105results about How to "Achieve vertical takeoff and landing" patented technology

The invention relates to the field of aircrafts, in particular to a six rotor-wing aircraft. The six rotor-wing aircraft comprises a body, six rotor wings, a power device and an electric control system arranged in the body, wherein the power device is directly connected with the rotor wings or is arranged inside the body to be connected with the rotor wings through a transmission device; the body is provided with six connecting rods which are distributed at the periphery of the body; the rotor wings are arranged at outer ends of the connecting rods; six angles of inclination are formed between rotating surfaces of the six rotor wings and an XOY plane of a body coordinate system; angles of inclination between each rotor wing and the third rotor wing which is two rotor wings away are equal; and positive and reverse propellers are arranged on two rotor wings and have opposite rotating directions. By controlling rotating speeds of the six rotor wings with non-parallel rotating planes, three-axis motion and posture are completely decoupled, and the aircraft has high maneuverability, and can realize vertical takeoff and landing, rapid forward flight, upside down flight, hovering and change of flight in any direction.

The invention discloses a single-lift-force duct vertical take-off and landing aircraft based on a tilting duct and relates to an aircraft. The single-lift-force duct vertical take-off and landing aircraft comprises an aircraft body, two wings, N tilting duct fans, a single-lift-force duct fan and a duct cover. The wings are arranged on the two sides of the rear middle portion of the aircraft bodycorrespondingly, and each wing is formed by means of the method that the wing stretches outwards from the side portion. Each set of tilting duct fans is mounted on the two sides of the aircraft bodycorrespondingly, and each tilting duct fan is rotatably connected with the aircraft body through a corresponding connecting piece. The single-lift-force duct fan is inlaid among the aircraft body andthe two wings. The duct cover is mounted on the upper portion of the single-lift-force duct fan and can be opened or closed. Through the tilting duct fans, posture control in the vertical take-off andlanding stages and propulsion in the horizontal flying stage are achieved. Through the single-lift-force duct fan, main life force in the vertical take-off and landing stages is provided, vertical take-off and landing are achieved, and the lift force and the posture control part are decoupled, so that the complexity of the power characteristic is lowered, and the reliability is improved.

The invention discloses a double ducted-propeller electric manned aircraft capable of taking off and landing vertically, and belongs to the field of aviation products. The aircraft comprises an aircraft chamber, double ducted-propeller power systems and a control platform, wherein lateral wings with vertical planes are fixedly and integrally arranged on two sides of the aircraft chamber; the ducted-propeller power systems are arranged at the front end and the rear end of the aircraft chamber and are connected with the lateral wings respectively; a self-balancing mechanism is arranged on the lateral wing on one side; a duct rotating mechanism is arranged on the lateral wing on the other side; the self-balancing mechanism and the duct rotating mechanism are both connected with the ducted-propeller power systems; and the control platform and a battery pack are arranged in the aircraft chamber. The invention further provides a realization method for the aircraft, which adopts the rotation of propellers to generate pushing force, realizes left and right automatic balancing as well as forward and backward rotation of ducts by matching the self-balancing mechanism and the duct rotating mechanism, realizes the vertical taking off, landing and advancing of the aircraft by combining the wing-type streamline design of the aircraft chamber, makes full use of the efficiency of a motor, saves energy and is safer.

The invention discloses a micromechanical controllable flapping rotary wing aircraft and a manufacturing method as well as a control method thereof. Flight principle of the invention is that: wing oscillation is realized through motor driving; thrust force couple is produced to rotate; and then lift force is produced to realize flight. The control method provided by the invention comprises the following steps of: producing variable lift force by wings by adjusting motor power to realize control over vertical takeoff and landing and hovering; by using downwash produced by rotation of the wings, producing couple around a vertical oscillation shaft in a horizontal plane by controlling a steering control plane outside a body; driving the body to rotate to realize steering control; and forming resultant force in a certain direction in the horizontal plane by controlling a forward flight control plane outside the body to drive the aircraft to fly forward so as to realize forward flight control. The device has a simple and reliable structure and is low in cost. A steering and forward flight control system provided by the invention can realize the functions of vertical takeoff and landing, hovering, steering control and free forward flight of the aircraft.

The invention provides a water-air amphibious unmanned rescue platform which can sail on the water surface and can also fly in the air. Two sailing modes can be rapidly and freely switched, water surface sailing depends on two small water plane streamline ship bodies and marine propellers installed behind the ship bodies, and the propelling mode adopts double-propeller differential propelling; andfour four-rotor propellers and matched brushless motors are used for sailing in the air, and are fixed right over the rescue platform in a square shape. According to the invention, the remote rescuematerial throwing device provided by the invention adopts a simple and reliable door type structure, so autonomous tracking and autonomous obstacle avoidance functions can be realized. According to the unmanned rescue platform, the advantages of a small waterplane catamaran and a quadrotor unmanned aerial vehicle are combined, rapid crossing of a discontinuous water area can be achieved through the flight function of the unmanned rescue platform, the unmanned rescue platform can reach the water area without the launching condition of a conventional rescue ship in a flight mode, the environmental adaptability of the unmanned rescue platform is enhanced, and the working range of the unmanned rescue platform is enlarged.

The invention discloses a combined coaxial unmanned helicopter. The combined coaxial unmanned helicopter is provided with a helicopter shell, a helicopter body supporting structure, an engine, an oil tank, a helicopter main rotor, a helicopter main speed reducer, wings and a tail wing and further comprises a power distribution and clutch system and a propelling propeller. The propelling propeller is mounted on the rear portion of a helicopter body. The combined coaxial unmanned helicopter can fly at different flight stages according to different flight speeds, power of the engine is distributed to the main rotor and the propelling propeller through the power distribution and clutch system, and vertical take-off and landing, hovering, low-speed forward flying, medium-speed flying and high-speed flying are achieved. The combined coaxial unmanned helicopter has the advantages that compared with a conventional helicopter, the flying speed can be remarkably increased; one set of engine is used for supplying power to two sets of flying systems, and the weight is low; the two coaxial rotor wings are adopted, airflow is symmetrical, the pneumatic effect is good, the structure is compact, the size is small, the self-rotation mode is achieved at the high speed, and resistance force is smaller.

The invention discloses a structure of a vertical take-off and landing rotor aircraft, which comprises a flying wing aircraft body and wings connected with the flying wing aircraft body, wherein the rear part of the flying wing aircraft body is provided with a vertical stabilizer, a horizontal stabilizer and wing flaps; a pair of wings is arranged on each side of the flying wing aircraft body which is flat and long; the middle parts of the wings are connected with the flying wing aircraft body through tilting gears; rotor systems are arranged on the two ends of wings; and rudders are arrangedon the two ends of the wings and below the rotor systems. In the structure of the aircraft, the flying wing aircraft body is combined with the rotor systems, a reasonable design enables the aircraft to take off and land vertically and reaches the flight speed and range of a fixed wing aircraft. The structure is relatively simple.

The invention discloses a miniature mechanical sliding rail type controllable flapping rotor craft. According to the principle of rotors, the rotors are driven by a motor, the rotors flap by the adoption of a mechanical manner of a sliding rail, then the rotors rotate, lifting force is generated by flaps and rotation of the rotors, and therefore the craft can fly. The craft is remarkably improved for solving the problems existing in existing flapping rotors, the vertical lifting function, the hovering function, the steering control function and the natural forward flying function of the flapping rotors are achieved, the problem that the flapping rotors vibrate in the horizontal direction is effectively solved, the structure compactness is greatly improved, and the weight losing effect is remarkable.

The invention discloses an environment-friendly sampling air vehicle.The environment-friendly sampling air vehicle comprises an air vehicle body, motors, rotor wings, a sampling mechanism and a remote controller, wherein a control system and a wireless receiver are arranged in the air vehicle body, and the wireless receiver is connected with the control system; the motors are connected with the control system of the air vehicle body; rotating shafts of the rotor wings are connected with output shafts of the motors; the sampling mechanism is installed on the air vehicle body; the remote controller is provided with a wireless transmitter in signal connection with the wireless receiver.The environment-friendly sampling air vehicle can automatically complete high-altitude sampling and is high in working efficiency; an operator only needs to control the air vehicle on the ground without ascending, and personal safety of the operator is effectively guaranteed.In addition, collected gas is high in purity.

The invention discloses a micro fixed-wing aircraft capable of hovering. The micro fixed-wing aircraft comprises an aircraft body as well as two horizontal rudder surfaces, two vertical tails, even sets of motors and propellers which are symmetrically arranged on the axle wire of the aircraft body; the motors are connected with the propellers and then are arranged at the head of the aircraft body; the two horizontal rudder surfaces are hinged to the tail of the aircraft body through hinges; the two vertical tails are vertically arranged on two sides of the tail of the aircraft body and are protruded relative to the upper surface and the lower surface of the aircraft body; a flight control system is arranged inside the aircraft body. The direction of the aircraft disclosed by the invention is controllable in a three-dimensional space at a vertical take-off, a landing and a hovering stage; under the control of assisted augmentation of the flight control system, flight motion of the aircraft in the three-dimensional space can be realized. With a wing-body integrated structure and a thin-wall aircraft body, substantial reduction of the size of the aircraft body can be realized; the aircraft disclosed by the invention has the advantages of convenience in carrying and use, small structure and conservation of manufacturing materials.

The invention discloses a novel flapping rotary wing structure and a corresponding micro-miniature flapping rotary wing device. The flapping rotary wing structure is characterized in that two pairs of complete flapping wings are arranged on two ends of a cross beam in a dissymmetry manner, a flex-wing film generates a lifting force and a thrust force simultaneously during an upper-down flapping process of flapping wings, two thrust forces in opposite directions form a force couple to drive the cross beam and the flapping wings to perform self-driven rotation without generating reaction torque. The flapping rotary wing device designed by utilizing the structure comprises the flapping wings, an assembling body provided with a driving mechanism and a power supply, a connecting shaft and half cross beams, wherein the half cross beams are assembled together to form the cross beam, the middle of the cross beam is fixedly connected with one end of the connecting shaft, and the flapping wings are fixed on the assembling body; an axis which is relative to the connecting shaft is installed at the two ends of the cross beam in the dissymmetry manner. The flapping rotary wing structure provided by the invention has the good lifting efficiency, the useful load of an aircraft can be obviously increased, the requirements of hovering and level flight can be simultaneously met, and the application range of a micro-miniature aircraft is effectively widened.

The invention relates to a multi-stage powerful fan and a vertical takeoff and landing aircraft. The multi-stage powerful fan provided by the invention is composed of multiple stages of concentric fan rings which extend from the center to the outside, wherein a gear ring is arranged on the outer rack ring of each stage of fan ring in a rotating manner, a plurality of fan blades use the common extension center as the center of rotation and are arranged on the gear ring uniformly and radially; and the gear ring is a follower which is in mesh transmission with a jugged part which transmits the same rotation power. The technical scheme of the invention realizes the technical aim of increasing the wind power conversion efficiency of the entire fan and has wide range of application. The vertical takeoff and landing aircraft provided by the invention utilizes the powerful lifting force generated by the multi-stage powerful fan for driving, thus the vertical takeoff and landing of the aircraft can be realized; and the multi-stage powerful fan has simple structure and light weight, can be used as a part of the airfoil surface and can not affect the normal flight of the aircraft.

The invention provides a lifting-pushing type large-scale solar-powered unmanned aerial vehicle capable of taking off and landing in a non-runway field and hovering. The unmanned aerial vehicle has the layout of front-and-back parallel wings in a ladder shape; solar batteries are laid on the whole upper surface of a back wing; an elevon with the overall span is installed on the trailing edge of a front wing, and solar batteries are laid on other areas of the upper surface of the front wing except the elevon; four vertical plates are fixedly arranged on the lower surface of the back wing, and the lower end surfaces of the four vertical plates are fixedly connected with the four end surfaces of the front wing in the span direction by stay bars; a power propulsion system is fixedly installed on the leading edge of the back wing; and two vertical lifting systems are respectively fixed in two spaces formed by the front wing, the back wing and the stay bars. According to the lifting-pushing type large-scale solar-powered unmanned aerial vehicle, the problem of ultra-short distance/vertical takeoff and landing of a large-scale solar-powered airplane is solved by increasing the direct lifting power and reducing the takeoff field length, and additionally, the direct lifting power can be provided in a near space to realize spot hovering to perform a task.

The invention relates to a portable small cylinder type coaxial reverse propeller three-blade rotor wing type unmanned aerial vehicle, and belongs to the field of unmanned aerial vehicles. The steering engine rotates to drive the steering engine disc and the steering engine connecting rod to rotate; the tilting direction of the tilting tray device is changed, the tilting tray device can tilt around the central spherical hinge to generate a tilt angle, so that free control over the plane of the tilting tray device is achieved, the change of the plane of the tilting tray device brings the changeof the plane tendency of the upper rotor wing, the direction of the lift surface of the upper rotor wing is changed, and the aircraft flies in all directions. The control mechanism is not complex, control over the coaxial reverse-propeller three-blade rotor wing structure is achieved, and due to the fact that the steering engine controls the plane inclination angle of the swash plate device, thecontrol system of the coaxial reverse-propeller three-blade rotor wing structure is easier than other similar aircrafts when being designed. On the premise that the functions of the coaxial propellerreversing unmanned aerial vehicle are achieved and the advantages of the coaxial propeller reversing unmanned aerial vehicle are brought into play, the complex structure of an existing coaxial propeller reversing unmanned aerial vehicle can be overcome, and the design difficulty of a control system is lowered.

The invention relates to a flying car of a tilting ducted structure. The flying car comprises a car body, one folding wings are arranged on the upper sides of the two sides of the middle of the car body correspondingly, tilting room mechanisms are arranged on both the end parts of the two folding wings; the tilting module mechanisms comprise ducted fans, and the ducted fans are arranged on the endparts of the two folding wings rotatably; when the flying car is running on the ground, the folding wings are under a folded state, and the ducted fans are turned into a horizontal state; and when the flying car is flying, the folding wings are under a spread state, the ducted fans are turned into a vertical state, and perpendicular taking-off and landing can be realized. According to the flyingcar of the tilting ducted structure, running on the ground and flying in air can both be achieved, when a ground running mode is turned into a flying mode, lifting force and pushing force can be generated simultaneously, so that the flying car can fly at high speed and in a long range, and the energy consumption is also less.

The invention discloses a distributed electric propulsion tilt rotor unmanned aerial vehicle. According to the aircraft, a three-section fixed type wing overall layout is adopted; front wings and rearwings are arranged in two layers; the wings in the upper and lower layer are each provided with electric propulsion ducted fans; a middle wing is mainly used for generating lift force when fixed wings fly; the ducted fans serve as a power system, and thrust generated by the ducted fans is used for achieving the vertical take-off and landing, hovering and fixed wing patrolling of the aircraft; tilting mechanisms are arranged at the joints of the front wings, the rear wings and an aircraft body so as to achieve mutual switching between a vertical take-off & landing and hovering mode and a fixedwing patrolling mode. When the aircraft has the speed required for patrol flight, transition from the vertical take-off & landing and hovering mode to the fixed wing mode is completed. According to the distributed electric propulsion tilt rotor unmanned aerial vehicle of the invention, the distributed electric propulsion ducted fans are adopted as the aircraft power system, and therefore, the size and weight of the power system are reduced, the redundancy and reliability of the power system are improved; and a ducted fan rotating speed differential mode is adopted during fixed wing patrollingflight, so that control efficiency can be improved.

The invention discloses vertical lifting hovercar. The vertical lifting hovercar comprises a hovercar body with two irregular vertical plates as the principle portion, wheels, stationary wings, ducted fans and a rudder, wherein the stationary wings, the ducted fans and the rudder are sequentially arranged from the front lower portion to the last rear portion of the hovercar body and respectively fixed on the vertical plates on two sides of the hovercar body. One engine is respectively installed at the front and rear portions of a base plate of the hovercar body and respectively connected with two pairs of ducted fans. When the vertical lifting hovercar runs on a highway, air inlets and outlets of the ducted fans are in a horizontal state, the hovercar runs ahead by utilizing reacting force of the ducted fans push air, and steering and braking are achieved by using a steering wheel and a brake pump to control the wheels. When the vertical lifting hovercar flies in the air, the air inlets and outlets of the ducted fans are in a vertical state, and downward push force produced in working enables the hovercar to achieve vertical lifting and suspension. When the ducted fans obliquely and forward rotate, the hovercar produces horizontal speed, the stationary wings produces lift force, and the ducted fans gradually and mainly provide pushing force for the hovercar. The flying hovercar is controlled by ailerons and flaps of the rudder during steering and lifting.

The invention provides a wing, a fixed-wing aircraft and a fixed-wing aircraft lifting method, and belongs to the field of aerospace. The wing comprises a wing body and auxiliary lifters; the wing body is provided with mounting through-holes which run through the wing body along the thickness thereof; the auxiliary lifters refer to lift fans or propellers or rotors mounted in the mounting through-holes; retaining cover plates are respectively arranged at two ends of the mounting through-holes and are movably arranged on the wing for closing or opening the mounting through-holes. The fixed-wing aircraft is formed after the wings are mounted onto a fuselage, and the fixed-wing aircraft is combined with the auxiliary lifters to form a novel fixed-wing aircraft; thus, vertical takeoff and landing or short-range takeoff and landing of the fixed-wing aircraft can be realized, requirements for takeoff and landing sites are lowered, and the fixed-wing aircraft is adaptable to more applications and has more diversified functions. After the fixed-wing aircraft reaches the set cruising speed, the retaining cover plates close the mounting through-holes, and no influence is caused to normal cruising of the fixed-wing aircraft from the auxiliary lifters.

The invention relates to a flying disk comprising a capsule, a control system, an electrical system, facilities in the capsule and a starting system, wherein a capsule motion direction adjusting device and a capsule rotation stability adjustment device are installed on the capsule, and an intelligent machine is installed on the capsule and comprises a flywheel shaft, a flywheel and a plurality of air cylinders; the flywheel shaft is connected with the capsule, the flywheel is installed on the flywheel shaft, a linear particle generating chamber is arranged on the flywheel, an air inlet is arranged on the middle part of the linear particle generating chamber, and the plurality of air cylinders are installed on the periphery of the flywheel; and parts of the air cylinders, which are adjacent to the end of the flywheel shaft, are provided with air inlets of the air cylinders, the air inlets of the air cylinders are communicated with the periphery of the linear particle generating chamber, an included angle between the air jet direction of each air cylinder and the radius of the fly wheel is phi 1, and an included angle between the air jet direction of each air cylinder and a plane which supports the fly wheel and is perpendicular to the flywheel shaft is phi 2. Being identical with the aviation characteristics of the legendary UFO, the flying disk can get rid of the gravitational force, instantaneously achieve high speed, use any element or dark matters as fuel, realize free fuel and galaxy navigation and replace the traditional means of transportation, thereby being an ultimate means of transportation.

The invention discloses a three-airfoil layout vertical take-off and landing general aircraft, which comprises a wing, a fuselage, a tail wing, a duck wing, a power device, a connecting device, a propulsion system and a duck wing coaxial rotating device. The power device comprises a first power device, a second power device, a third power device and a fourth power device; the top of the fuselage is provided with the duck wing. Both ends of the duck wing are respectively provided with the first power device and the second power device. Both sides of the outer part of the fuselage and below theduck wing are respectively provided with wings. A connecting device is arranged below the wing. Both sides of the connecting device are respectively provided with the third power device and the fourthpower device. The bottom of the fuselage is provided with the tail wing. The control device is arranged inside the fuselage. The aircraft solves the problems of insufficient lift force, without direct force control, low static instability, low take-off and landing performance, poor safety reliability, heavy wing load, low take-off load and high use cost of the general aircraft.

The invention provides a fixed-wing aircraft taking off and landing system and method, belongs to the technical field of air vehicles, and particularlyrelates to a fixed-wing aircraft taking off and landing system and method. The system comprises a left four axis unmanned aerial vehicle, a right four axis unmanned aerial vehicle, a fixed wing aircraft and a back four axis unmanned aerial vehicle; the fixed wing aircraft is provided witha left combined section, a right combined sectionand a back combined section; each of the three four axis unmanned aerial vehicles comprises a fixed board and a combined rod, the combined rod comprises a combined head; when the aircraft takes off, the combined heads of the three combined rodsare embedded inthe three combined sections of the fixed wing aircraft, the three four axis unmanned aerial vehicles carry the fixed wing aircraft and are separated after the aircraft takes off; when the aircraft lands on the ground, the three four axis unmanned aerial vehicles are launched in the sky and combined with the fixed wing aircraft, the three combined headsare embedded in the three combined sections, and the three four axis unmanned aerial vehicles carry the fixed wing aircraft to land. The fixed-wing aircraft taking off and landing system and method exploitwell the advantages of the vertical taking off and landing of the four axisunmanned aerial vehicles, further overcome the disadvantage that the taking off or landing of the fixedwing aircraft needs the assistance of the runway;furthermore a way of aircraft taking off and landing is invented.

A flying method and aircraft, comprising a container, an aerodynamic forming device fixedly connected with the container, and an intelligent control system connected with the aerodynamic forming device; the container is a volumetric container, which can form a certain buoyancy; The aerodynamic forming device described above is designed and manufactured according to the principle of aerodynamics, and it can form a certain aerodynamic force; further, in order to make the aircraft realize intelligent driving, an intelligent control system is provided on this aircraft. The flight method of the present invention is not driven by the buoyancy formed by the aircraft or the aerodynamic force formed by the aerodynamic forming device formed by the aircraft to push the aircraft to fly. It is characterized in that the buoyancy formed by the aircraft and the aerodynamic force of the aircraft The two aerodynamic forces generated by the forming device act together on the aircraft to realize flight, and by controlling the size of the aerodynamic force, the aircraft can be lifted into the air, fly and land.

The invention provides a disc type aircraft, which has the advantages of small volume, simple structure, high safety and strong applicability. The aircraft comprises a control cabin, an aircraft body, a variable torque system, a rotor wing system, a transmission device, a power system and an undercarriage. The aircraft body is of a fixed frame body of the aircraft integral structure. The control cabin is arranged above the aircraft body. The variable torque system is driven by a servo motor. The servo motor is connected to a gear transmission mechanism and a variable torque hinge. The rotor wing system is connected at one side of the variable torque system. The rotor wing system is arranged on the outer edge of the aircraft body and comprises an upper paddle, a lower paddle and a propelling paddle. The outer ends of the upper paddle and the lower paddle are respectively fixed through a fixed ring. The propelling paddle is arranged at the bottom of the aircraft body and connected to a motor for driving the propelling paddle. A gear ring is arranged at the other side of the variable torque system. The gear ring is matched with the transmission device in the form of a gear. The power input shaft of the transmission device is connected with the power system. The power system is composed of a gearbox, a clutch and an engine and arranged in an aircraft body cabin. The undercarriage is fixed at the bottom of the aircraft body.

The invention relates to the field of aviation, in particular to a petrol-electric hybrid power airship. The petrol-electric hybrid power airship comprises an airship body (1) and a power device (2), and the power device (2) is arranged below the airship body (1). The petrol-electric hybrid power airship is characterized in that the power device (2) is a petrol-electric hybrid power device and comprises three propellers (21, 22, 23), wherein two of the propellers (21, 22) are electric propellers, and one propeller (23) is liquid fuel power propeller. According to the petrol-electric hybrid power airship, the liquid fuel power propeller and the electric propellers are organically combined, so that control response of the airship in the aviation process can be rapidly achieved, and the flight posture is rapidly adjusted so that different aviation requirements can be met.

The invention relates to a combined aircraft and a take-off and landing way thereof, which belong to the technical field of aviation. The combined aircraft comprises a fixed wing aircraft, a multi-rotary-wing aircraft, a connecting platform, electromagnetic occlusion columns, a communication system and a radar criterion apparatus, wherein the radar criterion apparatus comprises a monitoring radar and a transmitting radar; each electromagnetic occlulation column comprises an electromagnetic occlusion sub column and an electromagnetic occlusion main column; the electromagnetic occlusion main columns and the monitoring radar are disposed in the connecting platform, the connecting platform is disposed on the multi-rotary-wing aircraft at a certain oblique angle, and the electromagnetic occlusion sub columns and the transmitting radar are arranged in the fixed wing aircraft. When the combined aircraft takes off, the multi-rotary-wing aircraft drives the fixed wing aircraft to take off, and when the fixed wing aircraft reaches take-off speed, the multi-rotary-wing aircraft is separated from the fixed wing aircraft; and when the fixed wing aircraft lands, the multi-rotary-wing aircraft lifts for handover, a radar calibration apparatus is used for accurate docking, and the multi-rotary-wing aircraft carries the fixed wing aircraft to land. The take-off and landing way of the combined aircraft is not limited by fields, and the vertical take-off and landing of the fixed wing aircraft can be realized.