| 摘要 |
1,057,591. Controlling guided missiles. SOC. ANON. DE TELECOMMUNICATIONS. Feb. 26, 1964 [Feb. 27, 1963], No. 7903/64. Heading B7G. [Also in Divisions G3 and H4] Relates to a system incorporating an automatically rotating missile (A, Fig. 1) in which system a photo-electric direction finder at a ground station (B) determines the departure of the missile from a reference axis and transmits " command " signals to the missile to direct the latter on to the reference axis. According to the present invention the polar co-ordinates of the missile relative to the reference axis are cyclically detected in synchronism with the rotation of the missile utilizing signals sent by the missile and the command signals are sent to the missile at instants corresponding to a predetermined angular position of the missile relative to its rotational axis. In the embodiment the reference axis is the optical axis (X X) which may be that pointing to a target. Infrared radiation from the missile is imaged on to an obturator (6, Figs. 1, 2) which is rotated by cranks (7, 8) driven by a motor (14), the centre of the obturator following a path coinciding with the edge of a circular window (4). The amplified output of a photo-cell (2) is fed via an amplitude limiter to a frequency discriminator (18). A bridged-T phase equalizer (20) is provided, controlled by a torque motor (22) as a function of the angular velocity of the missile about its axis (Fig. 5). The motor (14) also drives signal generators (26 and 27). the latter producing an output frequency which is an integral multiple of that of the former which feeds a frequency discriminator (28) controlling the torque motor (22), whereby time lags are compensated. The output of a signal generator (26) is fed to trigger circuits (32a, 32b), the other inputs to which are the synchronizing signal emitted by the missile. The trigger circuit outputs are mixed and fed to the obturator motor (14). In the initial stages of missile motion its rotational velocity may vary; a temporary programmed control (36) is provided such that the speed of the obturator motor (14) follows the variations in the rotational speed of the missile. To prevent jamming or to increase signal/noise ratio the missile may transmit to the photo-cell signals modulated at a frequency other than that given by the obturator (6): in this event an amplifier and detector are inserted at the output of an amplifier (15). The command signals transmitted to the missile may be square-wave signals. |
