187results about "Aircraft ejection means" patented technology

Ejection seat systems include an ejection seat and a propellant assembly mounted to the ejection seat. A nozzle assembly having an adjustable nozzle is moveably attached to the ejection seat and configured to receive propellant exhaust from the propellant assembly and exhaust through the adjustable nozzle. A first linear electric actuator is operably connected to the adjustable nozzle and arranged to adjust an orientation of the adjustable nozzle in a first direction and a second linear electric actuator is operably connected to the adjustable nozzle and arranged to adjust an orientation of the adjustable nozzle in a second direction. The second direction includes a directional component that is normal to the first direction. A control module is configured to control operation of the first linear electric actuator and the second linear electric actuator.

An inflation control system for an inflatable may comprise a compressed fluid source, a valve module, a temperature sensor, and a controller. The valve module is connected to the compressed fluid source and configured to control a flow of gas to the inflatable. The temperature sensor measures an ambient temperature and outputs the ambient temperature measurement. The controller is operably coupled to the valve module and configured to receive the ambient temperature measurement and determine an open-valve time based on the ambient temperature measurement, the open-valve time being a duration of time the valve module is in an open position.

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 includes a body. The body includes an electronics chamber and an inflation chamber. The apparatus further includes a pressure sensor coupled to the body. The apparatus further includes a plurality of connector assemblies coupled to the inflation chamber. The apparatus further includes inflatable bags, where each inflatable bag is coupled to an individual connector assembly of the plurality of connector assemblies. The apparatus further includes a transmitter located within the electronics chamber. The apparatus further includes a processor located within the electronics chamber and coupled to a memory device. The processor is configured to detect submersion of the body in water, send a signal to cause initiation of a reaction in the inflation chamber, and cause the transmitter to send a data transmission.

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 utility model discloses an electric vertical take-off and landing aircraft, and relates to the technical field of aircrafts. The electric vertical take-off and landing aircraft comprises an aircraft body, a plurality of battery modules and a plurality of safety protection devices. Wherein a plurality of propellers are arranged on the machine body, and the propellers are driven by a motor. The plurality of battery modules are arranged on the machine body, the battery modules supply power to the motor, and each battery module comprises a plurality of batteries. One end of the safety protection device is connected with the machine body, the other end of the safety protection device is connected with or abuts against the battery, and the safety protection device detects the working state of the battery. And when the working state of the battery is detected to be abnormal, the safety protection device separates the battery in the abnormal state from the machine body.

A system for providing an indication of slide pack density is provided. The system includes a set of stretch sensors and a control unit coupled to the set of stretch sensors. The control unit is configured to receive an input from a stretch sensor in the set of stretch sensors; compare the input to a first predetermined threshold; and, responsive to the input meeting or exceeding the first predetermined threshold, transmit a signal that causes an indicator to illuminate, providing an alert associated with a condition of a slide pack.

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.

A stretch senor assembly may comprise a stretch sensor, a first housing and a second housing. The stretch sensor may include a first mounting end, a second mounting end, and a sensing region extending between the first mounting end and the second mounting end. The first housing may define a connector opening and the first mounting end may be located in the first housing. The second housing may be located around the second mounting end.

The application discloses a rocket ejection seat control method and system under an inertial navigation fault working condition, a program controller receives and processes data of PIU1 and PIU2, an overload sensing device and a pressure altitude sensor in real time, when chair-mounted inertial navigation communication fails or data is unavailable, the program controller adopts data in the PIU1 to perform mode determination and uses data collected by the pressure altitude sensor to complete remaining height control, when the PIU1 data is abnormal, the program controller adopts data in the PIU2 to perform mode determination and uses data collected by the pressure altitude sensor to complete remaining height control, when the PIU2 data is abnormal, the program controller uses data collected by the overload sensing device to perform mode determination and uses data collected by the pressure altitude sensor to complete remaining height control, and when the overload sensing device is abnormal, the program controller performs fixed delay time control. The application guarantees lifesaving performance of the ejection seat under the inertial navigation fault mode, and improves reliability and safety of rocket ejection lifesaving.

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.

To provide a convenient and safe vehicle.SOLUTION: An airbag extending to the outside of a vehicle body is inflated by igniting a gas generator when a monitor with a speed measuring instrument detects danger. Furthermore, solar power generation by a solar panel provided on a roof of the vehicle body, self-generated power by driving of propellers and tires, and hydrogen fuel are utilized to address energy issues and CO2 emission issues. In addition, even if one blade of a propeller encounters an abnormality, the other propeller can continue driving in a form of four-propeller-driving and in which the propeller has double blades in one set. A parachute for an escape in the event of an accident is provided.SELECTED DRAWING: Figure 1

A system (100) and a method include an emergency exit door (102) for an internal cabin (104, 230, 260, 281) of an aircraft (106). The emergency exit door (102) includes a window (110), and a lever (108) configured to be engaged to open the emergency exit door (102). One or more alert devices (111) are configured to emit one or more alerts to remind an individual to first look through the window (110) before engaging the lever (108).

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.

This invention discloses a smart pilot protection and rescue system. This system constructs an intelligent workflow from three aspects of intelligent functional characteristics: perception, decision-making, and action. It comprehensively optimizes the decision-making modules of three subsystems: intelligent active protection, intelligent ejection rescue, and wearable human-machine interaction, forming a powerful, responsive, and AI-powered situational diagnosis subsystem. This enables a significant transformation of the protection and rescue system from a passive, non-intelligent agent to an active, intelligent agent. Based on the pilot's personalized physiological, behavioral, and intentional information, it shifts from a broad, general performance model geared towards the general population to a refined, optimization-oriented model focused on the individual. It can systematically meet the protection, rescue, and wearable human-machine interaction needs of next-generation and future highly intelligent fighter jets (including smart cockpits), ensuring pilot safety while enhancing their situational awareness and decision-making response capabilities, thereby improving their combat effectiveness.

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 utility model discloses a sinking type buoy installation structure which comprises a buoy cabin, a skin and a connecting assembly. The back surface of the buoy cabin is matched with the outline of a helicopter body at the buoy cabin mounting position; a counter bore is formed in the position of the connecting assembly on the back surface of the buoy cabin; a through hole is formed in the position, connected with the assembly, of the skin. The connecting assembly comprises a mounting seat, a pressing seat and a threaded part, the mounting seat is placed in the counter bore and does not protrude out of the counter bore, the pressing seat abuts against the front face of the skin, threaded holes are formed in the mounting seat and the pressing seat, and the threaded part is located on the front face of the pressing seat and is matched in the threaded holes of the mounting seat and the pressing seat at the same time to clamp the buoy cabin and the skin together. By means of the structure, the buoy cabin can be completely attached to the helicopter body without gaps, the risk that water enters the buoy cabin is avoided, and glue failure caused by stress concentration is avoided.

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.

Described are fabrics or flexible composite materials for an inflatable safety product. The fabrics or flexible composite materials may include a substrate and a metallic layer. The substrate may define a surface. The metallic layer may be completely covering or discontinuous, and the metallic layer may cover at least one surface of the substrate.

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.