The proposed research program aims at developing a variable-fidelity software tool set for aeroservothermoelastic-propulsive (ASTE-P) modeling that can be routinely applied to the design of aerospace vehicles. The tool set can be applied to conventional vehicle types as well as hypersonic vehicles.… More

The proposed research program aims to develop a physics-based identification, modeling and management infrastructure for aeroelastic limit-cycle oscillations. This infrastructure will be built upon high fidelity state-of-the-art theoretical/computational methods as validated and verified by… More

The objective of the proposed research aims to develop Reduced Order Models (ROMs) (i.e. POD, HB, combined POD and HB) based upon flight data to better predict the aircraft aeroelastic response at next flight condition, e.g. higher Mach number. By incorporating flight test data and using the… More

CFD modeling and simulation has been heavily invested in decades of manpower by a large community of researchers. However, the excessive numerical diffusion inherently caused by discretization errors plus the possibly largest/finest grid requirement for rotor wake modeling prevents CFD to be… More

This SBIR aims at developing a high-fidelity, yet efficient and easy-to-use, composite rotor blade and wing section design environment to facilitate rapid and confident aeromechanics assessment during conceptual design stages. A well-known technical barrier for composite rotor blade and wing section… More

The proposed research program aims at developing a variable-fidelity software tool set for aeroservothermoelastic-propulsive (ASTE-P) modeling that can be routinely applied to the design of aerospace vehicles. The toolset can be applied to conventional vehicle types as well as hypersonic vehicles.… More

Research is proposed for the development and implementation of state of the art, reduced order nonlinear aeroelastic models for multidisciplinary/multi-fidelity optimization problems. Highly efficient and accurate aeroelastic simulation tools will be constructed based upon the mathematical formalism… More

The proposed research program will develop a physics-based identification, modeling and risk management infrastructure for aeroelastic transonic flutter and limit-cycle oscillations (LCO). This capability will be built upon high fidelity state-of-the-art theoretical/computational methods as… More

The proposed work aims at developing techniques that will address the current limitations of Cartesian-based Navier-Stokes CFD schemes by exploring three promising methods of implementing improved wall boundary conditions. The three methods are based on: (1) the diamond stencil approach of Delanaye… More

This SBIR aims at developing a high-fidelity, yet efficient and easy-to-use, composite rotor blade and wing section design environment to facilitate rapid and confident aeromechanics assessment during conceptual design stages. A well-known technical barrier for composite rotor blade and wing section… More

The aluminum alloys have low density, relatively high strength, and high strength-to-weight ratio, which brings some major advantages in marine structure design, fabrication, and operations. However, marine ships are subjected to a complex and severe loading, and the typical failure mode of aluminum… More

Research is proposed for the development and implementation of state of the art computational and experimental tools for the investigation of the impact of control surface freeplay on the flutter and limit cycle oscillation characteristics of two-dimensional and three-dimensional wings in subsonic… More

This Small Business Technology Transfer Phase I project is aiming at developing and implementing a multiscale composite model to predict the ceramic matrix composite (CMC) response to the impact loading by foreign objects. In particular, the physics-based model will be applied to describe the… More

Turbine disks are amongst the most critical components in aero- and naval-vessel engines. They operate in a high pressure and temperature environment requiring demanding properties. Nickel-based supperalloys which have high creep and oxidation resistance at high temperatures are widely used as the… More

Research is proposed for the development and implementation of state of the art, reduced order models for problems in nonlinear aeroelasticity. Highly efficient and accurate aeroelastic simulation tools will be constructed based upon the mathematical formalism of optimal prediction theory and a… More

Research is proposed for the development of a state-of-the-art computational aeroelastic tool. This tool will include various levels of fidelity and the ability to perform computational uncertainty quantification for data-driven risk analysis and certification. A number of novel reduced-order in… More

The proposed work will establish high fidelity computational methods and wind tunnel test model in support of new freeplay criteria for the design, construction and controlled actuation of control surfaces with varying amounts of freeplay and their aeroelastic response. These methods will be… More

The need to accurately predict aeroelastic phenomenon for a wide range of Mach numbers is a critical step in the design process of any aerospace vehicle. Complex aerodynamic phenomenon such as vortex shedding, shock-turbulence interaction, separation, etc. dominate at transonic and supersonic Mach… More