1220results about "Aircraft convertible vehicles" patented technology

A combined submersible vessel and unmanned aerial vehicle preferably includes a body structure, at least one wing structure coupled to the body structure, at least one vertical stabilizer structure coupled to the body structure, and at least one horizontal stabilizer structure coupled to the body structure. A propulsion system is coupled to the body structure and is configured to propel the flying submarine in both airborne flight and underwater operation. Preferably, the propulsion system includes a motor, a gearbox coupled to the motor and configured to receive power generated by the motor and provide variable output power, a drive shaft coupled to the gearbox and configured to transfer the variable output power provided by the gearbox, and a propeller coupled to the drive shaft and configured to accept power transferred to it from the drive shaft. The propeller is further configured to rotate and propel the flying submarine in both an airborne environment and in an underwater environment.

A combination rotor and wheel assembly for an unmanned vehicle with ground and aerial mobility has a rotor arm adapted to be attached at an inner end thereof to a vehicle body. A rotor is rotatably connected to an outer end of the rotor arm about a rotor axis, and a rotor drive mounted on the rotor arm rotates the rotor such that the rotor exerts an upward lift force on the rotor arm. An open spoked wheel is rotatably connected about the rotor axis independent of the rotor The diameter of the wheel is greater than that of the rotor, and a bottom edge of the wheel is below the rotor. A wheel drive rotates the wheel. Vehicles can have various numbers and orientations of the rotor and wheel assembly to provide aerial and ground mobility.

A hybrid fixed wing aircraft converts into a roadworthy vehicle in a matter of seconds therefore operating efficiently in both air and ground transportation systems. The single piece wing is mounted on a skewed pivot that is on the lower portion of the fuselage and is operated by a pushbutton operating system. The aircraft includes telescopic twin boom tail design that when extended allows good pitch stability and damping. The aircraft's wing area may be increased with additional telescopic wing tip segments. This allows an increase in aspect ratio, hence improving efficiency at high loads. This feature will also creates a reduction in induced drag at cruise speed by simply retracting the tips in flight. The vehicle has a unique synchronized control system that switches from flight to ground mode without input from the operator, thereby providing a natural interface for the operator.

A combination rotor and wheel assembly for an unmanned vehicle with ground and aerial mobility has a rotor arm adapted to be attached at an inner end thereof to a vehicle body. A rotor is rotatably connected to an outer end of the rotor arm about a rotor axis, and a rotor drive mounted on the rotor arm rotates the rotor such that the rotor exerts an upward lift force on the rotor arm. An open spoked wheel is rotatably connected about the rotor axis independent of the rotor The diameter of the wheel is greater than that of the rotor, and a bottom edge of the wheel is below the rotor. A wheel drive rotates the wheel. Vehicles can have various numbers and orientations of the rotor and wheel assembly to provide aerial and ground mobility.

Flying Car, readable aircraft, amphibian, multimode, multifunctional, composite versatile personal transport vehicle with twin, parallel fuselages, hulls, each with inflatable pontoons and / or wheels below and a cabin. Combined, aircraft, airplane, aeroplane, flying, air, aerial, airborne vehicle with variable, folding wings which is convertible via automatic transformation to a land vehicle and to a sea vessel. Two wings are stored between the fuselages. They extend on a system of rails, pivots and counter-rotating, fuselage-mounted arms which then sink flush into the wings' undersides and lock for flight. Upon wing extension and retraction, controls for road transport and flight controls alternately emerge or are stowed inoperably, as needed. Engine power alternately drives a propeller for flight, wheels for road travel and a separate, submersible, marine propeller for water transport.

The invention discloses a flying automobile with front folding wings and rear folding wings are arranged in series. The front wings are arranged on two sides of the front part of an automobile body; the rear wings are arranged on two sides of the rear part of the automobile body; after being turned and folded, the front wings can be collected on two sides of the automobile body in parallel or collected in a front carriage in a vertical stacking manner; after being turned and folded, the rear wings can be collected on the rear upper side on the top of the automobile body; large-area solar battery panels are arranged on the surfaces of respective parts of the wings and the automobile body; when the wings are unfolded completely, the flying automobile is turned into a serially-arranged fixed wing airplane and becomes a giant solar charger, and the solar battery panels and batteries supply power; when the wings are folded, the appearance and the size of the flying automobile are the same as those of a common sedan; and an underwater propeller is arranged at the bottom of the automobile, so that the flying automobile can be landed on water and sails in the water. The flying automobile is well combined with functions of an airplane, an automobile and a ship and is environment-friendly and high in continuous voyage capacity and suitable for families.

A road / air vehicle is able to quickly and easily convert between two configurations, air configuration and road configuration, to facilitate practical operation as both an aircraft and as an automobile. In air configuration the craft includes two laterally symmetrically flight surfaces; a smaller forward canard wing, generally horizontally disposed and a larger rearward main wing generally horizontally disposed with fin surfaces, generally vertically disposed, at each tip. Control surfaces on the main wing, the canard wing and the tip fins severally provide roll control, pitch control and yaw control in flight. The wheels / undercarriage are of a laterally symmetrical rectangular pattern, with the lateral distance between the two forward wheels and the two rearward wheels being similar. The forward wheels are steerable for ground operations. A suitable powerplant drives the rear wheels for ground operations. A second suitable powerplant provides direct atmospheric thrust for flight operations. In road configuration all flight surfaces and avionics sensors are folded and stored inside compartments within the body of the craft. Controls to facilitate both ground and flight operations are available for a single operator to perform the functions of both driver in road configuration and pilot in air configuration.

A telescopic aircraft wing having an articulated structural spar. The telescopic wing includes a root portion and a tip portion that is telescopically related to the root portion. A spar assembly connects the root portion to the tip portion for providing structural support to the tip portion, and the spar assembly has a plurality of links that are pivotally connected to one another. The spar assembly moves the tip portion with respect to the root portion between an extended position and a retracted position.

A method and apparatus are provided for constructing, operating, and marketing a vehicle that is alternatively adaptable for controlled, powered operation on the ground as an all-terrain vehicle (ATV), or in the air as a powered parachute, or for controlled, powered operation on both the ground and in the air as a flying ATV. On the ground, the vehicle is configured for controlled, powered operation over both smooth and rough terrain, as a true all-terrain vehicle.

A vertical take-off and landing aircraft is provided with a plurality of thrust generators which generate thrust substantially vertically upward with respect to the aircraft; a first prime mover which drives the thrust generators, and an occupant seat. At least one of the thrust generators is disposed at either a front section of the aircraft or a rear section of the aircraft, and the remaining thrust generator or thrust generators are disposed at either the rear section or the front section, whichever the at least one of the thrust generators is not disposed at. The prime mover and a sitting surface of the occupant seat are disposed between the at least one of the thrust generators at the front section of the aircraft and the at least one of the thrust generators at the rear section of the aircraft, and in a position lower than all of the thrust generators. The center of gravity of the vertical take-off and landing aircraft is below the center of the aircraft and hangs down when the aircraft is in flight due to the thrust generated by the thrust generators.

A vertical take-off and landing (VTOL) roadable aircraft which has the features and dimensions of a typical road vehicle is disclosed. When operated on the road the wheels are powered by the engine. When the vehicle is configured for flight, a plurality of propellers is deployed from the storage compartment located on the roof and is powered by the same engine. The conversion process transforms the vehicle into a highly manoeuvrable quadcopter or a multi-rotor aircraft. The design concept enables propellers of relative large diameter to be conveniently secure to the vehicle, while allowing reliable deployment, retrieval and storage of the propellers as required. The total combined area of the propellers enables a low disk loading in the range of some helicopters with equivalent flight efficiency. The propellers are shrouded for safe operation. The conversion is automated, fast, and can be carried out while the vehicle is still moving.

A combination powered parachute and motorcycle modifies an initially conventional motorcycle with the addition of various flight components to provide sustained flight for the machine. A peripheral and overhead safety structure is installed upon the motorcycle, with a second flight engine, propeller, folding propeller guard, and fuel system also installed. The flight engine and all of its systems are completely independent of the conventional motorcycle engine used for surface propulsion. A set of laterally disposed stabilizer wheels is also provided for transition from ground to flight and from flight to ground operation. Lift is provided by a folding parafoil device of either the ram air inflated or partially pneumatically inflated type. For flight operations, the lateral wheels are lowered and extended, the folding propeller guard is extended, and the parafoil is deployed behind the motorcycle, with the parafoil lifting conventionally upon attaining flight speed.

The invention relates to the field of air-ground dual-dwelling vehicle technology, in particular to a longitudinal-line-type dual-culvert vertical-lifting air-ground vehicle. The vehicle comprises a vehicle body, a driving cabin and vehicle wheels that are arranged on the vehicle body; the front end and the rear end of the vehicle body are respectively provided with a ducted propeller; each ducted propeller comprises a culvert, an airscrew and a bracket; the rotation shaft of the airscrew is arranged vertically; the airscrew is provided with an automatic inclining device; two airscrews are driven to rotate reversely by an engine of the vehicle body; the vehicle can be driven on road by the vehicle wheels and can realize vertical lifting and flying by the lifting force provided by the rotation of two vertical ducted propellers; the flying, landing, suspending, heading, withdrawing and rotating are realized by adjusting the rotation speed difference of the two ducted propellers and / or the elevation of the oars; the controllability is good and the structure is simple; the culverts protect the airscrews and the passerby simultaneously and avoid the passerby from being harmed by the airscrews, thus having high safety performance.

The multifunctional aircraft used for low altitude and low speed flying platform includes one aircraft body and one power plant as well as one walking mechanism below the aircraft body and comprising universal wheels and driving motor. The aircraft body is one hollow flat disc with inside culvert fan and fan motor and outside support rods. The power plant includes propellers and motors installed separately on the support rods. The present invention has simple structure, low cost, stable and flexible low altitude and low speed flying and functions of adsorbing and walking.

Systems and methods for using unassisted vehicles to assess damage in a particular location are described. According to certain aspects, the systems and methods may utilize an unmanned ground vehicle (UGV) and a plurality of unmanned aerial vehicles (UAVs). The UGV and the UAVs may be configured with various sensors to capture various damage or environmental data. The UGV and / or the UAVs may also transmit captured data to a central facility for processing. The UGV may serve as a mobile docking and recharging platform for the UAVs and may therefore extend the range and endurance of the UAVs. The UGV may be configured for remote operation, thus eliminating the need to send personnel into a potentially dangerous environment.

The invention relates to a novel four-rotor-wing amphibious robot, and belongs to the field of robots. The novel four-rotor-wing amphibious robot comprises a rotor wing craft mechanism, a control mechanism, a ground walking mechanism and an information collection mechanism. The rotor wing craft mechanism is composed of rotor wings, a motor a, a motor b, a motor c, a motor d and a rack; the control mechanism comprises a control box, and a high-energy-storage battery, a small type PLC system and an analog module are arranged inside the control mechanism; the information collection mechanism is composed of an airborne portion and a wireless transmission system, and the airborne portion comprises a micro camera and a video transmitter; two-segment design is carried out on the ground walking mechanism through four feet, and rapid transverse moving and steering are achieved. A lighting device is composed of two sodium lamps. The novel four-rotor-wing amphibious robot has the beneficial effects of being large in load, light in material, small in size, low in cost and not prone to being found. The novel four-rotor-wing amphibious robot is high in intelligent strength, multifunctional, multipurpose, and high in amphibious operability. Each walking structure can be freely rotated and driven, and a ground walking structure is more rapid and effect. The novel four-rotor-wing amphibious robot is beneficial to ground rapid action and is high in practicability.

A robust amphibious air vehicle incorporates a fuselage with buoyant stabilizers and wings extending from the fuselage. At least one lift fan is mounted in the fuselage. Movable propulsion units carried by the wings are rotatable through a range of angles adapted for vertical and horizontal flight operations.

The invention relates to a roadable aircraft vehicle (100) and related systems. An example roadable aircraft vehicle (100) includes a vehicle drive system (262) including an engine (264) and gearbox (206) selectively engageable with an automotive driveline (266) and at least one propeller (270), a user interface including a display (202) for controlling the drive system (262) in an automotive mode including a steering wheel (204) and in a flight mode including a control stick (272), a control system for switching between the flight mode and the automotive mode, and a system (236) for locking the propeller (270) during the automotive mode. The invention also relates to aircraft systems and elements such as an airfoil (106) having a nominal profile, a folding wing (102), and an occupant crash protection system for an aircraft (100).

The invention discloses a self-help switching type air-and-ground dual-purpose aircraft and belongs to the field of aircrafts. The aircraft mainly comprises an aircraft body, a switching driving mechanism, a taking-off and landing supporting mechanism and the like, wherein wheel rotors of the aircraft body are fixed at two ends of rotor cross beams; the switching driving mechanism controls the rotor cross beams to rotate through gear meshing, so that the wheel rotors are switched horizontally and vertically; the taking-off and landing supporting mechanism comprises a third motor, a lifting screw and a landing gear, the third motor is fixed on the aircraft body, the landing gear is rotationally connected with the lifting screw, and the lifting screw is driven by the third motor to perform lifting movement relative to the aircraft body. The landing gear having a lifting function is arranged on the aircraft body, so that the aircraft can be switched automatically between a flying mode and a ground driving mode, has the high intelligent degree and is applicable to field investigation.

Improvements to the hinge of a folding aircraft wing including a load bearing hinge mechanism with multiple locking mechanisms. The mechanism includes rigid panels that cover the hinge area when the wing is deployed, and the wing itself covers the hinge area when the wing is retracted. A control lever is used to actuate the wing and incorporates safety features to prevent unwanted actuation.

Systems and associated methods for rapid integration and control of payloads carded by a multi-mode, unmanned vehicle configured to accommodate a variety of payloads of varying size, shape, and interface and control characteristics. Mechanical, power, signal, and logical interfaces to a variety of payloads operate to enable environmental protection, efficient placement and connection to the vehicle, and control of those payloads in multiple environmental modes as well as operational modes (including in air, on the surface of water surface, and underwater).