Linear dynamic modeling of spacecraft with various flexibleappendages and on-board angular momentums
Linear dynamic modeling of spacecraft with various flexibleappendages and on-board angular momentums
复制标题
具有各种柔性附件和星上角动量的航天器的线性动力学建模
DOI：
--
复制
发表时间：
2008
期刊：
影响因子：
--
通讯作者：
K. Tantawi
中科院分区：
文献类型：
--
作者：
D. Alazard;C. Cumer;K. Tantawi
我们在这里介绍一种方法和一些工具，用于构建空间应用（通常是卫星）多体系统的线性模型。多体系统由配备刚性和柔性附件（太阳能电池板、天线、推进剂罐等）的主体（轮毂）和机载角动量（飞轮、控制力矩陀螺仪）组成。每个附件都可以通过悬臂接头或枢轴接头连接到轮毂。更一般地说，我们的方法可以应用于任何开放式机械链。在我们的方法中，刚性的六个自由度 (d.o.f)（三个平移和三个旋转）被一起处理。这对于建立复杂多体系统的线性模型非常方便。然后，可以很容易地导出用于设计 AOCS 的动力学模型，即力和扭矩（施加在轮毂上）以及轮毂的角位置、线性位置和速度之间的模型。该模型可以使用框图表示来解释。
We present here a method and some tools developed to build linear models of multi-body systems for space applications (typically satellites). The multi-body system is composed of a main body (hub) fitted with rigid and flexible appendages (solar panels, antennas, propellant tanks,...) and on-board angular momentums (flywheels, control moment gyros). Each appendage can be connected to the hub by a cantilever joint or a pivot joint. More generally, our method can be applied to any open mechanical chain. In our approach, the rigid six degrees of freedom (d.o.f) (three translational and three rotational) are treated all together. That is very convenient to build linear models of complex multi-body systems. Then, the dynamics model used to design AOCS, i.e. the model between forces and torques (applied on the hub) and angular and linear position and velocity of the hub, can be derived very easily. This model can be interpreted using block diagram representation.