Nonlinear Dynamic Inversion-Based Guidance and Control for a Pinpoint Mars Entry

Hormigo, Tiago; Araújo, J. C. A. de; Câmara, Francisco

doi:10.2514/6.2008-6817

Cited by 8 publications

(2 citation statements)

References 1 publication

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“…The first guided entry on Mars will be attempted by the NASA Mars Science Laboratory (MSL) 6 , which was launched on November 2011, and is planned to reach Mars in the early August 2012. Several techniques 7,8,9,10,11,12,13,14,15,16,17,18,19 have been proposed for improving the performance of the guided entry control. According to Kluever 7 , the approaches can be broadly separated into two methodologies: 1) reference-path tracking and 2) path-planning algorithms.…”

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confidence: 99%

Model-based guidance and control for atmospheric guided entry

Canuto

Ospina

Buonocore

2012

AIAA Guidance, Navigation, and Control Conference

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This paper presents a solution of the translational control for a biconic atmospheric entry capsule using the bank angle as a command. The control algorithm is separated into path planning and reference-path tracking. The path-planning algorithm computes the entry trajectory from the navigated state at the Entry Interface Point until the desired Parachute Deployment Point. The algorithm aims to recover the landing site uncertainty caused by Entry Interface Point dispersions. Atmospheric and aerodynamic dispersions are compensated in real-time following the Embedded Model Control methodology in which parametric uncertainty is estimated and rejected as an external disturbance. A hierarchical control structure is designed for facilitating non-linear dynamic inversion of the altitude/density relation and tuning of noise estimators and control laws. Both path planning and reference-path tracking exploit longitudinal and lateral decomposition of the translational dynamics, as well as state equation linearization around a reference trajectory. The main concepts and solutions of the algorithms are presented without formal proofs of convergence, performance and stability. The results of a Monte Carlo simulation campaign conducted on a high fidelity simulator are provided and discussed.

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confidence: 99%

Model-based guidance and control for atmospheric guided entry

Canuto

Ospina

Buonocore

2012

AIAA Guidance, Navigation, and Control Conference

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“…The Mars Science Laboratory (MSL), whose landing ellipse is 25 km x 20 km, was launched in 2011 and landed on Mars in 2012 (Vasavada et al, 2012;Dutta and Braun, 2014). So advanced high-precision autonomous navigation and active aerodynamic lift control are essential and need to be well researched (Kozynchenko, 2011;Fu et al, 2015;Li and Peng, 2011;Hormigo et al, 2008).…”

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confidence: 99%

Multiple Model Adaptive Rank Estimation for Integrated Navigation During Mars Entry

Xiao

Wang

et al. 2016

J. Navigation

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Accurate navigation systems are required for future pinpoint Mars landing missions. A radio ranging augmented Inertial Measurement Unit (IMU) integrated navigation system concept is considered for the Mars entry navigation. The uncertain system parameters associated with the Three Degree-Of-Freedom (3-DOF) dynamic model, and the measurement systematic errors are considered. In order to improve entry navigation accuracy, this paper presents the Multiple Model Adaptive Rank Estimation (MMARE) filter of radio beacons/IMU integrated navigation system.

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Optimal Dynamic Inversion Control for Spacecraft Maneuver-Aided Tracking

Jing

Pan

et al. 2018

Information Fusion and Data Science

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Nonlinear Dynamic Inversion-Based Guidance and Control for a Pinpoint Mars Entry

Cited by 8 publications

References 1 publication

Model-based guidance and control for atmospheric guided entry

Model-based guidance and control for atmospheric guided entry

Multiple Model Adaptive Rank Estimation for Integrated Navigation During Mars Entry

Optimal Dynamic Inversion Control for Spacecraft Maneuver-Aided Tracking

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