Session: 02-02-01: Aero-, Servo-, Thermo-Elastic Modeling and Optimization of Aerial Vehicles

Paper Number: 121652

121652 - On the Impact of Including Gust and Flutter Constraints on the Design of Flying Wing Aircraft 

Flying Wing Aircraft, while theoretically performant, suffer from a multitude of design challenges. These challenges include controllability and aeroelastic stability, among others. This paper introduces some early aeroelastic and control considerations into the conceptual/preliminary level design process and evaluates the impact these considerations have on the shape and weight of the design. Using the Equivalent Static Load method, gust responses from aeroelastic analyses are integrated into NASTRAN Solution 200, enabling the design of a wing structure sized with gust loads. Additionally, flutter constraints and maneuver trim conditions are implemented to determine aeroelastic stability and controllability. These NASTRAN-based optimizations are implemented as sub-optimizations in a Genetic Algorithm, allowing for variations in the planform of the vehicle. The design process utilized for this work is as follows: Using a Genetic Algorithm (GA), the planform geometry is changed to meet configuration and stability constraints. Then, one of three coupled optimization problems is solved using NASTRAN’s Solution 200 (SOL 200) to minimize the weight of the aircraft: a) static aeroelastic with maneuver loads, b) the ESLs from a gust analysis with maneuver loads, c) the ESLs and the flutter constraints with maneuver loads. The weight and longitudinal stability response from a converged NASTRAN solution will be used by the GA to determine an optimal planform design.

This paper is cleared for Public Release, Distribution Statement A: Approved for Public Release; Distribution is Unlimited. PA# AFRL-2023-247
    

Presenting Author: Joshua Deslich University of Dayton Research Institute

Presenting Author Biography: Joshua Deslich is an Aerospace Research Engineer with the University of Dayton Research Institute. His work supports research efforts at the Air Force Research Laboratory in the area of aeroelasticity in aircraft conceptual design.