349 results about "Airplane mode" patented technology

The invention relates to the field of unmanned aerial vehicle monitoring, in particular to a low-altitude unmanned aerial vehicle flight monitoring method and system. A low-altitude unmanned aerial vehicle flight monitoring system comprises an obstacle sensing module, a confidence coefficient calculation module, a risk assessment module, an obstacle avoidance distance adjustment module and a flight mode switching module. According to the invention, by quantifying the rainfall interference index, the visibility index, the illumination intensity index, the obstacle complex index and the electromagnetic interference index, the confidence coefficient weight of the millimeter wave radar, the visual sensor and other multi-element sensing equipment is calculated in real time, so that the limitation of traditional fixed priority fusion is broken through; the optimal sensor data can be automatically selected as an obstacle avoidance decision basis according to actual environmental conditions, misjudgment or delayed response caused by sensor conflicts is avoided, the obstacle avoidance decision precision is improved, and the method is particularly suitable for high-reliability flight in complex environments such as urban canyons.

The invention relates to the technical field of unmanned aerial vehicles, and discloses a gas-electric hybrid composite wing unmanned aerial vehicle system, which comprises an intelligent energy management module, a gas-electric hybrid composite wing unmanned aerial vehicle control module and a gas-electric hybrid composite wing unmanned aerial vehicle control module, the self-adaptive flight control module is used for optimizing the flight attitude, dynamically adjusting the flight route and improving the flight safety; the task adaptive scheduling module is used for adaptively adjusting a task execution strategy according to the task category, the load condition and the environmental parameters; the data monitoring and remote control module is used for collecting the operation state of the unmanned aerial vehicle in real time and storing and analyzing flight data; the intelligent safety management module is used for improving the autonomous safety of the unmanned aerial vehicle; and the environment perception optimization module is used for perceiving external environment factors in real time. According to the invention, the intelligent energy management module realizes intelligent scheduling of fuel and electricity power, and dynamically optimizes the power distribution of the battery and fuel oil, so that the flight time of the unmanned aerial vehicle is greatly prolonged.

The invention relates to the technical field of aircrafts, and discloses an aircraft attitude control method, device and equipment and a storage medium, and the method comprises the steps: collecting flight state parameters of an aircraft; the pitch angle data in the flight state parameters are compared with a preset angle threshold value, corresponding flight mode switching is executed, and the attitude deviation value is calculated; power distribution calculation is conducted on the three ducts, and the target rotating speed of each duct paddle is obtained; performing position optimization calculation on the guide plates below the duct to obtain the position control quantity of each guide plate; the three flow guide plates are configured as triangular control points, the position compensation amount of an aileron, a yaw rudder and an elevator is calculated and determined through vector synthesis, and the angle control amount of each control surface is obtained; according to the method, the attitude of the aircraft is converted into an execution signal, execution feedback data is acquired to correct a control instruction in real time, closed-loop attitude control of the aircraft is realized, the attitude control precision of the aircraft is improved, and the stability of the flight process is ensured.

The invention provides a multi-mode intelligent propulsion control method, device and equipment for a short vertical aircraft and a storage medium, and the method comprises the steps: firstly obtaining flight state data in real time, and classifying the flight state data according to a state classification model of a decision tree to generate a current flight mode; next, calling a control strategy group and performing parallel processing on the current flight mode by taking the lowest energy consumption as an optimization target so as to generate a plurality of control instructions, and calling a fusion device weight network to process the current flight mode so as to generate a fusion weight of each control instruction, and generating a final control quantity according to the plurality of control instructions and the fusion weight, and sending the final control quantity to a pre-constructed hybrid propulsion structure nonlinear model to control the short vertical aircraft, thereby solving the problem that the short vertical aircraft cannot be adaptively adjusted when a plurality of propulsion units have differential dynamic characteristics.

The invention discloses an aircraft intelligent trajectory planning and cooperative control method based on offline optimization-intelligent learning-online guidance, and the method comprises the steps: firstly building an aircraft motion model and an aircraft-target relative motion model, and constructing a full-airspace and full-feature-point optimal trajectory data set; secondly, parameterized representation is carried out on the three-dimensional optimal trajectory, and a proportional guidance coefficient data set is constructed; then neural network training fitting is carried out on the proportional guidance coefficient data set, and a multi-constraint guidance method based on a neural network is designed; and finally, designing a three-dimensional collaborative guidance law by combining a multi-constraint guidance method and a residual time accurate estimation technology. According to the invention, the problems of insufficient real-time performance, incapability of meeting index optimality, incapability of coping with multiple constraints, difficulty in realizing multiple flight modes and the like of the existing trajectory planning and collaborative guidance technology are solved; the multi-constraint and optimality of the trajectory are realized through offline optimization, the global adaptability and small calculation amount of the trajectory are realized through intelligent learning, and a multi-cooperative flight mode is realized through online cooperative guidance.

The invention relates to the field of aircraft intelligent control, and discloses a sensor fault resistant low-altitude aircraft multi-mode propulsion control method, which comprises the following steps: constructing a nonlinear model of a short-vertical aircraft hybrid propulsion system, taking deep exploration optimization reinforcement learning as a main control, and combining a fuzzy controller and a model prediction controller to form a strategy fusion group; the method comprises the following steps: introducing a residual perception mechanism and a GIRLS-EKF health estimation module, extracting residual signal features by using CNN and Transform, and carrying out real-time diagnosis and dynamic weight adjustment on an abnormal measurement state of a sensor in combination with generalized residual least square filtering and an extended Kalman structure; the controller fusion module outputs the optimal control quantity in a self-adaptive manner according to the health state and the flight mode, and the fault-tolerant performance and the energy efficiency scheduling capability of the multi-propulsion system under the complex working condition are improved; the method is suitable for low-altitude economy and urban air traffic task scenes, and has good engineering integration and intelligent control application prospects.

The invention relates to the technical field of flight control, in particular to a hybrid control FPV unmanned aerial vehicle flight control system and method. The method comprises the following steps: acquiring triaxial angular velocity data of the unmanned aerial vehicle in real time by using an inertial navigation system, eliminating high-frequency noise and performing zero offset calibration; constructing a corresponding linear extended state observer to adjust a gain parameter in real time based on an absolute value of an observation error, and filtering tiny noise disturbance through a dead zone function to realize high-precision estimation of the system state and total disturbance of the unmanned aerial vehicle so as to obtain an error and an error change rate; and designing a self-adaptive PID control law to dynamically adjust PID control quantities corresponding to proportion, integral and differential gains, carrying out dynamic weighted stacking according to a flight mode, generating a three-axis control quantity, carrying out flight control on the FPV unmanned aerial vehicle, and meanwhile, realizing real-time visual verification of a control effect corresponding to the flight control. According to the invention, high-precision and high-robustness attitude control can be realized.

The invention provides a split type hovercar which comprises an aircraft module, a cabin module and a chassis module, and the split type hovercar has a ground mode, a flight mode, a take-off mode and a landing mode. The aircraft module is connected with the top of the cabin module, and the chassis module is detachably connected with the bottom of the cabin module; wherein after the split type hovercar is switched from a take-off mode to a flight mode, the chassis module is separated from the cabin module; after the split type hovercar is switched from the flight mode to the landing mode, the chassis module is in butt joint with the cabin module. Through the arrangement, after the split type hovercar is switched from a take-off mode to a flight mode, the chassis module can be separated from the cabin module, so that the flight resistance is reduced, and the flight energy consumption is reduced; after the split type hovercar is switched from the flight mode to the landing mode, the chassis module can be in butt joint with the cabin module, so that the split type hovercar slides and lands stably, and the landing efficiency is improved.

The invention relates to an intelligent flight mode recognition method based on IFPRM-SBLFS deep learning, solves the problem of flight state recognition from the perspective of time detection for the first time, and provides an intelligent flight mode recognition method combining sensitive boundary recognition and long flight sequence processing. According to the method, the limitation of a traditional method in single-mode recognition and composite maneuvering recognition is successfully broken, the tense boundary of the flight mode can be accurately positioned, online automatic recognition can be achieved, and the practicability and operation convenience of the model are greatly improved. The self-adaptive graph embedding module designed by the invention is mainly used for mining the spatial relationship of various flight parameters in the flight data, and can dynamically adjust the graph structure and adapt to different flight modes. Besides, a multi-scale transformer detector is introduced, so that the model has a multi-scale characteristic, abnormal modes during flight can be detected under different time scales, and fine flight characteristic changes can be captured.

The invention discloses a tilting quad-rotor unmanned aerial vehicle and an unmanned aerial vehicle countering system, and the system comprises a flight control module which is used for controlling the tilting quad-rotor unmanned aerial vehicle to fly towards a target unmanned aerial vehicle, and adjusting the flight mode and the flight speed of the tilting quad-rotor unmanned aerial vehicle in real time according to the distance and the speed difference in the flight process. The target identification module is used for collecting video stream information of a target airspace and detecting whether a target unmanned aerial vehicle exists in the video stream information frame by frame; the target tracking module is used for determining the distance and the speed difference between the target unmanned aerial vehicle and the tilt quad-rotor unmanned aerial vehicle under the condition that the target unmanned aerial vehicle exists in the video stream information; and the net gun capturing module is used for calculating a launching parameter of a capturing net when the distance between the target unmanned aerial vehicle and the tilt quadrotor unmanned aerial vehicle is smaller than a preset distance, and launching the capturing net to the target unmanned aerial vehicle according to the launching parameter. According to the scheme, the unmanned aerial vehicle can be precisely countered.

The invention discloses an automatic control method of a four-power-source tiltable aircraft, relates to the technical field of flight control of tiltable aircrafts, is realized based on a PX4 flight control system, and is suitable for a tiltable aircraft provided with four independent tiltable power sources and corresponding tilting execution mechanisms. According to the method, through configuration of a tilting angle control module, a power distribution module and a full-stage flight logic scheduling module, full-stage automatic control of vertical take-off and landing, suspension, horizontal take-off, fixed-point horizontal flight, automatic cruise, one-key return flight, fixed-angle flight, power source fault handling and the like is achieved. Smooth transition of all flight modes is achieved, the stability of the attitude, the height and the position of the tiltable aircraft in different flight stages is maintained, meanwhile, the functions of automatic obstacle avoidance, fault emergency and the like are integrated, flight safety is guaranteed, flight stability and applicability are improved, and the method can be widely applied to various tiltable aircraft operation scenes.

The invention discloses a wireless communication method, device and equipment, and belongs to the field of communication, and the wireless communication method comprises the steps that a terminal sends first information to network side equipment; wherein the first information is used for indicating at least one of the following items: preference of the terminal for executing the first operation and information obtained by mobility reasoning based on an AI model; the first operation comprises at least one of the following items: cell switching, cell redirection, connection reestablishment, cell selection, cell reselection, activation of a turned-off cell, entering an idle state, leaving a connection state, shutdown, entering a flight mode, and mobility reasoning based on an AI model. In the embodiment of the invention, the terminal reports the preference of the terminal for executing the first operation or the information obtained by the mobility reasoning based on the AI model, so that the network side equipment can perform terminal-level configuration optimization according to the preference information of the terminal or the information obtained by the mobility reasoning based on the AI model, and the performance improvement taking the terminal as the center is realized.

An exemplary tiltrotor aircraft having a vertical takeoff and landing (VTOL) flight mode and a forward flight mode includes tiltable rotors located at forward boom ends, tiltable ducted fans located at wings aft of the forward boom ends, and aft rotors located on aft boom portions.

The invention discloses a fuselage-free unmanned aerial vehicle, an aviation container and a modular transportation system and method, and aims to solve the problems of high transportation cost of traditional aviation goods and low transportation efficiency of land goods. The aircraft is not provided with a warehouse and adopts a flying wing type layout or a conventional layout, wings in the flying wing type layout or the conventional layout are used for generating lift force and enter a straight wing flight mode after taking off, and the wings are provided with power systems, flight control systems and mounting structures used for being detachably connected with the streamline aerodynamic configuration aviation containers. Through the dynamic combination mode of the aircraft and the containers, the single aircraft can achieve the operation cycle of circularly transporting at least three containers. Through continuous container reloading operation, the aircraft can keep a continuous flight state without waiting for a loading and unloading process. And meanwhile, the container can be quickly circulated among different aircrafts through the modular design. According to the transportation mode, optimal configuration of transportation resources is achieved through efficient cooperation of the aircraft and the container.

The invention discloses a water-air cross-medium unmanned platform mode conversion aircraft. The water-air cross-medium unmanned platform mode conversion aircraft comprises a shell structure, a mode conversion mechanism and a bionic front fin structure. The mode switching mechanism switches different working modes when the aircraft is in an underwater navigation mode and a flight mode, when the aircraft is in the underwater navigation mode, the separable shell and the bionic shell are attached to each other to ensure the streamline appearance of the aircraft in the underwater mode, and when the aircraft is in the flight mode, the separable shell and the bionic shell are attached to each other to ensure the streamline appearance of the aircraft in the flight mode. A separable shell and a bionic shell in the shell structure are separated from each other, the position of the separable shell is located over the position of an underwater mode, and during mode conversion, the separable shell is controlled by a lifting push rod on the lower portion to ascend and descend. Different propulsion modes are selected according to the navigation modes of the aircraft in different media, and the mutual influence between the two propulsion modes is reduced to the minimum through reasonable arrangement of a variant scheme.

The invention relates to the technical field of flight control, in particular to a flight control system function logic model design method. The method comprises the following steps: acquiring multi-source data of an aircraft; performing data format unification on the aircraft multi-source data to generate an aircraft multi-source unified data set; performing flight virtual scene reconstruction on the multi-source unified data set of the aircraft to generate a three-dimensional flight virtual scene; carrying out aircraft flight condition analysis on the aircraft multi-source unified data set to obtain aircraft flight condition data; constructing a flight classifier according to the flight condition data of the aircraft to obtain an aircraft flight mode classifier; the aircraft flight mode classifier is used for carrying out aircraft flight mode recognition on the aircraft flight motion characteristic data, and aircraft flight mode data are generated. By unifying multi-source data, accurately analyzing the flight condition and optimizing the flight control strategy, the adaptability and optimization capacity of the flight control system function logic model design are improved.

The invention discloses an unmanned aerial vehicle formation flight control method and device, an unmanned aerial vehicle and a storage medium. The method comprises the steps that formation parameters, flight task instruction data and flight state data of other unmanned aerial vehicles in a formation are acquired or updated; judging a control mode according to the flight task instruction data, wherein the control mode comprises at least one of the following modes: a normal control enabling and conventional flight mode, a calculation mode, a suspended hovering mode or a disintegration mode; according to the judgment result of the control mode, based on an L1 guide algorithm of self-adaptive track tracking, fusing unmanned aerial vehicle spacing control logic and / or formation control logic of formation dynamic adjustment to obtain a control instruction of an expected track and / or attitude, and executing the control instruction; and circularly executing the steps to ensure the continuity and dynamic adaptability of the unmanned aerial vehicle and the formation flight thereof. According to the scheme, a completely decentralized distributed control architecture is adopted, and a fault-tolerant mechanism is matched, so that the reliability and survivability of the formation system are remarkably improved.

The invention discloses a vertical take-off and landing fixed-wing aircraft, and relates to the technical field of aircrafts. According to the invention, the conversion from a multi-rotor flight mode to a fixed-wing flight mode and from the fixed-wing flight mode to the multi-rotor flight mode can be easily realized. Due to the structural layout characteristics of the aircraft, the safety of the aircraft is guaranteed, and the aircraft can be safely and reliably landed according to the fault degree and urgency of the aircraft even if the aircraft breaks down seriously and only forced landing can be selected. Through multi-rotor-wing assisting control, the forced landing buffering function of the telescopic empennage assembly and the safety protection measure of a protection sponge lining in the manned cabin, various safety modes and measures such as an internal safety protection air bag, an external safety protection air bag and a forced landing parachute of the manned cabin can be selectively used according to the fault degree and urgency of the aircraft; and safe or low-damage forced landing of the aircraft is realized.

This application discloses a call method and system, and a related apparatus. When a specific condition is met (for example, a callee fails to be paged), a network device forwards, to a VoIP server, a first call request to a target number, where the first call request is a call request initiated by a calling terminal to the target number, and the target number has been subscribed to a call forwarding service. Then the VoIP server parses a forwarding message from the network device to obtain a called number, searches, based on the called number, for the called terminal associated with the called number, and initiates a VoIP call to the called terminal, so that the callee in an out-of-service state (for example, there is no signal of an operator network or the callee is in an airplane mode) can still receive the call request from the caller.

The application discloses a fusion positioning algorithm based on low-orbit satellite Doppler measurement, DME and VOR, relates to the technical field of satellite navigation, and comprises the following steps: acquiring the Doppler frequency shift of a low-orbit satellite, the slant range information of a DME and the azimuth angle data of a VOR, constructing a combined observation equation, and obtaining a corresponding Jacobian matrix; based on a geometric dilution of precision, selecting stations and stars through a genetic algorithm, optimizing the selection of the DME, the VOR and the low-orbit satellite, and obtaining an optimal navigation source combination; constructing a motion model under different flight modes, and dynamically estimating the state of an aircraft by using an interactive multiple model Kalman filter, and updating the position information in real time. Therefore, the real-time positioning of the aircraft under complex conditions is realized, the anti-interference capability of the system is improved, and the overall positioning precision and stability of the system are improved.

The invention relates to the technical field of aircrafts, and discloses a distributed asynchronous tilt-rotor aircraft and a control method, and the method comprises the steps: receiving an instruction from the ground to obtain a ground instruction, and obtaining position information, speed information and the health state of the aircraft; deciding an adopted flight mode; in the multi-rotor mode, the optimized cross inclination angle is adopted to enhance the yaw control performance of the aircraft; giving an optimized control quantity in a fixed wing mode; in the transition flight mode, corresponding control strategies are obtained based on different asynchronous tilting strategies for control; adjusting the attitude of the aircraft according to the control instruction; according to the method, different flight modes can be controlled by adopting corresponding control distribution algorithms, the problems of complex control and low reliability of the tilt-rotor aircraft in the transition process can be effectively solved, the full-attack-angle and full-speed-domain flight capability of the tilt-rotor aircraft in the transition process is realized, and the flight efficiency of the tilt-rotor aircraft is improved. And the stall state of the aircraft in the transition process is avoided.

The invention provides a method for measuring a three-dimensional route based on approaching photogrammetry of an unmanned aerial vehicle, which comprises the following steps of: S1, analyzing route planning methods based on a target initial model in different flight modes by utilizing route planning definition and two common methods for three-dimensional reconstruction of the unmanned aerial vehicle; according to concepts and processes close to photogrammetry, summarizing the requirements on route planning from the aspects of a planning method, a hardware platform and a route file format; s2, defining four types of aerial photography basic geometric objects used for selecting a to-be-reconstructed target in the initial model, and designing a surface target automatic extraction algorithm; and S3, according to constraint factors and a common method of three-dimensional path planning of the unmanned aerial vehicle, spatial obstacle avoidance analysis is performed through spatial environment modeling and collision detection, and a route optimization method including viewpoint adjustment and path search is designed on the basis of the spatial obstacle avoidance analysis. According to the method, aiming at the problem of unmanned aerial vehicle three-dimensional route planning in photogrammetry three-dimensional reconstruction work, photographing viewpoint planning meeting reconstruction requirements and unmanned aerial vehicle flight path planning considering various influence factors are researched.

The invention discloses a fusion positioning algorithm based on low earth orbit satellite Doppler measurement, DME and VOR, and relates to the technical field of satellite navigation, and the algorithm comprises the steps: obtaining Doppler frequency shift of a low earth orbit satellite, slant range information of the DME and azimuth angle data of the VOR, constructing a combined observation equation, and obtaining a corresponding Jacobian matrix; based on the geometric accuracy factor, channel and satellite selection is carried out through a genetic algorithm, DME, VOR and low-orbit satellites are optimized and selected, and an optimal navigation source combination is obtained; motion models in different flight modes are constructed, interactive multi-model Kalman filtering is utilized to dynamically estimate the state of the aircraft, and position information is updated in real time. Therefore, by the adoption of the method, real-time positioning of the aircraft under complex conditions is achieved, the anti-interference capability of the system is improved, and the overall positioning precision and stability of the system are improved.

The invention relates to the technical field of unmanned aerial vehicles, in particular to a power grid inspection method and system based on an unmanned aerial vehicle, and the method comprises the steps: obtaining a target tower and judging the type of the tower in combination with real-time visual detection and radar; locking the target pole tower and positioning in real time to determine a target position; if the target position is determined, entering a visual guidance flight following mode, otherwise, entering a radar line simulation flight mode until the target position is determined; before following of the current target pole tower is finished, different next pole tower searching strategies are executed according to the pole tower type, if the pole tower is a forked pole tower, a branch is manually selected, and if the pole tower is not the forked pole tower, locking of the current target pole tower is relieved when routing inspection crosses a preset position; and repeating the steps to continuously fly. According to the invention, the remote sensing advantage of vision and the short-distance detection advantage of radar can be deeply combined, the flight mode is adaptively switched, and the line patrol efficiency, accuracy and intelligent degree are improved.

The invention discloses an unmanned aerial vehicle anti-wind disturbance controller and a control method, and belongs to the technical field of unmanned aerial vehicle flight control. The method runs on an independent processing module which is connected in series between a main flight controller and an electronic speed regulator of the unmanned aerial vehicle, a dynamic reference is constructed by collecting motor current in real time, deviation is calculated, and wind disturbance equivalent disturbance torque is estimated in a prospective mode through a third-order linear extended state observer (LESO) with bandwidth parameterization design; in combination with a'user operation state + flight mode 'two-dimensional intelligent decision compensation strategy, a'look-ahead wind resistance + attitude backup' dual-redundancy channel is matched, so that the wind disturbance is compensated in advance, and the flight stability in a complex scene is ensured. A corresponding controller adopts a standardized independent hardware design, the adaptability is high, the integration cost is low, and the method can be widely applied to high-precision operation scenes of various multi-rotor unmanned aerial vehicles.

The invention discloses an intelligent flight path planning method for an unmanned aerial vehicle in a multi-type scene, and the method comprises the following steps: 1, building task input and task type recognition: setting the unmanned aerial vehicle to be in a fixed-height flight mode, and obtaining space information required by a task, including a take-off point position, a task point coordinate set and a task region boundary, the system identifies the task type through analysis; if the input is a discrete point set, the task is judged as a point task; if the structure is a broken line structure, judging the task as a line task; if the boundary is a task area boundary, the task is judged to be a surface task, and if the boundary width L is small, the task is still judged to be a line task. The method has the advantages that a fitness function is improved, the shortest total time of multiple unmanned aerial vehicle tasks is used as an optimization target, and task real-time weight parameters are introduced, so that a planning result meets task timeliness and energy consumption optimization at the same time; the coverage of planar tasks is realized in combination with a cattle farming algorithm, dynamic planning of electric quantity and a battery swap station is performed in combination with a greedy algorithm, and path optimization and improvement of energy management are realized.

The invention provides a complex area unmanned aerial vehicle surveying and mapping mode decision and path planning method, and relates to the technical field of unmanned aerial vehicles. According to the method, aiming at the defect that traditional unmanned aerial vehicle surveying and mapping cannot automatically adapt to different terrains in a terrain with large height fluctuation, flight modes of an unmanned aerial vehicle at different terrain heights are decided based on a height fall threshold algorithm, and surveying and mapping sub-regions adopting different flight modes are generated; the complexity of manual flight mode setting and surveying and mapping area delimiting is avoided, and it is ensured that each surveying and mapping sub-area can adopt the optimal surveying and mapping path according to the topographic characteristics of the surveying and mapping sub-area. Performing path planning on each surveying and mapping sub-region, and recording coordinates of a driving-in / driving-out point of each surveying and mapping sub-region; a mathematical model of coverage path planning of multiple surveying and mapping sub-regions of the single unmanned aerial vehicle is constructed, and a path which passes through all task points in the to-be-surveyed and mapped region and has the shortest flight distance is obtained based on a variable neighborhood search VNS-genetic algorithm, so that the surveying and mapping efficiency and precision are improved.

The invention discloses a multi-task PEM unmanned aerial vehicle energy scheduling method and system based on MPC and DDPG, and the method comprises the steps: building a stress model and a power model in each flight mode according to the flight mode of a hydrogen fuel cell unmanned aerial vehicle; establishing a mathematical model, an objective function and operation constraints of the hydrogen fuel cell unmanned aerial vehicle energy system; constructing an MPC model by combining the stress model and the power model of the unmanned aerial vehicle in each flight mode, collecting state parameters of the unmanned aerial vehicle, and obtaining electric power predicted by the MPC model; and constructing a DDPG model based on the mathematical model, the objective function and the operation constraint of the hydrogen fuel cell unmanned aerial vehicle energy system, and taking the predicted electric power as the input of the trained DDPG model to obtain an energy scheduling result. According to the invention, energy utilization can be optimized in a complex task environment, and the task completion efficiency and cruising ability of the unmanned aerial vehicle are improved.

In the descending process of the aircraft, the flight control system seeks and keeps a glide gradient, and the glide gradient is determined according to the parameters input by a single pilot; for example, the position of a control shaft of a flight joystick. During landing approach, a pilot visually observes a predetermined landing site, so that the pilot can easily determine an appropriate guide slope selection. The glide slope defines a ratio of forward and descent speeds that is automatically established and maintained / updated as a function of pilot input, while these speeds are automatically lowered during descent, although the two speed directions are each affected by significantly different aircraft mechanisms controlling them. The aircraft ends its glide path when the speed is zero or near zero so as to be able to land by short-distance vertical descent. Thus, the pilot gets rid of both the problems of coordinating the speed to reach a specific guide gradient and reducing the speed while maintaining such coordination.

Aspects presented herein may enable a tracking device to disable its transmitter based on determining whether the wireless device is within the vicinity or a threshold distance of an airport and / or based on information or measurements obtained from its modem receiver. In one aspect, a wireless device detects whether the wireless device is within a threshold distance of a target location or whether the wireless device is airborne. The wireless device disables a transmitter of the wireless device based on detecting that the wireless device is within the threshold distance of the target location or that the wireless device is airborne.