Three-spacecraft autonomous orbit determination and observability analysis with inertial angles-only measurements

Hu, Yunpeng; Sharf, Inna; Chen, Lei

doi:10.1016/j.actaastro.2020.01.005

Cited by 26 publications

(14 citation statements)

References 25 publications

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“…SSUKF Process Noise Estimation Based on APSO. In the iterative process of the SSUKF filtering algorithm, the noise statistical properties are determined a priori and remain constant throughout the filtering process; in fact, when using SBOS for target tracking, the accuracy of measurement is affected by the solar angle on the one hand and related to the pointing of the sensor on the other hand [33], and the pointing deviation of the sensor will cause all the measurements to deviate from the actual value, causing the noise covariance matrix R to change. This paper proposes to use the innovation sequence for real-time estimation of the measurement noise and combine the optimization algorithm for real-time tracking of the process noise Q to make the system more approximate to the actual value.…”

Section: Spherical Simplex Unscented Kalman Filter (Ssukf)mentioning

confidence: 99%

Angle-Only Target Tracking Method for Optical Imaging Micro-/Nanosatellite Based on APSO-SSUKF

Hua

Yang

et al. 2022

Space Sci Technol

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To ensure the safety of the space station and improve the accuracy of the estimated trajectory tracking of noncooperative target, an optical imaging micro-/nanosatellite based on APSO-SSUKF (adaptive particle swarm optimization-spherical simplex unscented Kalman filter) is proposed to track low-orbit target using angle-only measurement. First, the algorithm considers the effect of J2 perturbation, uses the angle-only data as the observation vector, and uses spherical simplex unscented Kalman filter (SSUKF) to reduce the cost of calculation of the UKF in space noncooperative target tracking. Secondly, it is proposed to use the actual and theoretical covariance of the innovation sequence for real-time estimation of measurement noise, designing the adaptive particle swarm optimization (APSO) algorithm for real-time tracking of the process noise in the SSUKF that improves the accuracy of the filter in angle-only tracking. Finally, the tracking simulation of low-orbit satellite is carried out by using optical imaging micro-/nanosatellite, and the result shows that, compared with UKF, SSUKF, and PSO-SSUKF, APSO-SSUKF reduces the root mean square of the error in predicting the position in space target tracking by 45.44%, 35.26%, and 20.94%, and APSO-SSUKF reduces the root mean square of the error in velocity by 45.58%, 33.53%, and 16.33%, respectively; in the angle-tracking target, APSO-SSUKF improves the convergence and estimated accuracy of the algorithm in tracking.

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Section: Spherical Simplex Unscented Kalman Filter (Ssukf)mentioning

confidence: 99%

Angle-Only Target Tracking Method for Optical Imaging Micro-/Nanosatellite Based on APSO-SSUKF

Hua

Yang

et al. 2022

Space Sci Technol

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“…Recently, a variety of methods have been proposed to solve the autonomous OD problem for a satellite constellation by using only interspacecraft relative measurements [ 23 , 24 , 25 , 26 ]. However, they all face the rank deficiency, meaning that the multispacecraft system with interspacecraft measurements alone is unobservable [ 27 ].…”

Section: Introductionmentioning

confidence: 99%

“…Another well-known method employs onboard cameras to obtain the relative angle measurements, which only include the relative direction information [ 24 , 25 ]. The angle-only navigation is simple, robust, and well proven in many applications [ 30 ].…”

Section: Introductionmentioning

confidence: 99%

Angle-Only Cooperative Orbit Determination Considering Attitude Uncertainty

Shi

Wang²,

Wang³

et al. 2023

Sensors

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In this paper, a novel concept for cooperative orbit determination (OD) using inter-spacecraft angle-only measurements is proposed. Different from the conventional cooperative OD that only estimates orbit states, the attitude of the observer spacecraft is considered by incorporating the attitude into the estimated vector. The observability of a two-spacecraft system is analyzed based on the observability matrix. Observability analysis reveals that inter-spacecraft angle-only measurements are inadequate to estimate both the attitude and the orbit states in two-body dynamics. The observability of the two-spacecraft system can be improved by considering high-order gravitational perturbation or executing an attitude maneuver on the observer spacecraft. This is the first time that we present the observability analysis and orbit estimation results for a two-spacecraft system considering attitude uncertainty for the observer. Finally, simulation results demonstrate the effectiveness of the proposed method. The results in this paper can be potentially useful for autonomous managements of a spacecraft constellation and formation.

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“…Multi-satellite absolute navigation based on inter-satellite measurements has also been studied by several researchers. Yunpeng Hu et al [ 12 ] proposed a novel solution for autonomous orbit determination for three spacecraft with inertial angles-only measurements, and analyzed the observability. Wei Kang et al [ 13 ] developed the observability theory and estimation algorithms for multi-satellite systems.…”

Section: Introductionmentioning

confidence: 99%

Multi-Satellite Relative Navigation Scheme for Microsatellites Using Inter-Satellite Radio Frequency Measurements

Jin

Chen

et al. 2021

Sensors

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The inter-satellite relative navigation method—based on radio frequency (RF) range and angle measurements—offers good autonomy and high precision, and has been successfully applied to two-satellite formation missions. However, two main challenges occur when this method is applied to multi-microsatellite formations: (i) the implementation difficulty of the inter-satellite RF angle measurement increases significantly as the number of satellites increases; and (ii) there is no high-precision, scalable RF measurement scheme or corresponding multi-satellite relative navigation algorithm that supports multi-satellite formations. Thus, a novel multi-satellite relative navigation scheme based on inter-satellite RF range and angle measurements is proposed. The measurement layer requires only a small number of chief satellites, and a novel distributed multi-satellite range measurement scheme is adopted to meet the scalability requirement. An inter-satellite relative navigation algorithm for multi-satellite formations is also proposed. This algorithm achieves high-precision relative navigation by fusing the algorithm and measurement layers. Simulation results show that the proposed scheme requires only three chief satellites to perform inter-satellite angle measurements. Moreover, with the typical inter-satellite measurement accuracy and an inter-satellite distance of around 1 km, the proposed scheme achieves a multi-satellite relative navigation accuracy of ~30 cm, which is about the same as the relative navigation accuracy of two-satellite formations. Furthermore, decreasing the number of chief satellites only slightly degrades accuracy, thereby significantly reducing the implementation difficulty of multi-satellite RF angle measurements.

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Three-spacecraft autonomous orbit determination and observability analysis with inertial angles-only measurements

Cited by 26 publications

References 25 publications

Angle-Only Target Tracking Method for Optical Imaging Micro-/Nanosatellite Based on APSO-SSUKF

Angle-Only Target Tracking Method for Optical Imaging Micro-/Nanosatellite Based on APSO-SSUKF

Angle-Only Cooperative Orbit Determination Considering Attitude Uncertainty

Multi-Satellite Relative Navigation Scheme for Microsatellites Using Inter-Satellite Radio Frequency Measurements

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