High-Fidelity Analysis of Deployed Bay Doors on Modern High-Speed Aircraft

Award Information
Agency: Department of Defense
Branch: Air Force
Contract: FA8650-13-M-2359
Agency Tracking Number: F131-004-0270
Amount: $149,912.00
Phase: Phase I
Program: SBIR
Awards Year: 2013
Solicitation Year: 2013
Solicitation Topic Code: AF131-004
Solicitation Number: 2013.1
Small Business Information
215 Wynn Dr., 5th Floor, Huntsville, AL, -
DUNS: 185169620
HUBZone Owned: N
Woman Owned: Y
Socially and Economically Disadvantaged: N
Principal Investigator
 Robert Harris
 Principal Engineer
 (256) 726-4997
 proposals-contracts@cfdrc.com
Business Contact
 Deborah Phipps
Title: Contracts Manager
Phone: (256) 726-4884
Email: dap@cfdrc.com
Research Institution
N/A
Abstract
ABSTRACT: Unsteady aerodynamic loading and flow separation on modern high speed aircraft weapons bay doors can excite aircraft structural modes and lead to buffet, flutter, or fatigue-induced failures. Rigorous numerical simulations, wind tunnel and flight tests are typically carried out to investigate the aerodynamic loading on the doors, but analyses often only consider steady loads on rigid doors and neglect transient and aeroelastic effects. Higher fidelity multidisciplinary analysis tools are critically needed to better understand and characterize the effects of unsteady loads and to design measures for mitigating buffet, flutter, and fatigue. This SBIR project will deliver breakthrough technologies to significantly improve predictive capabilities. Hybrid RANS/LES methods with low-dissipation schemes and tightly-coupled fluid-structure interaction will be used for weapons bay flow simulation including unsteady loading and structural response. The proposed research enables: (1) Improved fidelity and multidisciplinary analysis; (2) Greatly reduced numerical dissipation; and (3) Improved acoustics modeling for weapons bay tonal content. The merits of the proposed approach will be investigated and demonstrated in Phase I for benchmark weapons bay problems. Limited wind tunnel tests will be conducted for computational model validations. In Phase II, a comprehensive experimental program will be executed, and the simulation capabilities will be refined and validated against experimental data and realistic targeted applications. BENEFIT: The proposed computational and experimental effort will provide a much needed high-fidelity prediction tool for low-dissipation aerodynamics and fluid-structure interaction applications of high-speed aircraft over wide range of loading frequencies. This technology has immense potential in military and commercial aircraft sectors. Direct applications of this technology are in low-speed landing gear and speed brakes systems as well as high-speed weapons bay doors systems and for developing protocols for munitions delivery to achieve the desired impact. Other applications may include instrumentation cavities, control surfaces motion, and other moving parts. The proposed effort will have significant impact on improving reliability and safety procedures of weapons bay designs of tactical aircraft and will reduce dependence on flight and wind tunnel tests.

* Information listed above is at the time of submission. *

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