Conexpress orbital life extension vehicle (cx-olev) gnc
- Paper number
IAC-06-C1.8.08
- Author
Mr. Juan Manuel del Cura, SENER Ingeneria y Sistemas, S.A., Spain
- Coauthor
Mr. Alberto Sebastian, SENER Ingeneria y Sistemas, S.A., Spain
- Coauthor
Mr. Lorenzo Tarabini, GMV S.A., Spain
- Coauthor
Dr. Guillermo Ortega, European Space Agency (ESA)/ESTEC, The Netherlands
- Coauthor
Mr. Jean-Pascal Lejault, European Space Agency (ESA)/ESTEC, The Netherlands
- Year
2006
- Abstract
Telecommunications satellites typically cost 250 million dollars and they are designed for an average useful on-orbit life of 10-15 years. Once their on-board propellant load is depleted, the satellites are boosted into a disposal orbit and decommissioned, even though their revenue-generating communications relay payloads continue to function. Orbital Recovery Corporation’s ConeXpress-Orbital Life Extension Vehicle (CX-OLEV) is a novel spacecraft that will significantly prolong the operating lifetimes of these valuable telecommunications satellites. The CX-OLEV will operate as an orbital "tugboat," supplying the propulsion, navigation and guidance to keep a telecom satellite in its proper orbital slot for many years. Another application of the ConeXpress-OLEV is the rescue of spacecraft that have been placed in a wrong orbit by their launch vehicles, or which have become stranded in an incorrect orbital location during positioning maneuvers. CX-OLEV will be designed to mate with telecommunications satellites. After launch, it will rendezvous with the client platform. The CX-OLEV will link up using a capture tool that connects to the telecommunication satellite’s apogee kick motor. Apogee kick motors are used by nearly every telecommunications satellite for orbital boost and station-keeping, and they provide an interface point for the CX-OLEV linkup. Four nominal mission phases have been defined: Transfer, RendezVous, Docking and Mated. A very delicate part of the mission is the rendez-vous and docking phase. Once the transfer to the GEO has been completed, CX-OLEV will enter the proximity and docking phase. The following scenario is foreseen:
- CX-OLEV will approach the client in several subphases corresponding different distances ranges.
- At closer distance, the capture tool on a deployable boom will approach the apogee kick motor of the client spacecraft.
- After the contact has been established, the capture tool will achieve fixation of the client and the boom will retract to keep the chaser aligned with the client.
- After docking CX-OLEV will take over the AOCS of the combined spacecraft.
The task of the Guidance Navigation and Control Subsystem (GNC) is to control the spacecraft’s orbit and attitude during all mission phases. The subsystem design is based on proven technology (hardware and software building blocks) for GEO application where possible .A limitation to this consideration is the non availability of OTS systems for Rendez-Vous and Docking. Thus the Rendez-Vous Sensor and Docking Systems will be ad-hoc developed systems. SENER is the overall responsible of the AOCS/GNC subsystem, while GMV is supporting the design of the RendezVous phase.
- Abstract document
- Manuscript document
IAC-06-C1.8.08.pdf (🔒 authorized access only).
To get the manuscript, please contact IAF Secretariat.