221results about How to "Easy to fly" patented technology

A rotary-wing apparatus that is aeronautically stable, easy to fly with a multidimensional control, small size, and safe to fly and low cost to produce. The rotary-wing apparatus includes a coaxial counter rotating rotor drive providing lifting power with an inherent aeronautical stability; Auxiliary propellers that face the direction of flight and are located on opposite sides of said coaxial Rotary-wing apparatus and enable flying forwards, backwards and perform yawing; A rotary-wing coaxial helicopter toy that is remotely controlled and safe to fly in doors and out doors, while performing exciting maneuvers even by untrained kids

A dual, coaxial rotor helicopter is provided that is relatively easy to fly. Thrust is provided by two ducted fans that are mounted at the rear of the aircraft and spaced apart laterally. Differential thrust generated by the fans provides yaw control for the aircraft, and forward thrust is provided by the fans working in combination. The coaxial rotors are preferably utilized primarily for lift, and not for forward thrust, which simplifies the control requirements. The coaxial rotor with ducted fan configuration also results in lower vibratory loads being imposed on the helicopter, thereby increasing its speed capability. The fan ducts serve to protect the fans, augment the fan thrust at low airspeeds, increase the efficiency of the fans at cruise speeds, and provide horizontal and vertical stabilizing surfaces to ensure aircraft flight stability.

A system for aerial neutralization of a detected target aerial vehicle comprises a plurality of counter-attack unmanned aerial vehicles (UAVs), and an aerial vehicle capture countermeasure coupling together the plurality of counter-attack UAVs, to intercept and capture a detected target aerial vehicle in a coordinated manner. The system comprises an aerial vehicle detection system comprising at least one detection sensor operable to detect the target aerial vehicle, and operable to provide command data to at least one counter-attack UAV for tracking and neutralizing the target aerial vehicle. The counter-attack UAVs and a net can be deployed from a movable base station, and the net can be carried in a low-drag configuration until the counter-attack UAVs operate to deploy or open the net. The counter-attack UAVs and systems may be autonomously operated. Associated systems and methods are provided.

The invention discloses a master batch with a light scattering function, and a preparation method and application thereof. The master batch with a light scattering function comprises 20-99.5% of transparent thermoplastic resin, 0.1-40% of small-particle-size light scattering agent, 0.1-10% of large-particle-size light scattering agent, 0.01-10% of antioxidant and 0.01-20% of light stabilizer. By compounding the light scattering agents with two particle sizes, the optical properties of the light scattering material can be obviously enhanced. Under the condition of the same content of light scattering agent, since the light scattering agents with two particle sizes are compounded, the light scattering material not only can achieve the same light scattering effect, but also has better light transmittance. The light scattering agents, antioxidant, light stabilizer and other functional assistants are mixed with the matrix resin to prepare the functional master batch, so that the concentration of the assistants in the master batch is increased; and the functional master batch is blended with the matrix resin to prepare the light scattering material. The invention has the advantages of low consumption of light scattering agents, uniform distribution, excellent optical properties, fewer surface defects, lower cost and the like. The master batch with a light scattering function is suitable for producing high-quality optical components, lamp shells, diffuser plates in backlight modules, advertisement signboards, display windows and the like.

The invention discloses an unmanned aerial vehicle three-dimensional air route generation method based on hydrodynamics, and belongs to the air route programming field; according to the invention, a spherical obstacle flow steamline located at an original point along an X-axis incoming flow direction is firstly calculated; with a rotary translation matrix, a spherical obstacle flow steamline at any obstacle position in any incoming flow direction in a plane can be obtained; all the steamlines are merged into one steamline in two modes in accordance with whether a partial superposition condition is met; then the three-dimensional steamline is treated according to unmanned aerial vehicle restraint so as to obtain the unmanned aerial vehicle three-dimensional air route. The invention uses the phenomenon that running water can avoid rocks in the nature for reference, combines fluid calculation with air route programming, also considers the unmanned aerial vehicle restraint, and realizes the programming of a three-dimensional flying obstacle-avoided air route which is smooth and easy to fly. The invention is simple in landform modeling, few in calculation amount, can meet the unmanned aerial vehicle restraint, and is convenient for realization.

The invention discloses an airborne visual detecting and multi-target positioning system of an unmanned gyroplane, and belongs to the technical field of positioning navigation and control. The system comprises an airborne subsystem and a ground monitoring subsystem; the airborne subsystem comprises a video collecting unit, an image processing unit and an image transmission transmitting terminal, and an image collected by the video collecting unit is processed by the image processing unit and then transmitted to the ground monitoring subsystem through the image transmission transmitting terminal; the ground monitoring subsystem comprises a ground station and an image transmission receiving terminal connected with the ground station, and the image transmission receiving terminal is communicated with the image transmission transmitting terminal. The system is compact in structure and achieves perfect integration with the unmanned gyroplane, flight and control of the unmanned gyroplane are convenient, therefore, the precision of target positioning is effectively guaranteed, and multi-target positioning is achieved. The invention further discloses an implementation method of the airborne visual detecting and multi-target positioning system of the unmanned gyroplane.

The invention relates to an airship balloon, the capability of the airship balloon is variable, and consists of a balloon (1), an inflation mouth (2) and a balloon telescopic device which can be used for stretching the balloon in axial direction. the balloon telescopic device is arranged in the balloon (1); the air outlet of the inflation mouth (2) is communicated with the inner cavity of the balloon (1); the invention has the advantages that due to the balloon telescopic device which can be used for stretching the balloon in axial direction, when the airship climbs up to high, and when the relative pressure in the balloon is increasing, the balloon telescopic device can shorten the balloon in axial direction, and the capacity in the balloon is enlarged accordingly to reduce the stress of the balloon wall, thereby achieving the purpose of preventing the balloon wall from being damaged; at the same time, the aerodynamic appearance of the balloon which is in proper stiffness, and can be kept to help fly.

A multirotor aircraft with at least two thrust producing units, the multirotor aircraft being adapted for transportation of passengers and comprising an aircraft operating structure that is adapted for operation of the multirotor aircraft in failure-free operating mode, and a redundant security architecture that is at least adapted for operation of the multirotor aircraft in case of a failure of the aircraft operating structure in operation, the redundant security architecture being provided to comply with applicable authority regulations and certification requirements regarding passenger transportation.

The invention discloses an unmanned aerial vehicle three-dimensional air route generation method based on fluid mechanics, and belongs to the field of air route planning. The method comprises the steps of firstly calculating a ball obstacle flow-around flow line on an original point along an x-axis incoming flow direction, obtaining a flow-around flow line of any incoming flow direction and any obstacle position in a plane by utilizing a rotary translation matrix, merging all flow lines into one flow line by adopting two ways according to the situation that whether the flow lines are partially overlapped or not, and finally processing the three-dimensional flow line according to the constraint of the unmanned aerial vehicle to obtain an unmanned aerial vehicle three-dimensional air route. By referring to the phenomenon that running water in the nature can avoid rocks, the fluid calculation is combined with the air route planning; meanwhile, considering the flight constraint of the unmanned aerial vehicle, when the terrain is relatively complicated, the three-dimensional flight obstacle avoiding air route which is smooth and easy for the unmanned aerial vehicle to fly can be planned. According to the method, simplicity in terrain modeling can be realized, the calculation workload is small, the constraint of the unmanned aerial vehicle can be satisfied, and convenience in realization is achieved.

The invention discloses a flight verification system. The flight calibration system includes a UAV, UAV on-board device and UAV ground control device. The UAV ground control device is connected with the UAV and controls the flight of the UAV through the UAV ground control device. The UAV on-board device is arrange on the UAV, The UAV on-board device receives the air traffic control station signalof AN airport, processes and analyzes the signals, obtains the real-time calibration data, sends the real-time calibration data to the UAV ground control device, evaluates the real-time calibration data through the UAV ground control device, and determines the signal quality. The flight verification system reduces the input cost of the aircraft, consumes short time to refit, has low complexity, utilizes the unmanned aerial vehicle to carry out the flight verification, reduces the workload of the verifier, simplifies the flight operation of the unmanned aerial vehicle, not only reduces the costof the flight verification, but also improves the efficiency of the flight verification.

The invention provides a seaplane provided with a variable sweep aerofoil. The seaplane comprises two air bags, two undercarriages, two engine compartment doors, two turbofan engines, a fuselage and four rocket engines, wherein the fuselage is a cylindrical carbon fiber fuselage; a cockpit is arranged in the front of the fuselage; a wing mounting rack is arranged at the upper part of the fuselage; two first pin columns are symmetrically installed at the front end of the wing mounting rack, and two second pin columns are symmetrically installed at the rear end of the wing mounting rack. By adopting the retractable engine compartment doors, the seaplane avoids the danger that the turbofan engines are scrapped since the plane absorbs seawater when taking off and landing.

The invention relates to an aircraft and provides an unmanned aerial vehicle based on coaxial multi-rotor-wing posture adjustment so as to solve the problems that an existing single-propeller aircraft is poor in reliability and large in power loss, a multi-axis aircraft is large in weight and poor in carrying capacity, and a coaxial double-rotor-wing aircraft is large in weight and poor in maneuvering performance. The unmanned aerial vehicle based on coaxial multi-rotor-wing posture adjustment comprises a vehicle core, an aircraft frame and a deflection adjusting mechanism; the vehicle core comprises a double-output driving mechanism, a frame and a coaxial multi-rotor-wing mechanism; and the double-output driving mechanism is mounted on the frame, the coaxial multi-rotor-wing mechanism is connected to the two output ends of the double-output driving mechanism, counter rotating propellers are arranged on the coaxial multi-rotor-wing mechanism, a deflection manipulating rod is connected to the bottom of the frame, and the deflection adjusting mechanism is mounted on the aircraft frame and can control the deflection manipulating rod to swing. The unmanned aerial vehicle based on coaxial multi-rotor-wing posture adjustment can be used for aerial photography, agricultural spraying and unmanned probe.

The invention relates to a foldable multi-rotor plant protection unmanned aerial vehicle, which comprises a machine body, a plurality of machine arms and rotors arranged on the machine arms, wherein the machine arms comprise a first machine arm and a second machine arm located on the same straight line; the first end of the first machine arm is connected with the machine body; the second end of the first machine arm is rotatably connected with one end of the second machine arm. The second machine arm and the first machine arm can be placed foldably, so that the space occupied by the unmanned aerial vehicle is reduced, and the convenience in transportation, conveyance and maintenance are realized.

The invention provides a tail-sitter vertical take-off and landing unmanned aerial vehicle. The unmanned aerial vehicle comprises a fuselage (1), wings (2), tail wings (3), motors (4) and propellers (5), wherein the wings (2) and the tail wings (3) are disposed on the outer surface of the fuselage (1); the wings (2) are disposed in a lower dihedral manner, and the tail wings (3) are disposed in anupper dihedral manner; flight modes of the unmanned aerial vehicle comprise a vertical flight mode, a vertical-to-level transition mode, a level flight mode and a level-to-vertical transition mode, and the unmanned aerial vehicle combines both flight characteristics of a rotary-wing unmanned aerial vehicle and a fixed-wing unmanned aerial vehicle, so that an area for takeoff and landing is reduced. The speed in the level flight mode is high. The unmanned aerial vehicle has the characteristics of vertical take-off and landing, can be deployed in various restricted environments such as mountainous and hilly lands and narrow urban streets, and has a horizontal high-speed cruising function, so that the hang time is increased and the navigation is expanded. The invention also provides a control system and a control method of the tail-sitter vertical take-off and landing unmanned aerial vehicle.

A multirotor aircraft with an airframe and a thrust producing units arrangement, wherein the thrust producing units arrangement comprises a predetermined number of thrust producing units for producing thrust in a predetermined direction, and wherein a flexible suspension unit is rigidly mounted to the airframe, wherein the flexible suspension unit comprises at least one bearing that mechanically couples the thrust producing units arrangement to the airframe such that the thrust producing units of the predetermined number of thrust producing units are inclinable in relation to the airframe.

The invention relates to a general airplane landing radial line navigation method. The general airplane landing radial line navigation method comprises the following steps of 1, building a landing radial line by airborne navigation equipment according to airplane real-time position information provided by an airplane instrument, navigation information provided by a ground navigation station, and a received landing radial line building instruction, carrying out calculation, and displaying the landing radial line and a reverse-direction extending line of the landing radial line by cockpit display equipment, and 2, carrying out landing according to the landing radial line and the navigation information provided by the ground navigation station, guiding an airplane to the reverse-direction extending line of the landing radial line, and adjusting the airplane to make it fly or land along a direction of the landing radial line. The general airplane landing radial line navigation method solves the problem that the existing landing navigation method has a large potential safety hazard in a zone without ground navigation facilities. The general airplane landing radial line navigation method is a real-time, visual, convenient and reliable airplane navigation calculation method, improves an implementation method of real-time flight guidance of a general airplane and pilot autonomous operation display, and provides a visual and accurate landing navigation method.

The present disclosure relates a flight control method and a device for unmanned planes. The method comprises the steps of acquiring the current geographical position information of an unmanned plane; matching the current geographic position information of the unmanned plane with the collected flight airline parameter information; when the current geographic position information of the unmanned plane is matched with the collected flight airline parameter information, loading the matched flight airline parameter information to the unmanned plane; according to the flight airline parameter information, determining a target airline, and controlling the flight of the unmanned plane according to the target airline. Therefore, the complicated manipulation of users is avoided. Especially for unmanned plane users who are not familiar with terrains and environments, the flight is safer and more convenient through directly adopting the collected flight airline parameter information.

A toy airplane assembly (31) is provided that is easy to fly, inexpensive, and durable. The toy plane assembly includes a plane having a radio receiver (73) and a microprocessor (71). Batteries (19) housed in the fuselage (12) power the printed circuit board (14) to which the microprocessor (71) and radio receiver (73) are attached. The radio receiver (73) receives signals from a hand-held remote control radio transmitter (51) and are transmitted to the microprocessor (71). The microprocessor (71) decodes the signals and, in response thereto, distributes power to the motors (8,8A) for driving the propellers (2,2A). All movement of the plane is controlled by the microprocessor (71), thereby providing microprocessor assisted flight. The plane fuselage (12) is a one-piece molded part, made of a foam material to provide a durable plane.

An embodiment of the invention discloses a placement angle error calibration method and relates to the calibration technology. The method can improve precision of an airborne laser radar system. The method comprises the following steps: setting a placement angle error calibration field, wherein the placement angle error calibration field has flat terrain, has a lot of tall V-shaped factories and flat and straight roads and facilitates flying; setting a placement angle error calibration field air route meeting preset calibration conditions; in the placement angle error calibration field, according to the placement angle error calibration field air route, carrying out roll placement angle calibration first, and carrying out point cloud recalculation; then, carrying out pitch placement anglecalibration after point cloud recalculation; carrying out point cloud recalculation again after pitch placement angle calibration; finally, carrying out heading placement angle calibration after pointcloud recalculation; and applying placement angle error calibration parameters obtained through the final heading placement angle calibration to a preset correction program to realize correction of the point cloud. The method is suitable for placement angle error calibration.

A flying kite designed to be visible when flown in low light conditions. The flying kite includes a body that is generally triangular in shape and configured in a substantially planar manner. The flying kite also comprises a frame that provides structural support for the body. The frame includes three corner frame members and three longitudinal frame members that are interposed the corner frame members. The longitudinal frame members further include two compartments having disposed therein the chemicals necessary to create chemical luminescence subsequent to distressing the frame members. The flying kite further includes two pockets for receiving therein a conventional glowstick.