Power budget analysis for a LEO polar orbiting nano-satellite

Dahbi, Sanae; Aziz, Abdelhak; Zouggar, Smail; Hafyani, Mohamed El; Morocco, Oujda; Hanafi, Ahmed; Karim, Mohamed Rehan; Latachi, Ibtissam; Rachidi, Tajjeeddine

doi:10.1109/atsip.2017.8075580

Cited by 19 publications

(8 citation statements)

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“…A combination of both active and passive control techniques is usually required for large satellites (Figure b) to ensure temperature control within very tight margins. However, their application is limited by the power and mass budgets, which often result in the cancellation of mission studies. − Smaller satellites, such as CubeSats, require smaller and lighter thermal management solutions due to the size limitations, which restrict the utilization capacity of active systems − (Figure c). A good example is the commonly used thermal louver developed by the National Aeronautics and Space Administration (NASA) that uses bimetallic springs to control the position of the flaps.…”

Section: Introductionmentioning

confidence: 99%

“…Furthermore, JWST and other sensitive instruments required additional heaters to maintain temperature, cleanliness, and structural performance of the instruments and satellites. This further added extra mass and complexity. − Various smart electrochromic and thermochromic materials that are designed to operate over a selected range of wavelengths have also been investigated as a means of achieving variable thermal control, which would allow seamless operation. However, these materials usually require heavy equipment and they only vary the thermal emittance in the infrared spectrum (e.g., architectures based on vanadium dioxide (VO 2 ) films with an emissivity change from 0.13 to 0.68). − Furthermore, they are sensitive to thermal stresses and impacted by changes in levels of moisture. ,, This has been shown and rejected for the Sentinel missions under the Copernicus Earth Observation Programme. − …”

Section: Introductionmentioning

confidence: 99%

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Multifunctional Nanostructures with Controllable Band Gap Giving Highly Stable Infrared Emissivity for Smart Thermal Management

et al. 2023

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Thermal control is essential to guarantee the optimal performance of most advanced electronic devices or systems. In space, orbital satellites face the issues of high thermal gradients, heating, and different thermal loads mediated by differential illumination from the Sun. Todayś state-of-the-art thermal control systems provide protection; however, they are bulky and restrict the mass and power budgets for payloads. Here, we develop a lightweight optical superlattice nanobarrier structure to provide a smart thermal control solution. The structure consists of a moisture and outgassing physical barrier (MOB) coupled with atomic oxygen (AO)−UV protection functionality. The nanobarrier exhibits transmission and reflection of light by controlling the optical gap of individual layers to enable high infrared emissivity and variable solar absorptivity (minimum Δα S = 0.30) across other wavelengths. The multifunctional coating can be applied to heat-sensitive substrates by means of a bespoke room-temperature process. We demonstrate enhanced stability, energyharvesting capability, and power savings by facilitating the radiation cooling and facility for active self-reconfiguration in orbit. In this way, the reduction of the operating temperature from ∼120 to ∼60 °C on space-qualified and nonmechanically controlled composite structures is also demonstrated.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Multifunctional Nanostructures with Controllable Band Gap Giving Highly Stable Infrared Emissivity for Smart Thermal Management

et al. 2023

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“…A tiny satellite lifespan is greatly influenced by its electrical power system (EPS). In order to efficiently meet a number of objectives, the EPS must be able to generate, manage, store, control, safeguard, and distribute power to the platform equipment and payloads of spacecraft [5].…”

Section: Introductionmentioning

confidence: 99%

Comparative Study Of Energy Balance For A 3U CubeSat For Different Orientation Flight Scenarios

Hosny,

Mokhtar,

Safwat

2023

J. Phys.: Conf. Ser.

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The CubeSat standard makes development, launch, and operation possible for those with no experience in space technology to participate. The power demand coverage by the power supply system during all modes of operation is a critical issue that needs to focus on to avoid satellite mission failure. Therefore, the solar array (SA) and battery pack should be sized precisely based on the satellite architecture and flight orientation scenarios. A 3U Cube-Satellite has been used as a case study to evaluate the effect of satellite flight orientation (Nadir and sun tracking) on the energy balance between the supply system and the load demand and find out the appropriate flight orientation for achieving the mission successfully. The orbit simulation has been done via STK environment for both flight orientation scenarios with the same load profile where the electrical power system (EPS) has confronted the worst-case scenario of operation. Furthermore, the unregulated bus configuration has been selected to simulate EPS response during the orbit period using SIMULINK for different orientation flight scenarios.

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“…4 Professor, School of Information Science and Technology, Zhejiang Sci-Tech University. 5 Professor, Institute of Energy Technology, Aalborg University. 2 vast understanding of our planet, distant worlds and wonders of universe.…”

Section: Introductionmentioning

confidence: 99%

Optimized Design of Embedded Air Coil for Small Satellites with Various Dimensions

Khan

Ali

Yang

et al. 2021

Journal of Aerospace Information Systems

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Active attitude control systems using a novel six layers electromagnetic embedded printed Air-Coils for small satellites with various dimensions are presented in this paper. The proposed designs are optimized in terms of available area, generated torque, power dissipation and generated magnetic dipole moment. The designed printed Air-Coils are the best choice for small satellites attitude stabilization in terms of their modularity, reconfigurability, lower cost, lesser space occupation and low mass. The printed Air-Coil is designed and analyzed for three small satellites with dimensions 10 𝒄𝒎 𝟑 , 13𝒄𝒎 𝟑 and 16𝒄𝒎 𝟑 . The design is implemented with Commercial off the shelf (COTS) microdevices which are inexpensive, reliable and easily accessible. The printed Air-Coil is integrated in internal layers of printed circuit board (PCB) which does not require additional space on the spacecraft. The proposed Air-Coil with additional configurability features (2×3, 3×2 hybrid) provide more flexibility to the design aspects by changing the arrangement through the onboard processor according to mission requirements. Electrothermal analysis of the Air-Coil module is done to keep the thermals in check and validate its feasibility. Time varying rotational operation of nanosatellites is performed to test the rotation time for spin stabilized satellites. Significant performance parameters like generated magnetic moment, resultant torque and power dissipation are evaluated and compared with the already commercial state of the art.

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Power budget analysis for a LEO polar orbiting nano-satellite

Cited by 19 publications

References 0 publications

Multifunctional Nanostructures with Controllable Band Gap Giving Highly Stable Infrared Emissivity for Smart Thermal Management

Multifunctional Nanostructures with Controllable Band Gap Giving Highly Stable Infrared Emissivity for Smart Thermal Management

Comparative Study Of Energy Balance For A 3U CubeSat For Different Orientation Flight Scenarios

Optimized Design of Embedded Air Coil for Small Satellites with Various Dimensions

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