Application of Rotating Vector in Equations of Motion for All-attitude Aircrafts

doi:10.3969/j.issn.1000-1093.2016.03.008

Abstract

Abstract: A mathematical framework to apply a rotation vector in the equations of motion for all-attitude aircrafts is established based on the basic idea of that the rotation vector is to express an equivalent rotation corresponding to the change in angular position rather than the angular position. This idea is stimulated by the rotating vector in the strapdown attitude algorithm. The rotation vector method is available for all-attitude solution while the Euler angle method is not. Meanwhile, compared with the quaternion method, the rotation vector method can improve the efficiency of attitude solution. The non-commutative errors in the rotation vector method, the quaternion method and the Euler angle method are analyzed in detail. A rotation vector method based on the quasi-body frame is developed to improve the efficiency of attitude solution for axial-symmetry aircrafts of which a single channel has high dynamic characteristics. The digital simulations based on the equations of motion for some rolling missile show the effectiveness and generality of the rotation vector method.

Key words: control and navigation technoogy of aerocraft, rotation vector, Euler angle, quaternion, high-dynamic, all-attitude

CLC Number:

TJ765.1

WANG Hong-hui， YANG Shao-qing， WU Cheng-fu， HAO Feng, CHE Xiao-tao. Application of Rotating Vector in Equations of Motion for All-attitude Aircrafts[J]. Acta Armamentarii, 2016, 37(3): 439-446.

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