可攔截機(jī)動(dòng)目標(biāo)的終端角度約束制導(dǎo)律

李憲強(qiáng)，周 軍

(西北工業(yè)大學(xué)精確制導(dǎo)與控制研究所，西安 710072)

0 Introduction

In modern warfare，not only a small miss distance is required for the missiles，and in order to enhance the attacking effectiveness，but also certain impact angle constraints are also needed to be met［1］．Such as inverse trajectory interception is always employed to enhance the matching efficiency of fuse and warhead．And the desired direction of the velocity vector of the missile should be opposite to that of the target．In order to enhance the penetration effect when attacked fortification，the missile needs to attack the target in vertically direction．

The sliding mode control possesses the advantages of strong robustness and easy to implement，so it is widely used in the design of the guidance law with impact angle constraint．But for the guidance law with angle constraint designed based on the conventional sliding mode control，only asymptotical stability can be maintained．While the demand of the guidance law with finite-time stability is growing in modern warfare．For example，in the air-combat，the guidance laws with impact angle constraint with finite-time convergence is especially important［4－5］．In this regard，some scholars developed lots of corresponding finite-time guidance law based on the terminal sliding mode control theory．For instance，in References［6-7］the conventional terminal sliding mode control theory is used in the development of the finite-time guidance law，while there are singularities in the guidance laws developed in References［6-7］，and the guidance command may be saturated in the application．To tackle the singularity issue，the non-singular terminal sliding mode control theory is employed in the development of the finite-time guidance law with impact angle constraint in the References［4-8］．However，the finite-time guidance laws，which are developed in the above references，are generally characterized with discontinuity．The discontinuity in the guidance law can cause chattering，which may reduce the guidance accuracy，and even lead to system instability［1］．To alleviate the chattering，in Reference［9］a finite-time guidance law is designed based on the high-order sliding mode control theory．In the high-order sliding mode control theory，the control parameter should be chosen greater than the bound of the disturbance．And large control parameters will reduce the chattering suppression effect［10］．While in practice，for safety reasons，the actual bound of the disturbance often is chosen larger，so the parameters of high-order sliding mode control are always selected larger．Thus the chattering suppression effect may be degraded．

In this paper，a novel adaptive high-order sliding mode control is developed，in which the control parameters are adaptive to the disturbance．Thus the conservatism in choosing the control parameters can be greatly reduced．And the chattering of the sliding mode control will be greatly alleviated too．Moreover，in this paper the adaptive super-twisting algorithm is combined with the integral sliding mode surface for the first time．And based on this，a finite-time disturbance compensator is designed．Then the geometric homogeneous theory is employed to design a finite-time controller for the compensated system．The controller design method is then used in the designing of the guidance law with impact constraint angle，and a finitetime continuous guidance law is successfully developed．The effectiveness of the designed guidance law is also verified through three-dimension simulation．

1 Preliminaries

1．1 Design of the adaptive super-twisting algorithm

Lemma 1．Super-twisting algorithm［11］Consider the system as following:

in which，e1，e2∈R denote the states，ρ∈R denotes the disturbance，andThe states e1，e2will be globally finite-time stable，if k2＞τ and＞4k2．

The super-twisting algorithm proposed in Lemma 1 belongs to the high-order sliding mode control theory，in which the discrete switching term hides in the integral part of the input，so the chattering of the sliding mode control can be effectively alleviated．Through analysis it can be concluded that the control parameters of the super-twisting algorithm need to be larger than the bound of the disturbance．However，the precise bound of the disturbance is difficult to be obtained in practice．And in controller design，the bound of the disturbance is always chosen much larger than the actual value of the disturbance．And then the control parameters of the super-twisting algorithm will be chosen much larger，which will makes the chattering alleviating effect become worse［10］．To ensure the chattering alleviating effect，in this section，the super-twisting algorithm will be improved and an adaptive super-twisting algorithm will be developed，in which，the control parameters is adaptive to the disturbance．

Theorem 1．Adaptive super-twisting algorithm

Consider the system as follows:

where，L(t)=r+l，l is a constant and l＞0．

where，γ＞0，and

in which，ε is a positive constant．When the parameters are chosen as those denoted by equation(3)，e1(t)can converge to the intervalin finite time，in which，a is an arbitrary constant value and a＞1．

Proof．The lyapunove function is chosen as:

here，

According to equation(8)，one can obtain

According to equation(9)，one has

Noting equation(3)and

then from equation(13)，we have

Form equation(10)，we know

Substituting(11)，(13)and(16)into(7)，yields

(1)When L(t)=r+l≥τ，from(17)it can be concluded that≤0．

Based on the analysis above，we knownwhen e1is out of the interval，so e1is bounded．Defining a larger intervalaε}，and in the interval＜－? and ? is a positive constant which is relevant to the value of a．So e1can converge to the interval R1in finite time，and thenaε．The Theorem 1 is proved．

1．2 A finite-time composite control law designed based on adaptive super-twisting algorithm

Consider a system with disturbance as following:

where，xidenote the states，u=u1+uf，u1denotes the controller of the nominal system，ufdenotes the compensation law，f denotes disturbance．

For the system above，a compensator will be proposed in the following Theorem 2．

Theorem 2．For the system denoted as(19)，when the disturbance compensator is chosen as following:

where，k1and k1are chosen as those in Theorem 1，and

Then the sliding mode surface s1will converge to zero in finite time under the control of uf．And on the sliding mode surface，the disturbance is nearly fully compensated．So the system on the sliding mode surface can be viewed as a nominal system as following，which is without the disturbance．

Proof．Firstly，the integral sliding mode surface is designed as following:

Differentiating the equation(23)and combing with(19)，we have

According to Theorem 1，we known the reaching law as(25)is able to maintain s1which can converge to zero in finite time．When s1converges to zero，uf+f≈0 can be obtained from(24)．And then the system(19)reduces to the nominal system as(22)，which is without disturbance．

Remark 1．If the initial value of x2can be obtained，the approaching process of the sliding mode surface can be eliminated．According to equation(23)，the sliding mode surface is improved as following:

It is obviously that in(26)，the initial value of the sliding mode surface s1is zero，so the approaching process of the sliding mode surface is eliminated．

Remark 2．Through compensation，the disturbed system(19)can reduce to the nominal system(22)in finite time．In the following，a finite-time control law will be designed for the nominal system(22)．

1．3 A finite-time controller designed based on geometric homogeneous theory

Consider a kind of integral chain system as following:

where，xi(i=1，2…，r)are the states，u denotes input．For the system as(27)，the following lemma holds．

Lemma 3［12］．In equation(27)，when the input is chosen as(28)，then the states of the system(27)will converge to zero in finite time．

here，vi∈(1－ε，1)，ε∈(0，1)．k1，…，krare positive constants which can maintain the polynomial pr+krpr－1+…+k2p+k1is Hurwitz．v1…visatisfyr}and vr+1=1，vr=vr．

Remark 3．According to Theorem 2 and Lemma 3，we know if the input of(19)is designed as u=u1+uf，in which u1and ufare denoted as equation(20)and(28)separately，system(19)will be finite-time stable．

2 Modeling

2．1 Modeling of the engagement geometry

The engagement geometry between the missile and the target can be shown as Fig 1．

Fig．1 Engagement geometry

According to the geometry in Fig．1，the modeling equation can be formulated as:

where，θmdenotes the flight path angle of the missile，θtdenotes the flight path angle of the target．vmdenotes the velocity of the missile and vtdenotes the velocity of the target．R denotes the relative distance and q denotes the angle of the line of sight(LOS)．

2．2 Modeling of the impact angle constraint

In the design of the guidance law with impact angle constraint，it is desired that the missile can intercept the target along with a desired direction．So at the impact time，the direction of the missile velocity vector shall meet the following constraint:

where，θddenotes the desired flight path angle．If it is desired a head-on interception，then θd=θt－π．

If it is assumed that qdis the desired angle of the LOS at the impact time，the following equation holds．

Such that，one can uniquely determine the desired angle of sight，when the flight path angle of the target and the desired flight path angle of the missile are known．

2．3 Modeling of the LOS rate

Combing with the model above，and selecting the new states as，the equation of states can be established as follows when intercepting the maneuvering targets．

3 Design of the guidance law

Based on equation(32)，the guidance law is designed as following:

Under the control of the equation(33)，the system(32)will reduce to the equation as following:

In equation(34)，it is assumed that ueqis the equivalent control law when the system is without disturbance．And it can ensure that the system is finite-time stable，ufis a compensator，which is used to compensate the disturbance f．

3．1 Design of the compensator

In this section，a compensator ufwill be designed，which can fully compensate the disturbance f in finite time．And then the system(34)will reduce to a nominal system without disturbance．Based on Theorem 2，the compensator can be designed as following:

where，the parameters are selected according to Theorem 1．

Then，according to Theorem 2，uf+f can converge to zero in finite time，such that the disturbance can be fully compensated in finite time．And then the system(19)can reduces to the nominal system as following:

In the following，a finite-time stable control law uequwill be designed based on the nominal system．

3．2 Controller design based on the geometric homogeneous theory

in which，μ1=0．25，μ2=0．4．λ1and λ2are positive constants which can ensure that p2+λ2p+λ1is Hurwitz．

In summary，combing equations(33)，(35)，(36)with(38)，the guidance law can be obtained as:

In this section，a controller will be designed based on the geometric homogeneous theory．The controller should ensure that the system is asymptotically stable and possesses suitable negative homogeneous degree．And the finite time stability of the system(32)will be achieved when the system(32)is asymptotically stable and possesses suitable negative homogeneous degree．The corresponding controller is designed as follows based on Lemma 3．

From the guidance law(39)，we know that it is continuous nonsingular and finite-time stable．So the saturation cased by singularity can be avoided．And the chattering cased by non-discontinuous sliding mode control can also be avoided．Moreover，the parameters of the compensator are adaptive in guidance law(39)，thus it can avoid the performance degradation caused by improperly selected parameters．

4 Simulation

In this section，the guidance law proposed in this paper(ISMCFTGL)will be simulated．And for comparison，the guidance law with impact angle constraint(SMCGL)proposed in reference［1］，which is designed based on sliding mode control，will be also simulated．The SMCGL is denoted as:

In the following，both the case of intercepting constant velocity target and the case of intercepting the maneuvering target will be simulated．

4．1 Simulation for non-maneuvering target

It is desired that the missile can intercept the target along the invere trajectory of the target．In simulation，the position of the interceptor is selected as xm=0，ym=0，zm=0．The parameters relevant to the velocity of the interceptor are selected as vm=400，θ=45°，ψm=－40°．The position of the interceptor is selected as xt=7 500，yt=5 000，zt=4 330．The parameters relevant to the velocity of the target are selected as vt=300 m/s，θt=150°，ψt=150°．

The parameters of ISMCFTG used in longitudinal channel and lateral channel are the same．And they are λ1=4，λ2=4，r(0)=0．5，l=0．6，ε=0．001，γ=15．The parameters of SMCGL in longitudinal channel and lateral channel are the same too．And they are λ=3，k=4，ε=1．

The comparison simulation resultes are decipited as Table 1 and Fig．2 ～ Fig．5．

Table 1 Miss distance and the angle tracking error when intercepting the non-maneuvering target

Fig．2 Comparison of the trajectories，when intercepting the non-maneuvering target

Fig．3 Comparison of the payloads，when intercepting the non-maneuvering target

Fig．4 Comparison of the velocity of the line-of-sight，when intercepting the non-maneuvering target

From Fig．4，it can be concluded that，when intercepting the non-maneuvering target，ISMCFTGL can effectively control the LOS rate converge to the neighborhood of zero，while the LOS rate under the control of SMCGL diverges slowly．Therefore，it is verified that the guidance performance of ISMCFTGL is better than that of SMCGL．The advantage of ISMCFTGL is also reflected in Fig．3 and Table 1．Such that，the needed overload of ISMCFTGL，at the impact time，is smaller than that of SMCGL(see Fig．3)，so that the miss distance is smaller and the tracking accuracy to the desired LOS angle is also higher than that of SMCGL(see Table 1)．

Fig．5 Comparison of the true values and the estimates of the disturbance

In Fig．5，it shows a comparison of the estimated value and the true value of the disturbance in equation(31)．Through simulaton results，it can be concluded that the disturbance can be estimated accurately，thus it can maitains the guidance law controls the LOS rate effectively．

4．2 Simulation for maneuvering target

In this section it is also desired that the missile can intercept the target along the invere trajectory of the target．The longitudinal acceleration of the target is atz=50sin(0．8t)，and the lateral acceleration is atc=50sin(0．8t)．The other parameters are selected the same as those in section 4．1．the simulation results are decipited as Fig．6 ～ Fig．9 and Table 2．

Fig．6 Comparison of the trajectories，when intercepting the maneuvering target

Fig．7 Comparison of the payloads，when intercepting the maneuvering target

Fig．8 Comparison of the velocities of the line-of-sight，when intercepting the maneuvering target

Fig．9 Comparison of the true values and the estimates of the disturbance

Table 2 Miss distance and the angle tracking error when intercepting the maneuvering target

According to the simulation results，it can be concluded that the performance of ISMCFTGL in suppressing the LOS rate，in the last paragraph of the interception，is better than that of SMCGL(Fig．8)．And the overload of ISMCFTGL is much smaller(Fig．7)，which effectively reduce the miss distance and the tracking error to the desired LOS angle(Table 2)．The reason to obtain such a goog effect is that ISMCFTGL can precisely eatimate the disturbance caused by the accelaration of the target and other factors(Fig．9)．And the infulunce to the LOS rate caused by the disturbance can be nearly eliminated completely．Moreover，in the modelling of the LOS rate，the speed characteristic of the target is also fully considered，thus the proposed guidance law ISMCFTGL can effectively intercept the maneuvering target with high speed．

5 Conclusion

In this paper，an adaptive algrithom is firstly proposed through improving the super-twisting algrithom．Then a novel finite-time composite control method is designed through combing with the integral sliding mode surface and geometric homogeneous theory．And the composite control method is then used in designing of the guidance law with impact angle constraint．The proposed guidance law possesses some characteristics as following:

(1)It can not only effectively intercept the non-maneuvering target，but it can also effectively intercept the high maneuvering target．

(2)The guidance law is finite-time stable．

(3)The guidance law is continuous and the parameters are also adaptive．Thus the chattering of the sliding mode conrol is alleviated and the guidance precesion is improved．

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