in order to obtain independent representations on viewpoint, the three principal axes of the object should be found frm the moment of inertia matrix by computing its eigenvectors.
为了得到独立于观察点的表示,应通过计算惯量矩阵的特征向量确定客体的三个主轴。
for rigid spacecraft attitude tracking system with uncertain inertia matrix and external disturbances, an adaptive sliding mode approach is presented.
针对存在不确定惯量矩阵和外干扰的刚体航天器姿态跟蹤系统,提出了一种自适应滑模控制方法。
based on varieties of the inertia matrix for a combined spacecraft after separation, this paper proposes a adaptive control algorithm.
针对组合式航天器分离后惯量矩阵会产生较大变化的特点,提出了一种自适应控制律。
based on varieties of the inertia matrix for a combined spacecraft separated, this paper proposes a adaptive control algorithm.