Advanced GNC Solutions for Rendezvous in Earth and Planetary Exploration Scenarios

Paper number

IAC-08.A3.I.15

Author

Mr. Luigi Strippoli, GMV S.A., Spain

Coauthor

Mr. Pablo Colmenarejo, GMV S.A., Spain

Coauthor

Mr. David Modrego, GMV S.A., Spain

Coauthor

Mr. Thomas Vincent Peters, GMV S.A., Spain

Coauthor

Mrs. Catherine Le Peuvédic, Thales Alenia Space France, France

Coauthor

Mr. Andrea Guiotto, ThalesAlenia Space Italia S.p.A., Italy

Coauthor

Mr. Sohrab Salehi, European Space Agency (ESA), The Netherlands

Year

2008

Abstract

Rendezvous scenarios present some critical technological issues exacerbated in space exploration scenarios (autonomy, safety and robustness are three of the most crucial aspects). Between the critical issues, the GNC aspects are currently being addressed in the HARVD (High Integrity Autonomous RVD Control system) activity for ESA. HARVD provides GNC related technology support leading to, among others, the actual Mars Sample Return mission and includes GNC, AMM (Autonomous Mission Management) and FDIR design, SW prototyping and validation.

This paper focuses in the GNC solutions adopted in the frame of the HARVD test benching and shows how these solutions are suitable to accomplish autonomy, safety and robustness requirements in a generic rendezvous scenario. 

To focus necessities and requirements at GNC system level, the rendezvous mission has been conceptually split in three phases (Long Range, Intermediate Range and Short Range). For any of these phases the corresponding attitude guidance, translational guidance, navigation and control operational modes have been identified, together with the conditions leading to the triggering of the different modes. Any mission phase has been then exhaustively analysed to identify and figure out trade-offs at GNC level. The paper will detail the rendezvous scenario, which starts at long range with the computation of the attitude manoeuvres needed to acquire the target with the narrow angle camera and finishes with the forced motion leading to the capture/docking. 

A particular attention has been dedicated to the sensors selection and navigation trade-offs, and to find the best options about the orbital manoeuvres needed to approach the target, manoeuvres that shall ensure a high level of passive safety in order to minimise the risks of collision in case of control loss. The last forced motion phase has been especially studied to provide the required robustness at control and guidance level and to determine quantities as the approach corridor dimensions or the velocity profile, with the objective of maximising the passive safety and minimising the propellant consumption during this critical phase. Items like the capture basket blockage on the relative navigation sensors, causing the necessity of performing a blind capture (last meters free drift phase), have been also exhaustively assessed and a solution has been proposed. A specific assessment of the possible contingency situations caused by failures in the different subsystems has been made and constantly taken into account during the architectural and detailed design, with strong influence over GNC, FDIR and AMM functions.

Abstract document

IAC-08.A3.I.15.pdf

Manuscript document

IAC-08.A3.I.15.pdf (🔒 authorized access only).

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