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Limit Cycle in the Longitudinal Motion of the USB STOL ASKA - Control System Functional Mockup and Actual Aircraft
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Abstract
The Japanese Quiet Short Take Off and Landing experimental aircraft named ASKA was developed and flight tested during 1977 till 1989. The control system hard and software were examined by the functional mock-up with using the actual hardware. The small longitudinal limit cycle was observed in the closed loop test when the Pitch Control Wheel Steering software was on in the mock-up testing. In this paper, first, the method to analyze and to expect the limit cycle based on the describing function was shown. The limit cycle was induced due to the nonlinearities in the automatic control mechanism. The nonlinearities in the hardware were examined to make the model to simulate the system on the computer. The method was shown effective to predict the limit cycle in the mock-up. Second, with using the flight measured dynamics, the limit cycle was concluded as on border line between existing and not, which coincides with the actual flight result. The functional mock-up and the describing function method can provide an accurate prediction of the limit cycle in the actual aircraft.
Authors
- Hiroyuki Yamato
- Tadao Uchida - National Aerospace Lab.
- Noriaki Okada - National Aerospace Lab.
- Toshio Ogawa - National Aerospace Lab.
- Akira Tada - National Aerospace Lab.
- Isoroku Uchikawa - Kawasaki Heavy Industries, Ltd.
- Youichi Takesue - Kawasaki Heavy Industries, Ltd.
- Takashi Tsujimoto - Kawasaki Heavy Industries, Ltd.
Topic
Citation
Yamato, H., Uchida, T., Okada, N., Ogawa, T. et al., "Limit Cycle in the Longitudinal Motion of the USB STOL ASKA - Control System Functional Mockup and Actual Aircraft," SAE Technical Paper 921040, 1992, https://doi.org/10.4271/921040.Also In
References
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