An active vibration control system (AVCS) and method for reducing motion and/or vibration of a seat frame within an aircraft includes vibration sensors, a controller, and force generators. In some embodiments, the vibration sensors and/or the force generators are attached to the seat frames. In other embodiments, the vibration sensors and/or the force generators are attached to aircraft structures, proximate to the seat frame. By monitoring the motion and/or vibration of the seat frame, the controller calculates a cancelling force to be generated by the force generators to reduce the vibration experienced by the seat frame and its occupant. Such seat frame vibration control can be implemented as a separate AVCS in an aircraft, or can be integrated in an existing AVCS that is also configured to provide vibration control in other parts thereof.

In various embodiments, the present disclosure provides an energy attenuating mounting foot comprising a load beam having a longitudinal axis, a top surface, a bottom surface, an inner track interface lobe, and an outer track interface lobe, the inner track interface lobe and the outer track interface lobe extending laterally from the load beam, and a channel along the longitudinal axis having a depth extending from the load beam bottom surface toward the top surface. In various embodiments, the inner track interface lobe has a first length extending in a direction from the bottom surface towards the top surface and the outer track interface lobe has a second length extending in a direction from the bottom surface towards the top surface, the first length being less than the second length.

Described are passenger seat assemblies having an impact bracket for a support pin. The support pin may be a component of a monitor assembly. The impact bracket includes a body that defines an aperture and a flex member within the aperture. The flex member defines a support region and a travelling region of the aperture. The flex member retains the support pin in the support region responsive to a load that is less than a minimum impact load, and releases the support pin from the support region into the travelling region responsive to a load that is at least the minimum impact load.

Technologies are described for assemblies to recline a seat. The assemblies may comprise a shaft, a threaded end at a first end of the shaft, a Stroke limiter, a seat back mounting, a mounting fastener, an energy absorber, and at least one locknut. A first end of the Stroke limiter may be attached to a second end of the shaft. The seat back mounting may be attached to a second end of the Stroke limiter and the mounting fastener. The energy absorber may be a kinetic energy absorbing element and the shaft may pass through the energy absorber. The locknut may be configured to secure the shaft of the seat recline assembly to the seat frame mounting with the end of the shaft attached to the Stroke limiter on a first side of the seat frame mounting and the energy absorber on a second side of the seat frame mounting.

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.

An energy absorbing strut having, a first end coupled with an inner cylinder, and a second end connected with a hollow rod extending within the inner cylinder. A piston is carried by the rod having an outer surface sealing against an inside diameter of the inner cylinder and forming a compression chamber and a rebound chamber bounded by the piston, the rod having an internal passageway communicating between the compression chamber and the rebound chamber. An inertial mass carried by the rod movable axially on the rod between a closed position against and annular rod passageway and an open position opening the rod passageway and allowing the flow of a hydraulic fluid between the compression chamber and the rebound chamber. A spring acts on the inertial mass biasing the inertial mass toward the closed position. The energy absorbing strut may be used in a blast mitigation system for a military vehicle or other applications for providing shock isolation between two structures.

An aircraft passenger seat with dynamic seat back breakover including a pivotally-attached seat back element and a seat back breakover mechanism including an articulating weighted inertia linkage operable for coupling the seat back element in a first operating condition in which the seat back element is movable between an upright taxi takeoff and landing (TTOL) position and a reclined position, and decoupling the seat back element in a second operating condition to allow the seat back element to move forward past the upright position, the first operating condition corresponding to inertial loading below a predetermined threshold value and the second operating condition corresponding to inertial loading above the predetermined threshold value.

An apparatus for dynamically tilting a seatpan in an aircraft passenger seating assembly includes a seat frame, seatback, seat cushion, and cushion support structure (e.g., a seatpan), the seat cushion and seatpan together having a forward end and a rear end and together supporting a passenger occupying the seating assembly. Accelerometers may detect an inertial event such as a rapid deceleration that may cause the passenger to pitch forward; dynamic seatpan actuators (e.g., airbags or ballistic devices) connected to the accelerometers react to the inertial event by detonating, driving the seatpan and seat cushion upward. As a result, the head path of the passenger may be redirected upward, alleviating the risk of passenger injury and component damage. Additional airbags may react to the inertial event by tightening the passenger seatbelt.

A head-pan diaphragm structure attachable to or an integral part of a seat back structure, the head-pan diaphragm structure including high-performance fibers and the head-pan diaphragm structure positionable in a head strike target area of the seat back structure. A seat back assembly including a seat back frame member including spaced portions, a torsion bar attached between the spaced portions, a head-pan diaphragm structure positioned in a framed opening formed by the torsion bar and a portion of the seat back frame member, the head-pan diaphragm structure positioned in a head strike target area, and the head-pan diaphragm member including integrated high-performance fibers.

An Electric Vertical Take-off and Landing (EVTOL) Passenger Air Vehicle (PAV) using a plurality of electric motors positioned concentrically about the passenger compartment and utilizing ducted turbines to produce thrust allowing the vehicle to take off and land vertically and fly without the use of aerodynamic wings. Utilizes a plurality of independent electric battery powered motors providing sufficient thrust to ensure the vehicle can hover and complete a safe landing despite a loss of thrust from any two adjacent motors and up to half of the motors, if non-adjacent, by utilizing redundant onboard flight control systems to vary motor torque as need to maintain steady, controlled flight. Design utilizes a pivoting seat for passenger comfort as well as shock mounting of the seat for safety. Ingress and egress are facilitated by integrated folding air stairs. The turbine fairing is designed to be rapidly manufactured as two parts, as upper and lower shells, using a composite forging process.