Title:
MISSILE GUIDE SYSTEM AND MISSILE GUIDE METHOD
Document Type and Number:
Japanese Patent JP2014126355
Kind Code:
A
Abstract:
PROBLEM TO BE SOLVED: To solve a problem that there is a possibility that an oscillation angle of a missile deviates from or exceeds an oscillation possible range for maintaining a lock-on state, and lock-off is made when thrust for terminal guidance is generated in a multi-pulse type (a plurality of pulses) missile.SOLUTION: In a multi-pulse type missile, time from lock-on to terminal guidance start is effectively used, an attitude angle is gradually changed with the usage of a rotor blade of the missile during a period from lock-on to terminal guidance start, and the attitude angle facing a target direction can be secured in the terminal guidance start. A missile guide system for achieving the enhancement includes an error calculation means for calculating heading error quantity of the missile during the period from lock-on to terminal guidance start, an attitude control means for securing the attitude angle in accordance with the calculated heading error quantity and shifting to terminal guidance in the state of maintaining the attitude angle, and an acceleration thrust generation means for generating thrust for terminal guidance.
Inventors:
ANDO KEISUKE
SERA YOSHIHIRO
FURUYA SHOJIRO
SERA YOSHIHIRO
FURUYA SHOJIRO
Application Number:
JP2012286020A
Publication Date:
July 07, 2014
Filing Date:
December 27, 2012
Export Citation:
Assignee:
MITSUBISHI HEAVY IND LTD
International Classes:
F42B15/01; F42B10/66
Domestic Patent References:
| JPH02279995A | 1990-11-15 | |||
| JP2011242105A | 2011-12-01 | |||
| JP2008280967A | 2008-11-20 |
Attorney, Agent or Firm:
Minoru Kudo
Keisaku Nakao
Keisaku Nakao