Comparison of the Incident Solar Energy and Battery Storage in a 3U CubeSat Satellite for Different Orientation Scenarios

Sanchez-Sanjuan, Sergio; González-Llorente, Jesús; Hurtado-Velasco, Ronald

doi:10.5028/jatm.v8i1.531

Cited by 19 publications

(14 citation statements)

References 13 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…where S 0 is the solar constant given by the orbit, cell is the efficiency of the solar cells [29]. Considering the illuminated area is a function of the incidence angle, the power generated by each module can be different, especially in satellites with body mounted solar cells [30]. In this case, sides with different solar incidence angle will generate different power.…”

Section: Design Of Solar Power Generation Unitmentioning

confidence: 99%

Solar Module Integrated Converters as Power Generator in Small Spacecrafts: Design and Verification Approach

et al. 2019

Self Cite

View full text Add to dashboard Cite

As small satellites are becoming more widespread for new businesses and applications, the development time, failure rate and cost of the spacecraft must be reduced. One of the systems with the highest cost and the most frequent failure in the satellite is the Electrical Power System (EPS). One approach to achieve rapid development times while reducing the cost and failure rate is using scalable modules. We propose a solar module integrated converter (SMIC) and its verification process as a key component for power generation in EPS. SMIC integrates the solar array, its regulators and the telemetry acquisition unit. This paper details the design and verification process of the SMIC and presents the in-orbit results of 12 SMICs used in Ten-Koh satellite, which was developed in less than 1.5 years. The in-orbit data received since the launch reveal that solar module withstands not only the launching environment of H-IIA rocket but also more than 1500 orbits in LEO. The modular approach allowed the design, implementation and qualification of only one module, followed by manufacturing and integration of 12 subsequent flight units. The approach with the solar module can be followed in other components of the EPS such as battery and power regulators.

show abstract

Section: Design Of Solar Power Generation Unitmentioning

confidence: 99%

Solar Module Integrated Converters as Power Generator in Small Spacecrafts: Design and Verification Approach

et al. 2019

Self Cite

View full text Add to dashboard Cite

show abstract

“…Nadir-pointing is a case in which the same face of the CubeSat is always pointing to the centre of the Earth. This scenario allows for the four faces exposed to direct solar heat flux to exhibit a sinusoidal behavior of radiation [28]. The proposed composite material for the primary structure panels is a quasi-isotropic [0/45 2 /0 3 ] S carbon fibre/epoxy resin laminate with 3 mm in thickness.…”

Section: Conceptual Designmentioning

confidence: 99%

Thermal Numerical Analysis of the Primary Composite Structure of a CubeSat

Piedra

Torres

Ledesma³

2019

Aerospace

View full text Add to dashboard Cite

A thermal computational analysis for the composite structure of a CubeSat is presented. The main purpose of this investigation is to study the thermal performance of carbon fibre/epoxy resin composite materials with Zinc Oxide nanoparticles in order to be used in the panels of the primary structure of a CubeSat. The radiative heat fluxes over each composite panel are computed according to the orbit trajectory and they are utilized as boundary conditions for the analysis. The direct solar, albedo and Earth infrared radiation fluxes are considered in this study. The model implementation, including the computation of the orthotropic thermal conductivity of the composite material is presented. The thermal simulations were performed for three different orbit inclination angles: the selected mission ( β = 57 ∘ ), the worst hot ( β = 90 ∘ ) and the worst cold ( β = 0 ∘ ). The temperature ranges in the electronic boards are analyzed in order to show that are into the operating limits of each electronic component.

show abstract

“…Power storage is typically performed by rechargeable lithium-ion batteries; close attention should be paid to this component during thermal design [26]. A power management and distribution module (PMAD), often referred to as a battery management system is employed to control the control of power draw to the instrumentation and sub systems.…”

Section: Power Sub-system Overviewmentioning

confidence: 99%

“…Aerospace 2018, 5, x FOR PEER REVIEW 11 of 68 generation sources include Photovoltaic Cells, solar arrays, and thermonuclear power generators, although these are commonly found on much larger craft [23]. Power storage is typically performed by rechargeable lithium-ion batteries; close attention should be paid to this component during thermal design [26]. A power management and distribution module (PMAD), often referred to as a battery management system is employed to control the control of power draw to the instrumentation and sub systems.…”

Section: Power Sub-system Overviewmentioning

confidence: 99%

See 1 more Smart Citation

Design of Power, Propulsion, and Thermal Sub-Systems for a 3U CubeSat Measuring Earth’s Radiation Imbalance

Claricoats

Dakka

2018

Aerospace

View full text Add to dashboard Cite

The paper presents the development of the power, propulsion, and thermal systems for a 3U CubeSat orbiting Earth at a radius of 600 km measuring the radiation imbalance using the RAVAN (Radiometer Assessment using Vertically Aligned NanoTubes) payload developed by NASA (National Aeronautics and Space Administration). The propulsion system was selected as a Mars-Space PPTCUP -Pulsed Plasma Thruster for CubeSat Propulsion, micro-pulsed plasma thruster with satisfactory capability to provide enough impulse to overcome the generated force due to drag to maintain an altitude of 600 km and bring the CubeSat down to a graveyard orbit of 513 km. Thermal analysis for hot case found that the integration of a black high-emissivity paint and MLI was required to prevent excessive heating within the structure. Furthermore, the power system analysis successfully defined electrical consumption scenarios for the CubeSat's 600 km orbit. The analysis concluded that a singular 7 W solar panel mounted on a sun-facing side of the CubeSat using a sun sensor could satisfactorily power the electrical system throughout the hot phase and charge the craft's battery enough to ensure constant electrical operation during the cold phase, even with the additional integration of an active thermal heater. However, when the inevitable end-of-life degradation of the solar cell was factored into the analysis, an approximate power deficit of 2 kJ was found. This was supplemented by additional solar cell integrated into the antenna housing face.Aerospace 2018, 5, 63 2 of 68 Tyvak, NanoRacks, Innovative Solutions In Space (ISIS) and CalPoly [2]. The nanosatellites are placed within an orbital deployer which safely releases the satellites into orbit after launch. The orbital deployer also helps to ensure the safety of the vehicle by encapsulating the satellites [3].As of 19 September 2016, a total of 479 CubeSats had been officially launched worldwide [2]. Of those launched, 210 are still operational and gathering data [2]. 70 nanosatellites were destroyed during launch [2]. A total of 40.8% of nanosatellites were launched by academic institutions, the highest of all categories [2]. This was followed by private companies in second with a total of 40.2% of all launches. Other major contributors included the military (5.3%) and space agencies (6.7%) [2]. The 3U CubeSat holds the market majority for chosen dimensions. 52.9% of all launched satellites conformed to these dimensions. The second most popular choice was the 1U configuration which had a 17.9% share of all launched types [4].Although the first CubeSat was launched in 1999 the number of launches has grown significantly in recent years. The first major advancement in launch numbers came in 2013. The launch number for this year was 87, a huge increase on the previous year's total of 25 [2]. This grew to around 150 per year in 2014/2015 and had peaked to 288 in 2016. There were 295 launches for 2017 [2] which highlights how rapidly this technology is advancing and the increasing rate at which it is be...

show abstract

Comparison of the Incident Solar Energy and Battery Storage in a 3U CubeSat Satellite for Different Orientation Scenarios

Cited by 19 publications

References 13 publications

Solar Module Integrated Converters as Power Generator in Small Spacecrafts: Design and Verification Approach

Solar Module Integrated Converters as Power Generator in Small Spacecrafts: Design and Verification Approach

Thermal Numerical Analysis of the Primary Composite Structure of a CubeSat

Design of Power, Propulsion, and Thermal Sub-Systems for a 3U CubeSat Measuring Earth’s Radiation Imbalance

Contact Info

Product

Resources

About