An adaptive guidance approach for spinning projectiles

2004-01-01
Calise, Anthony J.
El-Shirbiny, Hesham A.
Kim, Nakwan
Kutay, Ali Türker
Previous work1 has shown a significant potential for improving the accuracy of direct fire spinning projectiles through the implementation of aerodynamic control. A guidance law optimized for this application was developed. Further research has shown that the guidance law cannot adjust quickly enough to accommodate actuator nonlinearities and uncertainties. Of particular interest is the use of miniature synthetic jets, which achieve a control force by interacting with the flow. The full model of such actuators might not be completely known leading to decreased controlled system performance. Actuator induced moment effect causes amplification or attenuation of the control force depending on the moment direction causing increased target misses and peak control force. Wind disturbances are expected to cause further performance degradation. We describe and provide a preliminary evaluation of a method of dealing with these problems by augmenting the guidance law with an adaptive controller. Copyright © 2004 by Georgia Institute of Technology.
AIAA Guidance Navigation and Control Conference and Exhibit

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Citation Formats
A. J. Calise, H. A. El-Shirbiny, N. Kim, and A. T. Kutay, “An adaptive guidance approach for spinning projectiles,” Providence, Rhode Island, 2004, vol. 5, Accessed: 00, 2020. [Online]. Available: https://hdl.handle.net/11511/56318.