A novel relative navigation method based on thrust on-line identification for tight formation keeping

Abstract

Purpose

The purpose of this paper is to present a novel high-precision relative navigation method for tight formation-keeping based on thrust on-line identification.

Design/methodology/approach

Considering that thrust acceleration cannot be measured directly, an on-line identification method of thrust acceleration is explored via the estimated acceleration of major space perturbation and the inter-satellite relative states obtained from space-borne acceleration sensors; then, an effective identification model is designed to reconstruct thrust acceleration. Based on the identified thrust acceleration, relative orbit dynamics for tight formation-keeping is established. Further, using global positioning system (GPS) measurement information, a modified extended Kalman filter (EKF) is suggested to obtain the inter-satellite relative position and relative velocity.

Findings

Compared with the normal EKF and the adaptive robust EKF, the proposed modified EKF has better estimation accuracy in radial and along-track directions because of accurate compensation of thrust acceleration. Meanwhile, high-precision relative navigation results depend on high-precision acceleration sensors. Finally, simulation studies on a chief-deputy formation flying control system are performed to verify the effectiveness and superiority of the proposed relative navigation algorithm.

Social implications

This paper provides a reference in solving the problem of high-precision relative navigation in tight formation-keeping application.

Originality/value

This paper proposes a novel on-line identification method for thrust acceleration and shows that thrust identification-based modified EKF is more efficient in relative navigation for tight formation-keeping.

Citation

Zhu, W., Zhang, D., Wang, J. and Shao, X. (2017), "A novel relative navigation method based on thrust on-line identification for tight formation keeping", Aircraft Engineering and Aerospace Technology, Vol. 89 No. 3, pp. 406-414. https://doi.org/10.1108/AEAT-10-2015-0224