Determining Optimal Orbital Path of a Nanosatellite for Efficient Exploitation of the Solar Energy Captured

Mocanu, Bogdan; Burlacu, Maria-Mihaela; Kohlenberg, Joséphine; Prathaban, Mahendiran; Lorenz, Pascal; Țapu, Ruxandra

doi:10.1109/spacomm.2009.23

Cited by 3 publications

(4 citation statements)

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“…Some approximations were adopted for this calculation: the satellite orbit is considered as a circle, and the Earth shape as a perfect sphere. [59][60][61]…”

Section: Satellite Orbitmentioning

confidence: 99%

“…Equation (36) allows an estimation of the period the satellite stays in the Earth shadow. Some approximations were adopted for this calculation: the satellite orbit is considered as a circle, and the Earth shape as a perfect sphere 59‐61

t_{o r b i t} = 2 π false(R + h false) \sqrt{\frac{false(R + h false)}{G M}},

t_{s h} = \frac{t_{o r b i t}}{π} a r c c o s ((), \frac{\sqrt{1 - {((), \frac{R}{R + h})}^{2}}}{c o s false(β false)}) .

…”

Section: Input Power Model and Simulationsmentioning

confidence: 99%

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Nanosatellite electrical power system architectures: Models, simulations, and tests

Slongo

Martinez

Eiterer

et al. 2020

Circuit Theory & Apps

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KESSLER SLONGO ET AL. power point tracking (MPPT) techniques, high-efficiency solar cells, and energy-aware scheduling algorithms are some of the hot topics under research nowadays. Due to size restrictions and aiming low complexity in design, many nanosatellite designers adopt the direct energy transfer (DET) architecture. KySat-2 is an example of a successfully accomplished mission, based on this EPS topology. Designed by Morehead State University Space Science and Engineering group, KySat-2 EPS was powered by a set of gold-plated deployable solar panels with 26% of efficiency. It provided four high-power regulated rails (two 3.3 V and two 5 V) and a low-noise, low power 3.3V rail for noise-sensitive devices. The energy storage system was made of three 18650 lithium-ion cells connected in series, and the high-power rails reached efficiencies approaching 90%. 12,21 Aiming minimum space occupation and low power consumption, the EPS proposed for the AraMiS project has a boost regulator operating the solar panels close to their MPP. 16 In order to reduce the number of components, the designers opted by the constant voltage MPPT algorithm, using only analog devices. The EPS steps up solar panels voltage from 4.4 V to the distribution bus voltage level (14 ± 2 V). It provides power buses with 3.3 and 5 V voltage levels. The EPS efficiency analysis is demonstrated, calculating the main components power losses. Although this is a very detailed and well-described work, it does not compare the proposed solution with other EPS architectures. A 3U EPS efficiency analysis is presented by Gonzalez-Llorente et al. 22 The subsystem is based on a buck converter that steps down the solar panels voltage (15 or 7.5 V) to the litChium-ion battery range of 3.3 or 6.6 V. The authors define an optimum operation point for the DC-DC converter in order to achieve its maximum efficiency. The operation point is defined by the converter input voltage, output voltage, and output power. Therefore, the discussion is based on different solar cells connections configurations, and battery cells arrangement, that result in the most efficient EPS configuration. Different scenarios have been analyzed to achieve 98% of peak efficiency on the best configuration: input voltage of 7.4 V, output voltage of 3.3 V, and output current varying from 0.1 mA to 2.1 A. Only the buck converter topology is discussed in this paper, and it does not consider any MPPT technique. An interesting solution adopted for the ERPSAT-1 picosatellite uses fuzzy logic to obtain energy harvesting maximization. 23 The developed subsystem has three main blocks, which are the fuzzy maximum power point tracker, the power conditioner, and the hierarchical fuzzy subsystem controller. The fuzzy logic algorithm has been implemented in a dedicated microcontroller that controls a boost converter. Simulations have been performed to demonstrate the better efficiency of the proposed method when compared to the Perturb and Observe MPPT algorithm. Although a comparison is provided in this work,...

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“…Some approximations were adopted for this calculation: the satellite orbit is considered as a circle, and the Earth shape as a perfect sphere. [59][60][61]…”

Section: Satellite Orbitmentioning

confidence: 99%

t_{o r b i t} = 2 π false(R + h false) \sqrt{\frac{false(R + h false)}{G M}},

t_{s h} = \frac{t_{o r b i t}}{π} a r c c o s ((), \frac{\sqrt{1 - {((), \frac{R}{R + h})}^{2}}}{c o s false(β false)}) .

…”

Section: Input Power Model and Simulationsmentioning

confidence: 99%

Nanosatellite electrical power system architectures: Models, simulations, and tests

Slongo

Martinez

Eiterer

et al. 2020

Circuit Theory & Apps

View full text Add to dashboard Cite

show abstract

“…One is to improve the input power and the other is to reduce the power usage without reducing the satellite performance. There were some research works aimed to improve the input power to the satellites through deployable solar panels [14][15][16][17][18], optimization of power gain [19][20][21][22][23][24][25][26][27][28][29], and optimization of the satellite's orbit path [30].…”

Section: Power On Miniaturized Satellitesmentioning

confidence: 99%

“…The main idea in this research is to maximize the solar energy captured on the satellites based on orbit path selection. [30] show how different orbit paths produce different sunexposure/eclipse duration and different orbit (beta) angle (the minimum angle between the satellite's orbit plane and solar vector). These differences would result in different solar energy harvested.…”

Section: Optimization Of Orbit Pathmentioning

confidence: 99%