满足多终端约束的二次曲线迭代制导方法研究

某些空间载荷会对入轨精度和入轨姿态同时提出很高的要求，应用于运载火箭控制系统的摄动制导方法的入轨精度无法满足要求，而传统的迭代制导方法无法约束终端的入轨姿态。为此提出了一种满足多终端约束的二次曲线迭代制导方法，该方法通过二次曲线形式规划整个真空段的飞行制导程序角，实时满足位置、速度与终端姿态约束，从而可以使得火箭以期望姿态角实现高精度入轨。算例结果表明，该方法能同时保证高精度的入轨指标和入轨姿态，并能适应偏差状态、约束姿态角变化与轨道根数小幅变化，具有较高的工程应用价值。

Research on quadratic curveI GM for multi-terminal constraints

Some space load has a high demand for the accuracy of orbit and flight attitude, and the accuracy of the perturbation guidance method applied in the launch vehicle cannot meet its requirements. The traditional iterative guidance method (IGM) cannot restrain the terminal attitude. Therefore, one quadratic curve IGM which satisfies the multi-terminal constraint was proposed. The method was used to plan the flight guidance program angle of the whole vacuum section through the quadratic curve, which satisfies the position constraint, velocity constraint and terminal attitude constraintinrealtime, making the attitude angle of rocket achieve high precision orbital parameters. Results show that the quadratic curve IGM can guarantee the high accuracy parameters of the orbit and the attitude of the orbit, and can adapt to the deviation states, the varieties of the constraint attitude angle and the number of the orbital parameters are slightly changed, and it has high engineering application value.