A Review on Drag Reduction and Stability Optimization Techniques for Small Satellite Launch Vehicles

Abstract

Small satellite launch vehicles have become increasingly critical in the space industry, providing dedicated, cost-effective access to space for a variety of missions, including commercial, scientific, and defense applications. As the demand for small satellites continues to rise, there is a growing need to optimize the design of small launch vehicles, particularly in terms of aerodynamic performance. The aerodynamic forces acting on these vehicles, such as drag and stability, play a crucial role in determining their overall efficiency and ability to reach the desired orbit. Traditional approaches to stabilizing rockets have relied on the use of fins, which, while effective in maintaining stability, also introduce significant drag, thereby reducing fuel efficiency and overall vehicle performance. This paper explores innovative strategies to reduce aerodynamic drag while maintaining or enhancing stability in small launch vehicles. The focus is on refining fin designs and investigating alternative stabilization methods, such as perpendicular thrust, to achieve these goals. By addressing these aerodynamic challenges, the paper aims to contribute to the development of more efficient and effective small satellite launch vehicles, ultimately improving access to space. The study leverages both theoretical analysis and computational fluid dynamics (CFD) simulations to evaluate the proposed designs and methods. Initial results indicate that the strategic redesign of fins, coupled with the integration of perpendicular thrust mechanisms, can lead to a substantial reduction in drag without compromising stability. These findings suggest that the adoption of these innovations could pave the way for more advanced small launch vehicles capable of meeting the growing demands of the space industry.