Vehicle and mission design of a future small payload launcher

Christie Alisa Maddock; Federico Toso; Lorenzo Ricciardi; Alessandro Mogavero; Kin Hing Lo; Sriram Rengarajan; Kostantinos Kontis; Andy Milne; Jim Merrifield; David Evans; Michael West; Stuart McIntyre

doi:10.2514/6.2017-2224

Vehicle and mission design of a future small payload launcher

Christie Alisa Maddock, Federico Toso, Lorenzo Ricciardi, Alessandro Mogavero, Kin Hing Lo, Sriram Rengarajan, Kostantinos Kontis, Andy Milne, Jim Merrifield, David Evans, Michael West, Stuart McIntyre

Mechanical And Aerospace Engineering

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution book

6 Citations (Scopus)

417 Downloads (Pure)

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 a 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.

Original language	English
Title of host publication	21st AIAA International Space Planes and Hypersonic Systems and Technologies Conference
Place of Publication	Reston, VA
Number of pages	21
ISBN (Electronic)	9781624104633
DOIs	https://doi.org/10.2514/6.2017-2224
Publication status	Published - 2 Mar 2017
Event	AIAA International Space Planes and Hypersonic Systems and Technology Conference - Xiamen, China Duration: 6 Mar 2017 → 9 Mar 2017 Conference number: 21 https://www.aiaa.org/EventDetail.aspx?id=33740

Publication series

Name	International Space Planes and Hypersonic Systems and Technologies Conferences
Publisher	American Institute of Aeronautics and Astronautics

Conference

Conference	AIAA International Space Planes and Hypersonic Systems and Technology Conference
Abbreviated title	Hypersonics 2017
Country/Territory	China
City	Xiamen
Period	6/03/17 → 9/03/17
Internet address	https://www.aiaa.org/EventDetail.aspx?id=33740

Keywords

launch vehicle system design
spaceplane
payloads
optimisation
small satellite launch
rocket propulsion systems

Access to Document

10.2514/6.2017-2224Licence: Unspecified

Maddock-etal-ISPHSTC-2017-Vehicle-and-mission-design-of-a-future-small-payload-launcherAccepted author manuscript, 4.64 MB

Christie Maddock, PhD, FHEA, MRAeS
- christie.maddockstrath.acuk
- Mechanical And Aerospace Engineering - Senior Lecturer
- Ocean, Air and Space
Person: Academic

NSTP Small Satellite Launcher (FSPL-UK)
Maddock, C. (Principal Investigator) & Minisci, E. (Co-investigator)
UK Space Agency
26/04/16 → 29/11/16
Project: Research

Cite this

Maddock, C. A., Toso, F., Ricciardi, L., Mogavero, A., Lo, K. H., Rengarajan, S., Kontis, K., Milne, A., Merrifield, J., Evans, D., West, M., & McIntyre, S. (2017). Vehicle and mission design of a future small payload launcher. In 21st AIAA International Space Planes and Hypersonic Systems and Technologies Conference Article AIAA 2017-2224 (International Space Planes and Hypersonic Systems and Technologies Conferences).. https://doi.org/10.2514/6.2017-2224

@inproceedings{841d60a59ec7447a81a2f82492ede10d,

title = "Vehicle and mission design of a future small payload launcher",

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 withrocket engines, with a reusable first stage capable of glided or powered flight, and expendable upper stage(s) to inject a 500 kg payload in different low Earth orbits. The spaceaccess 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.",

keywords = "launch vehicle system design, spaceplane, payloads, optimisation, small satellite launch, rocket propulsion systems",

author = "Maddock, {Christie Alisa} and Federico Toso and Lorenzo Ricciardi and Alessandro Mogavero and Lo, {Kin Hing} and Sriram Rengarajan and Kostantinos Kontis and Andy Milne and Jim Merrifield and David Evans and Michael West and Stuart McIntyre",

note = "{\textcopyright}2017 AIAA Maddock, C., Toso, F., Ricciardi, L. A., Mogavero, A., Lo, K. H., Rengarajan, S., ... McIntyre, S. (2017). Vehicle and mission design of a future small payload launcher. In 21st AIAA International Space Planes and Hypersonic Systems and Technologies Conference. [AIAA 2017-2224] (International Space Planes and Hypersonic Systems and Technologies Conferences). Reston, VA: American Institute of Aeronautics and Astronautics Inc, AIAA. DOI: 10.2514/6.2017-2224; AIAA International Space Planes and Hypersonic Systems and Technology Conference, Hypersonics 2017 ; Conference date: 06-03-2017 Through 09-03-2017",

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Maddock, CA, Toso, F, Ricciardi, L, Mogavero, A, Lo, KH, Rengarajan, S, Kontis, K, Milne, A, Merrifield, J, Evans, D, West, M & McIntyre, S 2017, Vehicle and mission design of a future small payload launcher. in 21st AIAA International Space Planes and Hypersonic Systems and Technologies Conference., AIAA 2017-2224, International Space Planes and Hypersonic Systems and Technologies Conferences, Reston, VA, AIAA International Space Planes and Hypersonic Systems and Technology Conference, Xiamen, China, 6/03/17. https://doi.org/10.2514/6.2017-2224

Vehicle and mission design of a future small payload launcher. / Maddock, Christie Alisa; Toso, Federico; Ricciardi, Lorenzo et al.
21st AIAA International Space Planes and Hypersonic Systems and Technologies Conference. Reston, VA, 2017. AIAA 2017-2224 (International Space Planes and Hypersonic Systems and Technologies Conferences).

Research output: Chapter in Book/Report/Conference proceeding › Conference contribution book

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AU - Maddock, Christie Alisa

AU - Toso, Federico

AU - Ricciardi, Lorenzo

AU - Mogavero, Alessandro

AU - Lo, Kin Hing

AU - Rengarajan, Sriram

AU - Kontis, Kostantinos

AU - Milne, Andy

AU - Merrifield, Jim

AU - Evans, David

AU - West, Michael

AU - McIntyre, Stuart

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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 withrocket engines, with a reusable first stage capable of glided or powered flight, and expendable upper stage(s) to inject a 500 kg payload in different low Earth orbits. The spaceaccess 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.

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 withrocket engines, with a reusable first stage capable of glided or powered flight, and expendable upper stage(s) to inject a 500 kg payload in different low Earth orbits. The spaceaccess 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.

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KW - spaceplane

KW - payloads

KW - optimisation

KW - small satellite launch

KW - rocket propulsion systems

U2 - 10.2514/6.2017-2224

DO - 10.2514/6.2017-2224

M3 - Conference contribution book

T3 - International Space Planes and Hypersonic Systems and Technologies Conferences

BT - 21st AIAA International Space Planes and Hypersonic Systems and Technologies Conference

CY - Reston, VA

T2 - AIAA International Space Planes and Hypersonic Systems and Technology Conference

Y2 - 6 March 2017 through 9 March 2017

ER -

Vehicle and mission design of a future small payload launcher

Abstract

Publication series

Conference

Keywords

Access to Document

Fingerprint

Profiles

Christie Maddock, PhD, FHEA, MRAeS

Projects

NSTP Small Satellite Launcher (FSPL-UK)

Cite this