Due to the modern battlefield environment, the new and challenging demands on the development of precision-guided weapons are proposed, and the terminal guidance and control problem with multiple constraints and complex environments become a hot issue in the world. However, since the complexity of the environments, nonlinearity, strong coupling and time variability of the flight vehicle's movement, it is difficult to do some research on system modeling and designing the guidance laws. In this work, we research on terminal guidance law with multiple constraints such as terminal angle constraint, terminal acceleration constraint, and attack time et al., which has important theoretical significance and broad engineering values. We choose three typical multiple constraints which are impact angle constraint, impact angle and acceleration constraints, impact angle and time constraints to research on the terminal guidance law designing problem. Firstly, to solve the problem of the robust guidance law with impact angle constraint, we propose an adaptive neuro-fuzzy inference system sliding mode control (ANFSMC) guidance law and a wavelet neural network sliding mode control (WNNSMC) guidance law. Secondly, a fuzzy sliding mode control (FSMC) guidance law is introduced to overcome the issue of the guidance law with impact angle and acceleration constraints. Finally, in order to solve the problem of the passive guidance law with impact angle and time cooperative constraints, we put forward an improved biased proportional passive guidance law (IBPPGL) method and a leader-follower strategy cooperative passive guidance law (L-FSCPGL) method for multi-missiles. The details and contributions are: In order to solve the problem of the robust guidance law with impact angle constraint, we propose two robust guidance law methods, namely, the ANFSMC guidance law and the WNNSMC guidance law. Both of two methods choose the same nonlinear sliding surface which can converge to convergent state in finite time and do not need to simplify the movement model between the flight vehicle and the target. The difference between the ANFSMC guidance law and the WNNSMC guidance law is that: they use the adaptive neuro-fuzzy inference system and the wavelet neural network to adjust the guidance gain, respectively. Thus, the system chattering is weakened and robustness is strengthened highly. Experiments compared with sliding mode control (SMC) guidance law illustrate that the p...
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