建立了机动再入弹头随机数学模型，根据攻击目标的要求选择合理的滑模变结构开关面。
The Stochastic mathematic model of maneuvering reentry warhead was proposed, and the rational slide switch surface was chosen based on the desire of attacking ground target.
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.
航天飞行器在再入大气过程中会受到严重的气动加热。返回式卫星、飞船返回舱及航天飞机等采取高空机动再入，再入时间长，其峰值加热过程一般在60-90千米高空。
Spacevehicles such as spacecraft and space shuttle are subjected to severe aerothermal environment with the peak heating at height of 60~90km while they maneuver to reentry the earth's atmosphere.
所设计的再入机动弹道能满足机动弹头对姿态、热流和速度的要求。
The designed maneuver reentry trajectory can meet the demands of attitude, heat flux and velocity for the warhead.
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.
本文主要讨论再入机动弹道的设计问题。
This report mainly discussed design problems of reentry maneuvering trajectories.
建立了再入机动弹道数学模型，给出了气动力系数为速度、迎角、高度的函数拟合式，进行了最佳再入机动弹道设计和仿真计算。
The mathematical model of reentry maneuvering trajectory is established. The fitting expression of aerodynamic coefficient function on velocity, attack of Angle and altitude is presented.
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.
利用典型状态的风洞试验结果对十字布局与叉字布局再入机动飞行器的气动特性进行了分析与比较。
In this paper aerodynamic characteristics of maneuvering reentry vehicle of cruciform configuration and bifurcate configuration are compared by means of the wind tunnel test results.
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.
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.
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.
本文主要讨论再入飞行器机动弹道的设计问题。
This paper mainly discusses the design of maneuverable trajectories of re-entry vehicle.
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.
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.
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