Missile guidance system
AssigneeThomson-CSF
InventorRemy Tabourier
Life of this patent
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Abstract
The invention relates to missile-guidance systems of the semi-active homing type using the Doppler effect, designed for air-to-air, ground-to-air or ship-to-air installations. On the radar installation, a first illuminator comprising a directional antenna illuminates a target with a wave of first frequency F.sub.1. The wave reflected by the target is picked up by an antenna situated at the front of the missile. A second illuminator comprising a wide-beam antenna illuminates an antenna situated at the rear of the missile with a continuous wave of second frequency F.sub.2 coherent with the wave of frequency F.sub.1. The local oscillator in the receiver of the missile is phase-controlled in dependence upon the continuous wave of frequency F.sub.2.
Claims6
In a guidance system for a self-propelled and self-steered missile provided with a rear antenna and a front antenna, in combination:
- a radar station including a pilot oscillator, a first illuminating transmitter coupled to a first antenna and to said pilot oscillator through a first frequency-multiplying circuit to produce a target-illuminating signal at a first frequency F.sub.1, and a second illuminating transmitter coupled to a second antenna and to said pilot oscillator through a second frequency-multiplying circuit to produce a rear reference continuous-wave signal for the missile at a frequency F.sub.2 different from F.sub.1 ;
- a receiver aboard said missile coupled to said front antenna, a front local oscillator connected to said receiver, a rear local oscillator phase-controlled by the continuous wave received by the rear antenna, and phase-control means comprising a frequency multiplier for controlling the frequency and the phase of said front local oscillator by said rear local oscillator;
- and
- flight-control means aboard said missile connected to said receiver for directing the missile toward the target.
In a guidance system for a self-propelled and self-steered missile provided with a rear antenna and a front antenna, in combination:
- a radar station comprising a pilot oscillator, a first illuminating transmitter coupled to a directional antenna pointed toward a target and to said pilot oscillator through a first frequency-multiplying circuit to produce a target-illuminating signal at a first frequency F.sub.1, and a second illuminating transmitter coupled to a wide-beam antenna mechanically integral with the directional antenna and pointed in the same direction and to said pilot oscillator through a second frequency-multiplying circuit to produce a rear reference continuous-wave signal for the missile at a frequency F.sub.2 different from F.sub.1 ;
- a receiver aboard said missile coupled to said front antenna, a front local oscillator connected to said receiver, a rear local oscillator phase-controlled by the continuous wave received by the rear antenna, and phase-control means comprising a frequency multiplier for controlling the frequency and the phase of said front local oscillator by said rear local oscillator;
- and
- flight-control means aboard said missile connected to said receiver for directing the missile toward the target.
Dependencies are inferred from the claim text.