FIELD: transport.
SUBSTANCE: invention relates to aircraft engineering, particularly to aircraft turbojet engine attachment strut. Strut 4 has rigid structure 10 comprising central torsion box 22 and two lateral torsion boxes 24a, 24b rigidly secured to front part of said central torsion box 22 and arranged on its both sides. Lengthwise central torsion box 22 is formed by two side panels 30 jointed together by crosswise ribs 23, while each side torsion box comprises frame (28a, 28b, 29a, 29b, 46a, 46b). One of said crosswise ribs is furnished with two stiffness ribs (52a, 52b), made integral with rib 23 and extending from two side panels (30) of lengthwise central torsion box (22) outward. Stiffness ribs (52a, 52b) are secured to frame (28a, 28b, 29a, 29b, 46a, 46b) of side torsion boxes (24a, 24b), respectively.
EFFECT: improved aerodynamics, higher engine power and reduced fuel consumption.
17 cl, 12 dwg
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