A safety system for aircraft passenger seats is described. A pallet that can be removably coupled to seats can also be removably coupled to the aircraft floor and one or more brackets, tension fittings, or machined straps that can be coupled to structural beams or components in an aircraft. A keel tension fitting can be attached to a keel beam and then be coupled to the pallet and thereby the seats. By attaching to the keel beam the safety system allows the seating arrangement (pallet and seats) to withstand greater stresses and forces, resulting in increased safety.

Frame for a primary structure of an aircraft seat, comprising longitudinal parts and transverse parts spaced apart from, and connected to, one another, the parts having various shapes and dimensions so as to reproduce a general three-dimensional shape of the primary structure, the longitudinal and transverse parts being planar and each comprising at least one joint, the parts being joined together by their joints.

A passenger seat is described which satisfies a head-injury criterion (HIC). To satisfy the HIC, the passenger seat translates or pivots one or more components of the seatback towards a passenger sitting behind the passenger seat. By translating and/or pivoting the components of the seatback towards the passenger, a crush zone for the passenger seat may be increased, thereby increasing the impact time and correspondingly decreasing the forces felt by the passenger.

A seat base includes a plurality of linear actuators each having a first end pivotally mounted to a base member and a second end pivotally mounted to a seat member. A controller is adapted for controlling an extension length of each of the plurality of linear actuators in a coordinated manner for adjusting a position of the seat member with six degrees-of-freedom and for damping vibration of the seat member. An active vibration mitigation method for reducing vibrations of an aircraft seat includes receiving vibration data from one or more accelerometers mounted to the aircraft seat and determining a vibration profile based on the vibration data. When vibration mitigation is warranted, control signals for damping vibration are determined and transmitted to a plurality of linear actuators adapted to support the aircraft seat.

Described are support assemblies for a passenger seat, that can include a supportive surface configured to connect with a frame of a passenger seat, and shaped to support a passenger. Supportive surfaces can include a first portion formed of a first plurality of cells having an auxetic cell geometry that can deform to adopt a synclastic curvature under stress, and a second portion formed of a second plurality of cells having a non-auxetic cell geometry that can deform to adopt an anticlastic or cylindrical curvature under stress. The regions having respective auxetic and non-auxetic cell geometries can be arranged to form a supportive surface that can flex to follow contours of a seated passenger.

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.

A static aircraft seat privacy panel may include a body. At least a portion of a surface of the body may be shaped to at least partially conform with at least a portion of an aircraft seat. A lower edge of the body may be configured to couple to a floor via a set of floor-mounted components. The set of floor-mounted components may be within the floor separate from a set of seat tracks of an aircraft seat compliant with 16G force requirements for aviation transport. An upper edge of the body may be configured to be offset a selected distance from a surface of one or more overhead structures of the aircraft cabin when the body is coupled to one or more structures positioned proximate to a ceiling of the aircraft cabin. The static aircraft seat privacy panel may be compliant with 9G force requirements for aviation transport.

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 seat back for an aircraft seat includes an energy absorbing device for permitting movement of the seat back from a first position to a second position when a force is applied to an upper region of the seat back and a guide for guiding movement of the seat back between the first position and the second position. A first connector for connecting the energy absorbing device to the seat back of an aircraft seat and a second connector for connecting the energy absorbing device to the frame of an aircraft seat or a recline mechanism are joined by a breakable member which is configured to break when a predetermined force is applied to move the first connector away from the second connecter.

An anti-crash helicopter seat integrating multiple protections, including a main framework, a weighing sensor, a magnetorheological damper system, an upper body forced tensioning and quick disengagement system, a seat pan, a multifunctional vest and a controller, wherein the seat pan is slidably connected with the main framework in a vertical direction, the magnetorheological damper system is fixedly arranged on the seat pan and is connected with the main framework by the weighing sensor, the upper body forced tensioning and quick disengagement system is arranged on the seat pan, the multifunctional vest is connected with the seat pan by the upper body forced tensioning and quick disengagement system, and the controller is connected with the weighing sensor and the magnetorheological damper system respectively.