Far Range Automatic Rendezvous and Soft Docking Demonstration Mission without the use of GPS.

Paper number

IAC-06-C1.7.09

Author

Mr. José María Fernández Ibarz, SENER Ingeneria y Sistemas, S.A., Spain

Coauthor

Mr. Amador Lopez, SENER Ingeneria y Sistemas, S.A., Spain

Coauthor

Mr. Peter Rathsman, Swedish Space Corporation, Sweden

Coauthor

Mr. Björn Jakobsson, Swedish Space Corporation, Sweden

Coauthor

Mr. Davy Vrancken, Belgium

Coauthor

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

Coauthor

Mr. Ulrich Thomas, European Space Agency (ESA)/ESTEC, The Netherlands

Year

2006

Abstract

Automatic Rendezvous and docking is a key technology for the operation of International Space Station and for exploration.

Some of these applications such as exploration in Mars ( i.e. Mars Sample Return)  require far field rendezvous without the use of GPS in elliptic orbit. For other applications such as exploration ( Mars or Moon ) or ISS servicing ( docking system for future servicing vehicles, such as Clipper) it is desirable to have Soft Docking technology available. 

In the frame of the development of Europe’s automatic Rendezvous and Docking technology capability, it has been analyzed the feasibility of a low-cost Demonstration Mission whose main goals are technology demonstration and risk mitigation for future applications of automatic rendezvous and docking without the use of absolute or relative GPS (in circular and elliptical orbit) as well as the demonstration of the docking function of the IBDM ( International Berthing and Docking Mechanism).

This Demonstration Mission implies the execution of several far field approach manoeuvres without the use of GPS, in circular and elliptic orbit (in order to demonstrate GNC algorithms), as well as multiple docking and undocking operations in order to demonstrate the docking function of the IBDM itself as well as to generate a complete set of flight data for correlation of docking on-ground simulators and test bench facilities.

In order to achieve a low cost Mission a very short mission duration and extensive re-use of available platform technology ( PROBA and SMART-1) has been considered. The baseline of the mission is thus, a Target ( PROBA) and a Chaser ( SMART-1)  launched jointly into LEO, in a circular orbit, carrying the IBDM and the Radio Frequency Far Field sensor (from Darwin Mission) and LIDAR ( upgraded ATV sensor)

All the relevant technical aspects such as requirement definition,  mission definition ( rendezvous manoeuvres and operations), mission analysis, launcher selection, Target and Chaser definition, rendezvous package definition ( rendezvous GNC algorithms, sensors, actuators definition), IBDM accommodation have been carried out. A simulator has been developed in order to demonstrate the mission feasibility and assess the pointing and position error and fuel budget of the concept. Programmatic aspects such as design and development plan and cost estimation  have also been addressed.

Abstract document

IAC-06-C1.7.09.pdf

Manuscript document

IAC-06-C1.7.09.pdf (🔒 authorized access only).

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