Attitude control system of the Delfi-n3Xt satellite

Reijneveld, J.; Choukroun, Daniel

doi:10.1051/eucass/201306189

Cited by 2 publications

(2 citation statements)

References 11 publications

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“…3. These assumptions are in close compliance with reported CubeSat configurations [13,27,41] and principal moments of inertia values in actual missions [3,32,40]. Additionally, this investigation is based on the common practice of performing in-orbit thruster characterisation via attitude changes [13,27,29].…”

Section: The Proposed Methodssupporting

confidence: 71%

Spiral coning manoeuvre for in-orbit low thrust characterisation in CubeSats

Macario-Rojas

Smith

2017

Aerospace Science and Technology

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The ability to accurately measure the level of thrust during in-orbit operations is fundamental to the characterisation of emerging propulsion systems for nanosatellites. Many new CubeSat missions use propulsion systems with thrust levels in the order of few micro-Newtons. Whilst laboratory sensing resources are able to resolve such low thrust values, in complementary in-orbit characterisation are limited and in the main not compatible with the standard CubeSat mission. Additionally, typical in-orbit assessment of micro-thrust is generally carried out through body angular speed changes, the effectiveness of which is drastically reduced when external perturbations and sensor noise approach or exceed the thruster action on the CubeSat. This investigation sets out to improve in-orbit micro-thrust characterisation via changes in body angular velocity periodicity due to off-centred thrust action in nearly axisymmetric CubeSats. Unlike traditional methods that rely on determining angular acceleration this method employs a frequency analysis of the transversal component of the angular velocity signal with the aim of reducing measurement error. Numerical simulations support the feasibility and adequacy of the proposed low-thrust gauging method, particularly for weak and noisy sensor signals. The robustness of the method allows for interchangeable analysed signal and enables the use of simple commercial-off-the-shelf rate sensors in fine micro-thrust characterisation.

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Section: The Proposed Methodssupporting

confidence: 71%

Spiral coning manoeuvre for in-orbit low thrust characterisation in CubeSats

Macario-Rojas

Smith

2017

Aerospace Science and Technology

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“…They are considerably smaller than typical commercial satellites, with a volume of 10 cm 3 for a standard size of 1 unit (1U) and a mass of less than 1.33 kg, and they typically use commercial off-the-shelf components [1]. Recently, CubeSats have been advocated for not only by academia [2][3][4] but also by space agencies [5] and industries [6,7] around the world as a means of achieving increasingly complex missions, including scientific, surveillance, and technology demonstration missions. Their advantages include their lower cost, shorter development time, and the opportunity to provide educational experience through hands-on experience.…”

Section: Introductionmentioning

confidence: 99%

Experimental feasibility study of concentrating photovoltaic power system for cubesat applications

Park

2015

IEEE Trans. Aerosp. Electron. Syst.

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The ability to produce sufficient power is an important factor in assuring the success of the challenging and complex cube satellite (CubeSat) missions within an extremely small size. A CubeSat has only a limited surface area on which solar panels can be installed to generate power. The incidence angle of sunlight on the solar panels also varies according to the revolution and rotation of the satellite. These are important parameters for determining the amount of power that a CubeSat can generate. In this study, we propose a concentrating photovoltaic system for CubeSats that enhances the efficiency of power generation by effectively concentrating the solar energy on the solar panels by using a multi-array lens system under the worst condition for sun incidence angle. The feasibility of using the concentrating photovoltaic system for CubeSat applications is demonstrated by power measurement tests using a solar simulator and a commercial multi-array lens under various light source angles.

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Attitude control system of the Delfi-n3Xt satellite

Cited by 2 publications

References 11 publications

Spiral coning manoeuvre for in-orbit low thrust characterisation in CubeSats

Spiral coning manoeuvre for in-orbit low thrust characterisation in CubeSats

Experimental feasibility study of concentrating photovoltaic power system for cubesat applications

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