656results about "Aircraft ejection means" patented technology

A method and apparatus for a composite helicopter comprising a rotary wing parent vehicle with various modular cabins detachable therefrom to facilitate various configuration aircraft platforms, dual operation and modular economy.

Methods and systems for an automated safety device inspection system for a vehicle are provided. The system includes an RFID reader including a transmit portion and a receive portion wherein the reader is physically translatable along a predetermined path, a directional antenna communicatively coupled to the reader wherein the antenna is configured to transmit and receive radio frequency (RF) signals in a direction substantially normal to the path, a relative position indicator configured to determine a relative position of the reader from a starting point, and a controller communicatively coupled to the reader. The controller includes a user interface, a processor communicatively coupled to the user interface, and a database communicatively coupled to the processor wherein the database includes location data of a plurality of safety devices in a plurality of different types of vehicles, the processor is configured to control the transmitted RF signals based on the location data.

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.

The invention provides the application and design for embedding a bionic honeycomb-shaped active safety escape capsule into an aircraft. The application and design comprise the following related technologies including redesign of a main machine body of the aircraft for the embedded type bionic honeycomb-shaped active safety escape capsule, internal space layout design of the main machine body of the aircraft for the embedded type bionic honeycomb-shaped active safety escape capsule, design of an escape capsule embedded type shell and the shape, analysis of influences of the embedded escape capsule on the overall load of the aircraft, integral analysis and determination of flight aerodynamic load data, selection of an escape capsule material, escape capsule ejection mode analysis and ejection device design, logic design of launch motion of the escape capsule, internal space structure analysis of the escape capsule; active safety design of space landing of the escape capsule, description of flight dynamics influences of the escape capsule on the aircraft during and after separation, and design of an active help seeking system of the escape capsule. In this way, the application and design for researching and manufacturing the bionic honeycomb-shaped active safety escape capsule embedded into the aircraft are achieved.

This invention relates to the design of a Modular Aerospace Plane (MAP) comprising a forward fuselage section, a main wing section, a tail section and wing attachments. Various sections can be integrated to offer a variety of aircraft characteristics, performance and missions. This modular design offers a new method of aircraft fabrication, maintenance, repair and ground handling to reduce costs for the manufacturers, owners and operators. The forward fuselage and tail sections may utilize a parachute device whereby these sections can separate in an emergency and safely lower the occupants to the ground.

An impact protection apparatus is provided, comprising a gas container configured to hold a compressed gas and an inflatable member configured to be inflated by the gas and function as an airbag of a movable object, such as an aerial vehicle. A valve controls flow of gas from the container to the inflatable member in response to a signal from a valve controller. The valve and valve controller are powered by an independent power source than one or more other systems of the movable object. A safety mechanism may also be provided that, unless deactivated, prevents inflation of the inflatable member.

A safety pre-impact deceleration system for a variety of conveyances includes a parachute structure formed from air bags inflated with gas. Alternatively, the parachute structure includes a canopy with orifices. Air spaces in the parachute structure or orifices in the canopy have adjustable and selective dimensions to control the operational parameters of the vehicle. The system includes sensors and rapid exposure rate cameras with continuous loop recording to measure operational parameters of the vehicle and to predict possible collision. Once a collision condition is detected, audio / video images are stored on storage media. The air bags are deployed and inflated. In addition to air bags constituting the parachute structure, a plurality of air bags are provided to be deployed external the vehicle to aid in a safe landing.

An assembly and a method for stowing away and removing a survival kit in a passenger cabin of an aircraft, comprising a first stowage compartment that may be put in place in a floor of the passenger cabin, wherein the first stowage compartment is equipped for completely accommodating the survival kit and for leading out a hook that is connected to the survival kit by way of a strap, which hook is used for hooking the survival kit to an attachment means of a rescue device with the first stowage compartment remaining closed.

A crash attenuation system for an aircraft, the system having an airbag carried by the aircraft and inflatable generally adjacent an exterior of the aircraft. The airbag has at least one vent for releasing gas from the interior of the airbag. A first gas source is in fluid communication with the interior of the airbag for inflating the airbag with gas generated provided by the first gas source. A vent valve is provided for controlling a flow of gas through each vent, each vent valve being selectively configurable between an open state, in which gas can pass through the associated vent from the interior of the airbag, and a closed state, in which gas is retained within the interior of the airbag. A second gas source is provided for at least partially re-inflating the airbag after venting of gas through the at least one vent.

The present invention is a lighting system for providing illumination to an aircraft evacuation slide. Light sources are safely utilized with an existing evacuation slide, a substantial improvement over prior assemblies that use a hard, plastic housing enclosing the light source. The invention increases light transmission, eliminates housing cracking, inadvertent puncturing, clouding, and decreases weight and cost of conventional slide systems. Each assembly comprises a mounting surface and a printed circuit board thereon, light sources, preferably light-emitting diodes (LEDs) mounted on the mounting surface, the light sources illuminating the aircraft evacuation slide, and a flexible containment covering, such as a heat shrink wrap that covers the assembly and protects the light sources. A protective shield can cover the mounting surface while allowing the LEDs to protrude through an aperture in the shield, protecting the LEDs from damaging forces while allowing light to illuminate the landing area.

An aircraft for unmanned aviation is described. The aircraft includes an airframe, a pair of fins attached to a rear portion of the airframe, a pair of dihedral braces attached to a bottom portion of the airframe, a first thrust-vectoring (“T / V”) module and a second T / V module, and an electronics module. The electronics module provides commands to the two T / V modules. The two T / V modules are configured to provide lateral and longitudinal control to the aircraft by directly controlling a thrust vector for each of the pitch, the roll, and the yaw of the aircraft. The use of directly articulated electrical motors as T / V modules enables the aircraft to execute tight-radius turns over a wide range of airspeeds.

An aircraft for unmanned aviation is described. The aircraft includes an airframe, a pair of fins attached to a rear portion of the airframe, a pair of dihedral braces attached to a bottom portion of the airframe, a first thrust-vectoring (“T / V”) module and a second T / V module, and an electronics module. The electronics module provides commands to the two T / V modules. The two T / V modules are configured to provide lateral and longitudinal control to the aircraft by directly controlling a thrust vector for each of the pitch, the roll, and the yaw of the aircraft. The use of directly articulated electrical motors as T / V modules enables the aircraft to execute tight-radius turns over a wide range of airspeeds.

An aspirator for inflating an aircraft evacuation slide, emergency raft or other inflatable device includes a flexible, collapsible aspirator barrel that is inflated during operation to form a substantially rigid tube. According to one embodiment, the inflatable support member receives a flow of high pressure air directly from the aspirator injector nozzle assembly. According to another embodiment, the collapsible aspirator barrel receives a flow of high pressure gas directly from the high pressure inflation source. Because the aspirator barrel of the present invention is collapsible, the present invention occupies significantly less space when stored than an equivalent aspirator with a rigid aspirator barrel.

A method of automatically triggering an emergency buoyancy system (10) for a hybrid helicopter (20) having a fuselage (21), two half-wings (23, 23′), and two propulsive propellers (24, 24′). During the method, said emergency buoyancy system (10) is primed, and then if a risk of said hybrid helicopter (20) ditching is detected, two retractable wing undercarriages (28, 28′) are deployed, each wing undercarriage (28, 28′) being fastened under a respective half-wing (23, 23′) and being provided with at least one immersion sensor (16). Finally, if the beginning of said hybrid helicopter (20) ditching is detected, at least one main inflatable bag (11, 11′) 7B suitable for being arranged under such fuselage (21) and at least one secondary inflatable bag (12, 12′) suitable for being arranged under each half-wing (23, 23′) are inflated so as to ensure that said hybrid helicopter (20) floats in stable manner.

An emergency floatation system associated with a landing gear of a rotorcraft comprising at least a float unit and a raft module. The float unit is formed by a base and a float cover with an inflatable float being positioned therebetween. The raft module is formed with a raft compartment adapted to receive an inflatable raft in the packed condition thereof. The raft module is supported on the float by the base. The raft is adapted for inflation and deployment from the raft module independently of the float deployment.

A safety pre-impact deceleration system for a variety of conveyances includes a parachute structure formed from air bags inflated with gas. Alternatively, the parachute structure includes a canopy with orifices. Air spaces in the parachute structure or orifices in the canopy have adjustable and selective dimensions to control the operational parameters of the vehicle. The system includes sensors and rapid exposure rate cameras with continuous loop recording to measure operational parameters of the vehicle and to predict possible collision. Once a collision condition is detected, audio / video images are stored on storage media. The air bags are deployed and inflated. In addition to air bags constituting the parachute structure, a plurality of air bags are provided to be deployed external the vehicle to aid in a safe landing.

A crash attenuation system for an aircraft, the system having an airbag carried by the aircraft and inflatable generally adjacent an exterior of the aircraft. The airbag has at least one vent for releasing gas from the interior of the airbag. A first gas source is in fluid communication with the interior of the airbag for inflating the airbag with gas generated provided by the first gas source. A vent valve is provided for controlling a flow of gas through each vent, each vent valve being selectively configurable between an open state, in which gas can pass through the associated vent from the interior of the airbag, and a closed state, in which gas is retained within the interior of the airbag. A second gas source is provided for at least partially re-inflating the airbag after venting of gas through the at least one vent.

A semi-active seat cushion is disclosed that comprises a plurality of chambers for containing a pressurized fluid, wherein each chamber is connected to at least one other chamber by an orifice that provides a fluid connection; a supply conduit for supplying a pressurized fluid to each of the plurality of chambers; and at least one relief valve that permits rapid and controlled deflation of the plurality of chambers.

An emergency equipment system comprising an elongate member, an emergency equipment package, and a cutter. The elongate member may have a first end and an angled end. The emergency equipment package may have a sleeve on one side capable of receiving the elongate member from the angled end. The cutter may be attached to a side of the elongate member and may be capable of cutting the sleeve.

An emergency evacuation slide system includes a control valve having a normally-open vent that closes after a predetermined period of time calculated to vent excess inflation gas produced by the gas generator. In operation, in the event of an aircraft emergency exit door being opened in the “armed” condition, the primary valve member of the control valve is opened allowing inflation gas to flow into the valve chamber. A portion of the gas entering the chamber is vented through the normally-open vent. After a predetermined period of time calculated to be sufficient to vent the excess inflation gas, the normally-open valve is closed to divert 100% of the remaining inflation gas into the evacuation slide.

An inflatable evacuation slide includes a flexible slide surface that is supported by longitudinal main support members. Illumination of the slide surface is provided by a plurality of illumination sources that are supported above the upper surface of the main support members on inflatable stanchions that extend upward from the upper surface of the main support members. The plurality of illumination sources may be high efficiency light emitting diodes or other high efficiency light sources. By providing an illumination source that is elevated above the upper surface of the main support members, a greater portion of the slide surface can be illuminated without shadows.

An emergency flotation device for crashed small airplanes which can be retrofited on most small airplanes as well as come preinstalled on new small airplanes, is self contained in a small container; has several independent triggering means; and has a visual as well as an RF beacon system integrated within to call for rescue.

A girt assembly for releasably connecting an evacuation slide to an aircraft includes superimposed flexible panels that are continuous at a pair of spaced connection points for connection with the aircraft. One or more catenary loops are formed in each panel for distributing forces on the flexible panels along a length of the loops. The connection points may be releasably connected to a girt bar with spaced bracket assemblies or directly connected to floor brackets associated with the aircraft.

An autonomous passenger module is releasably carried on a super-sonic aircraft, such as a military fighter jet, for carrying plural passengers on supersonic and near space flights. The passenger module is equipped with passenger service and life support systems to provide oxygen and the like, a parachute system, and a landing airbag or flotation aid system. The module remains mounted on the aircraft throughout a normal flight. In an emergency situation, the module separates from the aircraft by means of releasable connector elements and descends using parachutes. The module provides high passenger capacity at a low cost in a simple manner for commercial supersonic flights using an existing supersonic aircraft as a carrier platform.

The invention discloses a protection device for tumbling out of control of a rotor type unmanned aerial vehicle (UAV), and the technical scheme thereof is characterized in comprising ejection cylinders, a high-pressure gas cylinder, ejection opening and closing doors, a posture sensor and a control module, wherein top plates are mounted inside the ejection cylinders; each top plate divides the corresponding ejection cylinder into a high-pressure chamber and an ejection chamber; each ejection chamber is provided with a self-throwing parachute and the bottom of each high-pressure chamber is provided with an air inlet; the high-pressure gas cylinder is respectively connected with the air inlets of the two ejection cylinders through air duct pipes, and electromagnetic valves are respectively mounted near the two air inlets; the ejection opening and closing doors are hinged to the opening of the ejection cylinders; hinge shafts are provided with torsion springs; fixed parts for closing the ejection opening and closing doors at the opening of the ejection cylinders are mounted on the ejection cylinders; the posture sensor is arranged in a UAV body to periodically detect posture change data of the UAV body; and the control module receives the posture change data and outputs a corresponding control signal to the corresponding solenoid valve and the corresponding fixed part according to an angle of inclination to control the self-throwing parachute in the corresponding ejector cylinder to be forced out of the corresponding ejection chamber under the high pressure gas.

The present system provides a buoyancy system for moving an object (401) in a body of water. The system comprises at least one inflatable body (17) which, when inflated, increases the buoyancy of the object (401), and an inflation apparatus (37) to inflate the at least one inflatable body (17). The system also comprises an activation system (21) to activate the inflation apparatus (37). Upon activation of the activation system (21) the inflation apparatus (37) causes gas to flow to the at least one inflatable body (17), causing the object (401) to move. The inflation apparatus may comprise a hydrostatic sensor (407) and pressure relief valves (91, 93) to automatically control the depth of the object and a guide wire (411) to aid locate the object on the surface.

A head and neck restraint system includes a headpiece, a saddle, and tensioners connecting the headpiece to the saddle. The headpiece resides on top of a crew member's head and the saddle includes a saddle strap residing under the crew member's buttocks. The tensioners are pneumatic muscles which contract when a flow of gas is provided by gas generators. The gas generators are triggered by a G-sensor or by the initiation of a predetermined event. Triggering signals pass through a manifold from an ejection seat, aircraft, or vehicle. Contraction of the pneumatic muscles pulls the headpiece toward the saddle, thereby restraining the head, neck, and spine. The system is worn as an undergarment or incorporated into a garment. A manual adjustment provides head support during flight. The system is particularly useful for preventing head and neck injuries during ejection from or crash of an aircraft or vehicle

An inflatable evacuation slide system includes an inflatable evacuation slide stored in a packboard compartment the cover panel of which is retained by a plurality of frangible pneumatic latches. The frangible pneumatic latches each comprise a tension member one end of which is attached to the packboard housing and the other end of which is releasably attached to the cover panel. In normal operation, a pneumatic signal operating on an actuator piston withdraws the piston to allow the latch mechanism to release the cover panel. In the event of a failure of the release mechanism, since the releasable latch secures the cover panel to the frangible tension member rather than to the packboard directly, the force of the inflating evacuation slide breaks the frangible member allowing the cover panel to drop away with only a brief delay in slide deployment.