Abstract
This paper proposes a new terminal homing guidance law with line-of-sight angle constraint for a missile to intercept a noncooperative maneuvering target by integrating prescribed performance control with sliding mode control. The newly proposed guidance law is derived analytically with a prescribed performance controller in combination with the continuous nonsingular terminal sliding mode manifold and the disturbance observer. The prescribed performance controller is designed with a new prescribed performance function to avoid undesired abrupt change in the derivative of prescribed performance variable. In addition to its robustness and preciseness, this new homing guidance law is able to attenuate a largely abrupt change in guidance commands due to driving the sliding mode variable whose initial derivative is close to zero to a desired residual set at the beginning of the terminal homing phase. Furthermore, the time-varying control gain of the new guidance law is analytically determined by terminal tolerance. Theoretical analysis and numerical simulations are conducted to demonstrate the effectiveness of this new guidance law.
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References
He, S., Lin, D., Wang, J.: Robust terminal angle constraint guidance law with autopilot lag for intercepting maneuvering targets. Nonlinear Dyn. 81(1), 881–892 (2015)
Zarchan, P.: Tactical and Strategic Missile Guidance. American Institute of Aeronautics and Astronautics Publications, New York (1998)
Padhi, R., Chawla, C., Das, P.G.: Partial integrated guidance and control of interceptors for high-speed ballistic targets. J. Guid. Control Dyn. 37(1), 149–163 (2013)
Shneydor, N.A.: Missile Guidance and Pursuit: Kinematics, Dynamics and Control. Horwood Publish, Cambridge (1998)
Sarkar, A.K., Ghose, D.: Realistic pursuer evader engagement with feedback linearization based nonlinear guidance law. In: AIAA Guidance, Navigation,and Control Conference and Exhibit, pp. 2006–6096 (2006)
Menon, P.K., Ohlmeyer, E.J.: Integrated design of agile missile guidance and autopilot systems. Control Eng. Pract. 9(10), 1095–1106 (2001)
Gil, W., Ilan, R.: All-aspect three-dimensional guidance law based on feedback linearization. J. Guid. Control Dyn. 38(12), 2421–2428 (2015)
Qu, P., Shao, C., Zhou, D.: Finite time convergence guidance law accounting for missile autopilot. J. Dyn. Syst.-T. ASME. 137(5), 051014 (2015)
Song, J.H., Song, S.M.: Three-dimensional guidance law based on adaptive integral sliding mode control. Chin. J. Aeronaut. 29(1), 202–214 (2015)
Song, H., Zhang, T., Zhang, G., Lu, C.: Robust dynamic surface control of nonlinear systems with prescribed performance. Nonlinear Dyn. 76(1), 599–608 (2014)
Bechlioulis, C., Provithakis, G.: Adaptive control with guaranteed transient and steady state tracking errors bounds for strict feedback systems. Automatica 45(2), 532–538 (2009)
Kim, B.S., Lee, J.G., Han, H.S.: Biased PNG law for impact with angular constraint. IEEE Trans. Aerosp. Electron. Syst. 34(1), 277–288 (1998)
Ryoo, C.K., Cho, H., Tahk, M.J.: Optimal guidance laws with terminal impact angle constraint. J. Guid. Control Dyn. 28(4), 724–732 (2005)
Sun, X., Xia, Y.: Optimal guidance law for cooperative attack of multiple missiles based on optimal control theory. Int. J. Control 85(8), 1063–1070 (2012)
Zhou, D., Sun, S.: Guidance laws with finite time convergence. J. Guid. Control Dyn. 32(6), 1838–1846 (2009)
Zhang, Y.X., Sun, M.W., Chen, Z.Q.: Finite-time convergent guidance law with impact angle constraint based on sliding mode control. Nonlinear Dyn. 70(1), 619–625 (2012)
Wang, X.H., Wang, J.Z.: Partial integrated missile guidance and control with finite time convergence. J. Guid. Control Dyn. 36(5), 1399–1409 (2013)
Lu, K., Xia, Y.: Finite-time Intercept-angle guidance. Int. J. Control 88(2), 264–275 (2015)
Kumar, S.R., Rao, S., Ghose, D.: Nonsingular terminal sliding mode guidance with impact angle constraints. J. Guid. Control Dyn. 37(4), 1114–1130 (2014)
Zhou, J., Yang, J.: Smooth sliding mode control for missile interception with finite-time convergence. J. Guid. Control Dyn. 38(7), 1311–1318 (2015)
He, S., Lin, D.: Sliding mode-based continuous guidance law with terminal angle constraint. Aeronaut. J. 120(1229), 1175–1195 (2016)
Shima, T.: Intercept-angle guidance. J. Guid. Control Dyn. 34(2), 484–492 (2011)
Yin, C., Cheng, Y.Q., Chen, Y., Stark, B., Zhong, S.: Adaptive fractional-order switching-type control method design for 3D fractional-order nonlinear systems. Nonlinear Dyn. 82(1), 39–52 (2015)
Yin, C., Chen, Y.Q., Zhong, S.: Fractional-order sliding mode based extremum seeking control of a class of nonlinear systems. Automatica 50(12), 3173–3181 (2014)
Feng, Y., Han, F., Yu, X.: Chattering free full-order sliding-mode control. Automatica 50(4), 1310–1314 (2014)
Feng, Y., Yu, X., Man, Z.: Non-singular terminal sliding mode control of rigid manipulators. Automatica 28(11), 2159–2167 (2002)
Yu, S., Yu, X., Shirinzadeh, B., Man, Z.: Continous finite-time control for robotic manipulators with terminal sliding mode. Automatica 41(11), 1957–1964 (2005)
Lu, K., Xia, Y.: Adaptive attitude tracking control for rigid spacecraft with finite-time convergence. Automatica 49(12), 3591–3599 (2013)
Hong, Y., Huang, J., Xu, Y.: On an output feedback finite-time stabilization problem. IEEE Trans. Autom. Control 46(2), 305–309 (2001)
Shtessel, Y.B., Shkolnikov, I.A., Levant, A.: Guidance and control of missile interceptor using second-order sliding modes. IEEE Trans. Aerosp. Electron. Syst. 45(1), 110–124 (2009)
Ginoya, D., Shendge, P.: Sliding mode control for mismatched uncertain systems using an extended disturbance observer. IEEE Trans. Ind. Electron. 61(4), 1983–1992 (2014)
Ding, S., Zhang, Z., Chen, X.: Guidance law design based on non-smooth control. Trans. Inst. Meas. Control 35(8), 1116–1128 (2013)
Zhang, X., Yao, Y., He, F.: A study on biased guidance problem ofthe space flight vehicle. In: Control Conference (CCC), 2016 35thChinese. TCCT, pp. 5671–5676 (2016)
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This work is supported by the China Scholarship Council and the Discovery Grant of the Natural Sciences and Engineering Research Council of Canada (NSERC).
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Appendix
Appendix
The parameter \(\alpha \) at \(t\ge t_0\) is determined by following steps.
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Step 1 Determine an inequality
$$\begin{aligned} \exp \left( {-\alpha \left( {t-t_0} \right) } \right) -1{+}\alpha \left( {t-t_0} \right) >\alpha \left( {t-t_0} \right) {-}1\nonumber \\ \end{aligned}$$(43) -
Step 2 Determine the interception initial time-to-go for missile as,
$$\begin{aligned} t_{go} =\frac{R_f -R_0}{{\dot{R}}_0} \end{aligned}$$(44) -
Step 3 Determine the precision of PPV \(\rho _1 (t_f, R_f)\) at terminal time
(45)where \(\zeta \) is a positive constant which satisfies \(\zeta \le \rho _\mathrm{end}\) and \(t_f\) represents the terminal time.
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Step 4 Determine the value of \(\alpha \).
$$\begin{aligned} \alpha\approx & {} \frac{\ln \left( {{\left( {\left. {s_e} \right| _{t=t_0} -\rho _\infty } \right) }/{\rho _1 \left( {t_f ,R_f } \right) }} \right) R_f}{R_0 t_{go}} \nonumber \\&+\,\frac{1+\Delta }{t_{go}} \end{aligned}$$(46)where \(\Delta \) is a positive constant to speed up the convergence of \(\rho _1 (t,R)\) and assure the terminal precision of \(\rho _1 (t_f ,R_f)\).
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Lyu, S., Zhu, Z.H., Tang, S. et al. Prescribed performance slide mode guidance law with terminal line-of-sight angle constraint against maneuvering targets. Nonlinear Dyn 88, 2101–2110 (2017). https://doi.org/10.1007/s11071-017-3365-9
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DOI: https://doi.org/10.1007/s11071-017-3365-9