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 dynamics of orbit uncertainty in an unstable orbital environment are discussed
with specific application to the orbit determination of a halo orbit about
the Earth{Sun L1 point. This article documents a simplified orbit determination
covariance program developed under Telecommunications and Mission Operations
Division Technology support. The program is ideally suited to investigate spacecraft
trajectory navigation in challenging environments, where the basic dynamics
of the trajectory can no longer be modeled using near-Keplerian motion. Platform: |
Size: 647168 |
Author:yag |
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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: 椭圆轨道下卫星编队飞行相对运动动力学和控制-Relative Dynamics and Control of Spacecraft Formations in Eccentric Orbits Platform: |
Size: 345088 |
Author:蒙蒙 |
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Description: 本书介绍了飞行器姿态动力学的基本原理与任务控制，为英文原版-This book introduces the basic principles and mission control spacecraft attitude dynamics, as the English original Platform: |
Size: 24767488 |
Author:张文昭 |
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Description: 航天器动力学中用于计算E角各种方法MATLAB程序，包括迭代法，几何法-Spacecraft Dynamics various methods used to calculate the angle E MATLAB program, including the iterative method, geometric method, etc. Platform: |
Size: 6144 |
Author:李苗 |
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Description: 航天器动力学MATLAB程序，考虑大气阻力，估计神舟飞船每运行一个周期，轨道高度下降多少-Spacecraft Dynamics MATLAB program, consider the atmospheric drag, estimated that the Shenzhou spacecraft each run a cycle, the number of orbital altitude drop Platform: |
Size: 3072 |
Author:李苗 |
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Description: 航天器动力学中用于计算轨道转换的MATLAB程序，包括平面的转换为空间的与空间的转换为平面轨道。-Spacecraft Dynamics used to calculate the orbit convert MATLAB program, including the conversion plane converted to space and space for flat track. Platform: |
Size: 3072 |
Author:李苗 |
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Description: 利用龙格-库塔法求解了航天器深空返回再入运动动力学方程，并对返回再入运动进行了仿真分析。-Use of Runge- Kutta method to solve the deep-space spacecraft reentry return movement dynamics equations, and the return movement is simulated reentry. Platform: |
Size: 8192 |
Author:许宁 |
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Description: 航天动力学的一个分支，研究航天器的姿态运动，包括航天器整体围绕其质心的运动以及航天器各部分之间的相对运动-A branch of space dynamics that studies the spacecraft s attitude movement, including the motion of the spacecraft as a whole around its centroids and the relative movement between the various parts of the spacecraft Platform: |
Size: 17408 |
Author:victordue |
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Description: 航天器动力学代码，依次实现以下要求：
（1）给出一组轨道根数OE，求出初始的位置R和速度V。
（2）根据轨道根数，用代数方程画出轨道Orbit1
（3）根据初始的位置和速度，用微分方程画出Orbit2
（4）把平面的Orbit1转换为空间的Orbit3，并与Orbit2进行比较
（5）把空间的Orbit2转换为Orbit4，并与Orbit1进行比较(The spacecraft dynamics code achieves the following requirements in turn.
(1) give a set of orbital elements OE, find out the initial position R and speed V.
(2) according to the number of orbital elements, the orbital Orbit1 is drawn by algebraic equation.
(3) draw Orbit2 from differential equations based on the initial location and speed.
(4) transform the Orbit1 of the plane into the Orbit3 of space and compare it with Orbit2.
(5) convert the Orbit2 of space to Orbit4 and compare it with Orbit1.) Platform: |
Size: 2048 |
Author:liu-xt15 |
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