Conceptual design analysis for a two-stage-to-orbit semi-reusable launch system for small satellites

Christie Maddock, Federico Toso, Michael West, Joanne West, Kostantinos Kontis, Sriram Rengarajan, David Evans, Andy Milne, Stuart McIntyre

Research output: Chapter in Book/Report/Conference proceedingConference contribution book

Abstract

This paper presents the conceptual design and performance analysis of a partially reusable space launch vehicle for small payloads. The system uses a multi-stage vehicle with rocket engines, with a reusable first stage capable of glided or powered flight, and expendable upper stage(s) to inject 500 kg payload in different low Earth orbits. The space access vehicle is designed to be air-launched from a modified aircraft carrier. The aim of the system design is to develop a commercially viable launch system for near-term operation, thus emphasis is placed on the efficient use of high TRL technologies. The vehicle design are analysed using a multi-disciplinary design optimisation approach to evaluate the performance, operational capabilities and design trade-offs. Results from two trade-offs studies are shown, evaluating the choice wing area and thus aerodynamic characteristics, and the choice of stage masses and engines selection on the mission performance.
LanguageEnglish
Title of host publication68th Proceedings of the International Astronautical Congress
Place of PublicationAdelaide, South Australia
Number of pages14
Publication statusPublished - 25 Sep 2017
EventInternational Astronautical Congress - Adelaide, Australia
Duration: 25 Sep 201729 Sep 2017
Conference number: 68
http://www.iafastro.org/events/iac/iac-2017/

Conference

ConferenceInternational Astronautical Congress
Abbreviated titleIAC
CountryAustralia
CityAdelaide
Period25/09/1729/09/17
Internet address

Fingerprint

Conceptual design
Orbits
Satellites
Aircraft carriers
Launch vehicles
Rocket engines
Aerodynamics
Earth (planet)
Systems analysis
Engines
Air

Keywords

  • space access
  • trajectory optimisation
  • space transportation

Cite this

Maddock, C., Toso, F., West, M., West, J., Kontis, K., Rengarajan, S., ... McIntyre, S. (2017). Conceptual design analysis for a two-stage-to-orbit semi-reusable launch system for small satellites. In 68th Proceedings of the International Astronautical Congress [IAC-17-D2.7.12] Adelaide, South Australia.
Maddock, Christie ; Toso, Federico ; West, Michael ; West, Joanne ; Kontis, Kostantinos ; Rengarajan, Sriram ; Evans, David ; Milne, Andy ; McIntyre, Stuart. / Conceptual design analysis for a two-stage-to-orbit semi-reusable launch system for small satellites. 68th Proceedings of the International Astronautical Congress. Adelaide, South Australia, 2017.
@inproceedings{714dcde88fd947d4a8ddb50b4093e24a,
title = "Conceptual design analysis for a two-stage-to-orbit semi-reusable launch system for small satellites",
abstract = "This paper presents the conceptual design and performance analysis of a partially reusable space launch vehicle for small payloads. The system uses a multi-stage vehicle with rocket engines, with a reusable first stage capable of glided or powered flight, and expendable upper stage(s) to inject 500 kg payload in different low Earth orbits. The space access vehicle is designed to be air-launched from a modified aircraft carrier. The aim of the system design is to develop a commercially viable launch system for near-term operation, thus emphasis is placed on the efficient use of high TRL technologies. The vehicle design are analysed using a multi-disciplinary design optimisation approach to evaluate the performance, operational capabilities and design trade-offs. Results from two trade-offs studies are shown, evaluating the choice wing area and thus aerodynamic characteristics, and the choice of stage masses and engines selection on the mission performance.",
keywords = "space access, trajectory optimisation, space transportation",
author = "Christie Maddock and Federico Toso and Michael West and Joanne West and Kostantinos Kontis and Sriram Rengarajan and David Evans and Andy Milne and Stuart McIntyre",
note = "The paper was originally presented at the 68th International Astronautical Congress, 25-29 September 2017, Adelaide – Australia – www.iafastro.org",
year = "2017",
month = "9",
day = "25",
language = "English",
booktitle = "68th Proceedings of the International Astronautical Congress",

}

Maddock, C, Toso, F, West, M, West, J, Kontis, K, Rengarajan, S, Evans, D, Milne, A & McIntyre, S 2017, Conceptual design analysis for a two-stage-to-orbit semi-reusable launch system for small satellites. in 68th Proceedings of the International Astronautical Congress., IAC-17-D2.7.12, Adelaide, South Australia, International Astronautical Congress, Adelaide, Australia, 25/09/17.

Conceptual design analysis for a two-stage-to-orbit semi-reusable launch system for small satellites. / Maddock, Christie; Toso, Federico; West, Michael; West, Joanne; Kontis, Kostantinos; Rengarajan, Sriram; Evans, David; Milne, Andy; McIntyre, Stuart.

68th Proceedings of the International Astronautical Congress. Adelaide, South Australia, 2017. IAC-17-D2.7.12.

Research output: Chapter in Book/Report/Conference proceedingConference contribution book

TY - GEN

T1 - Conceptual design analysis for a two-stage-to-orbit semi-reusable launch system for small satellites

AU - Maddock, Christie

AU - Toso, Federico

AU - West, Michael

AU - West, Joanne

AU - Kontis, Kostantinos

AU - Rengarajan, Sriram

AU - Evans, David

AU - Milne, Andy

AU - McIntyre, Stuart

N1 - The paper was originally presented at the 68th International Astronautical Congress, 25-29 September 2017, Adelaide – Australia – www.iafastro.org

PY - 2017/9/25

Y1 - 2017/9/25

N2 - This paper presents the conceptual design and performance analysis of a partially reusable space launch vehicle for small payloads. The system uses a multi-stage vehicle with rocket engines, with a reusable first stage capable of glided or powered flight, and expendable upper stage(s) to inject 500 kg payload in different low Earth orbits. The space access vehicle is designed to be air-launched from a modified aircraft carrier. The aim of the system design is to develop a commercially viable launch system for near-term operation, thus emphasis is placed on the efficient use of high TRL technologies. The vehicle design are analysed using a multi-disciplinary design optimisation approach to evaluate the performance, operational capabilities and design trade-offs. Results from two trade-offs studies are shown, evaluating the choice wing area and thus aerodynamic characteristics, and the choice of stage masses and engines selection on the mission performance.

AB - This paper presents the conceptual design and performance analysis of a partially reusable space launch vehicle for small payloads. The system uses a multi-stage vehicle with rocket engines, with a reusable first stage capable of glided or powered flight, and expendable upper stage(s) to inject 500 kg payload in different low Earth orbits. The space access vehicle is designed to be air-launched from a modified aircraft carrier. The aim of the system design is to develop a commercially viable launch system for near-term operation, thus emphasis is placed on the efficient use of high TRL technologies. The vehicle design are analysed using a multi-disciplinary design optimisation approach to evaluate the performance, operational capabilities and design trade-offs. Results from two trade-offs studies are shown, evaluating the choice wing area and thus aerodynamic characteristics, and the choice of stage masses and engines selection on the mission performance.

KW - space access

KW - trajectory optimisation

KW - space transportation

UR - https://iafastro.directory/iac/archive/browse/IAC-17/D2/7/41497/

M3 - Conference contribution book

BT - 68th Proceedings of the International Astronautical Congress

CY - Adelaide, South Australia

ER -

Maddock C, Toso F, West M, West J, Kontis K, Rengarajan S et al. Conceptual design analysis for a two-stage-to-orbit semi-reusable launch system for small satellites. In 68th Proceedings of the International Astronautical Congress. Adelaide, South Australia. 2017. IAC-17-D2.7.12