Influence of Initial State Errors on Perturbation Guidance Accuracy

Wuxing Jing; Xu Zheng; Changsheng Gao

doi:10.14429/dsj.69.11527

Wuxing Jing Department of Aerospace Engineering, Harbin Institute of Technology, Harbin - 150 001, China
Xu Zheng Department of Aerospace Engineering, Harbin Institute of Technology, Harbin - 150 001, China
Changsheng Gao Department of Aerospace Engineering, Harbin Institute of Technology, Harbin - 150 001, China

DOI: https://doi.org/10.14429/dsj.69.11527

Keywords: long-range vehicle, inertial navigation system, initial state errors, perturbation guidance, Monte Carlo targeting

Abstract

The inertial navigation system is aligned and leveled before the launch of a long-range vehicle. However, the initial state errors caused by the non-uniformity of the Earth can influence the parameters in flight dynamics, which will bring about serious uncertainty for the impact point of a long-range vehicle. Firstly, this paper analyses the influence mechanism of initial state errors on nominal trajectory, navigation trajectory and guidance trajectory. Then, a propagation model of engine-cutoff state deviation caused by initial state errors is derived under the condition of without-guidance. On this basis, an accuracy analytical solution of initial state errors on perturbation guidance is finally proposed to obtain the real impact-point of the long-range vehicle. In the simulations, the influence properties of initial state errors on perturbation guidance is analysed, give influence regularities of single initial state error, and obtain the statistical properties of engine-cutoff state deviations and impact-point deviation by Monte Carlo technique. From the simulation results, it seems that the navigation state tracks the nominal state. However, the real impact- point deviation has not been truly eliminated, instead of the almost target-hit deviation calculated by navigation output. The proposed analytical guidance accuracy model can be rapidly computed to provide a compensation for guidance and control system to improve hit accuracy.

Author Biographies

Wuxing Jing, Department of Aerospace Engineering, Harbin Institute of Technology, Harbin - 150 001, China

Dr Xu Zheng received his MS and Phd in department of Aerospace Engineering from Harbin Institute of Technology in 2014 and 2018, respectively. He is currently an engineer in Nanjing Institute of Electronic Engineering. His research interests include nonlinear guidance and control, multidisciplinary design optimisation.
In the current study, he performed and simulated the rapid calculation model of engine-cutoff state uncertainty caused by ISEs.

Xu Zheng, Department of Aerospace Engineering, Harbin Institute of Technology, Harbin - 150 001, China

Dr wuxing jing received MS and Phd from Harbin Institute of Technology in 1989 and 1994, respectively. He was a visiting professor at University of Glasgow, UK, from 2000 to 2001. He is currently a professor and PhD supervisor in Harbin Institute of Technology. His research interests are autonomous navigation, nonlinear guidance, dynamics and control of spacecraft.
In the current study, he performed and analysed the influence mechanism of ISEs on norminal trajectory, navigation trajectory and guidance trajectory.

Changsheng Gao, Department of Aerospace Engineering, Harbin Institute of Technology, Harbin - 150 001, China

Dr changsheng Gao received MS and Phd from Harbin Institute of Technology in 2004 and 2007, respectively. His research interests are nonlinear guidance, dynamics and control of spacecraft.
In the current study, he performed and analysed the simulation results

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