The former includes data management and analysis, orbit and attitude simulation, space environment simulation, data communication and real-time animation.
飞行模拟及演示进程负责数据管理与分析、轨道姿态模拟计算、飞行环境模拟计算、数据通讯和实时动画演示工作；
Simulation results show that, in the closed-loop system, precise attitude control is accomplished in spite of the uncertainties and external disturbances in the system.
仿真结果表明：即使系统存在不确定性和外界干扰，仍可在闭环系统中实现精确的姿态控制。
Put the disturbance moments of typical astronaut's push-off act as the input datas of the control system simulation, and analyze the response of the attitude control system after disturbed.
以典型的航天员推离动作对飞船的扰动力矩作为控制系统仿真的输入参数，分析姿态控制系统受到扰动后的响应。
Furthermore, the computer simulation technique is applied to study initially the distortion law of CCD satellite images caused by errors of ephemeris parameters and initial attitude Angle.
利用计算机仿真技术初步研究了星历参数和初始姿态角误差引起的CCD卫星影像畸变的规律。
As illustration, these models are applied to an attitude control dynamics simulation of a three-axis stability satellite and the corresponding toques were plotted in curves.
为验证模型有效性，将其应用于某三轴稳定对地定向卫星姿态动力学仿真中，得到了相应的太阳光压干扰力矩曲线。
Simulation results show that the presented control can ensure the precision of the attitude control performance, suppression of the structure vibrations and robustness of the control system.
仿真结果表明，该方案可以保证卫星的姿态控制精度、结构振动抑制和控制系统鲁棒性。
At last, the hardware in the loop simulation system for three-axis stabilized satellite attitude control based on PC, with reaction wheel and gyro in the loop is designed.
最后，该文设计了一个基于PC机的三轴稳定卫星姿态控制硬件在回路仿真系统，将反作用飞轮、陀螺等实物接入仿真系统。
Finally, the distributed real time simulation is realized. The simulating results show that this kind of attitude control systems of the space station is feasible.
最后对整个系统进行了分布实时仿真，运行结果说明了这种空间站姿态控制系统方案是可行的。
The fault simulation of satellite attitude control system is crucial for research and experimental verification on optimizing configuration, fault diagnosis, reconstruction of control system.
进行卫星姿态控制系统故障模拟，对控制系统优化配置、故障诊断、系统重构技术研究与实验验证具有重要作用。
The concept and scheme for the simulation of attitude, orbit and important telemetry parameters of prolate dual-spin geostationary satellite have been given in the paper.
本文介绍了在计算机上进行细长型双自旋卫星姿态、轨道和重要遥测参数仿真的原理和方案。
Based on the simulation of the gyro attitude errors resulted from above mentioned, a simplified error equation is established and the analysis in complex domain is made.
对由此产生的陀螺姿态角误差进行了仿真分析，并在此基础上建立起与之相应的简化误差方程，对简化误差方程进行了复域分析。
Electromagnetic tracking systems are widely used in Virtual Reality and computer simulation system to measure the attitude and position of the users hand or head to perform Human-Computer Interaction.
虚拟现实系统和计算机仿真系统中广泛采用电磁跟踪系统测量用户的头部或手部的位置和姿态来实现人机交互。
Simulation results show that this integrated system can get navigation attitude position with high precision, also the position error and velocity error are decreased.
仿真结果表明：本文提出的组合导航系统能够给出载体的高精度姿态信息，位置误差和速度误差也较小。
Simulation results show that the control performance of the satellite attitude system is improved, and the difficulties of traditional PID parameter regulation can be avoided by this method.
仿真结果表明，使用遗传算法pid参数自整定方法，对卫星的姿态系统具有较好的控制性能，并且克服了传统PID调参困难的缺点。
The simulation results show that compared with the traditional quaternion algorithm, the method can smooth the effect of noise while resolving the system attitude.
仿真表明，与传统四元数算法比较，该方法在解算系统姿态的同时，能够较好地平滑噪声的影响。
Several different methods were compared with simulation results, and an application was proposed, which resolved the problem of coupling between the bank and the pitch in the attitude estimation.
将不同的算法进行了仿真比较，提出了一种应用方案，解决了姿态估计过程中横滚角与俯仰角耦合的问题。
The conditions for proper attitude acquisition after boom deployment are obtained from the simulation.
探讨了保证重力梯度杆伸展后卫星姿态能正确捕获所需的条件。
The effect of the blocked spouts on the performance of an attitude control rocket motor was analyzed by using numerical simulation and test.
通过数值模拟和试验研究，分析了喷口遮挡对姿控火箭发动机性能的影响。
The simulation result shows that the variable structure automatic pilot for KKV is fast and has high attitude control accuracy, which satisfies the requirements.
数学仿真表明，变结构自动驾驶仪具有很好的快速性和很高的姿态控制精度，可以满足动能拦截器对姿态控制的要求。
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踪期望值。
Theoretical analysis and the simulation results show that this method has the advantages of good attitude tracking accuracy, less real time calculations and easy realization.
理论分析和仿真研究表明此控制律具有姿态跟踪精度高，实时计算量小，便于工程实现等优点。
The simulation results show that the attitude accuracy of steady state of a system with RBF NN compensation blocks has been improved obviously.
结果表明：有rbf网络补偿的系统，姿态的稳态精度得到了明显的改善。
By analyzing the simulation results of the track and attitude of the AUV, the paper brings a useful help and reference value to stability analysis and control system design of AUV.
该模型的建立和仿真为AUV近水面的稳定性分析和控制系统的设计提供了便利的工具。
The simulation results shows that lateral attitude control system has good control performance and the auto-trim control strategy plays a effective role.
仿真验证结果表明，抗不确定干扰的横侧向姿态控制回路控制性能良好，自动配平控制策略能有效发挥作用。
Research on Distributed Interactive Simulation Method of Missiles Attitude Control System;
研究航天器集成能量与姿态控制系统中飞轮的控制律。
Research on Distributed Interactive Simulation Method of Missiles Attitude Control System;
研究航天器集成能量与姿态控制系统中飞轮的控制律。
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