Mounting device for interior equipment in aircraft
View Patent ↗A mounting device for aircraft comprises an energy absorber and wherein the mounting device is mounted between a primary structure of the aircraft and the interior equipment. In this way the load acting on an interior equipment connected to the primary structure of the aircraft by way of the mounting device can be limited if a crash impulse occurs. The load acting on the primary structure is also limited, which can result in enhanced passive safety for the passengers and in weight reduction.
1. A mounting system for interior equipment in an aircraft, comprising:
a first mounting device, comprising:
a first energy absorber;
a first housing;
wherein the mounting device is mounted between a primary structure of the aircraft and the interior equipment;
wherein the first energy absorber is at least partly arranged in the first housing;
wherein the first energy absorber is adapted for being pushed into the first housing or pulled out of the first housing thus being deformed inside the first housing and absorbing multiple impulses in opposite directions;
wherein the mounting system further comprises:
a linear guide;
a bearing;
wherein the first mounting device has a first direction of energy absorption;
wherein the linear guide has a guide direction;
wherein the guide direction has a component which is parallel to the energy absorption direction of the first mounting device; and
wherein the bearing fixes the interior equipment to the linear guide such that the interior equipment can slide along the linear guide.
2. The mounting system of claim 1 , further comprising:
a second mounting device comprising:
a second energy absorber;
a second housing;
wherein the second mounting device is mounted between a primary structure of the aircraft and the interior equipment;
wherein the second energy absorber is at least partly arranged in the second housing;
wherein the second energy absorber is adapted for being pushed into the second housing or pulled out of the second housing thus being deformed inside the second housing and absorbing multiple impulses in opposite directions;
wherein the second mounting device has a second energy absorption direction; and
wherein the guide direction has a component which is perpendicular to the second energy absorption direction; and
wherein the first fastening region of the second mounting device is fastened to the bearing.
3. The mounting system of claim 1 , wherein the mounting system is mounted in an aircraft.