Multi-disciplinary optimisation framework for dual-mode launch vehicle concepts

Abstract

Increasing demand for small satellite launch capability provides scope for the development of cost-efficient innovative payload delivery services. The advantages of air-launch capability are well-documented through the success of the Pegasus launch vehicle, but vertical ground-based takeoff is still the standard approach. This project details a transdisciplinary approach to designing a novel dualmode launch vehicle with air and ground launch capability, for small satellites. The vehicle's mission is determined to achieve a payload capacity of 50kg to a 700km sun-synchronous orbit. Alongside the vehicle design, potential carrier aircraft are assessed, and the interface between the two evaluated for feasibility. The proposed air-launch vehicle is a 3-stage HTPB solid rocket weighing just over 2.5t, with two 775kg strap-on boosters for ground-launch. Both the air-launch and ground-launch solutions are verified with the launch optimiser program ASTOS. Future subsystem studies are proposed for further refinement.