737results about How to "Stable flight" patented technology

The invention discloses an onboard device suitable for the sowing job of an unmanned aerial vehicle and a sowing method. The onboard device comprises a scattering device arranged below the unmanned aerial vehicle, wherein the scattering device comprises a material box, a material stirring mechanism, a material discharging adjusting mechanism and a material scattering mechanism; the material stirring mechanism is arranged inside the material box; the material scattering mechanism is arranged below the material box; the material box comprises a box wall and a baseboard; a ventage is formed in the baseboard; the material discharging adjusting mechanism comprises a switch baffle arranged in the ventage and an actuating mechanism used for pushing the switch baffle to move in the ventage and adjusting the size of the leak; the material scattering mechanism comprises a side plate connected to the bottom of the material box, a wheel disc motor and a wheel disc connected with the wheel disc motor; the wheel disc is arranged on the inner side of the side plate; a scattering openings are formed in the side plate. According to the invention, the onboard device has the advantages of being small in size, low in cost, high in flexibility and convenient for controlling.

This invention discloses one forest measurement method without human aviation cameral remote sensor, which adopts aviation device as remote platform without human and integrated digital codes camera, difference GPS and top platform, wherein, it uses digital camera technique to get high earth resolution rate without human remove image with large proportion rules fully in use of high flexible machine without special plane spot and capable of flying under clouds.

The invention relates to an immersive unmanned aerial vehicle (UAV) driving flight system comprising an airborne device and a ground device which are wirelessly connected. The airborne device, which is arranged on a UAV, controls the flight state of the UAV, collects the location information of the UAV and an image of the surrounding environment, sends the image and the location information to the ground device, and receives head angle information and a control instruction of the ground device. The ground device receives and analyzes the location information and the image sent by the airborne device, analog-simulates the surrounding environment information, road information, traffic information, label information and landmark information of the location of the UAV through processing based on the augmented reality technology, superposes the information into a real world image space, and presents the information to a pilot through a virtual reality eyepiece. Through the system, the pilot can receive the flight state information and the surrounding environment of the UAV in real time, and controls the UAV accurately to enable the UAV to fly smoothly and complete the target, reduce error and get an immersive experience.

Disclosed are a three-phase wireless power transfer (WPT) system and three-phase wireless rechargeable unmanned aerial vehicle (UAV) system based on the same. Three power receiving coils, including resonators, are installed at the ends of three landing leg of the UAV. A three-phase power converter installed in the UAV receives the three-phase AC induction current induced in three power receiving coils, including resonators, converting the three-phase AC induction current into a DC current to be charged in a battery. A three-phase power wireless charging apparatus wirelessly transfers three-phase power from three power transmitting coils to the three power receiving coils of the UAV when the three landing legs land on three coil seating units provided on a charging platform. A magnetic flux leakage shielding coil may be provided to prevent magnetic flux leakage from approaching the UAV. The power transfer efficiency is excellent, and electromagnetic interference can be also reduced.

Swept-wing box-type aircraft comprising a fuselage and a lifting system formed by two substantially horizontal wings. One of the wings has a positive sweep angle, while the other has a negative sweep angle, the wings lying in planes spaced apart from one another and joined by two vertical wings extending from their ends. The positively swept wing is the front wing and extends from the bottom of the fuselage, whereas the negatively swept wing is the rear wing and extends generally continuously above the fuselage, the fuselage being provided with a pair of fins at its tail section. The fins are joined at their ends to the rear wing, the fins, the rear wing and the fuselage defining an aerodynamic channel along which the surface of the fuselage is substantially flat.

A golf club head consists of a shell part, and a face part; the shell part has a front opening, a holding hollowness behind the front opening, several strengthening pieces in the holding hollowness, and a slot on an upper side, which communicates with the holding hollowness; the slot of the shell part has several connecting blocks therein, which are each connected to two lateral sides of the slot, for increasing capability of the shell part to bear force; the face part is closely fitted in the front opening of the shell part, and propped by means of the strengthening pieces in the holding hollowness; and, a kind of elastic shock absorbing material is injected in the holding hollowness of the shell part to prop the face part.

A less lethal projectile to be fired from a launcher comprising a body having a concentric cavity to hold a fluid payload, a nose cap attached to the body, said nose cap having a plurality of slits therein, which will spread open upon impact, allowing the fluid to escape.

The invention relates to a multi-rotor aircraft composed of a fuel engine and a motor. The aircraft comprises an electronic speed regulator, a flight control system, the fuel engine, the motor, a battery pack, a fuselage composed of multiple crankshafts, and multiple propellers, which can be divided into first propellers driven by the fuel engine and second propellers driven by the motor. The multiple first propellers provide the main lifting force of the whole aircraft, while the multiple second propellers are responsible for the balance, direction and a small part of the lifting force of the whole aircraft. Thus, most of the lifting force of the invention is provided by the fuel engine, and a small part of the lifting force, balance control, directional control, and height control are provided by the motor. Perfectly realizing fuel-electric hybrid, the aircraft of the invention is endowed with the maneuverability and flexibility of pure electric aircrafts as well as the large load capacity of fuel engines.

The invention relates to a retractable folding quad rotor which comprises a central supporting mechanism and four sets of propeller mechanisms. The improvement of the retractable folding quad rotor is as follows: the four sets of propeller mechanisms are four sets of retractable propeller mechanisms with identical structures; each set of retractable propeller mechanism comprises a bevel pinion, a telescopic rod, a propeller, a motor and a lifting arm mechanism, and also comprises a large conical gear and a servo motor; the servo motor, the large conical gear and the four bevel pinions form driving mechanisms of telescopic rods of the four sets of propeller mechanisms; and under the drive of the servo motor, the four bevel pinions respectively and simultaneously drive the four telescopic rods to realize outward retraction or inward retraction by virtue of screw drive of the screw rods. According to the improvement, four sets of folding mechanisms are arranged, wherein each set of folding mechanism drives each set of telescopic propeller mechanism to fold or unfold. According to the quad rotor, the telescopic mechanisms and the folding mechanisms are additionally arranged, so that the four-rotor body is greatly retracted; and compared with the conventional product, the retractable folding quad rotor disclosed by the invention has the advantages that the size of the quad rotor is effectively reduced, and the quad rotor is convenient to carry.

The invention discloses a rotor wing flight mechanical arm system and algorithm based on dynamic gravity center compensation. The system comprises a rotor wing flight platform, an image sensor, a connecting frame, a mechanical arm system, a system controller and a ground station control device. The rotor wing flight platform comprises a rotor wing aircraft and a flight controller. The image sensoris installed below the front part of the rotor wing flight platform. The connecting frame is a mechanical plate which is used for fixedly connecting the rotor wing flight platform, the image sensor and the mechanical arm system. The mechanical arm system is installed just below the rotor wing flight platform. The system controller is installed right above the rotor wing flight platform. The ground station control device is communicated with the system controller in a wireless mode. The system is rational in structural design, high in safety, and strong in stability. The algorithm is capable of improving the accuracy rate of capturing, and improving the time efficiency of capturing.

The invention relates to a rotary wing type unmanned aerial vehicle for spraying pesticides. The rotary wing type unmanned aerial vehicle comprises a vehicle body with a rotary wing component, wherein a plurality of pesticide boxes and a pesticide spraying device connected with the pesticide boxes are further mounted on the vehicle body; all the pesticide boxes are flatly arranged and the whole horizontal gravity center coincides with the horizontal gravity center of the vehicle body. According to the rotary wing type unmanned aerial vehicle for spraying pesticides disclosed by the invention, a large pesticide box is divided into a plurality of small pesticide boxes with the same size, so that the inertia of pesticide liquid inside a single pesticide box can be reduced, the horizontal center-of-gravity shift generated by the liquid inside each pesticide box is relatively small under the condition that the aerial vehicle suddenly stops, the overall horizontal center-of-gravity shift is greatly smaller than that under the condition that the single pesticide box is filled with the pesticide liquid, and thus the problem that flight control cannot correct out-of-control falling caused by too large horizontal center-of-gravity shift and too large dip angle of the vehicle body is avoided.

The invention discloses a method for aerially photographing a crop canopy picture for crop nitrogen analysis and soil fertilization guidance by using an unmanned aerial vehicle. The crop canopy picture is aerially photographed through the unmanned aerial vehicle, meanwhile, aerial latitude and longitude corresponding to the crop canopy picture are obtained, and crop nitrogen analysis and soil fertilization guidance are carried out by combining picture information and latitude and longitude information. According to the obtained method, large-area farmland information can be quickly obtained, influence and limitation of crop growth and farmland environments are avoided, a crop nitrogen state is diagnosed by using color parameters of the picture and the nitrogen fertilizer topdressing index is recommended, the method is accurate and reliable, accurate management of a nitrogen fertilizer is facilitated and better economical and ecological benefits are achieved. The method is fast and simple in operation, stable and reliable in structure, low in operation cost and beneficial to farmland application and popularization; and fine farming of the farmland can be significantly promoted. The aerial photograph equipment of the unmanned aerial vehicle is simple in structure and beneficial to efficient and stable aerial photographing of the crop canopy picture.

There is provided an information recording medium and a method of manufacturing a glass substrate for information recording media as well as a glass substrate manufactured using the method, according to which the take-off height (TOH) of a HDD for example can be made low. The surface shape in a predetermined region of an information recording medium is measured using an optical interferometer or an atomic force microscope. The measured surface shaped is subjected to line analysis along the circumferential direction of the information recording medium. A calculation is made of the product PSD×f of PSD corresponding to a predetermined wavelength ν and the reciprocal of the predetermined wavelength ν. The maximum value of the calculated PSD is controlled to not more than a predetermined value. As a result, the TOH can be made low by reducing waviness which hinders the magnetic head of a HDD or the like from stably flying.

The invention discloses a height control method and a height control system for an aerial vehicle. The height control method comprises the steps of 1), arranging a radar, an accelerometer, a barometer and a GPS module in the aerial vehicle; 2), in the flight process of the aerial vehicle, if the aerial vehicle is in an effective detecting range of the radar, the accelerometer, the barometer and the GPS module and performing fusion, performing fusion on the fused result and information detected by the radar; otherwise, performing data fusion processing based on the accelerometer, the barometer and the GPS module; and obtaining a current height, a current vertical speed and a current vertical acceleration; and 3), performing height control on the aerial vehicle according to the obtained current height, the current vertical speed and the current vertical acceleration. The height control system comprises a detecting module, an information fusion module and a height control module. The height control method and the height control system have advantages of simple control realization, high control precision, high stability, high adaptability, etc.

The invention relates to an airfoil flow control device. The airfoil flow control device is arranged on the upper surface of the main airfoil of an airplane near the front edge of the airfoil. The device consists of a fundamental frequency Gershgorim band and a subharmonic frequency Gershgorim band which are arranged in parallel; both the fundamental frequency Gershgorim band and the subharmonic frequency Gershgorim band are in a sawtooth shape; during the taking off stage, a front flap extends the airfoil flow control device, thereby controlling the boundary layer of the airfoil to fast transit and form an onflow boundary layer used for restraining or eliminating the separation of the boundary layers, thereby effectively improving the life force of the airfoil; during cruising flying, the front flap of the airfoil resets to cover the device, thus leading the device to be out of use and leading the boundary layer of the airfoil to maintain a layer flow during the cruising stage, so as to reduce the friction resistance at the airfoil surface and improve the lift-drag ratio. The airfoil flow control device has the advantages of simple structure, light weight and convenient for being maintained, can solve the separation problem of the boundary layers of the airfoil surfaces during the taking off state of the airplane under the situations of not increasing the weight of the airplane and the power; besides, the airfoil flow control device also avoids the increasing problem of the friction resistance brought by the transition of the boundary layers of the airfoil surfaces during the cruising flying stage.

The invention provides a target assignment method used in cooperative search of multi-unmanned aerial vehicles with communication restriction. The method is used for controlling the multi-unmanned aerial vehicles to search targets of an unknown region, under the circumstance of considering influences from communication restraint condition, target assignment is performed on searched targets, the multi-unmanned aerial vehicles for target assignment fly to targets for target confirmation, and the multi-unmanned aerial vehicles are enabled to accomplish searching and confirming tasks to a plurality of targets in a collaborative manner.

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 relates to an unmanned patrol aircraft for power transmission lines. The unmanned patrol aircraft comprises an aircraft body, a camera system, a cloud deck, a nanometer battery, an aircraft control system, a wireless transmission system, a GPS positioning system and a ground receiving, controlling and managing system. The unmanned patrol aircraft has four ailerons which are symmetrically installed at two sides of a main beam; the unmanned patrol aircraft has the advantages of stable flight, a fast flight speed, high flexibility and great loading capacity; front and rear beams are of segmented design, which facilitates adjustment and wiring. The aileron horns of the ailerons are movably connected with an aileron fixing frame through bolts; the aileron fixing frame is equipped with folding positioning seats; the aileron horns rotate with the bolts as centers and are limited through the folding positioning seats; such a structure enables the aileron horns to be parallely drawn close onto the main beam after folding, so the unmanned patrol aircraft has a small size and is easy to carry. After the front and rear aileron horns are open, lines among center points of four motors on the front and rear aileron horns form a square, and such a structure enables the aircraft to maintain balanced flight and to have reduced current loss and long flying time.

A producing method of a shuttlecock includes the following steps: step a, molding a flocking frame provided with a group of flocking bars and a group of flocking tubes integrated with the flocking bars; step b, arranging the flocking frame at a fixed ball head; and step c, flocking flocked ends of a group of feathers into corresponding flocking tubes to produce the shuttlecock. According to the producing method, machines are used for operation, therefore the producing efficiency of the shuttlecocks is improved; and the produced shuttlecock is provided with molded flocking frames, therefore the shuttlecock has good uniformity, and the quality of the shuttlecock is guaranteed.

The invention provides an unmanned aerial vehicle navigation decoy device and method based on flight destination prediction. The system comprises a main control device, a navigation decoy signal generating and transmitting device, a position measuring device and a remote control signal interference device, the unmanned aerial vehicle is forced to be in an autonomous flight state; a fixed-point navigation deception jamming signal is generated and transmitted to the unmanned aerial vehicle; the unmanned aerial vehicle is forced to change the flight angle after being cheated; calculating destination coordinates of autonomous flight of the unmanned aerial vehicle, and judging whether the unmanned aerial vehicle continuously flies according to the current trajectory according to the deviation between the current actual flight trajectory yaw angle and the expected flight trajectory yaw angle of the unmanned aerial vehicle; and if not, planning a false flight path for trapping the unmanned aerial vehicle, so that the unmanned aerial vehicle flies along the expected flight path as much as possible after being trapped until the unmanned aerial vehicle is forced to land. The problem that theunmanned aerial vehicle is out of control due to the fact that decoy signal parameters cannot be dynamically adjusted according to the flight path of the unmanned aerial vehicle in the prior art canbe solved.

The invention discloses a four-rotor aircraft flight control method based on a backstepping method. The four-rotor aircraft flight control method based on a backstepping method includes the steps: according to the principle of flight mechanics and aerodynamics, establishing a kinetic model of a four-rotor aircraft and simplifying the model: setting the aircraft as a rigid body, setting the structure of the aircraft to be completely symmetrical, setting the center of gravity of the aircraft to coincide with the center of the aircraft, taking the ground coordinate system as the inertia coordinate system, and ignoring changes in the curvature of the Earth and the acceleration of gravity; according to the kinetic model of the four-rotor aircraft, analyzing the coupling relation of the flight control system, and constructing a system control structure graph; and finally according to the kinetic model of the four-rotor aircraft and the system control structure graph, using the backstepping method, combining with the Lyapunov stability principle, and determining the feedback compensation control quantity of the system. The four-rotor aircraft flight control method based on a backsteppingmethod can stably control the position and the attitude of the four-rotor aircraft, and has the advantages of high trajectory tracking accuracy, high response speed, and high anti-interference capability.