基于栅格舵的运载火箭一子级落区控制技术

Impact Zone Control Technology for Launch Vehicle First Stage by Grid Fins

面对日益突出的落区安全问题,针对我国现有运载火箭一子级的特点,为达到残骸落区可控的目的,采用栅格舵系统对一子级进行落区控制。本文首先给出了栅格舵系统的总体方案和系统组成,并对栅格舵气动特性进行了分析,然后开展了一子级再入过程的控制系统设计和仿真,最后给出了2次长征四号乙运载火箭一子级栅格舵系统演示验证飞行试验结果。试验结果表明:基于栅格舵的一子级落区可控技术是合理可行的,实现了将原有落区面积缩小85%的目标,极大改善落区安全性,有效避免大规模人员疏散和可能造成的生命财产损失,对垂直起降重复使用运载火箭的工程应用具有重要支撑作用。

To reduce the impact zone range of the launch vehicle’s first stage,which was launched from the inland launch site,a control technology using grid fins was proposed.Depending on the target impact location,the proportional guidance law was generated based on the virtual seeker.The guide system produces command acceleration tracking using acceleration autopilot of both pitch-channel and yaw-channel.Under the action of acceleration autopilot,the launch vehicle’s first stage would fly toward the target impact point.The roll angle and roll rate were stabilized to zero by roll attitude autopilot for a three-channel decoupling design.The numerical simulation of a launch vehicle’s first stage with grid fins control was demonstrated.The results indicate that the impact zone range was reduced significantly by up to 85%.This impact zone control technology of the launch vehicle’s first stage by grid fins can be applied in aerospace engineering.