A seat assembly that is attached to a floor of a vehicle. The seat assembly can include a seat with one or more flex beams that support the seat above the floor. The flex beams comprise a bowed shape with a curving intermediate section positioned between opposing ends. The flex beam is configured to compress when a force is applied to the seat assembly to absorb energy. The flex beam is also configured to impede the return of the flex beam to the first position after the force is removed.

Various embodiments of the present technology may comprise a method and apparatus for a space-saving suspension system. In various embodiments, the apparatus may comprise a fine suspension device, a coarse suspension device, and a mechanical assembly. In various embodiments, the fine suspension device is arranged at an angle greater than zero degrees from the z-axis. In various embodiments, the mechanical assembly is coupled to the fine suspension device and a payload, such that when a force is exerted on the mechanical assembly by the payload, an applied force is transmitted to the fine suspension device.

An aircraft seat fixation device for a fixation at least of a portion of an aircraft seat on at least one fixation rail that is fixated on an aircraft structure comprises a seat base structure which is configured such that at least the aircraft seat is mounted thereon at least partially, further comprises at least one seat foot which is connected to the seat base structure, and comprises at least one fitting element which is connected to the seat foot and is at least configured to be coupled with the fixation rail,

wherein the aircraft seat fixation device comprises at least one compensation unit, which is arranged on the seat base structure, the seat foot and/or the fitting element and which is configured to permit at least one compensation movement of the seat base structure at least in an overload case.

An aircraft passenger seat assembly and backrest unit attachable to a seat assembly, the backrest being pivotally attached or fixed, and the backrest unit including at least one frame member having adjacent weakened and intact sections provided along a peripheral edge, the weakened section having a first failure load and the intact section having a second failure load greater than the first failure load such that, when a load on a backside of the backrest unit exceeds the first failure load, the weakened section fails and the intact section deforms allowing a portion of the backrest unit to tilt forward beyond an upright sitting position to absorb impact energy.

A method of assessing performance of a seat is provided. The method comprises identifying a number of critical seats for testing from a layout of passenger accommodation and building a computer simulation model, following a building block approach, for each identified critical seat. A number of loads are tested on each simulation model. Critical seats are selected for physical testing from simulation model test results according to a specified criteria assessment matrix.

The present invention relates to an energy absorption device for a seat of an aircraft, in particular of a helicopter, with at least one impact mechanism (2, 4) and at least one energy absorber (1) coupled with the impact mechanism (2, 4), wherein the impact mechanism (2, 4) acts on the energy absorber (1) for the energy absorption at least in the case of a crash.

There is provided a seat base frame (10) comprising one or more base frame tubes (16) having noncircular cross-sections. In a specific example, the tubes (16) have elliptical cross-sections. Further embodiments provide base frame tubes (16) made of magnesium or magnesium alloys.

A seat system for a passenger aircraft. The seat system includes a passenger seat frame having a backrest support assembly and a seat bottom support assembly. A quadrant assembly is connected between the backrest support assembly and the seat bottom support assembly. The quadrant assembly includes a quadrant member including a pivot point adapted to pivot the backrest with respect to the seat bottom support assembly and the quadrant member. The quadrant member is attached to the backrest and adapted to break away in the event of an impact with the backrest. The quadrant assembly may further include a pivot point brake assembly attached to the pivot point and adapted to provide a controlled stop of the backrest in the event of an impact with the backrest. In addition, a seat back tray table may be attached to the back of the passenger seat frame.

A seat device, particularly aircraft seat device, includes at least one head-support module, which device has a central cushion unit and at least one lateral cushion unit, wherein the lateral cushion unit is supported movably relative to the central cushion unit.

A mount assembly for mounting a cabin attendant seat to a support structure may comprise a first strap configured to plastically deform in response to a deflection of the support structure. The first strap may comprise a first perforation, a second perforation, and a third perforation located between the first perforation and the second perforation. The perforations may be configured to allow the strap to plastically deform.