160results about "Convertible aircrafts" patented technology

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 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.

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.

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 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.

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.

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 present invention relates to transportation equipment, in particular to means and methods for moving a payload, specifically to a system and method for moving a payload. Provided are a system and method for moving a payload which are based on the use of aircraft apparatuses configured to dock to one another so as to enable mutual exchange of a docking guide and a payload. 2 independent claims, 9 figures.

The application relates to a device and method for docking and separating unmanned aerial vehicles and unmanned vehicles based on spin motion, wherein the helical landing gear of the unmanned aerial vehicle has a helical bottom which can be matched with a helical track on the top base of the unmanned vehicle; the base and the helical landing gear realize docking and separation based on the spin motion of the unmanned aerial vehicle and the unmanned vehicle alone or jointly; the locking device can lock the base and the helical landing gear after the unmanned aerial vehicle and the unmanned vehicle are docked, and can also unlock the base and the helical landing gear when receiving a separation instruction. The application realizes rapid autonomous docking, locking and separation through spin, improves the system cooperation capability, and expands the application range of the traditional amphibious system. Through the device and method for docking and separating unmanned aerial vehicles and unmanned vehicles based on spin motion, the land-air amphibious system can realize land-air amphibious motion as an integrated platform, and can also be separated into two subsystems of air and ground to cooperatively execute tasks.

Wheels are arranged on the lower portion of a ground carrier in a bilateral symmetry mode, a power system and a communication and automatic driving control system are arranged in a vehicle head on the front portion of the ground carrier, and a connecting clamping groove is formed in a floor of the ground carrier. Electromagnetic spring buckles are arranged on the lower portion of the flight cabin and correspond to the four connecting clamping grooves formed in the ground carrier floor in position. Wings with upward inverted inner sections and straight outer sections are respectively arranged on the left and right sides of the upper part of the flight cabin; the inner section and the outer section of each wing are averagely divided into two sections; when the hydraulic mechanism is opened and closed, the inner section and the outer section can be folded or unfolded around the hinge connecting mechanism, and after folding, the spring positioning pins are inserted into the positioning holes. Oblique empennages are arranged on the left side and the right side of the tail portion of the upper portion of the flight cabin respectively, and deflection rudders are arranged on the rear edges of the outer ends of the oblique empennages. The hovercar can run on the ground, can take off and land vertically, can hover in the air or fly horizontally and can sail underwater; the safety and reliability are high, and the use efficiency is high.

To provide a steering device suitable for a moving body for both land and air, capable of performing operation suitable for both ground traveling and flight in the air, and capable of acquiring and notifying various information.SOLUTION: A steering device of a moving body for both land and air includes: a steering mechanism 1 that performs an operation for changing an attitude; reaction force units 8 to 1 that generate reaction force against the operation of the steering mechanism 1; and a controller 30 that controls the reaction force. The controller 30 has: a flight detection unit that detects a flight; and a responsiveness control unit that, when the flight is detected, makes reaction force control responsiveness by the reaction force units lower than that in a case of traveling on the ground.SELECTED DRAWING: Figure 1

To provide transportation equipment, in particular means and methods for moving a payload, specifically, systems and methods for moving a payload. [Solution] A system and method are provided for moving a payload based on the use of aircraft equipment configured to dock with each other in order to enable the mutual exchange of docking guides and payloads.

The invention discloses a three-mode aircraft based on a ground effect and a control method of the three-mode aircraft. The aircraft integrates three modes of vertical take-off and landing, ground effect cruising and fixed wing high-speed cruising, and efficient mode switching is achieved through aerodynamic layout optimization and self-adaptive control. And an airfoil profile geometric parameter self-adaptive adjustment technology is adopted, so that the flight performance of a ground-effect area is enhanced. According to the control method, adaptive PID, sliding mode control and LQR algorithms are integrated, and a hierarchical control architecture is constructed. And the LQR controller realizes optimal trajectory tracking based on the aerodynamic model in the high-speed cruise stage. A differential control strategy is adopted for each modal characteristic, and accurate control over the height and the speed is achieved. And through cooperative adjustment of the propeller angle and power, it is guaranteed that mode switching is stable and rapid. The problems that a traditional aircraft is low in mode conversion efficiency, insufficient in ground effect utilization and the like are solved, and the method has the advantages of being high in interference resistance, high in stability and wide in application range and is suitable for various low-altitude application scenes.

To provide a convenient and safe vehicle.SOLUTION: An airbag extending to the outside of a vehicle body is inflated by igniting a gas generator when a monitor with a speed measuring instrument detects danger. Furthermore, solar power generation by a solar panel provided on a roof of the vehicle body, self-generated power by driving of propellers and tires, and hydrogen fuel are utilized to address energy issues and CO2 emission issues. In addition, even if one blade of a propeller encounters an abnormality, the other propeller can continue driving in a form of four-propeller-driving and in which the propeller has double blades in one set. A parachute for an escape in the event of an accident is provided.SELECTED DRAWING: Figure 1

A motor vehicle hub station configured to function as a terminal for an air motor vehicle, a ground motor vehicle, or a water motor vehicle, the motor vehicle hub station including a plurality of levels by a combination of a water surface level connected to a water surface and having an entrance for a water motor vehicle, a port level having a takeoff and landing field for an air motor vehicle, or a ground level configured to be connected to a ground and having an entrance for a ground motor vehicle, wherein a lift passage having an internal space extending in an up-down direction of the motor vehicle hub station is provided between the levels, the internal space is connected to each of the water surface level, the port level, and the ground level, and the air motor vehicle, the ground motor vehicle, or the water motor vehicle is lifted or lowered through the internal space.

The invention discloses an auxiliary energy supply unmanned aerial vehicle, and belongs to the technical field of unmanned aerial vehicle collaborative transportation. The whole unmanned aerial vehicle comprises a power module, a rack, grabbing arms and other core components. The core of the invention lies in that a new mechanical whole is formed by introducing the grabbing arms to the unmanned aerial vehicle to connect external devices. The unmanned aerial vehicle can be understood as an unmanned aerial vehicle, an unmanned ship, a small unmanned rocket and the like according to different working environment media, and is suitable for tasks such as multi-unmanned-aerial-vehicle cooperative hoisting operation, multi-unmanned-ship cooperative traction transportation operation and space satellite (or space station) boosting of heavy-load goods of tonnage or above.

The invention discloses a cross-medium variable tilt rotor aircraft and a control method thereof, and relates to the technical field of cross-medium aircrafts. Comprising a fuselage, front rotor units, a tail tilting rotor assembly, main wing units and wing unfolding and folding mechanisms, wherein the front rotor units are arranged on high-position mounting platforms on the two sides of the fuselage and are in bilateral symmetry; the tail tilting rotor assembly is arranged at the tail end of the fuselage and can rotate around a transverse tilting shaft; the main wing units are in bilateral symmetry and can be folded; the buoyancy adjusting unit and the control system are arranged in the fuselage. Through collaborative design of fuselage bionic integration, the composite rotors, the variable main wings, active buoyancy adjustment and closed-loop control, the traditional single propulsion bottleneck is broken through, cross-medium adaptation, consideration of take-off and landing and cruising efficiency and smooth transition are achieved, multi-scene adaptation is achieved, and breakthrough support is provided for engineering application.

The application discloses a flying car wing and rotor hybrid type folding and unfolding system and a flying car, which comprises a car body, two side wings, a wing rotating mechanism, a rotor support, a rotor support rotating mechanism and a rotor assembly; the wings are movably connected to the car body; the wings and the wing rotating mechanism are symmetrically arranged on the car body, and the wing rotating mechanism drives the wings to rotate and unfold to the two sides of the car body or reversely rotate and fold to the inner side of the car body, so that the wings do not exceed the wing edges, and the conversion between the automobile working state and the flying working state of the wings can be completed; the rotor support is movably connected to the wings, and the rotor support is rotated by starting the rotor support rotating mechanism, so that the rotation of the rotor support on the wing surface is realized. The flying car can realize super-short distance take-off and landing and stable flight in the air. In addition, when driving on the ground, the wings and the rotor can be folded and placed in the inner side of the car body, space is saved, the appearance is beautiful, and the ground automobile use requirements are met.

The application discloses a reconfigurable multi-rotor unmanned aerial vehicle based on a bistable hinge, which comprises a bistable hinge, a rotor assembly, a magnet and a hand grabber, etc. The bistable hinge is composed of a fuselage module, a pin shaft and a tension spring. The unmanned aerial vehicle has two different fuselage configurations, i.e. a ring configuration (configuration A) and a "I" shape configuration (configuration B). The counter torque generated by the same direction clockwise / anticlockwise rotation of the rotor overcomes the magnet attraction and the spring tension, switches the fuselage hinge steady state, realizes the "opening" / "closing" of the fuselage of the unmanned aerial vehicle, changes the wheelbase of the unmanned aerial vehicle while converting the fuselage configuration of the unmanned aerial vehicle. Moreover, the tension of the tension spring and the attraction of the magnet together guarantee the structural stability of the unmanned aerial vehicle under the two fuselage configurations. In addition, the "I" shape fuselage configuration and the hollow ring fuselage configuration respectively make the unmanned aerial vehicle have the ability to shuttle in narrow space and grab objects.

An aircraft includes a body defining an interior compartment configured to hold at least one of a passenger and a payload, a battery system, a plurality of arms coupled to and extending from the body, and a plurality of propulsion devices configured to provide thrust to fly the aircraft. Each of the plurality of propulsion devices is coupled to a respective one of the plurality of arms. The plurality of propulsion devices are powered by the battery system. Each of the plurality of propulsion devices is selectively pivotable about at least one axis. The plurality of propulsion devices include at least one of (i) counter rotating ducted fans and (ii) ionizing electrode engines.

This invention discloses an amphibious variable aircraft based on a float and propulsion system, relating to the field of aircraft technology. It includes a main fuselage and wings connected to both sides of the main fuselage. A power nacelle is located in the middle section of the wings, and a float mechanism is located at the end of the wings away from the main fuselage. The float mechanism includes floats, a tilting component on the outside of the floats, and a water intake / discharge component inside the floats. A tail fin is located at the tail of the main fuselage, and a horizontal stabilizing plate is mounted on the tail fin. This invention employs the aforementioned amphibious variable aircraft based on a float and propulsion system, using a tilting float design. The float mechanism's shape is identical to the aircraft's airfoil, reducing ineffective weight while ensuring the aircraft can quickly complete water intake / discharge operations, and its simple structure facilitates maintenance.

The invention provides a magnetic connection type modular reconfigurable aerial robot and a control method thereof, and relates to the technical field of robots and intelligent control. The aerial robot module comprises a locking mechanism, and the locking mechanism comprises a stay wire mechanism and a butt joint mechanism which are connected through a stay wire. The docking mechanism is used for locking the aerial robots; and the stay wire mechanism is used for controlling the stay wire to be tightened, so that the docking mechanism moves close to the stay wire mechanism, and unlocking between the aerial robots is achieved. The locking mechanisms are arranged in the air robot modules, locking between the air robot modules can be achieved, a stable active unlocking means is provided, a specified interface can be accurately locked or unlocked according to needs, and the safety, controllability and success rate of the modular air robot in the air assembling process are greatly improved.

The invention relates to the field of aerospace, in particular to a telescopic composite wing which can be used for aerospace equipment such as hovercars and carrier-based aircrafts. The telescopic composite wing comprises a wing framework, a wing shell and a linear actuator, and further comprises a hidden propeller mechanism, the telescopic composite wing disclosed by the invention has the following beneficial effects that the shape and the size of the wing can be customized according to requirements; in a contraction state, the wings can be completely hidden, so that a limited space is reasonably utilized, and the whole wings are lighter than traditional wings; in the aspect of structural strength, the wing shell provides secondary bending torsion, the framework provides main bending torsion, and the framework is connected with the wing shell at each section and can synchronously stretch and retract, so that the synchronization degree is high, and the stability is strong; the rotary propellers are installed in the wing sections at the two ends of the wings, and the left and right lift force can be adjusted under the condition that the wings on the two sides are equal in length, so that the aircraft can achieve flight actions such as rolling, and the flight attitude controllability is high.

The present disclosure provides an unmanned vehicle system that includes: a first non-terminal cell enclosing a first plurality of terminal cells, each of the first plurality of terminal cells enclosing a respective unmanned arial vehicle (UAV); a second non-terminal cell enclosing a second plurality of terminal cells, each of the second plurality of terminal cells enclosing a respective UAV; a first non-terminal cell linkage member fixedly coupled to the first non-terminal cell; a second non-terminal cell linkage member movably coupled to the second non-terminal cell; and a non-terminal cell pivot joint to pivotally couple the first and second non-terminal cell linkage members; wherein the first and second non-terminal cells are arranged in a single plane, and first and second non-terminal cell linkage members and the non-terminal cell pivot joint provide controllable movement of the first and second non-terminal cells with respect to one another and within the single plane.