A folding wing structure for improved missile aerodynamic performance and manuverability with a minimum payload space requirement which comprises a leading edge spar and at least one trailing edge spar spaced apart from each other by a plurality of transverse ribs, the spars being approximately parallel to each other with the ribs positioned along the spars to divide the structure into a series of parallelograms. The spars and ribs are pivotally joined together with the spars being further pivotally joined to an air frame of an aerodynamic vehicle or missile. In a folded position the spars and rib structure collapse to occupy a minimal amount of volume in a recessed area of the air frame. A spring or piston member secured to at least one, spar forces the spars apart and out from the fuselage to an erected wing position at predetermined sweep angles relative to the fuselage.
An aerodynamic lifting and control surface comprising an external box structure that encloses an internal grid whose members are parallel to the box structure. The external box structure comprises four panels connected at their comers by spring hinges. When the hinges are unconstrained, the external box structure is compressed into a flat, thin parallelogram shape. The internal grid comprises a plurality of plates connected to each other and to the external box structure by flexible hinges. Control apparatus for use with an aerodynamic vehicle is also disclosed. The control apparatus comprises at least one aerodynamic lifting and control surface that is coupled to an actuator disposed within the vehicle and connected to the aerodynamic lifting and control surface for rotating it.
Pairs of aerofins used for stabilization and control of missile flight are deployed through shared longitudinal slots provided in the missile body. Before launch, the pairs of aerofins, each pair comprised of a canard and a deflector, are retained in a folded position by a releasable latch mechanism within the missile body. The deflectors are mounted in a laterally displaced position from the longitudinal slots and are constrained from sliding into alignment with the slots by the presence of the folded canards. When the canards are released by the latch mechanism and permitted to extend outward to their deployed positions, the deflectors are able to laterally shift, effectively displacing the canards in the alignment position and subsequently deploying. The latch mechanism is designed to simultaneously release all the canards following missile launch, with biasing torsional springs operating to urge the canards outward through the associated slots to the extended position upon release. The deflectors are also provided with biasing springs, with these springs providing not only torsional force for urging the deflectors outward, but also compressional force to effect the lateral shifting of the deflectors. The latch mechanism is activated by an actuation mechanism when the missile has cleared the launch tube or other launch facility.
