Simulation and Flight Control of an Aeroelastic Fixed Wing Micro Aerial Vehicle

Author:

Waszak Martin1,Davidson John1,Ifju Peter2

Affiliation:

1. NASA Langley Research Center

2. University of Florida

Publisher

American Institute of Aeronautics and Astronautics

Reference43 articles.

1. The actuators subsystem currently consists of first order actuator transfer functions and limiters that bound the permissible range of symmetric δsymand antisymmetric δasycontrol surface deflections (-25 degrees and -20 degrees, respectively) and commanded motor voltage (0 - 20 volts). The sensor subsystem currentlycontains no dynamics but will permit sensor modelstobeaddedatalatertime.

2. The longitudinal and lateral-directional subsystems consist of additional subsystems that systematically build up the equations of motion as derived in reference6. The equations representthe six degree-offreedommotion of a rigid aircraft relative to a flat, non-rotating earth. The atmosphere is representedusing the 1976 StandardAtmospheremodel.[6]UFMAV AeroModel

3. The functions are in the form of Taylor series;Theaerodynamicmodelwasobtainedprimarilyfrom NASA

4. Experimental Trim 1.0 18,900 10.4 -6.5 1.6 20,600 5.4 -3.5 2.0 21,900 4.0 -2.5

5. Analytical Trim (Simplified) 1.0 - 11.2 -5.6 1.6 - 5.4 -2.5 2.0 - 3.5 -1.9

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