Vision-aided inertial navigation for pinpoint planetary landing

Li, Shuang; Cui, Pingyuan; Cui, Hutao

doi:10.1016/j.ast.2007.04.006

Cited by 77 publications

(28 citation statements)

References 8 publications

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“…The accelerometer bias of the LN-200 is 0.3 mg. So, the unknown measurement systematic errors that contain constant bias and drift (Li et al, 2007) are shown in Table 1 for simple simulation in this paper.…”

Section: Inertial Measurement Unitsmentioning

confidence: 99%

Autonomous navigation method based on unbiased minimum-variance estimation during Mars entry

Yang

Xiao

et al. 2015

Advances in Space Research

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Section: Inertial Measurement Unitsmentioning

confidence: 99%

Autonomous navigation method based on unbiased minimum-variance estimation during Mars entry

Yang

Xiao

et al. 2015

Advances in Space Research

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“…Suppose that errors of initial states subject to normal distribution, as so as uncertainties of the aerodynamic parameters [7,18] . The details are shown in Table and Table . Besides, suppose that multi-source disturbance d is step form.…”

Section: A Plant Blockmentioning

confidence: 99%

Disturbance observer based constrained multi-model predictive control for Mars entry trajectory tracking

Yang

2014

Proceedings of 2014 IEEE Chinese Guidance, Navigation and Control Conference

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For future Mars entry missions, a composite entry tracking strategy is studied in this article. For precision entry, the nonlinear entry dynamics, complex uncertainties and multi-source disturbance are considered specially. The composite entry tracking strategy includes constrained multi-model predictive control (CMPC), to optimize tracking performance, as well as disturbance observer based control for active disturbance rejection. Monte Carlo simulations demonstrate the effectiveness of the proposed method under control saturation constraint, multi-source disturbances and uncertainties of initial states and aerodynamic parameters.

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“…The relative position and velocity of spacecraft with respect to the asteroid are described in this coordinate system. [7] : the origin of this frame lies in the spacecraft's mass centre, three body axis of symmetry are defined as three coordinate axes.…”

Section: A Formation Dynamicsmentioning

confidence: 99%

State estimation of spacecraft formation near small asteroid

Hui-xin

Yang

Zhang

2014

Proceedings of 2014 IEEE Chinese Guidance, Navigation and Control Conference

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An autonomous navigation method is investigated to estimate the states of each spacecraft relative to the asteroid. Inter-spacecraft position measurements are then combined with the spacecraft-toasteroid position measurements to improve the navigation accuracy. Two navigation schemes based on different combinations of measurements are constructed to evaluate the improvement in navigation performance. Unscented Kalman Filter is used to estimate the state for each spacecraft with respect to the asteroid. Results show that the navigation performance is significantly improved by adding the inter-spacecraft position measurements.

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Vision-aided inertial navigation for pinpoint planetary landing

Cited by 77 publications

References 8 publications

Autonomous navigation method based on unbiased minimum-variance estimation during Mars entry

Autonomous navigation method based on unbiased minimum-variance estimation during Mars entry

Disturbance observer based constrained multi-model predictive control for Mars entry trajectory tracking

State estimation of spacecraft formation near small asteroid

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