This paper studies the attitude determination and control system (ADCS) of the GNSSaS CubeSat. It investigates the disturbance analysis, the B-dot algorithm for the detumbling mode, and the PID controller for the nadir pointing mode. The analysis identified various types of disturbances that can impact the CubeSat's attitude control system and simulated their effects. The results shows that the implementation of the B-dot algorithm demonstrated good performance in detumbling the GNSSaS. The PID controller for Nadir pointing mode achieved the mission requirement which is to have a pointing stability of less than 0.1 deg/sec. Overall, the findings of this study offer valuable insights for optimizing the attitude control system of CubeSats for different missions.

This paper presents a workflow for implementing structural analysis on CubeSats using NX software. Four fundamental analyses, namely quasi-static, modal, random vibration, and buckling analyses, are demonstrated as a guide to simulate these tests for such CubeSats. AlAinSat-1 frame structure is used to apply the analyses using NX. The purpose of this paper is to guide beginners on how to use the software and perform such analyses. The methodology used in this study involves creating three types of FEM models that vary in the number of elements, conducting the four structural analyses, and evaluating the different techniques of the FEM models. To achieve accurate results using FEA, the element size of the meshing should be as small as possible. A convergence analysis shows that the results of models 2 and 3 are convergent. Therefore, the model 2 approach could be used to get acceptable results while reducing the computation time.

AlainSat-1 is an educational and scientific nanosatellite project that was initiated in late 2019 by the IEEE Geoscience and Remote Sensing Society (GRSS) along with National Space Science and Technology Center (NSSTC) of UAE University in the frame of the 2nd Student Grand Challenge [1]. The project involves close collaboration between four international universities to design, build, test and launch a remote sensing CubeSat.The spacecraft is a 3U CubeSat that has a mass of around 4 Kgs. The spacecraft has an active 3-axis control system capable of attitude determination and control to less than one degree. Two communications systems will be used on-board: a UHF System and an S-Band System. The project has passed the Critical Design Review (CDR) stage and is currently in the assembly and integration phase. The satellite is currently planned for launch to a sun-synchronous orbit on-board a Falcon 9 rocket in the second quarter of 2024.

This paper presents the development and implementation of control algorithms for the Attitude Determination and Control Subsystem (ADCS) of AlAinSat-1, a 3U CubeSat. It focuses on detumbling, sun pointing, nadir-pointing, and ground contact modes. Furthermore, it discusses the mathematical models of different sources of disturbance, such as gravity gradient, magnetic torque, atmospheric drag, and solar radiation pressure. The successful implementation of the B-dot algorithm for detumbling and a PID controller for nadir-pointing is demonstrated through numerical simulations. The simulation results indicate a final spinning rate of 1 deg/s in detumbling mode, confirming the efficacy of the algorithm. The implemented PID controller effectively regulates the attitude, resulting in a 1-degree pointing accuracy during the nadir-pointing mode.

CubeSats are cost-effective nanosatellites constructed using commercial-off-the-shelf (COTS) components, which are not specifically designed for space applications. Given the severe space environment where CubeSats are exposed to multiple heat sources such as solar radiation, albedo, and earth infrared radiation (IR), pre-launch testing of these components is of paramount importance. This study presents a simulation of the thermal behavior of AlAinSat-1 under extreme temperatures, utilizing Siemens NX’s 3D Space Systems Thermal module. The simulation process, which spanned from idealization to the assignment of appropriate assumptions and boundary conditions for each case, was conducted under both steady state and transient conditions. The results suggest that AlAinSat-1 can withstand the extreme thermal environment during its mission. However, these findings, being heavily reliant on theoretical assumptions and calculations, necessitate validation through actual experimental testing. Consequently, a series of thermal tests using a thermal vacuum chamber (TVAC) are scheduled in to confirm AlAinSat-1's survivability in the harsh space environment. These tests are crucial to prevent any potential in-orbit failures.