LAREDO: A Formation Flying and Rendezvous and Docking Simulator Tool for Exploration Missions
- Paper number
IAC-05-A3.P.13
- Author
Mr. David Modrego, GMV S.A., Spain
- Coauthor
Dr. Guillermo Ortega, European Space Agency (ESA)/ESTEC, The Netherlands
- Year
2005
- Abstract
Last years, several exploration missions have been designed and analyzed to perform Rendezvous and Docking maneuvers between two spacecraft not only around in Earth, but also around other solar system central bodies or librations points. Examples of possible scenarios demanding RvD sequences are, for instance, sample return missions from other planets or natural satellites. Despite this clear tendency, a lack of software tools able to support the required analysis was highlighted. LAREDO has been designed and implemented by GMV S.A., Spain, under GSTP contract with ESA/ESTEC with the aim to cover these new necessities from mission analysts. The goal of LAREDO Tool, developed under Matlab/Simulink-based environment, is to be able to reproduce the Rendezvous and Docking sequences applicable to different exploration mission-scenarios. Among those, it is possible to select the following scenarios: Earth, Moon, Mars, Venus, Deimos, Triton, Europa and L1 and L2 libration points for Sun-Mars, Earth-Moon and Sun-Earth-Moon systems. Within the scope of optimizing the launching phase of the second spacecraft involved in the Rendezvous and Docking once it has lifted off from the Earth, Moon or Mars surfaces, a launching optimization module has also been implemented in the tool. The mission analyst may plan and execute a sequence of maneuvers selected among a extensive set of maneuvering skills. The Clohessy Wiltshire equation and the transition matrix are used in the maneuver computation. An automatic Collision Avoidance Maneuver (CAM) is additionally implemented in order to avoid the failure of the mission due to a risk of collision. The simulator propagates considering various orbit perturbations, communications (both with ground stations and between satellites), and provides full analysis of the RvD trajectory. The GNC modules incorporate sensor models for LIDAR, camera and RF devices, and both orbit and attitude guidance and control. This paper presents the simulation results obtained for a Mars Sample Return mission scenario, those including the launch ascent trajectory optimization and the complete RvD with the orbiter. Additionally, launching and RvD missions around other central bodies or librations points will be briefly described in the paper.
- Abstract document