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首页> 外文期刊>International journal of non-linear mechanics >Analytical solutions for dynamics of dual-spin spacecraft and gyrostat-satellites under magnetic attitude control in omega-regimes
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Analytical solutions for dynamics of dual-spin spacecraft and gyrostat-satellites under magnetic attitude control in omega-regimes

机译：欧米茄区域磁姿态控制下双旋航天器和陀螺仪卫星的动力学解析解

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摘要

The attitude dynamics of a dual-spin spacecraft (a gyrostat with one rotor) with magnetic actuators attitude control is considered in the constant external magnetic field at the presence of the spacecraft's own magnetic dipole moment, which is created proportionally to the angular velocity components (this motion regime can be called as "the omega-regime" or "the omega-maneuver"). The research of the dual-spin spacecraft angular motion under the action of the magnetic restoring torque is fulfilled in the generalized formulation close to the classical mechanics' task of the heavy body/gyrostat motion in the Lagrange top. Analytical exact solutions of differential equations of the motion are obtained for all parameters in terms of elliptic integrals and the Jacobi functions. New obtained analytical solutions can be classified as results developing the classical fundamental problem of the rigid body and gyrostat motion around the fixed point. The technical application of the omega-regime to the angular reorientation of the spacecraft longitudinal axis along the angular momentum vector is considered. (C) 2017 Elsevier Ltd. All rights reserved.
机译：在航天器自身的磁偶极矩存在的情况下，在恒定的外部磁场中考虑具有磁致动器姿态控制的双自旋航天器（带一个转子的陀螺仪）的姿态动力学，该磁偶极矩与角速度分量成正比（这种运动方式可以称为“欧米茄体制”或“欧米茄机动”。在广义的公式中完成了在磁性恢复扭矩作用下的双自旋航天器角运动的研究，该公式接近经典力学的拉格朗日顶部重物/陀螺仪运动的任务。对于所有参数，根据椭圆积分和雅可比函数，可以获得运动微分方程的解析精确解。新获得的解析解可以归类为开发经典的基本问题，即刚体和陀螺仪围绕固定点运动的结果。考虑了欧米伽制度在航天器纵轴沿角动量矢量的角度重新定向中的技术应用。 （C）2017 Elsevier Ltd.保留所有权利。

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