161results about "Emergency apparatus" patented technology

An assembly having a chassis, two supports with a plate and a guide, a nesting system with a bore, a reservoir containing an extinguishing fluid and with two fastening tabs, two bearing tabs and a peg, and a fastener. The reservoir is able to move in translation between a premounting position in which each fastening and bearing tab rests on a plate and each guide guides the fastening and bearing tabs to align the peg and the bore, and a mounting position in which each fastening tab rests on the plate, the peg is introduced into the bore, the bearing tabs no longer rest on the plates and the fastener fastens each fastening tab to the plate. Such an assembly allows the reservoir to be withdrawn and put in place quickly and easily.

The invention provides a landing and life-saving system adaptive to a non-fully-coated single aircraft. The landing and life-saving system comprises a helmet for wearing, a flying suit connected with the aircraft and used for wearing, and a plurality of mechanical feet mounted on the aircraft, the helmet comprises a shell and a non-trigger air cushion arranged in the shell, and a visual window is arranged on the front side of the shell; the flying suit comprises a vest, a back air bag installed on the back of the vest, a thoracico-abdominal air bag installed on the front portion of the vest and a gas generator connected with the air bags through pipelines, the gas generator is installed on the vest or the aircraft, and a trigger switch for inflating the air bags is arranged on the gas generator. The mechanical foot comprises a supporting rod, a rotating rod and a mounting block, the mounting block is connected to the aircraft, one end of the rotating rod is rotationally connected with the mounting block or the aircraft, one end of the supporting rod is rotationally connected with the other end of the rotating rod, and the other end of the supporting rod serves as a supporting foot. The system is used for assisting normal flight landing of a manned flight non-coated single aircraft, and realizes forced landing and lifesaving.

Disclosed is a crash handling system for an aircraft, comprising an altitude surveillance system adapted to receive altitude data from an altitude sensor and issue an altitude warning signal when a predetermined altitude condition is fulfilled, a crash detection unit, comprising an acceleration detector and issues a crash detection signal when a predetermined acceleration condition is fulfilled, a control unit operatively coupled to the altitude surveillance system and the crash detection unit to receive respective altitude warning signals and crash detection signals; and an energy storage system isolation means operatively coupled to the control unit to electrically isolate an energy storage system of the aircraft upon reception of an activation signal, wherein the control unit transitions from a disabled operation state to an enabled operation state when the altitude warning signal is received; and to issue the activation signal upon reception of the crash detection signal when in enabled state.

The invention discloses a flying backpack for a low-altitude single aircraft, and relates to the field of manned aircrafts. The problems that an existing jet-propelled aircraft garment is large in self weight, inconvenient in pose adjustment and prone to hurting pilots are solved. An oil supply system is installed in a shell, an electrical system is installed on the upper end face of the shell, and a backpack micro turbine engine is installed on the lower portion of the shell. The shell comprises a back plate and a flying back covering part, the back plate is a plate body, a plurality of lightening holes are formed in the upper portion of the back plate, the back plate is made of aluminum alloy, penetrating holes are formed in the periphery of the back plate, and the middle of the safety belt is fixedly installed in the middle of the back plate through bolts and olecranon hooks. A strap of the safety belt penetrates through the penetrating-connecting hole and then is connected with the body of the pilot, the flying back covering part is a shell cover and covers the back plate, and a filiform net is arranged on the lower portion of the flying back covering part. The invention is used in aircrafts.

A low-altitude single-person aircraft powered by a micro-turbojet engine relates to the field of manned aircraft. The invention solves the problems of existing jet aircraft suits, such as heavy weight, inconvenient posture adjustment, and easy injury to the pilot. The invention comprises a flight backpack and two arm propulsion devices (7); the flight backpack comprises: a safety belt (1), a shell (2), an oil supply system (3), an electrical system (4), and a backpack micro-turbine engine (5); the oil supply system (3) is installed inside the shell (2), the electrical system (4) is installed on the upper end surface of the shell (2), and the backpack micro-turbine engine (5) is installed on the lower part of the shell (2); wherein the two arm propulsion devices (7) are respectively installed on the left and right sides of the shell (2) of the flight backpack. The flight backpack of the invention is the most complex component of a low-altitude single-person aircraft powered by a micro-turbojet engine. The invention is used in aircraft.

A system includes a collecting unit for collecting a current oxygen pressure value of the oxygen bottles, an estimating unit for estimating an average degradation model, an adapting unit for adapting the average degradation model, a generating unit for generating several future degradation scenarios, an estimating unit for estimating, for each of the future degradation scenarios, a remaining useful lifetime, and for generating a remaining useful lifetimes probability distribution, a transmitting unit for transmitting an end-of-lifetime alert signal to an alert device if a remaining useful lifetime of an oxygen bottle is below a predetermined alert threshold.

An emergency system for an aircraft. The emergency system comprises an autopilot controller arranged in a cockpit of the aircraft and configured to automatically fly the aircraft including performing predefined maneuvers, and an emergency button arranged in a crew rest compartment outside of the cockpit and configured to send an emergency landing signal to the surveillance system and / or the autopilot controller when activated. Also an aircraft section and aircraft.

The invention provides a helicopter full-view cabin door, and belongs to the technical field of helicopter cabin doors, the helicopter full-view cabin door specifically comprises a door plate and a visual window, the visual window bulges towards the outside of a helicopter cabin, the visual window is composed of two transparent units, and the two transparent units are rotationally connected with the door plate; the limiting and fixing assembly is installed in the door plate in a sliding mode, and an adjusting block is fixed to the limiting and fixing assembly; the output end of the driving assembly is connected with the limiting and fixing assembly through a connecting rod, and the driving assembly is used for driving the limiting and fixing assembly to be close to the edge of the transparent unit to limit rotation of the transparent unit or driving the limiting and fixing assembly to be away from the transparent unit to release limitation on the transparent unit; and the forcible entry assembly is used for damaging the connecting rod, the adjusting block is used for being manually operated to drive the limiting and fixing assembly to be away from the transparent unit to release limitation on the transparent unit after the connecting rod is damaged, and through the treatment scheme of the application, the escape probability after the helicopter has a safety accident is improved.

To provide an unmanned flying body that can move the center of gravity of the airframe so as to take a posture suited to such as parachute injection in emergency circumstances.SOLUTION: An unmanned flying body includes: a body part; a lock mechanism for maintaining a state where a center-of-gravity control body is in a first position relative to the body part; and a movable guide for moving the center-of-gravity control body to a second position in accordance with release of a maintenance state by the lock mechanism.SELECTED DRAWING: Figure 3

The composite sheet includes a textile component having a first surface and a second surface, and a first polymer coating on the first surface of the textile component, the textile component further including: a first structure of at least one woven fabric of continuous filament yarns, the woven fabric having an areal weight of about 70 to about 508 gsm; a second structure of a nonwoven fabric comprising a blend of discontinuous fibers of oxidized polyacrylonitrile fibers and silica fibers, the oxidized polyacrylonitrile fibers being present in an amount of about 30 to about 70 weight percent of the combined weight of the oxidized polyacrylonitrile fibers and the silica fibers; and a third structure of at least one woven fabric of continuous filament yarns, the woven fabric having an areal weight of about 70 to about 508 gsm, wherein the nonwoven fabric of the second structure may be mechanically attached to at least one of the other textile structures by an attachment means.

The invention relates to an electrical arrangement (100) for protecting an electrical apparatus intended to be located between an electrical power source (101) and an electrical load (102), the arrangement comprising:-a power contactor (120) comprising two contacts (121, 122) intended to be connected to the electrical power source; -at least two Hall sensors (161, 162) configured to measure the current at the input of the power contactor; -a pre-charging circuit (150) intended to be located between the power source and the power contactor and connected to the electrical load; -a relay (140) configured to connect or disconnect the pre-charge circuit; -pyrotechnic breaking means (130) intended to be connected to the power source and to the power contactor; and-a controller (110) configured to receive measurements of the Hall sensor and to open or close the power contactor and the relay.

To provide a high practical drone.SOLUTION: A drone equipped with an airbag 22 deploying downward when falling, is provided with a vent hole 32 accepting an outflow of inside gas at grounding. The vent hole accepts the outflow of inside gas at grounding, so that the bounding of the drone due to a pressure rise in the airbag is prevented.SELECTED DRAWING: Figure 1

The present invention relates to an electrical aircraft propulsion arrangement comprising: at least one electrically operated prime mover for providing thrust for the aircraft; at least one source of electrical energy arranged to provide electrical energy to at least one electrically operated prime mover; a controller arranged to control production, storage and provision of electrical energy from the at least one source of electrical energy; a sensor arrangement arranged to provide data to the controller, the data relating to flight condition, aircraft condition, and electrical energy source condition.

An aircraft passenger service unit (2) for being installed in an overhead position in an aircraft passenger cabin (102) comprises at least two gaspers (29). Each of the at least two gaspers (29) is oriented towards a respective passenger seat (80a). The aircraft passenger service unit (2) further comprises an electric motor (204) configured to drive an impeller (203). The impeller (203) is located inside an airflow tube (205) that is in fluid communication with the at least two gaspers (29) via respective airflow outlets (206). The impeller (203) is arranged to provide an airflow to the at least two gaspers (29). In addition, the aircraft passenger service unit (2) comprises at least one valve (207) for controlling the airflow to the at least two gaspers (29).

The present application provides a fall damage reduction system, a flying device, and a vehicle-mounted device. The flying device includes a flight communication section (24), a device fall determination section (25, S101), and a flight notification section (25, S104, S105). The flight communication section performs wireless communication in accordance with a communication standard for inter-vehicle communication. The device fall determination section determines whether the flying device is likely to fall. In a case where the flying device is determined by the device fall determination section to be likely to fall, the flight notification section transmits fall information including information indicating a presumed fall position via the flight communication section. The vehicle-mounted device includes a vehicle communication section (34) and a processing section (37, S207, S208, S210, S211, S212, S214, S215, S218, S219). The vehicle communication section performs wireless communication in accordance with a communication standard for inter-vehicle communication. In a case where the fall information is received via the vehicle communication section, the processing section executes fall avoidance processing that is processing for avoiding the fall position.

The invention relates to a protection device for protecting a hydrogen tank and an aircraft. In one aspect, there is described a protection device for protecting a hydrogen tank (4, 5), in particular for an aircraft, the protection device (1) comprising: an outer enclosure defining an inner volume; the invention relates to an aircraft (2) comprising an outer enclosure (10) having an inner volume (12), and a fire extinguishing agent in said inner volume, preferably in the gas phase, provided with at least one pressure relief valve (14) for releasing at least one of said fire extinguishing agent when the pressure present in the inner volume is greater than a threshold value, and shaped for installation in a fuselage (3) of the aircraft (2).

The invention relates to a method and system for deflating an oxygen mask. The method for throwing the oxygen mask comprises the steps that the current flight scene S of an aircraft is determined, wherein the flight scene S comprises a ground station-crossing and take-off stage S1, a climbing or cruising stage S2 and a descending and landing stage S3; calculating a cabin height warning value ZCW based on the flight scene S and the cabin height value ZC; judging a jettisoning height threshold value ZD based on the cabin height alarm value ZCW; in any flight scenario, the cabin height value ZC is compared to the jettisoning height threshold ZD, and when the cabin height value ZC is greater than the jettisoning height threshold ZD, the oxygen mask is automatically jettisoned.

A fall damage reducing system includes a flying device and a vehicle-mounted device. The flying device: performs a wireless communication under a vehicle to vehicle communication standard; determines a falling possibility of the flying device; and transmits falling information indicating an estimated falling position of the flying device in response to the falling possibility being determined. The vehicle-mounted device: performs a wireless communication under the vehicle to vehicle communication standard; executes a vehicle control on a subject vehicle to avoid the estimated falling position in response to the falling information being received; and transmits traveling information indicating the vehicle control executed on the subject vehicle. In response to the traveling information from a different vehicle being received, the vehicle-mounted device executes a collision avoidance process to avoid a collision with the different vehicle.

An electrical device for protecting an electrical installation intended to be placed between a power supply and an electrical load, the device including: a power contactor comprising two contacts that are intended to be connected to the power supply; at least two Hall sensors configured to measure the electric currents at the input of the power contactor; an electrical precharging circuit intended to be placed between the power supply and the power contactor and connected to the electrical load; a relay configured to connect or disconnect the electrical precharging circuit; a pyrotechnic electrical cutoff device intended to be connected to the power supply and to the power contactor, and a controller configured to receive the measurements from the Hall sensors and to open or close the power contactor and the relay.

The invention relates to a protective device for a hydrogen tank (4, 5), particularly for an aircraft, the protective device (1) comprising an outer casing delimiting an internal volume, and an extinguishing agent, preferably in gaseous phase, within said internal volume, the outer casing being provided with at least one pressure relief valve (14) for releasing said at least one extinguishing agent when the pressure within the internal volume exceeds a threshold value, and the outer casing being shaped for installation in the fuselage (3) of an aircraft (2). Abstract figure: Figure 2

An embodiment aircraft includes a fuselage, a wing coupled to the fuselage, a fixing portion connecting a portion of the wing to the fuselage, and a controller disposed in the fuselage, wherein the controller is configured to transmit a severing signal to cause a portion of the fixing portion to be severed.

The present invention belongs to the technical field of airborne life-saving equipment, and discloses a fixing mechanism and a mounting bracket for a throw-type emergency positioning life-saving equipment, which are used to fix the throw-type emergency positioning life-saving equipment and the mounting bracket, and include: a pin sleeve, one end of the pin sleeve has a flange, a side mounting hole is opened on the mounting bracket, and the sleeve body of the pin sleeve passes through the side mounting hole; a top pin is arranged in the pin sleeve, a spring is axially arranged in the middle of the pin body of the top pin, and the pin head of the top pin extends out of the pin sleeve; the pin sleeve is fixed on the side wall of the mounting bracket through a fastening nut, and the top pin is fixedly connected with the pin sleeve through a limit nut. The present invention can eliminate the gap between the top pin and the throwing device, ensure that the throw-type emergency positioning life-saving equipment can be safely and reliably installed in the mounting bracket, and eliminate the accident hidden danger that the throwing device causes excessive torque on the unlocking bolt due to interference fit, resulting in the inability of the equipment to separate.

The composite sheet comprises a textile component having a first surface and a second surface, and a first polymer coating on the first surface of the textile component, wherein the textile component further comprises at least one woven fabric of continuous filament yarns having an areal weight of from about 70 to about 508 gsm, and a nonwoven fabric comprising a blend of discontinuous fibers of oxidized polyacrylonitrile fibers and silica fibers, wherein the oxidized polyacrylonitrile fibers are present in an amount of from about 30 to about 70 weight percent of the combined weight of the oxidized polyacrylonitrile fibers and the silica fibers, and the nonwoven fabric may be mechanically attached to the woven fabric.

A control system for an aircraft, the aircraft comprising: two or more propulsors; two or more electric motors, each electric motor configured to drive a corresponding propulsor; a primary energy system comprising a rechargeable battery arranged to power the two or more electric motors; and a reserve energy system comprising two or more combustion engines and two or more generators arranged to power the two or more electric motors. The control system is configured to initiate operation of the reserve energy system when a go-around procedure has been initiated only if a state of charge determined at the point of initiation of the go-around procedure is lower than an upper threshold SoC

An electrical aircraft propulsion system (fig.1,100) has sensors (fig.1,140) providing data relating to flight condition, aircraft condition, and electrical energy source condition to a controller (fig.1,130) controlling production, storage, and provision of electrical energy from an electrical energy source (fig.1,120) providing electricity to an electric prime mover (fig.1,110), such as a propulsor. The electrical energy source and prime mover may be partially cryogenically operated, and the controller may be an intelligent electrical system controller. Also claimed is a method of operating the aircraft where the controller operates according to calculations of the presence of safety events, and, in response to detecting a safety event, calculating either a likelihood of return to normal flight conditions; a requirement to jettison an electrical energy fuel source; a requirement of a deep discharge event of an electrical energy source; an aircraft failure state; and / or an energy need for a failure state of the aircraft. This may be analogous to actions taken for combustion propelled aircraft where fuel is dumped overboard to reduce weight and improve flying or gliding capability.

An aircraft passenger service unit for being installed in an overhead position in an aircraft passenger cabin comprises at least two gaspers. Each of the at least two gaspers is oriented towards a respective passenger seat. The aircraft passenger service unit further comprises an electric motor configured to drive an impeller. The impeller is located inside an airflow tube that is in fluid communication with the at least two gaspers via respective airflow outlets. The impeller is arranged to provide an airflow to the at least two gaspers. In addition, the aircraft passenger service unit comprises at least one valve for controlling the airflow to the at least two gaspers.

A method of guidance for an aircraft includes obtaining relative position data indicative of a direction from a location of the aircraft to a location of a moving target point. The method also includes determining, based on the relative position data, a location of a virtual leader based on projecting the location of the aircraft onto a virtual leader path, where the virtual leader path corresponds to a straight approach path to the location of the moving target point along a desired approach direction. The method further includes determining, based on the location of the virtual leader, a guidance input to cause the aircraft to follow the virtual leader.

To provide a system and method for issuing an alert regarding the engagement of an emergency exit door of an aircraft.SOLUTION: An aircraft (106) includes a system (100) including an emergency exit door (102) within an internal cabin (104). The emergency exit door (102) includes a lever (108) configured to be engaged to open the emergency exit door (102). A first cover (110) is removably secured to the emergency exit door (102). The first cover (110) is configured to be removed to gain access to the lever (108). A second cover (112) is disposed between the lever (108) and the first cover (110). The second cover (112) is configured to be removed to gain access to the lever (108). One or more sensors (114) are configured to detect positions of the first cover (110) and the second cover (112).SELECTED DRAWING: Figure 1

The invention relates to an electrical device (100) for protecting an electrical installation intended to be placed between a power supply (101) and an electrical load (102), the device comprising: - a power contactor (120) comprising two contacts (121, 122) that are intended to be connected to the power supply; - at least two Hall sensors (161, 162) configured to measure the electric currents at the input of the power contactor; - an electrical precharging circuit (150) intended to be placed between the power supply and the power contactor and connected to the electrical load; - a relay (140) configured to connect or disconnect the electrical precharging circuit; - a pyrotechnic electrical cutoff device (130) intended to be connected to the power supply and to the power contactor, and - a controller (110) configured to receive the measurements from the Hall sensors and to open or close the power contactor and the relay.

An aircraft passenger suite (100) is provided. The suite (100) comprises an aircraft seat (110) for use by a passenger. The suite (100) also comprises a controller for controlling a number of output states (240) of the suite, the controller comprising a logic condition receiver operable to receive a logic condition input (210). The suite (100) also comprises sensor equipment operable to provide a sensor input (220) to the controller, the sensor input (220) providing an indication of at least one attribute of a passenger of the suite (100). The sensor equipment comprises one or more of: an image sensor (151, 152) a pressure sensor (154) and a physiological sensor. The controller is configured to control at least one of the output states (240) of the suite based on both the logic condition input (210) and the sensor input (220).