Recent Advancements of HPCMP CREATETM-AV Helios

This presentation discusses some of the latest applications and developments of the high-fidelity rotorcraft simulation software CREATETM-AV Helios. Helios is a product of the HPCMP CREATETM-AV program that provides a high-fidelity analysis capability to the Department of Defense for the acquisition of rotary-wing aircraft. Helios has been under continuous development since the very beginning of the CREATE program in 2008. Helios is currently being used for production applications in all major rotorcraft original equipment manufacturers in the U.S. as well as the U.S. Army, Navy, Air Force and NASA.

First, simulations of a UH-60A helicopter in steady autorotative descent are presented. This case combines many of the current capabilities that Helios offers such as including realistic vehicle geometry with multiple asynchronous rotors, full-vehicle free-flight trim, and coupled Computational Fluid Dynamics and Structural Dynamics (CFD/CSD) analysis. The vehicle was simulated in a realistic autorotative state and predictions of the vehicle’s rate of descent are compared against flight test data and flight dynamics codes. The interactional aerodynamics of the rotor and the fuselage are also studied with and without stub wings to explore potential impacts of compound wings on autorotation performance.

Afterwards, new capabilities including the new trim and aeroacoustics modules are highlighted by simulating the full-scale Joby Aviation aircraft, a six-propeller, all electric vertical take-off and landing aircraft designed to operate in urban environments. The aircraft’s propellers are modeled using both mid-fidelity actuator line approaches and high-fidelity CFD using body-conforming meshes. The new trim module is applied to trim the aircraft in cruise using both pitch control and RPM control. Noise predictions are generated using the new aeroacoustics module, and comparisons are made against experimental data and peer analysis.

Finally, progress on the development of a performance-portable unstructured compressible flow solver, RAPIDUS, is presented. RAPIDUS is validated as both a standalone solver and in a dual-mesh/dual-solver paradigm using NASA’s Common Research Model and the PSP rotor, respectively. Predicted loads are compared against experimental data and computational efficiencies are compared against existing software whenever possible.

PRESENTER

Tran, Steven
stevenatran28@gmail.com
781-789-3750

Science & Technology Corporation

CO-AUTHOR

Roget, Beatrice
beatrice.f.roget.civ@army.mil

Hosseinverdi, Shirzad
shirzad.hosseinverdi.ctr@army.mil

Lopez, Mark
mark.j.lopez11.civ@army.mil

Sitaraman, Jay
jayanarayanan.sitaraman.civ@army.mil

Lim, Joon
joon.w.lim.civ@army.mil

Jude, Dylan
dylan.p.jude.ctr@army.mil

Escobar, Daniel
daniel.escobar@jobyaviation.com

Thai, Austin
austin.thai@jobyaviation.com

Bain Jeremy
jeremy.bain@jobyaviation.com

CATEGORY

Computational Fluid Dynamics

SYSTEMS USED

onyx, mustang, narwhal, carpenter, koehr, warhawk

SECRET

No