Design of a Helicopter System Recovery for a Sounding Rocket

In this article, the feasibility of spacecraft recovery using rotary wings is analysed. This technology possesses the ability to perform a safe and controlled landing, allowing the spacecraft to be reused and utilised in missions with different requirements. A computational model that simulates the descent of a sounding rocket was developed. It is based on rotor’s aerodynamic theories and kinematics and computes several rotor parameters that allow the analysis of the system’s performance. The model’s verification was successfully carried out by comparing its behaviour with literature data. To understand how each design parameter influences the system, a parametric study of the rotor design variables was held. It was concluded that the blade’s pitch angle is extremely important for the system’s performance and should be carefully selected, and that weight penalties resultant from excessive blade’s number or radius can be prejudicial. Furthermore, a design optimisation was conducted, aiming to minimise the rocket’s terminal velocity. Finally, a flare manoeuvre was disclosed to reduce the touchdown velocity. This recovery system is concluded to be highly promising, though requiring further work in several fields of study.