Aeronautics and astronautics – Missile stabilization or trajectory control – Automatic guidance
Patent
1996-03-01
1997-01-28
Lobo, Ian J.
Aeronautics and astronautics
Missile stabilization or trajectory control
Automatic guidance
244 315, 244 319, F41G 724
Patent
active
055971369
ABSTRACT:
A method for the independent control of a guidable flying body that is provided with a warhead and to an arrangement for implementing the method.
The method resides in that the flying body flies on a curved flight path during its flight approach phase and, on the curved flight path, the ratio S/C between the signals S reflected by the ground target and the clutter C of the ground, on the average, is kept constant or at least approximately constant. The path vector of the flying body during the subsequent target approach phase is oriented in the direction of the ground.
The arrangement is configured in such a that an antenna array constructed of transmitting and receiving antennas is configured as a rigid component group that is fixed to the flying body and is switched to act on a transmit/receive unit, or a transmit/receive unit composed of light source(s) and detectors and operating on an optical basis is configured as a rigid component group that is connected with the flying body and the detectors are switched to act on an evaluation unit.
REFERENCES:
patent: 4614317 (1986-09-01), Stavis
patent: 4796834 (1989-01-01), Ahlstrom
patent: 5088659 (1992-02-01), Neff et al.
Deutsche Aerospace AG
Lobo Ian J.
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