Orbit Estimation for Spacecraft Based on Intermittent Measurements: An Event-Triggered UKF Approach

Hou, Lei; Zou, Hengguang; Zheng, Kaikai; Zhang, Lei; Zhou, Na; Ren, Junqiang; Shi, Dawei

doi:10.1109/taes.2021.3103581

Cited by 8 publications

(2 citation statements)

References 47 publications

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“…Further motivation for the use of the UKF as opposed to other modeling methods or comparison to the true dynamical ephemerides lies in the fact that the author's wish to give a useful comparison between two distinct estimation methods. Additionally, the UKF has been applied successfully to onboard processing for spacecraft missions and is known to better model the non-Gaussian behavior of orbital dynamics than linearized filters [43][44][45][46].…”

Section: Non-linear Estimation Model (Unscented Kalman Filter)mentioning

confidence: 99%

Rendezvous and Proximity Operations in Cislunar Space Using Linearized Dynamics for Estimation

Zuehlke,

Tiwari,

Jebari

et al. 2023

Aerospace

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As interest in Moon exploration grows, and efforts to establish an orbiting outpost intensify, accurate modeling of spacecraft dynamics in cislunar space is becoming increasingly important. Contrary to satellites in Low Earth Orbit (LEO), where it takes around 5 ms to communicate back and forth with a ground station, it can take up to 2.4 s to communicate with satellites near the Moon. This delay in communication can make the difference between a successful docking and a catastrophic collision for a remotely controlled satellite. Moreover, due to the unstable nature of trajectories in cislunar space, it is necessary to design spacecraft that can autonomously make frequent maneuvers to stay on track with a reference orbit. The communication delay and unstable trajectories are exactly why autonomous navigation is critical for proximity operations and rendezvous and docking missions in cislunar space. Because spacecraft computational hardware is limited, reducing the computational complexity of navigational algorithms is both desirable and often necessary. By the introduction of a linear system approach to the deputy spacecraft motion, this research avoids the computational burden of integrating the deputy relative equations of motion. In this research, the relative CR3BP equations of motion are derived and linearized using a matrix exponential approximation. This research continues the development of the matrix exponential linearized relative circular restricted three-body problem (CR3BP) equations by applying the dynamics model to estimation and control applications. A simulation is performed to compare state estimation results obtained from using the linearized equations of motion utilizing a Kalman filter and for state estimation utilizing an unscented Kalman filter with the full nonlinear equations of motion. The linearized exponential model is shown to be sufficient for state estimation in the presence of noisy measurements for an example scenario. Additionally, a linear quadratic regulator (LQR) controller was added to optimally control a deputy spacecraft to rendezvous with a chief spacecraft in cislunar space. The contribution of this work is twofold: to provide a proof of concept that the matrix exponential solution for the linearized relative CR3BP equations can be used as the dynamics model for state estimation, as well as to simulate an optimal rendezvous maneuver in the presence of measurement noise.

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Section: Non-linear Estimation Model (Unscented Kalman Filter)mentioning

confidence: 99%

Rendezvous and Proximity Operations in Cislunar Space Using Linearized Dynamics for Estimation

Zuehlke,

Tiwari,

Jebari

et al. 2023

Aerospace

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“…Ref. [29] designed an event-triggered orbit estimator for a spacecraft with intermittent sensor measurements. To deal with the implicit measurement model, an event-triggered IUKF is presented for celestial navigation using time delay measurement [30].…”

Section: Introductionmentioning

confidence: 99%

Parameter-Independent Event-Triggered Implicit UKF for the Celestial Navigation Using Time Delay Measurement

Gui

Wei

et al. 2023

Mathematics

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Celestial navigation using time delay measurement is an innovative autonomous navigation method. To calculate the equivalent measurement, the numerical method needs to be applied, which is time-consuming. The event-triggered mechanism intermittently and aperiodically processes measurements by judging if the update error has changed drastically. However, its performance is greatly affected by the constant threshold. To solve this problem, a parameter-independent event-triggered implicit unscented Kalman filter (UKF) is proposed and applied to the celestial navigation using time delay measurement. The innovation at the current moment and the updated estimate covariance at the last moment are compared with the previous value instead of the constant threshold. The event is automatically triggered when the accuracy of the state estimate is low. Simulation results indicate that the proposed parameter-independent event-triggered implicit UKF can reduce the running time by reducing unnecessary measurement updates, whose performance will not be affected by any parameter or window size. In a word, the proposed method substitutes the dynamic threshold for the constant threshold, ensuring that its performance will not be affected by any parameter or window size.

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Dual-quaternion-based satellite pose estimation and control with event-triggered data transmission

Zou

Shi

et al. 2023

Sci. China Technol. Sci.

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Orbit Estimation for Spacecraft Based on Intermittent Measurements: An Event-Triggered UKF Approach

Cited by 8 publications

References 47 publications

Rendezvous and Proximity Operations in Cislunar Space Using Linearized Dynamics for Estimation

Rendezvous and Proximity Operations in Cislunar Space Using Linearized Dynamics for Estimation

Parameter-Independent Event-Triggered Implicit UKF for the Celestial Navigation Using Time Delay Measurement

Dual-quaternion-based satellite pose estimation and control with event-triggered data transmission

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