1089 results about "Low altitude" patented technology

The present invention provides a traffic management system for managing unmanned aerial systems (UASs) operating at low-altitude. The system includes surveillance for locating and tracking UASs in uncontrolled airspace, for example, in airspace below 10,000 feet MSL. The system also includes flight rules for safe operation of UASs in uncontrolled airspace. The system further includes computers for processing said surveillance and for applying the flight rules to UASs. The traffic management system may be portable, persistent, or a hybrid thereof.

The present invention relates to a reduced scale industrial helicopter, with an integrated automatic flight control system, that includes core autopilot functions, GPS management, and full-function navigation systems. The autopilot technology includes rapid launch capability, real-time in-flight switching between one or more of a) remote control, b) autopilot-directed, c) ground station controlled, and d) home modes, and is upgradeable. The helicopter is used for high or low altitude surveillance, and can handle various payloads, including photographic missions. The helicopter may include onboard batteries and/or a unique battery unit disposed beneath the helicopter, and includes autonomous features such as automatic takeoff, automatic landing, safety return to home base, and predetermined mission plans.

The present invention is directed to a radio-acoustic sounding system for providing wind measurements at altitudes of 100 meters or less. Wind measurements are obtained by transmitting a pulse of audio frequency energy through one or more volumes corresponding to the coverage area of one or more radio frequency transceivers. The frequency of the audio pulse is selected to have a wavelength that is one-half the wavelength of the electromagnetic energy transmitted by the antenna or antennas. By monitoring a return radio frequency signal at selected times following the transmission of the audio pulse, wind data is obtained at selected altitudes. Wind speed and direction can be obtained by observing the Doppler frequency shift of return radio frequency signals, or by observing the amplitude of the return radio frequency signals. In accordance with an embodiment of the present invention, precipitation measurements may be made by transmitting a radio frequency signal at the same radio frequency as is used in connection with wind measurements, and observing return radio frequency signals.

Systems and methods for providing one-way rides by autonomous vehicles are disclosed. An exemplary embodiment of the invention operates as a personal ski lift that includes an autonomous snowmobile or all terrain vehicle for providing a low-cost and flexible means to ascend ski-able terrain to bring a skier to a high-altitude skiing destination, so that the skier may depart the vehicle and ski down the terrain independent from the vehicle. The vehicle of the exemplary embodiment may meanwhile travel autonomously to a lower-altitude rendezvous point to meet the skier upon completion of his skiing. Other embodiments within the invention for providing one-way rides by various types of vehicles for various purposes are disclosed.

An un-manned airborne vehicle (UAV), for acquiring aeromagnetic data for geophysical surveying at low altitude on land or over water, comprising an extended fuselage that is adapted to hold and maintain magnetometer and a magnetic compensation magnetometer at a minimum distance from the avionics and propulsion systems of the UAV. The magnetometer measures magnetic anomalies and the magnetic compensation magnetometer measures magnetic responses corresponding to the pitch, yaw and roll of the UAV. A data acquisition system stores and removes the magnetic response measurements from the magnetic anomaly measurements. The data acquisition system also stores a survey flight plan and transmits the same to the avionics system. The generator of the UAV is shielded and the propulsion system is stabilized to reduce magnetic and vibrational noises that can interfere with the operation of the magnetometer.

The invention relates to the field of unmanned aerial vehicles, in particular to a full-automatic unmanned aerial vehicle control system. The system, which is characterized in that: a ground control system comprises a main control system mainly comprising a central controller, a main control computer, the internet network and a central antenna, a user computer as a human-computer interactive interface, and a GPS navigation system; a vehicle-mounted flight control system of the unmanned aerial vehicle is provided with an aerial vehicle controller, a networking antenna, a GPS antenna, a DSP, a navigation camera, and a sensor; and the main control system of the ground control system gets the remote internet control authority, the main control computer inputs a signal to the central controller, the signal is processed by the central controller, and then the remote wireless communication and control of the vehicle-mounted flight control system are achieved through the antennas. Compared with the prior art, the system has the advantages of having high automation degree, realizing various flight missions of the unmanned aerial vehicle, and being applied to low altitude remote sensing, aerial photography, monitoring, photography measurement, videography, communication data retransmission and the like.

The invention relates to an unmanned aerial vehicle aerial photography sequence image-based slope three-dimension reconstruction method. The method includes the following steps that: feature region matching and feature point pair extraction are performed on un-calibrated unmanned aerial vehicle multi-view aerial photography sequence images through adopting a feature matching-based algorithm; the geometric structure of a slope and the motion parameters of a camera are calculated through adopting bundle adjustment structure from motion and based on disorder matching feature points, and therefore, a sparse slope three-dimensional point cloud model can be obtained; the sparse slope three-dimensional point cloud model is processed through adopting a patch-based multi-view stereo vision algorithm, so that the sparse slope three-dimensional point cloud model can be diffused to a dense slope three-dimensional point cloud model; and the surface mesh of the slope is reconstructed through adopting Poisson reconstruction algorithm, and the texture information of the surface of the slop is mapped onto a mesh model, and therefore, a vivid three-dimensional slope model with high resolution can be constructed. The unmanned aerial vehicle aerial photography sequence image-based slope three-dimension reconstruction method of the invention has the advantages of low cost, flexibility, portability, high imaging resolution, short operating period, suitability for survey of high-risk areas and the like. With the method adopted, the application of low-altitude photogrammetry and computer vision technology to the geological engineering disaster prevention and reduction field can be greatly prompted.

The invention relates to an airline routing algorithm of an unmanned plane in a large-range complicated three-dimensional space. The algorithm comprises the following steps: first dividing a three-dimensional space on the basis of a 2.5-dimensional grid (each grid point includes longitude, altitude and elevation information); improving the A* cost function by comprehensively considering the influence factors such as airline height, detected probability, airline distance under the constraint conditions of radar, disaster weather and forbidden areas, and determining an initial airline on the basis of an algorithm search flow; serially processing the initial airline to obtain a final flying airline for meeting the performance constraint of the unmanned plane (such as minimal step length, turning radius, climbing rate, safety height). The algorithm is good in stability and astringency, high in efficiency, capable of meeting the wide-range low-altitude airline routing requirement and applicable to relevant fields such as military, national defense, emergency relief.

The utility model relates to a method of rapid automatic matching for the low altitude remote sensing image and the aerial triangulation, which is characterized in that: capture serial images with the low altitude remote platform; extract the characteristic point from the image with the feature extraction technology; save automatically all extracted characteristic points of the images; match automatically characteristic points with same name of the adjacent images and transmit automatically the matched characteristic points with same names to all superimposed image to obtain a large quantity of characteristic points with three degree or more and same names; the semi-automatic measurement control point and the checkpoint of the image coordinate can combine with other observation values of non-photogrammetry to carry out the high precision aerial triangulation and the precision evaluation of the balancing results. The utility model has the advantages that the stable and reliable matching results and higher precision of the aerial triangulation can be obtained even the low altitude remote sensing images have large rotation deviation angle and the applicative demand of the large scale survey and the high precision three-dimensional reconstruction can be met.

Apparatus and a method utilizing correlation interferometer direction finding for determining the azimuth and elevation to an aircraft at long range and flying at low altitudes above water with a transmitting radar while resolving multipath signals. The signals from the radar are received both directly and reflected from the surface of the water using horizontally polarized and vertically polarized antenna arrays, are digitized and are stored in separate covariant matrices. Eigenvalues for the eigenvectors of the matrices processed on signal samples recorded on horizontally polarized X arrays are compared to the eigenvalues for the eigenvectors of the covariance matrices processed on signal samples recorded on vertically polarized X arrays. Incident field polarization is associated with the antenna array measurements that yield the strongest eigenvalue. The eigenvector and eigenvalues for the strongest signal are selected and used for subsequent signal processing. An initial global search assuming mirror sea-state reflection conditions using the signal eigenvector having the strongest eigenvalue is performed to yield an approximate elevation α and azimuth β to the aircraft. The approximate values are then used as the starting point for a subsequent conjugate gradient search to determine accurate elevation α and azimuth β to the aircraft.

The invention discloses a small low-altitude light area array laser radar measuring system. The master control sub-system of the measuring system triggers a pulse laser emitting module to emit lasers, the lasers are collimated and generate two paths of laser signals through a beam splitting sheet, one path is used for determining the time of emitting the lasers and generating timing starting signals, the other path irradiates an object through beam expansion, echo signals are received by an APD array detection module and generate N2 paths of stopping pulses, and a multi-channel high-precision time interval measuring module is combined with starting signals to measure the round-trip flight time difference of N2 paths of lasers of a rectangular detection area. The location attitude measuring sub-system, the master control sub-system and the area array laser radar distance-measuring sub-system of the measuring system are integrated, original three-dimensional information can be obtained in real time, and assembling and verification are eliminated. The laser radar measuring system does not need scanning, three-dimensional imaging can be achieved through a single pulse, the imaging speed is high, measuring precision and working efficiency are high, the size is small, the weight is small, and the small low-altitude light area array laser radar measuring system is suitable for being carried small low-altitude light remote sensing platforms.

The invention belongs to the technical field of path or flight path planning of robots as well as low-altitude flight aircrafts, specifically relates to a path planning method of a passable area divided at unequal distance, and is used for solving the problem that existing planning algorithm has large time complexity in time and space complexity. The path planning method comprises the following steps of: calculating convex extreme points of each barrier curve; dividing the passable area by using each convex extreme point as a horizontal line; abstracting each small area obtained by dividing into a peak of a graph; forming an undirected graph by all peaks; finding out a peak serial number corresponding to the small area at which a starting point and a final point are located; finding out all paths for the undirected graph by breadth-first or depth-first scanning; finding out an actual to-be-travelled path of a moving object according to the situation on an actual map. The path planning method disclosed by the invention has the beneficial effect of overcoming the problems of algorithms of A* and the like on memory space and operation time, and overcoming a convergence problem of an ant colony algorithm at the same time. Besides, time complexity and space complexity are improved greatly in comparison with other algorithms.

The invention discloses a low-altitude airship flight control system and a flight control method thereof, belonging to the technical field of aircraft control. The system comprises a front-end data acquisition and processing subsystem, a navigation and flight control and state monitoring subsystem, a rear-end driving execution module subsystem and a flight application subsystem, wherein the front-end data acquisition and processing subsystem is connected with sensing equipment and used for transmitting acquired flight environment and airship state information, the navigation and flight control and state monitoring subsystem is connected with an airship navigation sensor and the rear-end driving execution module subsystem and used for transmitting navigation and flight control information,the rear-end driving execution module subsystem is connected with an airship execution controller and used for transmitting empennage steering engine pulse width modulation signals, propelling rotating speed control voltages and valve blower switch information, and the flight application subsystem is connected with a ground station and used for transmitting flight control instructions and telemetry parameter information through a data radio. The low-altitude airship flight control system disclosed in the invention is suitable for various civil and military systems.

The invention discloses a low-altitude autonomous navigation system for a rotary-wing unmanned plane. The low-altitude autonomous navigation system is composed of a data acquisition device, a data preprocessing module, a data fusion module, a guidance control loop module and an attitude control loop module. The data preprocessing module is used for carrying out sampling filtering and error compensation on current location data information collected by the data acquisition device; the data fusion module is used for carrying out fusion and updating and obtaining a current position and speed of the rotary-wing unmanned plane; the guidance control loop module is used for calculating an expected attitude angle and an expected height value; and the attitude control loop module is used for generating a controlled quantity. According to the technical scheme, a problem of poor attitude estimation precision of the conventional navigation system can be solved; and requirements of high-precision heading attitude calculation and position and speed fusion of the rotary-wing unmanned plane can be met. High-precision filtering of the system is realized. On the basis of the analysis and calculation of the autonomous navigation system, the flight route and height can be corrected and the flight attitude can be adjusted autonomously; and the autonomous flight of the unmanned plane can be realized.

The invention provides an automatic lane line identification method based on low-altitude aerial images. The automatic lane line identification method based on the low-altitude aerial images is applied to the field of intelligent transportation. The automatic lane line identification method based on the low-altitude aerial images comprises the steps that (1) an original image of a road is collected through low-altitude aircrafts, and the situation that the shooting angle of the aerial photography road is in the horizontal direction, and the area of the road is arranged in the middle of the image is ensured; (2) the collected image is converted into a grayscale image, the contrast ratio is improved, the grayscale image is copied, and an edge detection image and a binarization image are obtained according to the grayscale image; (3) connected areas are detected in the edge detection image and the binarization image, and characteristics of the connected areas are recorded; (4) the connected areas are deleted according to the number of pixels of the connected areas, the number of connected boundaries, the size of a bounding rectangle and variance values to obtain a central road line; (5) search is carried out on the two sides of the central road line to find roadside lane lines. The automatic lane line identification method based on the low-altitude aerial images is easy and convenient to calculate, and high in arithmetic speed and reliability, the road portion in an aerial photography video can be effectively extracted, straight roads and curve roads in the aerial images can be detected, and the automatic lane line identification method based on the low-altitude aerial images cannot be disturbed by background changes, and is high in accuracy.

The invention discloses a drone's low-altitude remote-sensing image high-resolution landform classifying method based on characteristic fusion. The method comprises the following steps: selecting common and representative landforms from to-be-processed remote sensing images and using them as the training samples of the landforms; extracting the color characteristics and the texture characteristics from the training samples of each landform; fusing the color characteristics and the texture characteristics; using a classifying method to classify and learn the fused characteristics to obtain the classifying model for each landform; extracting and fusing the color characteristics and the texture characteristics of the low-altitude remote sensing images of the to-be-classified drones; and finally, based on the fused characteristics of the classifying objects and in combination with the classifying model of each obtained landform, using the classifiers to divide the classifying objects into a certain landform. Therefore, the classification of the drone's low-altitude remote sensing images is achieved. According to the method of the invention, it is possible to more effectively and more quickly to extract the verification characteristics so that the classification result becomes more accurate.

An embodiment of the invention discloses a low-altitude aircraft dynamic monitoring system, and includes: a positioning device used for sending positioning data to an aircraft; an airborne terminal used for utilizing the positioning device to determine the exact position of the aircraft, broadcasting flight information of the aircraft to ground equipment through a wireless communication network, receiving data of other aircrafts sent by the ground equipment, and analyzing the received data; ground equipment used for receiving information sent by airborne terminals of aircrafts, performing real-time posture monitoring of the aircrafts, analyzing possible flight risks, broadcasting and issuing in an uplink manner and providing anti-collision alarm information; and an airborne interactive device used for being connected with the airborne terminal, and displaying real-time posture data of the aircrafts and the alarm information. Through low-altitude aircraft dynamic monitoring system provided by the invention, reasonable implementation of airspace management and traffic management are facilitated, operation economy is improved, and airspace utilization efficiency is improved, thereby fundamentally improving navigation flight safety.

The invention discloses a low-altitude defense system of an unmanned aerial vehicle. The low-altitude defense system is characterized by comprising a detection and recognition system, a photoelectrictracking system and an interference inversion system, wherein the detection and recognition system is used for performing scanning, detection and early warning of an invading unmanned aerial vehicle;the photoelectric tracking system is used for identifying, tracking and locating the invading unmanned aerial vehicle, and determining the coordinates of the intruding unmanned aerial vehicle; and theinterference inversion system is used for interfering or controlling the unmanned aerial vehicle. In the low-altitude defense system of the unmanned aerial vehicle, multi-sensor fusion front-end signal acquiring equipment is adopted, so that various parameters can be obtained, and the intruding unmanned aerial vehicle can be found and tracked in time. Meanwhile, automatic defense of the unmannedaerial vehicle is realized through linkage among systems.

The invention discloses a low-altitude aviation service station. The low-altitude aviation service station comprises a weather service system, an information service system, a flight plan service system and a monitoring service system, wherein the weather service system is used for providing weather service and ensuring that an operating environment of an aircraft meets weather conditions. The information service system is used for searching, clearing up, designing, manufacturing and issuing information materials for usage of flight crews and technical guarantee units in the organization and flight implementation process. The flight plan service system is used for providing flight plans and capable of providing control and information service for the aircraft according to approved flight plans. The monitoring service system is used for dynamically displaying flying situation information of the aircraft and reporting an airspace state in a region within the jurisdiction to a control center. The low-altitude aviation service station can monitor various all-purpose aircrafts executing flight missions in a low-altitude airspace and provide necessary flight plans, aviation meteorology, aviation information and other service.

The multifunctional aircraft used for low altitude and low speed flying platform includes one aircraft body and one power plant as well as one walking mechanism below the aircraft body and comprising universal wheels and driving motor. The aircraft body is one hollow flat disc with inside culvert fan and fan motor and outside support rods. The power plant includes propellers and motors installed separately on the support rods. The present invention has simple structure, low cost, stable and flexible low altitude and low speed flying and functions of adsorbing and walking.

The invention provides a method of full-artificial culturing Cordyceps sinensis, including sampling, strain separating, host insect collecting, breeding and feeding, infecting and continuing feeding, on artificial condition, largely culturing Hirsutella sinensis; feeding host insects in an scale room at low altitude, completing the infection of Hirsutella sinensis to the host insects and sexuality of Cordyceps sinensis. By artificial culture, the host grubs are big and good-quality, and the success rate of infection is high, the infection time is short, the quality is stable and controllable, and the pesticide effect test fully indicates that the pesticide effect of the produced Cordyceps sinensis is equivalent to that of the natural Cordyceps sinensis and it can overcomes the disadvantages of long growing time of natural Cordyceps sinensis and low natural infection ratio, and implements the industrialized production of Cordyceps sinensis.

The invention relates to a low-attitude tracking system of unmanned aircraft on ground movable target and relative method. Wherein, said system comprises carrier system and ground system; the carrier system is formed by camera, table, carrier image sender and carrier data transmitter; the ground system is formed by image receiver, image collector, PC, and ground data transmitter; the tracking method comprises that extracting target via threshold value division, calculating out the position of target gravity center to find its position in track field, and manually interfering the track state. It uses several threshold values, which can be replaced to improve the track stability. The invention has high real-time property and stability.

The invention consists in an inflatable ultralight parachute deployable before jumping, for jumping or releasing a load from any altitude, without experiencing unduly harm from the impact with the ground. It comprises at least one torus-shaped inflatable tube covered by a thin film substantially flat shroud whose buoyance lifts the parachute and when pulled down by the gravity of the attached body develops the braking force that decelerates its fall. The ultralight parachute is deployed either by the jumper if he has one, or by emergency helpers on the ground and subsequently lifted to the potential jumper. Optional accessories that enhance the braking force of the parachute and attenuate the impact of the attached body with the ground, include an aerodynamically shaped inversed skirt surrounding the torus-shaped tube, an electro-mechanical reel that upon activation shortest the distance between the jumper and the canopy and an air mattress that floats beneath the jumper's feet for reducing the impact of the fall when hitting the ground.

The invention provides a low-altitude remote sensing system based on an automatic cruise unmanned aerial vehicle. The low-altitude remote sensing system comprises a load system, a data acquisition system, a data transmission system and a control system. High-precision constant altitude cruising of the unmanned aerial vehicle along a preset route can be realized, and remote sensing data acquisition is performed. The scheme has remarkable effects of being lightweight, high in time and space resolution and low in cost.

The invention discloses a flight monitoring service method and a system thereof. The method is characterized by through a black box of a low altitude flight aircraft, acquiring a position and flight path information of an unmanned aerial vehicle; after carrying out correlation processing, using an unmanned aerial vehicle air traffic control system to send peripheral flight path information of the unmanned aerial vehicle to an unmanned aerial vehicle ground control station. The system comprises a civil aviation secondary radar, a low-altitude radar, radar access equipment, mobile acquisition equipment, an ADSB ground station, mobile conversion equipment, an automatic navigator, a GPS radio station, ADSC information conversion equipment, mobile communication equipment, a Big Dipper airborne navigator, a flight monitoring cloud server and a flight monitoring information application system. The method and the system of the invention have an advantage that dynamic data of an acquired unmanned aerial vehicle flight path, a state and the like can be taken as a monitoring information source and is transmitted to an air traffic control system currently used by military and civil aviation in real time so that a management department can conveniently monitor a flight state of a low altitude airspace unmanned aerial vehicle, and a blind area of current low-altitude spatial domain monitoring is compensated.

A radar altimeter is provided that includes a transmitter operable to generate a radio signal at a modulation frequency, and transmit the radio signal toward a ground surface for reflection therefrom to thereby propagate a reflected radio signal. The radar altimeter also includes a receiver operable to receive the reflected radio signal, and determine the altitude of the aircraft based on the modulation frequency of the radio signal and a difference frequency derived from the radio signal and the reflected radio signal. The receiver is also operable to control the transmitter so as to vary the modulation frequency of the radio signal based on the altitude of the aircraft. Preferably, the modulation frequency of the radio signal is greater at lower altitudes than at higher altitudes.

The invention relates to a guidance unmanned aerial vehicle net cast interception method for a "low-altitude, slow-speed and small" target. The guidance unmanned aerial vehicle net cast interception method comprises the steps that an unmanned aerial vehicle is set as the standby state; a ground control station determines a threat target and controls photoelectric detection equipment to perform dynamic tracking on the threat target; the ground control station acquires the location of the threat target and transmits a flight instruction to the unmanned aerial vehicle; and the unmanned aerial vehicle enters the maneuvering flight mode and reaches the area near the target. When the distance between the unmanned aerial vehicle and the target is less than a first threshold, the unmanned aerial vehicle is controlled to accurately approximate the target through a visual guidance device and a distance measurement device. When the distance between the unmanned aerial vehicle and the target is less than a second threshold, a net cast device is automatically triggered to emit an interception net to wind the target to fall off and finally the unmanned aerial vehicle returns. With application of the method, the net cast device is automatically triggered to intercept the target according to the relative location information between the unmanned aerial vehicle and the target so that the interception precision and the degree of automation can be effectively enhanced.

The invention provides a measurement and control communication method and a measurement and control communication system based on a low-altitude unmanned aerial vehicle self-network, which are wide in acting coverage range and can realize cooperative matching and dynamic stabilization. The method comprises the steps of performing self-network clustering on low-altitude unmanned aerial vehicles at different heights in different regions; respectively linking the low-altitude aerial vehicles to an airborne communication platform and a ground communication terminal by taking a cluster as a unit; regularly updating and maintaining clusters in the low-altitude unmanned aerial vehicle self-network. The system comprises the airborne communication platform and a plurality of low-altitude unmanned aerial vehicles; the space-based communication platform is communicated with the low-altitude unmanned aerial vehicles, the ground communication terminal and other airborne communication platforms; the low-altitude unmanned aerial vehicles carry task loads and are used for being communicated with the airborne communication platform, the ground communication terminal and other low-altitude unmanned aerial vehicles. The airborne communication platform and all the self-networked low-altitude unmanned aerial vehicles are organized to form a two-layer composite three-dimensional information network. Therefore, the integral efficiency of the system is improved, and the stability is high.

The invention discloses a method and a device for identifying target types. The method comprises steps that a sound signal of a target is acquired through a planar sound transmission array, the target includes any one of a low-altitude aircraft, a light aircraft, a power delta wing, a cruise missile and a power paraglider, the direction of the sound signal is evaluated, spatial filtering processing on the sound signal after direction evaluation is carried out, after spatial filtering processing, characteristics of the sound signal, characteristic vectors corresponding to the characteristics of the sound signal and characteristics of the target are extracted, type confidence of the target is determined according to the characteristics of the sound signal, the characteristic vectors of the sound signal and the characteristics of the target, the type confidence is identified through the fusion identification technology, and thereby the type of the target is determined. Through the method, type identification accuracy of the target is improved.

The invention discloses an indoor simulation testing platform and method for a two-phase flow field of spraying of a plant protection unmanned aerial vehicle. The indoor simulation testing platform comprises a console, a simulation device, a fog drop distribution detection and/or wind field detection device and the like. The indoor simulation testing platform is used for simulating low-altitude operation of the plant protection unmanned aerial vehicle, and can conduct indoor pesticide application tests through different unmanned aerial vehicles under the conditions of different working heights, different flight speeds and different spraying concentrations, and therefore research of the two-phase flow field and spraying distribution of low-altitude pesticide spraying of the unmanned aerial vehicle is facilitated, operation parameters of the unmanned aerial vehicle are optimized, and the corresponding procedure is assigned for plant protection operation of the unmanned aerial vehicle.