Structural Design for Buckling, Snap-through, and Limit Cycle Oscillations with Applications to Supersonic and Hypersonic Environments
Abstract
Aerospace structural sizing and design for supersonic-hypersonic air vehicles involves complicated reaction forces between the hot outer surfaces and the cooler inner surfaces of the vehicle as they strive to reach a state of strain equilibrium. The skin panels of such air vehicles are known to further complicate design due to the coupled thermal, mechanical, and aerodynamic loads leading to nonlinear panel responses and potential aero-elastic instability. These panels are stiffened to combat these responses by adding hat stiffeners-honeycomb or by making the panel thicker; however, a stiffer skin necessitates stiffer internal structures adding weight to the vehicle. An alternative approach is the design of monocoque, or structural skin, panels with tailored compliance to passively control buckling, snap-through, internal resonances, and-or aero-elastic instabilities. The goal of the proposed effort is to understand how localized features can control the global quasi-static and dynamic response of extremely flexible nonlinear structures similar to skin panels on supersonic-hypersonic air vehicles. The PI seeks to build upon current work and utilize the laser powder bed fusion additive manufacturing (AM) machine to design, build, and test panels through an iterative numerical and experimental effort to efficiently explore the design space of localized features minimizing the number of prototypes built.
Document Details
- Document Type
- DoD Grant Award
- Publication Date
- Mar 06, 2024
- Source ID
- FA95502310423
Entities
People
- David Ehrhardt
Organizations
- Air Force Office of Scientific Research
- United States Air Force
- University of Illinois Urbana–Champaign