Orbit determination for a space-based gravitational wave observatory

Li, Zhuo; Zheng, Jianhua

doi:10.1016/j.actaastro.2021.04.014

Cited by 9 publications

(4 citation statements)

References 16 publications

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“…Each SC follows a heliocentric orbit, forming a massive equilateral triangle with sides spanning approximately three million kilometers. Generally, navigation methods for such formations, which are located in heliocentric orbits, rely on a combination of deep space network (DSN) and other ground observations to estimate the absolute state of the SC [2,3]. However, due to the limitation of the observation arc, neither of these methods can provide continuous coverage for the entire observation period of the formation.…”

Section: Introductionmentioning

confidence: 99%

Autonomous State Estimation and Observability Analysis for the Taiji Formation Using High-Precision Optical Sensors

Wen,

Tang,

Peng

et al. 2023

Sensors

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In certain observation periods of navigation missions for the Taiji formation, ground observation stations are unable to observe the spacecraft, while the state of the spacecraft can be estimated through the utilization of dynamic equations simulated on prior knowledge. However, this method cannot accurately track the spacecraft. In this paper, we focus on appropriately selecting the available onboard measurement to estimate the state of the spacecraft of the Taiji formation. We design two schemes to explore the performance of the state estimation based on the interspacecraft interferometry measurements and the measurements obtained from the Sun sensor and the radial velocity sensor. The observability of the system is numerically analyzed using the singular value decomposition method. Furthermore, we analyze error covariance propagation using the cubature Kalman filter. The results show that using high-precision interspacecraft angle measurement can improve significantly the observability of the system. The absolute position and velocity of the spacecraft can be estimated respectively with an accuracy of about 3.1 km and 0.14 m/s in the first scheme, where the prior information of the precision of the position and velocity is respectively 100 km and 1 m/s. When the measurement from the radial velocity sensor is used in the second scheme, the estimation accuracy of the velocity can be improved about 18 times better than that in the first scheme.

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Section: Introductionmentioning

confidence: 99%

Autonomous State Estimation and Observability Analysis for the Taiji Formation Using High-Precision Optical Sensors

Wen,

Tang,

Peng

et al. 2023

Sensors

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“…Some studies achieved attitude angle estimation with an accuracy of about 0.03 • through an extended Kalman filter [14], but it consumed a lot of computing power. There has also been research into the attitude of high-orbit targets through space-based observation facilities [15] and using a new fiberoptic gyroscope design to improve the zero-bias stability and measurement accuracy [16]. Some research groups adopted the new optical design of a high-precision star camera and high-precision measurement method [17,18] and achieved an angle measurement accuracy of 1.5 × 10 −4• , but the output frequency of high-precision data was limited, generally in the range of 10-20 Hz.…”

Section: Introductionmentioning

confidence: 99%

Prediction Algorithm for Satellite Instantaneous Attitude and Image Pixel Offset Based on Synchronous Clocks

Lingfeng

Dong

2022

Remote Sensing

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To ensure a high signal-to-noise ratio and high image volume, a geostationary orbiting ocean remote-sensing system needs to maintain high platform stability over a long integration time because it is affected by satellite attitude changes. When the observation target is the ocean, it is difficult to extract image features because of the lack of characteristic objects in the target area. In this paper, we attempt to avoid using image data for satellite attitude and image pixel offset estimation. We obtain the satellite attitude by using equipment such as gyroscopes and performing time registration between the satellite attitude and the image data to achieve pixel offset matching between images. According to the law of satellite attitude change, we designed a Kalman-like filter fitting (KLFF) algorithm based on the satellite attitude change model and the Nelder–Mead search principle. The discrete attitude data were time-marked by a synchronization system, and high-precision estimation of the satellite attitude was achieved after fitting with the KLFF algorithm. When the measurement accuracy of the equipment was 1.0 × 10−3°, the average prediction error of the algorithm was 1.09 × 10−3°, 21.58% better than the traditional interpolation prediction result of 1.39 × 10−3°. The peak value of the fitting angle error reached 2.5 × 10−3°. Compared with the interpolation prediction result of 6.2 × 10−3°, the estimated stability of the satellite attitude improved by about 59.68%. After using the linear interpolation method to compensate for the estimated pixel offset, its discrete range was 0.697 pixels. Compared with the 1.476 pixels of the interpolation algorithm, it was 52.8% lower, which improved the noise immunity of the algorithm. Finally, a KLFF algorithm was designed based on the satellite attitude change model by using external measurement data and the synchronous clock as a benchmark. The instantaneous attitude of the satellite was accurately estimated in real time, and the offset matching between the images was realized, which lays the foundation for in-orbit satellite data processing.

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“…The non-contact close-proximity formation satellite, consisting of a PM and an SM separated by the non-contact Lorentz actuator (NCLA), has significant application potential and can provide a satellite platform with ultra-high attitude pointing accuracy and stability for space gravitational wave detection [1,2], next-generation space telescopes [3,4], and other space exploration missions [5,6].…”

Section: Introductionmentioning

confidence: 99%

“…NTI denotes the number of the triggering instants 2. PRCT denotes the percentage reduction in communication times.…”

mentioning

confidence: 99%

Event-Triggered Attitude-Tracking Control for a Cableless Non-Contact Close-Proximity Formation Satellite

Liao

et al. 2022

Aerospace

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The cablelessness of non-contact close-proximity formation satellites can fundamentally avoid the influence of non-contact interface coupling effects and can further enhance the attitude pointing accuracy and stability of the payload module (PM). However, it also brings the problem of limited on-board resources and system latency. In this paper, an event-triggered attitude tracking controller of the support module (SM) that avoids the Zeno phenomenon was proposed. The update time of the control signal was determined by the event-triggering mechanism based on intermediate variables, thus, reducing the communication burden and actuator asynchrony between the two modules. The feasibility and effectiveness of the proposed approach was demonstrated by numerical simulations.

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Orbit determination for a space-based gravitational wave observatory

Cited by 9 publications

References 16 publications

Autonomous State Estimation and Observability Analysis for the Taiji Formation Using High-Precision Optical Sensors

Autonomous State Estimation and Observability Analysis for the Taiji Formation Using High-Precision Optical Sensors

Prediction Algorithm for Satellite Instantaneous Attitude and Image Pixel Offset Based on Synchronous Clocks

Event-Triggered Attitude-Tracking Control for a Cableless Non-Contact Close-Proximity Formation Satellite

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