An arm restraint assembly configured to pierce a canopy in response to expulsion of an ejection seat from a cockpit may comprise a primary arm configured to pivot relative to the ejection seat. A canopy piercer may be coupled to the primary arm. The primary arm may be configured to rotate to a fully-deployed position while located within the cockpit. An apex of the canopy piercer may be oriented toward the canopy, when the primary arm is in the fully-deployed position.

An arm restraint assembly configured to pierce a canopy in response to expulsion of an ejection seat from a cockpit may comprise a primary arm configured to pivot relative to the ejection seat. A canopy piercer may be coupled to the primary arm. The primary arm may be configured to rotate to a fully-deployed position while located within the cockpit. An apex of the canopy piercer may be oriented toward the canopy, when the primary arm is in the fully-deployed position.

An arm restraint assembly for an ejection seat may comprise a primary arm configured to pivot about a primary arm pivot joint, and a secondary arm configured to pivot about a secondary arm pivot joint. A primary airfoil structure may be coupled to the primary arm assembly. The primary airfoil structure may include an airfoil body.

An arm restraint assembly for an ejection seat may comprise a primary arm configured to pivot about a primary arm pivot joint, and a secondary arm configured to pivot about a secondary arm pivot joint. A primary airfoil structure may be coupled to the primary arm assembly. The primary airfoil structure may include an airfoil body.

A lateral support system for use in an ejection seat of an aircraft may comprise a pump; a first side bladder fluidly coupled to the pump; a second side bladder fluidly coupled to the pump, the second side bladder configured to be disposed opposite the first side bladder. The first side bladder and the second side bladder may be coupled to a seat pan pad or a seat back pad. The lateral support system may further include a third side bladder and a fourth side bladder coupled to a seat pan pad, and the first side bladder and the second side bladder may be coupled to a seat back pad.

A lateral support system for use in an ejection seat of an aircraft may comprise a pump; a first side bladder fluidly coupled to the pump; a second side bladder fluidly coupled to the pump, the second side bladder configured to be disposed opposite the first side bladder. The first side bladder and the second side bladder may be coupled to a seat pan pad or a seat back pad. The lateral support system may further include a third side bladder and a fourth side bladder coupled to a seat pan pad, and the first side bladder and the second side bladder may be coupled to a seat back pad.

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.

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.

The invention mainly relates to a system for the inertial unlocking of a seat back, in particular of an aircraft seat, characterized in that it comprises: a structural element of the seat back, called a connecting rod, a support piece for the fixation to a structural element of said seat, the support piece comprising a flyweight movable in translation between: a locking position in which the flyweight faces a lip of the connecting rod so as to prevent the connecting rod from rotating relative to the support piece about the axis of rotation, and an unlocking position in which the flyweight is released from the lip of the connecting rod so as to allow the connecting rod to rotate relative to the support piece about the axis of rotation, the passage of the flyweight from the locking position to the unlocking position being able to be carried out under the action of a deceleration by the seat.

The invention relates mainly to a seat comprising a backrest carrying on a rear face side a tray table that can be moved between a deployed position and a stowed position, said tray table comprising a latch that can be moved between an unlocked position and a locked position,
characterized in that said tray table further comprises a locking system configured to hold the tray table in a stowed position following the deformation of said seat during an impact.