| 摘要 |
<p>The invention concerns an aircraft propulsion assembly of which the suspension assembly comprises the following upstream suspension fasteners mounted on a blower housing (34) and/or on said intermediate housing (30) of the turbojet engine: at least one main upstream suspension fastener (130), configured in such a way as to absorb at least a moment (Mx) along the longitudinal axis (X) of the turbojet engine and the forces (Fy and Fz) in a plane perpendicular to the longitudinal axis, and at least one pair (120, 140, 200) of additional upstream suspension fasteners (120a, 120b, 140a, 140b, 121a, 121b, 200a, 200b) separate from the main suspension fastener (130) and configured in such a way as to absorb at least a moment (Mz) according to the vertical axis of the turbojet engine and, associated with a device for absorbing thrust forces (110), a moment (My) along the transverse axis of the turbojet engine and forces (Fx) along the longitudinal axis of the turbojet engine.</p> |
