| 摘要 |
The invention relates to a wing or fin deploying mechanism for a vehicle, particularly a box launched missile, having awing or fin in a retracted position prior to launching, said wing or fin 10 being pivotally movable about a pivot axis 12 from a retracted position to a deployed position by a drive means 15 which includes a pivoting member 16 connected to the wing or fin 10 at a point 17 displaced from the pivot axis 12, the other driving end 19 of the pivoting member 16 is moved through an arc so that the wing or fin is initially accelerated and then decelerated before reaching its final deployed position, a line 31 is fastened to the launcher, the other end passing around a drum 32 so that the drum 32 rotates to provide the wing or fin deploying driving force upon launching of the vehicle, stop means 26, 27 preventing reverse movement of the wing or fin from its deployed position, and the kinetic energy in the mechanism is allowed to dissipate due to friction by having the drive disengage. <IMAGE> |
