CN105488296A - Unmanned aerial vehicle modeling method covering wind field disturbance term - Google Patents

Abstract

The invention relates to an unmanned aerial vehicle modeling method covering a wind field disturbance term, wherein the unmanned aerial vehicle is a quadrotor unmanned aerial vehicle. The method comprises the following steps of 1, establishing a ground coordinate system and vehicle body coordinate system; 2, under the effect of a wind field, analyzing the aerodynamic condition of each rotor; 3, determining the torque of the unmanned aerial vehicle caused by the lift force of the rotors; 4, determining the torque of the unmanned aerial vehicle caused by the wind power; 5, establishing a linear motion equation in the ground coordinate system and establishing a rotation equation in the vehicle body coordinate system respectively; and 6, obtaining a kinetic model of the six-degree-of-freedom quadrotor unmanned aerial vehicle with the wind field disturbance term through deducing. According to the unmanned aerial vehicle modeling method provided by the invention, the wind field disturbance term is introduced based on the traditional kinetic model, so that the simulation precision of the unmanned aerial vehicle simulation system can be improved.

Description

A kind of unmanned plane modeling method considering wind disturbance

Technical field

The present invention relates to Modeling of Vehicle technical field, particularly relate to a kind of unmanned plane modeling method considering wind disturbance.

Background technology

Four rotor wing unmanned aerial vehicles belong to the one of Miniature Unmanned Helicopter, because it has the feature such as topology layout novelty, flying method uniqueness, have attracted the extensive concern of people and have become study hotspot new in the world.Four rotor wing unmanned aerial vehicles have that volume is little, lightweight, good concealment, flying height are low, structure is simple, cost is low, security is good, mobility strong, be applicable to multi-platform and can perform the advantages such as special assignment, therefore has wide military and civilian application prospect.

The foundation of kinetic model is the basis of research four rotor wing unmanned aerial vehicle, is generally to carry out aerodynamic analysis according to foline theory and momentum theory to rotor, and then derives the overall dynamics model of four rotor wing unmanned aerial vehicles according to newton-Eulerian equation.Because four rotor wing unmanned aerial vehicle flying heights are low, lightweight, nonlinear degree is high and coupling is large, therefore it is than being easier to the impact being subject to wind field.But the effect of wind field does not take into account by traditional modeling method, so the confidence level of four rotor wing unmanned aerial vehicle analogue systems is lower.

Summary of the invention

In view of above-mentioned analysis, the present invention proposes a kind of unmanned modeling method considering wind disturbance, the basis of traditional power model introduces wind disturbance item, the simulation accuracy of unmanned plane analogue system can be improved.

Object of the present invention is mainly achieved through the following technical solutions:

Consider a unmanned plane modeling method for wind disturbance, described unmanned plane is four rotor wing unmanned aerial vehicles, and described modeling method comprises the steps:

(1) earth axes S is set up _e={ x _e, y _e, z _eand body axis system S _b={ x _b, y _b, z _b, and determine by earth axes S _eto body axis system S _bcoordinate conversion matrix R;

(2), under Wind, the aerodynamic force situation of each rotor is analyzed;

(3) according to the torque M that the analysis result determination unmanned plane of step (2) is caused by rotor lift _b;

(4) according to the torque M that the analysis result determination unmanned plane of step (2) is caused by wind-force _w;

(5) in earth axes, set up the line equation of motion respectively and set up rotation equation in body axis system;

(6) derivation draws the kinetic model of six degree of freedom four rotor wing unmanned aerial vehicle with wind disturbance item.

Beneficial effect of the present invention is as follows:

The present invention introduces wind disturbance item on the basis of four traditional rotor wing unmanned aerial vehicle kinetics equations, the impact of wind field can be reflected among model accurately, according to this model establishment simulated program, the simulation accuracy of analogue system can be improved, analogue system and actual conditions are more pressed close to.

Accompanying drawing explanation

Accompanying drawing only for illustrating the object of specific embodiment, and does not think limitation of the present invention, and in whole accompanying drawing, identical reference symbol represents identical parts.

Fig. 1 is for setting up coordinate system schematic diagram;

Fig. 2 is the aerodynamic analysis schematic diagram of rotor under Wind;

Fig. 3-4 is Numerical Simulation Results schematic diagram in the first situation; Wherein Fig. 3 is that position exports (spot hover, the average wind disturbance of W=[1,1,0] Tm/s); Fig. 4 is that attitude angle exports (spot hover, the average wind disturbance of W=[1,1,0] Tm/s);

Fig. 5-6 is Numerical Simulation Results schematic diagram in the second situation; Fig. 5 position exports (spot hover, the average wind disturbance of W=[2,2,0] Tm/s); Fig. 6 attitude angle exports (spot hover, the average wind disturbance of W=[2,2,0] Tm/s).

Embodiment

Specifically describe the preferred embodiments of the present invention below in conjunction with accompanying drawing, wherein, accompanying drawing forms the application's part, and together with embodiments of the present invention for explaining principle of the present invention.

Assuming that quadrotor is rigid body and structure full symmetric, set up earth axes S _e={ x _e, y _e, z _eand body axis system S _b={ x _b, y _b, z _b, as shown in Figure 1.The initial point of earth axes is aircraft takeoff point on ground, z _eaxle straight down, longitudinal axis x _epointing to heading is just, y _eaxle is perpendicular to o _ex _ez _eplane, its positive dirction is determined by the right-hand rule.Body axis system is fixed on body, and its initial point is connected in fuselage barycenter, longitudinal axis x _bin aircraft symmetrical plane, overlap with the body longitudinal axis, pointing to body head is just; z _baxle, perpendicular to unmanned plane symmetrical plane, is just downwards; y _baxle is directly in o _bx _bz _bplane, its positive dirction is determined by the right-hand rule.

By two diagonal line, rotor is divided into two groups, front rotor 1 and rear rotor 3 are one group, and the dextrorotation wing 2 and the left-handed wing 4 form other one group, and two groups of rotors turn on the contrary, to offset the aerodynamic force moment of torsion produced because of rotor wing rotation.By adjusting the size of four gyroplane rotate speeds, the motion of four rotor wing unmanned aerial vehicle all directions can be controlled.

The flight attitude of four rotor wing unmanned aerial vehicles is by attitude angle Θ=[φ, θ, ψ] ^tdescribe.Roll angle φ (-pi/2 < φ <-pi/2) is axis z _bwith by axis x _bvertical guide between angle, be just to the right during rolling; Pitching angle theta (-pi/2 < θ < pi/2) is axis x _band angle between surface level is just upwards during pitching; Crab angle ψ (-π < ψ < π) is axis x _bprojection in the horizontal plane and earth's axis x _ebetween angle, driftage is for just to the right.

As shown in Figure 2, under Wind, the aerodynamic force of each rotor is analyzed (this partial parameters adopts unified presentation, omits subscript i), V _dthe induced velocity of rotor, V _wwind speed, be called total induced velocity, can be expressed as:

$\hat{V}=V_d+V_w---\left(1\right)$

The induced velocity V of rotor _dsize be:

$V_d=\sqrt{\frac{F_T}{2\mathrm{\&rho;}A}}---\left(2\right)$

ρ is atmospheric density, and A is rotor rotating disk area.

The lift F of rotor _tsize is:

F _T＝b·Ω ²(3)

B is lift coefficient, and Ω is rotor wing rotation angular velocity

During Wind, the aerodynamic force F of rotor _ait is tensile force f _twith wind-force F _wand, can F be expressed as _a=F _t+ F _w, size is:

$F_A=2{\mathrm{\&rho;AV}}_d\hat{V}---\left(4\right)$

Can be noticed by above formula, when without Wind, f _w=0, F _a=F _t, namely the suffered aerodynamic force of rotor is provided by the lift of rotor completely.

The moment of torsion M of rotor _qsize be:

M _Q＝d·Ω ²(5)

D is resistance coefficient

During Wind, the aerodynamic force moment of torsion M of rotor _asize be:

$M_A=M_w+M_Q=k_d{\hat{V}}^2---\left(6\right)$

In formula, M _wfor rotor torque, k _dfor the aerodynamic force torque coefficient of rotor, size is relevant with atmospheric density, rotor radius and rotor shape etc.

Set up the four rotor wing unmanned aerial vehicle kinetic models considering wind disturbance, first following simplification done to it:

(1) ignore the distortion of structure, four rotor wing unmanned aerial vehicles are considered as rigid body;

(2) four rotor wing unmanned aerial vehicle housing construction full symmetrics;

(3) ignore the distortion of blade, blade is considered as rigid body;

(4) overlap with body axis system at four rotor wing unmanned aerial vehicle takeoff point upper ground surface coordinate systems;

(5) do not consider that rotor is waved, square proportional relation of lift and anti-twisted moment and gyroplane rotate speed;

(6) effect of ground effect is not considered;

(7) lift coefficient and resistance coefficient are constant;

(8) Eulerian angle speed equals angular speed under body coordinate system.

After above-mentioned simplification, the motion in space of four rotor wing unmanned aerial vehicles can be thought and to be made up of space translation (line along three axles moves) and spatial rotation (rotations around three axles), namely can be regarded as the rigid body (front and back of a six degree of freedom, left and right, up and down, pitching, rolling and driftage).

Because the body front face area of four rotor wing unmanned aerial vehicles is less, therefore ignore the wind-force suffered by body, only consider the wind-force suffered by rotor.

In earth axes, set up the line equation of motion respectively according to newton-Eulerian equation and set up rotation equation in body axis system:

$m\stackrel{\&CenterDot;\&CenterDot;}{X}=R(\underset{i=1}{\overset{4}{\&Sigma;}}{F}_{T_i}+\underset{i=1}{\overset{4}{\&Sigma;}}{F}_{W_i})+mG---\left(7\right)$

$J\stackrel{\&CenterDot;}{\mathrm{\&omega;}}=-\mathrm{\&omega;}\&times;J\mathrm{\&omega;}+\mathrm{\&omega;}\&times;\&lsqb;0,0,J_r{\mathrm{\&Omega;}}_r\&rsqb;+M_B+M_w---\left(8\right)$

In formula (7), X=[x, y, z] ^tbe the position of four rotor wing unmanned aerial vehicle barycenter, m is quality, and R is coordinate conversion matrix, F _tiand F _wilift and the wind-force of rotor i respectively, G=[0,0 ,-g] ^tacceleration of gravity.

By earth axes S _eto body axis system S _btransition matrix be:

R＝R(z,ψ)R(y,θ)R(x,φ)

$R=\left[\begin{array}{ccc}\cos \mathrm{\&psi;}\cos \mathrm{\&theta;}& \cos \mathrm{\&psi;}\sin \mathrm{\&theta;}\sin \mathrm{\&phi;}-\sin \mathrm{\&psi;}\cos \mathrm{\&phi;}& \cos \mathrm{\&psi;}\sin \mathrm{\&theta;}\cos \mathrm{\&phi;}+\sin \mathrm{\&psi;}\sin \mathrm{\&phi;}\\ \sin \mathrm{\&psi;}\cos \mathrm{\&theta;}& \sin \mathrm{\&psi;}\sin \mathrm{\&theta;}\sin \mathrm{\&phi;}+\sin \mathrm{\&psi;}\cos \mathrm{\&phi;}& \sin \mathrm{\&psi;}\sin \mathrm{\&theta;}\cos \mathrm{\&phi;}-\cos \mathrm{\&psi;}\sin \mathrm{\&phi;}\\ -\sin \mathrm{\&theta;}& \cos \mathrm{\&theta;}\sin \mathrm{\&phi;}& \cos \mathrm{\&theta;}\cos \mathrm{\&phi;}\end{array}\right]$

Conversion between earth axes and body axis system meets following equation:

$\left\{\begin{array}{c}{S}_b=R\&CenterDot;S_e\\ S_e=R^T\&CenterDot;S_b\end{array}\right.$

In formula (8), ω=[p, q, r] ^tbody rotational angular velocity, J _rthe moment of inertia of rotor, ω × [0,0, J _rΩ _r] item represents is the gyroscopic torque produced due to rotor wing rotation, J is moment of inertia diagonal matrix:

$J=\left[\begin{array}{ccc}{I}_n& 0& 0\\ 0& I_{yy}& 0\\ 0& 0& I_{zz}\end{array}\right]---\left(9\right)$

I _xx, I _yy, I _zzfor axial principal moment of inertia, due to hypothesis before, therefore I _xy=I _yz=I _xz=0.

Ω _rthe relative velocity of rotor:

Ω _r＝-Ω ₁+Ω ₂-Ω ₃+Ω ₄(10)

M _bthe torque that rotor lift causes:

$M_B=\left[\begin{array}{c}l(-{F_{T_2}}^2+{F_{T_4}}^2)\\ l({F_{T_1}}^2-F_{T_3}^2)\\ M_{Q_1}-M_{Q_2}+M_{Q_3}-M_{Q_4}\end{array}\right]---\left(11\right)$

Wherein, l is the brachium of body.

M _wthe torque that wind-force causes:

$M_w=\left[\begin{array}{c}l(-{F_{w_2}}^2+{F_{w_4}}^2)\\ l({F_{w_1}}^2-{F_{w_3}}^2)\\ M_{W_1}-M_{W_2}+M_{W_3}-M_{W_4}\end{array}\right]---\left(12\right)$

Composite type (7)-(12), the kinetic model of six degree of freedom four rotor wing unmanned aerial vehicle with wind disturbance item can be derived:

$\&lsqb;\frac{\begin{array}{c}\stackrel{\&CenterDot;\&CenterDot;}{x}\\ \stackrel{\&CenterDot;\&CenterDot;}{y}\\ \stackrel{\&CenterDot;\&CenterDot;}{z}\end{array}}{\begin{array}{c}\stackrel{\&CenterDot;\&CenterDot;}{\mathrm{\&phi;}}\\ \stackrel{\&CenterDot;\&CenterDot;}{\mathrm{\&theta;}}\\ \stackrel{\&CenterDot;\&CenterDot;}{\mathrm{\&psi;}}\end{array}}\&rsqb;\&lsqb;\frac{\begin{array}{c}{U}_1\&CenterDot;(\cos \mathrm{\&phi;}\sin \mathrm{\&theta;}\cos \mathrm{\&psi;}+\sin \mathrm{\&phi;}\sin \mathrm{\&psi;})/m\\ U_1\&CenterDot;(\cos \mathrm{\&phi;}\sin \mathrm{\&theta;}\sin \mathrm{\&psi;}-\sin \mathrm{\&phi;}\cos \mathrm{\&psi;})/m\\ U_1\&CenterDot;\left(\cos \mathrm{\&phi;}\cos \mathrm{\&theta;}\right)/m/g\end{array}}{\begin{array}{c}\stackrel{\&CenterDot;}{\mathrm{\&theta;}}\stackrel{\&CenterDot;}{\mathrm{\&psi;}}(I_{yy}-I_{zz})/I_{xx}+\stackrel{\&CenterDot;}{\mathrm{\&theta;}}{\mathrm{\&Omega;}}_r{J}_r/I_{xx}+U_2\&CenterDot;l/I_{xx}\\ \stackrel{\&CenterDot;}{\mathrm{\&phi;}}\stackrel{\&CenterDot;}{\mathrm{\&psi;}}(I_{zz}-I_{xx})/I_{yy}-\stackrel{\&CenterDot;}{\mathrm{\&phi;}}{\mathrm{\&Omega;}}_r{J}_r/I_{yy}+U_3\&CenterDot;l/I_{yy}\\ \stackrel{\&CenterDot;}{\mathrm{\&phi;}}\stackrel{\&CenterDot;}{\mathrm{\&psi;}}(I_{xx}-I_{yy})/I_{zz}+U_4\&CenterDot;l/I_{zz}\end{array}}\&rsqb;\&lsqb;\frac{\begin{array}{c}{W}_1\\ W_2\\ W_3\end{array}}{\begin{array}{c}{W}_4\\ W_5\\ W_6\end{array}}\&rsqb;---\left(13\right)$

In formula, U=[U ₁, U ₂, U ₃, U ₄] ^tcontrol vector, U ₁lifting (hovering) controlled quentity controlled variable, U ₂, U ₃, U ₄rolling respectively, pitching and driftage controlled quentity controlled variable, size is as follows:

$v=\left[\begin{array}{c}b({{\mathrm{\&Omega;}}_1}^2+{{\mathrm{\&Omega;}}_2}^2+{{\mathrm{\&Omega;}}_3}^2+{{\mathrm{\&Omega;}}_4}^2)\\ b(-{{\mathrm{\&Omega;}}_2}^2+{{\mathrm{\&Omega;}}_2}^2)\\ b({{\mathrm{\&Omega;}}_1}^2-{{\mathrm{\&Omega;}}_3}^2)\\ d({{\mathrm{\&Omega;}}_1}^2-{{\mathrm{\&Omega;}}_2}^2+{{\mathrm{\&Omega;}}_3}^2-{{\mathrm{\&Omega;}}_4}^2)\end{array}\right]---\left(14\right)$

Wind disturbance item W=[W ₁, W ₂, W ₃, W ₄, W ₅, W ₆] ^tbe defined as follows:

$W=\left[\begin{array}{c}R\&CenterDot;\underset{i=1}{\overset{4}{\&Sigma;}}{F}_{W_i}/m\\ R\&CenterDot;\underset{i=1}{\overset{4}{\&Sigma;}}{F}_{W_i}/m\\ R\&CenterDot;\underset{i=1}{\overset{4}{\&Sigma;}}{F}_{W_i}/m\\ l(-{F_{w_2}}^2+{F_{w_4}}^2)/I_{xx}\\ l({F_{w_1}}^2-{F_{w_3}}^2)/I_{yy}\\ (W_{w_1}-M_{w_2}+M_{w_3}-M_{w_4})/I_{zz}\end{array}\right]---\left(15\right)$

First, wind speed W=[1,1,0] is introduced ^tthe average wind field of m/s, expects that four rotor wing unmanned aerial vehicles are at X _d=[0,0,1] ^tm place realizes hovering, and simulation time T=60s, the Wind time is 20-40s.Numerical Simulation Results as shown in Figure 3-4.

Can be seen by Fig. 3, within the time not having Wind, the position X of setting that what four rotor wing unmanned aerial vehicles were stable hover over _d=[0,0,1] ^tm; Within the time of T=20-40s Wind, x and y slightly fluctuates to position, but through the adjustment of controller, has been stabilized in again the position of setting; Z is to the static difference highly occurring about 0.05m.As seen from Figure 4, when Wind, roll angle is stabilized in-0.8 °, the angle of pitch is stabilized in 0.8 °, this is because be subject to the impact of the average wind field in x and y direction, needs pendulum to have a certain degree at this both direction head, the effect of wind-force could be resisted, to realize hovering; But, due to the coupling of four rotor wing unmanned aerial vehicle motions, cause z to highly having occurred static difference.

The wind speed of average wind field is increased to W=[2,2,0] ^tm/s, still expect that four rotor wing unmanned aerial vehicles realize hovering in situ, other conditions are all constant, and Numerical Simulation Results as seen in figs. 5-6.

Can be seen by Fig. 5, because average wind field wind speed increases, x and y increases to positional fluctuation, but in a period of time, controller has still been stabilized in desired location; Z also increases to about 0.1m to the static difference of height.As shown in Figure 6, along with the increase of wind speed, roll angle is stabilized in-1.5 °, and the angle of pitch is stabilized in 1.5 °, and the angle that head is put into increases, and to resist the impact of the wind-force of enhancing, result in the increase of z to height static difference, this conforms to actual conditions simultaneously.It can thus be appreciated that this kinetic model can reflect the dynamic property of four rotor wing unmanned aerial vehicles accurately.

The present invention introduces wind disturbance item on the basis of four traditional rotor wing unmanned aerial vehicle kinetics equations, the impact of wind field can be reflected among model accurately, according to this model establishment simulated program, the simulation accuracy of analogue system can be improved, analogue system and actual conditions are more pressed close to.

It will be understood by those skilled in the art that all or part of flow process realizing above-described embodiment method, the hardware that can carry out instruction relevant by computer program has come, and described program can be stored in computer-readable recording medium.Wherein, described computer-readable recording medium is disk, CD, read-only store-memory body or random store-memory body etc.

The above; be only the present invention's preferably embodiment, but protection scope of the present invention is not limited thereto, is anyly familiar with those skilled in the art in the technical scope that the present invention discloses; the change that can expect easily or replacement, all should be encompassed within protection scope of the present invention.

Claims (10)

1. consider a unmanned plane modeling method for wind disturbance, described unmanned plane is four rotor wing unmanned aerial vehicles, it is characterized in that, described modeling method comprises the steps:

(1) earth axes S is set up _e={ x _e, y _e, z _eand body axis system S _b={ x _b, y _b, z _b, and determine by earth axes S _eto body axis system S _bcoordinate conversion matrix R;

(2), under Wind, the aerodynamic force situation of each rotor is analyzed;

(3) according to the torque M that the analysis result determination unmanned plane of step (2) is caused by rotor lift _b;

(4) according to the torque M that the analysis result determination unmanned plane of step (2) is caused by wind-force _w;

(5) in earth axes, set up the line equation of motion respectively and set up rotation equation in body axis system;

(6) derivation draws the kinetic model of six degree of freedom four rotor wing unmanned aerial vehicle with wind disturbance item.

2. modeling method according to claim 1, is characterized in that: in described step (1), supposition four rotor wing unmanned aerial vehicles are rigid body and structure full symmetric, and the initial point of earth axes is unmanned plane takeoff point on ground, z _eaxle straight down, longitudinal axis x _epointing to heading is just, y _eaxle is perpendicular to o _ex _ez _eplane, its positive dirction is determined by the right-hand rule; Body axis system is fixed on body, and its initial point is connected in fuselage barycenter, longitudinal axis x _bin aircraft symmetrical plane, overlap with the body longitudinal axis, pointing to body head is just; z _baxle, perpendicular to unmanned plane symmetrical plane, is just downwards; y _baxle is directly in o _bx _bz _bplane, its positive dirction is determined by the right-hand rule.

3. modeling method according to claim 2, is characterized in that: analyze the lift F for obtaining each rotor in described step (2) _ti, wind-force F _wi, moment of torsion M _qiand torque M _wi, wherein i=1,2,3,4, be rotor label, front rotor is 1, rear rotor is 3, the dextrorotation wing is 2, the left-handed wing is 4.

4. modeling method according to claim 3, is characterized in that: the lift F of rotor _tisize is: F _ti=b Ω _i ², the moment of torsion M of rotor _qisize be: M _qi=d Ω _i ²; B is lift coefficient d is resistance coefficient, Ω _iit is the angular velocity of rotation of rotor i.

5. modeling method according to claim 4, is characterized in that, the torque that unmanned plane is caused by rotor lift is:

$M_B=\left[\begin{array}{c}l(-{F_{T_2}}^2+{F_{T_4}}^2)\\ l({F_{T_1}}^2-{F_{T_3}}^2)\\ M_{Q_1}-M_{Q_2}+M_{Q_3}-M_{Q_4}\end{array}\right],$ L is the brachium of body.

6. the modeling method according to claim 3 or 4 or 5, it is characterized in that, the torque that unmanned plane is caused by wind-force is:

$M_w=\left[\begin{array}{c}l(-{F_{w_2}}^2+{F_{w_4}}^2)\\ l({F_{w_1}}^2-{F_{w_3}}^2)\\ M_{W_1}-M_{W_2}+M_{W_3}-M_{W_4}\end{array}\right],$ L is the brachium of body.

7. modeling method according to claim 6, is characterized in that: step (5) utilizes newton-Eulerian equation to set up the line equation of motion and rotation equation, and the line equation of motion and rotation equation are specially

$m\stackrel{\&CenterDot;\&CenterDot;}{X}=R(\underset{i=1}{\overset{4}{\&Sigma;}}{F}_{T_i}+\underset{i=1}{\overset{4}{\&Sigma;}}{F}_{W_i})+mG$

$J\stackrel{\&CenterDot;}{\mathrm{\&omega;}}=-\mathrm{\&omega;}\&times;J\mathrm{\&omega;}+\mathrm{\&omega;}\&times;\&lsqb;0,0,J_r{\mathrm{\&Omega;}}_r\&rsqb;+M_B+M_w$

In formula, X=[x, y, z] ^tbe the position of four rotor wing unmanned aerial vehicle barycenter, m is quality, with lift and the wind-force of rotor i respectively, G=[0,0 ,-g] ^tacceleration of gravity, ω=[p, q, r] ^tbody rotational angular velocity, J _rthe moment of inertia of rotor, ω × [0,0, J _rΩ _r] item represents is the gyroscopic torque produced due to rotor wing rotation, J is moment of inertia diagonal matrix:

$J=\left[\begin{array}{ccc}{I}_{xx}& 0& 0\\ 0& I_{yy}& 0\\ 0& 0& I_{zz}\end{array}\right]---\left(9\right)$

I _xx, I _yy, I _zzfor axial principal moment of inertia, M _bthe torque that unmanned plane is caused by rotor lift, M _wthe torque that unmanned plane is caused by wind-force, Ω _rthe relative velocity Ω of rotor _r=-Ω ₁+ Ω ₂-Ω ₃+ Ω ₄.

8. the modeling method according to claim 1 or 7, is characterized in that, the kinetic model of six degree of freedom four rotor wing unmanned aerial vehicle that described step (6) derivation draws with wind disturbance item is specially:

$\&lsqb;\frac{\begin{array}{c}\stackrel{\&CenterDot;\&CenterDot;}{x}\\ \stackrel{\&CenterDot;\&CenterDot;}{y}\\ \stackrel{\&CenterDot;\&CenterDot;}{z}\end{array}}{\begin{array}{c}\stackrel{\&CenterDot;\&CenterDot;}{\mathrm{\&phi;}}\\ \stackrel{\&CenterDot;\&CenterDot;}{\mathrm{\&theta;}}\\ \stackrel{\&CenterDot;\&CenterDot;}{\mathrm{\&psi;}}\end{array}}\&rsqb;=\&lsqb;\frac{\begin{array}{c}{U}_1\&CenterDot;(\cos \mathrm{\&phi;}\sin \mathrm{\&theta;}\cos \mathrm{\&psi;}+\sin \mathrm{\&phi;}\sin \mathrm{\&psi;})/m\\ U_1\&CenterDot;(\cos \mathrm{\&phi;}\sin \mathrm{\&theta;}\sin \mathrm{\&psi;}-\sin \mathrm{\&phi;}\cos \mathrm{\&psi;})/m\\ U_1\&CenterDot;\left(\cos \mathrm{\&phi;}\cos \mathrm{\&theta;}\right)/m-g\end{array}}{\begin{array}{c}\stackrel{\&CenterDot;}{\mathrm{\&theta;}}\stackrel{\&CenterDot;}{\mathrm{\&psi;}}(I_{yy}-I_{zz})I_{xx}+\stackrel{\&CenterDot;}{\mathrm{\&theta;}}{\mathrm{\&Omega;}}_r{J}_r/I_{xx}+U_2\&CenterDot;l/I_{xx}\\ \stackrel{\&CenterDot;}{\mathrm{\&theta;}}\stackrel{\&CenterDot;}{\mathrm{\&psi;}}(I_{zz}-I_{xx})I_{yy}-\stackrel{\&CenterDot;}{\mathrm{\&phi;}}{\mathrm{\&Omega;}}_r{J}_r/I_{yy}+U_3\&CenterDot;l/I_{yy}\\ \stackrel{\&CenterDot;}{\mathrm{\&theta;}}\stackrel{\&CenterDot;}{\mathrm{\&psi;}}(I_{xx}-I_{yy})I_{zz}+U_4\&CenterDot;l/I_{zz}\end{array}}\&rsqb;+\&lsqb;\frac{\begin{array}{c}{W}_1\\ W_2\\ W_3\end{array}}{\begin{array}{c}{W}_4\\ W_5\\ W_6\end{array}}\&rsqb;---\left(13\right)$

In formula, [x, y, z] ^tbe the position of four rotor wing unmanned aerial vehicle barycenter, m is quality, and the flight attitude of four rotor wing unmanned aerial vehicles is by attitude angle Θ=[φ, θ, ψ] ^tdescribe, roll angle φ is axis z _bwith by axis x _bvertical guide between angle, be just to the right during rolling; Pitching angle theta is axis x _band angle between surface level is just upwards during pitching; Crab angle ψ is axis x _bprojection in the horizontal plane and earth's axis x _ebetween angle, driftage is for just to the right; U=[U ₁, U ₂, U ₃, U ₄] ^tcontrol vector, U ₁lifting or Hovering control amount, U ₂, U ₃, U ₄rolling respectively, pitching and driftage controlled quentity controlled variable; I _xx, I _yy, I _zzfor axial principal moment of inertia; J _rit is the moment of inertia of rotor; L is the brachium of body; Ω _rit is the relative velocity of rotor;

W=[W ₁, W ₂, W ₃, W ₄, W ₅, W ₆] ^tfor wind disturbance item.

9. modeling method according to claim 8, is characterized in that, when setting up the line equation of motion and rotation equation, does following simplification to unmanned plane:

(1) ignore the distortion of structure, four rotor wing unmanned aerial vehicles are considered as rigid body;

(2) four rotor wing unmanned aerial vehicle housing construction full symmetrics;

(3) ignore the distortion of blade, blade is considered as rigid body;

(4) overlap with body axis system at four rotor wing unmanned aerial vehicle takeoff point upper ground surface coordinate systems;

(5) do not consider that rotor is waved, square proportional relation of lift and anti-twisted moment and gyroplane rotate speed;

(6) effect of ground effect is not considered;

(7) lift coefficient and resistance coefficient are constant;

(8) Eulerian angle speed equals angular speed under body coordinate system.

10. modeling method according to claim 8, is characterized in that, control vector computing formula is as follows:

$U=\left[\begin{array}{c}b({{\mathrm{\&Omega;}}_1}^2+{{\mathrm{\&Omega;}}_2}^2+{{\mathrm{\&Omega;}}_3}^2+{{\mathrm{\&Omega;}}_4}^2)\\ b(-{{\mathrm{\&Omega;}}_2}^2+{{\mathrm{\&Omega;}}_4}^2)\\ b({{\mathrm{\&Omega;}}_1}^2-{{\mathrm{\&Omega;}}_3}^2)\\ d({{\mathrm{\&Omega;}}_1}^2-{{\mathrm{\&Omega;}}_2}^2+{{\mathrm{\&Omega;}}_3}^2-{{\mathrm{\&Omega;}}_4}^2)\end{array}\right];$

Wherein, b is lift coefficient, and d is resistance coefficient, Ω _iit is the angular velocity of rotation of rotor i;

Wind disturbance item is defined as follows:

$W=\left[\begin{array}{c}R\&CenterDot;\underset{i=1}{\overset{4}{\mathrm{\&Sigma;}}}{F}_{W_i}/m\\ R\&CenterDot;\underset{i=1}{\overset{4}{\mathrm{\&Sigma;}}}{F}_{W_i}/m\\ R\&CenterDot;\underset{i=1}{\overset{4}{\mathrm{\&Sigma;}}}{F}_{W_i}/m\\ l(-{F_{w_2}}^2+{F_{w_4}}^2){\mathrm{/I}}_{xx}\\ l({F_{w_1}}^2-{F_{w_3}}^2){\mathrm{/I}}_{yy}\\ (M_{w_1}-M_{w_2}+M_{w_3}-M_{w_4})/I_{zz}\end{array}\right].$