728 results about "Cruise" patented technology

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 fan blade autonomous inspection method based on an unmanned aerial vehicle. The method comprises the following steps that S1, determining whether the geometric structure of ato-be-inspected fan is known, if yes, entering the step S2, if not, entering the step S3; S2, carrying out image shooting on a to-be-inspected fan, determining coordinate information of a plurality of inspection points on the fan in combination with the geometric structure of the to-be-inspected fan, and entering the step S4, the inspection points being target points shot during inspection; S3, carrying out image shooting on the to-be-inspected fan, acquiring coordinate information of a plurality of inspection points on the fan through image processing, and entering the step S4; and S4, according to the coordinate information of the inspection point, determining a cruise point coordinate and generating an autonomous cruise trajectory, the cruise point being a place where the unmanned aerial vehicle hovers and shoots, and the unmanned aerial vehicle completing inspection of the fan blade according to the autonomous cruise trajectory. According to the invention, the workload of autonomous inspection route generation can be effectively reduced, the accuracy of the route is improved, and the inspection efficiency of the fan is improved.

The invention discloses a fixed-wing aircraft on which retractable multi-rotor assemblies are mounted and which can perpendicularly take off and land. In the scheme of the fixed-wing aircraft, the fixed-wing aircraft comprises fixed-wing assemblies, retractable multi-rotor assemblies, a multi-rotor extending and retracting control mechanism, a multi-rotor hatch which can be opened and closed and a hatch opening and closing control mechanism. The fixed-wing aircraft is characterized in that when the aircraft is in a take-off stage or a landing stage or when the aircraft needs to hover in the air, the retractable multi-rotor assemblies in the lower part of an aircraft body are unfolded to provide a perpendicular take-off and landing capacity; when the aircraft cruises at a high speed, the multi-rotor assemblies are retracted in the aircraft body, the multi-rotor hatch is closed to keep the aerodynamic performance of the fixed-wing aircraft; and besides, when the fixed-wing aircraft is in perpendicular take-off and landing state, hovering state and cruising state at a high speed, the highest energy service efficiency can be obtained, so that the fixed-wing aircraft disclosed by the invention has a large perpendicular take-off and landing weight and a long range at the same time. According to the fixed-wing aircraft disclosed by the invention, a solution of a perpendicular take-off and landing fixed-wing unmanned aerial vehicle which is low in cost and high in energy efficiency is provided, is wide in application, and is particularly suitable for being applied to trades including point-to-point article transportation, long-distance cruise and the like.

The invention discloses an unmanned operational intelligent ship apparatus which comprises an intelligent ship body. The intelligent ship body is provided with a main control module. The main control module is connected with a navigation system, a water quality detection system and a data transmission module. The water quality detection system comprises a sensor module arranged at the lower part of the intelligent ship body. The navigation system comprises a Beidou and GPS dual-mode positioning module and a compass module. The main control module is further connected with an execution mechanism, a range finding module, and an electricity amount detection system. The data transmission module communicates data with an intelligent terminal. The intelligent terminal is provided therein with a control system APP used to control the intelligent ship. The apparatus and the control system of the invention are able to realize self-cruise, to automatically avoid barriers, to automatically back charge, to communicate data with the intelligent terminal and to control an unmanned operational intelligent ship according to the data acquired on the site. And at the same time, the monitoring and managing of the intelligent ship and the water areas become more convenient by providing checkable intelligent ship's travel trajectory at any time, the ship power amount state, the water quality parameters of a culturing area to control the working of the intelligent ship.

The invention relates to the technical field of aerospace equipment, in particular to a flight bird repellent and a flight bird repelling system. The flight bird repellent comprises a central body and 2n+2 wings respectively connected to the central body, wherein n is a positive integer, a power mechanism is mounted on each wing, a navigation control module and a repelling device for repelling birds are fixedly mounted on the central body, and the power mechanisms and the repelling device are respectively connected with the navigation control module which is connected with a remote control signal transmitter. The ground station system of the flight bird repelling system is connected with the navigation control module and controls the operation of the flight bird repellent. The flight bird repellent and the flight bird repelling system have the advantages that the flight bird repellent has stable and reliable flying ability, the covering range of the bird repelling is enlarged evidently, and operation flexibility and work efficiency are increased; the flight bird repelling system controls one or more flight bird repellents to perform cruise flight or tracking bird repelling through the ground station system, and spatially three-dimensional and flexible and mobile bird repelling effect can be achieved.

The invention discloses an unmanned aerial vehicle inspection method for an unknown fan structure. The method comprises the following steps: S1, multi-angle photographing of a whole fan is carried outat a long distance, and the whole fan should be contained in each picture and be close to the center of each picture; S2, inspection point coordinate information for equally dividing the blade is calculated by utilizing obtained key inspection point coordinate information; S3, required cruise point coordinate information is calculated by utilizing the inspection point coordinate information, anda flight path is generated; S4, an unmanned aerial vehicle takes off and arrives at a cruise point, and the pose of the unmanned aerial vehicle is adjusted by utilizing inspection point coordinate information to enable the unmanned aerial vehicle to face a target point; and S5, target identification is performed on an inspection point once before photographing of a cruise point, and the attitude of a holder is adjusted again to make the inspection point be close to the center of each picture as much as possible. The inspection point can be close to the center of each picture as much as possible, and the reliability of autonomous inspection of the unmanned aerial vehicle is higher while the efficiency is improved.

A system for bistatic radar target detection employs an unmanned aerial vehicle (UAV) having a ramjet providing supersonic cruise of the UAV. Deployable antenna arms support a passive radar receiver for bistatic reception of reflected radar pulses. The UAV operates with a UAV flight profile in airspace beyond a radar range limit. The deployable antenna arms have a first retracted position for supersonic cruise and are adapted for deployment to a second extended position acting as an airbrake and providing boresight alignment of the radar receiver. A mothership aircraft has a radar transmitter for transmitting radar pulses and operates with an aircraft flight profile outside the radar range limit. A communications data link operably interconnects the UAV and the tactical mothership aircraft, transmitting data produced by the bistatic reception of reflected radar pulses in the UAV radar antenna to the mothership aircraft.

The invention provides a vertical take-off and landing unmanned aerial vehicle and a control method thereof. A vehicle body of the unmanned aerial vehicle adopts aerodynamic layout of high lift-drag ratio class flying wings, and four motors and propellers are installed on the vehicle body in a mode of cross-shaped arrangement. An elevating control torque is formed by the thrust difference generated by the upper propeller and the lower propeller of the vehicle body, a yaw control torque is formed by the thrust difference generated by the left propeller and the right propeller of the vehicle body, and through the roll control torque formed by the different rotating speeds of the four propellers, the attitude control of the vehicle body of the unmanned aerial vehicle is conducted so that vertical take-off and landing in a narrow region and spot hover at any positions in the flying process of the unmanned aerial vehicle can be achieved. After the unmanned aerial vehicle is switched into a flat flying state, the vehicle body of the class flying wing layout can generate a large cruise lift-drag ratio, the effective loading level of the unmanned aerial vehicle is greatly improved, and the flying distance of the unmanned aerial vehicle is greatly prolonged. When the unmanned aerial vehicle horizontally flies, propelling can be conducted for low-speed flying only by using the left propeller and the right propeller, and propelling can be conducted for high-speed flying by simultaneously using the four propellers.

The invention discloses a method for automatic cruise detection of comprehensive information of greenhouses. According to the method, an optimal cruise path can be set according to the needs of different greenhouse soil bin structures and greenhouse comprehensive information acquisition, the precision of cruise is guaranteed through ultrasound position detection, a detection target is located based on laser sensing, and power is timely supplemented to a mobile platform through an automatic charging device during cruise intervals. Thus, continuous-cruise dynamic monitoring on greenhouse environment and crop information is realized, the detection efficiency and accuracy are improved, and an unmanned management mode is realized. The method of the invention can be applied to detection of greenhouse environment and crop growth information.

The invention discloses a method for extracting the cruise section of a flight path from a three dimensional position sequence of an air craft, including: (1) reading atmospheric pressure height data of the air craft and recording the time of the data; (2) calculating the flight level at which the air craft is located currently; (3) cutting off climbing and descending sequence section in level flight section to obtain the level flight sequence section of the cruise section; (4) reading GPS longitude and latitude data and recording the time of the data; (5) intercepting the GPS longitude and latitude sequence into direct flight sequence section and cutting off turning sequence section to obtain the direct flight sequence section of the cruise section of the air craft; (6) solving an intersection of the level flight sequence section and the direct flight sequence section over time; calculating the difference of atmospheric pressure height data with lower sample rate in the sequence duration of which meets the duration requirement to extract the cruise section of the flight path is extracted. The method realizes analysis and processing on the three dimensional position sequence of the air craft, effectively removes climbing, descending and turning sections and extracts the cruise section of the flight path.

The invention belongs to the field of water quality monitoring. The purpose of the invention is to provide a water area water quality abnormal point detecting and pre-warning method which has very high detection accuracy and degree of intelligence. According to the technical scheme, the water area water quality abnormal point detecting and pre-warning method comprises the following steps: (a) intelligent cruise; (b) monitoring data model analysis; (c) suspected abnormal data point check; and (d) abnormal data point on-site water sample collection. According to the method, an intelligent cruise ship is used as a carrier, a water quality abnormality analysis model serves as a software support, and human-computer interaction is performed based on the Internet-of-things technology. Water quality abnormal point detecting and pre-warning is truly realized.

The invention belongs to the field of flight mechanics, and particularly relates to a subsonic cruise voyage optimization design method for a fixed-wing aircraft. The method comprises the steps: obtaining 1, flight parameters of the fixed-wing aircraft, wherein the flight parameters comprise the maximum lift-drag ratio Kmax, the cruise lift coefficient Cy and the cruise Mach number M; 2, determining the engine thrust oil consumption rate Ce0 of a cruise entry point and the engine thrust oil consumption rate Ce1 of a cruise end point according to the flight parameters; 3, calculating the average oil consumption rate according to the engine thrust oil consumption rate Ce0 at the cruise entry point and the engine thrust oil consumption rate Ce1 at the cruise end point, and taking the averageoil consumption rate as the voyage calculation oil consumption rate Ce; and 4, calculating the variable-height cruise voyage L of the fixed-wing aircraft according to the voyage calculation oil consumption rate Ce. According to the optimization design method for the subsonic cruise voyage of the fixed-wing aircraft, a large amount of original data used by professional performance software or simulation software is not needed, calculation is rapid and simple, and the model argumentation precision requirement is met.

Vertical takeoff and landing (VTOL) aircraft are provided with fixed-position port and starboard wings extending laterally from an elongate fuselage having an empennage at an aft end of the fuselage and a propeller to provide horizontal thrust to the aircraft in a direction of the longitudinal axis thereof. A series of port and starboard rotor units are provided, each of which includes axially opposed rotor blades, and a motor to rotate the rotor blades and provide vertical thrust to the aircraft. A logic control unit (LCU) controllably sets an angular position of the opposed rotor blades along a position axis relative to the longitudinal axis of the aircraft in response to determining an optimal position of the rotor blades during cruise flight operation to thereby minimize airflow disruption over the fixed-position wings.

The invention relates to a lateral guidance command generation method for an aircraft flight tracking linear and circular path. A flight path of an aircraft gradually converges to a straight or arc path that is preset to pass, the vertical distance between the aircraft and the preset linear path or/and the arc path is controlled for getting shorter and shorter, moreover, the flight direction of the aircraft is controlled for converging to the linear direction or/and the arc tangential direction. The method is advantaged in that easy control is realized, the aircraft is not required to fly overa certain point at a certain time, so that requirements of the small-sized aircraft for effectively following the preset path under the premise of being vulnerable to external environment such as thewind during the cruise level flight can be met, technical supports are provided for completion of preset tasks for the cruise level flight of the small aircrafts, and system reliability and accuracyare improved.

The invention provides an unmanned aerial vehicle cruise system. The system comprises an unmanned aerial vehicle and a plurality of cruise control devices preset in a cruise route of the unmanned aerial vehicle. The unmanned aerial vehicle sequentially cruises to each cruise control device according to a preset cruise route; when the unmanned aerial vehicle arrives at any cruise control device, the unmanned aerial vehicle is connected with the cruise control device, the unmanned aerial vehicle is subjected to cruise operation through the cruise control device, so that the unmanned aerial vehicle does not need to return to the previous cruising control device for charging or other cruise operations, the unmanned aerial vehicle can continue to perform inspection work to a farther cruise destination, and the automatic cruise range of the unmanned aerial vehicle is expanded.

The invention provides a regional pollution condition analysis device and method. The device comprises: an unmanned cruise module which is used for driving the analysis device to enter a cruise mode,and carrying out the cruise in a to-be-detected region; an online pollutant collection module which is used for collecting concentration data of various pollutants along the road and at a to-be-monitored point after the analysis device enters the cruise mode; an analysis module which is used for analyzing the concentration data of the pollutants at each detection block so as to select a pluralityof high-pollution point locations, planning a cruise path according to the location distribution of the plurality of high-pollution point locations, and selecting a shortest path; and an off-line pollutant acquisition module which is used for acquiring concentration data of various pollutants at the high-pollution point on the shortest path when cruising according to the shortest path. The contradiction among the number of detected species, accuracy and cost is considered. Pollution sources can be autonomously discovered, and multi-species online accurate analysis sampling and pollutant samplecollection can be autonomously carried out on the pollution sources in a control area.

The invention relates to an unmanned aerial vehicle swarm takeoff and landing control method, an unmanned aerial vehicle swarm takeoff and landing control device, computer equipment and a storage medium, wherein the method comprises the following steps of obtaining located position information of an unmanned aerial vehicle swarm and corresponding first cruise point position information; selectingan unmanned aerial vehicle from unmanned aerial vehicles on which takeoff is not set in the unmanned aerial vehicle swarm; by using the selected unmanned aerial vehicle as a reference, sequentially selecting a plurality of unmanned aerial vehicles beyond a safe distance range until the quantity of the selected unmanned aerial vehicles reaches the single-time maximum takeoff quantity; using all ofthe current selected unmanned aerial vehicles as a current takeoff group for simultaneous takeoff; simulating the whole takeoff process of the current takeoff group according to the takeoff interval time; judging whether the current takeoff group and the takeoff group which have already taken off generate collision or not; if the collision occurs, gradually increasing the takeoff interval time until the collision cannot occur between the takeoff groups; and if the collision does not occur, determining the takeoff time of the current takeoff group. The automatic control of the takeoff and landing of the unmanned aerial vehicles is realized, and the safety and the reliability of the whole takeoff and landing process are ensured.

The invention belongs to the pneumatic layout technology of a conventional pneumatic layout aircraft, and relates to a method for determining an installation angle of a conventional pneumatic layout aircraft wing. The method for quickly determining the installation angle of the aircraft wing comprises the following steps that a preliminary wing installation angle is firstly given, and only a knownpitching moment coefficient of a zero angle of attack wing and fuselage combination body is needed, a horizontal tail lift force coefficient is calculated through a whole-aircraft pitching moment balance condition, and in the case that the horizontal tail lift force coefficient and a wing and fuselage combination body lift force coefficient are known, a whole-aircraft lift coefficient is obtained; a series of wing installation angles are given, and the relationship between the whole-aircraft lift coefficient and the wing installation angle is obtained under conditions that the angle of attackof the fuselage is zero and the whole-aircraft pitch moment coefficient is zero; and based on the cruise design point condition, the final wing installation angle is determined by interpolation according to the cruise whole-aircraft lift coefficient. The method has the advantages that the calculation amount is small, the size of the installation angle of the traditional pneumatic layout wing canbe directly and rapidly determined, the aerodynamic property calculation or wind tunnel test workload is effectively saved, and the method has relatively large practical application value.

The invention discloses a nonlinear self-healing control method for a multi-sensor fault of a hypersonic flight vehicle, and the method comprises the steps: obtaining a longitudinal affine nonlinear system of the hypersonic flight vehicle through employing an input and output feedback linearization technology for a longitudinal nonlinear model of a cruise stage of the hypersonic flight vehicle; establishing a sliding mode surface for the obtained system, and designing a sliding mode controller under a fault-free condition; and injecting a multi-sensor constant deviation fault into an originalhealth system, and designing a fault estimation scheme. Specifically, a nonlinear adaptive observer is designed for a speed channel; aiming at a height channel, a backstepping sliding mode observer isdesigned to estimate a state quantity and a sensor fault; and after a fault estimation result of the height sensor and the speed sensor is obtained, a fault-tolerant controller is designed to compensate output signals of the height sensor and the speed sensor. The method can solve the problem of fault-tolerant control under the condition that the longitudinal system of the hypersonic aircraft suffers from speed and angle channel multi-sensor faults, and the self-healing capacity of the system is improved.