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: |
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Author:跃进 |
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Description: 用来计算航天器再入质点弹道，其中包括插值算法，龙格库塔法以及大气模型-Used to calculate the particle trajectory of spacecraft re-entry, including the interpolation algorithm, Runge-Kutta method as well as atmospheric model Platform: |
Size: 250880 |
Author:wang de |
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Description: 新一代高速气象卫星数据通讯协议，支持高速云图发送以及JPEG压缩编码。和最新的风云系列格式基本一致。-Global Specification for Low Rate and High Rate Information Transmission
(LRIT/HRIT) [AD.1] has been agreed by the Co-ordination Group for Meteorological
A Satellites (CGMS). The global specification is based on the ISO standard 7498 (OSI
Reference Model) [RD.1] and the CCSDS recommendations of Advanced Orbiting Systems
(AOS) [RD.2]. It defines the structure and the formatting of the LRIT/HRIT files and the
processing and transport protocols of all OSI layers applicable to all geostationary
meteorological spacecraft. Platform: |
Size: 299008 |
Author:zhfjyq |
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Description: 一个VB三维飞行游戏轮廓模型演示程序，图中会生成类似宇宙飞船、直升机形状的三维轮廓图形，而且还会变换角度飞来飞去。程序较早，是在老外网站发现的，不知道对您是否有用，在VB6下顺利编译，感兴趣的可以看下源代码。
-VB game a three-dimensional contour model flight demonstration program, the figure will be generated similar spacecraft, the helicopter-shaped three-dimensional outline of graphics, but also transform the perspective of flying. Earlier procedures is found in the foreign site, I do not know whether it is useful to you, in VB6 to compile successfully, could be of interest to facie source code. Platform: |
Size: 21504 |
Author:冉彬 |
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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: Matlab航天器工具箱，用于轨道计算，2D或3D的平面显示，包含计算多卫星轨道动力学模型和地面覆盖分析等-Matlab toolbox spacecraft for orbit calculation, 2D or 3D graphic display, including the calculation of multi-satellite orbital dynamics analysis model and floor coverings Platform: |
Size: 362496 |
Author:zhangyuedong |
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Description: 一个航天器的动力学响应程序，采用模态价值分析准则和内平衡法则进行模型降阶。-Dynamic response of a spacecraft program, the use of value analysis mode within the balance guidelines and rules for model reduction. Platform: |
Size: 1024 |
Author:liupan |
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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: 用于地月轨道返回航天器轨道仿真，包括仿真主程序和大气模型-Back for the Earth-Moon orbit spacecraft orbit simulation, including the main program and the atmospheric model simulation Platform: |
Size: 5120 |
Author:Wangwen |
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Description: The Monte Carlo Investigation of Trajectory Operations and Requirements (MONITOR) program was developed to perform spacecraft mission maneuver simulations for geosynchronous, single maneuver, and comet encounter type trajectories. MONITOR is a multifaceted program which enables the modeling of various orbital sequences and missions, the generation of Monte Carlo simulation statistics, and the parametric scanning of user requested variables over specified intervals. The MONITOR program has been used primarily to study geosynchronous missions and has the capability to model Space Shuttle deployed satellite trajectories. The ability to perform a Monte Carlo error analysis of user specified orbital parameters using predicted maneuver execution errors can make MONITOR a significant part of any mission planning and analysis system. Platform: |
Size: 108544 |
Author:amir |
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Description: Matlab进行再入式飞行器轨道建模与仿真，建立各种模型，最后获得飞行器的动力学模型，并调用龙格库塔函数求解该微分方程初值问题。-Matlab for reentry spacecraft orbit modeling and simulation, the establishment of various models, and finally obtain the dynamic model of the aircraft, and call the Runge-Kutta function of the initial value problem solving differential equations. Platform: |
Size: 7168 |
Author:zcx |
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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: 地月系统中，探月航天器运动的简单的数学模型，月球绕地运动近似为匀速圆周运动，程序中各天体坐标可以在JPL的星历表中查询修改。(In the Earth Moon system, the simple mathematical model of lunar exploration spacecraft motion is similar to the uniform motion around the moon. The coordinates of celestial bodies can be querying in the ephemeris of JPL.) Platform: |
Size: 1024 |
Author:莽叔叔 |
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Description: 航天器姿态控制仿真程序，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，利用linmod对非线性模型线性化。(The simulation program of spacecraft attitude control uses the sfunction method of Simulink to establish the dynamic model and kinematic model of spacecraft attitude, and uses limod to linearize the nonlinear model.) Platform: |
Size: 8192 |
Author:woyaokaobo |
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Search - spacecraft model