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Validation of UAM Dynamics Modeling Tool Suite Using Scaled Modular Aerial Research Testbed

Award Information
Agency: National Aeronautics and Space Administration
Branch: N/A
Contract: 80NSSC19C0094
Agency Tracking Number: 188332
Amount: $748,300.00
Phase: Phase II
Program: SBIR
Solicitation Topic Code: A1
Solicitation Number: SBIR_18_P2
Timeline
Solicitation Year: 2018
Award Year: 2019
Award Start Date (Proposal Award Date): 2019-08-14
Award End Date (Contract End Date): 2021-08-13
Small Business Information
3580 Sueldo St., San Luis Obispo, CA, 93401-7338
DUNS: 149341534
HUBZone Owned: N
Woman Owned: N
Socially and Economically Disadvantaged: N
Principal Investigator
 Nick Brake
 (805) 275-1053
 nick.brake@esaero.com
Business Contact
 Tina Landes
Phone: (228) 813-6364
Email: tina.m.landes@nasa.gov
Research Institution
N/A
Abstract
In Phase I, a comprehensive tool suite for the quantitative assessment of UAM aircraft ride qualitieswith respect to passenger comfort. As a result of this effort the validation of the tool suite wasattempted however due to the lack of publicly available validation datasets for the dynamic handlingqualities of UAM aircraft this effort proved difficult. The proposed Phase II work will attempt tocomprehensively address this gap in knowledge through the construction of a Scaled Modular AerialResearch Testbed. The main design of the SMART vehicle will be to allow for installation of amodular vertical lift system with modules representing common UAM aircraft configurations. Thevehicle will be outfitted with provisions for scaling of the aerodynamic and mass properties intended toallow for the matching of the sub-scale vehiclersquo;s dynamics to larger full-scale dynamics. A series ofground tests will be conducted to document the lsquo;as-builtrsquo; configuring, measurements will include keygeometric and structural properties as well as mass properties. The SMART vehicle will be flownindoors through a series of flights including a tethered lsquo;jerkrsquo; flight test intended to represent an externalimpulse gust disturbance. The use of the SIDPAC tool suite will be used to design flight test cards aswell as post-processing flight data to validate the 6DoF dynamics tool suite produced from the Phase Iefforts. The as-built vehicle characteristics and flight test data of three different UAM configurationswill be provided to NASA at the end of the effort enabling validation of UAM and rotorcraft dynamicstool suites.

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

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