科研之友
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摘要
A nonlinear three-dimensional all-aspect guidance problem of an acceleration-constrained missile is dealt with. The feedback linearization method is applied to derive a three-dimensional guidance law, which enables the missile to intercept a maneuvering target under all-aspect initial boresight and heading conditions. The new guidance law is characterized by convergence to a collision course. It is shown that the proposed guidance law enables interception where the proportional navigation and the augmented proportional navigation guidance laws fail. Simulations demonstrate that the proposed law has the capability to perform several interception trials.
- 出版日期2015-12
