| 摘要 |
<p>The device has two attachment units (6) attached to an engine (1) and shifted along an axial direction of the engine. One of the attachment units has parallel rods (8, 13a, 13b, 17a, 17b) that are fixed at two points of the engine. An asymmetric half ring (12) is fixed at an oblique suspension mast (2). The rods are fixed at two opposite ends of the half ring and directed along a transverse direction of an aircraft. The ring extends in a vertical direction from the aircraft. The half ring is thinned down from a connection region connected to the mast towards the ends. An independent claim is also included for an oblique suspension mast.</p> |
