Title:
SPEED REDUCING STEERING DEVICE FOR MISSILE
Document Type and Number:
Japanese Patent JPH04316997
Kind Code:
A
Abstract:
PURPOSE: To permit the reduction of a flying speed without generating any lift on a missile.
CONSTITUTION: A missile 1 is provided with a pair of steering wings 2, 2 so as to be symmetrical with respect to the axis of the fuselage and two sheets of the steering wing 2, 2 are steered into opposite directions to cancell lifts and generate only resistances. According to this method, the flying speed of the missile 1 can be reduced without effecting any lateral motion.
Inventors:
SHIRAISHI HITOSHI
Application Number:
JP8522891A
Publication Date:
November 09, 1992
Filing Date:
April 17, 1991
Export Citation:
Assignee:
MITSUBISHI HEAVY IND LTD
International Classes:
B64C13/18; F42B10/48; F42B10/64; (IPC1-7): B64C13/18; F42B10/48; F42B10/64
Attorney, Agent or Firm:
Ishikawa Arata