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Air Vehicle Gust Response Analysis for Conceptual Design

Award Information
Agency: National Aeronautics and Space Administration
Branch: N/A
Contract: 80NSSC21C0025
Agency Tracking Number: 192965
Amount: $749,999.00
Phase: Phase II
Program: STTR
Solicitation Topic Code: T15
Solicitation Number: STTR_19_P2
Solicitation Year: 2019
Award Year: 2021
Award Start Date (Proposal Award Date): 2021-01-26
Award End Date (Contract End Date): 2023-01-25
Small Business Information
1919 North Ashe Court
Auburn, AL 36830-0000
United States
DUNS: 078301615
HUBZone Owned: No
Woman Owned: No
Socially and Economically Disadvantaged: No
Principal Investigator
 Imon Chakraborty
 (404) 395-1694
Business Contact
 Roy Hartfield
Phone: (334) 444-8523
Research Institution
 Auburn University
23 Samford Hall
Auburn, AL 36849-5338
United States

 Nonprofit College or University

The Controls and Load Alleviation Simulation Platform (CLASP) framework was developed in the NASA STTR Phase I activity preceding this Phase II proposal. CLASP has been created to perform time-domain simulations of gust and turbulence encounters with a focus on UAM and VTOL aircraft concepts. The centerpiece of CLASP is a Simulink flight simulation model that has been developed with significant modularity and modeling flexibility with regard to aircraft aero-propulsive, control system, and structural dynamics models as well as the definition of gust and turbulence characteristics. The NASA LA-8 configuration was used to demonstrate the developed capabilities of the CLASP framework. Phase I simulations were limited to considering the configurationrsquo;s forward flight mode, while Phase II will extend the framework capabilities to vertical flight mode as well.The CLASP framework utilizes a hybrid aero-propulsive modeling approach in which strip theory is used to develop the loads on the fore and aft wings while lookup tables are used to represent the aerodynamic loads on the rest of the airframe. FlightStreamreg; is used extensively for the aero-propulsive analysis within CLASP. A prototype semi-automated FlightStreamreg; Reduced Order Model (ROM) was developed in Phase I and will be automated in this Phase II activity. This feature enables the data reduction necessary to integrate the flow solver into the CLASP framework with very high computational efficiency.The modal approximation method is used to model the structural dynamics of the flexible fore and aft wings. Control system modeling in CLASP includes inner loop controllers for pitch-hold, bank-hold, and yaw damping; an altitude-hold autopilot function, and a proportional-derivative Gust Load Alleviation (GLA) control law operating on estimated gust-induced angle of attack

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

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