Automation of Structural Sizing of Aircraft Concepts Under Static Aeroelastic Constraints

Li, Wu ; Geiselhart, Karl ; Olson, Erik ; Robinson, Jay

关键词: AEROELASTICITY;    FLIGHT CONDITIONS;    STATIC MODELS;    STRUCTURAL WEIGHT;    SUPERSONIC AIRCRAFT;    CENTER OF GRAVITY;    FINITE ELEMENT METHOD;    STRUCTURAL DESIGN;    WINGS;   

RP-ID  :  NF1676L-27278

学科分类：软件

美国|英语

来源: NASA Technical Reports Server

【 摘 要 】

This paper presents an automation process for structural sizing of subsonic and supersonic aircraft concepts under static aeroelastic constraints. The automation process starts with an OpenVSP geometry and ends with a PATRAN plot of a NASTRAN solution for static aeroelastic analysis or optimization. ModelCenter is used to integrate all analysis codes with easy-to-use interfaces. Automation tools are developed to streamline the setup process and avoid user errors. Fuel is distributed by solving an optimization problem to match the center of gravity of aircraft at a specified flight condition. Fuel weights are also automatically attached to the structural model as point masses. All other weights used in FLOPS mission analysis (excluding fuselage and wing structural weights) are automatically attached to or smeared on the structural model. For any given OpenVSP geometry and FLOPS analysis data, a static aeroelastic sizing model for NASTRAN analysis can be generated in a couple of hours. The empirical fuselage and wing structural weights from FLOPS are replaced by structural panel weights from the sized finite-element model. Three supersonic and two subsonic aircraft concepts are used to demonstrate the automation process as a physics-based weight estimation tool for aircraft conceptual design.