Splitter plates for alleviation of missile hook drag.

摘要

The overall drag upon a missile body after launch can be reduced and hence the range and average speed of the missile increased by reducing the aerodynamic drag at supersonic velocities attributable to missile hooks (10) which are normally used to attach and launch the missile body from a launcher assembly. After launch a pair of splitter plates (20, 22) are popped up into a position next to each missile hook (10). One splitter plate (20) is positioned in front of the missile hook (10) and a second splitter plate (22) positioned behind the missile hook. The splitter plates are generally planar and arranged so that their planar surfaces are approximately parallel to the fore and aft direction of the missile body (34). In the illustrated embodiment, the splitter plates are erected into an operative configuration with respect to their missile hooks by rotating each splitter plate about a hinge line (36). The splitter plate is biased to assume the erect configuration by means of a torsion spring (42). An electromechanical latch (58) maintains the splitter plates (20, 22) in a folded configuration against the missile body (34) until the missile body has cleared the launch assembly. Thereafter the latch (58) releases the splitter plates (20, 22) allowing the torsional spring (42) to rotate each splitter plate (20, 22) into an operative configuration. Upon full erection of each splitter plate, each splitter plate is mechanically locked into the erect configuration. In one embodiment a fifty percent reduction in the drag coefficient is realized at supersonic velocities as a result of the splitter plates.