Abstract
The accuracy of autonomous orbit determination of Lagrangian navigation constellation will affect the navigation accuracy for the deep space probes. Because of the special dynamical characteristics of Lagrangian navigation satellite, the error caused by different estimation algorithm will cause totally different autonomous orbit determination accuracy. We apply the extended Kalman filter and the fading–memory filter to determinate the orbits of Lagrangian navigation satellites. The autonomous orbit determination errors are compared. The accuracy of autonomous orbit determination using fading-memory filter can improve 50% compared to the autonomous orbit determination accuracy using extended Kalman filter. We proposed an integrated Kalman fading filter to smooth the process of autonomous orbit determination and improve the accuracy of autonomous orbit determination. The square root extended Kalman filter is introduced to deal with the case of inaccurate initial error variance matrix. The simulations proved that the estimation method can affect the accuracy of autonomous orbit determination greatly.
Highlights
Deep space exploration has become a hot spot of aerospace
In [23], Gao et al discussed the feasibility of autonomous orbit determination using only the crosslink range measurement for a combined Lagrangian navigation constellation and GNSS
To overcome the divergence of autonomous orbit determination (AOD) error caused by the state estimation error covariance matrix losing its properties of positive definite symmetric, we introduce the square root extended Kalman filter (SR-EKF) to estimate the state of
Summary
Deep space exploration has become a hot spot of aerospace. Several deep space probes have been launched. The satellite navigation constellation can provide navigation information for deep space probes. The Lagrangian navigation constellation is introduced to navigate the deep space probes autonomously. Relative navigation usually is applied to satellites in a formation or constellation involved using GPS which restricts the spacecraft formation to near-Earth applications, such as Deep Space Mission 3 [15] and Grace project [16]. Autonomous orbit determination of the Lagrangian navigation constellation is using the relative measurement to achieve absolute navigation. In [23], Gao et al discussed the feasibility of autonomous orbit determination using only the crosslink range measurement for a combined Lagrangian navigation constellation and GNSS. In order to improve the robustness and stability accuracy, Wang and Gu applied fault tolerant UKF in autonomous determination of relative orbit for satellite formation flying [29]. We introduce four estimation methods to achieve the AOD of Lagrangian navigation constellation to analyze the effect on AOD by estimation method
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