Description: 本文首先建立了航天器姿态动力学及运动学方程，该方程具有较强的非线性特性。通过将状态耦合部分作系统干扰项的处理，使原来的非线性模型转化为线性模型加非线性干扰的形式，从而得到了更加简单明了的姿态控制系统的表达式。
在应用滑模变结构原理对系统进行控制器设计时，首先通过二次型最优法求出了最优滑动面，在此基础上，利用自适应滑模控制原理，设计出了合适的系统控制律。
最后，运用所设计的姿态控制系统对某航天器进行数值仿真，并对仿真结果进行了分析。仿真结果很好地体现出所设计的变结构控制器的优点，并成功地对该航天器姿态进行了控制。
-paper first established the spacecraft attitude dynamics and kinematics equation, the equation has strong nonlinear characteristics. By coupling part of the state system for the disturbance, so the original nonlinear model into a linear model nonlinear increases in the form of interference, and thus a more straightforward attitude control system expression. The application SMVSC tenets of the system controller design, the first through the quadratic optimal method, the optimal sliding surface, on this basis, using adaptive sliding control theory and design a suitable system control law. Finally, using the design of the attitude control system for a spacecraft numerical simulation, and simulation results are analyzed. Simulation results reflect good design of variable structure controller, Platform: |
Size: 310978 |
Author:跃进 |
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Description: Spacecraft Attitude Dynamics and Control 航天器姿态控制的课件，十分难得；内容通俗易懂；十分完整；是从事航天研究的必须知识-Spacecraft Attitude Dynamics and Control of Spacecraft Attitude Control courseware, very rare the content of user-friendly very integrity is engaged in space research must be knowledge Platform: |
Size: 3743744 |
Author:临风 |
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Description: The ballistic category of atmospheric vehicles includes missiles, launch ve-
hicles, and entry capsules. Some missiles and launch vehicles incorporate fi ns
as aerodynamic stabilizing and control surfaces. The spacecraft are also catego-
rized according to their missions, such as low-earth orbit, medium-earth orbit,
geosynchronous orbit , lunar, and interplanetary spacecraft. Each mission is
defi ned by the payload, and orbital elements of the fi nal orbit. Of course, a
reusable launch vehicle, such as the space shuttle, is also a spacecraft with a
unique mission. -The ballistic category of atmospheric vehicles includes missiles, launch ve-
hicles, and entry capsules. Some missiles and launch vehicles incorporate fi ns
as aerodynamic stabilizing and control surfaces. The spacecraft are also catego-
rized according to their missions, such as low-earth orbit, medium-earth orbit,
geosynchronous orbit , lunar, and interplanetary spacecraft. Each mission is
defi ned by the payload, and orbital elements of the fi nal orbit. Of course, a
reusable launch vehicle, such as the space shuttle, is also a spacecraft with a
unique mission. Platform: |
Size: 7983104 |
Author:kalaiarasan.R |
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Description: 进行航天器轨道运算经常用到的函数，包括坐标转换，经纬度转换，二体运动，轨道要素计算-For spacecraft orbit operations frequently used functions, including coordinate conversion, latitude and longitude conversion, two-body movement, and so calculated orbital elements Platform: |
Size: 18432 |
Author:李鑫 |
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Description: 用LabVIEW实现的“飞行姿态控制仿真”。内有vi：俯仰和滚转控制器、航向控制器、键按下增大、键盘操作、姿态角误差转换、阻尼器。还有9个显示vi和12个模型vi。
飞行控制的目的主要是通过控制飞行器的姿态和轨迹来完成飞行任务，然而飞行轨迹很大程度由飞行姿态决定。可见飞行器姿态控制，在整个飞行控制系统中处于重中之重的地位。飞行姿态控制的好坏直接关系到飞机能否安全、平稳、快速的地飞行。与其它控制系统一样，可用稳定性和动稳态性能来衡量控制效果。稳态时，要使飞行器姿态足够接近所需的飞行姿态，才能让飞机以一定的航迹航行。而姿态变化的过程，要求系统稳定，响应快，超调小，振荡少，即姿态能够快速平稳过渡。早期，可以通过优化飞机的气动布局来改良飞机的飞行性能，但随着飞行的速度与高度的增加，空气变得稀薄，阻尼随之减小，飞行的气动模型也发生了大的改变，已经难以通过外形设计来增强稳定性，而设计优良飞行姿态控制器是必由之路.
-Using LabVIEW to achieve the "flight attitude control simulation." There vi: pitch and roll control, heading control, key press increases, keyboard operation, attitude angle error change, and the dampers. There are nine show vi and 12 model vi.
The main purpose of the flight control is by controlling the aircraft attitude and flight trajectory to complete the task, but a large degree trajectory decision by the flight attitude. Spacecraft attitude control can be seen in the flight control system in the most important position. Flight attitude control has direct bearing on whether the aircraft safe, stable, fast to the ground. And other control systems, stability and dynamic steady-state performance can be measured in control performance. Steady state, make the aircraft attitude close enough to the required flight attitude, to allow the aircraft to a certain track navigation. The attitude change process, requiring system stability, fast response, small overshoot, small oscillations, Platform: |
Size: 424960 |
Author:zhou |
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Description: The Spacecraft Control Toolbox is composed of MATLAB m-fi les and mat-fi les, organized into a set of modules by subject. It is essentially a library of functions for analyzing spacecraft and missions. There is a substantial set of
software which the Spacecraft Control Toolbox shares with the Aircraft Control Toolbox, and this software is in a module called Common. The core spacecraft fi les are in SC and SCPro along with special plotting tools in Plotting.
The new CubeSat module demonstrates mission planning and simulation for nanosatellites. These fi ve modules are referred to together as the Core toolbox. Functions for estimation, orbit analysis, subsystem analysis, and detailed
attitude control system examples are grouped in separate modules. All of the modules are described in the following table, including the add-on modules which are purchased separately. Platform: |
Size: 9728000 |
Author:Huy |
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Description: 1、利用simulink中sfunction方法建立航天器姿态动力学模型和运动学模型；
2、利用linmod对非线性模型线性化；
3、姿态模型线性化后，利用极点配置（pole）方法求取控制参数；
4、将控制参数带入非线性模型仿真控制效果。-One using simulink sfunction method to establish the dynamic model and kinematic model of the spacecraft attitude
2, the use of linmod linearization of the nonlinear model
Attitude model linearization, the use of pole configuration (pole) is used to obtain the control parameters
4, the control parameters into the nonlinear model simulation control effect. Platform: |
Size: 9216 |
Author:战斗机 |
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Description: 采用变速控制力矩陀螺的航天器自适应姿态跟踪和稳定控制研究-Using variable speed control moment gyros Spacecraft Adaptive Attitude Tracking Study and stability control Platform: |
Size: 327680 |
Author:王德杰 |
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Description: In this paper, formation control ideas for multiple spacecraft using the virtual structure approach
are presented. If there is no formation feedback from the spacecraft to the virtual structure, the
spacecraft will get out of formation when the virtual structure moves too fast for the spacecraft to
track due to spacecraft control saturation or the total system must sacriˉce convergence speed in
order to keep the spacecraft in formation. The spacecraft may also get out of formation when the
system is a® ected by internal or external disturbances. To overcome these drawbacks, an idea of
introducing formation feedback from the spacecraft to the virtual structure is illustrated in detail.
An application of these ideas to multiple spacecraft interferometers in deep space is given. Platform: |
Size: 314368 |
Author:alkatel |
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Description: In this paper, formation control ideas for multiple spacecraft using the virtual structure approach
are presented. If there is no formation feedback from the spacecraft to the virtual structure, the
spacecraft will get out of formation when the virtual structure moves too fast for the spacecraft to
track due to spacecraft control saturation or the total system must sacriˉce convergence speed in
order to keep the spacecraft in formation. The spacecraft may also get out of formation when the
system is a® ected by internal or external disturbances. To overcome these drawbacks, an idea of
introducing formation feedback from the spacecraft to the virtual structure is illustrated in detail.
An application of these ideas to multiple spacecraft interferometer Platform: |
Size: 1251328 |
Author:alkatel |
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Description: 飞机姿态算法。从这篇文章是我尝试的飞行器姿态检测采用四元数方法,然后利用卡尔曼滤波算法,并尝试卡尔曼滤波器耦合的多个状态变量可以是一个复杂的过程,线性系统状态估计进行了简单的解耦,将最优估计的态度和最优估计陀螺漂移,通过这种方式,可以通过直观的方法来调整参数的两个部分。-Aircraft attitude algorithm.From this article is my attempt to spacecraft attitude detection by using the quaternion method, to then using kalman filter algorithm, and try to kalman filter coupling multiple state variables can be a complex process of linear system state estimation has carried on the simple decoupling, which will be the attitude of the optimal estimation and the optimal estimate gyro drift apart, in this way, can through the intuitive method to adjust the parameters of the two parts. Platform: |
Size: 35840 |
Author:张文龙 |
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Description: 四轴飞行器姿态控制系统设计
四轴飞行器具有不稳定、非线性、强耦合等特性,姿态控制是四轴飞行器飞行控制系统的核心 通过分析四轴飞行器的飞行
原理,根据其数学模型和系统的功能要求,设计了四轴飞行器的姿态控制系统 该系统采用stm32系列32位处理器作为主控制器,使用
ADIS16355惯性测量单元等传感器用于姿态信息检测 系统基于模块化设计的思想,各传感器都使用数字接口进行数据交换,结构简
单 使用PID控制算法进行姿态角的闭环控制,实验结果表明,飞行器能较好的稳定在实验平台上,系统满足四轴飞行器室内飞行姿态
控制的要求。
-Four axis is instability, nonlinear, strong coupling and other features, four axis attitude control is the core of the aircraft flight control system By analyzing the four axis aircraft flight principle, according to its mathematical model and the function of the system, designed the four axis spacecraft attitude control system The system USES stm32 series of 32-bit processor as the main controller, using ADIS16355 sensors such as inertial measurement unit are used in attitude information detection System based on the idea of modular design, each sensor using the digital interface for data exchange, structure is simple For closed-loop control of attitude Angle using PID control algorithm, experimental results show that the craft can better stability in the experimental platform, the system meet the requirements of four axis aircraft flying indoor attitude control. Platform: |
Size: 577536 |
Author:竹林海宝 |
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Description: Goal of this project is to simulate the rotational motion of a spacecraft in orbit. Plots of Euler angles and polhode curves (angular velocity time histories) are generated. Equations of Motion included in this package are for a rigid body in a torque-free environment and in circular orbit. See the EOM section under the Source Code Guide for more information.
The code is designed to be modular. Without getting very fancy, the user only needs to modify sc_attitude, sc_init, and sc_batch, depending on the experiment. Platform: |
Size: 221184 |
Author:nab05
|
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