Patent GB-945613-A (GB)
Title: Improvements in guidance systems for missiles and other moving bodies
Inventor: SENDLES JOHN LEONARD
IPC: F41G7/30
Filed: 1960-02-23
Abstract: 945,613. Radar missile guidance; multiplex pulse signalling. SHORT BROS. & HARLAND Ltd. Feb. 13, 1961 [Feb. 23, 1960], No. 6401/60. Headings H4D and H4L. In a command missile guidance system a directional ground pulse radar transmitter 14 automatically locks on to a moving target 13 and echoes therefrom are received by a conical scan radar receiver 11 in the nose of the missile 12 whose scan axis is stabilized in space and which produces a scan frequency A.C. signal whose phase relative to a reference signal is indicative of the angular deviation of the target from the space stabilized conical scan axis, said signals being transmitted to a ground control station by a radio data link to produce on a C.R.T. a visual display of the pitch and yaw components of said angular deviations which are observed by a human operator who generates corresponding rate control signals which are transmitted to the missile by a radio command link to maintain the missile on an interception path. At the missile, Fig. 2 (not shown), the aerial of the radar receiver 11 comprises an offset dipole in a paraboloidal reflector which is rotated about its axis to effect conical scanning and the reference signal comprises a pulse train synchronized with the rotation. The echo pulses are gated by strobe pulses derived from pulses received directly from the ground radar transmitter 14 by means of a variable delay automatically controlled by a discriminator and integrator which produces a D.C. voltage approximately proportional to the range of the target from the missile. The A.C. deviation signal is combined with three pulses whose amplitudes and phases represent respectively (1) the scan frequency reference signal; (2) the target range; and (3) voltage and time references and the resultant complex signal frequency modulates a sub-carrier which amplitude modulates the main carrier of the data link transmitter 15. At the ground control station, Fig. 3 (not shown), the complex data signal received by the data link receiver 16 is detected and the A.C. deviation signal is applied to a phase detector together with the scan frequency reference to produce yaw and pitch deviation signals which are applied to the x and y plates of a C.R.T. The operator generates corresponding deviation signals by means of a joystick control 20 and these are applied together with the range data derived from the complex data signal to a shaping unit 21 which simulates the missile aerodynamic and prinematic characteristics and produces corresponding yaw and pitch rate control signals which are applied to a sub-modulator unit to produce recurrent groups of four sequential sub-carrier oscillations, the magnitude and sign of a control signal being represented by the relative duration of the corresponding pair of oscillations, these sub-carrier oscillations being then amplitude modulated on to the main carrier of the command link transmitter 22. At the missile the command transmission is received by a command link receiver 23 and demodulated to give D.C. yaw and pitch rate control signals which actuate corresponding control surfaces. The missile also includes means for automatically stabilizing its roll attitude and for damping weathercock oscillations to improve its aerodynamic response to the control signals.