Abstract
This work presents an integrated thermal-electrical simulation model, capable of taking into account the thermal and electrical effects of the battery and photovoltaic panels for each instant of time in a given orbit and attitude. Using the physical equations that govern the thermal and electrical models involved during a CubeSat operation, the proposed integrated model can estimate the temperature and energy conditions of the battery, not only in an isolated way but also in considering the mutual effects on the system. Besides, special attention is given to photovoltaic panels used in the energy harvesting process, whose performance is affected by irradiance and temperature along the orbit. The integrated model can be useful for engineers when developing the subsystems of their CubeSats, taking into account, for example, the battery temperature control through a heater. Simulations were performed to illustrate the functioning of the proposed model with variations in the power requirements of its modules and the temperature of the battery throughout the orbit, and a heater’s influence on it.
Highlights
As a result of electronic miniaturization, compact and light platforms were projected for space applications, including the CubeSat standard proposed in 1999 [1]
The introduction of CubeSat standard and COTS components reduced the price to put a small satellite in orbit by sharing the costs of a launch with multiple CubeSats as piggyback payloads, enabling universities and private companies worldwide to undertake technology demonstration missions in outer space at affordable prices and sustainable business models dedicated to CubeSats
The CubeSat rotates twice per orbit around one axis to align with the Earth’s magnetic field, and the free spin around the secondary axis has the arbitrary value of 10 rotations/per orbit, representative of a spin condition without any damping
Summary
As a result of electronic miniaturization, compact and light platforms were projected for space applications, including the CubeSat standard proposed in 1999 [1]. The introduction of CubeSat standard and COTS components reduced the price to put a small satellite in orbit by sharing the costs of a launch with multiple CubeSats as piggyback payloads, enabling universities and private companies worldwide to undertake technology demonstration missions in outer space at affordable prices and sustainable business models dedicated to CubeSats. The projections are that around 49% of them will be from private initiatives, 32% from universities, 5% from space agencies, and 4% from militaries [2]. A CubeSat is usually covered by photovoltaic panels (PV) on its surface to recharge the batteries and power the subsystems. Due to the solar panels’ small size and volume, the energy harvesting capability heavily depends on its attitude concerning the
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