全部

1·In this paper, the method of reentry maneuver guidance applying to attack the ground fixed target is described by using flight dynamics principle and modern control theory.

本文运用飞行力学原理和现代控制理论，对攻击地面固定目标的飞行器的再入机动制导方法进行了研究。

2·The objective of this paper is to design the reentry flight control laws for the Suborbital Reusable Launch Vehicle(SRLV) based on nonlinear dynamic-inversion.

基于非线性动态逆理论，设计了亚轨道可重复使用运载器（SRLV）的再入控制律。

3·So maneuver reentry trajectory design problem was transferred into the more complex optimum control problem with terminal constraints and inner state constraints.

这就增加了内点约束，从而使机动再入弹道设计问题成为具有内点约束和终端约束更复杂的最优控制问题。

4·Spacecraft reentry trajectory optimization is a kind of optimal control problem.

飞行器再入轨迹优化是一类最优控制问题。

5·In view of the particularity for maneuver warhead reentry trajectory and the guidance method, key techniques in attitude control system design are analyzed.

针对机动弹头再入弹道和制导方式的特殊性，分析了激光末制导机动弹头姿控系统设计的关键技术。

6·As to the attitude stablization of reentry vehicle with parameter uncertainties, its variable structure decoupling control law is designed and simulation results are given.

讨论了其滑模面的构造方法和解耦控制条件，在姿态控制中保证了姿态跟踪期望值。

7·The optimal high altitude guidance law with reentry constraint condition is derived by using the optimal control theory, and the algorithm of time to go is also given.

给出了一种新的飞行器运动数学模型和这一模型下的最优制导律以及再入飞行器发动机工作时间、过载系数和估算方法。

8·The problems concerning an aerospace vehicle's(ASV) atmospheric reentry flight attitude control system were researched.

研究了空天飞行器（ASV）再入跨大气层飞行时的姿态控制问题。

9·For the finite propulsion reentry guidance, the conventional closed-thruster equation based on open-loop control loses its way.

解决有限推力模型的再入飞行器初制导问题，利用传统开环控制的关机方程达不到要求的精度。

10·Finally, 6 DOF simulations are made based on a kind of reentry aerocraft. The results show that the proposed control scheme and the guidance law are rational, efficient and easy for implementation.

最后，进行了六自由度仿真，结果表明：设计的制导律及控制方案是合理、有效的，易于实现。