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- W2260698723 abstract "Mathematical models and implementation issues are described for simulations developed in the active flexible wing wind tunnel test program, which resulted in successful application of active flutter control. The wind tunnel test program required a truth batch simulation for off-line tests of proposed control designs and functional, hot-bench tests of digital controller hardware and software. To provide the hot-bench test environment, a real-time simulation of the wind tunnel model and test environment was desired. Although mathematical model complexity and computing power limitations prevented attainment of real-time operation, essential test goals were met with a hot-bench simulation running at a timescale ratio no slower than 1:5. To achieve the required timescale, model reduction methods were applied to the aeroservoelastic portion of the full-order mathematical model. The reduction method was based on the internally balanced realization of a linear dynamic system. The error-bound properties of the internally balanced realization contributed to the method utility in the model reduction process. The state dimensions of the aeroservoelastic model were reduced by a factor of 2. The errors due to reduction appeared beyond the 10th bit of the analog-to-digital converters for all 560 combinations of simulation inputs and outputs." @default.
- W2260698723 created "2016-06-24" @default.
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- W2260698723 date "1996-04-01" @default.
- W2260698723 modified "2023-09-27" @default.
- W2260698723 title "Aeroservoelastic Simulation of an Active Flexible Wing Wind Tunnel Model" @default.
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