Purpose This study aims to predict the types of thermally induced dynamics (TID) that can occur on deployable solar panels of a small form factor satellite, CubeSat which flies in low Earth orbit (LEO). The TID effect on the CubeSat body is examined. Design/methodology/approach A 3U CubeSat with four short-edge deployable solar panels is considered. Time historic temperature of the solar panels throughout the orbit is obtained using a thermal analysis software. The results are used in numerical simulation to find the structural response of the solar panel. Subsequently, the effect of solar panel motion on pointing the direction of the satellite is examined using inertia relief method. Findings The thermal snap motion could occur during eclipse transitions due to rapid temperature changes in solar panels’ cross-sections. In the case of asymmetric solar panel configuration, noticeable displacement in the pointing direction can be observed during the eclipse transitions. Research limitations/implications This work only examines an LEO mission where the solar cells of the solar panels point to the Sun throughout the daylight period and point to the Earth while in shadow. Simplification is made to the CubeSat structure and some parameters in the space environment. Practical implications The results from this work reveal several practical applications worthy of simplifying the study of TID on satellite appendages. Originality/value This work presents a computational method that fully uses finite element software to analyze TID phenomenon that can occur in LEO on a CubeSat which has commonly used deployable solar panels structure.

Nanosatellites, like CubeSat, have begun completing advanced missions that require high power that can be obtained using deployable solar panels. However, a larger solar array area facing the Sun increases the solar radiation torque on the satellite. In this study, we investigated solar radiation torque characteristics resulting from the increased area of solar panels on board the CubeSats. Three common deployable solar panel configurations that are commercially available were introduced and their reference missions were established for the purpose of comparison. The software algorithms used to simulate a variety of orbit scenarios are described in detail and some concerns are highlighted based on the results obtained. The solar power generation of the respective configurations is provided. The findings are useful for nanosatellite developers in predicting the characteristics of solar radiation torques and solar power generation that will be encountered when using various deployable solar panels, thus helping with the selection of a suitable configuration for their design.

Malaysia had in the past sent two remote sensing satellites to orbit by collaborating with foreign space companies to build homegrown capacities for space technology development. At the educational institutions, a pico-satellite development program would be an ideal first step to establish such capacity as students could gain the experience and know-how through the complete cycle of designing, building and testing a satellite. As it is now, some of their overseas counterparts have already succeeded in running CubeSat programs due to strong support from kit manufacturers and their national space agencies. However, the cost to purchase such kits could be discouraging and National Space Agency (ANGKASA) recognises the needs to initiate some designs that could be used or referred to for further development or expansion. In this paper, a hardware design of On-Board Data Handling (OBDH) board using PIC Microcontroller is presented. OBDH is a main subsystem which controls all subsystems in the satellite. It provides a series of important services like command, telemetry, data communication, data acquisition, process, storage and management. The PIC Microcontroller made by Microchip Corporation is chosen as it is widely used by the industry and academia in Malaysia. The 16-bit PIC24 microcontroller has been recognized as a suitable part due to its performance, memory, peripherals, cost effective solutions as well as availability. The method used in designing the OBDH in this pico-satellite is first based on a main mission to investigate ionospheric effect on GPS signal transmission. Other considerations taken are that the parts used should be of commercial off the shelf product and having its own development board for ease of testing. The expected result would be the successful arrangement of all required parts in limited pico-satellite’s size and the accomplishment in achieving the satellite’s missions through simulation.

No abstract