This paper contains an analysis of the design trade-ofs for a semi-reusable two-stage to orbit, rocket- powered launch system for small payloads. The system is to be air-launched of a modifed commercial aircraft with a full reusable, flight capable return vehicle. This allows the system to be operational from any suitable space or airport; a increasingly common aim of new, agile launch concepts for small payloads. The system was modelled with a multidisciplinary design optimisation (MDO) framework using two different optimal control solvers: MODHOC, a multi-objective optimiser that combined an evolutionary- based global optimisation together with a collocation-based optimal control solver; and TROPICO, a single-objective optimiser using a direct multi-shooting approach.
|Number of pages||1|
|Publication status||Published - 24 Oct 2019|
|Event||International Astronautical Congress 2019 - Washington DC, United States|
Duration: 21 Oct 2019 → 25 Oct 2019
|Conference||International Astronautical Congress 2019|
|Abbreviated title||IAC 19|
|Period||21/10/19 → 25/10/19|
- space transportation
- small launchers
- small payloads
- launch systems
Maddock, C., Ricciardi, L. A., Toso, F., & Vasile, M. (2019). Multidisciplinary design analysis of a semi-reusable two-stage-to-orbit small payload launch system. Poster session presented at International Astronautical Congress 2019, Washington DC, United States.