Through-life modelling of nano-satellite power system dynamics

Research output: Contribution to conferencePaper

1 Citation (Scopus)
83 Downloads (Pure)

Abstract

This paper presents a multi-fidelity approach to finding optimal, mission-specific power system configurations for CubeSats. The methodology begins with propagation of the orbit elements over the mission lifetime, via a continuous-time model, accounting for orbital perturbations (drag, solar radiation and non-spherical geo-potential). Analytical sizing of the power system is then achieved at discrete long-term intervals, to account for the effects of variations in environmental conditions over the mission life. This sizing is based on worst case power demand and provides inputs to a numerical assessment of the in-flight energy collection for each potential solar array deployment configuration. Finally, two objective functions (minimum deviation about the orbit average power and maximum average power over the entire mission) are satisfied to identify the configurations most suitable for the specific mission requirement. Most Nano-satellites are designed with relatively simple, static-models only and tend to be over-engineered as a result, often leading to a power-limited system. The approach described here aims to reduce the uncertainty in energy collection during flight and provide a robust approach to finding the optimal solution for a given set of mission requirements.
Original languageEnglish
PagesArticle IAC-13-C3.4.4
Number of pages10
Publication statusPublished - 23 Sep 2013
Event64th International Astronautical Congress 2013 - Beijing, China
Duration: 23 Sep 201327 Sep 2013

Conference

Conference64th International Astronautical Congress 2013
CountryChina
CityBeijing
Period23/09/1327/09/13

Fingerprint

System Dynamics
Power System
Dynamical systems
Orbits
Satellites
Configuration
Solar radiation
Orbit
Modeling
Drag
Continuous-time Model
Solar Radiation
Requirements
Energy
Fidelity
Lifetime
Deviation
Objective function
Optimal Solution
Entire

Keywords

  • CubeSat mission
  • power system control
  • nano-satellites
  • modelling and assessment

Cite this

Lowe, C. J., Macdonald, M., & Greenland, S. (2013). Through-life modelling of nano-satellite power system dynamics. Article IAC-13-C3.4.4. Paper presented at 64th International Astronautical Congress 2013, Beijing, China.
Lowe, Christopher John ; Macdonald, Malcolm ; Greenland, Stephen. / Through-life modelling of nano-satellite power system dynamics. Paper presented at 64th International Astronautical Congress 2013, Beijing, China.10 p.
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Lowe, CJ, Macdonald, M & Greenland, S 2013, 'Through-life modelling of nano-satellite power system dynamics', Paper presented at 64th International Astronautical Congress 2013, Beijing, China, 23/09/13 - 27/09/13 pp. Article IAC-13-C3.4.4.

Through-life modelling of nano-satellite power system dynamics. / Lowe, Christopher John; Macdonald, Malcolm; Greenland, Stephen.

2013. Article IAC-13-C3.4.4 Paper presented at 64th International Astronautical Congress 2013, Beijing, China.

Research output: Contribution to conferencePaper

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Lowe CJ, Macdonald M, Greenland S. Through-life modelling of nano-satellite power system dynamics. 2013. Paper presented at 64th International Astronautical Congress 2013, Beijing, China.