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A semi-analytical guidance algorithm for autonomous landing

A semi-analytical guidance algorithm for autonomous landing
A semi-analytical guidance algorithm for autonomous landing
One of the main challenges posed by the next space systems generation is the high level of autonomy they will require. Hazard Detection and Avoidance is a key technology in this context. An adaptive guidance algorithm for landing that updates the trajectory to the surface by means of an optimal control problem solving is here presented. A semi-analytical approach is proposed. The trajectory is expressed in a polynomial form of minimum order to satisfy a set of boundary constraints derived from initial and final states and attitude requirements. By imposing boundary conditions, a fully determined guidance profile is obtained, function of a restricted set of parameters. The guidance computation is reduced to the determination of these parameters in order to satisfy path constraints and other additional constraints not implicitly satisfied by the polynomial formulation. The algorithm is applied to two different scenarios, a lunar landing and an asteroidal landing, to highlight its general validity. An extensive Monte Carlo test campaign is conducted to verify the versatility of the algorithm in realistic cases, by the introduction of attitude control systems, thrust modulation, and navigation errors. The proposed approach proved to be flexible and accurate, granting a precision of a few meters at touchdown
0273-1177
2719-2738
Lunghi, Paolo
b82f1dc2-133b-4a41-ad45-25cf56eeb026
Lavagna, Michèle
f20bb48e-35e1-4e54-bc43-59c18ba37a14
Armellin, Roberto
61950d5c-3dcf-45f5-b391-7e8c6ffb8e6f
Lunghi, Paolo
b82f1dc2-133b-4a41-ad45-25cf56eeb026
Lavagna, Michèle
f20bb48e-35e1-4e54-bc43-59c18ba37a14
Armellin, Roberto
61950d5c-3dcf-45f5-b391-7e8c6ffb8e6f

Lunghi, Paolo, Lavagna, Michèle and Armellin, Roberto (2015) A semi-analytical guidance algorithm for autonomous landing. Advances in Space Research, 55 (11), 2719-2738. (doi:10.1016/j.asr.2015.02.022).

Record type: Article

Abstract

One of the main challenges posed by the next space systems generation is the high level of autonomy they will require. Hazard Detection and Avoidance is a key technology in this context. An adaptive guidance algorithm for landing that updates the trajectory to the surface by means of an optimal control problem solving is here presented. A semi-analytical approach is proposed. The trajectory is expressed in a polynomial form of minimum order to satisfy a set of boundary constraints derived from initial and final states and attitude requirements. By imposing boundary conditions, a fully determined guidance profile is obtained, function of a restricted set of parameters. The guidance computation is reduced to the determination of these parameters in order to satisfy path constraints and other additional constraints not implicitly satisfied by the polynomial formulation. The algorithm is applied to two different scenarios, a lunar landing and an asteroidal landing, to highlight its general validity. An extensive Monte Carlo test campaign is conducted to verify the versatility of the algorithm in realistic cases, by the introduction of attitude control systems, thrust modulation, and navigation errors. The proposed approach proved to be flexible and accurate, granting a precision of a few meters at touchdown

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Accepted/In Press date: 17 February 2015
Published date: June 2015
Organisations: Astronautics Group

Identifiers

Local EPrints ID: 377352
URI: http://eprints.soton.ac.uk/id/eprint/377352
ISSN: 0273-1177
PURE UUID: 9866a3f4-6360-4e90-a653-20f64f6cef3f

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Date deposited: 29 May 2015 13:05
Last modified: 14 Mar 2024 20:01

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Contributors

Author: Paolo Lunghi
Author: Michèle Lavagna

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