Controlled energy absorption of seats for impact is described herein. One disclosed example method includes determining a weight of an occupant of a seat of an aircraft, and calculating, using a processor, a stroke load of a seat energy absorber operatively coupled to the seat based on the weight of the occupant. The example method also includes setting the seat energy absorber to the calculated stroke load.

An aircraft seat includes a seat bucket that is integral by its seatback with a single beam oriented along an axis that is approximately perpendicular to the aircraft floor, which beam is integral with fastening points located on at least two separate lines on the aircraft floor.

An aircraft seat includes a seat bucket that is integral by its seatback with a single beam oriented along an axis that is approximately perpendicular to the aircraft floor, which beam is integral with fastening points located on at least two separate lines on the aircraft floor.

An aircraft seat assembly including stanchions defining elongated guide channels and elongated motion sleds nested in the guide channels and affixed to a seat bucket. An energy absorber implemented as a wire bender assembly is coupled between the stanchions and the motion sled. In use, the elongated guide channels guide motion of the motion sleds and the wire bender assemblies attenuate energy during a dynamic event exceeding a predetermined threshold load value. The elongated interface between the guide channels and motion sleds serve to transfer excessive loading to the seat frame thereby protecting the seat assembly from damage and the occupant from excessive lumbar spinal loads.

An aircraft seat assembly including stanchions defining elongated guide channels and elongated motion sleds nested in the guide channels and affixed to a seat bucket. An energy absorber implemented as a wire bender assembly is coupled between the stanchions and the motion sled. In use, the elongated guide channels guide motion of the motion sleds and the wire bender assemblies attenuate energy during a dynamic event exceeding a predetermined threshold load value. The elongated interface between the guide channels and motion sleds serve to transfer excessive loading to the seat frame thereby protecting the seat assembly from damage and the occupant from excessive lumbar spinal loads.

Provided are a parachute that can be improved in strength as compared with a conventional parachute even though the number of panels is relatively small, and can be increased in size at low cost, a safety device and a flight vehicle provided with the parachute. A parachute 100 includes an umbrella body 11 including an umbrella top portion 14 and an umbrella edge portion 15, and a plurality of lines 12. A portion along a circumferential direction in a range from the umbrella edge portion 14 to a position on the way to the umbrella top portion 15 is folded in a triple fold in the circumferential direction of the umbrella body 11 and fixed by sewing or the like to form a fold portion 17, and one end of one line 12 is connected to the fold portion 17.

An energy absorbing system that is adapted for absorbing energy of an object in a vehicle in a crash situation by decreasing acceleration and force acting on the object in the crash situation, the energy absorbing system comprising at least one plastically deformable energy absorber that is plastically deformable in the crash situation. A mass-dependent self-adjusting mechanism is provided, the mass-dependent self-adjusting mechanism being adapted for adjusting, on the basis of an underlying mass of the object, a required compensation force that is to be provided by the energy absorbing system in the crash situation for plastically deforming the at least one plastically deformable energy absorber in order to decrease the acceleration and force acting on the object.

A control device including at least one control member for measuring an acceleration of an aircraft, for generating an inflation order, and for transmitting the inflation order to an inflation member, the inflation member serving to inflate at least one inflatable safety bag, the control device, the inflation member and the inflatable bag being arranged together on a single seat of the aircraft. Such a control device includes at least one readying system connected to the at least one control member, the readying system comprising: at least a first sensor suitable for continuously measuring a first current acceleration of the aircraft relative to at least one axis; and at least one switch that is controllable as a function of the first current acceleration of the aircraft as measured by the first sensor.

A control device including at least one control member for measuring an acceleration of an aircraft, for generating an inflation order, and for transmitting the inflation order to an inflation member, the inflation member serving to inflate at least one inflatable safety bag, the control device, the inflation member and the inflatable bag being arranged together on a single seat of the aircraft. Such a control device includes at least one readying system connected to the at least one control member, the readying system comprising: at least a first sensor suitable for continuously measuring a first current acceleration of the aircraft relative to at least one axis; and at least one switch that is controllable as a function of the first current acceleration of the aircraft as measured by the first sensor.

A seat assembly includes a seat pan that is tilted automatically by way of a seat bucket moving up and down relative to a base structure. The seat bucket is pivotably coupled to a carrier. The carrier and the seat bucket each follow respective channels of a base structure. The movement of the seat bucket along the channel of the base structure causes the pivoting of the seat bucket relative to the carrier. The channels are shaped with an angular orientation resulting in the seat pan angle changing as the seat bucket moves up and down.