching section, the base is connected with one end of the inner-layer skin, and the switching section is connected with the aircraft body; and the top cover is connected with the other end of the inner-layer skin. Stable hydrodynamic performance and low underwater resistance can be provided under different water entry speeds and angles, head appearance damage caused in the deformation process of a traditional energy absorption structure is effectively avoided, and the key technical problems in design of the air-water cross-medium aircraft are solved.

A transport vehicle that transports packages includes: a first arm; a second arm; a first wheel connected to the first arm; a second wheel connected to the second arm; at least one actuator; and a controller (control processor). When the transport vehicle is slidably hung from the first rail via the first wheel and the second wheel, the controller controls the at least one actuator (arm actuator, roller actuation motor) to disengage the first wheel from the first rail and place the first wheel on the second rail, and disengage the second wheel from the first rail and place the second wheel on the second rail.

A flying vehicle with folding wings that drives well on the ground and flies well in the air; controlled from inside, it changes from automotive to aircraft configuration without the operator needing to get out of the vehicle. The balance point of the vehicle is located midway between the front and back wheels, providing good handling on the road. In the aircraft configuration with wings unfolded, there is a front wing and a back wing. The incidence of the front wing is controllable, enabling the craft to rotate and take off with a center of gravity located well ahead of the rear wheels. The back wing is fitted with foldable vertical stabilizers near its wing tips. In automobile configuration the wings are folded on top of the body; the wings resemble a roof rack with large surfboards on it. Driven wheels provide motive power on the ground; ducted fans provide thrust for air travel. An autopilot system provides stability and navigation aid, particularly in bad weather or poor visibility. In the roadable configuration, filling water ballast tanks provides additional crosswind stability and crash protection. Also in a roadable configuration, the present invention may be licensed as a three-wheeled motorcycle towing a two-wheeled trailer. In its flying configuration, the invention can be licensed as a Light Sport Aircraft.

The invention discloses a fuel cell-turbofan engine hybrid power system for a cross-medium aircraft, and relates to the technical field of aero-engines, the system comprises a solid oxide fuel cell, a turbofan engine, a lithium battery, an energy management module, a motor, a propeller, a reforming hydrogen production device and a medium self-adaptive oxidant supply subsystem. In an air flight mode, the system adopts autothermal reforming hydrogen production, a fuel cell and a turbofan engine to cooperatively work, a high-efficiency low-oil-consumption low-speed cruise and high-thrust acceleration mode is provided, and meanwhile, a lithium battery is charged. In the underwater submerging and water surface sailing mode, a turbofan engine flow channel is closed, steam reforming hydrogen production is adopted, a hybrid power system composed of a fuel cell and a lithium battery is used for driving a propeller, the fuel cell provides stable power, and the lithium battery meets the instantaneous high-power requirement. The system solves the problems that a traditional power system is low in efficiency, poor in cruising ability, single in working mode and the like.

An aerial and preferably marine vehicle intended to operate in its principal mode near the surface of water or land employing the Wing-in-Ground Effect (WIG) and capable to take-off and land vertically (VTOL) by means of thrust vectoring, which vehicle has a wing arranged at the lowermost part of the fuselage, propulsion units comprising four rotatable pylons extending transversely in pairs on both sides of the upper part of the fuselage, four elongated nacelles mounted on the outer tips of said pylons, which nacelles contain electric motors (E) and provided with propellers at their extremities, so that the rotation of the pylons results in turning the nacelles and thrust of propellers from substantially vertical, ensuring take-off and landing, to substantially horizontal providing a flight mode, retractable hydroskis for emergency landing on water, while said propulsion units and said wing are spaced apart vertically and horizontally and do not overlap.

A payload including a housing provided with one or more toothed guides or with one or more docking mechanisms, each of which is configured to detachably toothedly interact with an unmanned aircraft apparatus being docked so as to enable the movement of said docked unmanned aircraft apparatus with respect to the housing of the payload, wherein the housing of the payload is further configured to detachably toothedly interact with yet another (other) unmanned aircraft apparatus so as to enable the action of said yet another unmanned aircraft apparatus onto said docked unmanned aircraft apparatus for withdrawal of the latter from interaction with the housing of the payload. Furthermore, embodiments of an air transport system include two or more unmanned aircraft apparatuses and one of the payload.

The invention discloses an operation type water-air cross-domain rope-driven bionic robot and a using method thereof. The robot comprises an aircraft body, a rotor wing arm installed on the aircraft body, an underwater propelling structure and a mechanical arm assembly installed at the bottom of the aircraft body. The rotorcraft arm comprises a rotating device and a rotor assembly, and the rotating device is used for driving the rotor assembly to rotate; the mechanical arm assembly comprises a driving device, a mechanical arm, a driving rope and a mechanical claw installed at the tail end of the mechanical arm, and the driving device is installed at the bottom of the aircraft body and used for driving the tensioning degree of the driving rope; the mechanical arm comprises a plurality of joint sections, and the overall shape of the mechanical arm is changed by adjusting the tensioning degree of the driving rope. According to the mechanical arm, the design of the multiple joint sections is adopted, a flexible bendable structure is formed, the mechanical arm is controlled to be bent and deformed on multiple degrees of freedom through the driving rope, the overall bending flexibility of the mechanical arm is improved, and the mechanical arm can adapt to the complex or narrow working environment.

The invention relates to the technical field of aircrafts, and discloses a cross-medium aircraft which comprises a functional module, a power module, a control module, a comprehensive module and a submerging module, the power module is divided into a front power mechanism and a rear power mechanism, the control module is arranged between the front power mechanism and the rear power mechanism and used for controlling the lift force directions of the front power mechanism and the rear power mechanism so as to control the flight attitude of the aircraft, and the front power mechanism and the rear power mechanism are in the structural form of hinge-free rotors. Lift force is provided for the aircraft; the other side of the front power mechanism is connected with the functional module, and the functional module is used for carrying functional equipment for working of the aircraft and can carry different modules such as a reconnaissance photoelectric ball, a high-energy explosive and a relay communication cabin according to the requirements of task execution. Through modular design, the structure of an aircraft and the structure of an underwater vehicle are integrated, and the problems that a cross-medium flight structure is complex and huge, and the function is single are solved.

The invention relates to a cross-medium aircraft variant nose cone with dynamically adjustable surface wettability, and belongs to the field of cross-medium aircrafts. Comprising a variant skeleton and a flexible skin. Under the heating condition, the variant framework can drive the flexible skin to deform, the flexible skin keeps the deformed state after normal temperature is recovered, and therefore curvature distribution and section characteristics of the nose cone structure are changed. The surface of the flexible skin is covered with a wettability intelligent response coating. After the wettability intelligent response coating is irradiated by ultraviolet rays, the surface wettability can be converted into a super-hydrophilic state, and the wettability intelligent response coating can be recovered into a super-hydrophobic state after being heated. The head configuration and the surface wettability layout of the cross-medium aircraft are adjusted according to the specific water entry working condition, the hydrodynamic force and the hydrodynamic moment borne by the aircraft in the water entry process are changed through the influence effect of the configuration and the surface wettability on water entry cavitation evolution, the impact load is reduced as needed, and the attitude and trajectory stability is improved; the purposes of being compatible with various launching platforms and guaranteeing the water entry efficiency and safety are achieved.

The invention discloses a cross-medium aircraft and belongs to the technical field of aircrafts. Comprising a power propulsion system which provides a power hybrid control system for an aircraft body and is used for realizing data acquisition and operation and accurate control of the power propulsion system, a navigation system and a sinking and floating system; the navigation system is used for providing navigation support for the vehicle body; the gradient skin is composed of multiple gradient materials and covers the outer surface of the aircraft body, and the sinking and floating system is used for controlling floating and diving of the aircraft body. According to the invention, the vehicle can obtain the optimal pneumatic / hydrodynamic performance in the air and seawater medium navigation state; according to the power propulsion system, the requirements of high speed, long distance and high thrust of the aircraft are met; a distributed network and a visual navigation system meet the navigation requirements of the cross-medium aircraft in the air, on the water surface and under the water and the combined combat; the hybrid control system is used for accurately controlling the aircraft; the aircraft application material can complete deformation adaptive to the changed environment.

The invention provides a four-shaft eight-propeller rotor wing folding mechanism suitable for a hovercar. The four-axis eight-propeller rotor wing structure is characterized in that the four-axis eight-propeller rotor wing structure comprises foldable supporting arms and march-up blades, the blades and the supporting arms are sequentially folded step by step through control driving, a limiting structure is designed to assist a control system in precise folding, and finally environment-friendly folding of the large-size four-axis eight-propeller rotor wing structure is achieved. Through the design of a paddle protection layer and the design of a mechanism protection device, multi-protection and storage of the rotor wing folding mechanism in a parking state on the ground are realized step by step. Based on the method, precise and efficient small folding and comprehensive protection design of the four-axis eight-propeller rotor wing mechanism can be achieved, and the problems that a traditional hovercar rotor wing mechanism is large in occupied area and low in safety are effectively solved. The four-axis eight-propeller rotor wing folding mechanism has the advantages of being easy, convenient and rapid to operate, ingenious in folding design, high in folding efficiency and precision, comprehensive in protection and the like, and can be widely applied to design of the four-axis eight-propeller rotor wing folding mechanism of the hovercar.

A hybrid aerial hydro drone includes a body with a plurality of hydraulic thrusters supported on an outer surface of the body and configured to propel the body in a marine environment. The drone also includes a plurality of rotor arms arranged on the body, each rotor arm comprising a rotor system configured to propel the body in an aerial environment. Each rotor arm is deployably configured between a deployed position in which the rotor systems are extended from the body for aerial traversal, and a folded position in which the arms are hydrodynamically folded behind the body for marine traversal. The body also includes a controller, an energy source, a main ballast chamber and a pump with snorkel for operation of the drone.

Modular flying platform including an airship body defining an internal space and configured to achieve buoyancy, an internal structure supporting a transfer channel, an attachment mechanism positioned on the transfer channel to detachably connect with a second platform. The transfer channel is configured to permit transfer therethrough of a payload between the flying platforms when securely connected. A chain of modular flying platforms with one or more motors mounted to the airship body to control motion thereof. A method for managing a chain of modular flying platforms includes deploying a plurality of platforms, connecting the platforms to form the chain, transferring a payload through channels of the connected platforms and distributing at least one of propulsion, electrical power and computing across the chain.

A circuit-based vehicle archway assembly having an arched casing with a cylinder ramp at one end and an opposing semi-oval end. It includes a plurality of rotational cylinders within the casing and has respective airfoil bridges between the rotational cylinders. The airfoil bridges and cylinder ramps may be structured to create a cambered hybrid magnus lift airfoil assembly generating directional force to a circuit-based vehicle.

An aerial vehicle has a passenger cabin for receiving at least one passenger, a load-bearing structure beneath the cabin, and a propulsion system including a number of propulsion units, which propel the aerial vehicle for powered flight and vertical take-off and landing (VTOL). The propulsion units are preferably carried by support arms attached to the load-bearing structure and extending upwards therefrom so as to support the propulsion units at a level above the cabin. The aerial vehicle is preferably reconfigurable to a compact configuration after landing, with at least some of the propulsion units overlapping the cabin and / or each other, while still allowing passenger transfer in and out of the vehicle, thereby facilitating efficient use of space for implementing a vertiport.

The invention relates to the technical field of aircrafts, and discloses a triphibian aircraft and a triphibian form switching method thereof. Comprising an aircraft main body, a left auxiliary body and a right auxiliary body, retractable wings are arranged between the aircraft main body and the left auxiliary body and the right auxiliary body, sliding wheel assemblies are arranged at the bottoms of the three bodies respectively, foldable rotor wing mechanisms are arranged at the tops of the left auxiliary body and the right auxiliary body, a propeller is arranged at the tail of the aircraft main body, and foldable small wings are arranged on the outer sides of the left auxiliary body and the right auxiliary body. During take-off, the wings and the winglets are unfolded, the rotor mechanisms are started, and rising is achieved; during air cruise, the sliding wheel assemblies and the rotor mechanisms are stored, the propellers are started, and smooth flight is ensured; when the unmanned aerial vehicle runs on land, the sliding wheel assemblies are opened, the rotor mechanisms are stored, the wings and the winglets are folded, wind resistance is reduced, and the propellers are started to run; when sailing on the water, the three-body structure ensures buoyancy, and the propeller is pushed to move forwards; through the three-body structure, seamless switching of air, land and water triphibian scenes is achieved, the system adapts to multiple environments, the use flexibility is improved, and the application range is widened.

The application is suitable for the field of flying cars, and provides a vertical take-off and landing flying car, which comprises a car body, a main lift assembly arranged on the car body and placed inside the car body, a folding wing assembly arranged on the car body and placed on the top of the car body, and a back thrust power assembly arranged on the car body and placed on the top of the tail end of the car body. The application aims to solve the technical problems in the prior art that one kind of flying car is vertically taken off and landed, but does not have a fixed-wing flight mode, provides lift by a rotor, is more like a variant of a helicopter, has a small flight speed, a short flight range, and a complex control; another kind of flying car is taken off by sliding, has a main wing for generating lift, but has a long sliding distance for taking off and landing, has a high requirement for a landing site, and greatly limits the use scene.

The water-land-air triphibian variable-configuration robot comprises a robot body, a deformation wheel, a rotating wheel and a clamping jaw mechanism, and the robot body comprises a middle connecting pipe, a clamping jaw seat and two robot body deformation assemblies; the clamping jaw seat is rotatably arranged on the middle connecting pipe, and the clamping jaw mechanism is arranged on the clamping jaw seat; the two aircraft body deformation assemblies are arranged on the middle connecting pipe and connected with the deformation wheels and the rotating wheels correspondingly so that the deformation wheels and the rotating wheels can rotate around the middle connecting pipe, and then the whole aircraft can be switched among a flight mode, a ground mode and a water surface mode. And the deformation wheels are provided with paddle legs which can be embedded or opened, so that the whole machine is deformed between a wheel type state and a wheel paddle leg state. According to the invention, triphibian multi-mode movement can be realized, and a flexible operation tail end is provided.

The invention relates to the technical field of unmanned operation, and discloses an active deformation multi-aircraft integrated operation platform, which comprises a first aircraft, a second aircraft and a controller, one ends of the two fixed connecting rods are connected with the first aircraft, and steering engines are fixed to the other ends of the two fixed connecting rods; one ends of the two swing connecting rods are fixedly connected with the driving ends of the two steering engines respectively, a second aircraft and a third aircraft are connected to the two swing connecting rods respectively, the first aircraft, the second aircraft and the third aircraft are arranged in a triangular shape, and then a triangular collaborative architecture operation platform is formed; a first arc-shaped contact plate and a second arc-shaped contact plate are detachably arranged at the other ends of the two swing connecting rods respectively, a first clamping jaw is detachably arranged at one end of the first arc-shaped contact plate, and a second clamping jaw is detachably arranged at one end of the second arc-shaped contact plate. The platform can adapt to stable contact of diversified contact surfaces (flat / non-flat / corrugated wall surfaces, stand columns and the like), and the scene adaptation cost is reduced.

The invention discloses a multi-mode propulsion system of a water-air cross-domain aircraft and a water-air amphibious aircraft. The multi-mode propulsion system of the water-air cross-domain aircraft comprises a brushless motor. The water-air force transmission system comprises a high-speed output transmission set and a low-speed output transmission set, and the input end of the water-air force transmission system is connected with an output shaft of the brushless motor; the output end of the water-air force transfer system is connected with the variable-pitch propeller assembly; when the rotating speed of the brushless motor is lower than or equal to a preset threshold value, a low-speed output transmission set of the water-air force transmission system provides driving force for the variable-pitch propeller assembly. When the rotating speed of the brushless motor is higher than a preset threshold value, a high-speed output transmission set of the water-air force transmission system provides driving force for the variable-pitch propeller assembly. According to the power transmission mechanism, the transmission shaft can be switched to different rotating speed positions, and rotating speed and torque parameter matching of power transmitted to the propeller is achieved.

A lifting system includes an unmanned aerial vehicle, a thruster device, a first wire, a first reel, a second thruster device, a second wire, a second reel, and a controller. When the unmanned aerial vehicle is in a position separated from the ground, the controller detaches the first thruster device and the second thruster device from the unmanned aerial vehicle, causes the first reel to reel out the first wire, detaches the second thruster device from the first thruster device, and causes the second reel to reel out the second wire.