Static Aeroelastic Analysis and Study of Control Effectiveness of a Typical Reusable Launch Vehicle 2024-26-0447

Launch vehicles are vulnerable to aeroelastic effects due to their lightweight, flexible, and higher aerodynamic loads. Aeroelasticity research has therefore become an inevitable concern in the development of the Reusable Launch Vehicle (RLV). RLV is the space analogy of an aircraft, a unanimous solution to achieve more affordable access to space. The lightweight control surface of the RLV signifies the relevance of the study on control effectiveness. It is the capability of a control surface such as an elevon or rudder to produce aerodynamic forces and moments to change the launch vehicle's orientation and maneuver it along the intended flight path. The static aeroelastic problem determines the efficiency of control, aircraft trim behaviour, static stability, and maneuvering quality in steady flight conditions. In this study, static aeroelastic analysis was performed on a typical RLV using MSC/NASTRAN inbuilt aerodynamics. This study is performed using a finite-element structural model (MSC/NASTRAN, MSC/PATRAN) coupled to an aerodynamic model (Doublet Lattice Method) based on Panel method, along the descent phase trajectory of the launch vehicle. The aim of this analysis is to quantify the control effectiveness of the typical RLV and to evaluate its efficiency to control the vehicle during flight. This paper also focuses on the parametric study of the control effectiveness of the elevon for diverse parameters, including altitudes, density, dynamic pressure, and Mach numbers. Keywords: Reusable Launch vehicle, Aeroelasticity, Control Effectiveness, Aerodynamics