I. Introduction
In recent years, small satellites of 1-10 kg standard Nano Satellites (NanoSat) have gained an enormous concentration from the diverse community of educational institutions, government organizations, and private companies; but not only limited to that. In this class, the Cube Satellite (CubeSat) is in speedy growth with dimensions of 10×10×10 cm and a mass of 1.33 kg known as 1 unit (1U). The CubeSat is extendable to further bigger units of 2U, 3U, and so on. These satellites provide solutions from space exploration to earth observation and other scientific and technological demonstrations mostly installed in Low Earth Orbit (LEO). These Nano Satellites (NanoSats) are comprised of some subsystems i.e., Attitude Determination and Control System (ADCS), Communication Transceiver (COM), Onboard Data Handling (OBDH) subsystem, Electrical Power System (EPS), and Payloads. The EPS powers the entire subsystems of the satellite for successful operations. In terms of power systems, EPS is a perfect example of a space microgrid comprising mainly Distributed Generations (DGs), a controlled coordination system, an integrated energy storage system, and loads [1], [2]. A typical SmallSat microgrid is shown in Fig. 1. However, the NanoSat microgrid is constrained by some regulation of mass and volume while the power is generated from the body-mounted solar panels. Each LEO NanoSat follows a dedicated orbit and an orientation as per the mission requirements. From some famous orientations, i.e., Sun-pointing, nadir-pointing, and free-orientation scenarios [3]. The solar flux significantly varies in each orientation on the faces of the satellite resulting in a continues change in Nanosat’s angle toward the Sun [4]. Therefore, the solar array at the Maximum Power Point Tracking (MPPT) seems to be the most suitable solution for these operation conditions, instead of the Direct Energy Transfer (DET) option [5] [6].