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。
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.
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。
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.
适当地结合规划-跟踪算法和航迹角控制器可给再入制导带来极大的灵活性和适应性。
Proper combination of planning-tracking algorithm and FPA controller can bring great flexibility and adaptability to reentry guidance.
在具有控制和轨迹约束的再入制导中，提出了一种新的基于多模型预测再入飞行器纵向制导方法。
A new method based on multi-model prediction is proposed for the longitudinal guidance of re-entry vehicles with trajectory and control constraints.
本文简要介绍了再入体六自由度控制系统半实物仿真的系统结构与软件系统设计，并探讨了相应的仿真技术途径。
In this paper, system structure and software design of reentry vehicle Sir -dof semi physical simulation are introduced briefly, and corresponding simulation technical methods is discussed.
飞行器再入轨迹优化是一类最优控制问题。
Spacecraft reentry trajectory optimization is a kind of optimal control problem.
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。
So maneuver reentry trajectory design problem was transferred into the more complex optimum control problem with terminal constraints and inner state constraints.
结果表明，过载反馈系统在再入机动飞行器的飞行控制中效果较好。
The results shows that the overload feedback structure is better than the attitude feedback structure on the maneuverable flight control.
该方法利用最优控制理论的思想方法，不仅使飞行器命中目标时满足了终端角度约束的条件，而且保证了再入飞行器机动速度损失最小。
The guidance method satisfies terminal angular constraint as reentry vehicle hitting target, but also ensures minimum loss of maneuvering velocity for reentry vehicle.
再入飞行是RLV飞行任务的重要阶段，而制导、导航与控制（GNC）系统则是RLV的核心系统之一，是RLV再入飞行的“脑系统”。
The guidance, navigation and control(GNC) system, the brain system, is the one of the key systems of RLV. In this paper the mission requirements and system structure are first studied.
分析了沿最优轨迹飞行的物理原因和基本迎角控制规律，可为滑翔式再入飞行器的最优轨迹方案设计提供依据。
The physical causation of the optimal trajectory and the corresponding angleofattack profile are presented. It is a good reference for schematic trajectory design for gliding type reentry vehicles.
弹道式飞行器再入时，常常要求在规定高度上发出开伞信号，过载延时控制方法误差太大，不能满足精度要求。
The opening parachute signal is required to sent on the fixed height when the vehicle reentry. The height controlled error through axis apparent acceleration can not meet the required precision.
本文主要对采用移动质心控制方式的再入弹头的姿态控制方法进行研究。
The paper research on the attitude control approach for a reentry warhead controlled by the way of moving mass.
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。
The problems concerning an aerospace vehicle's(ASV) atmospheric reentry flight attitude control system were researched.
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。
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。
For the finite propulsion reentry guidance, the conventional closed-thruster equation based on open-loop control loses its way.
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