本项目研究了可重组航天器的姿态动力学与控制问题。
The present project deals with attitude dynamics and control of reconfigurable spacecrafts.
对航天器姿态动力学模型和姿态控制技术进行了概括和总结。
The model of spacecraft attitude dynamics and the attitude control technology are generalized.
建立卫星姿态动力学数学模型，并分析星体所受的外部扰动力矩。
Mathematic model of satellite attitude dynamic is set up, and external disturbance torque is analyzed.
由混合坐标方程导出姿态动力学逆传递函数矩阵，并分析其正规性。
The inverse transfer function matrix of attitude dynamics is derived from the hybrid coordinates equations, and its normality is analyzed.
卫星姿态动力学系统与其线性化模型之间的误差会影响姿态控制的精度。
The error between satellite attitude dynamics and its linearized model can affect the attitude control precision.
由于地磁场的方向在轨道上周期变化，卫星的姿态动力学方程是一个线性周期系统。
Since the geomagnetic field varies periodically on orbit, the dynamics of satellite is a linear periodic system.
与传统的以混合坐标表示的模型相比，此模型能够获得更全面、更精确的姿态动力学特性。
Comparing with the conventional hybrid coordinate model, this model provides more detailed, more accurate dynamic properties.
首先建立了以变速控制力矩陀螺为执行机构的航天器姿态动力学模型，并给出了全局稳定的姿态反馈控制律。
The attitude dynamic equation of a spacecraft with VSCMG attached and a global asymptotical attitude feedback control law are presented firstly.
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。
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.
所得结果不仅适用于具有大型运动部件的航天器的姿态动力学分析及控制系统设计，也适用于灵敏小卫星的相应研究。
The proposed results are useful to the attitude dynamic analysis and control system design for not only the spacecraft with large rotation parts, but also the agile small satellite.
结果表明设计出的新型太阳帆板驱动机构对卫星姿态动力学和控制具有重大影响，能够明显改善卫星姿态控制的效果。
Results showed that the new driving mechanism has significant influence on dynamics of satellite and could improve attitude control performance.
通过考虑单元间的边界条件可以得到姿态动力学的解析模型，并由此可以获得外扰动和姿态角到附件弹性位移之间的传递特性。
Boundary conditions are used to assemble the global system model, and transfer properties from external disturbance or attitude to elastic deflection of appendages are obtained.
本文讨论了这种姿态控制系统的设计方法和动力学性能。
The design procedure and dynamic behavior of this system are discussed.
实现类人型机器人动态行走，必须对机器人进行动力学建模、步态设计和稳定姿态控制算法设计。
To realize dynamic walking of the humanoid robot, robot dynamic models have to be established, the control algorithm for gait and the stability postures should be designed.
以一个呈现混沌姿态运动的航天器动力学模型为例说明了该控制律的应用。
A mathematical model derived from spacecraft attitude dynamics is treated as an example to demonstrate its application.
提出了一种基于逆动力学和在线参数辨识的方法，用于直接设计综合控制系统中的姿态控制器。
A synthesis method based on inverse dynamics and online parameter identification was developed and was directly used to design the attitude controller in the integrated control system.
利用伞-弹系统动力学模型，从工程应用的角度出发，分析了阵风小扰动作用下，子弹姿态的运动特性，并以此为基础给出了末修子弹弹下点的计算模型。
The dynamics model of parachute-munition system is used to analyze the motion characters of submunition under the effect of wind gust, and the calculation model of projective point is presented.
在挠性卫星动力学模型的基础上，建立了只考虑太阳帆板三阶振动模态的挠性卫星三轴姿态控制模型。
The three-axis attitude stabilization system of the flexible satellite has been studied, in which three basic vibration modes of the solar array have been considered.
姿态运动学和动力学用误差四元数描述。
The attitude kinematics and dynamics are both described by error quaternions.
太阳帆航天器动力学建模与求解是姿态控制与结构振动抑制的基础，具有重要的理论与工程意义。
Solar sail spacecraft dynamic modeling and solving are the basis of attitude control and structural vibration suppression, and they are of important theoretical and engineering significance.
考虑控制输入耦合，建立服务航天器对目标航天器的相对位置和姿态一体化耦合动力学模型。
Considering coupled control inputs, an integrated coupling relative position and attitude dynamic model of the on-orbit servicing spacecraft is built with respect to the target spacecraft.
以非线性瞬态动力学理论为基础，计算和分析了某型火箭发射过程中管内姿态情况。
The posture of a rocket in launch tube was calculated and analyzed Basel on the theory of non-linear transient dynamics.
昆虫在空中各种姿态的空气动力学特性、原理、计算方法。
Study on the aerodynamics, theory and design methods for robot insects flying postures.
目标在空中的姿态及轨迹由动力学和运动学方程确定。
The pose and trajectory of the flying radar target are calculated by means of dynamical and kinematical equations.
对相对姿态进行了运动学和动力学分析，重点研究了相对姿态四元数运动方程。
The relative attitude is analyzed in kinematics and dynamics respectively. And the kinematics equations of attitude quaternion are studied in detail.
最后，对天平模型进行了动力学分析，用基于模型体坐标系的分析结果代替原来的基于地面坐标系的模型姿态的数学公式和动力学方程。
At the last of this paper, dynamics and kinematics analysis is given, which is based on the model's coordinates rather than on the ground coordinates.
基于对飞机模型在不同姿态下进行的空气动力学测试，文中设计了用于低速风洞的变角度系统。
Based on the aerodynamic test of plane models under different positions, the variable Angle system used in low-speed wind tunnels is designed in this paper.
讨论了本体姿态受控、位置不受控的情况下，漂浮基双臂空间机器人系统协调运动的动力学控制问题。
The dynamic control problem for coordinated motion of a free-floating dual-arm space robot system was discussed.
讨论了本体姿态受控、位置不受控的情况下，漂浮基双臂空间机器人系统协调运动的动力学控制问题。
The dynamic control problem for coordinated motion of a free-floating dual-arm space robot system was discussed.
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