姿态控制

运载火箭姿态控制系统的鲁棒H∞控制与设计

Robust H ∞ Control and design of Launch Vehicle Attitude Control Systems

其中，水下自航行器的航行与姿态控制采用PID算法实现。

Among them , the attitude control is implemented with PID algorithm .

基于MATLAB的卫星姿态控制半物理实时仿真平台

A Semi-Physical Real-Time Simulation Platform for Satellite Attitude Control System Based on MATLAB

仿真结果表明了SAR星姿态控制实时仿真系统和串行口通信接口模型的正确性。

Results of simulation show the reliability of this real-time simulation system and the interface models for serial-port communication .

验证了本文设计的分数阶PID控制器针对无人机的姿态控制系统而言是有效的。

The comparations of simulation results , verified that the designed fractional order controllers for the attitude control system of UAV is effective .

基于拟人智能控制的BTT导弹姿态控制

Attitude Control for Bank-to-turn Missiles Based on Human-imitating Intelligent Control

本系统采用美国NationalInstrument公司的虚拟仪器开发软件LabWindows／CVI作为系统的软件开发工具，开发了模型姿态控制系统软件平台。

This system adopts LabWindows / CVI , the American National Instrument corporation 's virtual instrument developing software , develop control system software platform of model attitude .

变结构优化控制在MAV姿态控制中的研究

Variable Structure Optimizing Control Method Used in the Attitude Control of Micro Air Vehicle

针对存在未建模动态、模型参数不确定性和外力矩扰动的挠性卫星，通过选择合适的加权函数将挠性卫星姿态控制问题转化为H∞混合灵敏度问题。

For flexible satellite disturbed by neglected dynamics , parametric uncertainties and external torque disturbance , attitude control problem was converted into an H ∞ mixed sensitivity problem through choosing suitable weighting functions .

采用CFD方法对一类火箭弹姿态控制发动机扩散段流场进行了数值模拟，并对几种典型流场进行了分析。

CFD method is used to simulate the flow field in divergent section of an attitude contorl motor , then several typical flow fields are analyzed .

微推进器是一种基于MEMS技术的新型微推进系统，主要用于微小型航天器的位置保持、姿态控制、轨道调整等。

Micro thruster is a new kind of micro propulsion system based on MEMS ( Micro-Electro-Mechanical System ), which is mainly used in micro spacecraft for keeping position , controlling orientation and adjusting orbit .

由于导弹姿态控制系统模型的精确性有限，常规Kalman滤波方法因其鲁棒性差很难检测故障，这种方法能有效检测故障。

Because the accuracy of missile attitude control system model is limited , it is difficult to detect fault for the traditional Kalman filter owing to its weak robustness . The improved algorithm can detect faults effectively .

太阳导行镜（SGT）是空间太阳望远镜（SST）姿态控制的关键技术之一。

The Sun Guide Telescope ( SGT ) is a critical part for controlling the attitude of the Space Solar Telescope ( SST ) .

通过对卫星地磁场和微分Riccati方程进行近似处理，给出有外界扰动和结构化摄动圆轨道卫星系统的H∞磁姿态控制规律。

Through the approximate handling of geomagnetic intensity and differential riccati equation , the magnetic attitude H control law of the microsatellite in a circle orbit which has external disturb and the structural perturbation is presented .

首先给出了RBF网络的学习算法，然后根据全补偿原则设计了神经网络补偿姿态控制方案，最后结合某型卫星的姿态控制系统设计实例，进行了数学仿真。

At first , we presents the learning algorithms of RBF NN , then designed NN compensation based attitude control scheme according to full-compensation principle . Finally , numerical simulation is presented for a certain satellite .

在零动量的假设下，利用Backstepping滑模控制方法，为基于（w，z）参数描述的欠驱动姿态控制系统设计了一个新型的姿态控制器。

A new controller is designed by using the Backstepping sliding mode control method for the under-actuated systems described by ( w , z ) parameter , under the assumption of zero momentum for the spacecraft .

利用H∞控制理论对船舶减摇鳍横摇姿态控制系统进行了混合灵敏度设计，并针对船舶减摇鳍系统的特殊性，解决了H∞控制器设计中与该系统不匹配的有关问题。

By using the H ∞ control theory , a mixture sensibility design was made for a fin stabilizer system . The mismatch problem in the design of H ∞ controller associated with the system was solved in accordance with the features of the ship roll damping .

将再励学习引入模糊神经网络的T-S模型，建立了模糊神经网络控制器和控制评估网络的再励学习算法，并应用于三轴稳定卫星的姿态控制。

In this paper , the reinforcement learning ( RL ) is introduced into the T-S model of fuzzy neural network ( FNN ) , which is then employed in the attitude control of a three-axis-stabilized satellite .

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 .

基于MEMS技术的微型推进系统成本低、质量轻、体积小、集成度高，卫星间相对轨道位置的保持、高精度的姿态控制对其提出较高的要求。

Micro-propulsion system based on MEMS technology has some advantages of low cost , low mass quality , small size , high integrated level . The relative position between the satellites orbits and high precision of the attitude control put forward higher requirement to Micro-propulsion system .

传感反射以加速度计、振动陀螺仪、力传感器获得的信息为依据，通过上体姿态控制、ZMP控制和落地时间控制实现传感反射控制。

It describes actualization of a sensory reflex , which consists of a body posture control , an ZMP control and a landing time control .

分析该体系结构下Drag-Free控制回路、质量块控制回路和卫星本体姿态控制回路的组成和实现原理。

Three parts of the architecture was detailed analyzed : Drag-Free control loop , proof mass control loop and satellite attitude control loop .

为此，针对空间站姿态控制/动量管理系统的线性化模型，设计了一个线性二次型调节器，并利用计算机仿真的手段分析了CMG操纵性能及其对姿态控制/动量管理系统的影响。

Therefore , simulation analysis was made concerning the steering performance of CMGs and their effects after a linear quadratic regulator ( LQR ) was designed for the attitude control and momentum management system .

根据空间飞行器姿态控制用四轴主动控制型混合磁悬浮动量轮的动力学方程，采用变结构控制（VSC）法设计了一种多输入多输出系统控制器。

According to the dynamic equation of four axial radial hybrid magnetic bearing momentum wheel for attitude control of spacecraft , the variable structure controller of multiple output and multiple input for magnetic bearing momentum wheel was designed in this paper .

脉冲等离子体推力器（PPT）具有结构简单可靠，比冲高，推力在较大范围可控的特点，适合用于微、小卫星轨道控制和小卫星高精度姿态控制，其研究和应用得到了重视。

With advantages of simple and reliable in structure , high Isp and easy control over a wide range of thrust , Pulsed Plasma Thruster ( PPT ) is very suitable for micro-satellite 's orbit control and high precision attitude control .

本篇论文研究提出了一种运载火箭姿态控制系统的故障分析法，称为故障-功能分析法（简称为F-FAM）。

This paper proposes a failure diagnosis method , called failure-function analysis method ( F-FAM ), for an attitude control system in a carrier rocket .

上述方法已经用于以实际的卫星姿态控制系统为背景的实时故障诊断专家系统（SCRDES），它是ES技术在实时监测系统中应用的一个新探索。

A kind of feasible structure of hardware and software for knowledge processing is given , the above-mentioned methods have been applied to the Real-time Diagnosis Expert System for recoverable Satellite attitude Control system ( SCRDES ), which is a new probing into ES in real-time monitor filed .

本文结合国家863科研计划项目深空探测自主技术与仿真演示系统（2004AA735080），对深空探测器姿态控制系统设计方法进行了研究。

For deep space explorer , the attitude control system design methods were studied in this dissertation , which is funded by the National 863 Plan ( 2004AA735080 ), Autonomy Technology and Simulation Demonstration System for Deep Exploration .

控制系统研究分为姿态控制和路径规划避障两部分。

The control system research includes pose control and path layout .

旋转状态下姿态控制发动机喷流流场的数值模拟

The Jet Flow Field Simulations of a Rotating Attitude Control Motor