Flight control method and equipment of unmanned aerial vehicle and unmanned aerial vehicle

文档序号：1174163 发布日期：2020-09-18 浏览：2次中文

阅读说明：本技术 一种无人机的飞行控制方法、设备及无人机 (Flight control method and equipment of unmanned aerial vehicle and unmanned aerial vehicle ) 是由吕熙敏张子豪商志猛林灿龙于 2019-05-29 设计创作，主要内容包括：提供了一种无人机的飞行控制方法、设备及无人机,其中,该方法包括：获取飞行模式切换指令,飞行模式切换指令用于指示无人机的飞行模式在旋翼飞行模式和固定翼飞行模式之间切换(S301)；根据无人机当前的飞行状态信息和/或无人机当前所处环境信息,确定无人机是否满足飞行模式切换条件(S302)；当无人机满足飞行模式切换条件时,对无人机当前的飞行模式进行切换(S303)。通过这种方式,可以提高无人机在飞行模式切换过程中的安全性和可靠性。(Provided are a flight control method and device for an unmanned aerial vehicle and the unmanned aerial vehicle, wherein the method comprises the following steps: acquiring a flight mode switching instruction, wherein the flight mode switching instruction is used for instructing the flight mode of the unmanned aerial vehicle to switch between a rotor wing flight mode and a fixed wing flight mode (S301); determining whether the unmanned aerial vehicle meets the switching condition of the flight mode according to the current flight state information of the unmanned aerial vehicle and/or the current environment information of the unmanned aerial vehicle (S302); and when the unmanned aerial vehicle meets the flight mode switching condition, switching the current flight mode of the unmanned aerial vehicle (S303). Through this kind of mode, can improve unmanned aerial vehicle security and reliability in flight mode switches over the in-process.)

1. A flight control method of an unmanned aerial vehicle is characterized by comprising the following steps:

acquiring a flight mode switching instruction, wherein the flight mode switching instruction is used for indicating the flight mode of the unmanned aerial vehicle to be switched between a rotor wing flight mode and a fixed wing flight mode;

determining whether the unmanned aerial vehicle meets a flight mode switching condition or not according to the current flight state information of the unmanned aerial vehicle and/or the current environment information of the unmanned aerial vehicle;

and when the unmanned aerial vehicle meets the flight mode switching condition, switching the current flight mode of the unmanned aerial vehicle.

2. The method of claim 1,

the flight state information includes any one or more of position error information, attitude error information, velocity error information, acceleration error information, angular acceleration error information, and angular velocity error information.

3. The method of claim 1, wherein the environmental information comprises environmental wind information and/or obstacle information.

4. The method of claim 1, wherein the flight mode switching instructions are for instructing switching the flight mode of the drone from the rotor flight mode to the fixed-wing flight mode, the method further comprising:

acquiring lateral speed error information or lateral offset error information of the unmanned aerial vehicle;

determining a target attitude angle of the unmanned aerial vehicle according to the lateral speed error information or the lateral offset error information;

and controlling the attitude of the unmanned aerial vehicle according to the target attitude angle in the process of switching the flight mode of the unmanned aerial vehicle from the rotor flight mode to the fixed wing flight mode.

5. The method of claim 4, further comprising:

acquiring the moment of a rotor motor of the unmanned aerial vehicle and the moment of a control surface of a fixed wing;

according to the moment of rotor motor and first preset weight, and the moment of fixed wing control surface and the second preset weight, right unmanned aerial vehicle's gesture is controlled.

6. The method of claim 4, wherein the drone is determined to successfully switch to a fixed-wing flight mode when the drone satisfies one or more of the following conditions:

the unmanned aerial vehicle accelerates to a preset speed range, and the flight height error of the unmanned aerial vehicle is smaller than a preset error value; alternatively, the first and second electrodes may be,

unmanned aerial vehicle's rotor motor's thrust is less than and presets the thrust value at presetting the time horizon, just unmanned aerial vehicle's flight height error is less than and presets the error value.

7. The method of claim 6, further comprising:

when the drone has not successfully switched from a rotor flight mode to a fixed-wing flight mode within a first specified time frame, then controlling the drone to switch back to the rotor flight mode.

8. The method of claim 1, wherein the flight mode switching instructions are for instructing switching the flight mode of the drone from the fixed-wing flight mode to the rotor flight mode, and prior to switching the flight mode of the drone from the fixed-wing flight mode to the rotor flight mode, further comprising:

and controlling the attitude angle of the unmanned aerial vehicle to be smaller than a preset angle threshold value.

9. The method of claim 8, further comprising:

acquiring the ambient wind speed of the unmanned aerial vehicle in the fixed wing flight mode;

determining a target pitch angle of the unmanned aerial vehicle according to the ambient wind speed;

and controlling the unmanned aerial vehicle to fly at the target pitch angle in a deceleration mode.

10. The method of claim 8, further comprising:

acquiring the ambient wind speed and the flight speed of the unmanned aerial vehicle in real time in the process that the flight mode of the unmanned aerial vehicle is switched from the fixed wing flight mode to the rotor wing flight mode;

determining a target pitch angle according to the ambient wind speed and the flight speed of the unmanned aerial vehicle;

and controlling the unmanned aerial vehicle to fly at the target pitch angle in a deceleration mode.

11. The method of claim 8, further comprising:

acquiring lateral speed error information or lateral offset error information of the unmanned aerial vehicle;

determining a target attitude angle of the unmanned aerial vehicle according to the lateral speed error information or the lateral offset error information;

and in the process of switching the current fixed wing flight mode of the unmanned aerial vehicle to the rotor wing flight mode, controlling the attitude of the unmanned aerial vehicle according to the target attitude angle.

12. The method of claim 8, wherein the drone is determined to successfully switch to the rotor flight mode when the drone satisfies the following condition:

the unmanned aerial vehicle decelerates to a preset speed threshold.

13. The method of claim 12, further comprising:

when the drone is not switched from the fixed-wing flight mode to the rotor flight mode within the second specified time range, then controlling the drone to switch back to the rotor flight mode.

14. The method of claim 1, further comprising:

when the unmanned aerial vehicle does not meet the flight mode switching condition, outputting prompt information to a control terminal;

wherein, the prompt message is used for prompting the user to adjust the flight state of the unmanned aerial vehicle.

15. The method of claim 1, further comprising:

and outputting prompt information to a control terminal at the starting moment, the ending moment and the intermediate process of the switching flight mode of the unmanned aerial vehicle.

16. A flight control device comprising a memory and a processor;

the memory to store program instructions;

the processor, configured to invoke the program instructions, and when the program instructions are executed, configured to:

and when the unmanned aerial vehicle meets the flight mode switching condition, switching the current flight mode of the unmanned aerial vehicle.

17. The apparatus of claim 16,

18. The apparatus of claim 16,

the environmental information includes environmental wind information and/or obstacle information.

19. The apparatus of claim 16, wherein the flight mode switching instructions are configured to instruct switching the flight mode of the drone from the rotor flight mode to the fixed-wing flight mode, the processor further configured to:

acquiring lateral speed error information or lateral offset error information of the unmanned aerial vehicle;

determining a target attitude angle of the unmanned aerial vehicle according to the lateral speed error information or the lateral offset error information;

20. The device of claim 19, wherein the processor is further configured to:

acquiring the moment of a rotor motor of the unmanned aerial vehicle and the moment of a control surface of a fixed wing;

according to the moment of rotor motor and first preset weight, and the moment of fixed wing control surface and the second preset weight, right unmanned aerial vehicle's gesture is controlled.

21. The apparatus of claim 19, wherein the drone is determined to successfully switch to a fixed-wing flight mode when the drone satisfies one or more of the following conditions:

22. The device of claim 19, wherein the processor is further configured to:

23. The apparatus of claim 16, wherein the flight mode switching instructions are configured to instruct switching the flight mode of the drone from the fixed-wing flight mode to the rotor flight mode, and wherein the processor is further configured to, prior to switching the flight mode of the drone from the fixed-wing flight mode to the rotor flight mode:

and controlling the attitude angle of the unmanned aerial vehicle to be smaller than a preset angle threshold value.

24. The device of claim 23, wherein the processor is further configured to:

acquiring the ambient wind speed of the unmanned aerial vehicle in the fixed wing flight mode;

determining a target pitch angle of the unmanned aerial vehicle according to the ambient wind speed;

and controlling the unmanned aerial vehicle to fly at the target pitch angle in a deceleration mode.

25. The device of claim 23, wherein the processor is further configured to:

determining a target pitch angle according to the ambient wind speed and the flight speed of the unmanned aerial vehicle;

and controlling the unmanned aerial vehicle to fly at the target pitch angle in a deceleration mode.

26. The device of claim 23, wherein the processor is further configured to:

acquiring lateral speed error information or lateral offset error information of the unmanned aerial vehicle;

determining a target attitude angle of the unmanned aerial vehicle according to the lateral speed error information or the lateral offset error information;

27. The apparatus of claim 23, wherein the drone is determined to successfully switch to the rotor flight mode when the drone satisfies the following condition:

the unmanned aerial vehicle decelerates to a preset speed threshold.

28. The device of claim 27, wherein the processor is further configured to:

when the drone is not switched from the fixed-wing flight mode to the rotor flight mode within the second specified time range, then controlling the drone to switch back to the rotor flight mode.

29. The device of claim 16, wherein the processor is further configured to:

when the unmanned aerial vehicle does not meet the flight mode switching condition, outputting prompt information to a control terminal;

wherein, the prompt message is used for prompting the user to adjust the flight state of the unmanned aerial vehicle.

30. The device of claim 16, wherein the processor is further configured to:

and outputting prompt information to a control terminal at the starting moment, the ending moment and the intermediate process of the switching flight mode of the unmanned aerial vehicle.

31. An unmanned aerial vehicle, wherein the unmanned aerial vehicle has a rotor flight mode and a fixed-wing flight mode, the unmanned aerial vehicle comprising:

a body;

the power system is arranged on the airframe and used for providing power for the unmanned aerial vehicle to move;

a flight control apparatus as claimed in any one of claims 16 to 30.

32. A computer-readable storage medium, in which a computer program is stored which, when being executed by a processor, carries out the method according to any one of claims 1 to 15.

Technical Field

The invention relates to the technical field of control, in particular to a flight control method and equipment of an unmanned aerial vehicle and the unmanned aerial vehicle.

Background

Vertical Take-Off and Landing (VTOL) unmanned aerial vehicle is a novel aircraft which develops rapidly in recent years, and the VTOL unmanned aerial vehicle has the capabilities of taking Off and Landing vertically of a rotor aircraft and hovering and flying at low speed at the same time, and has the capability of flying at high speed with lower energy consumption by a fixed wing aircraft, thereby having extremely strong industrial application value.

The unmanned aerial vehicle that takes off and land perpendicularly's flight in-process needs switch between rotor flight mode and fixed wing flight mode, and the unmanned aerial vehicle that takes off and land appears switching failure easily or at the switching in-process unmanned aerial vehicle and hit the circumstances such as barrier at present when carrying out flight mode switching. Therefore, how to more effectively control the flight mode switching process of the VTOL UAV has very important significance.

Disclosure of Invention

The embodiment of the invention provides a flight control method and equipment of an unmanned aerial vehicle and the unmanned aerial vehicle, which can improve the reliability and safety of mode switching of the unmanned aerial vehicle in the flight process and improve the user experience.

In a first aspect, an embodiment of the present invention provides a flight control method for an unmanned aerial vehicle, including:

and when the unmanned aerial vehicle meets the flight mode switching condition, switching the current flight mode of the unmanned aerial vehicle.

In a second aspect, an embodiment of the present invention provides a flight control device, including a memory and a processor;

the memory to store program instructions;

the processor, configured to invoke the program instructions, and when the program instructions are executed, configured to:

and when the unmanned aerial vehicle meets the flight mode switching condition, switching the current flight mode of the unmanned aerial vehicle.

In a third aspect, an embodiment of the present invention provides an unmanned aerial vehicle, including:

a body;

the power system is arranged on the airframe and used for providing power for the unmanned aerial vehicle to move;

a flight control apparatus as claimed in the second aspect above.

In a fourth aspect, the present invention provides a computer-readable storage medium, in which a computer program is stored, and the computer program, when executed by a processor, implements the method according to the first aspect.

In the embodiment of the invention, when acquiring a flight mode switching instruction, a flight control device can determine whether the unmanned aerial vehicle meets a flight mode switching condition according to the current flight state information of the unmanned aerial vehicle and/or the current environment information of the unmanned aerial vehicle; when determining unmanned aerial vehicle satisfies flight mode and switches the condition, flight control equipment can be right unmanned aerial vehicle current flight mode switches to improve unmanned aerial vehicle and carry out mode switching's reliability and security at the flight in-process.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings without creative efforts.

Fig. 1 is a configuration diagram of an unmanned aerial vehicle according to an embodiment of the present invention;

fig. 2 is a schematic structural diagram of a flight control system of an unmanned aerial vehicle according to an embodiment of the present invention;

fig. 3 is a schematic flow chart of a flight control method of an unmanned aerial vehicle according to an embodiment of the present invention;

fig. 4 is a schematic flow chart of a flight control method of another unmanned aerial vehicle according to an embodiment of the present invention;

FIG. 5 is a schematic structural diagram of a flight control apparatus provided in an embodiment of the present invention;

FIG. 6 is a schematic diagram of a flight path during switching flight modes according to an embodiment of the present invention.

Detailed Description

The technical solutions in the embodiments of the present invention will be described clearly below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

Some embodiments of the invention are described in detail below with reference to the accompanying drawings. The embodiments described below and the features of the embodiments can be combined with each other without conflict.

The flight control method of the unmanned aerial vehicle provided by the embodiment of the invention can be executed by a flight control system of the unmanned aerial vehicle. Wherein, the flight control system of unmanned aerial vehicle includes flight control equipment and unmanned aerial vehicle, and in certain embodiments, the flight control equipment can install on unmanned aerial vehicle, and in certain embodiments, the flight control equipment can be independent of unmanned aerial vehicle in space, and in certain embodiments, the flight control equipment can be unmanned aerial vehicle's part, promptly the unmanned aerial vehicle includes flight control equipment.

In some embodiments, the drone may include, but is not limited to, a vertical take-off and landing drone including a compound, tilt rotor, rotary wing, tail seat, etc. drone, and a typical compound vertical take-off and landing fixed wing drone configuration is shown in fig. 1, where fig. 1 is a configuration diagram of a drone provided by an embodiment of the present invention. As shown in fig. 1, the configuration includes a set of multi-rotor power systems 11 and a set of fixed-wing power systems 12. Only rotor power system 11 is active when hovering; when the flight mode needs to be converted into the fixed wing flight mode, the fixed wing power system 12 is started, and the aircraft flies before accelerating; when the forward flight speed reaches the preset cruising speed range, the fixed wing power system 12 takes over the unmanned aerial vehicle, and the rotor wing power system 11 is closed. When needs convert rotor flight mode into from fixed wing flight mode, control unmanned aerial vehicle slows down to predetermineeing speed threshold value, and rotor driving system opens 11, and unmanned aerial vehicle switches into rotor flight mode 11.

In one embodiment, the primary task of the drone to switch from rotor flight mode to fixed-wing flight mode is to have the drone obtain sufficient airspeed during which the drone will fly a distance in the direction of the nose to smoothly switch to fixed-wing flight mode; unmanned aerial vehicle carries out reasonable speed reduction from the high-speed flight state of fixed wing flight mode from the main task that fixed wing flight mode switched to rotor flight mode, and unmanned aerial vehicle also can fly a section distance along the aircraft nose direction at this in-process to can smooth switch to rotor flight mode.

In the embodiment of the invention, when acquiring a flight mode switching instruction, a flight control device in a flight control system of the unmanned aerial vehicle can determine whether the unmanned aerial vehicle meets a flight mode switching condition according to current flight state information of the unmanned aerial vehicle and/or current environment information of the unmanned aerial vehicle; and when the unmanned aerial vehicle meets the flight mode switching condition, switching the current flight mode of the unmanned aerial vehicle. In certain embodiments, the flight mode switching instructions are for instructing the drone to switch flight modes between a rotor flight mode and a fixed-wing flight mode. In some embodiments, the flight mode switching instruction may be sent by a control terminal (such as a remote controller, a ground station device, and the like) to a flight control device; in other embodiments, the flight mode switching instruction may also be automatically generated by the unmanned aerial vehicle according to an automatic flight route planning policy, and the embodiment of the present invention is not particularly limited.

In one embodiment, if the current flight mode of the drone is a rotor flight mode, and the flight mode switching instruction is used to instruct the flight mode of the drone to switch from the rotor flight mode to the fixed-wing flight mode, the flight control device may control the drone to switch from the rotor flight mode to the fixed-wing flight mode upon acquiring the flight mode switching instruction.

In one embodiment, the flight control device may detect flight status information of the drone and/or environmental information where the drone is currently located before controlling the drone to switch from a rotor flight mode to a fixed-wing flight mode, and determine whether the drone satisfies a flight mode switching condition according to the flight status information of the drone and/or the environmental information where the drone is located, and switch the current flight mode of the drone when the drone satisfies the flight mode switching condition. Through this kind of embodiment, can improve unmanned aerial vehicle and carry out validity and security that the mode switched.

In one embodiment, the flight status information includes any one or more of position error information, attitude error information, velocity error information, acceleration error information, angular acceleration error information, and angular velocity error information.

In one embodiment, when the flight status of the drone satisfies: and when the acceleration error information is less than a first preset threshold, the speed error information is less than a second preset threshold, the position error information is less than a third preset threshold, the angular acceleration error information is less than a fourth preset threshold, the angular speed error information is less than a fifth preset threshold, and the attitude error information is less than any one or more of a sixth preset threshold, determining that the unmanned aerial vehicle meets the flight mode switching condition. In some embodiments, the calculation manner of the error information may be a mean value, a variance, a standard deviation, and the like of a difference between an expected value and an actual value within a period of time.

In one embodiment, the environmental information includes environmental wind information including a wind direction and a wind speed of the environmental wind. Unmanned aerial vehicle can pass through sensor perception or measure the wind speed and the wind direction of the current environment of unmanned aerial vehicle, and judge whether wind speed and wind direction satisfy preset condition, if satisfy, then can confirm unmanned aerial vehicle satisfies flight mode and switches over the condition. In some embodiments, the wind speed in the ambient wind information is determined according to a module length of the ambient wind in the body coordinate system, and the wind direction in the ambient wind information is determined according to a vector direction of the ambient wind in the body coordinate system. In some embodiments, the body coordinate system may be a coordinate system in which a head direction of the drone is an x-axis direction, a right side direction of a head of the drone is a y-axis direction, and a downward direction of the drone is a z-axis direction.

In some embodiments, when the ambient wind direction is different, the wind speed conditions for switching the drone from the rotor flight mode to the fixed-wing flight mode are different, for example: when the ambient wind is opposite to the nose direction, i.e. upwind, the wind speed condition for switching the drone from the rotor flight mode to the fixed-wing flight mode is not greater than 8m/s, and when the ambient wind is perpendicular to the nose direction, the wind speed condition for switching the drone from the rotor flight mode to the fixed-wing flight mode is not greater than 5 m/s.

In one embodiment, the environment information includes obstacle information including, but not limited to, the height of an obstacle and the distance from the obstacle to the drone, and if the height of the obstacle and the distance from the obstacle to the drone in the environment where the drone is currently located satisfy preset conditions, it may be determined that the drone satisfies a flight mode switching condition.

In some embodiments, the drone may determine the geographic location of the drone via a Global Positioning System (GPS). Optionally, the height of the unmanned aerial vehicle from the ground may be obtained by fusing one or more of a barometer, an Inertial Measurement Unit (IMU), an image sensor, an ultrasonic sensor, and a Time of flight (TOF) sensor. Further, the unmanned aerial vehicle can obtain obstacle information in the environment such as buildings, mountains and the like around the unmanned aerial vehicle by combining with a high-precision map. It should be noted that the positioning system of the unmanned aerial vehicle includes, but is not limited to, any one or more of a GPS positioning system, a beidou positioning system, and a Real-time kinematic (RTK) carrier-phase differential positioning system. For example, assuming that the current ground clearance of the drone is 50m, there is a hill 100m high directly in front of the drone, and if the drone makes a switch from the rotor flight mode to the fixed-wing flight mode by accelerating forward, the drone will hit the hill, so in order to ensure the reliability and safety of the drone in switching flight modes, the drone is not allowed to switch from the rotor flight mode to the fixed-wing flight mode.

In an embodiment, when the unmanned aerial vehicle does not satisfy the flight mode switching condition, the unmanned aerial vehicle may send a prompt message to the control terminal, and a prompt module (which may be APP) through the control terminal prompts a user to respond to constraints such as a heading and a height to the ambient wind by adjusting the flight state of the unmanned aerial vehicle, so that the adjusted unmanned aerial vehicle satisfies the flight mode switching condition.

For example, when the ambient wind perpendicular to the nose direction of 6m/s causes the drone not to satisfy the flight mode switching condition for switching from the rotor flight mode to the fixed-wing flight mode, the drone heading may be adjusted by prompting the user so that the drone satisfies the flight mode switching condition. For another example, when a hill 100m high in front of the drone is such that the drone does not satisfy the flight mode switching condition for switching from the rotor flight mode to the fixed-wing flight mode, the drone may satisfy the flight mode switching condition by prompting the user to raise the drone to more than 100m or adjust the head to a direction without a risk of collision.

In some embodiments, the prompt module of the control terminal is mainly used for interacting with a user, and the interaction path includes but is not limited to a mobile phone APP voice, a mobile phone APP character, a remote controller vibration, a remote controller liquid crystal display screen and the like. Taking the switching to the fixed-wing flight mode as an example: wind direction and wind speed are unsuitable to be switched to the fixed wing flight mode, cell-phone APP voice prompt: when the wind speed is too high, the nose turns left or falls. "; another example is: the geographical environment is not suitable for being switched to a fixed wing flight mode, and the mobile phone APP carries out voice prompt: "Forward obstruction, right hand turn or lift of the handpiece. "; another example is: when beginning to switch over to fixed wing flight mode remote controller vibration, cell-phone APP voice prompt: and starting to switch to a fixed wing flight mode, wherein the wind speed is 5m/s, the airspeed is 10m/s, the airspeed is 15m/s and the airspeed is 20m/s, and entering the fixed wing flight mode. "; another example is: and when the fixed wing flight mode is switched to, the remote controller vibrates once again.

Take switching to rotor flight mode as an example: when beginning to switch to rotor flight mode remote controller vibration, cell-phone APP voice prompt: and starting to switch to a rotor flight mode, wherein the wind speed is 4m/s, the airspeed is 19m/s, the airspeed is 15m/s, the airspeed is 10m/s and the airspeed is 5m/s, and entering the rotor flight mode. When the switching to the rotor flight mode is completed, the remote controller vibrates once again.

The implementation mode of sending the prompt information to the control terminal can prompt the user how to operate and the current state, flight mode and other information of the unmanned aerial vehicle, so that the user experience is improved.

In one embodiment, during the process of switching the unmanned aerial vehicle from the rotor flight mode to the fixed-wing flight mode, the pulling force generated by the accelerated rotation of the pull-forward motor of the unmanned aerial vehicle can control the unmanned aerial vehicle to advance in an accelerated manner, and when the wind direction of the ambient wind has a large included angle with the direction of the head of the unmanned aerial vehicle, the direction of the route of the unmanned aerial vehicle when the unmanned aerial vehicle switches the flight mode may not be consistent with the direction of the target route. In order to enable the unmanned aerial vehicle to fly along the target air route when the flight mode is switched, the target attitude angle of the unmanned aerial vehicle can be calculated and controlled according to the lateral speed error (namely the difference value between the expected lateral speed and the actual lateral speed) or the lateral offset error (the distance between the target air route and the actual air route), so that the real-time control of the lateral speed or the lateral offset of the unmanned aerial vehicle is realized. In some embodiments, the target attitude angle of the drone may include, but is not limited to, any one or more of a target roll angle, a target pitch angle, and a target yaw angle. Through this kind of embodiment, can be under the side wind environment, the wind direction of ambient wind promptly with when unmanned aerial vehicle's aircraft nose direction has great contained angle, reduce unmanned aerial vehicle's lateral velocity or lateral offset error, control unmanned aerial vehicle flies according to the target course. In some embodiments, the target course direction coincides with a nose direction of the VTOL drone at a start time of the switch flight mode.

Specifically, the description may be given by taking fig. 6 as an example, where fig. 6 is a schematic view of a flight path in a process of switching a flight mode according to an embodiment of the present invention, and fig. 6 is a schematic view of a flight path in a process of switching the unmanned aerial vehicle from a rotor flight mode to a fixed-wing flight mode. Suppose that the unmanned aerial vehicle starts to switch from the rotor flight mode to the fixed-wing flight mode from the point A, the target flight line of the unmanned aerial vehicle switched from the rotor flight mode to the fixed-wing flight mode is an AB flight line, the direction of the nose of the unmanned aerial vehicle at the point A is the direction from A to B, and the included angle between the wind direction of the environmental wind V1 and the AB flight line (namely the direction of the nose) is 90 degrees, so that a larger included angle is met. The course direction of the drone when switching from the rotor flight mode to the fixed-wing flight mode starting from point a is actually the direction from a to C, the actual course being the AC course, due to the influence of the ambient wind V1. Therefore, the unmanned aerial vehicle has deviation on the flight path when the unmanned aerial vehicle is switched from the rotor flight mode to the fixed wing flight mode, and the distance between the AB flight path and the AC flight path can be determined as a side offset error, for example, when the unmanned aerial vehicle flies to a point D, the side offset error is a distance D between a point E on the AB flight path and a point D on the AC flight path; and determining the difference between the expected lateral speed and the actual lateral speed as a lateral speed error, and if the expected lateral speed is 0 and the actual lateral speed is V2, determining the lateral speed error as V2. Therefore, in order to make the unmanned aerial vehicle fly along the AB route as much as possible when switching from the rotor flight mode to the fixed-wing flight mode, a target attitude angle (e.g., roll angle) of the unmanned aerial vehicle can be calculated and controlled according to the lateral speed error V2 or the lateral offset error (e.g., d) so that the unmanned aerial vehicle flies as close to the AB route as possible, the lateral offset error between the AB route and the AC route is reduced, and the unmanned aerial vehicle is controlled to fly according to the target route.

It should be noted that the target route may be a line segment as shown in fig. 10, or may be a ray starting from point a. That is, the location of the ending point of the target route may not be limited.

In one embodiment, the unmanned aerial vehicle is in the process of switching from the rotor flight mode to the fixed wing flight mode, the rotor motor and the fixed wing control surface generate moment simultaneously, and the unmanned aerial vehicle control device can control the attitude of the unmanned aerial vehicle according to the moment of the rotor motor and the first preset weight, and the moment of the fixed wing control surface and the second preset weight so as to control the attitude of the unmanned aerial vehicle in the flight process.

In one embodiment, when the drone accelerates to a preset speed range during the switching from the rotor flight mode to the fixed-wing flight mode, the flight altitude error of the drone is less than a preset error value; or, the thrust of unmanned aerial vehicle's rotor motor is less than and presets the thrust value at presetting the time horizon, just when unmanned aerial vehicle's flight height error is less than and presets the error value, can confirm that unmanned aerial vehicle successfully switches to fixed wing flight mode.

In one embodiment, the drone may be controlled to switch back to the rotor flight mode if the drone fails to switch from the rotor flight mode to the fixed-wing flight mode within a first specified time frame.

In one embodiment, if the current flight mode of the drone is a fixed-wing flight mode, and the flight mode switching instruction is used to instruct the flight mode of the drone to switch from the fixed-wing flight mode to a rotor flight mode, the flight control device may control the drone to switch from the fixed-wing flight mode to the rotor flight mode upon acquiring the flight mode switching instruction.

In one embodiment, during the switching of the drone from the fixed-wing flight mode to the rotor flight mode, the target pitch angle of the drone may vary according to the wind speed in order to ensure that the drone can have similar braking distances at different wind speeds and wind directions. In some embodiments, the braking distance is a flight distance of the drone during a transition from a fixed-wing flight mode to a rotor flight mode.

In one embodiment, the flight control device may calculate a target pitch angle at which the drone decelerates prior to switching to rotor flight mode based on ambient wind speed at the moment of switching from fixed-wing flight mode to rotor flight mode.

In another embodiment, the flight control device may calculate the target pitch angle in real time based on the real-time wind speed and the current airspeed of the drone during the transition from the fixed-wing flight mode to the rotor flight mode.

In one embodiment, the flight control device may control the lateral speed or lateral offset of the drone by controlling the attitude angle during the transition from the fixed-wing flight mode to the rotor flight mode.

In one embodiment, when the flight speed of the drone decelerates to a preset speed threshold, it may be determined that the drone successfully switches to the rotor flight mode; in another embodiment, the drone may be controlled to switch back to the rotor flight mode when the drone does not switch from the fixed-wing flight mode to the rotor flight mode within the second specified time range.

In some embodiments, if the unmanned aerial vehicle is not satisfied with the flight mode switching condition for switching from the fixed-wing flight mode to the rotor flight mode, a prompt message may be output to the control terminal to improve user experience, and the specific embodiments and examples are as described above and are not described herein again.

The following describes schematically a flight control system of an unmanned aerial vehicle according to an embodiment of the present invention with reference to fig. 2.

Referring to fig. 2, fig. 2 is a schematic structural diagram of a flight control system of an unmanned aerial vehicle according to an embodiment of the present invention. The flight control system of unmanned aerial vehicle includes: unmanned aerial vehicle 22, control terminal 20. The drone 22 has a rotor flight mode and a fixed-wing flight mode. In some embodiments, the flight control device 21 is disposed in the drone 22 and may establish a communication connection with other devices in the drone (e.g., the power system 221) via a wired communication connection. In other embodiments, the drone 22 and the flight control device 21 are independent of each other, for example, the flight control device 21 is disposed in a cloud server, and establishes a communication connection with the drone 22 through a wireless communication connection. In certain embodiments, the flight control device 21 may be a flight controller. The control terminal 20 may be a remote control, a smart phone, a tablet computer, a laptop computer, a watch, a bracelet, and the like, and combinations thereof. The control terminal 20 may send remote control instructions to the drone 22, and the drone 22 may transmit images to the control terminal 20 in real time. In an implementation, the control terminal may further display a prompt message sent to the control terminal by the drone.

In the embodiment of the present invention, when the flight control device 21 acquires the flight mode switching instruction, it may determine whether the unmanned aerial vehicle 22 meets the flight mode switching condition according to the current flight state information of the unmanned aerial vehicle 22 and/or the current environment information of the unmanned aerial vehicle 22, and if the unmanned aerial vehicle 22 meets the flight mode switching condition, the current flight mode of the unmanned aerial vehicle may be switched. In certain embodiments, the current flight mode of the drone 22 includes a rotor flight mode or a fixed-wing flight mode. The drone 22 includes a rotor power system and a fixed-wing power system, the rotor power system providing the flight power of the drone 22 in the rotor flight mode, and the fixed-wing power system providing the flight power of the drone 22 in the fixed-wing flight mode.

The following describes schematically a flight control method of an unmanned aerial vehicle according to an embodiment of the present invention with reference to fig. 3 to 5.

Referring to fig. 3 specifically, fig. 3 is a schematic flowchart of a flight control method of an unmanned aerial vehicle according to an embodiment of the present invention, where the method may be executed by a flight control device, and a specific explanation of the flight control device is as described above. Specifically, the method of the embodiment of the present invention includes the following steps.

S301: obtaining a flight mode switch instruction for instructing the flight mode of the drone to switch between a rotor flight mode and a fixed wing flight mode.

In the embodiment of the invention, the flight control device can acquire a flight mode switching instruction, and the flight mode switching instruction is used for indicating the flight mode of the unmanned aerial vehicle to be switched between a rotor flight mode and a fixed wing flight mode. In some embodiments, the flight mode switching instruction may be sent by a control terminal to the flight control device; in other embodiments, the flight mode switching instruction may be automatically generated by the drone according to a route planning strategy for automatic flight, and is not specifically limited herein.

In some embodiments, the flight mode switching instruction may be configured to instruct the drone to switch from a rotor flight mode to a fixed-wing flight mode, where switching of the drone from the rotor flight mode to the fixed-wing flight mode means controlling the heading of the drone to fly at an accelerated speed along the nose orientation of the drone during switching from the rotor flight mode to the fixed-wing flight mode, automatically turning off the rotor flight mode and turning on the fixed-wing flight mode, and when the speed of the drone accelerates to a preset speed range and the flight altitude error of the drone is smaller than a preset error value, switching from the rotor flight mode to the fixed-wing flight mode is implemented.

S302: and determining whether the unmanned aerial vehicle meets the switching condition of the flight mode according to the current flight state information of the unmanned aerial vehicle and/or the current environment information of the unmanned aerial vehicle.

In the embodiment of the invention, the flight control device can determine whether the unmanned aerial vehicle meets the flight mode switching condition according to the current flight state information of the unmanned aerial vehicle and/or the current environment information of the unmanned aerial vehicle.

In some embodiments, the position error information includes, but is not limited to, a mean, a variance, a standard deviation, etc. of the difference between the desired position and the actual position within a preset time range; in some embodiments, the actual position may be obtained by a positioning system of the drone. In some embodiments, the acceleration error information includes, but is not limited to, a mean, a variance, a standard deviation, etc. of the difference between the desired acceleration and the actual acceleration over a preset time range. In certain embodiments, the angular acceleration error information includes, but is not limited to, a mean, a variance, a standard deviation, etc. of the difference between the desired angular acceleration and the actual angular acceleration over a preset time range. In some embodiments, the angular velocity error information includes, but is not limited to, a mean, a variance, a standard deviation, etc., of differences between the desired angular velocity and the actual angular velocity over a preset time range.

In one embodiment, when the flight status of the drone satisfies: and when the acceleration error information is less than any one or more of a first preset threshold, the speed error information is less than a second preset threshold, the position error information is less than a third preset threshold, the angular acceleration error information is less than a fourth preset threshold, the angular speed error information is less than a fifth preset threshold, and the attitude error information is less than a sixth preset threshold, determining that the unmanned aerial vehicle meets the flight mode switching condition.

In one embodiment, the environmental information includes environmental wind information and/or obstacle information. The environment wind information comprises the wind speed and the wind direction of environment wind, and the obstacle information comprises the height of an obstacle and the distance from the obstacle to the unmanned aerial vehicle. The unmanned aerial vehicle can sense or measure the wind speed and the wind direction of the current environment where the unmanned aerial vehicle is located through a sensor. The unmanned aerial vehicle can determine the height of the obstacle and the distance from the obstacle to the unmanned aerial vehicle through the positioning module and the high-precision map. Unmanned aerial vehicle satisfies flight mode and switches the condition, include: the wind speed and the wind direction in the environmental wind information meet preset range thresholds; and/or the height of the obstacle and the distance from the obstacle to the unmanned aerial vehicle meet preset conditions.

S303: and when the unmanned aerial vehicle meets the flight mode switching condition, switching the current flight mode of the unmanned aerial vehicle.

In the embodiment of the invention, when the unmanned aerial vehicle meets the flight mode switching condition, the flight control equipment can switch the current flight mode of the unmanned aerial vehicle.

In one embodiment, the flight mode switching instruction is used to instruct to switch the flight mode of the drone from the rotor flight mode to the fixed-wing flight mode, the flight control device may obtain lateral speed error information or lateral offset error information of the drone and determine a target attitude angle of the drone according to the lateral speed error information or the lateral offset error information, and the attitude of the drone may be controlled according to the target attitude angle in the process of switching the flight mode of the drone from the rotor flight mode to the fixed-wing flight mode. Control through the gesture to unmanned aerial vehicle, help reducing unmanned aerial vehicle's lateral velocity error or lateral deviation distance error reduce unmanned aerial vehicle and deviate from the error of air route when carrying out flight mode switching to ensure unmanned aerial vehicle reliability and security at the flight in-process.

For example, the flight control device may obtain an actual lateral velocity of the drone during the transition from the rotor flight mode to the fixed-wing flight mode, and calculate a lateral velocity error based on the actual lateral velocity and the desired lateral velocity. The flight control equipment can obtain the target roll angle of the unmanned aerial vehicle through calculation of a lateral controller, and determine a roll angle error according to the target roll angle and an actual roll angle. And the flight control equipment can control the attitude of the unmanned aerial vehicle according to the roll angle error through an attitude controller.

It can be seen that through this kind of implementation to the posture that unmanned aerial vehicle switches over to fixed wing flight mode in-process from rotor flight mode controls, can reduce the error between actual lateral velocity and the expectation lateral velocity, improves the lateral velocity control accuracy when unmanned aerial vehicle switches over to fixed wing flight mode under the crosswind environment.

For another example, the flight control device may obtain an actual flight path of the unmanned aerial vehicle in a process of switching from a rotor flight mode to a fixed-wing flight mode, calculate a lateral offset error according to the actual flight path and a target flight path, and send the lateral offset error to the lateral controller, so that the lateral controller calculates a target roll angle of the unmanned aerial vehicle. The method for calculating and obtaining the side offset error according to the actual route and the target route comprises the following steps: and calculating to obtain a side offset error according to the position of the unmanned aerial vehicle in the actual air route at the current moment and the target air route. The flight control equipment can acquire the actual roll angle of the unmanned aerial vehicle, and determine the roll angle error according to the target roll angle and the actual roll angle. The flight control equipment can send the roll angle error to an attitude controller, so that the attitude controller controls the attitude of the unmanned aerial vehicle according to the roll angle error.

Therefore, through the implementation mode that the attitude of the unmanned aerial vehicle is controlled in the process of switching from the rotor flight mode to the fixed wing flight mode, the lateral position precision of the unmanned aerial vehicle in the process of switching to the fixed wing flight mode in the crosswind environment can be improved, and the error between the actual air route and the target air route of the unmanned aerial vehicle in the process of switching to the fixed wing flight mode is reduced.

In one embodiment, the flight control device may obtain a torque of a rotor motor of the unmanned aerial vehicle and a torque of a control surface of a fixed wing, and control the attitude of the unmanned aerial vehicle according to the torque of the rotor motor and a first preset weight, and the torque of the control surface of the fixed wing and a second preset weight. Through this kind of embodiment, can provide more nimble control moment to control unmanned aerial vehicle better and switching flight mode in-process gesture, ensure unmanned aerial vehicle safety at the flight in-process.

In one embodiment, the drone may be determined to successfully switch to a fixed-wing flight mode when the drone satisfies one or more of the following conditions: the unmanned aerial vehicle accelerates to a preset speed range, and the flight height error of the unmanned aerial vehicle is smaller than a preset error value; or, unmanned aerial vehicle's rotor motor's thrust is less than and presets the thrust value at presetting the time horizon, just unmanned aerial vehicle's flying height error is less than and presets the error value. The fly-height error is the difference between the desired height and the actual height.

For example, assuming that the preset speed range is 7m/s-8m/s, the current speed of the drone is 3m/s, if the drone accelerates to a range of 7m/s-8m/s when a flight mode switching condition for switching from a rotor flight mode to a fixed wing flight mode is satisfied, and the flight altitude error of the drone is smaller than a preset error value, it may be determined that the drone is successfully switched from the rotor flight mode to the fixed wing flight mode.

For another example, assuming that a preset thrust value is 2 newtons, if the thrust of the rotor motor of the drone is smaller than the preset thrust value of 2 newtons within 1 minute of a preset time range, and the flight height error of the drone is smaller than a preset error value of 0.5m, it may be determined that the drone is successfully switched from the rotor flight mode to the fixed-wing flight mode.

Through this kind of embodiment, can improve the reliability of unmanned aerial vehicle in switching from rotor flight mode to fixed wing flight mode.

In one embodiment, the drone may be controlled to switch back to the rotor flight mode when the drone has not successfully switched from the rotor flight mode to the fixed-wing flight mode within a first specified time frame.

In one embodiment, when the drone has not successfully switched from a rotor flight mode to a fixed-wing flight mode within a first specified time frame, then the drone's fixed-wing motor may be turned off and controlled to slow down to a preset speed threshold, thereby switching back to the rotor flight mode. Through the implementation mode of switching the rotary wing flight mode under the condition that the switching is overtime to the fixed wing flight mode, the possibility that the unmanned aerial vehicle flies out of a safe region due to long-time accelerated flight in the switching process can be avoided, so that the dangers such as collision and the like are caused, the protection of the unmanned aerial vehicle is realized, and the safety of the unmanned aerial vehicle in the flight mode switching process is improved.

For example, assuming that the first specified time range is 3 minutes and the current flight speed is 6m/s, if the drone fails to switch from the rotor flight mode to the fixed-wing flight mode within 3 minutes, the fixed-wing flight mode of the drone may be turned off, and the drone is controlled to decelerate from 6m/s to a preset speed threshold of 3m/s, thereby switching back to the rotor flight mode.

In one embodiment, when it is detected that the unmanned aerial vehicle does not satisfy the flight mode switching condition, prompt information may be output to a control terminal; wherein, the prompt message is used for prompting the user to adjust the flight state of the unmanned aerial vehicle. In some embodiments, the prompt information may be output through a prompt module of the control terminal, and the control terminal may include, but is not limited to, a remote controller and other devices. In an embodiment, the flight control device may output a prompt message to the control terminal at a start time, an end time, and an intermediate process of switching the flight mode of the unmanned aerial vehicle, which is not specifically limited in the embodiment of the present invention. The interaction process and examples of the output prompt information between the flight control device and the control terminal are as described above, and are not described herein again.

In the embodiment of the invention, when the flight control device acquires the flight mode switching instruction and determines that the unmanned aerial vehicle meets the flight mode switching condition, the flight control device switches the current flight mode of the unmanned aerial vehicle, so that the safety of the unmanned aerial vehicle in the switching process is ensured, and the reliability of mode switching of the unmanned aerial vehicle in different flight states and/or different environments is improved on the premise of ensuring the safety of the unmanned aerial vehicle in the switching process; by sending the prompt information to the control terminal, the user experience is improved.

Referring to fig. 4 in detail, fig. 4 is a schematic flowchart of a flight control method of another unmanned aerial vehicle according to an embodiment of the present invention, where the method may be executed by a flight control device, and a detailed explanation of the flight control device is as described above. The embodiment of the present invention differs from the embodiment described in fig. 3 in that the embodiment of the present invention is a schematic illustration of the implementation of the switching from the fixed-wing flight mode to the rotor flight mode. Specifically, the method of the embodiment of the present invention includes the following steps.

S401: acquiring a flight mode switching instruction, wherein the flight mode switching instruction is used for indicating that the flight mode of the unmanned aerial vehicle is switched from a fixed wing flight mode to a rotor wing flight mode.

S402: and controlling the attitude angle of the unmanned aerial vehicle to be smaller than a preset angle threshold value.

In the embodiment of the invention, when the flight control device acquires the flight mode switching instruction, the attitude angle of the unmanned aerial vehicle can be controlled to be smaller than a preset angle threshold value.

In one embodiment, the flight mode switching instructions are for instructing switching of the flight mode of the drone from the fixed-wing flight mode to the rotor flight mode, and the flight control device may control the attitude angle of the drone to be less than a preset angle threshold before the flight mode of the drone is switched from the fixed-wing flight mode to the rotor flight mode. For example, the roll angle of the drone is controlled to be less than a preset angle threshold.

Through this kind of embodiment, can improve the follow-up stability of switching to rotor flight mode in-process from fixed wing flight mode of unmanned aerial vehicle to and improve and switch to rotor flight mode in-process from fixed wing flight mode reliability.

S403: switching a flight mode of the drone from the fixed-wing flight mode to the rotor flight mode.

In an embodiment of the present invention, the flight control device may switch the flight mode of the drone from the fixed-wing flight mode to the rotor flight mode.

In one embodiment, the flight control device may acquire an ambient wind speed of the drone in the fixed-wing flight mode when switching the flight mode of the drone from the fixed-wing flight mode to the rotor flight mode, and determine a target pitch angle of the drone according to the ambient wind speed, so as to control the drone to decelerate at the target pitch angle.

In one embodiment, the flight control device may acquire the ambient wind speed and the flying speed of the drone in real time during the process of switching the flight mode of the drone from the fixed-wing flight mode to the rotor flight mode, and determine the target pitch angle according to the ambient wind speed and the flying speed of the drone, so as to control the drone to decelerate at the target pitch angle.

In one embodiment, the flight control device may obtain lateral velocity error information or lateral offset error information of the drone when switching the flight mode of the drone from the fixed-wing flight mode to the rotor flight mode, determine a target attitude angle of the drone according to the lateral velocity error information or the lateral offset error information, and control the attitude of the drone according to the target attitude angle in the process of switching the current fixed-wing flight mode of the drone to the rotor flight mode. Control through the gesture to unmanned aerial vehicle, help reducing unmanned aerial vehicle's lateral velocity error or lateral offset error to ensure unmanned aerial vehicle at the security of flight in-process.

In one embodiment, the drone is then determined to be successfully switched to the rotor flight mode when the drone satisfies the following conditions: the unmanned aerial vehicle decelerates to a preset speed threshold.

In some embodiments, when the drone switches from the fixed-wing flight mode to the rotor flight mode, automatically turn off the fixed-wing flight mode and turn on the rotor flight mode, and control the drone to fly at the target pitch angle deceleration, so that when the drone decelerates to a preset speed threshold, it is determined that the drone switches from the fixed-wing flight mode to the rotor flight mode.

For example, assuming a current flight speed of 6m/s, if the drone decelerates to 3m/s, it may be determined that the drone successfully switches from a fixed-wing flight mode to the rotor flight mode.

In one embodiment, the drone may be controlled to switch to the rotor flight mode when the drone does not switch from the fixed-wing flight mode to the rotor flight mode within the second specified time range.

In one embodiment, when the drone is not switched from the fixed-wing flight mode to the rotor flight mode within the second specified time range, then the drone may be forcibly controlled to switch back to the rotor flight mode. Through this kind of embodiment, can realize switching the protection to unmanned aerial vehicle when overtime, improved the security that unmanned aerial vehicle switches in-process.

For example, assuming that the second specified time range is 2 minutes and the current flight speed is 6m/s, the drone may be controlled to switch back to the rotor flight mode by force if it is not successful to switch from the fixed-wing flight mode to the rotor flight mode within 2 minutes.

In the embodiment of the invention, when acquiring a flight mode switching instruction for instructing the flight mode of the unmanned aerial vehicle to switch from the fixed-wing flight mode to the rotor flight mode, the flight control device controls the attitude angle of the unmanned aerial vehicle to be smaller than a preset angle threshold value, and switches the flight mode of the unmanned aerial vehicle from the fixed-wing flight mode to the rotor flight mode. Through this kind of embodiment, can improve unmanned aerial vehicle stability, reliability and security in the switching process.

Referring to fig. 5, fig. 5 is a schematic structural diagram of a flight control device according to an embodiment of the present invention. Specifically, the flight control device includes: memory 501, processor 502.

In one embodiment, the flight control device further comprises a data interface 503, wherein the data interface 503 is used for transmitting data information between the flight control device and other devices.

The memory 501 may include a volatile memory (volatile memory); the memory 501 may also include a non-volatile memory (non-volatile memory); the memory 501 may also comprise a combination of memories of the kind described above. The processor 502 may be a Central Processing Unit (CPU). The processor 502 may further include a hardware chip. The hardware chip may be an application-specific integrated circuit (ASIC), a Programmable Logic Device (PLD), or a combination thereof. The PLD may be a Complex Programmable Logic Device (CPLD), a field-programmable gate array (FPGA), or any combination thereof.

The memory 501 is used for storing program instructions, and the processor 502 can call the program instructions stored in the memory 501 for executing the following steps:

and when the unmanned aerial vehicle meets the flight mode switching condition, switching the current flight mode of the unmanned aerial vehicle.

Further, the flight state information includes any one or more of position error information, attitude error information, velocity error information, acceleration error information, angular acceleration error information, and angular velocity error information.

Further, the environmental information includes environmental wind information and/or obstacle information.

Further, the flight mode switching instructions are configured to instruct switching the flight mode of the drone from the rotor flight mode to a fixed-wing flight mode, and the processor 502 is further configured to:

acquiring lateral speed error information or lateral offset error information of the unmanned aerial vehicle;

determining a target attitude angle of the unmanned aerial vehicle according to the lateral speed error information or the lateral offset error information;