文中着重叙述了再入体滚转共振和小不对称气动力问题的研究结果和存在问题。
Research results of the re-entry body in rolling resonance and small asymmetrical aerodynamic force as well as existential problems are emphatically described. It indicates that to determine rand…
建立了再入体再入大气层形成的尾迹的工程模型，并运用边界层理论求解二维等压湍流尾迹流动。
An engineering model for hypersonic reentry body trail is established in this paper, and a calculation is performed by using boundary layer theory.
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.
当再入目标高超声速穿越大气层时，将产生等离子体鞘套和尾流，其雷达散射特性受到目标包覆等离子体参数变化的影响而产生剧烈波动。
While the reentry target passes through the earths atmosphere at ultrasonic speed, the RCS of the reentry Capsule changed violently because of the plasma sheath and wake.
以已有的湍流尾迹等离子体流场数据为基础，分析了再入尾迹湍流等离子体流动对雷达散射截面的影响。
Based on the flow field parameters about the turbulent wake and this scattering model, the effects of reentry wake turbulent plasma is analyzed on the radar cross section.
带喷流再入假目标是战略导弹弹头突防的一种重要手段，电子密度及其分布是等离子体发生器实现飞行器隐身的关键。
Reentry bait with cascade is an important means of strategic missile-warhead penetration . Eletron consistence and their distribution is the sticking point of the plasm production implement.
对再入飞行器等离子体尾迹及其雷达散射特性进行了分析、研究和大量的计算。
In this paper, plasma wake flow of hypersonic reentry vehicle and radar scattering characteristics have been studied.
重点解决在没有轨道观测数据的情况下，如何利用再入飞行中的测量数据进行状态和参数估值。数据包括体轴角速率和过载，由固连于飞行体的速率陀螺和加速计给出。
The emphasis is put on estimating the states and parameters only on the basis of the re-entry on-board measurement data in the absence of trajectory observation data.
电弧等离子体风洞是一种能产生高温、高压的热源设备，用于在地面模拟航天用再入式飞行器的气动环境。
Plasma wind tunnel is equipment which can generate high-temperature and high-pressure to simulate the air environment of aerospace reentry vehicles.
本文采用联立求解粘性剪切层和有旋无粘区的方法计算了再入钝头体层流近尾流场。
The near wake flow fields are calculated by simultaneously solving the viscous shear layer and the inviscid rotational region.
本文采用联立求解粘性剪切层和有旋无粘区的方法计算了再入钝头体层流近尾流场。
The near wake flow fields are calculated by simultaneously solving the viscous shear layer and the inviscid rotational region.
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