Absolute navigation for Mars final approach using relative measurements of X-ray pulsars and Mars orbiter

Wang, Shuo; Cui, Pingyuan; Gao, Ai; Yu, Zhengshi; Cao, Menglong

doi:10.1016/j.actaastro.2017.05.017

Cited by 23 publications

(7 citation statements)

References 17 publications

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“…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. 王密等人 [17] 针对火星探测巡航段和接近段, 分别就光学自主导航进行了讨论.…”

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.

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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.

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“…High precision is a key requirement for autonomous navigation in deep space exploration, especially for the phase during which the spacecraft is approaching the target planet or asteroid [3], [15]. If the navigation accuracy does not meet expectations, the orbit determination error will affect the the orbit control system, which could lead to inaccurate orbit maneuver.…”

Section: China Has Established a Mars Exploration Project And Plansmentioning

confidence: 99%

Geometric Coplanar Constraints-Aided Autonomous Celestial Navigation for Spacecraft in Deep Space Exploration

Ning

Chen

et al. 2019

IEEE Access

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Autonomous celestial navigation has been exploited for orbit determination of deep space exploration. Geometric constraints in celestial measurement are the inherent attributes in actual comprehensive autonomous celestial navigation physical systems; they are usually neglected in autonomous navigation systems which causes a loss of information in measurement. For the purpose of high-precision autonomous celestial navigation, the geometric constraints should be utilized as fully as possible. This paper proposes a geometric coplanar constraint for the mutually dependent celestial measurement (line of sight or vectors), and the geometric coplanar constraint model is established. The sequence quadratic program (SQP) algorithm based on the geometric coplanar constraint is put forward to eliminate the dependence of multiple celestial measurements, and suppress the noises in celestial measurement geometrically. Taking both geometry coplanar constraints of celestial measurement and the nonlinear characteristics of system models into account, cubature Kalman filter with measurement optimization is proposed for decreasing the random noise in measurements geometrically and statistically. Simulations demonstrate that the proposed geometric coplanar constraints-aided autonomous celestial navigation method can effectively eliminate the measurement noise geometrically and statistically, and achieve high-precision performance.

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“…Spacecraft cooperation, taking the advantage of inter-satellite measurements, has been widely used to aid navigation performance [1][2][3][4] . Usually, cooperative navigation relies on a main satellite which processes all measurements collected by other spacecraft and estimates the states of all spacecraft [5][6][7] .…”

Section: Introductionmentioning

confidence: 99%

“…Although the accuracy is improved, the iteration process increases the total calculation of the navigation system, which in turn contradicts the original purpose of a decentralized system. 3 Systematic contributions to the decentralization of the navigation system have been made from the view of estimation algorithms, but fail to construct a fully decentralized navigation system, in which each spacecraft operates a navigation subsystem totally independent from other spacecraft.…”

Section: Introductionmentioning

confidence: 99%

Fully Decentralized Cooperative Navigation for Spacecraft Constellations

Qin

Macdonald

Dong

2021

IEEE Trans. Aerosp. Electron. Syst.

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This paper proposes a method to decentralize the navigation burden, and improve the fault tolerance for a spacecraft constellation. The constellation body reference system is introduced, which is the perifocal frame of one satellite in the constellation. The structure of the proposed navigation method is constructed to enable each spacecraft to estimate its own orbit in this body reference system. This step is essentially the relative orbit determination based on inter-satellite range measurements. Thereafter, the approach to transfer an orbit from the constellation body reference system to inertial reference system is developed. The essential requirements on absolute

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Absolute navigation for Mars final approach using relative measurements of X-ray pulsars and Mars orbiter

Cited by 23 publications

References 17 publications

Integrated navigation for the approach phase of Mars probe

Integrated navigation for the approach phase of Mars probe

Geometric Coplanar Constraints-Aided Autonomous Celestial Navigation for Spacecraft in Deep Space Exploration

Fully Decentralized Cooperative Navigation for Spacecraft Constellations

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