再入

基于Turbo码的PCM/FM再入遥测系统性能分析

Performance analysis of PCM / FM reentry telemetry system based on Turbo codes

基于CMAC网络的飞行器再入标准轨道制导

Reentry Trajectory Guidance Design for Hypersonic Vehicles Based on CMAC Network

建议我们调整进入奥米克戎区矢量J太塔区的再入点。

Recommend we adjust re-entry point to Omicron J-Vector Theta .

再入飞行物等离子体尾迹RCS的计算

Calculation for RCS of Reentry Body 's Plasma Wake

利用FDTD法分析再入过程时计算区域入射波的引入

Analysis of Incident Waves Introduction to the Calculation Region in the Reentry Process with FDTD Method

UnscentedKalman滤波用于再入飞行器跟踪

Unscented Kalman Filtering for Reentry Vehicle Tracking

BTT导弹再入段非线性鲁棒控制

Nonlinear Robust Control of BTT Missile in Reentry Phase

相分离Nd（0·5）Ca（0·5）MnO3体系的再入型自旋玻璃行为和电荷有序

Reentering spin glass behavior and charge ordering in phase separation Nd_ ( 0 · 5 ) Ca_ ( 0 · 5 ) MnO_3 system

PCM发射机是再入遥测设备的核心部件，它的发展水平直接影响再入遥测系统的发展。

PCM transmitter is the key part of reentry telemetry system and its level influences the development of the entire system .

RLV再入姿态双环滑模控制及舵喷混合配置

Re-Entry Attitude Two-Loop SMC Control and Rudders-Nozzles Blending Selection Allocation of RLV

基于预测校正方法的RLV再入制导律设计

Reentry guidance law design for RLV based on predictor-corrector method

为了减小再入段风干扰造成的误差，利用在Simulink中建立的数字打靶平台对它进行了研究。

To reduce the wind disturbance error , the wind disturbance regular pattern is studied using a missile simulation system based on the SIMULINK .

飞行器再入时GNC系统一体化仿真研究

A Research on Integrative Simulation of Reentry Vehicle GNC System

最后在对RCS系统操作的基础上，研究了航天飞机在再入段飞行时的RCS控制问题。

And based on the system operation of RCS , some problems of RCS control and availability of actuators for spacecraft re-entry flight were performed .

文中把最大有效载荷的再入轨迹分三种情况作了分析：航天器TPS质量不确定时，通过返回轨迹优化来获得航天器的最大有效载荷，并选择确定相应TPS的质量；

When TPS mas of the space vehicle is determined , the maximum payload is obtained by the design of optimal reentry trafetory ;

基于遗传算法的RLV再入轨迹优化设计

Genetic algorithm optimization of RLV reentry trajectory

利用ANSYS软件模拟了遭受不同程度损伤的防热瓦在再入过程中的温度分布情况，并进行了比较分析与讨论，论证了方法的可行性。

Make use of the ANSYS software to simulate and analyze the temperature distribute of Thermal Protection tile suffered of reentry space shuttle damaged by different degree , demonstrate the feasibility of the method .

本文首先根据再入航天器飞行高度高、速度快、飞行距离远等特点，对GPS定位方式进行选择。

First , proper way of GPS positioning are selected according to the high dynamic flight characters of re-entry spacecrafts , such as high distance from the earth , high velocity and far awy from the launching point .

方法用logistic回归分析2003年11月-2004年1月住院就诊并缓解出院的80例CHF患者再入院的危险因素；

Methods The risk factors of hospital readmission for 80 CHF patients , who hospitalized from Nov 2003 to Jan 2004 and discharged due to remission , were analyzed through Logistic Regression Analysis .

首先建立了飞行器再入时制导、导航和姿控GNC系统一体化的六自由度数学仿真模型。

In this paper , the six degrees-of-freedom simulation mathematical model of the GNC system is built at first .

研究了空天飞行器（ASV）再入跨大气层飞行时的姿态控制问题。

The problems concerning an aerospace vehicle 's ( ASV ) atmospheric reentry flight attitude control system were researched .

再入作战飞行器系统效能评估指标体系，以ADC方法为基本框架，基于WSEIAC模型建立。

A system effectiveness evaluation model for the re-entry aircraft was established on the basis of the frame of ADC method and the WSEIAC concept .

适应2Mbit/sPCM信号的微波锁相调频遥测发射机是21世纪再入遥测系统中的重要设备。

The microwave FM transmitter locked in phase , which is suitable for 2Mbit / s PCM signal , is the major equipment of the reentrant telemetry system in the 21st century .

本文采用多目标遗传算法来确定再入飞行器气动布局优化问题的Pareto最优解集，并和传统的多目标优化方法（加权和方法、约束法）进行比较。

The Pareto genetic algorithm is modified to solve the engineering problems of the aerodynamic shape optimization of reentry body . The comparison of the traditional multi objective optimization methods with the Pareto genetic algorithm is also shown .

空间站充气式下载系统（IDS）是在俄罗斯充气式再入与降落技术（IRDT）基础上发展起来的一种新概念航天回收技术。

An innovative aerospace recovery technology known as Inflatable Download System ( IDS ) is based on the Russian Inflatable Re-entry and Descent Technology ( IRDT ) .

ASV再入大气层的飞行环境变化剧烈、干扰大，因而其姿态控制系统的设计是一项非常前沿的研究课题。

For the varieties of the aerosphere and the large disturbances , the design of attitude control system of ASV is a very difficult problem during the re-entry .

从化学非平衡NS方程或其简化形式（粘性激波层方程、PNS方程）出发，求解高超声速再入体的绕流和底部尾流流场。

In this paper , the flows over hypersonic vehicles and their wake flows are simulated numerically based on the Navier-Stocks equations with chemical source terms or the simplified form of them ( VSL equations and PNS equations ) .

RLV再入标准轨道制导与轨道预测制导方法比较分析制导方法大概可以分为两大类：基于参考弹道的标准轨道法和预测制导法。

Comparisons Between Reference-trajectory and Predictor-corrector Entry Guidances for RLVs The guidance design methods may be classified into two main categories : nominal trajectory-based techniques and on-line trajectory prediction schemes .

本文在干涉型光纤陀螺（IFOG）成熟产品模块化结构的基础上，提出了无源和有源再入式集成光学陀螺（IOG）的系统方案。

In this paper the based on the mature optic modules of IFOG , passive and active re entrant integrated optic gyros ( IOG ) configurations are proposed .

在脉冲相位键控（PPK）再入遥测系统中，除了传输常规遥测信号外，还要传输特种遥测信号，即单次宽脉冲信号。

Telemetry signals , which are not only convention but also a special type-single wide-pulse ones , are transmitted by the Pulse Phase Key ( PPK ) Reent rant Telemetry system .