Abstract: A roll stabilization system for an aircraft ejection seat may be provided. An integral seat sequencer may activate an ejection sequence causing an aircraft ejection seat to be ejected from an aircraft. In various instances, particularly with lighter occupants of the aircraft ejection seat, the aircraft ejection seat may begin a rotational movement. To ameliorate this rotational movement, a roll correction rocket motor is installed on the aircraft ejection seat and selectively activated by the integral seat sequencer in the event that an undesired rotational movement is detected.

Abstract: A drogue bridle attachment assembly may comprise a housing, a lock pin, jackscrew gear pin, and a drive gear pin. The housing may define a bridle opening. The lock pin may be configured to translate into the bridle opening. The jackscrew gear pin may include a threaded portion and a gear portion. The threaded portion may engage a threaded opening in the lock pin. The drive gear pin may include a drive gear portion intermeshed with the gear portion of the jackscrew gear pin.

Abstract: An onboard oxygen system for aircraft includes an oxygen source, a regulator connected to the oxygen source, and an oxygen mask connected to the regulator. The oxygen source is stored in a cavity in a passenger seat armrest. The oxygen mask is stored in a mask storage compartment attached to the armrest. The oxygen mask is deployed for use through an opening in the mask storage compartment.

Abstract: A method for sensor-based ejection of an aircraft occupant from an aircraft may comprise: receiving, via a processor and through a sensor, an ejection command from the aircraft occupant; comparing, via the processor, the ejection command to a predetermined ejection command; determine, via the processor, whether the ejection command matches the predetermined ejection command; and commanding, via the processor, initiation of an ejection event in response to the ejection command matching the predetermined ejection command.

Abstract: An ejection seat system is described. The ejection seat system includes a seat frame for supporting an aircraft occupant. The seat frame includes one or more of a ballast material or an auto-inflating unit. By the ballast material or the auto-inflating unit, the seat frame may be positively buoyant in saltwater or freshwater for improved recovery of the seat frame. The ballast material may include one or more of a gas or foam. The auto-inflating unit may include one or more of a pump or a gas cartridge. Such flotation means may be included within an internal void of one or more of a seat bucket or a seat back of the seat frame.

Abstract: An air mobility may include a seat in which an airbag or a parachute is stored; and an escape portion configured to support the seat mounted to the escape portion, coupled to the air mobility to form part of the air mobility, and configured to enable a passenger to perform an emergency bailout with the seat to an outside of the air mobility when the escape portion is separated from the air mobility.

Abstract: An aircraft ejection seat assembly is disclosed where a survival kit is incorporated into a seat back of an ejection seat, and that is released from the ejection seat by one or more actuators. The survival kit is attached to the parachute lines. One or more retention pins may secure the survival kit relative to the seat back. Representative actuators that may be used to move the retention pin(s) to a release configuration including mechanical (e.g., a bell crank), electrical (e.g., a controller such as a MASS), or pressurized fluid.

Abstract: A rocket catapult assembly for an ejection seat may comprise a motor assembly including a proximal end and a distal end, a first cartridge, and a second cartridge. The first cartridge and the second cartridge may be configured to provide a variable thrust based on an occupant's weight. The first cartridge may provide a thrust corresponding to a relatively light weight occupant, the second cartridge may provide a thrust corresponding to a relatively average weight occupant, and the first cartridge and second cartridge may provide a combined thrust corresponding to a relatively heavy weight occupant.

Abstract: A seat configured to support an occupant may include a urine-based power generator and an adjustable cushion. The urine-based power generator includes a urine accumulation reservoir configured to receive urine from the occupant, and the urine-based power generator is configured to provide power to the adjustable cushion. The seat may be an ejection seat, and the urine-based power generator and the adjustable cushion may be mounted to the seat such that the urine-based power generator and the adjustable cushion are configured to be ejected with the ejection seat.

Abstract: Techniques to deploy a parachute are disclosed. In various embodiments, a first projectile is configured to be propelled in a first direction, causing the parachute to be deployed. A second projectile configured to be propelled in a second direction is coupled to a line tethered to the parachute in such a way that a force in a direction opposite the first direction is applied to the line of the parachute when the second projectile is propelled in the second direction.

Abstract: A vehicle includes an interior cabin including a floor and a ceiling. A deployable seat assembly is moveably coupled to the ceiling. The deployable seat assembly is moveable between a stowed position in which at least a portion of the deployable seat assembly is stowed within a stowage space within the ceiling, and a deployed position in which the deployable seat assembly extends between the ceiling and the floor.

Abstract: In an embodiment, a parachute deployment system includes a parachute coupled to a release via a first load path. The first path includes crown lines. The release is adapted to attach the parachute to a rocket via the crown lines, and disengage the parachute from the rocket if a load shifts from the first path to a second path. The system also includes a line constrainer between the release and the parachute. The crown lines pass through the line constrainer, and the line constrainer is adapted to restrict an extent to which the crown lines are able to extend away from a longitudinal axis. An example release includes a back plate configured to couple a tow line to crown lines and a soft pin. The pin is adapted to separate from the back plate in response to tensioning of the release line, causing the parachute to disengage.

Abstract: From the dynamic shock of the parachute canopy applied to an aircraft and unmanned aerial vehicle-(UAV) in an emergency, there is unlimited mechanical force available for exploitation through Bowden cables connected to the ends of the parachute straps, and transfer of the force in the form of a pull onto the emergency safety systems of the aircraft for the safety of passengers, and onto the aerial vehicle-(UAV).

Abstract: The invention reduces the impact of flowfield forces on objects launched from high speed aircraft during flight. For example, the invention provides a solution for overcoming ejection windblast injuries to pilots and increases the probability of injury-free or low-injury ejection. The gas flow is used to rapidly create a very short duration protective “bubble” in the incoming air flow ahead of the ejecting pilot. The bubble reduces the local flow velocity and aerodynamic forces on the pilot during the injury-critical time period of ejection. The invention also is suitable for reducing the intensity of flowfield forces that act on released military aircraft ordnance, such as bombs and missiles.

Abstract: The present invention relates to a parachute rescue system which is intended for rescuing people from danger zones and comprises a parachute and a seat. The seat can be maneuvered outwards into the open air from a multistory building by means of a guiding device through an opening in the walls of the building.

Abstract: An ejection escape system for passenger airplane that there is a locking mechanism at the connection of the left top cabin cover, the right top cabin cover with the airplane body, there is also a locking mechanism at the connection of the left top cabin cover and the right top cabin cover, the passenger seat is an ejection escape seat, the switches for the locking mechanism and the ejection escape seat are installed in the cockpit, where the pilot can turn on the locking mechanism switch to open the left and right top cabin covers and turn on the ejection escape switch to eject the seat out of the airplane through the opening of the left and right top cabin covers.

Abstract: An ejection escape system for passenger airplane that there is a locking mechanism at the connection of the left top cabin cover, the right top cabin cover with the airplane body, there is also a locking mechanism at the connection of the left top cabin cover and the right top cabin cover, the passenger seat is an ejection escape seat, the switches for the locking mechanism and the ejection escape seat are installed in the cockpit, where the pilot can turn on the locking mechanism switch to open the left and right top cabin covers and turn on the ejection escape switch to eject the seat out of the airplane through the opening of the left and right top cabin covers.

Abstract: A parachute is stored within the specially configured seat back of each passenger seat of a commercial aircraft, behind a removable front upholstery panel. The parachute harness extends outwardly from the concealed parachute, through and beyond the periphery of the removable panel, for donning by the seated passenger. An openable upper cover extends over the top of the concealed parachute. When the parachute is needed, the passenger (having previously donned the parachute harness) pulls forward from the seat to release the front upholstery panel from the seat back to pull the parachute free, and escapes from the aircraft. In the event the seat structure separates from the aircraft, the still seated passenger opens the top flap of the seat back to access the parachute rip cord. A second embodiment comprises a child harness having a series of D-rings thereon, for face-to-face attachment to the parachute harness of an accompanying adult.

Abstract: A person can safely descend from a burning high-rise building or the like using an inflatable flying body that has a hollow conical form in an inflated deployed condition, but is deflated and folded into a backpack form in a stowed condition. The flying body includes an upper stabilizing ring, a lower nose structure with a pneumatic damping body, spoke struts extending conically therebetween, a cover skin covering the abovementioned inflatable components to form the conical outer surface and provide aerodynamic braking drag, and gas generators to inflate the inflatable components. A person straps on the apparatus in the stowed backpack form and pulls a handle to actuate the gas generators for inflating the apparatus, whereby the expanding apparatus ejects the person from the building and then orients itself in a nose-down attitude during the descent. The pneumatic damping body damps and dissipates the landing impact energy.

Abstract: A rescue system for rescuing persons by air, particularly from tall buildings or airplanes, has a receptacle with at least one parachute or paraglider. A harness for the parachute or paraglider is connected to the receptacle. The receptacle is constructed as a closable package with a substantially cuboid or suitcase-like shape and also has an opening mechanism. The harness for the parachute or paraglider is disposed inside the closed receptacle.

Abstract: A common flight deck module for use with a plurality of aircraft platforms. The common flight deck module includes a discrete structure that is independent of the structure of the aircraft fuselage and may includes an avionics system and other hardware, controls and equipment. The common flight deck module is configured to “plug into” the fuselage from each of the aircraft platforms. The “plug in” modularity of the common flight deck module permits the standardization of various components and procedures to thereby make possible efficiency-based cost reductions for both aircraft manufacturers and aircraft consumers.

Abstract: An ejection seat having a blast protection system comprising an inflatable curtain stowed on the ejection seat and deployable to at least substantially envelop an occupant of the seat.

Abstract: For improving a method for rescuing a person sitting in an ejection seat that has ejected from an aircraft in an emergency, wherein depending on data collected by measuring apparatus arranged on the ejection seat a control device initiates deployment of stabilizing and/or braking parachutes attached to the seat and furthermore initiates separation of the person from the ejection seat, it is provided that while the connection between aircraft and ejection seat exists, current flight data for the aircraft are fed via a data bus to an ejection seat computer situated on the ejection seat and once the ejection seat has separated from the aircraft the movement data for the ejection seat in space are collected and forwarded to the ejection seat computer by a navigation platform attached to the ejection seat and, that the relevant flight data for the ejection seat are calculated in the ejection seat computer starting with flight position data for the aircraft at the time the ejection seat separated and when pre-estab

Abstract: A occupant protection system for protecting an occupant of a motor vehicle, boat, or airplane during a crash. The occupant protection system includes a chair positioned inside a vehicle such as an airplane, automobile, truck, or a boat. The chair has a seat portion and a backrest portion. The seat portion has a pair of leg clamp panels pivotally coupled to it to lock a pair of legs to the seat portion in anticipation of a crash. The backrest portion has a pair of arm clamp panels pivotally coupled to it to press the arms and torso of a user towards the backrest and hold them tightly therebetween. Also disclosed is a capsule in which the chair is disposed. The capsule has several protective layers. An emergency raft forms part of the backrest of the chair when not in use, and is removable for use in case of an accident on or above water.

Abstract: A safety system that will evacuate passengers on an airplane while in flight. The In-Flight Evacuation System operates while the airplane is still in flight. While in operation the In-Flight Evacuation System will systematically evacuate passengers from the airplane. During the process the seats will rotate 180 degrees to face the rear of the plane. The seats will move towards the rear of the plane due to a rotating device connected along the bottom of the seats. When evacuation is deemed necessary, the rear doors on the plane will opened. The seats will continue to be rotated until it reaches the evacuation doors. At that point the seats will disengage. The top portion of the seat complete with a survival kit will be released with the passengers as the bottom of the seat rotates into a open compartment beneath the passenger cabin. A parachute will be activated as the passengers leave the rear of the plane. The passengers will slowly ascend to earth.

Abstract: An improved cockpit area for manned atmospheric or space vehicles includes a generally spherical, multi-axis G-compensating cockpit capsule which houses the crewmen, together with the appropriate operational and navigational instruments and the mechanisms necessary for controlling the vehicle and which is rotatably mounted in the vehicle and is controllable by the crewman to permit the crewman direct visual observation throughout virtually a full circle about the vehicle, without altering the course of the vehicle, together with a device for automatically rotating the capsule to minimize the effect of high G-forces on the crewmen, and an emergency mechanism for ejecting the capsule, with the crewmen therein, and for protecting the crewmen during and after descent and landing of the capsule.

Abstract: An aircraft passenger seat assembly, including an emergency oxygen system, a seat frame, seat bottom and seat back, and respective cushions for the seat bottom and seat back. A chemical reaction oxygen generating canister is positioned in the seat bottom below the seat bottom cushion. Oxyen flow conduit interconnect the oxygen canister and an oxygen mask compartment. A cable is operatively connected by a first end to the firing pin mechanism of the oxygen generating canister and extends from the firing pin mechanism to the mask compartment. A lever arm is positioned in the oxygen mask compartment to which a second end of the cable is attached. Another lever also includes a tether releasably connected to the lever arm and to a mask.

Abstract: An ejected pilot's seat is provided with a drogue chute anchored to the seat by means of a bridle. The bridle includes a strap having redundant load cells parallel connected in redundant fashion. The load cells measure tension in the strap. Data from the load cell is conducted through the bridle to a microprocessor contained within the seat. The microprocessor includes look-up tables for correlating tensile load in the strap to forward velocity of the ejected pilot. Upon acquisition of a preselected optimum velocity, the drogue chute is released and a main chute is deployed to increase the likelihood of a safe descent to the ground.

Abstract: A chair (1) serving as a safety device for a passenger in an airplane includes a plural circular array of balloon elements (2) each comprising an inflatable balloon member (2a, 2a') made of heat resistant elastomeric sheet material and a hose portion (2b, 2b') through which compressed air is supplied from a storage chamber (3) under the seat (4) of the chair to the balloon member. The balloon elements are folded in a predetermined order of arrays around the chair, except the seat and backrest portions, and in an emergency are inflated with the compressed air so that they are expanded, unfolded and extended outwardly of the chair in plural radial directions to form a single large expanded cellular balloon structure with the passenger located at a central part thereof, each inflated element being a cell of the expanded balloon structure. This large balloon structure functions as a safety device for the passenger. An emergency valve is actuated by a pilot or, alternatively, by an individual passenger for use.

Abstract: A harness and belt assembly for a crewmember of an aircraft including left and right slings, a first belt assembly having first end second ends, a survival kit strap assembly attachment fitting which slidably engages the belt assembly, and a mechanism for releasably attaching the fitting to a seat of an aircraft. The slings are designed to extend from the chest of the crewmember, over the crewmember's shoulders, to the back of the crewmember. The first end of the belt assembly is attached to one of the slings at the portion designed to be adjacent the crewmember's chest. The second end of the belt assembly is attached to the other of the slings. A survival kit belt can be affixed to the fitting so that the survival kit ejects with the crewmember during an ejection.

Abstract: A yaw fin deployment apparatus provides a continuous depolyment force to fin during the entire range of deployment. A shaft, a movable sleeve bearing for riding along the shaft, a strut connected between the sleeve bearing and the fin, and a lanyard for continuously pulling the sleeve bearing along the shaft are provided. The momentum created when the ejection seat separates from the aircraft is transmitted to the lanyard, to the sleeve bearing, and to the strut for deploying the fin. A pulley is attached to the seat and is located near the aft end of the shaft and guides the lanyard to assure that the actuation force exerted on the sleeve bearing is in a direction parallel to the axis of the shaft. When the fin is fully deployed, the lanyard separates from the sleeve bearing through a split ring at the bottom of the sleeve bearing. A primary spring-loaded latch located at the aft end of the shaft locks the fin in a fully deployed position.

Abstract: An escape device such as an ejection seat system (10) has a propulsion system (42) that accelerates and changes the angular orientation of the device. The system (10) includes sensors (54) for determining certain parameters associated with device altitude, attitude, and sink rate. A microprocessor (36), operatively connected to both the sensors (54) and the propulsion system (42), operates the propulsion system so that the device will move at desired acceleration levels and turn to a desired attitude.

Abstract: A safety chamber of the telescopic type usable for an airplane includes a plurality of wall segments, granular cushioning materials and a parachute. As long as it is not in use, the wall segments are accommodated in a contracted state in the space on the ceiling of the airplace. In the event of an occurrence of emergency the wall segments are lowered one after another to constitute a chamber in which a single seat assembly is incased together with passengers sitting thereon. When the lowermost wall segment reaches the floor of the airplace, a plurality of hooks around the lower edge thereof are engaged with recessed parts on the bottom of the seat assembly and at the same time the cushioning materials fall down from the ceiling while expanding by themselves whereby the hollow space in the expanded chamber surrounding the passengers is filled with cushioning materials for the purpose of preventing the passengers from the influence of shocks.

Abstract: A system and method for stabilizing an aircraft ejection seat and crew member after seat ejection and prior to main parachute inflation. The system also providing for delayed opening of the main chute until air speed and altitude have decreased to an acceptable parachute inflation range.

Abstract: Inner catapult tubes (8) of aircraft (2) are pivotably mounted on the upper rear portion of ejection seat (12). When they separate from outer catapult tubes (4), tubes (8) pivot upwardly and rearwardly to form stabilizing booms (8). A drag device (30,30',30") is stowed inside the outer end of each boom (8) and extends axially outwardly therefrom upon deployment to apply a small drag load to the upper portion of seat (12) and counteract a tendency of seat (12) to pitch forward during operation of stabilization control rockets (18,20). The drag surfaces of devices (30,30',30") are folded around a center shaft (32,32',32") when stowed and extend radially outwardly from shaft (32,32',32") when deployed. The drag device may be a ram air inflatable device (30), a split tube/daisy petal device (30"), or a device having spring steel ribbons (40) forming a tuft-like appendage (30'). Ribbons (40) are wound around shaft (32' ) when stowed and spring radially outwardly from shaft (32') upon deployment.

Abstract: Seat with protecting shell, fastened to a floor contained inside two hinged hollow hemispheres, suitable to close onto each other, provided with a back constituted by articulated segments. The seat is furthermore equipped with safety devices housed within special hollows provided inside the same shell.

Abstract: A crewmember (12) is positioned within an ejection seat or other escape device (10). The escape device (10) is ejected from the aircraft or other flying vehicle when it is desired to effect an escape. At the start of ejection, the altitude, sink rate and roll angle of the escape device (10) are determined, by appropriate sensors (128, 132). A microprocessor (66) is used for dividing the altitude by the sink rate to obtain a first time value. The microprocessor (66) is used to divide the roll angle by a desired rate of roll angle correction, to obtain a second time value. The second time value is subtracted from the first time value to obtain a third time value, t.sub.c. In response to t.sub.c being larger than a predetermined value, the microprocessor (66) controls separation to subject the crewmember (12) to a relatively low injury risk level. In response to t.sub.

Abstract: A parachute system for an airman ejected from an aircraft in an ejection seat includes at least one drouge parachute housed within a rigid hollow container. In conventional manner, the drogue parachute is connected by lines with releasable attachments on the seat, one of the lines being further connected with the main parachute so that the latter will be deployed after release of said attachments. The container is formed as a projectile mounted in a gun mounted on the ejection seat. The container has, at its end facing away from the direction in which it is fired, a closure connected with the lines and with the drogue parachute. When the container and closure are fired from the gun, and the closure is arrested abruptly by the lines, the container continues in its trajectory whilst the drogue parachute is drawn from the container and deployed by the lines.

Abstract: A programmable crewmember emergency ejection system is disclosed which will eject the crewmember expeditiously from a disabled aircraft, while at the same time assuring that the crewmember will not be subjected to forces that are beyond crewmember tolerance. This is accomplished by a control system involving sensors having signals that are processed and used to vary ejection thrust and acceleration onset rate. The system involves a two phase ejection: A catapult phase followed by a rocket phase, both phases cooperating to provide a substantially constant maximum thrust that is well within human tolerances such that a second jolt to the crewmember is substantially minimized.

Abstract: An ejection seat (10) having roll thrusters (38, 40, 112, 114) and propellant chambers in the inner catapult tubes (44, 46, 124, 126). The roll thrusters (38, 40, 112, 114) are adapted to roll the seat (10), when ejected from an inverted or unsatisfactory attitude to an upright proper attitude. Solid propellants (44, 46, 128, 130) within the inner catapult tubes are to be ignited after the seat is being ejected. There is a roll thruster valve housing (36, 110) connected to both roll thruster nozzles (38, 40, 112, 114) and to both inner catapult tubes (24, 26, 124, 126) so that propellant gas may flow from both catapult tubes to both nozzles. The check valve (52) in each inner catapult is operable to open during ejection by ejection gas and is operable to close by the roll thruster gas when the roll thruster propellants are ignited. The check valve system modulates the catapult gas pressure during ejection, prior to roll thruster propellant ignition.

Abstract: In the operation of modern tactical aircraft, crew members are subjected to periodic high acceleration loads that cause fatigue and a decrease in operating capacity. Restraining the torso of a crew member and pulling the crew member back against the ejection seat (2) of the aircraft would help prevent such fatigue. Known restraint and haul back apparatus for use during ejection are not adapted for repeated in flight use. The invention provides a single mechanism that retracts torso restraint straps (6) any number of times during in flight maneuvering and also retracts straps (6) for ejection. A loop (7) of each strap (6) extends around an inflatable member (28). When in flight acceleration loads exceed a preset limit, engine bleed air inflates member (28) to expand loops (7). This retracts straps (6) and positions the crew member. Member (28) is allowed to deflate when the acceleration subsides. When the ejection procedure is initiated, a gas generator (44) inflates member (28).

Abstract: A crashworthy helicopter cockpit having a pyrotechnic system actuated by a stroking pilot seat for repositioning the upper portion of the cyclic control stick upon a severe or crash landing that is independent of aircraft electric and hydraulic systems.

Abstract: A thermal blast shield (64) is located on an aircraft (10) between two adent seats (20 and 22) to be stored in a housing (62) during normal aircraft operation. The thermal blast shield includes cables (84 and 86) passing through fairleads attached to the aircraft and then connected to the seats to pull the shield out of the housing and fully deploy it as the seat is ejected. A break-away mechanism (100, 102) causes the cables to break/separate after the thermal blast shield is fully deployed and jamming/locking mechanisms (104, 106) further control deployment of the thermal blast shield and preclude its post-deployment retraction. The thermal blast shield can be stowed window-shade like or accordianfold-like, and can be formed of a variety of flexible thermal resistant, blast resistant materials.

Abstract: Emergency oxygen system of the type where masks are in compartments in the backs of aircraft seats uses an underseat compartment located under the plane of the seat cushion to house the large canister of chemicals which generate the oxygen when the canister is activated. A spring loaded cable connects the two compartments so that when any of the tether cords connected to each mask is pulled, a locking pin is pulled free from a release mechanism for the cable. Once released, the cable spring immediately moves the cable axially so its lower end can actuate another release mechanism in the canister compartment to activate the canister and produce oxygen. Since the canister can reach a temperature of over 500.degree. F., its removal from the seat back reduces any possibility of burns to passengers while allowing for a lower back height and less back thickness, thereby providing more passenger living space and less obstruction to viewing of visual entertainment.

Abstract: A seat-mounted parachute employs two-way stretch material to prevent the ease cord for canopy glide control from bunching or binding.

Abstract: An aircraft ejection seat is provided with deployable fins for stabilizing aw rotation. The fins are normally stowed along the sides of the ejection seat. During ejection, the fins are deployed aft of the seat by means of rotational actuators. Anti-entanglement sheets are collapsibly disposed between the fins and the sides of the seat in order to prevent fouling of the parachute.

Abstract: A parachute deployment sequencer includes two sequencer systems in electromagnetic shielding housings. Each housing contains two bellows connected to pitot tubes, a third bellows for measuring ambient pressure and three switch contact sets connected in series, each contact set being operated by one of the bellows. Each housing also contains a battery actuated by seat ejection and a deployment firing circuit with a series switch circuit in between. After ejection, deployment is initiated when all three switches are closed.

Abstract: An ultralight aircraft and/or pilot recovery system includes a parachute having a canopy connected by means of a plurality of shroud lines to a first elongated cable having a length to position the parachute clear of the aircraft engine and propeller with a second cable for connecting the parachute to the frame of the aircraft and including a harness worn by the pilot which includes a pouch for containing the canopy folded within an inner pouch to permit the pilot to grasp and toss the chute clear of the aircraft for deployment for recovery of the aircraft. An alternate embodiment provides for connecting the parachute to the harness worn by the pilot and securing the harness to the aircraft to thereby give the pilot the option to recover the aircraft or cut loose from the aircraft for pilot recovery only.

Abstract: A line cutter or discharge valve responsive to aircraft attitude is posited on an aircraft ejection seat to interrupt the gas initiated sustainer rocket system. During inverted ejections, the cutter or valve will either sever or discharge pressure from a tube which leads from the firing squib to the sustainer rocket. Preventing sustainer rocket ignition enhances inverted ejection survivability by reducing crew member velocity toward the ground, thereby lengthening the time available for parachute deployment.

Abstract: A yaw stabilization system for an aircraft ejection seat having a vane for sensing the angular offset of the yaw air flow velocity vector and for extending paddles into the air stream in response to the velocity vector offset. The extended paddle is acted upon by the air stream to provide a restoring moment around the center of gravity of the seat and occupant to return the seat to the desired attitude with respect to the air flow velocity vector.