CN113157000A - Flight formation cooperative obstacle avoidance self-adaptive control method based on virtual structure and artificial potential field - Google Patents
Flight formation cooperative obstacle avoidance self-adaptive control method based on virtual structure and artificial potential field Download PDFInfo
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Abstract
The invention relates to a flight formation cooperative obstacle avoidance self-adaptive control method based on a virtual structure and an artificial potential field, belongs to the field of formation flight control, and is used for formation obstacle avoidance control of multiple unmanned aerial vehicles and processing the influence of dynamics uncertainty of an unmanned aerial vehicle model. The method adopts a virtual formation structure and an artificial potential field strategy, and combines a target track of a formation reference point and a formation virtual structure mass point kinematics model to obtain a virtual mass point motion track under collision avoidance and obstacle avoidance as an expected instruction of a closed-loop system. And the control input of the unmanned aerial vehicle is designed by adopting a backstepping method, so that the target tracking control under formation accurate maintenance and effective obstacle avoidance is realized. The dynamics uncertainty of the neural network estimation model is utilized, a serial-parallel model is established to obtain a parallel estimation state, a learning evaluation index of a prediction error mining system is established, and a neural network weight updating law is designed by combining a tracking error. The invention enhances the accuracy of uncertain estimation and provides a new technical approach for improving the formation flight performance.
Description
Technical Field
The invention relates to a multi-aircraft tracking control method, in particular to a flight formation cooperative obstacle avoidance self-adaptive control method based on a virtual structure and an artificial potential field, and belongs to the field of formation flight control.
Background
With the wide application of unmanned aerial vehicles in military and civil use, the flight control technology for formation of multiple unmanned aerial vehicles has important application value in realizing tasks such as cooperative reconnaissance and battle, pesticide spraying and the like. Aiming at multi-unmanned aerial vehicle cooperative tracking control, the strategy based on the virtual structure integrally describes group behaviors and simplifies task description and distribution, and higher formation control accuracy can be obtained. Aiming at collision avoidance and formation obstacle avoidance control of unmanned aerial vehicles between formations, a cooperative control algorithm is designed by combining an artificial potential field and a virtual structure to realize accurate formation maintenance and effective obstacle avoidance. Considering the influence of dynamics uncertainty and nonlinearity existing in an unmanned aerial vehicle system on formation flight tracking performance, an intelligent control algorithm for estimating by using the approximation capability of a neural network is widely researched. However, the current intelligent control can only ensure the stability of the system and neglects the evaluation of the expected nonlinear estimation performance. In order to improve the performance of cooperative tracking control and ensure the nonlinear estimation effect, the research on the compound learning strategy based on parallel estimation has important significance on formation flight safety.
Composite Learning finish-Time Control With Application to Quadrotors (B.xu, IEEE Transactions on Systems, Man, and Cybernetics: Systems, 2018, volume 48, No. 10) designs a Finite-Time neural network Control algorithm aiming at an under-actuated unmanned aerial vehicle, and the research goal of the thesis is to realize the tracking of the unmanned aerial vehicle individual to an expected track instruction. Virtual leaders, intellectual features and coordinated Control of groups (Leonard N E, Fiorelli E, IEEE Conference on Decision and Control, 2001) design a multi-agent formation Control algorithm based on artificial potential fields and Virtual agents. The thesis takes the virtual leader as a reference point, and controls the formation of the multi-agent by adjusting the artificial potential field. However, the control algorithm designed by the paper depends on the dynamic characteristics of the model, and the rapid and stable control of the system is difficult to realize.
Disclosure of Invention
Technical problem to be solved
Aiming at maintaining and avoiding control of formation of multiple unmanned aerial vehicles and considering the influence of model dynamics uncertainty on control precision, the invention provides a flight formation cooperative obstacle avoidance self-adaptive control method based on a virtual structure and an artificial potential field.
Technical scheme
A flight formation cooperative obstacle avoidance self-adaptive control method based on a virtual structure and an artificial potential field is characterized by comprising the following steps:
step 1: adopting a dynamic model of the unmanned aerial vehicle:
wherein x, y, z are positions,roll angle, theta pitch angle, psi yaw angle, m mass, g gravitational acceleration, Ix,Iy,IzFor the inertial matrix, l is the distance from the center of mass of the unmanned aerial vehicle to the center of the rotor, JrIs the moment of inertia of the motor, omegar=ω2+ω4-ω1-ω3,ωiThe rotation speed of the ith motor is 1,2,3, 4; u shape1,U2,U3,U4The control inputs for vertical, roll, pitch, and yaw motions, respectively, are:
wherein b is a lift coefficient, and d is a moment coefficient;
step 2: decoupling the unmanned aerial vehicle dynamic model to obtain a position subsystem and an attitude subsystem; definition of xj,1=zj,The jth drone altitude subsystem dynamics may be written as:
in the formula (I), the compound is shown in the specification,τj,1=Uj,1in order to control the input of the electronic device,for the unknown smooth function obtained from equation (1),a known function obtained by the formula (1), wherein j is the number of the unmanned aerial vehicles in the formation, j is 1, … N, and N is the number of the unmanned aerial vehicles in the flying formation;
definition of xj,3=xj,xj,4=yj, Assuming that the attitude angle near the equilibrium position is small; the jth horizontal motion dynamics of the unmanned aerial vehicle can be simplified as follows:
the jth drone attitude subsystem dynamics may be written as:
in the formula (I), the compound is shown in the specification,τj,2=[Uj,2,Uj,3,Uj,4]in order to control the input of the electronic device,for the unknown smooth function obtained from equation (1),a known function derived from formula (1);
and step 3: the positions and the yaw angles of the unmanned aerial vehicle formation particles are designed as follows:
in the formula, xj,rd,yj,rd,zj,rdPosition signal of formation particle for jth drone, psij,rdYaw angle signal, x, for the jth drone formation particled,yd,zdFor position expectation command of formation reference point, #dAn instruction is expected for the yaw angle of the formation,for the relative position of the jth drone formation particle and the reference point,forming a relative yaw angle of a particle and a reference point for the jth unmanned aerial vehicle;
the virtual structure particle model is described as:
in the formula, xj,d,yj,d,zj,dIs the position signal of the jth virtual dot, μj,1,μj,2,μj,3A control input signal of the jth virtual dot;
the virtual particle control inputs are designed as:
in the formula (I), the compound is shown in the specification,is a negative gradient term of the artificial potential field, V (-) is a total potential energy function of the particle, for formation obstacle avoidance, Vm(. is obstacle avoidance potential energy of mass point, c11>0,c12>0,c21>0,c22>0,c31>0,c32More than 0 is a design parameter;
assuming particle j is in the potential field generated by neighboring particles, the total potential energy function of the jth particle is defined as:
in the formula, the kth drone is a neighbor node of the ith drone, and Φ (·) is a potential energy function represented as follows:
k is a potential field intensity coefficient, a proper value is selected according to the inertia of the unmanned aerial vehicle and the control output of an actuating mechanism, and R is a potential field action range;
defining the obstacle avoidance potential energy function of the mass point as:
in the formula (I), the compound is shown in the specification,the coordinates of the projection point of the mass point j on the obstacle avoidance area (O)xm,Oym,Ozm) Position surrounding the centre of the circle for the m-th obstacle, RkThe radius of a circle is enclosed, M is an obstacle number, M is 1, …, M is the number of obstacles;
the desired heading angle of the virtual particle is defined as:
ψj,d=ψj,rd+ψj,t (12)
in the formula, #j,tIs an equal azimuth heading angle, which can be expressed as:
wherein, Deltae0 is the designed forward-looking distance;
and 4, step 4: defining an altitude tracking error e for the altitude subsystem (3)j,1=xj,1-zj,d(ii) a Designing virtual control quantitiesComprises the following steps:
in the formula, kj,1The more than 0 is the design parameter,is the derivative of the highly desired instruction;
the first order filter is designed as follows:
design of the compensation signal zj,1Comprises the following steps:
in the formula, zj,2Given in subsequent designs;
tracking error after compensation is defined as:
vj,1=ej,1-zj,1 (17)
in the formula (I), the compound is shown in the specification,for the optimal weight estimation value of the neural network,is a vector of basis functions of the neural network, kj,2More than 0 is a design parameter;
design of the compensation signal zj,2Comprises the following steps:
tracking error after compensation is defined as:
vj,2=ej,2-zj,2 (20)
the prediction error is defined as:
in the formula (I), the compound is shown in the specification,for parallel estimation of states, it is obtained by the following serial-parallel model:
wherein, betaj,1More than 0 is a design parameter;
designing a neural network adaptive updating law as follows:
in the formula, λj,1>0,kj,ω1> 0 and deltaj,f1More than 0 is a design parameter;
and 5: for horizontal motion (4), the design PD controller calculates the expected acceleration as:
in the formula, kj,3>0,kj,4>0,kj,5>0,kj,6The more than 0 is the design parameter,the derivative of the desired command for horizontal position;
obtaining the desired roll and pitch angles as:
step (ii) of6: for the attitude sub-system (5), defining an attitude angle tracking error as ej,X1=Xj,1-Xj,dWhereinAn attitude angle expectation command; designing virtual control quantitiesComprises the following steps:
in the formula, kj,7The more than 0 is the design parameter,a derivative of the desired command for attitude angle;
the first order filter is designed as follows:
design of the compensation signal zj,3Comprises the following steps:
in the formula, zj,4Given in subsequent designs;
tracking error after compensation is defined as:
νj,3=ej,X1-zj,3 (29)
in the formula (I), the compound is shown in the specification,is an estimation value of the optimal weight of the neural network,is a vector of basis functions of the neural network, kj,8More than 0 is a design parameter;
design of the compensation signal zj,4Comprises the following steps:
tracking error after compensation is defined as:
vj,4=ej,X2-zj,4 (32)
the prediction error is defined as:
in the formula (I), the compound is shown in the specification,for parallel estimation of states, it is obtained by the following serial-parallel model:
wherein, betaj,2More than 0 is a design parameter;
designing a neural network adaptive updating law as follows:
in the formula, λj,2>0,kj,ω2> 0 and deltaj,f2More than 0 is a design parameter;
and 7: the obtained control input U of the vertical, rolling, pitching and yawing motionj,1,Uj,2,Uj,3,Uj,4Returning to the dynamics model of the unmanned aerial vehicle system, and realizing the expected instruction x under formation maintenance and obstacle avoidanced,yd,zdAnd performing tracking control.
A computer system, comprising: one or more processors, a computer readable storage medium, for storing one or more programs, which when executed by the one or more processors, cause the one or more processors to implement the above-described method.
A computer-readable storage medium having stored thereon computer-executable instructions for performing the above-described method when executed.
A computer program comprising computer executable instructions which when executed perform the method described above.
Advantageous effects
The invention provides a flight formation cooperative obstacle avoidance self-adaptive control method based on a virtual structure and an artificial potential field. The dynamics uncertainty of the unmanned aerial vehicle model is estimated by adopting a neural network algorithm, a serial-parallel model is established to obtain a parallel estimation state and construct prediction error evaluation estimation capability, and the tracking error is applied to a self-adaptive updating law, so that the uncertainty learning capability of the unmanned aerial vehicle is improved, and the system control performance is improved. The beneficial effects are as follows:
(1) the invention adopts a coordination strategy of a virtual formation structure and combines a formation reference point to form an expected organization formation; acquiring a particle track signal of a virtual structure as an expected instruction of a closed-loop system by the action of attractive force and repulsive force between unmanned aerial vehicles based on an artificial potential field strategy;
(2) the dynamics uncertainty of the under-actuated unmanned aerial vehicle is considered, the unknown nonlinearity is estimated by adopting a neural network algorithm, the control input is designed based on a backstepping method and fed forward to an unmanned aerial vehicle model, and the target tracking under formation accurate maintenance and obstacle avoidance is realized;
(3) the method deeply analyzes system dynamics, establishes a serial-parallel model to obtain a parallel estimation state so as to construct a prediction error mining estimation evaluation index, designs a self-adaptive updating law by combining tracking error design, and improves uncertain learning precision.
Drawings
The drawings are only for purposes of illustrating particular embodiments and are not to be construed as limiting the invention, wherein like reference numerals are used to designate like parts throughout.
Fig. 1 is a flow chart of a flight formation cooperative obstacle avoidance self-adaptive control method based on a virtual structure and an artificial potential field.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention will be described in further detail below with reference to the accompanying drawings and examples. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention. In addition, the technical features involved in the embodiments of the present invention described below may be combined with each other as long as they do not conflict with each other.
Referring to fig. 1, the invention relates to a flight formation cooperative obstacle avoidance self-adaptive control method based on a virtual structure and an artificial potential field, which is realized by the following steps:
(a) adopting a dynamic model of the unmanned aerial vehicle:
wherein x, y, z are positions,roll angle, theta pitch angle, psi yaw angle, m 2.3kg mass, g 9.81m/s2As acceleration of gravity, Ix=1.676×10-2kg·m2,Iy=1.676×10-2kg·m2,Iz=2.314×10- 2kg·m2Is an inertia matrix, l is the distance from the center of mass of the unmanned aerial vehicle to the center of the rotor wing, J is 0.1725mr=3.36×10-5kg·m2Is the moment of inertia of the motor, omegar=ω2+ω4-ω1-ω3,ωiThe rotation speed of the ith motor is 1,2,3 and 4. U shape1,U2,U3,U4The control inputs for vertical, roll, pitch, and yaw motions, respectively, are:
wherein, b is 2.92 multiplied by 10-6kg · m is the lift coefficient, d 1.12 × 10-7kg·m2Is a moment coefficient.
(b) Decoupling the unmanned aerial vehicle dynamic model to obtain a position subsystem and an attitude subsystem. Definition of xj,1=zj,The jth drone altitude subsystem dynamics may be written as:
in the formula (I), the compound is shown in the specification,τj,1=Uj,1in order to control the input of the electronic device,j is the serial number of the unmanned aerial vehicle in the formation, j is 1, … N, and N is 5.
Definition of xj,3=xj,xj,4=yj, The attitude angle around the equilibrium position is assumed to be small. The jth horizontal motion dynamics of the unmanned aerial vehicle can be simplified as follows:
the jth drone attitude subsystem dynamics may be written as:
in the formula (I), the compound is shown in the specification,τj,2=[Uj,2,Uj,3,Uj,4]in order to control the input of the electronic device,
(c) the positions and the yaw angles of the unmanned aerial vehicle formation particles are designed as follows:
in the formula, xj,rd,yj,rd,zj,rdPosition signal of formation particle for jth drone, psij,rdFormation of jth UAVYaw angle signal, x, of a particled=yd=zd100m is the position expectation command for the formation reference point, #dPi/16 rad is the yaw angle expectation command in formation,for the relative position of the jth drone formation particle and the reference point, for the relative yaw angle of the jth drone formation particle and the reference point,
the virtual structure particle model is described as:
in the formula, xj,d,yj,d,zj,dIs the position signal of the jth virtual dot, μj,1,μj,2,μj,3The control input signal of the jth virtual dot.
The virtual particle control inputs are designed as:
in the formula (I), the compound is shown in the specification,for artificial potential fieldsThe negative gradient term of (c), V (-) is the total potential energy function of the particle, for formation obstacle avoidance, Vm(. is obstacle avoidance potential energy of mass point, c11=5,c12=1,c21=5,c22=1,c31=5,c32=1。
Assuming particle j is in the potential field generated by neighboring particles, the total potential energy function of the jth particle is defined as:
in the formula, the kth drone is a neighbor node of the ith drone, and Φ (·) is a potential energy function represented as follows:
wherein, k-4 is the potential field intensity coefficient, and R-10 m is the potential field action range.
Defining the obstacle avoidance potential energy function of the mass point as:
in the formula (I), the compound is shown in the specification,the coordinates of the projection point of the mass point j on the obstacle avoidance area (O)xm,Oym,Ozm) For the position of the m-th obstacle surrounding the centre of the circle, Ox1=800m,Oy1=50m,Oz1=300m,Ox1=800m,Oy1=250m,Oz1=750m,Rk60m is the radius of the enclosing circle, m is the obstacle number,m=1,2。
the desired heading angle of the virtual particle is defined as:
ψj,d=ψj,rd+ψj,t (47)
in the formula, #j,tIs an equal azimuth heading angle, which can be expressed as:
wherein, Deltae10 is the designed look-ahead distance.
(d) For the height subsystem (3), a height tracking error is defined as. Designing virtual control quantitiesComprises the following steps:
The first order filter is designed as follows:
design of the compensation signal zj,1Comprises the following steps:
in the formula, zj,2Given in the subsequent design, zj,1(0)=0。
Tracking error after compensation is defined as:
νj,1=ej,1-zj,1 (52)
in the formula (I), the compound is shown in the specification,is an estimation value of the optimal weight of the neural network,is a vector of basis functions of the neural network,kj,2=3。
design of the compensation signal zj,2Comprises the following steps:
in the formula, zj,2(0)=0。
Tracking error after compensation is defined as:
νj,2=ej,2-zj,2 (55)
the prediction error is defined as:
in the formula (I), the compound is shown in the specification,for parallel estimation of states, it is obtained by the following serial-parallel model:
wherein, betaj,1=0.1。
Designing a neural network adaptive updating law as follows:
in the formula, λj,1=0.1,kj,ω1100 and δj,f1=0.1。
(e) For horizontal motion (4), the design PD controller calculates the expected acceleration as:
in the formula, kj,3=1,kj,4=1,kj,5=1,kj,6=1,The derivative of the command is expected for horizontal position.
Obtaining the desired roll and pitch angles as:
(f) for the attitude sub-system (5), defining an attitude angle tracking error as ej,X1=Xj,1-Xj,dWhereinThe command is expected for the attitude angle. Designing virtual control quantitiesComprises the following steps:
in the formula, kj,7The number 5 is a design parameter,the derivative of the desired command is the attitude angle.
The first order filter is designed as follows:
design of the compensation signal zj,3Comprises the following steps:
in the formula, zj,4Given in the subsequent design, zj,3(0)=0。
Tracking error after compensation is defined as:
vj,3=ej,X1-zj,3 (64)
in the formula (I), the compound is shown in the specification,is an estimation value of the optimal weight of the neural network,is a vector of basis functions of the neural network,kj,8=5。
design of the compensation signal zj,4Comprises the following steps:
in the formula, zj,4(0)=0。
Tracking error after compensation is defined as:
vj,4=ej,X2-zj,4 (67)
the prediction error is defined as:
in the formula (I), the compound is shown in the specification,for parallel estimation of states, it is obtained by the following serial-parallel model:
wherein, betaj,2=0.1。
Designing a neural network adaptive updating law as follows:
in the formula, λj,2=0.1,kj,ω2100 and δj,f2=0.1。
(g) According to the obtained control input U of vertical, rolling, pitching and yawing motionj,1,Uj,2,Uj,3,Uj,4Returning to the dynamics model of the unmanned aerial vehicle system, and realizing the expected instruction x under formation maintenance and obstacle avoidanced,yd,zdAnd performing tracking control.
While the invention has been described with reference to specific embodiments, the invention is not limited thereto, and various equivalent modifications or substitutions can be easily made by those skilled in the art within the technical scope of the present disclosure.
Claims (4)
1. A flight formation cooperative obstacle avoidance self-adaptive control method based on a virtual structure and an artificial potential field is characterized by comprising the following steps:
step 1: adopting a dynamic model of the unmanned aerial vehicle:
wherein x, y, z are positions,roll angle, theta pitch angle, psi yaw angle, m mass, g gravitational acceleration, Ix,Iy,IzFor the inertial matrix, l is the distance from the center of mass of the unmanned aerial vehicle to the center of the rotor, JrIs the moment of inertia of the motor, omegar=ω2+ω4-ω1-ω3,ωiThe rotation speed of the ith motor is 1,2,3, 4; u shape1,U2,U3,U4The control inputs for vertical, roll, pitch, and yaw motions, respectively, are:
wherein b is a lift coefficient, and d is a moment coefficient;
step 2: decoupling the unmanned aerial vehicle dynamic model to obtain a position subsystem and an attitude subsystem; definition of xj,1=zj,The jth drone altitude subsystem dynamics may be written as:
in the formula (I), the compound is shown in the specification,τj,1=Uj,1in order to control the input of the electronic device,for the unknown smooth function obtained from equation (1),a known function obtained by the formula (1), wherein j is the number of the unmanned aerial vehicles in the formation, j is 1, … N, and N is the number of the unmanned aerial vehicles in the flying formation;
definition of xj,3=xj,xj,4=yj, Assuming that the attitude angle near the equilibrium position is small; the jth horizontal motion dynamics of the unmanned aerial vehicle can be simplified as follows:
the jth drone attitude subsystem dynamics may be written as:
in the formula (I), the compound is shown in the specification,τj,2=[Uj,2,Uj,3,Uj,4]in order to control the input of the electronic device,for the unknown smooth function obtained from equation (1),a known function derived from formula (1);
and step 3: the positions and the yaw angles of the unmanned aerial vehicle formation particles are designed as follows:
in the formula, xj,rd,yj,rd,zj,rdPosition signal of formation particle for jth drone, psij,rdYaw angle signal, x, for the jth drone formation particled,yd,zdFor position expectation command of formation reference point, #dDesired command for yaw angle for formation,/xi,lyi,lziFor the jth drone formation particle and the relative position of the reference point, lψiForming a relative yaw angle of a particle and a reference point for the jth unmanned aerial vehicle;
the virtual structure particle model is described as:
in the formula, xj,d,yj,d,zj,dIs the position signal of the jth virtual dot, μj,1,μj,2,μj,3A control input signal of the jth virtual dot;
the virtual particle control inputs are designed as:
in the formula (I), the compound is shown in the specification,is a negative gradient term of the artificial potential field, V (-) is a total potential energy function of the particle, for formation obstacle avoidance, Vm(. is obstacle avoidance potential energy of mass point, c11>0,c12>0,c21>0,c22>0,c31>0,c32More than 0 is a design parameter;
assuming particle j is in the potential field generated by neighboring particles, the total potential energy function of the jth particle is defined as:
in the formula, the kth drone is a neighbor node of the ith drone, and Φ (·) is a potential energy function represented as follows:
k is a potential field intensity coefficient, a proper value is selected according to the inertia of the unmanned aerial vehicle and the control output of an actuating mechanism, and R is a potential field action range;
defining the obstacle avoidance potential energy function of the mass point as:
in the formula (I), the compound is shown in the specification,the coordinates of the projection point of the mass point j on the obstacle avoidance area (O)xm,Oym,Ozm) Position surrounding the centre of the circle for the m-th obstacle, RkThe radius of a circle is enclosed, M is an obstacle number, M is 1, …, M is the number of obstacles;
the desired heading angle of the virtual particle is defined as:
ψj,d=ψj,rd+ψj,t (12)
in the formula, #j,tIs an equal azimuth heading angle, which can be expressed as:
wherein, Deltae0 is the designed forward-looking distance;
and 4, step 4: defining an altitude tracking error e for the altitude subsystem (3)j,1=xj,1-zj,d(ii) a Designing virtual control quantitiesComprises the following steps:
in the formula, kj,1The more than 0 is the design parameter,is the derivative of the highly desired instruction;
the first order filter is designed as follows:
design of the compensation signal zj,1Comprises the following steps:
in the formula, zj,2Given in subsequent designs;
tracking error after compensation is defined as:
vj,1=ej,1-zj,1 (17)
in the formula (I), the compound is shown in the specification,for the optimal weight estimation value of the neural network,as a neural networkVector of basis functions, kj,2More than 0 is a design parameter;
design of the compensation signal zj,2Comprises the following steps:
tracking error after compensation is defined as:
vj,2=ej,2-zj,2 (20)
the prediction error is defined as:
in the formula (I), the compound is shown in the specification,for parallel estimation of states, it is obtained by the following serial-parallel model:
wherein, betaj,1More than 0 is a design parameter;
designing a neural network adaptive updating law as follows:
in the formula, λj,1>0,kj,ω1> 0 and deltaj,f1More than 0 is a design parameter;
and 5: for horizontal motion (4), the design PD controller calculates the expected acceleration as:
in the formula, kj,3>0,kj,4>0,kj,5>0,kj,6The more than 0 is the design parameter,the derivative of the desired command for horizontal position;
obtaining the desired roll and pitch angles as:
step 6: for the attitude sub-system (5), defining an attitude angle tracking error as ej,X1=Xj,1-Xj,dWhereinAn attitude angle expectation command; designing virtual control quantitiesComprises the following steps:
in the formula, kj,7The more than 0 is the design parameter,a derivative of the desired command for attitude angle;
the first order filter is designed as follows:
design of the compensation signal zj,3Comprises the following steps:
in the formula, zj,4Given in subsequent designs;
tracking error after compensation is defined as:
νj,3=ej,X1-zj,3 (29)
in the formula (I), the compound is shown in the specification,is an estimation value of the optimal weight of the neural network,is a vector of basis functions of the neural network, kj,8More than 0 is a design parameter;
design of the compensation signal zj,4Comprises the following steps:
tracking error after compensation is defined as:
vj,4=ej,X2-zj,4 (32)
the prediction error is defined as:
in the formula (I), the compound is shown in the specification,for parallel estimation of states, it is obtained by the following serial-parallel model:
wherein, betaj,2More than 0 is a design parameter;
designing a neural network adaptive updating law as follows:
and 7: the obtained control input U of the vertical, rolling, pitching and yawing motionj,1,Uj,2,Uj,3,Uj,4Returning to the dynamics model of the unmanned aerial vehicle system, and realizing the expected instruction x under formation maintenance and obstacle avoidanced,yd,zdAnd performing tracking control.
2. A computer system, comprising: one or more processors, a computer readable storage medium, for storing one or more programs, wherein the one or more programs, when executed by the one or more processors, cause the one or more processors to implement the method of claim 1.
3. A computer-readable storage medium having stored thereon computer-executable instructions for, when executed, implementing the method of claim 1.
4. A computer program comprising computer executable instructions which when executed perform the method of claim 1.
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