739results 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 prediction correcting guidance method of a deep space exploration returning process comprises the steps that (1) a heeling angle section used for deep space exploration returning process track prediction is determined; (2) the amplitude value | sigma 0 | of the heeling angle of a current point is computed in an iterative mode; (3) a salutatory reentry flight track of a returning device is divided into an initial reentry stage, a primary reentry descending stage, a primary reentry ascending stage, a Kepler stage and a final reentry stage, a final guidance rule of the returning device is determined, and the final guidance rule is that when the returning device is in the initial reentry stage or the primary reentry descending stage or the primary reentry ascending stage or the final reentry stage, the amplitude value | sigma 0 | determined in the step (2) of the heeling angle sigma 0 of the current point is used for guidance; and when the returning device is in the Kepler stage, | sigma 0 | = 180 degrees is used for guidance, and accordingly prediction correcting guidance of the deep space exploration returning process is completed. The guidance rule is designed at the Kepler stage of the track for achieving overload restrain on the deep space exploration returning process, and safe and accurate landing of the returning device is guaranteed.

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 purpose of the present invention is to provide a kind of variable-pitch three-rotor aircraft. The variable-pitch three-rotor aircraft adopts a three-axis structure. Each axis adopts a rotor with a large diameter and low speed. The speed is set at a constant value. The pitch difference controls the balance of the pitching direction of the aircraft. A guide vane with a variable angle is designed under one of the rotors. Under the action of the down swirl generated by the rotor, by changing the angle between the guide vane and the down swirl, the The force of the downward swirl on the deflector, the moment of the force on the center of gravity cancels the counter moment of the rotor. The invention comprises a variable-pitch rotor, a guide vane, a tail pipe and a fuselage. The aircraft has stable flight and strong anti-interference ability, and is especially suitable as an aerial platform for small unmanned aircraft and aerial photography aircraft.

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 discloses a multi-rotor type unmanned aerial vehicle available for adjusting direction of thrust, which is provided with a battery module, and is used to fly according to commands of a control module used for controlling rotation of a plurality of propellers. The multi-rotor type unmanned aerial vehicle includes: a main body including the battery module and the control module; a plurality of frames connected to a side surface of the main body and extending therefrom; a first motor connected to a distal end of each of the frames; and a drive unit connected to the first motor, wherein the drive unit includes a rotary frame and a stationary frame each having a circular shape and connected to each other in the form of a gyroscope, a second motor supported at the center of the rotatable frame, and a propeller connected to the second motor, and a vector of thrust generated by rotation of the propeller is variable according to rotation of the first and second motors.

Modern farming is currently being done by powerful ground equipment or aircraft that weigh several tons and treat uniformly tens of hectares per hour. Automated farming can use small, agile, lightweight, energy-efficient automated robotic equipment that flies to do the same job, even able to farm on a plant-by-plant basis, allowing for new ways of farming. A hybrid airship-drone has both passive lift provided by a gas balloon and active lift provided by propellers. A hybrid airship-drone may be cheaper, more stable in flight, and require less maintenance than other aerial vehicles such as quadrocopters. However, hybrid airship-drones may also be larger in size and have more inertia that needs to be overcome for starting, stopping and turning.

The invention discloses a portable foldable spherical unmanned aerial vehicle. The scheme of the portable foldable spherical unmanned aerial vehicle is provided in order to solve the problems that a traditional multi-rotor unmanned aerial vehicle cannot be folded and is large in occupied space and the like. The unmanned aerial vehicle has two states which are the folded state and the unfolded state, and the two states can be switched. By the adoption of the technical scheme, compared with the prior art, the portable foldable spherical unmanned aerial vehicle has the following technical beneficial effects that due to the unique foldable spherical design, certain art elements are introduced into the unmanned aerial vehicle, and the unmanned aerial vehicle has certain artistic ornamental value; exquisite self-locking structural design guarantees that the unmanned aerial vehicle is not heavier on the basis that the positions of vehicle arms and a vehicle body are relatively fixed when the unmanned aerial vehicle flies; the unique folding structural design and spherical structural design are adopted, so that the portability of the unmanned aerial vehicle is greatly improved, and the unmanned aerial vehicle can be conveniently carried by a user outside and carried by a solider; and when in the unfolded state, the unmanned aerial vehicle is in a four-rotor mode, flight is stable, and operation is easy.

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 present invention discloses a method for monitoring soil erosion based on unmanned aerial vehicle aerial photography. The method is characterized by: adopting an unmanned low altitude aerial vehicle as a remote sensing platform, and integrating a digital camera, a differential GPS and a gyro platform; adopting a digital photography technology, and adopting a low altitude unmanned aerial vehicle with characteristics of high resolution and large scale to acquire a plurality of long-period observation image data of a research area; adopting a computer digital image processing system to import a processed image into a CAD; carrying out recognition and measurement on quantity and quality of soil erosion investigation factors in the CAD based on culture conformation law and image characteristics in the research area, wherein the factors comprise length, width, depth, volume and other factors of a channel; and calculating values of channel head advancing, channel widening, and channel down-cutting, and then calculating channel erosion and an average erosion modulus in many years so as to monitor soil erosion change in the whole research area, such that a convenient and efficient method is provided for good treatment and monitor of water and soil loss.

The invention discloses a flight control navigation system of a miniature flapping-wing flying vehicle. A signal output by a sensor unit is subjected to AD (analog-to-digital) conversion, and then is sent into a flight control navigation computer by a data communication interface; a GPS (global positioning system) receiver sends the signal into the flight control navigation computer to carry out configuration through the data communication interface; all programs and data of the flight control navigation computer run in an SRAM (static random access memory); and the flight control navigation computer outputs a control instruction to a steering engine and an electronic speed regulator through the data communication interface, is connected with a data link through the data communication interface, and carries out data telemeasuring and remote control command communication. By using the flight control navigation system of the miniature flapping-wing flying vehicle, the autonomous flight of the miniature flapping-wing flying vehicle is achieved, and the strict requirements of the miniature flapping-wing flying vehicle on aspects of space, weight, electromagnetic compatibility and the like are met.

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.

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 an U-shaped pesticide box for an agriculture unmanned helicopter. The U-shaped pesticide box comprises a pesticide box body, wherein a groove is formed in the pesticide box body, the cross section of the pesticide box body is of an U-shaped structure, the U-shaped structure is provided with an U-shaped inside surface for forming the groove and an U-shaped outside surface for coating the U-shaped inside surface, the U-shaped inside surface and the U-shaped outside surface are smoothly connected to form the pesticide box body, the upper end surface of the pesticide box body is provided with pesticide liquid inlets, a steam hole is formed in the part near each pesticide liquid inlet, and the bottom part of the pesticide box body is provided with a pesticide liquid outlet. The U-shaped pesticide box has the advantages that the bottom part is provided with a separating plate, so the left pesticide liquid flowing position and the right pesticide liquid flowing position are reduced, and the left level and the right level of pesticide liquid of the pesticide box are consistent in the flight process; the pesticide box is arranged at the bottom part of the center of a helicopter body, so the carried pesticide liquid is mostly close to the center of gravity, the shaking of the pesticide liquid is reduced in the flight process, and the flight is more stable; meanwhile, the bottom part of the pesticide box body is provided with an impurity guide groove and an impurity storage area, so the blockage of the pesticide liquid outlet by the impurities of the pesticide liquid is avoided, and the discharge of residues is convenient.

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.