358results 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.

The invention discloses an ejection device, a control method of the ejection device and electric mobile equipment, and the ejection device comprises a guide structure which is connected to a body; the ejected body is contained in the guide structure and is connected to the body in a releasable manner through a fastener; the parachute is accommodated in the guide structure in a foldable manner and is connected with the ejected body; the gas generator is mounted on the outer wall of the guide structure; wherein the fastener releases the catapulted body when responding to ignition current to be broken, and the gas generator inflates the parachute when responding to the ignition current, so that the parachute is converted into an unfolded state from a folded state, and the catapulted body is driven to fall. The dangerous source or the unit needing to be protected serves as the ejected body to be ejected from the body, damage to the body caused by fire of the dangerous source is effectively reduced, the safety of passengers is greatly improved, and an efficient and practical safety solution is provided for various scenes related to flight safety and equipment protection.

A supply glider is disclosed herein. The supply glider includes a body having a first end and a second end, the body being configured to be coupled to a host aircraft, a container disposed between the first end and the second end of the body, wings coupled to the body between the first end and the second end, and stabilators coupled to the body adjacent the second end.

The invention provides a sliding door structure with an emergency exit and an emergency throwing method thereof.In the structure, an upper sliding rail, a middle sliding rail and a lower sliding rail are fixed to a machine body structure, a sliding door slides in the upper sliding rail, the middle sliding rail and the lower sliding rail through a pulley and a swing arm, and the sliding door is provided with an emergency exit channel above the waterline position; the ball socket support, the first lock seat, the second lock seat and the sliding block are installed on the periphery of an emergency exit channel on the sliding door. The bulb hinge, the bolt throwing mechanism, the handle, the transparent protective cover plate and the interior trim panel are mounted on the emergency door; the emergency door is respectively matched with the ball socket support, the first lock seat and the second lock seat through the ball head hinge and the bolt throwing mechanism and is fixed on the sliding door; the handle is connected with the bolt throwing mechanism and is used for operating the throwing emergency door; the overland and overwater emergency evacuation requirements can be met at the same time.

A method is disclosed herein. The method includes receiving, by a processor, an ejection command for ejecting an ejection seat from an aircraft; determining, by the processor, an airspeed and an altitude of the ejection seat; responsive to the altitude of the ejection seat indicating a second mode of operation, determining, by the processor, whether the airspeed of the ejection seat is at or above a first threshold and below a second threshold; and responsive to the airspeed of the ejection seat being at or above the first threshold and below the second threshold: sending, by the processor, a command to deploy a drogue parachute; and, responsive to a first predetermined time period expiring, sending, by the processor, a command to deploy a main parachute and sever the drogue parachute based on a variable drogue severance delay.

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.

A method is disclosed herein. The method includes receiving, by a processor, an ejection command for ejecting an ejection seat from an aircraft; determining, by the processor, an equivalent airspeed and an equivalent altitude of the ejection seat; and, responsive to the airspeed and the altitude indicating a second mode of operation: sending, by the processor, a command to deploy a drogue parachute; determining, by the processor, a variable drogue severance delay; and responsive to the variable drogue severance delay expiring, sending, by the processor, a command to sever the drogue parachute and deploy a main parachute.

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 airplane mainly extending along an axis between a nose group and a tail group is provided. The airplane has a fuselage extending axially between the nose group and the tail group and having a fuselage wall internally defining a fuselage housing, wings extending transversely to the axis from the fuselage, and at least one passenger pod having a pod wall defining a pressurized passenger housing in which passengers are accommodable. The at least one passenger pod is removably housable in the fuselage housing. The airplane is configurable in an operating configuration, suitable for allowing flight of the airplane, in which the at least one passenger pod is housed in the fuselage housing and an emergency configuration, in which, with the airplane in flight, the at least one passenger pod is ejected from the fuselage housing.

An inflation valve arrangement includes an actuation cavity housing connected to a pneumatic valve, the actuation cavity housing comprising an actuation cavity and a piston rod extending from the actuation cavity at least partially into a main fluid channel of the pneumatic valve in an initially extended position for securing the pneumatic valve in a closed position. The arrangement further comprises a solenoid actuated pressure cartridge connected to the actuation cavity housing. The solenoid actuated pressure cartridge comprises a self-contained source of actuation gas. In response to the solenoid actuated pressure cartridge being energized, the solenoid operated pressure cartridge is configured to release the actuation gas from the pressure cavity into the actuation cavity, thereby retracting the piston rod into the actuation cavity, and opening the pneumatic valve body to release a source of inflation gas to an inflation device.

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.

Provided includes the main body part 100 in which a number of rotors 101 controlled by the control unit 110 are installed on the outside, a number of wing bodies 200 in which the elastic member 220 is opened to both sides to absorb the impact in the event of a collision with the guide 210 placed on the outer side of the rotor 101, a parachute deployment unit 300 installed on the upper side of the main body part 100 and ejecting the parachute canopy 320 upward in an emergency situation, a lower airbag ejection unit 400 installed under the main body part 100 and inflating the lower airbag 401 downward in an emergency situation, and a landing gear unit 500 installed under the main body part 100.

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 discloses an active separation device for a comprehensive helmet and an ejection seat during ejection lifesaving and a using method.The device comprises an anti-loosening connector, a lever clamping mechanism, an electric excitation type gunpowder gas mechanism and a socket fixing mechanism which are all fixed to the ejection seat, and a 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 electrical excitation type gunpowder gas mechanism, and the resistance end of the lever clamping mechanism corresponds to a spring self-locking mechanism on the anti-loosening 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, and when the plug is inserted into the socket, the resistance end of the lever clamping mechanism is pressed 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 success rate of ejection lifesaving in a complex lifesaving environment can be effectively increased.

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.

- AIRCRAFT SAFETY DEVICE - This aircraft safety device transforms the fuselage into an emergency module in the event of damage [Fig.42]. There are three parts, the fuselage, the wings, and the elevator, [Fig.26]. They can be separated from each other, each of its parts grouping sub-devices which ensure this transition. The first part of this assembly, (the fuselage) represents the emergency module. This one has a Sigma device [Fig.30] which is composed of two ailerons. They have the particularity of blending into the mass of the wings of the aircraft of part 2 [Fig.28][Fig.29]. This emergency module integrates an Alpha device, [Fig.7] of two stabilizers which have the role of relay elevator. In the fuselage, there is a Theta device [Fig.30] composed of four fans distributed judiciously on each side of it hidden inside a dedicated compartment; and whose main function is to slow the fall of this rescue module, if necessary, but we can attribute other possibilities to it. This rescue module includes an Iota device [Fig.38][Fig.40], hatches which serve as landing gear, to cushion the impact on the ground and guarantee a horizontal plane whatever the type of terrain encountered. The second part of this assembly serves as a reception base for the rescue module. As for the third part of this assembly (the elevator) [Fig.41] [Fig.53] it is a drone whose mission is to tow this rescue module or to participate in rescue searches. FIGURE FOR ABBREVIATION: [Fig.3].

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.