초록 ▼

An improved missile tail fin assembly. The missile utilizes four tail fin assemblies, each assembly comprising a fitting having three locking portions, each of which comprises a gudgeon having a pair of locking teeth, and a fin having mating recesses for the locking portions. A portion of the materi

An improved missile tail fin assembly. The missile utilizes four tail fin assemblies, each assembly comprising a fitting having three locking portions, each of which comprises a gudgeon having a pair of locking teeth, and a fin having mating recesses for the locking portions. A portion of the material associated with recesses of the two forward locks of each fin is removed, leaving clearances which permit limited rotation about the fin pivot axis in one direction only. When the fin is loaded in a direction to produce clockwise torque, all three locks which form the lock assembly are loaded approximately equal and this locates the elastic axis of the tail lock approximately just aft of the center of pressure which produces a small increase in cant angle with load. When the tail fin is loaded in the direction to produce a counterclockwise torque, the aft lock of the assembly will take all the torque. This moves the elastic axis further aft thus producing a larger increase in cant angle with load. The difference of these two changes in cant angle will be a net torque in the counterclockwise direction. When the deflection at the two forward lock positions reaches the clearance limit, all three locks will pick up the load and the surface will have the same stiffness as an unmodified tail fin.

대표청구항 ▼

A missile tail fin assembly for maintaining the roll rate of the missile within a predetermined range independent of variations in missile angle of attack comprising: at least one pivotably mounted tail fin; a fixture provided on the aft portion of said missile, said fixture including a plurality of

A missile tail fin assembly for maintaining the roll rate of the missile within a predetermined range independent of variations in missile angle of attack comprising: at least one pivotably mounted tail fin; a fixture provided on the aft portion of said missile, said fixture including a plurality of members extending therefrom and including a key-shaped portion formed on each said member for engaging an associated fin; a set of complementary notches formed on said fin and arranged to receive the key-shaped portions when the fin is in a predetermined angular position extending outwardly from the fixture, said notches being located at various positions along the fin forward and rearward, respectively, of a center line of the fin, at least the most rearward notch being shaped to lock the key-shaped portion received therein in a fixed angular position and the notches forward of the most rearward notch being shaped with predetermined cutout portions to permit limited torsional distortion of the fin relative to said predetermined angular position under the influence of lateral aerodynamic forces for missile flight angles of attack within a preselected range; and a hinge pin mounted on said fixture; the fin being folded in against the fixture before launch and being directed outward after launch, said key-shaped portions being received by said fin notches and thereby locking said fin into position for limited torsional distortion. The tail fin assembly as defined in claim 1 wherein said notches are shaped by milling a wedge-shaped portion of material from opposite sides of said notch.