Vega: the European Initiative for Launching Small Satellites

Abstract

Vega is a small launcher under development by the European Space Agency (ESA). Its size and performance have been tailored to a design reference mission corresponding to the capability to launch a satellite of 1500 kg from the European Spaceport in Kourou (French Guyana) into a circular polar orbit at 700 km altitude. The possibility of other types of missions, including double launches, are included.

The development of Vega is part of an overall European launchers strategy devised during the year 2000, aimed at enhancing the European independent access to space by new launchers complementary to the Ariane family. In this perspective, Vega represents the smaller element of a possible family built up on the basis of common technology developments and components. During the last two and a half years, when the definition phase was carried out, several iterations have been performed, in particular in the selection of the first stage. The parameters playing a key role in the trade-off process were the overall development costs, the potential savings in the recurrent production costs, the increase of performance to adapt to the evolving market projections and the investment in new technology offering positive spin-offs in other ESA programmes.

The baseline configuration includes three solid-propulsion stages and an upper module with liquid propulsion for orbital manoevre and control. The first stage, called P80, features a 3 m diameter and carries about 80 tonnes of propellant accommodated in a new-technology filament-wound case. This stage adopts new technology solutions for thermal protection, for the nozzle and its actuators, as well as in the composition of the propellant grain. Due to its innovative content, this stage requires a longer development schedule, which drives the overall Vega schedule. The second stage makes use of the Zefiro motor, in a version carrying 23 tonnes of propellant: this motor is in an advanced stage of development with three successful full-scale firing tests. The third stage is a shorter and lighter (9 tonnes) version of the Zefiro motor.

The upper module, called AVUM for “Attitude and Vernier Upper Module”, is composed of two separate elements to accommodate the liquid bi-propellant system for primary manoevres and the avionics modules with GNC, power supply, telemetry and safeguards.