Three-dimensional finite-time guidance laws are proposed in this paper. Differing from the traditional approach that considers homing guidance problems as two identical and perpendicular channels, guidance laws proposed in this paper employ the coupled three-dimensional engagement dynamics to improve the guidance precision. A new reaching law is adopted to guarantee guidance laws continuous, which eliminates the chattering phenomenon caused by discontinuous terms. Moreover, the guidance law accelerates the convergence rate of closed-loop systems and avoids the singularity. Afterwards, the paper discusses the problem that the upper bound of the lumped uncertainty including the target information is unavailable. Therefore, to deal with this problem, another adaptive guidance law is presented, which can also guarantee the finite-time convergence of guidance systems. Numerical simulations have demonstrated that the two guidance laws have effective performance and outperform traditional terminal sliding mode guidance laws.
ErerKSMerttopcuogluO (2012) Indirect impact-angle-control against stationary targets using biased pure proportional navigation. Journal of Guidance, Control and Dynamics35(2): 700–704.
2.
FallahaCJSaadMKanaanHY (2011) Sliding-mode robot control with exponential reaching law. IEEE T. Ind. Electron. 58(2): 600–610.
3.
GaoWB (1996) Theory and Design Method of Variable Structure Control. Beijing: Science Press.
4.
HeSWangWWangJ (2016) Three-dimensional impact angle guidance laws based on model predictive control and sliding mode disturbance observer. J. Dyn. Syst. Meas. Contr. 138(8): 081006.
5.
HouMZDuanGR (2008) integrated guidance and control of homing missiles against ground fixed targets. Chinese J. Aeronaut. 21(2): 162–168.
6.
HuangXYanYZhouYHaoDL (2016) Fast terminal sliding mode control of underactuated spacecraft formation reconfiguration. J. Aerospace Eng. 29(5): 10.1061/(ASCE)AS.1943–5525.0000610, 04016020.
7.
KumarSRGhoseD (2017) Three-dimensional impact angle guidance with coupled engagement dynamics. P. I. Mech. Eng. G-J. Aer. 231(4): 621–641.
8.
KumarSRRaoSGhoseD (2014) Nonsingular terminal sliding mode guidance with impact angle constraints. J. Guid. Control Dynam. 37(4): 1114–1130.
9.
LeeCHKimTHTahkMJ (2013a) Design of impact angle control guidance laws via high-performance sliding mode control. P. I. Mech. Eng. G-J. Aer. 227(2): 235–253.
10.
LeeCHKimTHTahkMJ (2013b) Interception angle control guidance using proportional navigation with error feedback. J. Guid. Control Dynam. 36(5): 1556–1561.
11.
LeeCHKimTHTahkMJ (2012a) Optimality of linear time-varying guidance for impact angle control. IEEE Trans. Aerosp. Electron. Syst. 48(4): 2802–2817.
12.
LeeCHKimTHLeeJI (2012b) Analytic solutions of generalized impact-angle-control guidance law for first-order lag system. J. Guid. Control Dynam., 36(1), 96–112.
13.
LiGJiH (2016) A Three-dimensional Robust Nonlinear Terminal Guidance Law with ISS Finite-time Convergence. Int. J. Control89(5): 938–949.
14.
LiuKCaoYWangS (2015) Terminal sliding mode control for landing on asteroids based on double power reaching law. In: IEEE International Conference on Information and Automation, Lijiang, China, 2015. Lijiang: IEEE, pp. 2444–2449.
15.
LiuJHShanJYLiuQ (2016) Optimal pulsed guidance law with terminal impact angle constraint. Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering231(11): 1993–2005.
16.
LiuZZhaoLZhuQGaoC (2017) Design of sliding-mode observer for a class of uncertain neutral stochastic systems. Int. J. Syst. Sci. 48(7): 1380–1394.
17.
OzaHBPadhiR (2012) Impact-angle-constrained suboptimal model predictive static programming guidance of air-to-ground missiles. J. Guid. Control Dynam. 35(1): 153–164.
18.
QuPShaoCZhouD (2015) Finite time convergence guidance law accounting for missile autopilot. J. Dyn. Syst. Meas. Contr. 137(5). DOI: 10.1115/1.4029241.
19.
RaoSGhoseD (2013) Terminal impact angle constrained guidance laws using variable structure systems theory. IEEE T. Contr. Syst. T. 21(6): 2350–2359.
20.
SiYJSongSM (2017) Three-dimensional adaptive finite-time guidance law for intercepting maneuvering targets. Chinese Journal of Aeronautics30(6): 1985–2003.
21.
SongJSongS (2016) Three-dimensional guidance law based on adaptive integral sliding mode control. Chinese J. Aeronaut. 29(1): 202–214.
22.
SongQZMengXY (2012) Design and simulation of guidance law with angular constraint based on non-singular terminal sliding mode. Physics Procedia25(2012): 1197–1204.
23.
SongSHHaIJ (1994) A Lyapunov-like approach to performance analysis of 3-dimensional pure PNG laws. IEEE Trans. Aerosp. Electron. Syst. 30(1): 238–248.
24.
UtkinVIChangHC (2002) Sliding mode control on electro-mechanical systems. Math. Probl. Eng. 8(4–5): 451–473.
25.
WangWXiongSWangS (2016) Three dimensional impact angle constrained integrated guidance and control for missiles with input saturation and actuator failure. Aerospace Science and Technology53(2016): 169–187.
26.
WangZ (2015) Adaptive smooth second-order sliding mode control method with application to missile guidance. Transactions of the Institute of Measurement and Control39(6). DOI: 0142331215621616.
27.
XiongSWangWLiuX (2014) Guidance law against maneuvering targets with intercept angle constraint. ISA T. 53(4): 1332–1342.
28.
XuBZhouDSunS (2016) Finite time sliding sector guidance law with acceleration saturation constraint. IET Control Theory A. 10(7): 789–799.
29.
YuSHYuXHManZH (2005) Continuous finite-time control for robotic manipulators with terminal sliding mode. Automatica41(11): 1957–1964.
30.
ZarchanP (2002) Tactical and Strategic Missile Guidance. Seattle: Astronautics and Aeronautics.
31.
ZhaoJZhouJ (2016) Strictly convergent nonsingular terminal sliding mode guidance law with impact angle constraints. Optik-International Journal for Light and Electron Optics127(22): 10971–10980.
32.
ZhaoLJiaY (2015) Finite-time attitude tracking control for a rigid spacecraft using time-varying terminal sliding mode techniques. Int. J. Control88(6): 1150–1162.
33.
ZhaoLJiaY (2016) Neural network-based distributed adaptive attitude synchronization control of spacecraft formation under modified fast terminal sliding mode. Neurocomputing171(2016): 230–241.
34.
ZhouDSunSTeoKL (2009) Guidance laws with finite time convergence. J. Guid. Control Dynam. 32(6): 1838–1846.
