초록 ▼

A speed brake apparatus reduces the airspeed of an aircraft by increasing aerodynamic drag. First and second brake panels are located on opposite sides of a portion of the aircraft, such as the fuselage, and are adapted to swing outward about a downstream hinge axis into deployed positions extending

A speed brake apparatus reduces the airspeed of an aircraft by increasing aerodynamic drag. First and second brake panels are located on opposite sides of a portion of the aircraft, such as the fuselage, and are adapted to swing outward about a downstream hinge axis into deployed positions extending into the air stream. The panels are controlled by an operating device that includes a linear actuator. The actuator moves an operating head connected to a pair of toggle assemblies to convert linear movement of the operating head to the deployment and retraction movement of the brake panels.

대표청구항 ▼

1. A speed brake apparatus for reducing the airspeed of an aircraft by increasing aerodynamic drag, comprising: an operating head adapted for linear movement generally parallel to an axis of a fuselage of the aircraft,a pair of brake panels mounted on opposites sides of portion of the aircraft, the

1. A speed brake apparatus for reducing the airspeed of an aircraft by increasing aerodynamic drag, comprising: an operating head adapted for linear movement generally parallel to an axis of a fuselage of the aircraft,a pair of brake panels mounted on opposites sides of portion of the aircraft, the panels being operatively associated with the operating head so as to swing outwardly in opposite directions generally about their downstream end portions, between a retracted position, to a deployed position in which the panels project outward into the air stream, anda toggle mechanism associated with each brake panel and operatively connecting the associated brake panel to the operating head and a support structure such that linear movement of the operating head causes the panels to move between the retracted and deployed positions, said toggle mechanism including a control link and a carrier link, said control link being pivotally attached, at one end, to said support structure at a fixed joint and, at the other end, being pivotally secured to a first end of the carrier link at a pivot joint, said carrier link having a second end connected to the operating head at a hinge joint, wherein a first distance, extending from the fixed joint to the pivot joint, is generally equal to a second distance, extending from the pivot joint to the hinge joint, wherein the panel has an aerodynamic center, and wherein the aerodynamic center is disposed at an intersection of a line that is an extension of the carrier link and a line that extends through the fixed joint and perpendicular to the axis. 2. The speed brake apparatus as defined in claim 1, wherein each brake panel is mounted on one of the carrier links. 3. The speed brake apparatus as defined in claim 1, further comprising a linear actuator that is operatively coupled to the operating head and adapted to move the operating head linearly back and forth along the axis of the fuselage. 4. The speed brake as defined in claim 3, wherein the linear actuator includes a cylinder and piston, said cylinder being attached to the support structure and said piston including a piston rod, and wherein the operating head is at a free end of the piston rod. 5. The speed brake apparatus as defined in claim 1, wherein each brake panel is mounted on one of the carrier links. 6. The speed brake apparatus as defined in claim 1, wherein a third distance, extending from the pivot joint to the aerodynamic center of the panel, is generally equal to the first and second distances. 7. A speed brake apparatus for reducing the airspeed of an aircraft by increasing aerodynamic drag, comprising: an operating head located in the aircraft and adapted to move in a linear path,a pair of toggle assemblies, each toggle assembly including: a control link pivotally connected at one end to a supporting structure at a fixed joint, anda carrier link pivotally connected between the other end of the control linkage and the operating head,wherein the operating head has a rest position in which the links are relatively away from one another, and an actuated position in which the links are retracted toward one another;a linear actuator mounted adjacent the support structure and operatively connected to the operating head for moving the operating head linearly along an axis, anda pair of brake panels, each being mounted on a respective carrier link so as to swing between retracted positions in which the panels generally conform to a shape of adjacent portions of the aircraft and deployed positions in which the panels extend outwardly into the air stream to produce aerodynamic drag, wherein each of the panels has an aerodynamic center, and wherein the aerodynamic center is disposed at an intersection of a line that is an extension of the carrier link and a line that extends through the fixed joint and perpendicular to the axis. 8. The speed brake apparatus as defined in claim 7, wherein each control link has a first length and each carrier link has a second length, and wherein the first and second lengths are generally equal to one another. 9. The speed brake apparatus as defined in claim 8, wherein a third length, extending from an end of the carrier link to the aerodynamic center of the panel, is generally equal to the first and second lengths. 10. The speed brake apparatus as defined in claim 9, wherein as each of the panels is moved between the deployed and retracted positions, the aerodynamic center moves in a direction that is perpendicular to the axis. 11. The speed brake apparatus as defined in claim 10, wherein movement of each of the panels occurs without any load being placed on the linear actuator. 12. The speed brake apparatus as defined in claim 11, wherein the linear actuator is a hydraulic cylinder, and wherein the operating head is disposed on a piston rod that projects from the cylinder. 13. A speed brake apparatus for reducing the airspeed of an aircraft by increasing aerodynamic drag, comprising: an operating head adapted for linear movement generally parallel to an axis of a fuselage of the aircraft,a pair of brake panels mounted on opposites sides of portion of the aircraft, the panels being operatively associated with the operating head so as to swing outwardly in opposite directions generally about their downstream end portions, between a retracted position, to a deployed position in which the panels project outward, each panel having an aerodynamic center,a support structure fixed to the fuselage,control links associated with the brake panels, each control link being pivotally attached to the support structure at a fixed joint, andcarrier links associated with the brake panels, each control link being pivotally secured to a respective control link at a pivot joint and to the operating head at a hinge joint,wherein the aerodynamic center for each panel is disposed at an intersection of a line that is an extension of the carrier link that is associated with the respective panel and a line that extends through the fixed joint and perpendicular to the axis. 14. The speed brake apparatus of claim 13, wherein each carrier link is fixed to or integrated with an inner surface of the panel. 15. The speed brake apparatus of claim 13, wherein each brake panel is mounted on one of the carrier links. 16. The speed brake apparatus of claim 13, wherein a distance along a respective control link from the fixed joint to the pivot joint is generally equal to a distance from the pivot joint to the aerodynamic center of the panel associated with the respective control link. 17. The speed brake apparatus of claim 13, wherein a distance along a respective carrier link from the pivot joint to the hinge joint is generally equal to a distance from the pivot joint to the aerodynamic center of the panel associated with the respective carrier link.