Rear engine redundant mount

Claim 2

A mounting system for the rear end of a jet aircraft engine in which the engine has peripheral mount attaching means, two primary mounts attached to said attaching means on opposite sides of the engine normally providing rigid support for the rear of the engine capable of resisting forces in all directions, and a redundant mount attached to said mount attaching means between said primary mounts which normally provides no significant support for the engine, said redundant mount including a housing member adapted to be attached to aircraft structure and having a socket, a pair of links having convergent ends extended into said socket, said links having their divergent ends attached to said engine mount attaching means, and means for securing the convergent ends of said links together to form a hub within said socket which is loosely encircled by said socket and normally held out of engine supporting relationship with the walls of said socket by said primary mounts.

Claim 3

In combination, a jet engine for aircraft including a rear mounting flange extending circumferentially about the engine, two primary rear engine mounts, one on each side of the engine, for supporting the rear of the engine rigidly on aircraft structure against forces in torsional, vertical and lateral directions, and a redundant rear engine mount which normally provides no significant support for the engine, said redundant mount including a base fixed to the aircraft beneath the engine midway between said primary mounts having an enclosure, and a cooperating member within said enclosure normally entirely out of contact with and spaced a substantial distance from the walls of said enclosure, said cooperating member having two links connected thereto which extend tangentially to and are attached to said engine mounting flange.

Claim 4

In combination, a jet engine for aircraft including a rear mounting flange extending circumferentially about the engine, two primary rear engine mounts, one on each side of the engine, for supporting the rear of the engine rigidly on aircraft structure against forces in torsional, vertical and lateral directions, and a redundant rear engine mount which normally provides no significant support for the engine, said redundant mount including a base fixed to the aircraft beneath the engine midway between said primary mounts having an enclosure, and a cooperating member within said enclosure normally entirely out of contact with and spaced a substantial distance from the walls of said enclosure, said cooperating member having two links connected thereto which extend tangentially to and are attached to said engine mounting flange.

Claim 5

A rear mounting system for an aircraft jet engine havinG a peripheral rear mount attachment member, said system including two primary mounts located on opposite sides of said engine in the transverse plane including said mount attachment member, said primary mounts having means connecting them to fixed aircraft structure to provide a rigid support for said engine in torsional, vertical and lateral directions, and a redundant mount located beneath said mount attachment member having cooperating engine supporting members, one carried by said attachment member and the other by fixed aircraft structure, said cooperating supporting members being normally completely spaced apart from each other so as to provide no support for the engine until one of said primary mounts fails.

Claim 6

A rear mounting system for an aircraft jet engine havinG a peripheral rear mount attachment member, said system including two primary mounts located on opposite sides of said engine in the transverse plane including said mount attachment member, said primary mounts having means connecting them to fixed aircraft structure to provide a rigid support for said engine in torsional, vertical and lateral directions, and a redundant mount located beneath said mount attachment member having cooperating engine supporting members, one carried by said attachment member and the other by fixed aircraft structure, said cooperating supporting members being normally completely spaced apart from each other so as to provide no support for the engine until one of said primary mounts fails.

Claim 7

A mounting system for the rear end of a jet aircraft engine in which the engine has peripheral mount attaching means, two primary mounts attached to said attaching means on opposite sides of the engine normally providing rigid support for the rear of the engine and capable of resisting forces in all directions, and a redundant engine mount for an aircraft engine comprising a housing having means for securing it to aircraft structure, said housing also having a chamber adapted to receive the convergent ends of a pair of links, the divergent ends of which are adapted to be secured to the engine, the convergent ends of said links being bifurcated and nested in overlapping relation with space between the furcations, a hub forming member occupying the space between said furcations, and means for securing said hub member to said links, the walls of said chamber encircling said hub member and being entirely spaced from said hub member a substantial distance so that the redundant engine mount does not normally contribute to the support of the engine.

Claim 8

A mounting system for the rear end of a jet aircraft engine in which the engine has peripheral mount attaching means, two primary mounts attached to said attaching means on opposite sides of the engine normally providing rigid support for the rear of the engine and capable of resisting forces in all directions, and a redundant engine mount for an aircraft engine comprising a housing having means for securing it to aircraft structure, said housing also having a chamber adapted to receive the convergent ends of a pair of links, the divergent ends of which are adapted to be secured to the engine, the convergent ends of said links being bifurcated and nested in overlapping relation with space between the furcations, a hub forming member occupying the space between said furcations, and means for securing said hub member to said links, the walls of said chamber encircling said hub member and being entirely spaced from said hub member a substantial distance so that the redundant engine mount does not normally contribute to the support of the engine.

Claim 9

The combination of claim 4 wherein the hub member is circular and the walls of the chamber include a plurality of concentric arcuate surfaces spaced about the periphery of said hub member which are struck about a radius greater than the radius of said hub member.

Claim 10

In combination, a jet aircraft engine including engine mounting means located circumferentially about the rear of the engine, two primary mounts secured to said mounting means, one on each side of said engine for supporting the rear of the engine rigidly on fixed aircraft structure against forces in torsion and in both vertical and lateral directions, and a redundant engine mount which provides no support for the engine until one of said primary mounts fails, said redundant mount including divergent links having their divergent ends connected to said supporting means and having their convergent ends connected to form a hub, and a member carried by fixed aircraft structure for cooperating with said hub and either one of said primary mounts upon failure of the other primary mount, said cooperating member providing abutment surface means encircling said hub in spaced relation to the latter for limiting the movement of said hub in all directions in a vertical plane transverse to the longitudinal axis of said engine.

Claim 11

In combination, a jet aircraft engine including engine mounting means located circumferentially about the rear of the engine, two primary mounts secured to said mounting means, one on each side of said engine for supporting the rear of the engine rigidly on fixed aircraft structure against forces in torsion and in both vertical and lateral directions, and a redundant engine mount which provides no support for the engine until one of said primary mounts fails, said redundant mount including divergent links having their divergent ends connected to said supporting means and having their convergent ends connected to form a hub, and a member carried by fixed aircraft structure for cooperating with said hub and either one of said primary mounts upon failure of the other primary mount, said cooperating member providing abutment surface means encircling said hub in spaced relation to the latter for limiting the movement of said hub in all directions in a vertical plane transverse to the longitudinal axis of said engine.

Claim 12

A rear engine mount system for a jet aircraft engine having mount attaching means located peripherally about the engine, laterally spaced inboard and outboard mounts connected to said attaching means and constituting the primary engine mounts which normally provide the entire rear support for the engine, and a redundant engine mount located beneath the engine between said primary mounts, said redundant mount including a hub member and an enclosure member encircling said hub member, one of said members being carried by said engine attaching means and the other by fixed aircraft structure, the inner encircling surface of said enclosure member having a larger diameter than the diameter of said hub member, the latter being spaced a substantial distance from said encircling surface until failure of a primary mount occurs.

Claim 13

A rear engine mount system for a jet aircraft engine having mount attaching means located peripherally about the engine, laterally spaced inboard and outboard mounts connected to said attaching means and constituting the primary engine mounts which normally provide the entire rear support for the engine, and a redundant engine mount located beneath the engine between said primary mounts, said redundant mount including a hub member and an enclosure member encircling said hub member, one of said members being carried by said engine attaching means and the other by fixed aircraft structure, the inner encircling surface of said enclosure member having a larger diameter than the diameter of said hub member, the latter being spaced a substantial distance from said encircling surface until failure of a primary mount occurs.

Claim 14

A rear engine mount system for a jet engine having a mounting flange extending peripherally about the engiNe, two primary mounts, one on each side of the engine, for supporting the rear of the engine rigidly on aircraft structure against forces in all directions and normally providing the entire support for the rear of the engine, and a redundant engine mount located beneath the engine midway between said primary mounts which normally provides no support for the engine, said redundant mount including cooperating members, one of which is connected to said mounting flange and the other of which is fixed to aircraft structure, said cooperating members comprising a hub member and a socket member encircling and spaced a substantial distance from said hub member so as normally to be entirely out of engine supporting relation.

Claim 15

A rear engine mount system for a jet engine having a mounting flange extending peripherally about the engiNe, two primary mounts, one on each side of the engine, for supporting the rear of the engine rigidly on aircraft structure against forces in all directions and normally providing the entire support for the rear of the engine, and a redundant engine mount located beneath the engine midway between said primary mounts which normally provides no support for the engine, said redundant mount including cooperating members, one of which is connected to said mounting flange and the other of which is fixed to aircraft structure, said cooperating members comprising a hub member and a socket member encircling and spaced a substantial distance from said hub member so as normally to be entirely out of engine supporting relation.