Optical/radio/pulsars integrated navigation for Mars orbiter

Gu, Long; Jiang, Xiuqiang; Li, Shuang; Li, Wendan

doi:10.1016/j.asr.2018.09.005

Cited by 15 publications

(9 citation statements)

References 21 publications

Supporting

Mentioning

Contrasting

Unclassified

Order By: Relevance

“…with I the inertia matrix, u the angular momentum of the reaction wheel and T the external torques imposed on the spacecraft, including the aerodynamic drag, geopotential gradient, equivalent magnetic disturbance torque from spaceborne currents, etc. Abdelrahman et al used (1) as the observation model for simultaneous attitude and orbit determination by setting an augmented dynamics extended Kalman filter (ADEKF) with a state vector incorporating angular rate, quaternion, position, velocity and drag coefficient. 7) It has been proven to be efficient in real missions due to the fact that at least two vector measurements guarantee the observability of the full attitude of R b NED .…”

Section: Time-differential Geomagnetic Modelmentioning

confidence: 99%

“…It has been studied recently that multiple sources can be employed to determine an orbit, including visual information, temperature variation and laser scanning measurements. [1][2][3] In fact, in view of the universality in scientific research and the low cost and light weight attained in the study of nano-satellites, most spacecraft now carry a magnetometer. 4) Therefore, the geomagnetic measurements can be applied to almost any spacecraft as part of an autonomous orbit determination sub-system.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Hybrid Geomagnetic Attitude and Orbit Estimation Using Time-Differential Feedback

Zhang

Liu

2021

Trans. Japan Soc. Aero. S Sci.

View full text Add to dashboard Cite

This paper introduces a novel filter for hybrid attitude and orbit estimation of spacecraft using geomagnetic measurements and their time-differential information. Geomagnetic measurements can be used to simultaneously estimate attitude and orbit of spacecrafts. In practice, the attitude estimation from a single magnetometer is achieved by fusing the magnetometer readings and their time derivatives together. The orbit can also be estimated using the relationship between the geomagnetic model and spacecraft coordinates in the Earth geodetic frame. However, the magnetic time derivatives have not been utilized in estimating the orbit elements. According to the mathematical structures of the geomagnetic models, the time-differential feedback can effectively enhance estimation of the velocity and can therefore provide better performance for the position loop. This paper first introduces direct feedback and formulates a new filter with better characteristics. The simulation study of a medium Earth orbit (MEO) Nadir-pointing satellite mission shows that the proposed filter achieves faster convergence and lower estimation errors.

show abstract

Section: Time-differential Geomagnetic Modelmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Hybrid Geomagnetic Attitude and Orbit Estimation Using Time-Differential Feedback

Zhang

Liu

2021

Trans. Japan Soc. Aero. S Sci.

View full text Add to dashboard Cite

show abstract

“…Ma等人 [12,13] 提出了基于光学相机、脉冲星测量和星间无线电测量的组合导航方法, 此方法采用集中式融合滤波策略提高了探测器巡航段的自主导航精度. Gu等人 [14,15] 进一步采用可观测性分析的方法对比研究了在火星探测巡航段末端不同组合导航方案的导航效果. Wang等人 [16] 针对火星探测器接近段采用基于脉冲星和火星环绕探测器相对测量的方法, 实现了对探测器的自主导航.…”

Section: 另外基于探测器间无线电测量和惯性导航的方法是unclassified

Integrated navigation for the approach phase of Mars probe

Li¹,

Yan²,

Jiang³

et al. 2020

Sci. Sin.-Tech.

View full text Add to dashboard Cite

“…Its key techniques include the computer-based feature extraction, the information fusion, and the time synchronization [42]. The integrated navigation can make up the disadvantage of the sole navigation method, realize the seamless navigation, and achieve the information redundancy designing of the navigation system [43]. Its system reliability and the navigation accuracy can be improved a lot.…”

Section: The Integrated Navigationmentioning

confidence: 99%

Autonomous Navigation for Mars Exploration

Liu¹

2020

Mars Exploration - A Step Forward

View full text Add to dashboard Cite

The autonomous navigation technology uses the multiple sensors to percept and estimate the spatial locations of the aerospace prober or the Mars rover and to guide their motions in the orbit or the Mars surface. In this chapter, the autonomous navigation methods for the Mars exploration are reviewed. First, the current development status of the autonomous navigation technology is summarized. The popular autonomous navigation methods, such as the inertial navigation, the celestial navigation, the visual navigation, and the integrated navigation, are introduced. Second, the application of the autonomous navigation technology for the Mars exploration is presented. The corresponding issues in the Entry Descent and Landing (EDL) phase and the Mars surface roving phase are mainly discussed. Third, some challenges and development trends of the autonomous navigation technology are also addressed.

show abstract

Optical/radio/pulsars integrated navigation for Mars orbiter

Cited by 15 publications

References 21 publications

Hybrid Geomagnetic Attitude and Orbit Estimation Using Time-Differential Feedback

Hybrid Geomagnetic Attitude and Orbit Estimation Using Time-Differential Feedback

Integrated navigation for the approach phase of Mars probe

Autonomous Navigation for Mars Exploration

Contact Info

Product

Resources

About