초록 ▼

A multiposition folding control surface for missiles designed to provide improved launch stability therefor. The control surface can be folded in one of two positions depending upon size and stability requirements, a first folded position for compact carriage with minimal stability requirements, and

A multiposition folding control surface for missiles designed to provide improved launch stability therefor. The control surface can be folded in one of two positions depending upon size and stability requirements, a first folded position for compact carriage with minimal stability requirements, and a second folded position for a less compact carriage with added stability requirements. The multiposition folding control surface comprises a spindle fitting which is attached to the missile, and which is rotatably controlled by a flight control actuator. A center fitting is hingedly attached to the spindle fitting, and provides a nonactuated folding of the center fitting to accommodate more compact missile storage in a shipping container. An actuator housing is hingedly attached to the center fitting, and provides the major aerodynamic surfaces for the control surface. An actuated hinged linkage is attached to the actuator housing, and has an anchor link, one end of which can be attached by a release pin to either the center fitting to provide the first folded position, or the actuator housing to provide the second folded position, depending upon which of the first and second fold positions is selected. A power actuator is provided for powering the actuated hinged linkage, and uses the same power stroke to deploy the actuator housing from either of the first or second folded positions to a fully deployed and extended flight position.

대표청구항 ▼

[ What is claimed is:] [1.] A multiposition folding control surface for missiles designed to provide improved launch stability therefor and which can be folded in one of two positions depending upon size and stability requirements, a first folded position for compact carriage with minimal stability

[ What is claimed is:] [1.] A multiposition folding control surface for missiles designed to provide improved launch stability therefor and which can be folded in one of two positions depending upon size and stability requirements, a first folded position for compact carriage with minimal stability requirements, and a second folded position for a less compact carriage with added stability requirements, comprising:a. a spindle fitting which is attached to the missile and is rotatably controlled by a flight control actuator;b. a center fitting attached by a hinge means to the spindle fitting and providing a nonactuated folding of the center fitting to accommodate more compact missile storage in a shipping container;c. an actuator housing attached by a hinge means to the center fitting and providing the major aerodynamic surfaces for the control surface;d. an actuated hinged linkage attached to the actuator housing and having an anchor link, wherein one end of the anchor link can be attached by a release pin to either the center fitting to provide the first folded position or the actuator housing to provide the second folded position, depending upon which of the first and second fold positions is selected; ande. a power actuator for actuating the actuated hinged linkage and using the same power stroke to deploy the actuator housing from either of the first and second folded positions to a fully deployed and extended flight position.