| 摘要 |
PROBLEM TO BE SOLVED: To obtain a controller of missile, which controls the airframe without conducting aerodynamic control. SOLUTION: This controller comprises a front guidance control computer 36, front and rear thrust-generators 37, and 38, a rear guidance control computer 40, a rear thrust-generator 41, and a maneuver computer 39. The computer 36 outputs a thrust command in response to a fed-back airframe acceleration and angular velocity. The front and rear thrust generator 37, 38 output respectively a pitch-thrust acceleration and yaw-thrust acceleration in response to the thrust command from the computer 36. The computer 40 outputs a thrust command in response to a fed-back airframe acceleration and an angular velocity. The generator 41 outputs a roll thrust acceleration in response to a thrust command from the computer 40. The computer 39 converts the thrust and momentum generated in the airframe to an airframe acceleration and an angular velocity and feeds back the converted values to the computers 36 and 40 respectively.
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