英汉例句

• in this paper, plasma wake flow of hypersonic reentry vehicle and radar scattering characteristics have been studied.

  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 aerodynamic characteristics of maneuvering reentry vehicle of cruciform configuration and bifurcate configuration are compared by means of the wind tunnel test results.

  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。

• 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.

  首先，使用局部线性方法给出模型的系数函数的初始估计； 然后使用积分方法，给出它们的积分估计； 进一步，研究这些积分估计的渐近正态性。

• as to the attitude stablization of reentry vehicle with parameter uncertainties, its variable structure decoupling control law is designed and simulation results are given.

  讨论了其滑模面的构造方法和解耦控制条件，在姿态控制中保证了姿态跟蹤期望值。

• 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。

• this paper researches into reentry vehicle impact errors which result from the roll velocity changes by use of rotor dynamic theory.

  用转子动力学理论研究了再入航天器滚速变化引起的落点误差。

• firstly, the state variables of the reentry vehicle are decomposed into two sub-systems of different time scales using the singular perturbation theory.

  首先，利用奇异摄动理论对再入飞行器状态变量进行两个时间尺度的划分，将系统状态方程分解成两个低维子系统。

• against the big error of height determination for the reentry vehicle because of the information provided by low precision geomagnetic sensor, a novel real-time prediction method is proposed.

  针对于目前地磁传感器测量精度较低，将其信息直接用于飞行器再入段定高误差较大的问题，提出了一种在线预测进行定高的方法。

• by means of the scheme, the position of the maneuvering start point of the reentry vehicle is precisely determined by radio sensor.

  该方案利用辐射传感装置，精确地确定再入飞行器机动起点的位置。

• 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.

  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。

• programming maneuvering flight guidance scheme about reentry vehicle is presented in this paper.

  文提出一种关于再入飞行器程序机动飞行的制导方案。

• hmmm… . a double-dip reentry after an uneventful trip around the moon?additionally, that reentry vehicle is far larger than would be launched by a sample-and-return mission.

  嗯…平安无事绕月后的一个二次再入?此外，再入飞行器远远高端于发射简单的取样返回任务。 。

• 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。

• a dynamic analysis model for reentry vehicle is established by means of finite element method and msc/nastran software system.

  采用有限元方法和mscnastran软件，建立了某型号再入飞行器的动力学分析模型。

• therefore, the direct collocation method is a viable approach to the reentry vehicle trajectory optimization problem.

  因此，直接配点法对于再入轨迹优化问题的求解是可行的。

• the guidance method satisfies terminal angular constraint as reentry vehicle hitting target, but also ensures minimum loss of maneuvering velocity for reentry vehicle.

  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。

• a predictive guidance method for reentry vehicle in the case of attacking the stationary target on the surface is also investigated.

  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。

• an 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。

• finite element method for thermal stress analysis of reentry vehicle nose tip is one application of finite element analysis of solid axisymmetric body.

  端头热应力分析的有限元法是属于轴对称实心体的有限元分析。

• this paper deals with the problem of determining the aerodynamic shape of a reentry vehicle with minimum total trajectory heat transfer.

  本文研究确定再入飞行器的最小总加热量气动外形问题。