Beam for suspending a turboshaft engine from an aircraft structure
View Patent ↗A beam for suspending a turboshaft engine from an aircraft structure, including a first attachment mechanism configured to be secured to the aircraft structure and at least one second attachment mechanism configured to be secured to the engine. The beam is at least partially made from a metal-matrix composite material including reinforcing fibers. In one embodiment, the beam takes a form of a circle arc.
1. A beam for suspending a turboshaft engine from a structure of an aircraft, comprising:
a first attachment means to be fixed to the aircraft structure; and
second and third attachment means to be fixed to the engine,
wherein the beam is made at least in part of metal matrix composite incorporating reinforcing fibers,
wherein the beam is in a shape of an arc encompassing less than a full circle, the second and third attachment means are arranged at first and second ends of the beam, respectively, and
wherein the reinforcing fibers extend only between the second and third attachment means along the arc.
2. The beam as claimed in claim 1 , wherein the first attachment means being formed between the second and third attachment means, in a middle of the beam.
3. The beam as claimed in claim 1 , wherein the arc extends between 40° and 180°.
4. The beam as claimed in claim 1 , wherein the second and third attachment means are devises.
5. The beam as claimed in claim 1 , wherein the second attachment means is on standby.
6. An aircraft comprising a turboshaft engine and a beam for suspending the turboshaft engine as claimed in claim 1 .
7. A beam for suspending a turboshaft engine from a structure of an aircraft, comprising:
a first attachment means to be fixed to the aircraft structure; and
a second attachment means to be fixed to the engine,
wherein the beam is made at least in part of metal matrix composite incorporating reinforcing fibers,
wherein the beam is in a shape of a ring, the ring configured to encircle the turboshaft engine,
wherein the reinforcing fibers of the ring-shaped beam are arranged in rings that are concentric with the ring-shaped beam, and
wherein a radial thickness of the beam is substantially uniform around the ring.
8. The beam as claimed in claim 7 , wherein the second attachment means, formed of devises, is distributed about a periphery of the ring.
9. An aircraft comprising a turboshaft engine and a beam for suspending the turboshaft engine as claimed in claim 7 .
10. A beam for suspending a turboshaft engine from a structure of an aircraft, comprising:
a mounting plate configured to accept fixing means, the mounting plate being in a form of a metal block with first attachment means for fixing to the structure of the aircraft on each side of the beam in a lengthwise direction; and
a second attachment means to be fixed to the engine,
wherein the beam is made at least in part of metal matrix composite incorporating reinforcing fibers, and
wherein the reinforcing fibers are straight and extend substantially parallel to the lengthwise direction of the beam through the mounting plate.
11. The beam as claimed in claim 10 , wherein the mounting plate includes at least one clevis forming a second attachment means.
12. The beam as claimed in claim 10 , wherein the fibers do not, within the beam, extend in line with one of the attachment means.
13. The beam as claimed in claim 10 , wherein the mounting plate comprises the second attachment means including at least one connecting clevis with at least one orifice through which to pass a clevis pin.
14. The beam as claimed in claim 10 , wherein the beam further comprises a lower mounting plate for fixing to the turboshaft engine, the mounting plate and the lower mounting plate being formed as single monolithic component.
15. An aircraft comprising a turboshaft engine and a beam for suspending the turboshaft engine as claimed in claim 10 .
16. The beam as claimed in claim 10 , wherein the first attachment means comprises orifices.