| 摘要 |
PURPOSE:To make a computer exclusive for high speed unnecessary, produce a guiding device for a missile inexpensively and permit the intertia guidance of the missile by a method wherein the guiding device is provided with a detecting means, in which a seeker axis is stabilized in space from the time of launching while the attitude angle of the missile is detected even during flying utilizing an angle between the seeker axis and the fuselage of the missile. CONSTITUTION:Upon launching, a target angle lambdaT and the attitude angle theta0 of a missile, which are seen from the point of launching, are inputted from external sources into a signal processing computer 10. Simultaneously with the launching, a switch 11 is set at a position 1 by a sequence signal Sc1 from the signal processing computer 10. According to this setting, a seeker axis becomes a mode stabilized in space. After launching, the signal processing computer 10 monitors an angle lambdaM between the seeker axis and the axis of a fuselage at all times. Since the initial value of the angle lambdaM is lambdaC, the changing amount of the attitude angle during flying becomes DELTAtheta=lambdaM-lambdaC. The signal proceeding computer 10 outputs a steering signal deltac utilizing the angle theta while the signal is transmitted to a steering device 6 through another switch 12 whereby the inertia guidance of the missile may be effected. When the missile approaches a target, sequence signals Sc1, Sc2 are sent to the switches 11, 12 by the signal processing computer 10 whereby the guiding mode of the missile becomes homing guidance mode. |
