基于相对速度偏角的带落角约束滑模导引律

Guidance Law with Impact Angle Constraint Based on Relative Velocity Deflection Angle

为满足导弹的末端落角约束要求,提高毁伤效能,基于有限时间控制和终端滑模控制理论,提出了一种带落角约束的滑模导引律。该导引律选取终端滑模面,包含弹目相对速度偏角和落角约束项,采用快速幂次趋近律,可实现制导系统状态的有限时间收敛,满足命中精度和落角约束的要求。运用有限时间控制理论对该导引律进行了分析,证明了制导系统状态的有限时间收敛特性,并给出了收敛时间的具体表达形式。最后,进行了对比仿真分析,仿真结果验证了该导引律的有效性、鲁棒性和优越性。

Aiming at the requirement of the missile terminal impact angle constraint to enhance the damage efficiency,a sliding mode guidance law with impact angle constraint is proposed based on finite-time control and terminal sliding mode control theories. This guidance law chooses terminal sliding mode that contains relative velocity deflection angle and impact angle constraints,and selects the fast power reaching law to ensure that the states of the guidance system are converged in finite time and satisfy the requirement of hit precision and impact angle constraint. The law is analyzed by utilizing the finite-time control theory,thus the finite-time convergent feature of the guidance system states is proved,and the mathematical expression of convergent time is given. Finally,a contrast simulation is made and the simulation results verify the effectiveness,robustness and superiority of the proposed guidance law.