发明名称 CONTROL METHOD OF SEEKER FOR MISSILE
摘要 <p>PURPOSE:To effect lock-on operation for a target without limiting any flight of a master plane. CONSTITUTION:The helmet of a pilot is equipped with a gyro 2a to send the direction of the sight line of the pilot to a master plane controller 1a to move an oscillating angle of a seeker 3a in conjunction with the flight data and the line of sight through the controller 1a. According to this method, lock-on operation for a target can be effected regardless of the attitude of the master plane.</p>
申请公布号 JPH05264200(A) 申请公布日期 1993.10.12
申请号 JP19920063241 申请日期 1992.03.19
申请人 发明人
分类号 B64D47/00;F41F3/06;F41G7/22;F42B15/01;G01S13/88;G05D1/12;(IPC1-7):F42B15/01 主分类号 B64D47/00
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