BEESAT: A Pico Satellite for the On Orbit Verification of Micro Wheels

Kayal, Hakan; Baumann, F.; Brieß, K.; Montenegro, Sérgio

doi:10.1109/rast.2007.4284041

Cited by 20 publications

(9 citation statements)

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“…In a 500 -km orbit altitude (see [64], [65]) above Earth's surface, our simulated CubeSat spends roughly 62% of its orbit (59 min) in sunlight during which energy is collected via solar panels, producing about 7 W of power, and stored in a 7.4 V, 4.4 Ah LiOn battery [66], [67]. While it is possible to store energy in the microwheels (see [68], [69]), we assume they are used strictly for attitude control and that energy for control of the microwheels is only delivered from the battery system [67].…”

Section: A Physical Characteristics and Setupmentioning

confidence: 99%

“…While it is possible to store energy in the microwheels (see [68], [69]), we assume they are used strictly for attitude control and that energy for control of the microwheels is only delivered from the battery system [67]. We also assume that the solar energy harvesting is sufficient during each orbital period to replenish the energy expended during eclipse.…”

Section: A Physical Characteristics and Setupmentioning

confidence: 99%

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Coupled Cyber–Physical System Modeling and Coregulation of a CubeSat

Bradley

Atkins

2015

IEEE Trans. Robot.

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We propose the application of state-space techniques to develop a novel coupled cyber-physical system (CPS) model and use feedback control to dynamically adjust CPS resource use and performance. We investigate the use of a gain scheduled discrete linear quadratic regulator controller and a forward-propagation Riccati-based controller to handle the discrete-time-varying system. We demonstrate the value of our approach by conducting a disturbance-rejection case study for a small satellite (CubeSat) application in which resources required for attitude control are adjusted in real-time to maximize availability for other computational tasks. We evaluate CPS performance through a set of metrics quantifying physical system error and control effort as well as cyber resource utilization and compare these with traditional fixedrate optimal control strategies. Results indicate that our proposed coupled CPS model and controller can provide physical system performance similar to fixed-rate optimal control strategies but with less control effort and much less computational utilization.

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Section: A Physical Characteristics and Setupmentioning

confidence: 99%

Section: A Physical Characteristics and Setupmentioning

confidence: 99%

Coupled Cyber–Physical System Modeling and Coregulation of a CubeSat

Bradley

Atkins

2015

IEEE Trans. Robot.

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“…In [1] the BEESAT picosatellite is detailed which will be flown using three micro-reaction wheels together with magnetic torquers for attitude control. The total weight of their system is 0.105 kg and they are able to change the attitude 180 deg within three minutes.…”

Section: A Previous Workmentioning

confidence: 99%

Reaction wheel design for CubeSats

Oland

Schlanbusch

2009

2009 4th International Conference on Recent Advances in Space Technologies

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This paper presents a reaction wheel design for CubeSats where it takes the limitation of size and mass into consideration. It presents an overview of which altitudes it is feasible to use magnetic torquers for momentum dumping as well as presenting equations for customizing reaction wheels for a CubeSat mission. The reaction wheels are then simulated for different CubeSat sizes and proved capable of performing attitude maneuvers. During these simulations a non-linear passivity-based sliding surface controller is used which through Lyapunov stability theory has been shown to be uniformly asymptotically stable.

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“…The higher output voltage of serial wiring offers higher efficiency of subsequent switched regulators and also the output voltage is better suited to the final voltage of Li-Ion or Li-Pol accumulators which help to enable a safe mode of direct accumulator charging in case of nonstandard situations on picosatellite power buss after system failure. A standard solar panel with two multijunction solar cells can be found in [3,4].…”

Section: Introductionmentioning

confidence: 99%

Efficient and Reliable Solar Panels for Small CubeSat Picosatellites

Veřtát

Vobornik

2014

International Journal of Photoenergy

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CubeSat picosatellites have a limited area of walls for solar cells assembling and the available area has to be effectively shared with other parts, such as planar antennas, optical sensors, camera lens, and access port. With standard size of solar cell strings, it is not possible to construct a reliable solar panel for CubeSat with redundant strings interconnection. Typical solar panels for CubeSat consist of two solar cell strings serially wired with no redundancy in case of solar string failure. The loss of electric energy from one solar panel can cause a serious problem for most picosatellites due to minimum margin in the blueprints of the picosatellite subsystem power budget. In this paper, we propose a new architecture of solar panels for PilsenCUBE CubeSat with a high level of redundancy in the case of solar string failure or following switched power regulator failure. Our solar panels use a high efficiency triple junction GaInP2/GaAs/Ge in the form of small triangle strings from the Spectrolab Company. A suitable technology for precise solar cell assembling is also discussed, because CubeSat picosatellites are usually developed by small teams with limited access to high-end facilities.

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BEESAT: A Pico Satellite for the On Orbit Verification of Micro Wheels

Cited by 20 publications

References 0 publications

Coupled Cyber–Physical System Modeling and Coregulation of a CubeSat

Coupled Cyber–Physical System Modeling and Coregulation of a CubeSat

Reaction wheel design for CubeSats

Efficient and Reliable Solar Panels for Small CubeSat Picosatellites

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