摘要
设计了一种连续且有限时间稳定的终端角约束制导律,该制导律不但能够打击非机动目标而且能有效打击机动性的目标。文中首先将超扭曲算法进行改进,设计了一种自适应超扭曲算法,该算法的参数是随着干扰的大小自动调节的,从而避免了常规的超扭曲算法由于参数选取不当而引起的对滑模抖振的抑制能力下降。文中将自适应超扭曲算法首次与积分滑模相结合,设计了一种有限时间收敛的干扰补偿器,该干扰补偿器能够在有限时间内对干扰进行精确补偿,然后采用几何齐次理论针对干扰补偿后的系统设计了有限时间收敛控制器。以上干扰观测器和控制器组成的复合控制律,能够保证系统的有限时间稳定性,此外该控制律不但是连续的,而且参数是自适应的,因而大大降低了滑模的抖振特性。文中将以上控制理论应用于终端角约束制导律的设计过程中,最后通过仿真验证了该制导律的有效性。
A continuous finite-time stabilization guidance law with terminal impact angle constrained is presented in this paper,which can be used to intercept the non-maneuvering and maneuvering target. Firstly,an adaptive super-twisted algorithm is designed based on the super-twisted algorithm,which can effectively alleviate the chattering,through using the adaptive parameters. A finite-time stabilization disturbance compensator is designed based on the adaptive super-twisted algorithm and the integrated sliding surface. Secondly,the geometric homogeneous theory is employed to design the finite-time stabilization controller for the compensated nominal system. The controller,composited by above disturbance observer and the geometric homogeneous theory controller,can ensure the system＇s finite time convergence. In addition,the composite controller is continuous and the parameters are adaptive,which can effective suppress the chattering of the sliding mode. The above control theory is applied to design the guidance law with terminal impact angle constrained,and the effectiveness of the guidance law is verified through simulation.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2015年第5期614-621,共8页
Journal of Solid Rocket Technology
基金
Natural Science of China(61304238)
National High-tech R&D Program of China(863)(2012AA120602)
关键词
终端角约束
制导律
有限时间稳定
滑模
terminal impact angle constrained
guidance law
finite-time stabilization
sliding mode
