Apparatus for improving the installation moments of external loads on aircraft
AssigneeEADS Deutschland GmbH
InventorsRonald Deslandes, Stefan Donauer, Alois Pantele
Life of this patent
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Abstract
Apparatus for reducing the installation moments of an external load installed at at least one fastening station of an aircraft includes a ramp arranged in front of the shoulder station relative to the direction of flight. The height of the ramp increases toward the fastening station, and the end of the ramp that is located in proximity of the shoulder station forms a break-off edge that is disposed at a predetermined distance from the outer side of the external load that is directed toward the break-off edge, in order to influence pitch moments and yawing moments of the external load.
Claims9
Apparatus for reducing installation moments for an external load installed at at least one fastening station of an aircraft, comprising:
- a ramp arranged in front of the at least one fastening station, relative to a direction of flight of the aircraft;
- wherein,
- a vertical dimension of the ramp increases from a forward edge toward the fastening station;
- a rearward end of the ramp located in proximity to the at least one fastening station forms a discrete break edge which is disposed opposite an outer longitudinal periphery of the external load that faces toward the break edge, and is separated from said break edge by a longitudinally extending gap having a predetermined vertical width, said break edge causing a flow separation in said gap for influencing pitch moments and yawing moments of the external load.
Apparatus for influencing in-flight fluid flow forces that act on connection elements for an external load installed at a fastening station on an aircraft, comprising:
- a ramp arranged on a body of the aircraft forward of the mounting station, relative to a direction flight of the aircraft, said ramp having a surface which is inclined from frontward to rearward, relative to said direction of flight, toward the external load and away from the body of the aircraft, whereby a vertical dimension of the ramp increases from frontward to rearward;
- wherein, a rearward extremity of the ramp located proximate to the at least one fastening station forms a discrete break edge which is separated from a longitudinal periphery of said external load by a longitudinally extending gap having a predetermined vertical width, said break edge causing a flow separation in said gap.
Dependencies are inferred from the claim text.