초록 ▼

The invention relates to a thrust reverser comprising two symmetrical doors, approximately hemi-truncated in shape, pivotally mounted about an axis which is transverse and substantially diametrical to the jet of a jet engine and which is disposed downstream of the jet exhaust pipe thereof, the doors

The invention relates to a thrust reverser comprising two symmetrical doors, approximately hemi-truncated in shape, pivotally mounted about an axis which is transverse and substantially diametrical to the jet of a jet engine and which is disposed downstream of the jet exhaust pipe thereof, the doors occupying a folded, or stowed, position in which they determine a sleeve forming part of the fairing of the engine and fuselage of the aircraft, or an unfolded, or opened out, position in which they are disposed transversely with respect to the jet, wherein the structure of each of the doors is such that, in stowed position, the inner volume of the sleeve forms a useful extension of the jet pipe of the engine. The invention finds particular application in the braking of aircraft.

대표청구항 ▼

A thrust reverser adapted for use with an aircraft jet engine having a jet exhaust pipe, said reverser comprising two symmetrical doors, each of which is at least substantially hemi-truncated in form, having opposed arcuate leading and trailing edges and opposed rectilinear side edges, said doors be

A thrust reverser adapted for use with an aircraft jet engine having a jet exhaust pipe, said reverser comprising two symmetrical doors, each of which is at least substantially hemi-truncated in form, having opposed arcuate leading and trailing edges and opposed rectilinear side edges, said doors being mounted to pivot about an axis adjacent said trailing edges, said axis being transverse and substantially diametrical with respect to the jet of said engine, and which is disposed downstream of the jet exhaust pipe thereof, each of said doors comprising a thin wall having a concave inner face and a convex outer face, and elongated reinforcing members attached to said concave face adjacent the arcuate leading and trailng edges and the rectilinear side edges thereof, said reinforcing members projecting inwardly from said concave face, said wall having a crescent-shaped section at its rearward end, defined by the trailing edge of said wall and said reinforcing member adjacent thereto, said section having an inner concave and an outer convex face which form continuations of the concave and convex faces of said wall, an arcuate lining having two faces which intersect to form a trough having an approximately V-shaped cross-section, said lining spanning the reinforcing member adjacent the trailing edge of said door with said reinforcing member in the trough of said lining, said lining faces comprising a rearward face covering substantially all of the concave face of said crescent-shaped section and a forward face covering less than half of the concave face of said wall, each door being movable between a first, folded position in which said outer face forms an extension of a section of said aircraft, and a second, unfolded position in which said outer face is disposed transversely with respect to said jet, said rearward faces forming, in the folded position of said doors, a converging extension of said jet pipe having a substantially circular rear port with a diameter smaller than the exit diameter of said jet pipe.