载人运载火箭全要素约束迭代制导技术

The Iterative Guidance Method with All-elements Constrained for Manned Launch Vehicle

运载火箭使用的制导技术目前有摄动制导和迭代制导。摄动制导方法无法满足载人火箭的高精度入轨要求,而迭代制导方法能满足高精度入轨要求,但无法约束其终端姿态。提出了一种载人运载火箭用全要素约束迭代制导技术,通过优化终端姿态反馈算法和精细化考虑迭代末段的速度和位置约束量,使得运载火箭以期望终端姿态角实现高精度入轨。算例表明,该算法解决了载荷在入轨时刻有高分离姿态约束需求的工程实际问题,具有很高的工程应用价值。

There are two kinds of guidance technologies commonly used in launch vehicles:perturbation guidance method(PGM)and iterative guidance method(IGM).PGM cannot meet the high-precision orbit requirements of the manned launch vehicles.IGM can meet the high-precision orbit requirements,but it cannot constrain the terminal attitude.Therefore,an all-element constrained IGM for the manned launch vehicle is proposed.This technology optimizes the terminal attitude feedback algorithm and finely considers the speed and position constraints at the end of the flight stage.This allows the launch vehicle to achieve high-precision orbit at the desired attitude angle.Simulation results show that this algorithm solves the practical engineering problem that the load has a high separation attitude constraint requirement when the load enters the orbit.It has high engineering application value.