一种级间无动力飞行时间在线自适应确定方法

An On-line Adaptive Determination Method of Unpowered Flight Time

针对直接入轨固体运载火箭的多约束条件,为减小飞行攻角指令大小和飞行轨迹散布,以改善火箭飞行的力热环境和减小入轨点速度损失,提出了一种根据实际飞行情况在线确定级间无动力滑行时间的数值预测方法。首先,在合理的假设下,综合考虑计算精度和计算效率,建立了无量纲化的数值预测制导模型。随后,考虑飞行过程约束和入轨终端约束,制定了级间无动力滑行时间数值预测制导策略和流程。最后,通过数学仿真,表明所提方法在满足入轨点参数及控制精度要求的情况下,大幅减小了飞行攻角指令,缩小了飞行轨迹散布,具有较好的应用价值。

Regarding the directly injecting solid rocket, in order to reduce attack angle and flight trajectory dispersion, improve the thermal environment of rocket flight and reduce the speed loss at orbit entry point, a numerical prediction method for on-line determination of interstage unpowered flight time according to the actual flight situation is proposed in this paper. Firstly, under reasonable assumptions, considering the calculation precision and efficiency, a dimensionless numerical prediction guidance model is established. Then, considering the flight process constraints and orbit entry constraints, the numerical prediction guidance strategy and process of interstage unpowered taxiing time are formulated. Finally, the simulation results show that the attack angle and flight trajectory dispersion can be greatly reduced by using the proposed method which has better application value.