Kinematics of deployable solar array mechanisms in CubeSat satellites have considerable influence on the stability and attitude control of a satellite, especially in low mass systems as CubeSats. One of the issues with the conventional solar panel deployment mechanisms in CubeSats is the speed of its deployment, especially when position‐lock to hold the panels back from oscillation is lacking. The generated oscillation becomes more pronounced in a system equipped with solar tracking unit and thus, reduces available projected area of the panels and causing fatigue at the yoke and panel hinges. This work aims at modeling and simulation of the 1‐U CubeSat solar panel deployment mechanism vibration control using fisher wire. Two‐fold panel deployment mechanism with a rolling sun‐tracking tilt mechanism was developed. The system performance from viewpoint of vibration analysis was evaluated using mass‐spring‐damper method and bond graph techniques. Numerical simulations and experiments were performed to validate the proposed method. The modeling and computational analysis were done with SOLIDWORKS software. The system was tested for vibration and stability using the seismic mass‐spring‐and‐damper arrangement to validate the model. A 3‐D printing was generated and tested to evaluate its vibration performance and its effects during deployment. The result was such that the two panels attached to a wing hinged at Y – and – Y directions deployed slowly and smoothly at approximately 2 s, giving room for the vibration to decay exponentially towards zero. This agrees with reported works where a DC motor was used to control speed of deployment by increasing time to 6.8 s. The simulated and experimental results of the printed model showed close agreement with the theoretical values with an error of 0.03% in energy supply reliability and up to 400% power generation potential when compared to body mounted solar panels with the same satellite specification without a significant impact on system strength and stability.

Cubesats have transcended mere demonstration systems to sophisticated missions which invariably require the use of deployable solar arrays for more power generation. The kinematics of deployment have considerable influence on the stability and attitude control of a satellite, especially one with such low mass as Cubesats. This work aimed to model and simulate two-wing deployable solar array, with a sun tracking tilt function for a 1-U CubeSat, with emphasis on the deployment mechanism using materials locally available in the country. The design is such that four panels attached to two wings hinged at Y and – Y directions deploy slowly and smoothly at approximately 2 seconds where the vibration decays exponentially and approaches zero. The model of all parts, as well as the computational analysis were done with SOLIDWORKS software. The system was tested for vibration and stability using the seismic mass-spring-and-damper arrangement and the Bond Graph technique was used to conduct kinematic analysis of the mechanism. A 3-D printing was generated and tested to evaluate its operational performance. The simulated results of the model were validated with the prototype outputs with an error of 0.03% in energy supply reliability, about 400% more power generated than the body mounted solar panels of same satellite specification without a significant impact on system strength and Stability.