This paper proposes the three-dimensional impact angles constrained integral sliding mode guidance laws for the missile with the constraint of the input saturation. To solve the problem of the input constraint, an integral sliding mode surface is given for the first time by using the saturation function. The first three-dimensional integral sliding mode guidance law can solve the impact angle constraint and the target accelerations with known upper bound, while the second one can solve the impact angle constraint, input saturation, and the target accelerations with unknown upper bound simultaneously. Finally, numerical simulations are used to verify the effectiveness of the guidance laws.
YangC-DYangC-C. Analytical solution of three-dimensional realistic true proportional navigation. J Guid Control Dyn1996; 19(3): 569–577.
2.
SuWYaoDLiK, et al.A novel biased proportional navigation guidance law for close approach phase. Chin J Aeronautics2016; 29(1): 228–237.
3.
LinY-PLinC-LLiY-H. Development of 3-D modified proportional navigation guidance law against high-speed targets. IEEE Trans Aerosp Electron Syst2013; 49(1): 677–687.
4.
PanditSPanchalBTaloleSE. Design of three-Dimensional Guidance Law for tactical missiles. 2018 AIAA Guidance, Navigation, and Control Conference, Kissimmee, Florida, 8–12 January 2018, p. 1323.
5.
ZhaoJZhouRDongZ. Three-dimensional cooperative guidance laws against stationary and maneuvering targets. Chin J Aeronautics2015; 28(4): 1104–1120.
6.
HeSLinD. Three-dimensional optimal impact time guidance for antiship missiles. J Guid Control Dyn2018; 42(4): 941–948.
7.
WeissGRusnakI. All-aspect three-dimensional guidance law based on feedback linearization. J Guidance, Control Dyn2015; 38(12): 2421–2428.
LiGJiH. A three-dimensional robust nonlinear terminal guidance law with ISS finite-time convergence. Int J Control2016; 89(5): 938–949.
10.
WangZMaJFuJ. Research on sliding mode method about three-dimensional integrated guidance and control for air-to-ground missile. J Aerospace Techn Manag2019; 11(1), doi:10.5028/jatm.v11.982.
11.
GeLShenYGaoY, et al.Head pursuit variable structure guidance law for three-dimensional space interception. Chin J Aeronautics2008; 21(3): 247–251.
12.
SongJSongSXuS. Three-dimensional cooperative guidance law for multiple missiles with finite-time convergence. Aerospace Sci Techn2017; 67: 193–205.
13.
SongJSongS. Three-dimensional guidance law based on adaptive integral sliding mode control. Chin J Aeronautics2016; 29(1): 202–214.
14.
HeSWangWWangJ. Three-dimensional impact angle guidance laws based on model predictive control and sliding mode disturbance observer. J Dynamic Syst Meas Control2016; 138(8): 081006.
15.
HuQHanTXinM. Three-dimensional guidance for various target motions with terminal angle constraints using twisting control. IEEE Trans Ind Electron2019; 67(2): 1242–1253.
16.
WangXWangJ. Partial integrated guidance and control for missiles with three-dimensional impact angle constraints. J Guid Control Dyn2014; 37(2): 644–657.
17.
LeeYKimY. Three-dimensional impact angle control guidance law for missiles using dual sliding surfaces. IFAC Proc Volumes2013; 46(19): 137–142.
LaiCWangWLiuZ, et al.Three-dimensional impact angle constrained partial integrated guidance and control with finite-time convergence. IEEE Access2018; 6: 53833–53853.
20.
LyuTLiCGuoY, et al.Three-dimensional finite-time cooperative guidance for multiple missiles without radial velocity measurements. Chin J Aeronautics2019; 32(5): 1294–1304.
21.
GuoYHuangBLiA, et al.Integral sliding mode control for Euler‐Lagrange systems with input saturation. Int J Robust Nonlinear Control2019; 29(4): 1088–1100.
22.
SunJ-GSongS-MChenH-T, et al.Finite-time tracking control of hypersonic aircrafts with input saturation. Proc Inst Mech Eng G: J Aerospace Eng2018; 232(7): 1373–1389.
23.
GuoYHuangBSongS, et al.Robust saturated finite-time attitude control for spacecraft using integral sliding mode. J Guid Control Dyn2018; 42(2): 440–446.
24.
ShiehC-S. Design of three-dimensional missile guidance law via tunable nonlinear H∞ control with saturation constraint. IET Control Theor Appl2007; 1(3): 756–763.
25.
WangWXiongSWangS, et al.Three dimensional impact angle constrained integrated guidance and control for missiles with input saturation and actuator failure. Aerospace Sci Techn2016; 53: 169–187.
26.
LiuWWeiYDuanG. Barrier Lyapunov function-based integrated guidance and control with input saturation and state constraints. Aerospace Sci Techn2019; 84: 845–855.
27.
ZhouDXuB. Adaptive dynamic surface guidance law with input saturation constraint and autopilot dynamics. J Guid Control Dyn2016; 39: 1155–1162.
28.
SongJSongS. Robust impact angle constraints guidance law with autopilot lag and acceleration saturation consideration. Trans Inst Meas Control2019; 41(1): 182–192.
29.
WangLJinWZLiGY. Three-dimensional adaptive dynamic surface guidance law against maneuvering targets with input constraints and second-order dynamics autopilot. Int J Innovative Comput Inf Control2018; 14(5): 1725–1739.
30.
YanHJiH-B. Guidance laws based on input-to-state stability and high-gain observers. IEEE Trans Aerosp Electron Syst2012; 48(3): 2518–2529.
31.
GuoYHuangBGuoJ-h, et al.Velocity-free sliding mode control for spacecraft with input saturation. Acta Astronautica2019; 154: 1–8.
