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首页> 外文会议>Cranfield Conference on Dynamica and Control of Systems and Structures in Space; 2004; Liguria; IT >A Comparison between Models of Flexible Spacecraft
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A Comparison between Models of Flexible Spacecraft

机译：挠性航天器模型之间的比较

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摘要

Flexibility plays an important role in the design of space missions. Algorithms able to derive the dynamical equations for a generic chain of flexible and rigid bodies have been developed in the past decades so that accurate dynamic simulations of large multi-body chains are possible. On the other hand control devices are getting more and more sophisticated so that the guidance of satellite platforms equipped with last generation fly-wheels is a quite complex task. In order to develop control laws, restrictive hypotheses are commonly introduced to make the equation of motion as simple as possible: rigid body dynamic, small angular velocities, small deformations, symmetric appendages bending, reduced degrees of freedom and many other hypotheses lead to as many different mathematical models. Simple modeling leads to fast simulations and allows an easier design of attitude steering laws or vibration suppression controls. In this work a mathematical model describing the full non-linear dynamic of a flexible satellite platform equipped with a system of rigid fly-wheels is developed in an explicit form. The equations are than compared to those obtained by applying standard multi-body analysis. The advantages of having an explicit form of the equations in term of the sole state of the central platform (the state of the wheels is considered as a control) are particularly attractive for control design. The set of ordinary differential equations written returns widely used model when restrictive hypotheses are introduced and has to be used in connection to a preliminary Finite Element Method analysis in order to evaluate the structural invariants.
机译：灵活性在太空任务设计中起着重要作用。在过去的几十年中，已经开发出了能够推导通用的柔性和刚体链动力学方程的算法，从而可以对大型多体链进行精确的动力学仿真。另一方面，控制设备变得越来越复杂，因此配备上一代飞轮的卫星平台的制导是一项相当复杂的任务。为了制定控制律，通常引入限制性假设以使运动方程尽可能简单：刚体动力学，较小的角速度，较小的变形，对称的附件弯曲，减小的自由度以及许多其他假设导致了很多不同的数学模型。简单的建模可以实现快速的仿真，并可以简化姿态转向定律或振动抑制控件的设计。在这项工作中，以明确的形式开发了描述装备有刚性飞轮系统的柔性卫星平台的全部非线性动力学的数学模型。然后将该方程与通过应用标准多体分析获得的方程进行比较。就中央平台的唯一状态（车轮的状态被视为控件）而言，具有明确形式的方程式的优点对于控件设计特别有吸引力。当引入限制性假设时，编写的一组常微分方程可返回使用广泛的模型，并且必须将其与初步有限元方法分析结合使用才能评估结构不变性。

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