Partial Integrated Missile Guidance and Control with Finite Time Convergence

Wang, Xianghua; Wang, Jinzhi

doi:10.2514/1.58983

Cited by 86 publications

(73 citation statements)

References 29 publications

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“…Taking the derivative of r * and e r with respect to time, we geṫ r * = −μV 0 min (19) e r =ṙ −ṙ * (20) Substituting Eqs. (1) and (19) into Eq.…”

Section: Design Of Cooperative Strategymentioning

confidence: 99%

“…Many cooperative guidance laws are deduced on the basis of fixed missile velocity [3,10,[13][14][15][16][19][20][21], which is difficult to realize in practice. In this paper, no assumption of fixed missile velocity is made and the velocity is calculated by dynamic equation of missile.…”

Section: Remarkmentioning

confidence: 99%

“…In [19], a suboptimal control method, called θ-D method was employed to obtain an approximate closed-form controller. Missile guidance law and autopilot design were formulated into a single unified state space framework and the cost function was chosen to reflect both guidance and control concerns.…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Integrated guidance and control law for cooperative attack of multiple missiles

Wang

Zheng

Hai

2015

Aerospace Science and Technology

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“…Taking the derivative of r * and e r with respect to time, we geṫ r * = −μV 0 min (19) e r =ṙ −ṙ * (20) Substituting Eqs. (1) and (19) into Eq.…”

Section: Design Of Cooperative Strategymentioning

confidence: 99%

Section: Remarkmentioning

confidence: 99%

See 1 more Smart Citation

Integrated guidance and control law for cooperative attack of multiple missiles

Wang

Zheng

Hai

2015

Aerospace Science and Technology

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“…Therefore, the system response speed was increased. In [20], an adaptive nonsingular TSM control method was proposed for PIGC. The finite-time convergence was separated in both reaching and sliding phases, which could be improved by the novel fast TSM (FTSM) control [21].…”

Section: Introductionmentioning

confidence: 99%

Fast Robust Integrated Guidance and Control Design of Interceptors

Song

Zhang

2016

IEEE Trans. Contr. Syst. Technol.

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In this brief, a fast robust integrated guidance and control design approach, considering the 3-D interception of interceptors for hypersonic vehicles, is proposed. The proposed method is designed using the modified fast terminal sliding mode control and dynamic surface control with signal compensation. The fractional integral fast terminal sliding functions are presented independently, and all the sliding phases run parallel to increase the system response speed. Utilizing the dynamic surface control method, the robust compensation signals are constructed to eliminate the influence of uncertainty equivalents thoroughly. Therefore, the proposed approach guarantees the fast convergence of line-of-sight angular rates and the system robustness for uncertainties. The simulation results demonstrate the robustness of the proposed controller, and a variety of comparison studies are also carried out to demonstrate the advantage of the new approach.Index Terms-Dynamic surface control, fast terminal sliding mode (FTSM) control, integrated guidance and control (IGC), interceptor.

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“…(4) in [1] to guarantee the finite time convergence under the initial estimation valued max 0 arbitrarily chosen and the bound of disturbance d max unknown. In this case, the updating law is very necessary.…”

mentioning

confidence: 99%

Reply by the Authors to K. B. Li and L. Chen

Wang

2016

Journal of Guidance, Control, and Dynamics

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We thank K. B. Li and L. Chen for their comments on our papers. The comment on "Partial Integrated Missile Guidance and Control with Finite Time Convergence" can be summarized and categorized as follows.1) The updating law may be not necessary for the control law to guarantee the finite time convergence.2) The control command may also become quite large or even exceed the physical limitation.We make the following reply to the comments. 1) Under the assumption that the initial estimation valued max 0 satisfies the inequality d max −d max 0σ < 0, point 1 of the comment is correct, namely, the updating law in the original paper is actually not necessary to guarantee the finite time convergence to zero of sliding variable s.However, ifd max t is not updated by the adaptive law as stated in the comment, then it will be difficult to determine how large the constantd max should be chosen in practice to satisfy the inequality d max −d max tσ < 0 under the consideration that the bound of disturbance d max is unknown. We also ignore this point in our original paper. In the following, a small modification is introduced to the updating law in the original paper, with which finite time convergence will be guaranteed under the initial estimation valuê d max 0 arbitrarily chosen and the bound of disturbance d max unknown.2) Point 2 of the comment is not correct. We can get the following results from the proof of theorem 1 in; hence, the control command will not become quite large.3) Here, a small modification is introduced to the updating law, namely, Eq. (4) in [1] to guarantee the finite time convergence under the initial estimation valued max 0 arbitrarily chosen and the bound of disturbance d max unknown. In this case, the updating law is very necessary.The updating law is modified as follows:the initial valued max 0 is an arbitrarily positive constant, σ ≥ 1 and 0 < ε < 1. s is the sliding variable, and s x 2 αjx 1 j ρ sgnx 1 ; see Eq.(2) in [1]. We rewrite theorem 1 as follows.Theorem 1: Consider the system _ x 1 x 2 ; _ x 2 fx; t bx; tu dx; t with the terminal sliding variable s x 2 αjx 1 j ρ sgnx 1 . Under the conditions that the bound of disturbance d max is unknown and the initial estimation valued max 0 is arbitrarily chosen, using the control law u bx; t −1 −fx; t −d max σs∕jsj − λx 1 x 2 − kjsj γ sgns, namely, Eq. (3) in [1] and the modified updating law Eq. (1), the states of the system can reach the sliding surface in finite time and then converge to the origin along the sliding surface in finite time, too. The updating law Eq. (1) has actually the following form: _d max 8 < :σjsj; jsj ≥ ε σjsj arccos jsj; jsj < ε and jsj≢0 0;jsj ≡ 0When jsj ≥ ε,d max t d max 0 σ∫ t 0 jsj dτ ≥d max 0 σεt. Hence, σd max t − d max ≥ σd max 0 − d max σ 2 εt. It is obtained that, when t ≥ T 1 withthe inequality d max −d max tσ < 0 holds. In summary, as long as jsj≢0, σd max t − d max will be always larger than an increasing linear function of time t. Hence, there exists finite time T, for any t ≥ T, the inequality d max −d max tσ < 0...

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Partial Integrated Missile Guidance and Control with Finite Time Convergence

Cited by 86 publications

References 29 publications

Integrated guidance and control law for cooperative attack of multiple missiles

Integrated guidance and control law for cooperative attack of multiple missiles

Fast Robust Integrated Guidance and Control Design of Interceptors

Reply by the Authors to K. B. Li and L. Chen

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