摘要
为了保证再入飞行器以期望倾角和速度准确投放载荷,利用终端倾角约束下的滑模变结构控制进行实时弹道预测,通过速度修正指令实现飞行器的机动减速,以达到期望的投弹倾角和速度。分别计算了目标点位于13km和3km高度时的飞行轨迹及飞行参数。对仿真结果的对比分析表明:采用倾角约束导引律时,飞行器终端倾角满足期望的-30°,但是其终端速度分别为1 550m/s和1 450m/s,远高于期望的1 200m/s;采用倾角-速度多约束导引律时,终端倾角和速度均达到了期望水平,而且攻角、倾斜角以及各向过载均满足限制条件;多约束预测-修正导引律更有利于再入飞行器准确投放载荷。
To ensure the vehicle releasing store at expected angle and velocity accurately, the sliding-mode variable structure control was used to predict trajectory of vehicle in real time,and the vehicle was maneuvered under the control of eorrector command to decelerate to reach the target point at expected angle and velocity. For the final height of 13 km and 3km,the trajectory and parameters of vehicle were computed respectively. The simulation results were compared. The results show that under the control with angle constraint, the final path angles satisfy the expected -30°,but the velocities are 1 550 m/s and 1 450 m/s respectively,higher than expected 1 200 m/s;by using the guidance law with angle and velocity constraints,the final path angle and velocity reach the expected value,and the angle of attack, the angle of bank and the over-loadings meet the limiting conditions. The predictor-corrector terminal guidance law with multiple constraints is in favor of store releasing accurately for reentry vehicle.
出处
《弹道学报》
CSCD
北大核心
2013年第1期5-9,31,共6页
Journal of Ballistics
基金
国家863计划项目
关键词
再入飞行器
滑模变结构控制
预测
导引律
多约束
reentry vehicle
sliding-mode variable structure control
predictor
guidance law
multiple constraints
