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Automated Parametric Analysis of Defect Effects on Flight Dynamics

Award Information
Agency: Department of Defense
Branch: Air Force
Contract: FA9451-22-P-A023
Agency Tracking Number: F221-0003-0415
Amount: $149,440.77
Phase: Phase I
Program: SBIR
Solicitation Topic Code: AF221-0003
Solicitation Number: 22.1
Solicitation Year: 2022
Award Year: 2022
Award Start Date (Proposal Award Date): 2022-09-01
Award End Date (Contract End Date): 2023-06-08
Small Business Information
13290 Evening Creek Drive South
San Diego, CA 92128-4695
United States
DUNS: 133709001
HUBZone Owned: No
Woman Owned: No
Socially and Economically Disadvantaged: No
Principal Investigator
 Anthony Ricciardi
 (703) 225-7451
Business Contact
 Joshua Davis
Phone: (858) 480-2028
Research Institution

A process to evaluate the overall performance impact of externally generated defects in the outer mold line or control surfaces of aircraft and missiles is proposed. A state-space model will be used to evaluate the system response; aerodynamic loads for system response analyses will be calculated from aerodynamic quantities, such as aerodynamic coefficients and stability derivatives, which will be determined using computational aerodynamic models. Analysis will be automated by upfront parametrization of models. Adaptive mesh refinement (AMR) will be used to ensure model quality. Analysis will be accelerated using response sensitivity computations and frequency-domain aerodynamic methods. A successful Phase I effort will demonstrate the numerical strategy for computation of aerodynamic coefficients, stability derivatives, and corresponding flight dynamic response. Prediction accuracy will be validated against published test data, recommendations will be made for additional validation experiments, process efficiency will be documented, the value of parameter sensitivity results will be demonstrated, the readiness of state-of-the-art AMR methods for use by nonexpert users will be shown, and effective engagement strategy development will be demonstrated. The planned Phase II effort will mature the process into a functional tool with a graphical user interface and user documentation. Either wind tunnel or free-flight validation experiments, as recommended during Phase I, will be conducted, and the results will be used to validate response predictions. Any AMR robustness challenges identified in Phase I will be addressed during Phase II so that the software can be used by engineers who are not CFD experts. The final software will provide a user-focused workflow enabling efficient definition of parametric defect sets, calculation of aerodynamic derivatives, and demonstration of defect impact on flight dynamics.

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

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