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Orbital transfer vehicle (OTV) system sizing study for manned GEO satellite servicing

Published online by Cambridge University Press:  20 April 2016

B. Chudoba ,
G. Coleman ,
L. Gonzalez ,
E. Haney ,
A. Oza  and
V. Ricketts
B. Chudoba*
Affiliation:
AVD Laboratory, University of Texas at Arlington, Arlington, Texas, US
G. Coleman
Affiliation:
AVD Laboratory, University of Texas at Arlington, Arlington, Texas, US
L. Gonzalez
Affiliation:
AVD Laboratory, University of Texas at Arlington, Arlington, Texas, US
E. Haney
Affiliation:
AVD Laboratory, University of Texas at Arlington, Arlington, Texas, US
A. Oza
Affiliation:
AVD Laboratory, University of Texas at Arlington, Arlington, Texas, US
V. Ricketts
Affiliation:
AVD Laboratory, University of Texas at Arlington, Arlington, Texas, US
*
[email protected]
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Abstract

In an effort to quantify the feasibility of candidate space architectures for astronauts servicing Geosynchronous Earth Orbit (GEO) satellites, a conceptual assessment of architecture-concept and operations-technology combinations has been performed. The focus has been the development of a system with the capability to transfer payload to and from geostationary orbit. Two primary concepts of operations have been selected: (a) Direct insertion/re-entry (Concept of Operations 1 – CONOP 1); (b) Launch to low-earth orbit at Kennedy Space Center inclination angle with an orbital transfer to/from geostationary orbit (Concept of Operations 2 – CONOP 2). The study concludes that a capsule and de-orbit propulsion module system sized for the geostationary satellite servicing mission is feasible for a direct insertion/re-entry concept of operation CONOP 1. Vehicles sized for CONOP 2 show overall total mass savings when utilising the aero-assisted orbital transfer vehicle de-orbit propulsion module options compared to the pure propulsive baseline cases. Overall, the consideration of technical, operational and cost factors determine if either the aero-assisted orbital transfer vehicle concepts or the re-usable/expendable ascent/de-orbit propulsion modules is the preferred option.

Keywords

System forecastingarchitecture planningmanned GEO servicingdesign synthesishypersonic flowsrocket enginesspace
Type
Research Article
Information
The Aeronautical Journal , Volume 120 , Issue 1226 , April 2016 , pp. 573 - 599
Copyright
Copyright © Royal Aeronautical Society 2016 

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