Detachable thrust vector mechanism for an aeronautical vehicle

Abstract

A relatively inexpensive, high efficiency, detachable thrust vector mechanism is provided for addressing the current shortcomings in the art. In the illustrative embodiment, the invention is used in conjunction with a nautical or aeronautical vehicle having primary propulsion means and at least one fin movable, to provide maneuverability, in response to a conventional control system. The invention is a detachable thrust vector mechanism comprising auxiliary propulsion means pivotally attached to the missile through connecting means. Contact means are provided for transferring bi-directional motion of the fin to the auxiliary propulsion means. The mechanism is operable to provide auxiliary thrust for the missile along a thrust vector determined by the control system. The invention is effective to provide missile steerage at low speeds, particularly during initial launch and pitchover. The mechanism of the present invention falls away during flight to fully exploit the original optimized aerodynamic or hydrodynamic design of the missile. The thrust vector mechanism of the present invention conserves the main motor fuel, reduces the initial missile launch signature and effectively increases its range. The invention also provides a low cost, disposable mechanism for converting a missile designed for high speed (air-to-air) launches to one adapted for low speed (surface) launches. That is, under the teachings of the present invention, existing missiles may be inexpensively retrofit to provide thrust vector control.

Dependencies are inferred from the claim text.