Abstract:
A parameterised generic launch vehicle design is subjected to performance evaluation
using the ORBITER model which is capable of optimising both the design and trajectory
of the vehicle. The launcher initial mass, flight path angle, velocity and altitude
are varied around design points of existing vehicle concepts to investigate the subsequent
effect on performance for payload delivery into a 90km by 200km orbit. The
performance results suggest that SSTO systems are unfeasible, delivering marginal
positive payload performance only when externally accelerated to high speed using a
sled mechanism. The optimal vehicle type from a purely performance perspective is
deemed to be the TSTO vertically launched configuration.
Description:
Paper presented at Dynamics and Control of Systems and Structures in Space (DCSSS), 5th conference, Kings College, Cambridge, July 2002
