- 一般社団法人 日本航空宇宙学会
- 日本航空宇宙学会論文集 (ISSN:13446460)
- vol.52, no.605, pp.280-288, 2004 (Released:2004-06-30)
This paper presents a new guidance law for a missile with varying velocity against a maneuvering target with a constant acceleration. Since an approximate missile velocity change during boost phase or after thrust cutoff can be calculated, the intercept point can be estimated if the target acceleration is measured. The guidance law presented guides the missile to the point directly. The guidance law is constructed by combining augmented proportional navigation and pure pursuit navigation with some mixture ratio. From some simulations, it is found that the guidance law presented is more effective and has the higher off-boresight ability and the smaller lateral divert requirements than conventional augmented proportional navigation or proportional navigation even if there exist the LOS angle noises.