Guided missile

Abstract

Abstract PURPOSE: To enhance motion performance and aerodynamic stability while preventing mechanical interference with a mother machine by incorporating stabilizer fins in the body of a guided projectile and developing the fins by a torsional torque stored in a spiral spring with a specified time lag after launching through a locking unit-comprising a powder of time prolonging compound and output compound and a gas cylinder. CONSTITUTION: Torsional torque stored in a torsion bar 8 acts to develop stabilizer fins 3 through bevel gears 9, 10 and gears 12, 13 but it is blocked by a locking unit 7 and the fins 3 are retained in a contained state. When a body 1 is launched from an aircraft, an ignition plug 18 fires a time prolonging compound 19 based on an electric signal at the time of launching and the time proloning compound 19 fires an output compound 20 upon elapsing a specified combustion time. A piston 15 enters into ascending motion at that moment by the pressure of a large quantity of combustion gas generated from the output compound 20 and it is drawn out by a hole 16 made in the stabilizer fin 3. Since the quantity of the time prolonging compound 19 is selected, the fins are developed with a specified time lag after a projectile is launched from a mother machine.

Inventors

• 👤 Ichiji Nishimura

Bibliographic Details