WO2022047669A1 - 空中旋翼与螺旋桨协同驱动无人飞船超声水下探测方法 - Google Patents

空中旋翼与螺旋桨协同驱动无人飞船超声水下探测方法 Download PDF

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WO2022047669A1
WO2022047669A1 PCT/CN2020/113034 CN2020113034W WO2022047669A1 WO 2022047669 A1 WO2022047669 A1 WO 2022047669A1 CN 2020113034 W CN2020113034 W CN 2020113034W WO 2022047669 A1 WO2022047669 A1 WO 2022047669A1
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unmanned
detection
unmanned spacecraft
servo motor
control coefficient
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PCT/CN2020/113034
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English (en)
French (fr)
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韦岗
黄晓鸿
曹燕
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华南理工大学
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Priority to PCT/CN2020/113034 priority Critical patent/WO2022047669A1/zh
Publication of WO2022047669A1 publication Critical patent/WO2022047669A1/zh

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C35/00—Flying-boats; Seaplanes
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
    • G01S15/00—Systems using the reflection or reradiation of acoustic waves, e.g. sonar systems
    • G01S15/02—Systems using the reflection or reradiation of acoustic waves, e.g. sonar systems using reflection of acoustic waves
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
    • G01S15/00—Systems using the reflection or reradiation of acoustic waves, e.g. sonar systems
    • G01S15/88—Sonar systems specially adapted for specific applications

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  • the invention mainly relates to the field of water detection of unmanned ships, in particular to a method for ultrasonic underwater detection of unmanned ships driven by air rotors and propellers in coordination.
  • Unmanned ship is a fully automatic surface robot that can navigate on the water surface according to preset tasks with the help of precise satellite positioning and self-sensing without remote control.
  • the English name is unmanned surface vessel, and the English abbreviation is USV.
  • Unmanned ships are mostly used for Mapping, hydrology and water quality monitoring. Replacing manpower with unmanned ships can greatly reduce manpower and improve efficiency.
  • the detection personnel needed to carry their own detection equipment and carry boats to the detection site for water detection. During the detection process, the boat may hit the rocks. , water pollution, bad weather and other conditions threaten the safety of the detectors themselves.
  • Unmanned ships can replace detectors to detect waters.
  • the detection personnel can perform detection tasks by remotely controlling the unmanned ship, or in some environments, let the unmanned ship perform the detection task autonomously and intelligently.
  • the existing unmanned ships are easily affected by waves when sailing on the water surface, which causes the hull to sway.
  • the shaking caused by the waves makes the underwater detection module both send and receive signals.
  • the attitude of each moment has a relatively large change, which affects the reception of the ultrasonic echo signal reflected by the underwater target, resulting in low detection accuracy.
  • the ultrasonic microarray When the unmanned ship uses the ultrasonic microarray for underwater detection, the ultrasonic microarray transmits ultrasonic signals with a specific spectrum structure to the water area to be measured, and the ultrasonic microarray receives the ultrasonic echo signals reflected by the underwater target, and then calculates various types of waters. parameter.
  • Existing unmanned ships can only perform fixed-point directional water detection, and can only obtain a wider range of water parameters by moving the position.
  • the purpose of the present invention is to overcome the limitations of unmanned ships that are easily subject to natural geographical environment or man-made engineering barriers, slow underwater detection speed, easy to be affected by waves during detection to reduce detection accuracy, and single detection method during underwater detection.
  • An ultrasonic underwater detection method for an unmanned spaceship driven by an air rotor and a propeller in coordination which can easily and quickly reach the detection water area, can control the balance of the unmanned spaceship, can control the unmanned spaceship to perform detection and scanning, can reduce the draft, reduce the sailing resistance, and speed up the detection and scanning. sailing speed.
  • An ultrasonic underwater detection method for an aerial rotor and a propeller to cooperatively drive an unmanned spacecraft comprising the following steps:
  • step S8 If scanning and detection are required, change the roll angle and yaw angle of the unmanned spacecraft and keep them, and return to step S6;
  • step S9 determine whether to complete the water environment detection around the fixed point, if not, return to step S5 and move to another position in the water area around the fixed point for detection; if so, return to step S1 to detect the waters of the next detection point.
  • the detection fixed point position of the step S1 is from the detection fixed point position specified by the remote user or from the position of the next detection fixed point obtained by the unmanned spacecraft according to the path planning.
  • step S2 is:
  • the unmanned spaceship controls the rotation of the air rotor above the unmanned spaceship to provide thrust F z to push the unmanned spaceship away from the water surface.
  • the height of the unmanned spaceship from the water surface is obtained by the ultrasonic microarray distributed on the bottom of the ship.
  • the throttle value of the brush motor and the throttle value of the servo motor that controls the orientation of each air rotor are:
  • m i is the throttle value of the ith brushless motor
  • s i is the throttle value of the ith servo motor
  • the thrust control coefficient of the brushless motor is the zero bias control coefficient of the servo motor
  • the unmanned spacecraft then controls the air rotor above the unmanned spacecraft to generate a roll angular moment and the pitch angle moment ⁇ ⁇ , changing the roll angle and pitch angle of the unmanned spacecraft, the thrust F z generated by the rotation of the rotor above the unmanned spacecraft generates a horizontal thrust due to the change of the roll angle and the pitch angle, so that the unmanned spacecraft flies horizontally, where The current horizontal position of the unmanned spacecraft is obtained by the satellite locator.
  • the throttle value of the brushless motor that controls the rotation speed of each air rotor and the throttle value of the servo motor that controls the direction of each air rotor are:
  • m i is the throttle value of the ith brushless motor
  • s i is the throttle value of the ith servo motor
  • the thrust control coefficient of the brushless motor is the zero-bias control coefficient of the servo motor
  • the rolling angle torque control coefficient of the brushless motor is the brushless motor pitch angle torque control coefficient
  • is the roll angle torque control coefficient of the servo motor is the pitch angle torque control coefficient of the servo motor.
  • step S3 use the attitude instrument to measure and record the yaw angle and pitch angle of the unmanned spacecraft, and delete the values of the yaw angle and the pitch angle that are less than the threshold, obtain n groups of data, and obtain by the following formula statistics
  • ⁇ i is the pitch angle of the ith group of unmanned spacecraft
  • n is the number of data.
  • the process of the step S4 is: control the air rotor above the unmanned spacecraft to generate a yaw angle moment ⁇ ⁇ , so that the unmanned spacecraft rotates clockwise
  • the direction of the unmanned spacecraft is perpendicular to the direction of the wave motion, where ⁇ is the angle between the direction of the wave motion and the hull of the unmanned spacecraft.
  • the throttle value of the brushless motor that controls the rotational speed of each air rotor and the servo that controls the direction of each air rotor is:
  • m i is the throttle value of the ith brushless motor
  • s i is the throttle value of the ith servo motor
  • yaw angle torque control coefficient of the brushless motor is the yaw angle torque control coefficient of the servo motor
  • step S5 control the rotation of the propeller below the tail of the unmanned spacecraft, provide forward thrust F f , push the unmanned spacecraft to sail forward, and control the air rotor above the unmanned spacecraft to generate a yaw angle moment ⁇ .
  • the generated yaw angle moment ⁇ ⁇ is used to control the sailing direction
  • the generated thrust F z is used to control the draft, of which the current draft of the unmanned spacecraft is obtained by the pressure gauge distributed on the bottom of the ship, at this time the control
  • the throttle values of the brushless motors for the rotational speed of each aerial rotor, the throttle values of the servo motors that control the orientation of each aerial rotor, and the throttle values of the underwater brushless motors that control the rotation of the propellers are:
  • m i is the throttle value of the ith brushless motor
  • s i is the throttle value of the ith servo motor
  • the thrust control coefficient of the brushless motor is the zero-bias control coefficient of the servo motor
  • the yaw angle torque control coefficient of the brushless motor is the yaw angle torque control coefficient of the servo motor
  • mu is the throttle value of the underwater brushless motor
  • k is the forward thrust control coefficient.
  • the process of the step S6 is: the ultrasonic microarray sends a detection signal, and calculates the water area parameters according to the received detection signal: calculates the water flow speed based on the frequency offset of the ultrasonic received echo and the transmitted wave signal; based on the ultrasonic received echo Calculate the water depth with the time delay of the transmitted wave signal; based on the time delay, reflection coefficient, and direction of arrival parameters of the ultrasonic received echo and the transmitted wave signal, combined with the water surface geographic location of the unmanned spacecraft, the bottom topography is inverted.
  • the process of the step S7 is: the unmanned spacecraft collects the attitude instrument at a high frequency to obtain the attitude of the unmanned spacecraft, and when a slight change in the attitude of the unmanned spacecraft is detected, the air rotor is immediately controlled to generate a rolling angular moment.
  • the pitch angle moment ⁇ ⁇ and the yaw angle moment ⁇ ⁇ are used to correct the roll angle, pitch angle, and yaw angle of the unmanned spacecraft, respectively.
  • Servo motor throttle value is:
  • m i is the throttle value of the ith brushless motor
  • s i is the throttle value of the ith servo motor
  • the zero-bias control coefficient of the servo motor is the rolling angle torque control coefficient of the brushless motor
  • the brushless motor pitch angle torque control coefficient is the brushless motor pitch angle torque control coefficient
  • the yaw angle torque control coefficient of the brushless motor is the roll angle torque control coefficient of the servo motor
  • is the pitch angle torque control coefficient of the servo motor is the yaw angle torque control coefficient of the servo motor.
  • the process of the step S8 is: the unmanned spacecraft controls the air rotor to generate a roll angular moment Yaw angle moment ⁇ ⁇ , rotate the unmanned spacecraft to the specified roll angle and specified yaw angle, the ultrasonic microarray on the bottom of the unmanned spacecraft will change the detection direction with the rotation of the unmanned spacecraft, and at this time control the rotation speed of each air rotor.
  • the brushless motor throttle values and the servo motor throttle values that control the orientation of each air rotor are:
  • m i is the throttle value of the ith brushless motor
  • s i is the throttle value of the ith servo motor
  • the zero-bias control coefficient of the servo motor is the rolling angle torque control coefficient of the brushless motor
  • the brushless motor pitch angle torque control coefficient is the brushless motor pitch angle torque control coefficient
  • the yaw angle torque control coefficient of the brushless motor is the roll angle torque control coefficient of the servo motor
  • is the pitch angle torque control coefficient of the servo motor is the yaw angle torque control coefficient of the servo motor.
  • the present invention has the following advantages and effects:
  • the rotation of the rotor of the unmanned spacecraft in the air generates thrust to control the flight of the unmanned spacecraft.
  • the flight resistance is less than the water surface navigation resistance, and the movement speed is fast.
  • Fig. 1 is a flow chart of a method for ultrasonic underwater detection of an aerial rotor and a propeller to cooperatively drive an unmanned spacecraft disclosed in the present invention
  • Fig. 2 is the top view of two-rotor unmanned spacecraft in the implementation of the present invention
  • Fig. 3 is the right side view of two-rotor unmanned spacecraft in the implementation of the present invention.
  • FIG. 4 is a cross-sectional view of a two-rotor unmanned spacecraft in the implementation of the present invention.
  • This embodiment will take a two-rotor unmanned spacecraft as an example, and the hull structure of the two-rotor unmanned spacecraft is shown in FIGS. 2 , 3 and 4 .
  • the hull structure of the two-rotor unmanned spacecraft is shown in FIGS. 2 , 3 and 4 .
  • Above the hull of the two-rotor unmanned spacecraft there are No. 1 servo motor 5, No. 2 servo motor 6, No. 1 brushless motor 3, No. 2 brushless motor 4, No. 1 air rotor 1, No. 2 air rotor 2, and the distribution below the tail
  • a brushless motor 7 and a propeller 8 an ultrasonic microarray 10 and a pressure sensor 11 at the bottom, an attitude gauge 12 and a satellite positioning receiver 13 on the inner wall, and a satellite positioning receiver antenna 9 at the top.
  • the No. 1 servo motor 5 and the No. 2 servo motor 6 are fixed on the bracket above the hull through the bracket, the No. 1 servo motor 5 is fixed to the No. 1 brushless motor 3, and the No. 2 servo motor 6 is fixed to the No. 2 brushless motor 4.
  • the No. 1 brushless motor 3 shaft is fixed on the No. 1 air rotor 1, and the No. 2 brushless motor 4 shaft is fixed on the No. 2 air rotor 2.
  • the No. 1 brushless motor 3 controls the first aerial rotor 1 to rotate forward, and the No.
  • the 2 brushless motor 4 controls the second aerial rotor 2 to rotate in reverse.
  • the throttle value of the No. 1 brushless motor 3 above the hull of the two-rotor unmanned spacecraft, the No. 2 brushless motor 4 and the 1 brushless motor 7 below the tail is 0, the motor is stationary, and when the throttle value is 1000, the motor reaches maximum speed.
  • the throttle value of the servo motor is 500, the angle of the servo motor shaft is 90 degrees, that is, the No. 1 brushless motor 3 and No. 2 brushless motor 4 fixed on the rotating shafts of the No. 1 servo motor 5 and No. 2 servo motor 6 are perpendicular to the bottom of the boat.
  • the angle of the servo motor shaft is 0 degrees, that is, the No. 1 brushless motor 3 fixed on the No. 1 servo motor 5 rotating shaft faces the stern, that is, the No. 2 servo motor 6 fixed on the No. 6 rotating shaft
  • the shaft of the brush motor 4 faces the bow.
  • the angle of the servo motor shaft is 180 degrees, that is, the No. 1 brushless motor 3 fixed on the No. 1 servo motor 5 rotating shaft faces the bow, that is, the No. 2 servo motor 6 fixed on the rotating shaft No. 2
  • the shaft of the brushless motor 4 is towards the stern.
  • control process of the ultrasonic underwater detection method for the unmanned spacecraft to be driven by the air rotor and the propeller is as follows:
  • the unmanned spaceship controls the No. 1 air rotor 1 and the No. 2 air rotor 2 to generate thrust F z to push the unmanned spaceship out of the water.
  • Level flight Control the air rotor 1 and No. 2 air rotor 2 above the unmanned spacecraft to generate a roll angular moment and the pitch angle moment ⁇ ⁇ , changing the roll angle and pitch angle of the unmanned spacecraft, the thrust F z generated by the rotation of the unmanned spacecraft air rotor 1 and the second air rotor 2 generates a horizontal thrust due to the change of the roll angle and the pitch angle, so that no Man spaceship flying horizontally.
  • Landing reduce thrust F z .
  • the height of the unmanned spacecraft from the water surface is obtained by the ultrasonic microarray distributed on the bottom of the ship, and the current horizontal position of the unmanned spacecraft is obtained by the satellite locator.
  • ⁇ i is the pitch angle of the ith group of unmanned spacecraft
  • n is the number of data.
  • the steps of controlling the unmanned spacecraft to sail on the water surface are: control the rotation of the propeller below the tail of the unmanned spacecraft to provide forward thrust F f , push the unmanned spacecraft to sail forward, and control the No. 1 air rotor 1 and No. 2 air rotor above the unmanned spacecraft 2.
  • the yaw angle moment ⁇ ⁇ and the thrust F z are generated.
  • the generated yaw angle moment ⁇ ⁇ is used to control the sailing direction, and the generated thrust F z is used to control the draft.
  • the current draft of the unmanned spacecraft is determined by the pressure distributed on the bottom of the ship. counted.
  • the unmanned spaceship collects the attitude instrument at a high frequency to obtain the attitude of the unmanned spaceship.
  • the No. 1 air rotor 1 and the No. 2 air rotor 2 are immediately controlled to generate roll angular moment Pitch angle moment ⁇ ⁇ , yaw angle moment ⁇ ⁇ ; roll angle moment
  • the pitch angle moment ⁇ ⁇ and the yaw angle moment ⁇ ⁇ are used to correct the roll angle, pitch angle and yaw angle of the unmanned spacecraft, respectively.
  • the unmanned spacecraft controls the No. 1 air rotor 1 and No. 2 air rotor 2 to generate a rolling angular moment
  • the yaw angle moment ⁇ ⁇ rotates the unmanned spacecraft to a specified roll angle and a specified yaw angle; the ultrasonic microarray on the bottom of the unmanned spacecraft will change the detection direction with the rotation of the unmanned spacecraft. And return to step S6.
  • step S9 Determine whether the environmental detection of the waters around the fixed point is completed. If not, return to step S5 and move to another position in the waters around the fixed point for detection. If so, go back to step S1 to perform water detection at the next detection point.
  • thrust F z roll angular moment
  • the pitch angle moment ⁇ ⁇ and the yaw angle moment ⁇ ⁇ are generated by controlling the rotational speed and orientation of the No. 1 air rotor 1 and No. 2 air rotor 2 distributed above the unmanned spacecraft; the unmanned spacecraft generates thrust F z , roll angle moment
  • the corresponding throttle values of the brushless motor and servo motor are:
  • m 1 is the throttle value of the No. 1 brushless motor 3
  • m 2 is the throttle value of the No. 2 brushless motor 4
  • s 1 is the throttle value of the No. 1 servo motor 5
  • s 2 is the throttle of the No. 2 servo motor 6 value.
  • the forward thrust F f is generated by controlling the speed of the propellers distributed under the tail of the unmanned spacecraft; the propeller is fixed on an underwater brushless motor, and the throttle value of the underwater brushless motor determines the speed of the propeller; the unmanned spacecraft generates When the forward thrust is F f , the corresponding throttle value of the brushless motor is:
  • mu is the throttle value of the underwater brushless motor 7 under the tail of the unmanned spacecraft.
  • the present invention balances the unmanned spacecraft by controlling the torque generated by the air rotors of the unmanned spacecraft, maintains the detection direction of the ultrasonic microarray, and improves the detection accuracy; the torque generated by the air rotors of the unmanned spacecraft can also be used to actively change the unmanned spacecraft.
  • the yaw angle moment and the upward thrust generated by the airborne rotor of the unmanned spacecraft can be combined with the propeller to realize the water surface navigation task of controlling the draft;
  • the airborne rotor of the unmanned spacecraft rotates Generate thrust to control the flight of the unmanned spacecraft, the flight resistance is less than the water surface navigation resistance, and the movement speed is fast.

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  • Engineering & Computer Science (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Remote Sensing (AREA)
  • Physics & Mathematics (AREA)
  • Acoustics & Sound (AREA)
  • Computer Networks & Wireless Communication (AREA)
  • General Physics & Mathematics (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)

Abstract

一种空中旋翼（1, 2）与螺旋桨（8）协同驱动无人飞船超声水下探测方法，空中旋翼（1, 2）与螺旋桨（8）协同驱动无人飞船超声水下探测方法通过控制无人飞船上方的空中旋翼（1, 2），尾部下方的水下螺旋桨（8），来移动和平衡无人飞船，包括以下步骤：接收控制命令得到探测定点位置；飞行到达探测定点；使用姿态仪（12）测量记录无人飞船的姿态，统计波浪运动方向；控制无人飞船朝向垂直于波浪运动方向；控制无人飞船在探测定点周围航行；控制超声微阵列（10）采集水域参数；保持无人飞船姿态；若需要进行扫描探测，改变无人飞船翻滚角和偏航角并进行探测；若完成定点水域探测，则接收控制命令并飞行至下一个探测定点，否则继续航行探测。空中旋翼（1, 2）与螺旋桨（8）协同驱动无人飞船超声水下探测方法可提高无人飞船的探测速度和探测精度。

Description

空中旋翼与螺旋桨协同驱动无人飞船超声水下探测方法 技术领域
本发明主要涉及无人船水域探测领域，具体涉及一种空中旋翼与螺旋桨协同驱动无人飞船超声水下探测方法。
背景技术
无人船是一种可以无需遥控，借助精确卫星定位和自身传感即可按照预设任务在水面航行的全自动水面机器人，英文名称为unmanned surface vessel，英文缩写为USV，无人船多用于测绘、水文和水质监测。用无人船代替人力可以大大地减少人力和提高效率，在以往的探测任务中，探测人员需要自身携带探测设备，搭载船艇前往探测地点进行水域探测，在探测过程中可能会出现船艇触礁，水域污染，天气恶劣等情况，威胁探测人员自身的安全，同时在一些空间狭窄，探测困难的环境下，探测员很难前往探测地点进行探测，无人船可以替代探测人员进行探测水域任务，探测人员可以通过远程操控无人船进行探测任务，也可以在一些环境下，让无人船自主智能地进行探测任务。
现有的无人船通过螺旋桨推动无人船在水面上航行，这种方式的航行速度普遍比较慢，降低探测效率。
现有的无人船在水面航行时容易受到波浪的影响导致船体出现摇摆，当使用超声微阵列进行水下探测时，这种波浪带来的晃动，使得水下探测模块在发送和接收信号两个时刻的姿态有比较大的变化，影响接收水下目标反射的超声回波信号，导致探测精度低。
无人船在使用超声微阵列进行水下探测时，超声微阵列向待测水域发 射特定频谱结构的超声信号，超声微阵列接收水下目标反射的超声回波信号，进而计算出水域的各种参数。现有的无人船只能进行定点定向的水域探测，只能通过移动位置的方式来获取更大范围的水域参数。
发明内容
本发明的目的是为了克服无人船容易受自然地理环境或人造工程屏障的限制、水下探测速度慢、探测时容易受到波浪影响而降低探测精度、水下探测时探测方式单一缺陷，提供一种空中旋翼与螺旋桨协同驱动无人飞船超声水下探测方法，能方便快速地抵达探测水域，可控制无人飞船平衡，可控制无人飞船进行探测扫描，能降低吃水量，减少航行阻力，加快航行速度。
本发明解决上述问题所采用的的技术方案如下。
一种空中旋翼与螺旋桨协同驱动无人飞船超声水下探测方法，包括以下步骤：
S1、接收控制命令得到探测定点位置；
S2、使用飞行的方式到达探测定点；
S3、到达探测定点后，控制空中旋翼和螺旋桨静止一段时间，并使用姿态仪测量记录无人飞船的姿态变化率，统计波浪运动方向；
S4、控制无人飞船朝向垂直于波浪运动方向；
S5、控制无人飞船在探测定点周围航行；
S6、控制超声微阵列采集水域参数；
S7、在控制超声微阵列采集水域参数时，保持无人飞船姿态；
S8、若需要进行扫描探测，改变无人飞船翻滚角和偏航角并进行保持，并返回步骤S6；
S9、判断是否完成该定点周围水域环境探测，若否，返回步骤S5移动至该定点周围水域的另一位置进行探测；若是，返回步骤S1进行下一 个探测点的水域探测。
进一步地，所述步骤S1的探测定点位置是来自于远程用户指定的探测定点位置或者是来自于无人飞船根据路径规划得到的下一次探测定点的位置。
进一步地，所述步骤S2的过程为：
无人飞船控制无人飞船上方空中旋翼转动提供推力F z，推动无人飞船离开水面，其中无人飞船距离水面高度由分布在船底的超声微阵列得到，此时控制各个空中旋翼转动速度的无刷电机油门值和控制各个空中旋翼朝向的伺服电机油门值为：
Figure PCTCN2020113034-appb-000001
Figure PCTCN2020113034-appb-000002
其中m i为第i个无刷电机油门值，s i为第i个伺服电机油门值，
Figure PCTCN2020113034-appb-000003
为无刷电机推力控制系数，
Figure PCTCN2020113034-appb-000004
为伺服电机零偏控制系数；
无人飞船再控制无人飞船上方空中旋翼产生翻滚角力矩
Figure PCTCN2020113034-appb-000005
和俯仰角力矩τ θ，改变无人飞船翻滚角和俯仰角，无人飞船上方空中旋翼转动产生的推力F z因为翻滚角和俯仰角的变化产生水平的推力，使无人飞船水平飞行，其中无人飞船当前水平位置由卫星定位仪得到，此时控制各个空中旋翼转动速度的无刷电机油门值和控制各个空中旋翼朝向的伺服电机油门值为：
Figure PCTCN2020113034-appb-000006
Figure PCTCN2020113034-appb-000007
其中m i为第i个无刷电机油门值，s i为第i个伺服电机油门值，
Figure PCTCN2020113034-appb-000008
为无刷电机推力控制系数，
Figure PCTCN2020113034-appb-000009
为伺服电机零偏控制系数，
Figure PCTCN2020113034-appb-000010
为无刷电机翻滚角力矩控制系数，
Figure PCTCN2020113034-appb-000011
为无刷电机俯仰角力矩控制系数，
Figure PCTCN2020113034-appb-000012
为伺服电 机翻滚角力矩控制系数，
Figure PCTCN2020113034-appb-000013
为伺服电机俯仰角力矩控制系数。
进一步地，所述步骤S3的过程为：使用姿态仪测量记录无人飞船的偏航角和俯仰角，并删除偏航角和俯仰角小于阈值的值，得到n组数据，由下式统计得到波浪运动方向和无人飞船船体的夹角α：
Figure PCTCN2020113034-appb-000014
其中
Figure PCTCN2020113034-appb-000015
为第i组无人飞船偏航角，θ i为第i组无人飞船俯仰角，n为数据个数。
进一步地，所述步骤S4的过程为：控制无人飞船上方的空中旋翼产生偏航角力矩τ ψ，使无人飞船顺时针旋转
Figure PCTCN2020113034-appb-000016
此时无人飞船朝向与波浪运动方向垂直，其中，α为波浪运动方向和无人飞船船体的夹角，此时控制各个空中旋翼转动速度的无刷电机油门值和控制各个空中旋翼朝向的伺服电机油门值为：
Figure PCTCN2020113034-appb-000017
Figure PCTCN2020113034-appb-000018
其中m i为第i个无刷电机油门值，s i为第i个伺服电机油门值，
Figure PCTCN2020113034-appb-000019
为伺服电机零偏控制系数，
Figure PCTCN2020113034-appb-000020
为无刷电机偏航角力矩控制系数，
Figure PCTCN2020113034-appb-000021
为伺服电机偏航角力矩控制系数。
进一步地，所述步骤S5的过程为：控制无人飞船尾部下方的螺旋桨转动，提供向前推力F f，推动无人飞船向前航行，控制无人飞船上方的空中旋翼产生偏航角力矩τ ψ和推力F z，产生的偏航角力矩τ ψ用来控制航行方向，产生的推力F z用来控制吃水量，其中无人飞船当前吃水量由分布在船底的压力计得到，此时控制各个空中旋翼转动速度的无刷电机油门值、控 制各个空中旋翼朝向的伺服电机油门值和控制螺旋桨转动的水下无刷电机油门值为：
Figure PCTCN2020113034-appb-000022
Figure PCTCN2020113034-appb-000023
mu＝kT f           公式(10)
其中m i为第i个无刷电机油门值，s i为第i个伺服电机油门值，
Figure PCTCN2020113034-appb-000024
为无刷电机推力控制系数，
Figure PCTCN2020113034-appb-000025
为伺服电机零偏控制系数，
Figure PCTCN2020113034-appb-000026
为无刷电机偏航角力矩控制系数，
Figure PCTCN2020113034-appb-000027
为伺服电机偏航角力矩控制系数，mu为水下无刷电机油门值，k为向前推力控制系数。
进一步地，所述步骤S6的过程为：超声微阵列发送探测信号，根据接收到的探测信号，计算水域参数：基于超声接收回波与发射波信号的频偏计算水流速度；基于超声接收回波与发射波信号的时延计算水深；基于超声接收回波与发射波信号的时延、反射系数、波达方向参数，结合无人飞船的水面地理位置，反演水底的地形地貌。
进一步地，所述步骤S7的过程为：无人飞船以高频率采集姿态仪，得到无人飞船姿态、当检测到无人飞船姿态发生微小变化时，即刻控制空中旋翼产生翻滚角力矩
Figure PCTCN2020113034-appb-000028
俯仰角力矩τ θ、偏航角力矩τ ψ；翻滚角力矩
Figure PCTCN2020113034-appb-000029
俯仰角力矩τ θ、偏航角力矩τ ψ分别用于纠正无人飞船翻转角、俯仰角、偏航角，此时控制各个空中旋翼转动速度的无刷电机油门值和控制各个空中旋翼朝向的伺服电机油门值为：
Figure PCTCN2020113034-appb-000030
Figure PCTCN2020113034-appb-000031
其中m i为第i个无刷电机油门值，s i为第i个伺服电机油门值，
Figure PCTCN2020113034-appb-000032
为伺服电机零偏控制系数，
Figure PCTCN2020113034-appb-000033
为无刷电机翻滚角力矩控制系数，
Figure PCTCN2020113034-appb-000034
为无刷电机俯仰角力矩控制系数，
Figure PCTCN2020113034-appb-000035
为无刷电机偏航角力矩控制系数，
Figure PCTCN2020113034-appb-000036
为伺服电机翻滚角力矩控制系数，
Figure PCTCN2020113034-appb-000037
为伺服电机俯仰角力矩控制系数，
Figure PCTCN2020113034-appb-000038
为伺服电机偏航角力矩控制系数。
进一步地，所述步骤S8的过程为：无人飞船控制空中旋翼产生翻滚角力矩
Figure PCTCN2020113034-appb-000039
偏航角力矩τ ψ，旋转无人飞船至指定翻滚角、指定偏航角，无人飞船船底超声微阵列会随着无人飞船的旋转而改变探测方向，此时控制各个空中旋翼转动速度的无刷电机油门值和控制各个空中旋翼朝向的伺服电机油门值为：
Figure PCTCN2020113034-appb-000040
Figure PCTCN2020113034-appb-000041
其中m i为第i个无刷电机油门值，s i为第i个伺服电机油门值，
Figure PCTCN2020113034-appb-000042
为伺服电机零偏控制系数，
Figure PCTCN2020113034-appb-000043
为无刷电机翻滚角力矩控制系数，
Figure PCTCN2020113034-appb-000044
为无刷电机俯仰角力矩控制系数，
Figure PCTCN2020113034-appb-000045
为无刷电机偏航角力矩控制系数，
Figure PCTCN2020113034-appb-000046
为伺服电机翻滚角力矩控制系数，
Figure PCTCN2020113034-appb-000047
为伺服电机俯仰角力矩控制系数，
Figure PCTCN2020113034-appb-000048
为伺服电机偏航角力矩控制系数。
本发明相对于现有技术具有如下的优点及效果：
(1)通过控制无人飞船空中旋翼产生的力矩来平衡无人飞船，保持超声微阵列探测方向，提高探测精度。
(2)通过控制无人飞船空中旋翼产生的力矩来主动改变无人飞船姿态，进而改变超声微阵列探测方向，实现扫描探测的功能；
(3)无人飞船空中旋翼产生的偏航角力矩和向上的推力可结合螺旋 桨，实现控制吃水量的水面航行任务；
(4)无人飞船空中旋翼转动产生推力控制无人飞船飞行，飞行所受阻力小于水面航行阻力，运动速度快。
附图说明
图1是本发明公开的一种空中旋翼与螺旋桨协同驱动无人飞船超声水下探测方法流程图；
图2是本发明实施中两旋翼无人飞船俯视图；
图3是本发明实施中两旋翼无人飞船右视图；
图4是本发明实施中两旋翼无人飞船剖视图。
具体实施方式
为使本发明实施例的目的、技术方案和优点更加清楚，下面将结合本发明实施例中的附图，对本发明实施例中的技术方案进行清楚、完整地描述，显然，所描述的实施例是本发明一部分实施例，而不是全部的实施例。基于本发明中的实施例，本领域普通技术人员在没有做出创造性劳动前提下所获得的所有其他实施例，都属于本发明保护的范围。
实施例
本实施例将以两旋翼无人飞船为例，该两旋翼无人飞船船体结构如图2、图3、图4所示。该两旋翼无人飞船船体上方分布有一号伺服电机5、二号伺服电机6、一号无刷电机3、二号无刷电机4、一号空中旋翼1、二号空中旋翼2、尾部下方分布有1个无刷电机7和1个螺旋桨8，底部有超声微阵列10和压力传感器11，内壁有姿态仪12和卫星定位接收机13，顶部有卫星定位接收机天线9。该两旋翼无人飞船船体上方分布的一号伺服电机5、二号伺服电机6、一号无刷电机3、二号无刷电机4、一号空中旋翼1、二号空中旋翼2，连接方式为一号伺服电机5、二号伺服电机6通 过支架固定在船体上方支架上，一号伺服电机5转轴固定有一号无刷电机3，二号伺服电机6转轴固定有二号无刷电机4，一号无刷电机3转轴固定一号空中旋翼1，二号无刷电机4转轴固定二号空中旋翼2。一号无刷电机3控制第一空中旋翼1正转，二号无刷电机4控制第二空中旋翼2反转。该两旋翼无人飞船船体上方的一号无刷电机3、二号无刷电机4和尾部下方的1个无刷电机7的油门值为0时，电机静止，油门值为1000时，电机达到最高转速。伺服电机油门值为500时，伺服电机转轴角度为90度，即一号伺服电机5、二号伺服电机6转轴上固定的一号无刷电机3、二号无刷电机4转轴垂直于船底，当伺服电机油门值为0时，伺服电机转轴角度为0度，即一号伺服电机5转轴上固定的一号无刷电机3转轴朝向船尾，即二号伺服电机6转轴上固定的二号无刷电机4转轴朝向船头。当伺服电机油门值为1000时，伺服电机转轴角度为180度，即一号伺服电机5转轴上固定的一号无刷电机3转轴朝向船头，即二号伺服电机6转轴上固定的二号无刷电机4转轴朝向船尾。
如图1所示，该空中旋翼与螺旋桨协同驱动无人飞船超声水下探测方法的控制过程如下：
S1、接收控制命令得到探测定点位置(x d,y d)。
S2、使用飞行的方式到达探测定点(x d,y d)。控制无人飞船飞行步骤为：起飞、平飞、降落。
起飞：无人飞船控制一号空中旋翼1、二号空中旋翼2产生推力F z，推动无人飞船离开水面。平飞：控制无人飞船上方空中旋翼1、二号空中旋翼2产生翻滚角力矩
Figure PCTCN2020113034-appb-000049
和俯仰角力矩τ θ，改变无人飞船翻滚角和俯仰角，无人飞船空中旋翼1、二号空中旋翼2转动产生的推力F z因为翻滚角和俯仰角的变化产生水平的推力，使无人飞船水平飞行。降落：减小推力F z。其中无人飞船距离水面高度由分布在船底的超声微阵列得到，无人飞船当前水平位置由卫星定位仪得到。
S3、到达探测定点(x d,y d)后，控制一号空中旋翼1、二号空中旋翼2和螺旋桨8静止一段时间，使用姿态仪测量记录无人飞船的(偏航角，俯仰角)，并删除偏航角，俯仰角较小的值，得到n组数据，由下式统计得到波浪运动方向和无人飞船船体的夹角α：
Figure PCTCN2020113034-appb-000050
其中
Figure PCTCN2020113034-appb-000051
为第i组无人飞船偏航角，θ i为第i组无人飞船俯仰角，n为数据个数。
S4、控制无人飞船上方的一号空中旋翼1、二号空中旋翼2产生偏航角力矩τ ψ，使无人飞船顺时针旋转
Figure PCTCN2020113034-appb-000052
此时无人飞船朝向与波浪运动方向垂直。
S5、控制无人飞船在探测定点周围航行。控制无人飞船水面航行步骤为：控制无人飞船尾部下方的螺旋桨转动，提供向前推力F f，推动无人飞船向前航行，控制无人飞船上方的一号空中旋翼1、二号空中旋翼2产生偏航角力矩τ ψ和推力F z，产生的偏航角力矩τ ψ用来控制航行方向，产生的推力F z用来控制吃水量，无人飞船当前吃水量由分布在船底的压力计得到。
S6、控制超声微阵列发送探测信号，根据接收到的探测信号，计算水域参数：基于超声接收回波与发射波信号的频偏计算水流速度；基于超声接收回波与发射波信号的时延计算水深；基于超声接收回波与发射波信号的时延、反射系数、波达方向等参数，结合无人飞船的水面地理位置，反演水底的地形地貌。
S7、在控制超声微阵列采集水域参数时，保持无人飞船姿态。保持无人飞船姿态过程为：无人飞船以高频率采集姿态仪，得到无人飞船姿态、当检测到无人飞船姿态发生微小变化时，即刻控制一号空中旋翼1、二号 空中旋翼2产生翻滚角力矩
Figure PCTCN2020113034-appb-000053
俯仰角力矩τ θ、偏航角力矩τ ψ；翻滚角力矩
Figure PCTCN2020113034-appb-000054
俯仰角力矩τ θ、偏航角力矩τ ψ分别用于纠正无人飞船翻转角、俯仰角、偏航角。
S8、若需要进行扫描探测，无人飞船控制一号空中旋翼1、二号空中旋翼2产生翻滚角力矩
Figure PCTCN2020113034-appb-000055
偏航角力矩τ ψ，旋转无人飞船至指定翻滚角、指定偏航角；无人飞船船底超声微阵列会随着无人飞船的旋转而改变探测方向。并返回步骤S6。
S9、判断是否完成该定点周围水域环境探测，若否，返回步骤S5移动至该定点周围水域的另一位置进行探测。若是，返回步骤S1进行下一个探测点的水域探测。
其中，推力F z、翻滚角力矩
Figure PCTCN2020113034-appb-000056
俯仰角力矩τ θ、偏航角力矩τ ψ是通过控制分布在无人飞船上方一号空中旋翼1、二号空中旋翼2的转速和朝向产生的；使无人飞船产生推力F z、翻滚角力矩
Figure PCTCN2020113034-appb-000057
俯仰角力矩τ θ、偏航角力矩τ ψ时，对应的无刷电机油门值和伺服电机油门值为：
Figure PCTCN2020113034-appb-000058
Figure PCTCN2020113034-appb-000059
s 1＝-τ θ+τ ψ+500         公式(3-1)
s 2＝τ θ+τ ψ+500           公式(3-2)
其中，m 1为一号无刷电机3的油门值，m 2为二号无刷电机4的油门值，s 1为一号伺服电机5的油门值，s 2为二号伺服电机6的油门值。
其中，向前推力F f是通过控制分布在无人飞船尾部下方的螺旋桨转速产生的；螺旋桨固定在一个水下无刷电机上，水下无刷电机油门值决定螺 旋桨转速；使无人飞船产生向前的推力F f时，对应的无刷电机油门值为：
mu＝T f           公式(4)
其中mu为无人飞船尾部下方的水下无刷电机7的油门值。
综上所述，本发明通过控制无人飞船空中旋翼产生的力矩来平衡无人飞船，保持超声微阵列探测方向，提高探测精度；无人飞船空中旋翼产生的力矩还可用来主动改变无人飞船姿态，进而改变超声微阵列探测方向，实现扫描探测的功能；无人飞船空中旋翼产生的偏航角力矩和向上的推力可结合螺旋桨，实现控制吃水量的水面航行任务；无人飞船空中旋翼转动产生推力控制无人飞船飞行，飞行所受阻力小于水面航行阻力，运动速度快。
上述实施例为本发明较佳的实施方式，但本发明的实施方式并不受上述实施例的限制，其他的任何未背离本发明的精神实质与原理下所作的改变、修饰、替代、组合、简化，均应为等效的置换方式，都包含在本发明的保护范围之内。

Claims (9)

  1. 一种空中旋翼与螺旋桨协同驱动无人飞船超声水下探测方法，其特征在于，包括以下步骤：
    S1、接收控制命令得到探测定点位置；
    S2、使用飞行的方式到达探测定点；
    S3、到达探测定点后，控制空中旋翼和螺旋桨静止一段时间，并使用姿态仪测量记录无人飞船的姿态变化率，统计波浪运动方向；
    S4、控制无人飞船朝向垂直于波浪运动方向；
    S5、控制无人飞船在探测定点周围航行；
    S6、控制超声微阵列采集水域参数；
    S7、在控制超声微阵列采集水域参数时，保持无人飞船姿态；
    S8、若需要进行扫描探测，改变无人飞船翻滚角和偏航角并进行保持，并返回步骤S6；
    S9、判断是否完成该定点周围水域环境探测，若否，返回步骤S5移动至该定点周围水域的另一位置进行探测；若是，返回步骤S1进行下一个探测点的水域探测。
  2. 根据权利要求1所述的空中旋翼与螺旋桨协同驱动无人飞船超声水下探测方法，其特征在于，所述步骤S1的探测定点位置是来自于远程用户指定的探测定点位置或者是来自于无人飞船根据路径规划得到的下一次探测定点的位置。
  3. 根据权利要求1所述的空中旋翼与螺旋桨协同驱动无人飞船超声水下探测方法，其特征在于，所述步骤S2的过程为：
    无人飞船控制无人飞船上方空中旋翼转动提供推力F z，推动无人飞船离开水面，其中无人飞船距离水面高度由分布在船底的超声微阵列得到，此时控制各个空中旋翼转动速度的无刷电机油门值和控制各个空中旋翼朝向的伺服电机油门值为：
    Figure PCTCN2020113034-appb-100001
    Figure PCTCN2020113034-appb-100002
    其中m i为第i个无刷电机油门值，s i为第i个伺服电机油门值，
    Figure PCTCN2020113034-appb-100003
    为无刷电机推力控制系数，
    Figure PCTCN2020113034-appb-100004
    为伺服电机零偏控制系数；
    无人飞船再控制无人飞船上方空中旋翼产生翻滚角力矩
    Figure PCTCN2020113034-appb-100005
    和俯仰角力矩τ θ，改变无人飞船翻滚角和俯仰角，无人飞船上方空中旋翼转动产生的推力F z因为翻滚角和俯仰角的变化产生水平的推力，使无人飞船水平飞行，其中无人飞船当前水平位置由卫星定位仪得到，此时控制各个空中旋翼转动速度的无刷电机油门值和控制各个空中旋翼朝向的伺服电机油门值为：
    Figure PCTCN2020113034-appb-100006
    Figure PCTCN2020113034-appb-100007
    其中m i为第i个无刷电机油门值，s i为第i个伺服电机油门值，
    Figure PCTCN2020113034-appb-100008
    为无刷电机推力控制系数，
    Figure PCTCN2020113034-appb-100009
    为伺服电机零偏控制系数，
    Figure PCTCN2020113034-appb-100010
    为无刷电机翻滚角力矩控制系数，
    Figure PCTCN2020113034-appb-100011
    为无刷电机俯仰角力矩控制系数，
    Figure PCTCN2020113034-appb-100012
    为伺服电机翻滚角力矩控制系数，
    Figure PCTCN2020113034-appb-100013
    为伺服电机俯仰角力矩控制系数。
  4. 根据权利要求1所述的空中旋翼与螺旋桨协同驱动无人飞船超声水下探测方法，其特征在于,所述步骤S3的过程为：使用姿态仪测量记录无人飞船的偏航角和俯仰角，并删除偏航角和俯仰角小于阈值的值，得到n组数据，由下式统计得到波浪运动方向和无人飞船船体的夹角α：
    Figure PCTCN2020113034-appb-100014
    其中
    Figure PCTCN2020113034-appb-100015
    为第i组无人飞船偏航角，θ i为第i组无人飞船俯仰角，n为数据个数。
  5. 根据权利要求1所述的空中旋翼与螺旋桨协同驱动无人飞船超声水下探测方法，其特征在于，所述步骤S4的过程为：控制无人飞船上方的空中旋翼产生偏航角力矩τ ψ，使无人飞船顺时针旋转
    Figure PCTCN2020113034-appb-100016
    此时无人飞船朝向与波浪运动方向垂直，其中，α为波浪运动方向和无人飞船船体的夹角，此时控制各个空中旋翼转动速度的无刷电机油门值和控制各个空中旋翼朝向的伺服电机油门值为：
    Figure PCTCN2020113034-appb-100017
    Figure PCTCN2020113034-appb-100018
    其中m i为第i个无刷电机油门值，s i为第i个伺服电机油门值，
    Figure PCTCN2020113034-appb-100019
    为伺服电机零偏控制系数，
    Figure PCTCN2020113034-appb-100020
    为无刷电机偏航角力矩控制系数，
    Figure PCTCN2020113034-appb-100021
    为伺服电机偏航角力矩控制系数。
  6. 根据权利要求1所述的空中旋翼与螺旋桨协同驱动无人飞船超声水下探测方法，其特征在于，所述步骤S5的过程为：控制无人飞船尾部下方的螺旋桨转动，提供向前推力F f，推动无人飞船向前航行，控制无人飞船上方的空中旋翼产生偏航角力矩τ ψ和推力F z，产生的偏航角力矩τ ψ用来控制航行方向，产生的推力F z用来控制吃水量，其中无人飞船当前吃水量由分布在船底的压力计得到，此时控制各个空中旋翼转动速度的无刷电机油门值、控制各个空中旋翼朝向的伺服电机油门值和控制螺旋桨转动的水下无刷电机油门值为：
    Figure PCTCN2020113034-appb-100022
    Figure PCTCN2020113034-appb-100023
    mu＝kT f    公式(10)
    其中m i为第i个无刷电机油门值，s i为第i个伺服电机油门值，
    Figure PCTCN2020113034-appb-100024
    为无刷电机推力控制系数，
    Figure PCTCN2020113034-appb-100025
    为伺服电机零偏控制系数，
    Figure PCTCN2020113034-appb-100026
    为无刷电机偏航角力矩控制系数，
    Figure PCTCN2020113034-appb-100027
    为伺服电机偏航角力矩控制系数，mu为水下无刷电机油门值，k为向前推力控制系数。
  7. 根据权利要求1所述的空中旋翼与螺旋桨协同驱动无人飞船超声水下探测方法，其特征在于，所述步骤S6的过程为：超声微阵列发送探测信号，根据接收到的探测信号，计算水域参数；基于超声接收回波与发射波信号的频偏计算水流速度；基于超声接收回波与发射波信号的时延计算水深；基于超声接收回波与发射波信号的时延、反射系数、波达方向参数，结合无人飞船的水面地理位置，反演水底的地形地貌。
  8. 根据权利要求1所述的空中旋翼与螺旋桨协同驱动无人飞船超声水下探测方法，其特征在于，所述步骤S7的过程为：无人飞船以高频率采集姿态仪，得到无人飞船姿态、当检测到无人飞船姿态发生微小变化时，即刻控制空中旋翼产生翻滚角力矩
    Figure PCTCN2020113034-appb-100028
    俯仰角力矩τ θ、偏航角力矩τ ψ；翻滚角力矩
    Figure PCTCN2020113034-appb-100029
    俯仰角力矩τ θ、偏航角力矩τ ψ分别用于纠正无人飞船翻转角、俯仰角、偏航角，此时控制各个空中旋翼转动速度的无刷电机油门值和控制各个空中旋翼朝向的伺服电机油门值为：
    Figure PCTCN2020113034-appb-100030
    Figure PCTCN2020113034-appb-100031
    其中m i为第i个无刷电机油门值，s i为第i个伺服电机油门值，
    Figure PCTCN2020113034-appb-100032
    为 伺服电机零偏控制系数，
    Figure PCTCN2020113034-appb-100033
    为无刷电机翻滚角力矩控制系数，
    Figure PCTCN2020113034-appb-100034
    为无刷电机俯仰角力矩控制系数，
    Figure PCTCN2020113034-appb-100035
    为无刷电机偏航角力矩控制系数，
    Figure PCTCN2020113034-appb-100036
    为伺服电机翻滚角力矩控制系数，
    Figure PCTCN2020113034-appb-100037
    为伺服电机俯仰角力矩控制系数，
    Figure PCTCN2020113034-appb-100038
    为伺服电机偏航角力矩控制系数。
  9. 根据权利要求1所述的空中旋翼与螺旋桨协同驱动无人飞船超声水下探测方法，其特征在于，所述步骤S8的过程为：无人飞船控制空中旋翼产生翻滚角力矩
    Figure PCTCN2020113034-appb-100039
    偏航角力矩τ ψ，旋转无人飞船至指定翻滚角、指定偏航角，无人飞船船底超声微阵列会随着无人飞船的旋转而改变探测方向，此时控制各个空中旋翼转动速度的无刷电机油门值和控制各个空中旋翼朝向的伺服电机油门值为：
    Figure PCTCN2020113034-appb-100040
    Figure PCTCN2020113034-appb-100041
    其中m i为第i个无刷电机油门值，s i为第i个伺服电机油门值，
    Figure PCTCN2020113034-appb-100042
    为伺服电机零偏控制系数，
    Figure PCTCN2020113034-appb-100043
    为无刷电机翻滚角力矩控制系数，
    Figure PCTCN2020113034-appb-100044
    为无刷电机俯仰角力矩控制系数，
    Figure PCTCN2020113034-appb-100045
    为无刷电机偏航角力矩控制系数，
    Figure PCTCN2020113034-appb-100046
    为伺服电机翻滚角力矩控制系数，
    Figure PCTCN2020113034-appb-100047
    为伺服电机俯仰角力矩控制系数，
    Figure PCTCN2020113034-appb-100048
    为伺服电机偏航角力矩控制系数。
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