A configuration for a high energy final stage for a satellite launching vehicle
- Paper ID
IAF-66-008
- author
- company
Hawker Siddeley Ltd.
- country
United Kingdom
- year
1966
- abstract
This paper is derived from the results of work carried out by Hawker Siddeley Dynamics for the European Launcher Development Organisation. The main purpose of the work was to study a design for the final stage for a three stage European launching vehicle, the general configuration of which is indicated in Fig. 1. This vehicle uses Blue Streak as the first stage which could have a take-off thrust of up to 150 tonnes. The total vehicle mass is assumed to be approximately 115 tonnes, giving a take-off acceleration of between 1.2 and 1.3 g.