The explosive formed penetrator （EFP） warhead missile projects the blast fragments in one direction normal to the missile longitudinal axis. Through analyzing on the two restrictions of EFP warhead explosion： traje...The explosive formed penetrator （EFP） warhead missile projects the blast fragments in one direction normal to the missile longitudinal axis. Through analyzing on the two restrictions of EFP warhead explosion： trajectory restriction and attitude requirement, the concept of fuze time-delay tolerance is presented to be the measurement of the time of the EFP warhead explosion. The calculation models of fuze time-delay tolerance under two restrictions are provided. Some crucial parameters playing important roles in calculation under attitude requirements are simulated. The simulation results show that the engagement plane angle, roll rate and warhead attack standoff influence the tolerance dramatically.展开更多
This paper investigates the boost phase＇s longitudinal autopilot of a ballistic missile equipped with thrust vector control. The existing longitudinal autopilot employs time-invariant passive resistor-inductor-capaci...This paper investigates the boost phase＇s longitudinal autopilot of a ballistic missile equipped with thrust vector control. The existing longitudinal autopilot employs time-invariant passive resistor-inductor-capacitor （RLC） network compensator as a control strategy, which does not take into account the time-varying missile dynamics. This may cause the closed-loop system instability in the presence of large disturbance and dynamics uncertainty. Therefore, the existing controller should be redesigned to achieve more stable vehicle response. In this paper, based on gain-scheduling adaptive control strategy, two different types of optimal controllers are proposed. The first controller is gain-scheduled optimal tuning-proportional-integral-derivative （PID） with actuator constraints, which supplies better response but requires a priori knowledge of the system dynamics. Moreover, the controller has oscillatory response in the presence of dynamic uncertainty. Taking this into account, gain-scheduled optimal linear quadratic （LQ） in conjunction with optimal tuning-compensator offers the greatest scope for controller improvement in the presence of dynamic uncertainty and large disturbance. The latter controller is tested through various scenarios for the validated nonlinear dynamic flight model of the real ballistic missile system with autopilot exposed to external disturbances.展开更多
文摘The explosive formed penetrator （EFP） warhead missile projects the blast fragments in one direction normal to the missile longitudinal axis. Through analyzing on the two restrictions of EFP warhead explosion： trajectory restriction and attitude requirement, the concept of fuze time-delay tolerance is presented to be the measurement of the time of the EFP warhead explosion. The calculation models of fuze time-delay tolerance under two restrictions are provided. Some crucial parameters playing important roles in calculation under attitude requirements are simulated. The simulation results show that the engagement plane angle, roll rate and warhead attack standoff influence the tolerance dramatically.
基金National Natural Science Foundation of China (60904066)National Basic Research Program of China (2010CB327904)"Weishi" Young Teachers Talent Cultivation Foundation of Beihang University (YWF-11-03-Q-013)
文摘This paper investigates the boost phase＇s longitudinal autopilot of a ballistic missile equipped with thrust vector control. The existing longitudinal autopilot employs time-invariant passive resistor-inductor-capacitor （RLC） network compensator as a control strategy, which does not take into account the time-varying missile dynamics. This may cause the closed-loop system instability in the presence of large disturbance and dynamics uncertainty. Therefore, the existing controller should be redesigned to achieve more stable vehicle response. In this paper, based on gain-scheduling adaptive control strategy, two different types of optimal controllers are proposed. The first controller is gain-scheduled optimal tuning-proportional-integral-derivative （PID） with actuator constraints, which supplies better response but requires a priori knowledge of the system dynamics. Moreover, the controller has oscillatory response in the presence of dynamic uncertainty. Taking this into account, gain-scheduled optimal linear quadratic （LQ） in conjunction with optimal tuning-compensator offers the greatest scope for controller improvement in the presence of dynamic uncertainty and large disturbance. The latter controller is tested through various scenarios for the validated nonlinear dynamic flight model of the real ballistic missile system with autopilot exposed to external disturbances.
