reentry vehicle信息详情
[航]再入飞行器
vehicle───n.车辆；工具；交通工具；运载工具；传播媒介；媒介物
reentry shock───再入激波
vehicle simulator───车辆模拟器
vehicle type───车型；车辆类型
airless vehicle───无空气车辆
aerial vehicle───[航]飞行器
vehicle control───[医]车辆控制
vehicle exhaust───[医]车辆排气；汽车废气
motor vehicle───汽车；机动车辆；n.机动车辆，摩托车辆; 汽车
optimal guidance law for reentry vehicle with high altitude maneuvering on downward phase is studied.───研究了在降弧段进行高空机动的再入飞行器最优制导律。
Programming maneuvering flight guidance scheme about reentry vehicle is presented in this paper.───种关于再入飞行器程序机动飞行的制导方案。
High temperature chemical non equilibrium phenomena have a great effect on the flow field around a reentry vehicle.───高温非平衡化学反应对高超声速再入飞行器绕流流场的气动热特性有较大影响。
Variable bend tail concept may be one of the possible approaches for satisfying the maneuvering requirement of hypersonic reentry vehicle.───可变弯尾飞行器的气动方案是高超声速机动的潜在可行方案。
Finally, the tracking of the guided angle command for a nominal trajectory of a reentry vehicle is simulated as an example.───本文最后以一再入飞行器为例，对标称轨道制导指令角的跟踪进行了仿真。
The shape of ballistic reentry vehicle generally is axial symmetry, but its mass center may be departure from the axis of its symmetry.───弹道式再入飞行器一般为轴对称旋成体，但其质心可以偏离对称轴。
A novel guidance law is devised for developing the guidance technology of optimal glide of a hypersonic reentry vehicle.───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 three-dimensional(3D) guidance law is proposed for a reentry vehicle with impact angle constraints.───针对再入飞行器带碰撞角约束的末端导引问题，设计了一种新型三维制导律。
The simulation results have demonstrated that the 3CCGL assures the reentry vehicle to impact the target from a specified direction.───数学仿真结果表明：此制导律能导引再入飞行器沿末端约束方向精确命中目标；
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.
The estimation state for high velocity reentry vehicle is an important subject in the modern defence.
Finally, some considerations to identify the time - variant parameters for reentry vehicle are also presented.
An optimal guidance law for reentry vehicle with high altitude maneuvering on downward phase is studied.
This paper mainly studies the optimal transition trajectory of a reentry vehicle.
The paper widens the application of local method which used to be utilized in rarefied flow to the quick prediction of aerodynamic characteristics of missile-like reentry vehicle in hypersonic flow.