20results about "Convertible aircrafts" patented technology

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.

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 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.

The invention relates to transportation equipment, in particular to an assembly and a method for moving a payload, in particular to a system and a method for moving a payload. The present invention provides a system and method for moving a payload based on the use of aircraft devices configured to interface with each other in order to enable interchange of guides and payloads. The invention comprises two independent claims and nine drawings.

A processing system including at least one processor executing a traffic management application may detect a proximity to a traffic zone for vehicular traffic, the dual-mode vehicle having two modes of operation, the two modes of operation comprising a surface mode of operation and an aerial mode of operation, and may verify a rule set for vehicular operations within the traffic zone. The processing system may then identify a leader traffic management application from among a plurality of traffic management applications of a plurality of dual-mode vehicles within or near the traffic zone, obtain at least one navigation instruction from the leader traffic management application, and perform at least one of: executing a navigation action in accordance with the at least one navigation instruction, or displaying at least a portion of a permitted route that is in conformance with the at least one navigation instruction.

According to the present disclosure, a vehicle configured to travel on roads and fly through the air is provided. The vehicle of the present disclosure includes a fuselage extending from a forward end to an aft end along a roll axis of the vehicle, a pair of main wings attached to the aft end of the fuselage, a pair of canards attached to the fuselage forward of the main wings, a plurality of wheels configured to enable travel on roads, and a rotor system including a plurality of rotors. Each of the main wings and the canards is configured to be displaced from the fuselage to a position extending along the pitch axis of the vehicle when deployed, and to be displaced to a position overlapping the fuselage when retracted. The rotor system includes a pair of tiltable main rotors respectively attached to each of the main wings, and each tiltable main rotor is configured to be tiltably displaced to a plurality of tilt positions between a forward position in which its rotation axis is substantially parallel to the roll axis of the vehicle and an upper position in which its rotation axis is substantially parallel to the yaw axis of the vehicle.

A supply glider is disclosed herein. The supply glider includes a body having a first end and a second end, the body being configured to be coupled to a host aircraft, a container disposed between the first end and the second end of the body, wings coupled to the body between the first end and the second end, and stabilators coupled to the body adjacent the second end.

The present invention concerns a compliant Robot comprising a frame (1), a payload (2) and locomoting wheels (3) for driving as a rover or swimming, characterized in that the frame (1) comprises at least two elastic rods each configured in the shape of a ring, both rings being assembled together by short connectors (10) and long connectors (11), thereby defining a repetitive eye-shape pattern around the circumference of the rings, the robot further comprising tendons (4) actuated by winches (5) and pulling on short connectors (10) at tight locations while the wheels (3) are mounted on long connectors (11).

Transportation equipment, in particular to systems and methods 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.

This utility model relates to the field of aircraft technology and discloses a cross-medium aircraft, comprising: a functional module, a power module, a control module, an integrated module, and a submersible module. The power module is divided into a front power mechanism and a rear power mechanism. The control module is located between the front and rear power mechanisms and is used to manipulate the lift direction of the front and rear power mechanisms, thereby controlling the flight attitude of the aircraft. The front and rear power mechanisms are hingeless rotors that provide lift for the aircraft. The other side of the front power mechanism is connected to the functional module, which carries the functional equipment for the aircraft's operation. Depending on the mission requirements, it can carry different modules such as reconnaissance electro-optical spheres, high-energy explosives, and relay communication cabins. Through modular design, the structure of an airborne aircraft and a submersible is integrated, solving the problems of complex and bulky cross-medium flight structures and limited functionality.

A flight vehicle includes a frame, a propulsion system coupled to the frame, a first source of power coupled to the frame and configured to power the propulsion system, a traction wheel coupled to the frame and configured for tractional engagement with a ground surface during low-speed ground operation of the flight vehicle, and a second source of power coupled to the frame and configured to power to the traction wheel.

The propulsion unit including a casing having an inner curved surface and an outer curved surface, at least one tire disposed within the casing within a duct defined by the inner curved surface and the outer curved surface, a first propeller and a second propeller having a plurality of blades extending from within the casing toward a center axis of the casing, and one or more motors housed within the casing, the one or motor being configured to operate the at least one tire, the first propeller, and the second propeller independently of one another. There is also provided a vehicle with one or more propulsion units of the present disclosure.

To provide an unmanned aerial vehicle for an effective perching UAV having a releasable crawler for inspecting or maintaining a structure.SOLUTION: A UAV 100 includes a body, and three or more legs connected to the body and configured to land and perch the UAV on a curved ferromagnetic surface 50. Each leg includes a first portion connected to the body, a second portion including a magnet 120 and configured to magnetically attach and maintain the magnetic attachment of the leg to the ferromagnetic surface during the landing and perching, and a passive articulation joint connecting the first and second portions and configured to passively articulate the second portion with respect to the first portion in response to the second portion approaching the ferromagnetic surface. The UAV further includes a releasable crawler 150 including magnetic wheels, which detach the crawler from the body during the perching and maneuver the crawler on the ferromagnetic surface while magnetically attaching the crawler to the ferromagnetic surface after the detachment.SELECTED DRAWING: Figure 1A

The group of inventions relates to a system and a method for moving a payload. The system comprises two or more aircraft apparatuses, wherein at least on a first one of said aircraft apparatuses there is detachably installed a payload and on a second one of said aircraft apparatuses there are detachably installed one or more docking guides. In order to move the payload two aircraft apparatuses, on one of which there is installed a payload and on the other one of which there are installed docking guides, are docked to each other, the payload is moved to the second aircraft apparatus and the docking guides are transferred to the first aircraft apparatus. The inventions make it possible to increase the delivery range of the payload and expand the armory of technical means for carrying out such delivery.

The application relates to an aircraft, which comprises a body, front walking wheels, rear walking wheels and an adjusting mechanism; the adjusting mechanism comprises a guide rail, a guide rack, a sliding seat, a transmission gear and a driving motor; the guide rail and the guide rack are arranged on the body, the length direction of the guide rail and the length direction of the guide rack are arranged along the length direction of the body, the sliding seat is slidably connected with the guide rail, the transmission gear is rotatably arranged on the sliding seat, the transmission gear is in meshing connection with the guide rack, the driving motor is arranged on the sliding seat and is used for driving the transmission gear to rotate; the front walking wheels are rotatably arranged on the body, and the rear walking wheels are rotatably arranged on the sliding seat. The application can effectively adjust the overall gravity center of the aircraft, improve the driving stability of the aircraft in a complex road traffic system and effectively reduce the overturning risk.

The application discloses a cross-medium aircraft variable nose cone device and a cross-medium aircraft, and relates to the technical field of cross-medium aircrafts. The cross-medium aircraft variable nose cone device comprises a base and a variable mechanism. The base is used for fixedly connecting to the aircraft body. The variable mechanism comprises a head shell assembly and a driving assembly. The head shell assembly is movably arranged on the front side of the base. The driving assembly is arranged on the base and is in transmission connection with the head shell assembly. The driving assembly can drive the head shell assembly to expand outward or contract inward relative to the base. The cross-medium aircraft variable nose cone device and the cross-medium aircraft provided by the application can improve the navigation performance of the cross-medium aircraft.

[Problem] To make it possible to fly stably using a large lift and thrust, continue flying or safely land when the rotation of one propeller has stopped mid-flight, land from a flying state onto a road on which vehicles are traveling and travel on the same, and stabilize the attitude in a left / right direction even against a sudden crosswind. [Solution] A land-and-air mobile body 1 comprises: a mobile body main body 10; front wheels 31, 32 and rear wheels 33, 34 that are for travel and are at the front and rear of an occupant cabin 11 of the mobile body main body; and a set of an upper front section propeller 421 and a lower front section propeller 441 and a set of an upper rear section propeller 461 and a lower rear section propeller 481 that are for flight and are in positioning spaces of a front section and a rear section of the mobile body main body, wherein the front wheels are driven by an electric motor, and inner rotary shafts 411, 451 and outer rotary shafts 431, 471 of the propellers, said inner rotary shafts and said outer rotary shafts using electric motors 231, 241, 251, 261 to rotate in the opposite manner from each other and generate lift and thrust, are positioned coaxially and parallel to the vertical direction of the mobile body main body.

This invention relates to the field of amphibious vehicle technology, and in particular to a multi-modal amphibious vehicle capable of operating across water and air media. The amphibious vehicle comprises a main shell, a dual-rotor counter-rotating motor, a connecting rod, aerial rotors, and an underwater duct propulsion system. The dual-rotor counter-rotating motor is located on the top of the main shell, with its output end connected to the connecting rod. Aerial rotors are mounted at both ends of the connecting rod. The main shell extends to both sides to form biomimetic wings, with underwater duct propulsion systems mounted at their ends. The rotor configuration is adjusted using an electrically operated telescopic rod. This invention reduces overall size and weight by using the dual-rotor counter-rotating motor to deploy and retract the rotors, avoiding interference between the water and air propulsion devices. During flight, the rotors deploy to increase airflow coverage, and retract upon entering the water to reduce drag, achieving dual-mode switching between water and air. The structure is compact, highly stable, and suitable for multi-scenario, cross-media operations.

This invention provides an amphibious off-road vehicle capable of overcoming obstacles and equipped with emergency safety features. It features a spine-type longitudinal beam, with a driver's cabin and power and transmission system mounted on the outer side of the middle section of the beam. The front and rear ends of the beam are supported by a front axle with front wheels and a rear axle with rear wheels, respectively. Floats are mounted under the beam. A retractable buffer landing device is located directly behind the beam, featuring a retractable, non-rotating piston rod extending from within the beam's tubular body to the rear outer side. A tail wheel is located at the end of the piston rod. Retractable tubular support legs, extending backward at an angle, are fixedly connected to the outer side of the rear section of the beam. From rear to front, a coaxial counter-rotating dual rotor, an electric multi-propeller propeller, and an ejection-type parachute assembly are sequentially arranged at the front of the beam. This vehicle possesses powerful off-road driving force, capable of traversing steep slopes exceeding 45 degrees, and can travel or fly on land and water at horizontal, upward, or near-vertical angles. It can also overcome obstacles and perform aerial hoisting, plant protection, and other operations.

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.