Abstract
CubeSats, the class of small standardized satellites, are becoming a viable scientific research platform. At present, a variety of high value Earth Science missions require multiple collecting instruments on separate platforms maintained in precise configurations. A new software tool was created to compute propellant-minimizing maneuvers for multiple CubeSats for use with mission preliminary design. This tool incorporates parallelization of the derivative calculations, and demonstrates speed improvements over previous parallel formulations of small satellite cooperative trajectory design problems.
| Original language | English (US) |
|---|---|
| Pages (from-to) | 1-14 |
| Number of pages | 14 |
| Journal | Acta Astronautica |
| Volume | 130 |
| DOIs | |
| State | Published - Jan 1 2017 |
| Externally published | Yes |
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ASJC Scopus subject areas
- Aerospace Engineering
Cite this
Application of parallel algorithmic differentiation to optimal CubeSat trajectory design. / Ghosh, Alexander; Coverstone, Victoria.
In: Acta Astronautica, Vol. 130, 01.01.2017, p. 1-14.Research output: Contribution to journal › Article
}
TY - JOUR
T1 - Application of parallel algorithmic differentiation to optimal CubeSat trajectory design
AU - Ghosh, Alexander
AU - Coverstone, Victoria
PY - 2017/1/1
Y1 - 2017/1/1
N2 - CubeSats, the class of small standardized satellites, are becoming a viable scientific research platform. At present, a variety of high value Earth Science missions require multiple collecting instruments on separate platforms maintained in precise configurations. A new software tool was created to compute propellant-minimizing maneuvers for multiple CubeSats for use with mission preliminary design. This tool incorporates parallelization of the derivative calculations, and demonstrates speed improvements over previous parallel formulations of small satellite cooperative trajectory design problems.
AB - CubeSats, the class of small standardized satellites, are becoming a viable scientific research platform. At present, a variety of high value Earth Science missions require multiple collecting instruments on separate platforms maintained in precise configurations. A new software tool was created to compute propellant-minimizing maneuvers for multiple CubeSats for use with mission preliminary design. This tool incorporates parallelization of the derivative calculations, and demonstrates speed improvements over previous parallel formulations of small satellite cooperative trajectory design problems.
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UR - http://www.scopus.com/inward/citedby.url?scp=84992021221&partnerID=8YFLogxK
U2 - 10.1016/j.actaastro.2016.08.018
DO - 10.1016/j.actaastro.2016.08.018
M3 - Article
AN - SCOPUS:84992021221
VL - 130
SP - 1
EP - 14
JO - Acta Astronautica
JF - Acta Astronautica
SN - 0094-5765
ER -