| Year of publication |
2003 |
| Category |
Int. Conference |
| Subject |
|
| Title |
Optimal Guidance with Constraints on Impact Angle and Terminal Acceleration |
| Author |
Yong-In Lee, 유창경, Eulgon Kim |
| Journal title |
Proceedings of the 2003 AIAA Guidance, Navigation, and Control Conference and Exhibit, AIAA 2003-5795 |
| Publication date |
Aug. 11-14, 2003 |
| Volume & Other data |
|
| Abstract |
Numbers of impact angle guidance laws have been studied in order to satisfy the flight path angle constraint on each waypoint that unmanned aerial vehicles for reconnaissance should pass by, or to increase the warhead effect for anti-ship or anti-tank missles. These guidance laws converge to a finite value as the missle approaches to the target so that sometimes maneuver acceleration can easily be saturated in real situation. The saturation of maneuver acceleration in terminal phase may cause large miss distance and impact angle error. In this paper, an optimal guidance law with the capacity of adjusting terminal maneuver acceleration is studied to for deriving closed-form state feedback guidance law. Since the proposed guidance law is able to nullify the maneuver acceleration at impact instant, not only it is robust to disturbance or uncertainties in terminal phase, but also the performances of terminal miss due to command saturation to prevent strucural failure or flight instability is improve. |
| Keywords |
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| Issn Number |
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| Link |
 http://arc.aiaa.org/doi/abs/10.2514/6.2003-5795 [626] |
