제어로봇시스템학회:학술대회논문집
- 2001.10a
- /
- Pages.125.2-125
- /
- 2001
Trajectory Optimization in Consideration of Inertial Navigation Errors
- Ryoo, Chang-Kyung (Agency for Defense Development) ;
- Kim, Jong-Ju (Agency for Defense Development) ;
- Cho, Hang-Ju (Agency for Defense Development)
- Published : 2001.10.01
Abstract
Inertial navigation error is the major source of miss distance when only the inertial navigation system is used for guidance, and tend to monotonically increase if the flight time is small compared to the Schuler period. Miss distance due to these inertial navigation errors, therefore, can be minimized when a missile has the minimum time trajectory. Moreover, vertical component of navigation error becomes null if he impact angle to a surface target approaches to 90 degrees. In this paper, the minimum time trajectories with the steep terminal impact angle constraint are obtained by using CFSQP 2.5, and their properties are analyzed to give a guideline for he construction of an effective guidance algorithm for short range tactical surface-to-surface missiles.
Keywords