Patent ID: 7510147

Claim:
A vibration damping pylon affixed to the exterior of an aircraft, the pylon configure to carry a payload, the pylon comprising: a) a base element configured for affachment to the aircraft; b) a payload interface element; and c) a plurality of resilient suspension elements each configured as helical coiled-cable spring elements, each resihent suspension element attached to both said base element and to said payload interface element, said plurality of resilient suspension elements including at least: (i) a first group of at least a first and at least a second helical coiled-cable spring elements deployed such that, when at rest, a weight of the payload is substantially equally distributed between said at least first and said at least second helical coiled-cable spring elements; and (ii) a second group of at least a third helical coiled-cable spring element deployed so as to be longitudinally spaced apart from said first group, such deployment effective for limiting pitch movements of said payload interface element; wherein said resilient suspension elements are a sole support structure by which said payload interface is attached to said base element and said helical coiled-cable spring elements are deployed such that longitudinal axes of all said coiled-cable spring elements are substantially parallel one to another and a longitudinal axis of the pylon.