# Fast Realization of Collision Risk Calculation in Power Line Patrol Flight Based on CUDA

Authors: Jiandong Liao; Ying Zhang; Guoqiang Li
Journal: Mathematical Problems in Engineering
 (2021)

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## Abstract

In this paper, a low-altitude risk collision model based on CUDA is designed to avoid problems that may occur in the process of unmanned aerial power patrol. By collecting and analyzing the data related to the unmanned aerial power patrol task, the collision accident probability is extracted and the probability distribution model and the influence of weather factors on the collision risk are combined. The model validates the collision risk of unmanned aerial vehicles in different locations and verifies the reliability and computational efficiency of the model based on different operating systems. The model algorithm can effectively improve the response time to avoid collision risk during UAV patrol and reduce the risk level of UAV collision accidents.


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## Body

## 1. Introduction

Due to many distribution points, wide area, complex terrain, and harsh natural environment, traditional manual inspection methods are becoming more and more expensive, time-consuming, and risky, which increasingly cannot meet the needs of safe and stable operation of smart grids. In recent years, the State Grid Company has vigorously promoted the application of a new patrol mode in which transmission line helicopters, unmanned aerial vehicles, and manual patrols work together. In the popularization of applications, the operation efficiency is effectively improved, the site security risk is reduced, and the line is reduced. The rush repair time of road outage enriches the means of operation and maintenance of power network and effectively guarantees power network with safe and stable operation. However, the security risks of unmanned aerial vehicles are gradually highlighted.Scholars at home and abroad have conducted a lot of research on the risk of aircraft flight collision in low-altitude airspace [1]; based on the concept of free flight, the positioning error of aircraft under the influence of anticollision system, wind, and other factors were analyzed. Meanwhile, a data fusion algorithm combined with inertial navigation and satellite positioning was proposed to periodically correct the positioning error. In [2], the event collision risk assessment model was adopted to assess the collision risk of aircraft in flight and based on horizontal and vertical directions, the conflict resolution methods were given. In [3], the longitudinal separation between aircrafts and the lateral separation of parallel routes based on ADS-B signal monitoring mode were proposed. At the same time, the flight separation standard in the flight training state was provided in combination with the actual flight training requirements of flight training institutions. In [4], the three-dimensional Monte Carlo location distribution model of UAV was explored to evaluate the collision risk of UAV to civil aircraft in the airport. By establishing the boundary of warning area, the collision caused by UAV eyewitness in various operation scenarios was determined. In [5], through the statistics of the day and night situation of birds, the characteristics of their main flight height and range were analyzed. In addition, the collision probability of bird activities on transmission lines and wind power generation facilities was offered. The study in [6] analyzed the collision risk of the current flight separation standard based on ADS-C control in the cross ocean route flight, established the collision risk model of adjacent flights, and obtained the conclusion that the current flight separation standard can be further reduced by solving the collision risk of two adjacent aircraft, so as to improve the operation efficiency and reduce the flight cost. Although domestic and foreign scholars have conducted in-depth research on the collision risk of aircraft, there are still few research studies on the collision risk between UAV and transmission lines and transmission towers and surrounding buildings in the aspect of UAV power line inspection. Different from civil aircraft or other types such as general aviation photography, UAV power line patrol has a narrow operation range and complex surrounding environment and it is greatly affected by the terrain and airflow. Due to the particularity of operation nature, UAV needs to fly continuously around the transmission line and transmission tower.In order to reduce the collision accident occurred during the UAV power inspection, by combining the probability distribution model of the UAV inspection and the influence of the meteorological factors of the power corridor on the collision hazard, the CUDA-based low-altitude hazard collision model of the UAV inspection is designed to effectively make up for the shortage of current UAV obstacle avoidance measures in the power inspection operation, improve the safety performance of the UAV, and provide a guarantee for the smooth implementation of the UAV inspection work.


## 2. UAV CUDA Collision Risk Construction

### 2.1. CUDA Overview

The basic framework of the CUDA collision model is Reich model. The basic principle of Reich model [7] could make a cuboid collision box for aircraft along its longitudinal axis, horizontal axis, and vertical axis. The length, width, and height of the cuboid refer to the length of the aircraft on this axis. After the collision box is enlarged, an adjacent layer is designed around aircraft A. Aircraft B is regarded as a particle. In terms of the positioning error in the actual operation process, when aircraft B enters the adjacent layer of aircraft A, it is considered that there is a collision risk in the direction of longitudinal axis, horizontal axis, and vertical axis between A and B, which is the lowest acceptable collision risk in aircraft operation. The length, width, and height of the adjacent layer are the longitudinal, lateral, and vertical separation standards of the collision box. With the continuous development and improvement of scholars in various countries [8], the Reich model has also been applied in various subdivision fields of aviation direction. In recent years [9–13], the Reich model was mainly applied in free flight collision risk research, short-range parallel runway approach and landing risk analysis, wake interval standard impact assessment, and so on.CPU is good at flow control and logic processing, irregular data structure, unpredictable storage structure, single thread program, and branch intensive algorithm. When parallel computing is implemented in the regular data structure and predictable storage mode, GPU has more advantages [14]. CUDA is a general parallel computing architecture developed by NVIDIA, which enables GPU to solve complex computing problems through multiple CUDAs, which includes the CUDA instruction set architecture (ISA) and parallel computing engine in GPU. In this paper, the CPU and GPU were combined in the heterogeneous computing mode. The CPU was used to complete the serial computing part, including data initialization and final integration. Furthermore, the GPU was used to complete the parallel computing part to complete the collision risk calculation of UAV in multiple possible locations.


### 2.2. Establishment of the Collision Risk Model for UAV Power Line Patrol

Reich model is the main body of the collision risk model. This paper makes the following settings, and some variables are shown in Figure1:(1)
This model only considers the collision risk of one UAV in the power patrol environment and does not consider the multiple collision risks between UAVs or between multiple UAVs and the surrounding environment.(2)
The positioning accuracy of UAV still remains unchanged, and the UAV flies in a straight line at a relatively stable speed.(3)
Vx,Vy, and Vz are the velocity of UAV in the longitudinal axis, horizontal axis, and vertical axis and remain stable.(4)
λx,λy, and λz are half of the length of collision box of UAV in longitudinal, horizontal, and vertical directions.(5)
Sx,Sy, and Sz are half of the length of the adjacent layer of UAV in the longitudinal, horizontal, and vertical directions.(6)
The location error distributions of UAV in the longitudinal, horizontal, and vertical directions are independent of each other and obey their normal distribution, respectively.(7)
O=x1,y1,z1,x2,y2,z2,x3,y3,z3,…,xn,yn,zn represents the set of obstacles in the aircraft patrol operation environment. Each obstacle is approximately composed of several discrete spheres with the diameter and the set of the centers of the spheres. If there is no collision risk between these discrete points and the UAV, there is no collision risk between the obstacle and the UAV.Figure 1
Schematic diagram of UAV patrol operation.It is assumed that the UAV is flying at a uniform speed in a stable wind environment, as displayed in Figure2.Figure 2
UAV trajectory.Because the positioning accuracy of UAV stands for independent normal distribution on the coordinate axis, its density function is(1)fx=12πσxexp−x−μxt22σx2,fy=12πσyexp−y−μyt22σy2,fy=12πσzexp−y−μzt22σz2,where μtx,y,z is the position of UAV at time t, under the condition of static wind,(2)μtx,y,z=x0,y0,z0+Vx,Vy,Vzt.When there is wind in the patrol operation environment, the components of steady wind speed on the three coordinate axes areWx,Wy, and Wz. The components of gust induced turbulence wind speed on the three coordinate axes are Gx,Gy, and Gz, where Gz marks the low-level wind shear in the vertical direction due to thunderstorm, front, terrain, and other environmental factors.(3)μGtx,y,z=∫0ΔtGxudu,∫0ΔtGzudu,∫0ΔtGzudu,It is assumed that the turbulent wind speed follows the independent normal distributionsNx0,δx, Ny0,δy, and Nz0,δz in each direction of the coordinate axis. It can be inferred that the actual instantaneous position of UAV at a certain moment is as follows:(4)μtx,y,z=x1,y1,z1+Vx+Wx,Vy+Wy,Vzt+μGtx,y,z,μGtx,y,z=∫0△tGxudu,∫0△tGzudu,∫0△tGzudu,Gx∈Nx0,δx,Gy∈Ny0,δy,Gz∈Nz0,δz.Without losing generality, due to the collision relationship between the UAV and building in the two-dimensional plane without turbulence, the following conclusions can be drawn.As shown in Figure2, the shadow part refers to the actual running path of the UAV critical layer. For a known sphere, if there is no intersection with the shadow part, it is determined that the sphere collides with the UAV. According to Figure 3, the angle of UAV's actual running direction:(5)θr=ArctanVy+WyVx+Wx.Figure 3
Schematic diagram of UAV motion equation.The course of UAV is(6)θh=ArctanVyVx.The angle between the rectangular diagonal of UAV critical layer and UAV running direction is(7)θS=ArctanSySx+θr−θh=ArctanSySx+arctanVy+WyVx+Wx−ArctanVyVx.The width of the shadow area is(8)Sxy=sinθSSx2+Sy2=sinArctanSySx+arctanVy+WyVx+Wx−arctanVyVxSx2+Sy2.The central line equation of the long side of the shadow area can be calculated:(9)y−μyt=Vy+WyVx+Wxx−μxt.After the equations are sorted out, we can obtain(10)y=Vy+WyVx+Wxx−μxt+μyt.For the center point of any discrete sphere, the distance from the center line to the long side of the shadow area is(11)Disxy=Vy+Wy/Vx+Wxxi−μxt+μyt−yi1+Vy+Wy/Vx+Wx2.To maintain the risk of collision between the UAV and building within the acceptable range, it is necessary to meet the requirements of(12)Disxy≥r+Sxy2.In the vertical direction, because the vertical stable wind speed is 0, then the width of the shadow area isSz. In order to keep the collision risk between the UAV and building in an acceptable range, it is necessary to meet the following requirements:(13)Disz≥r+Sz2.Due to the existence of turbulence, whether in the vertical or horizontal direction,Dis will have a certain error. According to the formula derived above, in the case of turbulence, it needs to meet the requirements to keep the collision risk between UAV and building within the acceptable range.(14)Disxy+μGtx,y≥r+Sxy2,Disz+μGtz≥r+Sz2.In the public air transportation of large aircraft, ICAO has made corresponding target risk level for longitudinal, lateral, and vertical safety separation. For example, ICAO has stipulated that the corresponding target risk level for longitudinal, lateral, and vertical safety separation conditions are5×10−9. Therefore, an acceptable safety target risk level should be established in the UAV power line patrol operation. It is assumed that the turbulence in power line patrol operation follows normal distribution GxN0,1,GzN0,1, and GzN0,1. The target risk levels corresponding to longitudinal, lateral, and vertical safety intervals are Rx,Ry,andRz, and the corresponding risk level in at least one direction should not exceed 5×10−9.In order to achieve the corresponding risk level of no more than5×10−9, the probability of UAV appearing in the adjacent layers μtx−Sx,μtx+Sx,μty−Sy,μty+Sy,andμtz−Sz,μtz+Sz in each direction should be no less than 1−5×10−9 at least. Therefore, the collision risk of UAV can be controlled by judging the position relationship between adjacent floors and buildings. In the standard normal distribution, the probability between −5.84717 and 5.84717 is 1−5×10−9.Therefore, the position of the adjacent layer is(15)μtx−λx−5.84717Gx2,μtx+λx+5.84717Gx2,μty−λy−5.84717Gy2,μty+λy+5.84717Gy2,μtz−λz−5.84717Gz2,μtz+λz+5.84717Gz2.


## 2.1. CUDA Overview

The basic framework of the CUDA collision model is Reich model. The basic principle of Reich model [7] could make a cuboid collision box for aircraft along its longitudinal axis, horizontal axis, and vertical axis. The length, width, and height of the cuboid refer to the length of the aircraft on this axis. After the collision box is enlarged, an adjacent layer is designed around aircraft A. Aircraft B is regarded as a particle. In terms of the positioning error in the actual operation process, when aircraft B enters the adjacent layer of aircraft A, it is considered that there is a collision risk in the direction of longitudinal axis, horizontal axis, and vertical axis between A and B, which is the lowest acceptable collision risk in aircraft operation. The length, width, and height of the adjacent layer are the longitudinal, lateral, and vertical separation standards of the collision box. With the continuous development and improvement of scholars in various countries [8], the Reich model has also been applied in various subdivision fields of aviation direction. In recent years [9–13], the Reich model was mainly applied in free flight collision risk research, short-range parallel runway approach and landing risk analysis, wake interval standard impact assessment, and so on.CPU is good at flow control and logic processing, irregular data structure, unpredictable storage structure, single thread program, and branch intensive algorithm. When parallel computing is implemented in the regular data structure and predictable storage mode, GPU has more advantages [14]. CUDA is a general parallel computing architecture developed by NVIDIA, which enables GPU to solve complex computing problems through multiple CUDAs, which includes the CUDA instruction set architecture (ISA) and parallel computing engine in GPU. In this paper, the CPU and GPU were combined in the heterogeneous computing mode. The CPU was used to complete the serial computing part, including data initialization and final integration. Furthermore, the GPU was used to complete the parallel computing part to complete the collision risk calculation of UAV in multiple possible locations.


## 2.2. Establishment of the Collision Risk Model for UAV Power Line Patrol

Reich model is the main body of the collision risk model. This paper makes the following settings, and some variables are shown in Figure1:(1)
This model only considers the collision risk of one UAV in the power patrol environment and does not consider the multiple collision risks between UAVs or between multiple UAVs and the surrounding environment.(2)
The positioning accuracy of UAV still remains unchanged, and the UAV flies in a straight line at a relatively stable speed.(3)
Vx,Vy, and Vz are the velocity of UAV in the longitudinal axis, horizontal axis, and vertical axis and remain stable.(4)
λx,λy, and λz are half of the length of collision box of UAV in longitudinal, horizontal, and vertical directions.(5)
Sx,Sy, and Sz are half of the length of the adjacent layer of UAV in the longitudinal, horizontal, and vertical directions.(6)
The location error distributions of UAV in the longitudinal, horizontal, and vertical directions are independent of each other and obey their normal distribution, respectively.(7)
O=x1,y1,z1,x2,y2,z2,x3,y3,z3,…,xn,yn,zn represents the set of obstacles in the aircraft patrol operation environment. Each obstacle is approximately composed of several discrete spheres with the diameter and the set of the centers of the spheres. If there is no collision risk between these discrete points and the UAV, there is no collision risk between the obstacle and the UAV.Figure 1
Schematic diagram of UAV patrol operation.It is assumed that the UAV is flying at a uniform speed in a stable wind environment, as displayed in Figure2.Figure 2
UAV trajectory.Because the positioning accuracy of UAV stands for independent normal distribution on the coordinate axis, its density function is(1)fx=12πσxexp−x−μxt22σx2,fy=12πσyexp−y−μyt22σy2,fy=12πσzexp−y−μzt22σz2,where μtx,y,z is the position of UAV at time t, under the condition of static wind,(2)μtx,y,z=x0,y0,z0+Vx,Vy,Vzt.When there is wind in the patrol operation environment, the components of steady wind speed on the three coordinate axes areWx,Wy, and Wz. The components of gust induced turbulence wind speed on the three coordinate axes are Gx,Gy, and Gz, where Gz marks the low-level wind shear in the vertical direction due to thunderstorm, front, terrain, and other environmental factors.(3)μGtx,y,z=∫0ΔtGxudu,∫0ΔtGzudu,∫0ΔtGzudu,It is assumed that the turbulent wind speed follows the independent normal distributionsNx0,δx, Ny0,δy, and Nz0,δz in each direction of the coordinate axis. It can be inferred that the actual instantaneous position of UAV at a certain moment is as follows:(4)μtx,y,z=x1,y1,z1+Vx+Wx,Vy+Wy,Vzt+μGtx,y,z,μGtx,y,z=∫0△tGxudu,∫0△tGzudu,∫0△tGzudu,Gx∈Nx0,δx,Gy∈Ny0,δy,Gz∈Nz0,δz.Without losing generality, due to the collision relationship between the UAV and building in the two-dimensional plane without turbulence, the following conclusions can be drawn.As shown in Figure2, the shadow part refers to the actual running path of the UAV critical layer. For a known sphere, if there is no intersection with the shadow part, it is determined that the sphere collides with the UAV. According to Figure 3, the angle of UAV's actual running direction:(5)θr=ArctanVy+WyVx+Wx.Figure 3
Schematic diagram of UAV motion equation.The course of UAV is(6)θh=ArctanVyVx.The angle between the rectangular diagonal of UAV critical layer and UAV running direction is(7)θS=ArctanSySx+θr−θh=ArctanSySx+arctanVy+WyVx+Wx−ArctanVyVx.The width of the shadow area is(8)Sxy=sinθSSx2+Sy2=sinArctanSySx+arctanVy+WyVx+Wx−arctanVyVxSx2+Sy2.The central line equation of the long side of the shadow area can be calculated:(9)y−μyt=Vy+WyVx+Wxx−μxt.After the equations are sorted out, we can obtain(10)y=Vy+WyVx+Wxx−μxt+μyt.For the center point of any discrete sphere, the distance from the center line to the long side of the shadow area is(11)Disxy=Vy+Wy/Vx+Wxxi−μxt+μyt−yi1+Vy+Wy/Vx+Wx2.To maintain the risk of collision between the UAV and building within the acceptable range, it is necessary to meet the requirements of(12)Disxy≥r+Sxy2.In the vertical direction, because the vertical stable wind speed is 0, then the width of the shadow area isSz. In order to keep the collision risk between the UAV and building in an acceptable range, it is necessary to meet the following requirements:(13)Disz≥r+Sz2.Due to the existence of turbulence, whether in the vertical or horizontal direction,Dis will have a certain error. According to the formula derived above, in the case of turbulence, it needs to meet the requirements to keep the collision risk between UAV and building within the acceptable range.(14)Disxy+μGtx,y≥r+Sxy2,Disz+μGtz≥r+Sz2.In the public air transportation of large aircraft, ICAO has made corresponding target risk level for longitudinal, lateral, and vertical safety separation. For example, ICAO has stipulated that the corresponding target risk level for longitudinal, lateral, and vertical safety separation conditions are5×10−9. Therefore, an acceptable safety target risk level should be established in the UAV power line patrol operation. It is assumed that the turbulence in power line patrol operation follows normal distribution GxN0,1,GzN0,1, and GzN0,1. The target risk levels corresponding to longitudinal, lateral, and vertical safety intervals are Rx,Ry,andRz, and the corresponding risk level in at least one direction should not exceed 5×10−9.In order to achieve the corresponding risk level of no more than5×10−9, the probability of UAV appearing in the adjacent layers μtx−Sx,μtx+Sx,μty−Sy,μty+Sy,andμtz−Sz,μtz+Sz in each direction should be no less than 1−5×10−9 at least. Therefore, the collision risk of UAV can be controlled by judging the position relationship between adjacent floors and buildings. In the standard normal distribution, the probability between −5.84717 and 5.84717 is 1−5×10−9.Therefore, the position of the adjacent layer is(15)μtx−λx−5.84717Gx2,μtx+λx+5.84717Gx2,μty−λy−5.84717Gy2,μty+λy+5.84717Gy2,μtz−λz−5.84717Gz2,μtz+λz+5.84717Gz2.


## 3. Case Simulation Verification

The process of solving the model is shown in Figure4.Figure 4
Model solving process.


### 3.1. Calculation Conditions

(1)
Initial position of the UAV(2)
UAV dimensions(3)
Steady wind speed(4)
Turbulent wind speed(5)
Velocity vector of the UAVThe location of the building/obstacle is illustrated in Figure5. To simplify the calculation, the obstacle is surrounded by 2379 discrete spheres.Figure 5
Schematic diagram of the initial state position of the model.The position information of discrete points is shown in Table1.Table 1
Location of discrete points of buildings.
Serial numberX-axisY-axisZ-axisSerial numberX-axisY-axisZ-axis1307.63310.631.501200305.37329.3716.002308.28311.282.001201305.37329.3716.503308.69311.692.501202305.45329.4517.004308.88311.883.001203305.70329.7017.505308.92311.923.501204306.19330.1918.006308.93311.934.001205306.91330.9118.507309.03312.034.501206307.82331.8219.008309.31312.315.001207308.81332.8119.509309.82312.825.501208309.77333.7720.0010310.58313.586.001209310.57334.5720.50… …… …600306.19319.698.502370292.20337.2016.00601306.50320.009.002371292.20337.2016.50602306.61320.119.502372292.28337.2817.00603306.62320.1210.002373292.53337.5317.50604306.65320.1510.502374293.02338.0218.00605306.82320.3211.002375293.74338.7418.50606307.20320.7011.502376294.65339.6519.00607307.82321.3212.002377295.64340.6419.50608308.66322.1612.502378296.60341.6020.00609309.63323.1313.002379297.40342.4020.50The CPU model used in this experiment is i7-8550u, with the main frequency being 1.80 GHz. NVIDIA GeForce MX 150 is used as the graphics card. There are three SMs (streaming multiprocessors) in the card, and each SM can schedule up to 2048 threads.


### 3.2. Calculation Results

By calculating the risk of UAV power line patrol operation, the collision risk results are obtained at different times, as demonstrated in Figures6–9, in which the dark part indicates the existence of collision risk.Figure 6
Collision risk at 650 seconds.Figure 7
Collision risk at 675 seconds.Figure 8
Collision risk at 700 seconds.Figure 9
Collision risk at 750 seconds.By recording the time spent in each run of the program, the calculation efficiency of computing collision risk using CPU is only compared with that using CPU + CUDA hybrid parallel computing, as shown in Table2.Table 2
Comparison of CPU only and CPU + CUDA algorithm efficiency results.
Number of discrete points in simulation environmentComputation time (MS)CPU onlyCPU + CUDAShortened time ratio (%)23791554173.5595166717289.2738064298310596.48


## 3.1. Calculation Conditions

(1)
Initial position of the UAV(2)
UAV dimensions(3)
Steady wind speed(4)
Turbulent wind speed(5)
Velocity vector of the UAVThe location of the building/obstacle is illustrated in Figure5. To simplify the calculation, the obstacle is surrounded by 2379 discrete spheres.Figure 5
Schematic diagram of the initial state position of the model.The position information of discrete points is shown in Table1.Table 1
Location of discrete points of buildings.
Serial numberX-axisY-axisZ-axisSerial numberX-axisY-axisZ-axis1307.63310.631.501200305.37329.3716.002308.28311.282.001201305.37329.3716.503308.69311.692.501202305.45329.4517.004308.88311.883.001203305.70329.7017.505308.92311.923.501204306.19330.1918.006308.93311.934.001205306.91330.9118.507309.03312.034.501206307.82331.8219.008309.31312.315.001207308.81332.8119.509309.82312.825.501208309.77333.7720.0010310.58313.586.001209310.57334.5720.50… …… …600306.19319.698.502370292.20337.2016.00601306.50320.009.002371292.20337.2016.50602306.61320.119.502372292.28337.2817.00603306.62320.1210.002373292.53337.5317.50604306.65320.1510.502374293.02338.0218.00605306.82320.3211.002375293.74338.7418.50606307.20320.7011.502376294.65339.6519.00607307.82321.3212.002377295.64340.6419.50608308.66322.1612.502378296.60341.6020.00609309.63323.1313.002379297.40342.4020.50The CPU model used in this experiment is i7-8550u, with the main frequency being 1.80 GHz. NVIDIA GeForce MX 150 is used as the graphics card. There are three SMs (streaming multiprocessors) in the card, and each SM can schedule up to 2048 threads.


## 3.2. Calculation Results

By calculating the risk of UAV power line patrol operation, the collision risk results are obtained at different times, as demonstrated in Figures6–9, in which the dark part indicates the existence of collision risk.Figure 6
Collision risk at 650 seconds.Figure 7
Collision risk at 675 seconds.Figure 8
Collision risk at 700 seconds.Figure 9
Collision risk at 750 seconds.By recording the time spent in each run of the program, the calculation efficiency of computing collision risk using CPU is only compared with that using CPU + CUDA hybrid parallel computing, as shown in Table2.Table 2
Comparison of CPU only and CPU + CUDA algorithm efficiency results.
Number of discrete points in simulation environmentComputation time (MS)CPU onlyCPU + CUDAShortened time ratio (%)23791554173.5595166717289.2738064298310596.48


## 4. Conclusion

At present, the main application object of Reich model is civil aircraft, rarely involving general aviation. The application scenario is mainly large aircraft public air transportation, while UAV power line patrol has not been studied; The CUDA method is used to calculate the collision risk probability during UAV power patrol inspection, which can effectively reduce the processing time of UAV computing collision risk. In the actual aircraft patrol operation process, wind speed and direction and gust wind speed and direction significantly affect the flight safety of UAV. In this paper, the collision risk model was first proposed and the solution was provided. Also, an algorithm was proposed based on CUDA, because the wind speed and direction of gust are real time and unpredictable, which can calculate the risk of collision probability in real time. Especially in the complex operating environment, the operation efficiency is greatly improved compared with the collision risk calculated by conventional CPU, which enables UAV to avoid obstacles and collision in time.When performing power inspection tasks, the drone wants to effectively avoid the risk of collision, not only from the algorithm calculation time consideration but also from the human-machine ring and other aspects of consideration. The future will continue to study a full range of low-altitude airspace drone power inspection with the collision avoidance methods.



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*Source: 7048145-2021-12-08.xml*