Structure of the load introduction zone in the rear end of an aircraft
View Patent ↗Load introduction zone in the rear end of an aircraft comprising receiving elements ( 3, 4 ) of the loads of the horizontal and vertical tail stabilizers connected to structural elements ( 2, 8, 9 ) wherein: a) said structural elements are the cladding ( 8 ), two contiguous load-bearing frames ( 2 ) with a Π or omega cross-section and, at least, a third frame ( 9 ); b) the receiving element of the horizontal tail stabilizer load is a first fitting ( 3 ) structured as a torque box, transversely arranged between said load-bearing frames ( 2 ) and connected to them, and the receiving elements of the vertical tail stabilizer loads are some second fittings ( 4 ) coupled to these frames ( 2, 9 ); c) said frames ( 2, 9 ) and said first and second fittings ( 3, 4 ) are entirely made of composite material.
1. Rear end of an aircraft with a horizontal tail stabilizer and vertical tail stabilizer load introduction zone that comprises receiving elements of the loads of these stabilizers connected to structural elements of the fuselage, wherein:
a) the structural elements of the rear end are cladding, two contiguous load-bearing frames configured at least in this load introduction zone with two lateral elements and one base element, such that their cross section has a closed shape, and at least a third frame contiguous to one of these two load-bearing frames;
b) the receiving element of the horizontal tail stabilizer load is a first fitting structured as a torque box, with side walls and a cover and transversally arranged between the load-bearing frames and connected to them, and the receiving elements of the vertical tail stabilizer loads are second fittings coupled to these frames; and
c) the frames and the first and second fittings are entirely made of composite material.
2. Rear end of an aircraft, as per claim 1 , wherein the cross section of the load-bearing frames has a Π shape.
3. Rear end of an aircraft, as per claim 1 , wherein the cross section of these load-bearing frames has an omega shape.
4. Rear end of an aircraft, according to claim 1 , wherein the load-bearing frames are shaped as unit parts, with configuring elements connected prior to their assembly in the fuselage.
5. Rear end of an aircraft, according to claim 1 , wherein configuring elements of the load-bearing frames are shaped separately and are connected during assembly in the fuselage.
6. Rear end of an aircraft, according to claim 1 , wherein said two lateral elements have a height and said load bearing frames have a diameter (D) proximate to the second fittings such that said height and said diameter have a ratio that ranges from 12-13%.
7. Rear end of an aircraft, according to claim 1 , wherein the total number of its frames is 5.
8. Rear end of an aircraft, according to claim 1 , wherein the first fitting also comprises omega-shaped laminates connected to the outer sides of its side walls.
9. Rear end of an aircraft, according to claim 1 , wherein the first fitting also comprises omega-shaped laminates connected to the inner sides of its side walls.