提出了一种针对可重复使用运载器的再入制导算法。
A new reentry guidance algorithm for RLV (reusable launching vehicle) is presented.
新一代可重复使用运载器对再入制导提出了更高地要求。
The new generation of Reusable Launch Vehicles (RLVs) demands improvements to the current entry guidance capability.
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.
针对高超声速再入飞行器最远距离滑翔制导关键技术，设计了一种新型制导律。
A novel guidance law is devised for developing the guidance technology of optimal glide of a hypersonic reentry vehicle.
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.
文提出一种关于再入飞行器程序机动飞行的制导方案。
Programming maneuvering flight guidance scheme about reentry vehicle is presented in this paper.
为了消除设计偏差，提出了一种基于虚拟再入点补偿的有限推力制导方案，并简要分析了关机点参数的选取原则。
Then a scheme of limited thrust guidance with virtual reentry point compensation was put forward to eliminate planning error and the selection of shutdown parameter was analyzed briefly.
研究了在降弧段进行高空机动的再入飞行器最优制导律。
An optimal guidance law for reentry vehicle with high altitude maneuvering on downward phase is studied.
基于惯性制导工具误差模型，推导出存在工具误差时的再入点运动参数模型。
Based on the inertial guidance instrument error model, the model of reentry point's parameters is established in this paper.
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。
In view of the particularity for maneuver warhead reentry trajectory and the guidance method, key techniques in attitude control system design are analyzed.
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。
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.
论文最后研究了预测制导方法在高速再入飞行器攻击地面固定目标任务中的应用问题。
A predictive guidance method for reentry vehicle in the case of attacking the stationary target on the surface is also investigated.
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.
基于惯性制导工具误差模型，推导出存在工具误差时的再入点运动参数模型。
This paper proposes a nonlinear model for guidance instrument systematic error separation based on tracking trajectory data.
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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