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Power budget analysis for a LEO polar orbiting nano-satellite
Abstract
In April 2014, a nano-satellite project was initiated at the University of Sidi Mohamed Ben Abdellah, Fez, Morocco in order to give graduate students the rare opportunity to experience all the challenging aspects associated with satellite design, manufacture, launch and operation. The nano-satellite follows the design concept of a 1U CubeSat, which has the shape of a cube of 10cm3edge, of 1.33kg mass and which consumes a power of 1W. The initial orbital parameters of the nano-satellite were set to a circular sun-synchronous Low Earth Orbit (LEO) with an inclination of 90°. The operation time was set to two years. To ensure a successful flight, it is necessary, within the scope of the project, to establish an adequate power budget to ensure that the consumed power on board does not exceed the produced power. In this work we analyze deeply the available energy required per single orbit, and summarize the estimated produced and consumed power for several operation modes of the nanosatellite in the execution of its mission.
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“According to [6], the power consumption is calculated in terms of energy for each part of the orbit, daylight, and eclipse.”
From A Method for Validating CubeSat Satellite EPS Through Power Budget Analysis Aligned With Mission Requirements (2023) · cites this paper as [6]
In the citing paper
“Generally, 1U, 2U, and 3U CubeSats maximum power budgets range from 1 W to 2.5 W, 2 W to 5 W, and 7 W to 20 W [2], [6], [7], [8], [10], [11], [12].”
From A Method for Validating CubeSat Satellite EPS Through Power Budget Analysis Aligned With Mission Requirements (2023) · cites this paper as [6]
Citations
Cites
Design and sizing of electrical power source for a nanosatellite using photovoltaic cells
Dahbi, S., Aziz, A., Zouggar, S., Benazzi, N., Zahboune, H., & Elhafyani, M. L. (2015) · International Renewable and Sustainable Energy Conference (IRSEC) · doi:10.1109/irsec.2015.7455059 · Cited by 14
Self-citation
Research works printed but not linked: 7
- chariet, 2014, Ingénierie Système sur le Nanosatellite IGOsat, Phase A, University Paris-Diderot, 37
- despont, 2006, S3-A-SET-1-0-System_Engineering Space center Lausanne Switzerland, 17
- 0, Azur Space Solar Power GmbH 30% Triple Junction GaAs Solar Cell
- beukelaers, 2009, From mission analysis to space flight simulation of the OUFTI-1 nano-satellite, 20
- ahmed, 2015, Document des Exigences Système - version 1 0 Fès, 10
- thirion, 2009, Design and Implementation of the Electrical Power System of student nanosatellite oufti-1, 106
- mehrparvar, 2014, Cube Sat Design Specification 13 rev California Polytechnic state university
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Metadata
- Authors
- Dahbi, S., Aziz, A., Zouggar, S., Hafyani, M. E., Morocco, O., Hanafi, A., Karim, M., Latachi, I., & Rachidi, T.
- Affiliations
- Al Akhawayn University (MA)
- Venue
- 2017 International Conference on Advanced Technologies for Signal and Image Processing (ATSIP)
- Publisher
- IEEE
- Published
- 2017-05
- Pages
- 1-6
- OpenAlex
- W2765901493
- Cited by
- 21
- References
- 1
- Citations by year
- 2026: 1 · 2025: 5 · 2024: 1 · 2023: 6 · 2022: 3 · 2021: 5
- FWCI
- 0.00
- Type
- conference paper
- Language
- en
- Open access
- closed
- Locations
- International Conference on Advanced Technologies for Signal and Image Processing (publishedVersion)
- Topics
- Physical Sciences › Engineering › Aerospace Engineering › Spacecraft Design and Technology
- Physical Sciences › Engineering › Aerospace Engineering › Space Satellite Systems and Control
- Physical Sciences › Engineering › Aerospace Engineering › Spacecraft Dynamics and Control
- Keywords
- power budget analysis, CubeSat, nanosatellites, low Earth orbit, polar orbit, sun-synchronous orbit, solar energy, power consumption, satellite mission design
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