FIELD: armament, in particular, guided missiles.
SUBSTANCE: the guided missile has a body with on-board systems, frame with drive shafts made with journals, with air vanes hinge-installed in their end face grooves for folding in the body and fixation in the unfolded position. The guided missile is provided with control-surface deflection transducers and a printed circuit board secured through an insulator on the front end face of the frame and connected by means of a bundled conductor to the on-board systems of the guided missile.
EFFECT: reduced spread in the value of the sweep angle of the air vanes in the process of manufacture.
2 dwg
Title | Year | Author | Number |
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CONTROLLED PROJECTILE, STEERING DRIVE GROUP OF CONTROLLED PROJECTILE, PNEUMATIC DISTRIBUTION DEVICE OF STEERING DRIVE OF CONTROLLED PROJECTILE, MECHANISM OF INITIATION OF STEERING DRIVE OF CONTROLLED PROJECTILE | 2017 |
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METHOD FOR DETERMINATION OF AERODYNAMIC CHARACTERISTICS OF GUIDED MISSILE IN FLIGHT, METHOD FOR DETERMINATION OF ANGLE OF ATTACK OF MISSILE IN FLIGHT, METHOD FOR DETERMINATION OF MISSILE ATTITUDE AND DEVICES FOR THEIR REALIZATION | 2002 |
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RU2218550C2 |
Authors
Dates
2005-01-20—Published
2003-07-08—Filed