119results about "Aircraft ejection means" patented technology

An ejection seat includes an ejection seat sequencing system. The sequencing system enables time delays to various components of the system, such the drogue parachute, the main parachute, and harness release cartridge. A sequence controller receives data for a parameter, such as airspeed, from at least two sensors. The sequence controller selects a sequence timing delay mode to implement the time delays for the components of the sequencing system. The sequence controller also accesses a lookup table in a database accessible by the sequence controller. The sequence controller uses a delay parameter of the lookup table to modify a time delay within the sequence timing delay mode, as configured by a user.

An apparatus associated with a vehicle, includes a body, wherein the body includes a chamber. The apparatus further includes a buoyancy ring coupled to the body. The apparatus further includes a battery located within the chamber. The apparatus further includes a transmitter, wherein a portion of the transmitter is disposed within a recess of the body. The apparatus further includes a processor located within the chamber and coupled to a memory device, wherein the processor is configured to: receive a signal indicating detection of submersion of the vehicle in water, send a signal to switch a power source from the vehicle to the battery, send a signal to cause inflation of an inflatable bag, and cause the transmitter to send a data transmission.

An electronic drogue reefing release system includes a drogue parachute having a canopy, one or more reefing lines coupled to the canopy, one or more reefing line cutters coupled to the canopy, and one or more signal lines configured to deliver an electrical signal. The reefing lines are configured to restrict expansion of the canopy while in a first reefing state. The reefing line cutters are configured to place the at least one reefing line into a second reefing state in response to receiving the electrical signal so as to expand the canopy.

A lighter-than-air airship has an exoskeleton constructed of spokes and hubs to create a set of connected hexagrams comprised of isosceles triangles wherein the spokes flex and vary in length to produce the slope of said airship's surface. In one embodiment, the exoskeleton connects to a nose cone that includes a cockpit cabin for controlling the airship's operation from a single location that can be physically separated from the exoskeleton in response to catastrophic events and for autonomous and / or remotely piloted operation. An improved means is also provided for landing and unloading cargo, and through use of unmanned aerial vehicles in another embodiment, the airship is configured for remote pickup, transport, delivery and return of payloads such as packages. In yet another embodiment, the airship provides a communications platform for beam form transmission and satellite signal relay, including in combination with the foregoing disclosed attributes.

This invention, relates to a body (2), a door (3) on the body (2), which allows the user access to the body (2) or prevents access to the body (2), at least one hinge (4) on the door (3), allowing the door (3) to be supported on the body (2) and allowing the door (3) to be opened by pivoting around the axis on which it is supported on the body (2), at least one trigger (5) to trigger the door (3), a first hinge channel (6) located on the hinge (4) and having a through opening, at least one hinge pin (7) located on the hinge (4) and extending along its length, a closed position (I) in which the door (3) encloses the body (2) in a form-fitting manner, the door (3) being closed on the body (2), an open position (II) in which the hinge pin (7) contacts the first hinge channel (6) within the first hinge channel (6), the door (3) being moved outwardly from the body (2) by means of rotation of the hinge (4) from the closed position (I) to allow the user to access the body (2), an emergency trigger position (III) in which the hinge pin (7) protrudes from the first hinge channel (6) and there is a distance between the first hinge channel (6) and the hinge pin (7), in which the trigger (5) is triggered in the event that the user needs to be evacuated from the body (2), an evacuation position (IV) in which the door (3) is brought from the emergency trigger position (III) so that the hinge (4) and the body (2) move independently of each other, and the door (3) and hinge (4) are pushed out of the body (2), allowing the user to evacuate from the body (2), at least one latch (8) located on the door (3), which allows the door (3) to be locked, at least one latch holder (9) located on the body (2), which enables the door (3) to be locked in the closed position (I) by being placed in the latch (8), and which enables the door (3) to be opened in the open position (II) when it is brought out of the latch (8) so as to keep a distance between it and the latch (8).

The invention discloses a design method of a connecting cloth assembly of a cabin door and a slide and the connecting cloth assembly. The length sum of front connecting cloth and back connecting cloth from respective separated ends to the convergence end of the front connecting cloth and the back connecting cloth is determined; the separated ends of the front connecting cloth and the back connecting cloth are set to be connected to the highest point a and the lowest point b in the horizontal direction of a cylinder at the end of the slide respectively, and the convergence end of the front connecting cloth and the back connecting cloth is located on a threshold of the cabin door. According to the geometrical relationship and stress condition selection of the slide, the front connecting cloth, the back connecting cloth and the threshold under the normal threshold condition and the minimum threshold condition, the grounding angle between the slide and the ground under the normal threshold condition and the grounding angle between the slide and the ground under the minimum threshold condition are all in a proper range. And the upheaval angle of the highest point of the slide relative to the threshold is in a safe range under the condition of the minimum threshold. The method can maintain the grounding angle, and can prevent the highest point of the slide from protruding too high relative to the threshold.

The invention relates to the technical field of engine recovery, in particular to a turbojet engine ejection recovery system and method in an aircraft fault state, and the system comprises an ejection mechanism which is arranged between a turbojet engine and an aircraft and used for disconnecting the turbojet engine from the aircraft. The turbojet engine is ejected out of the aircraft; the cut-off mechanism is arranged in the aircraft and used for cutting off an oil way and a circuit of the turbojet engine. The protection mechanism comprises a parachute assembly and an air bag assembly, the parachute assembly is connected with the turbojet engine, and a parachute is automatically opened in the landing process of the turbojet engine; the air bag assembly is folded and contracted outside the turbojet engine and automatically expands to wrap the turbojet engine in the landing process. The recycling device is compact in structure and flexible and convenient to use, recycling of the turbojet engine can be efficiently and safely completed when the fixedly-mounted turbojet engine is in an emergency, and the technical requirement for recycling of the turbojet engine in the field is met.

The application discloses a comprehensive helmet and active separation device of ejection seat in ejection rescue and a use method, the device comprises an anti-loose connector, a lever clamping mechanism, an electrically excited fire gas mechanism and a socket fixing mechanism, and the anti-loose connector, the lever clamping mechanism, the electrically excited fire gas mechanism and the socket fixing mechanism are fixed on the ejection seat; the fulcrum of the lever clamping mechanism is connected with the socket fixing mechanism; the power end of the lever clamping mechanism is aligned with the electrically excited fire gas mechanism; the resistance end of the lever clamping mechanism corresponds to the spring self-locking mechanism on the anti-loose connector of the anti-loose connector; the socket of the anti-loose connector is fixed through the socket fixing mechanism; a pull-off steel cable is installed on the unlocking mechanism of the plug; when the plug is inserted into the socket, the resistance end of the lever clamping mechanism is pressed into the space between the plug and the socket by the unlocking mechanism of the plug and is fixed by the unlocking mechanism of the plug and cannot rotate freely. The application can effectively improve the success rate of ejection rescue in a complex rescue environment.

The invention belongs to the field of helicopter flight mechanics design, and particularly relates to a helicopter floating system air opening safety analysis and verification method. Comprising the steps of 1, determining a security analysis framework; based on the unfolding process of the helicopter emergency floating system, a multi-dimensional safety analysis framework for flight state change analysis, packaging covering cap trajectory analysis and buoy deformation analysis is constructed; 2, determining a test verification scheme; a theoretical analysis result is verified through a wind tunnel test, collision damage verification and a ground simulation test; 3, carrying out a flight test; and the unfolding process of the emergency floating system is tested in actual flight.

The application relates to a device and method for improving the opening reliability of a rescue parachute of an ejection seat, and relates to the field of air dropping. The device for improving the opening reliability of the rescue parachute of the ejection seat comprises a rescue parachute box and a deceleration parachute box which are installed on the ejection seat and are connected with each other, the deceleration parachute box is configured to be separable from the rescue parachute box, the rescue parachute box is internally provided with a rescue parachute, the deceleration parachute box is internally provided with a connecting belt, a deceleration parachute and a constant force breaking rope, one end of the connecting belt is connected with a parachute rope of the deceleration parachute, the other end of the connecting belt is connected with the top of the rescue parachute box, one end of the constant force breaking rope is connected with the top of a canopy of the deceleration parachute, the other end of the constant force breaking rope is connected with the top of the deceleration parachute box. The device and method for improving the opening reliability of the rescue parachute of the ejection seat solve the bending phenomenon of the parachute rope and the canopy during the high-speed ejection of the ejection seat, avoid the problems of early inflation of the rescue parachute, serious damage and local parachute turning, avoid the safety hazards caused by the interference after the separation of the parachute box and the rescue parachute, and improve the high-speed working reliability of the rescue parachute matched with the ejection seat.

A life raft is provided. The life raft includes at least one inflatable tube, an inflatable canopy support tube coupled to the at least one inflatable tube, and a solar powered universal serial bus (USB) charger. The solar powered USB charger is coupled to the inflatable canopy support tube. The solar powered USB charger is configured to store a charge by being exposed to sunlight. The solar powered USB charger is configured to charge a mobile device responsive to being connected to the mobile device.

The invention provides a rotorcraft emergency floating device and method.The rotorcraft emergency floating device comprises a buoy assembly and an inflation assembly, and the buoy assembly comprises a right front buoy assembly, a left front buoy assembly and a rear buoy assembly and is used for providing buoyancy and floating stability for a rotorcraft; the inflation assembly comprises a cylinder valve assembly and a pipeline assembly, is used for inflating the buoy assembly and has a manual / dampening automatic starting function; a right front buoy assembly and a left front buoy assembly are symmetrically arranged on the left and right sides of the front machine body, and are cylindrical in packaging shape; the right front buoy assembly and the left front buoy assembly are in a capsule shape when being inflated and unfolded. The rear buoy assembly is of a flat box body structure in a packaging state and has a good aerodynamic configuration; the rear buoy assembly is of a three-buoy structure connected side by side in the inflated unfolding state.

A data recording apparatus, data recording system and an orientation determination method thereof is disclosed. The data recording apparatus may include a housing, a wireless communication interface, one or more memories that store executable code; and one or more processors configured to execute the executable code, which causes the one or more processors to: control the communication interface to obtain data from Flight Data Acquisition Unit (FDAU) and store the obtained data in the one or more memories. The obtained data may include one or more of flight data, cockpit data (e.g., cockpit voice data), or cabin data (e.g., cabin voice data). The data recording apparatus may include a detachable attachment means for allowing the data recording apparatus to separate from the airplane in the event of a crash via a passive detachment means.

The present disclosure relates to an inflatable evacuation slide for a maritime evacuation system, the slide having a first end, a second end, a length and a width, the slide comprising a central section extending along the length and having a central face, a first side section arranged adjacent to the central section and having a first side face, a second side section arranged adjacent to the central section on the opposite side of the first side section and having a second side face, the first side section and the second side section are extending along the length of the slide and the central section, wherein the first side face and the second side face, respectively, are arranged with an angle being less than 180 degrees relative to the central face.

The invention discloses an air bag assembly used for restraining and protecting the head and the neck and an ejection seat, the air bag assembly used for restraining and protecting the head and the neck comprises a headrest plate, two neck restraining devices and a head buffering device, the two neck restraining devices and the head buffering device are arranged on the headrest plate, and the headrest plate is used for being arranged on a seat backrest. The neck restraining devices are located on the two sides of the neck of the human body on the seat, and the head buffering device is located above the head of the human body on the seat. While the requirements for reliable structure, quick response and high adaptability are met, strong constraining force and a high energy absorption effect are actively provided for the head of a pilot, and the injury risk of the head and the neck is reduced.

This invention relates to the field of engine recovery technology, and in particular to a system and method for the ejection and recovery of a turbojet engine in the event of an aircraft malfunction. The system includes an ejection mechanism positioned between the turbojet engine and the aircraft, used to disconnect the turbojet engine from the aircraft and eject the engine outside the aircraft; a cutting mechanism located inside the aircraft, used to cut off the turbojet engine's oil and electrical circuits; and a protective mechanism including a parachute assembly and an airbag assembly. The parachute assembly is connected to the turbojet engine and automatically deploys during the engine's descent; the airbag assembly folds and retracts outside the turbojet engine and automatically expands to enclose the engine during descent. This invention has a compact structure, is flexible and convenient to use, and can efficiently and safely recover a fixed-mounted turbojet engine in an emergency, meeting the technical requirements for turbojet engine recovery in this field.

Described is a system (S, S ', S ' ', S ' ' ', Siv) for the emergency evacuation of persons from a structure (P), such as a building, ship, raised platform, stadium or the like, comprising supporting means (6), designed to be positioned at a window (F) of said structure (P) for the emergency evacuation from said structure (P); at least one load-bearing structure (1), coupled with said supporting means (6), comprising in turn a plurality of modules (Μ1-Μη, Μ'1-Μ'η), each comprising two inflatable longitudinal tubular elements (21-31, 22-32, 23-33,...) positioned parallel to each other, said modules (Μ1-Μη, Μ'1-Μ'η) being positioned in series with each other; a slide (4) having a surface on which the persons evacuated from said structure (P) can slide, said slide being interposed between said two inflatable longitudinal tubular elements (21-31, 22-32, 23-33,...) of said modules (Μ1-Μη, M'1-M'n); and a pneumatic inflation system(5) for the selective inflation of said two inflatable longitudinal tubular elements (21-31, 22-32, 23-33,...) of said modules (Μ1-Μη, Μ'1-Μ'η).

Described are inflation systems having an electric propellant device and an inflatable safety device. The electric propellant device may be configured to generate gas for the inflatable safety device, and the electric propellant device may include an electric propellant that is configured to be converted to gas by the electric propellant device using an electric current. The inflatable safety device may be positioned to receive the gas from the electric propellant device.

The present invention pertains to the field of life-saving equipment having accommodation for passengers and crew, comprising capsules (1), wherein each capsule (1) is impact-resistant, has an oval shape, and comprises a seat (2), wherein said seat (2) is provided with safety belts (4), wherein a sphere (6) is mounted to withstand an initial impact, such that when they undergo said initial impact, the spheres (6) issue a command to the seat, assisting in cushioning the impact inside the capsule (1), which is oval and formed in two parts, and is further provided with a plurality of airbags (7) strategically fastened to the internal walls, as well as apertures (8) to enable oxygen exchange with the environment, and wherein each capsule additionally comprises a manual safety system equipped with an internal battery for use in the event of aircraft failure.

The invention belongs to the technical field of unmanned aerial vehicles, and particularly relates to an eVTOL safety seat system of a heavy-load unmanned aerial vehicle, and the system comprises a sensing layer which is used for firstly measuring data of a safety seat and then collecting the measured data; the decision-making layer is used for performing real-time analysis and decision-making according to the data acquired by the sensing layer, generating a corresponding instruction and diagnosing whether the unmanned aerial vehicle has a fault or not; and the execution layer is used for correspondingly controlling the unmanned aerial vehicle according to the instruction of the decision layer. According to the invention, various sensors work cooperatively, environment information can be captured comprehensively, and the influence of loss or error of a single signal is reduced.

A system for releasing a blowout panel (110) and softcover (206) release of an evacuation slide in an aircraft is provided. The system includes a first actuator (202), a second actuator (212); and a controller. The controller is configured to receive an indication that an evacuation event has begun; and, responsive to receiving the indication of the evacuation event beginning: send a first signal to the first actuator that magnetizes a first magnetostriction material within the first actuator, thereby releasing the blowout panel of a packboard compartment (204) in which the evacuation slide is present; and send a second signal to the second actuator that magnetizes a second magnetostriction material within the second actuator, thereby releasing a key-loop of lacing (210) associated with the softcover in which the evacuation slide is present in the packboard compartment.

The invention discloses an output control method for separating parachute shooting in an ejection lifesaving seat, which comprises the following steps: separating parachute shooting electric detonators comprise two paths of separating electric detonators and one path of parachute shooting electric detonators, and the method comprises the following steps: detecting the separating electric detonators 1, 2 and the parachute shooting electric detonators in sequence when the ejection lifesaving seat is electrified for self-inspection; the ejection lifesaving seat sends the detection result of each electric detonator to the VMC through the health management data packet; and after the ejection lifesaving seat is judged to meet the releasing condition, the program controller measures the longitude, latitude, flight speed and height of the aircraft according to an inertial measurement module in the program controller, and dynamically controls the separation electric detonators and the parachute ejection electric detonators to output according to a time sequence. The problem that in an existing control mode of the ejection lifesaving seat, due to the fact that the static pressure measurement value cannot correctly reflect the real environment air pressure, the height data obtained based on the static pressure signals have large errors, and effective support cannot be provided for control over an ejection lifesaving system is solved.

A stretch senor assembly (152) may comprise a stretch sensor (200), a first housing (220) and a second housing (222). The stretch sensor (200) may include a first mounting end (204), a second mounting end (206), and a sensing region (202) extending between the first mounting end (204) and the second mounting end (206). The first housing (220) may define a connector opening (226) and the first mounting end (204) may be located in the first housing (220). The second housing (222) may be located around the second mounting end (206).

Described are gas cooling systems having a gas generator, a cooling device, and an inflatable safety device. The gas generator may be configured to generate gas for the inflatable safety device based on propellant. The cooling device may be coupled with the gas generator to receive the gas and to remove heat from, and / or expel at least a portion of, the gas to provide gas having a threshold temperature. The inflatable safety device may be coupled with the cooling device to receive the gas having the threshold temperature.

A data recording apparatus, data recording system and an orientation determination method thereof is disclosed. The data recording apparatus may include a housing, a wireless communication interface, one or more memories that store executable code; and one or more processors configured to execute the executable code, which causes the one or more processors to: control the communication interface to obtain data from Flight Data Acquisition Unit (FDAU) and store the obtained data in the one or more memories. The obtained data may include one or more of flight data, cockpit data (e.g., cockpit voice data), or cabin data (e.g., cabin voice data). The data recording apparatus may include a detachable attachment means for allowing the data recording apparatus to separate from the airplane in the event of a crash via a passive detachment means.

This disclosure describes systems, methods, and devices related to a portable accessibility system. The system may comprise two or more modular tracks configured to be temporarily and securely mounted onto aircraft stairs. The system may comprise a powered lift unit (PLU) movably mounted on the two or more modular tracks, wherein the PLU configured to counteract an angle of the aircraft stairs to provide a level surface. The system may comprise a hoist mechanism integrated within the PLU, wherein the hoist mechanism includes at least one lifting cable. The system may comprise a limit switch operably connected to the hoist mechanism, wherein the limit switch configured to halt hoist operation upon reaching a defined endpoint. The system may comprise a redundant cable routing such that a failure of one cable allows continued operation of the PLU.

The application discloses a lifesaving radio starting mode conversion device, which comprises a sliding sheet, a constant force connecting rope, a sliding groove sheet and a gasket layer which are connected together and arranged on both sides of the sliding sheet, a through hole on the sliding groove sheet and a through hole on the gasket layer form a channel for the constant force connecting rope to pass through, the sliding sheet can slide a distance relative to the sliding groove sheet and the gasket layer when the sliding sheet is pushed and pulled, one end of the constant force connecting rope is connected with a lifesaving radio starting pull pin, and the other end of the constant force connecting rope is connected with a seat, the constant force connecting rope is provided with a safety device and a steel ball, the sliding of the sliding sheet makes different parts of the special-shaped hole appear in the channel for the constant force connecting rope to pass through, so that the steel ball can pass through the channel or be blocked by the special-shaped hole, and the gasket layer is connected with a lifesaving bag. The application can be applied to lifesaving bags of multiple models of rocket ejection seats, has good applicability and is simple to operate.

Example aircraft and aircraft evacuation slides and related methods are disclosed herein. An example evacuation slide assembly for an aircraft disclosed herein includes an inflatable slide body attachable to the aircraft and configured to inflate in response to an evacuation event, and a readiness indicator gate supported by the inflatable slide body, wherein the readiness indicator gate is movable from an unready position during inflation of the inflatable slide body, thereby indicating the inflatable slide body is not ready for use, to a ready position thereby indicating readiness of the inflatable slide body for user egress from the aircraft onto the inflatable slide body.

The present application relates to an aerial maneuvering apparatus, a control method thereof, and a computer-readable storage medium. An aerial maneuvering apparatus includes a seat in which a safety airbag and a parachute are stored, and an escape portion configured to support the seat mounted to the escape portion, coupled to the aerial maneuvering apparatus to form a part of the aerial maneuvering apparatus, and configured to enable a passenger to perform an emergency jump with the seat to the outside of the aerial maneuvering apparatus when the escape portion is separated from the aerial maneuvering apparatus.