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Title:
GUIDED MISSILE
Document Type and Number:
Japanese Patent JPH07103696
Kind Code:
A
Abstract:

PURPOSE: To improve tracking, guiding capacity of a guided missile by preventing saturation of a sensor due to introduction of a solar light to an optical sensor, variably setting a solar light inhibit angle according to a state of a weather, and so flying the missile as to eliminate introduction of a solar light within the inhibit angle.

CONSTITUTION: Effective and reactive solar inhibit angle are previously set to a solar light inhibit angle setter 17 according to a state of a weather, a daytime, a night, etc., and a direction of an optical sensor 1 and a flying route are so controlled by an orbit correction signal generator 18 as not to introduce a solar light into the inhibit angle of the sensor 1 when the inhibit angle is to be effective. Simultaneously, even when the solar light is incident on the sensor 1, if a reception level of the sensor 1 exceeds a redetermined level, a flying route is steered to a route in which the light is not incident on the sensor 1 by a bias signal generator 13.


Inventors:
TORIKAI KAZUO
KIMOTO KENJI
Application Number:
JP25328393A
Publication Date:
April 18, 1995
Filing Date:
October 08, 1993
Export Citation:
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Assignee:
MITSUBISHI ELECTRIC CORP
International Classes:
B64C13/18; F42B15/01; G01S3/782; G05D1/10; G05D1/12; F41G7/22; (IPC1-7): F41G7/22; B64C13/18; F42B15/01; G01S3/782; G05D1/10; G05D1/12
Attorney, Agent or Firm:
Takada Mamoru