18results about "Flying suits" patented technology

According to the pulsating anti-load pants and the simplified air bag heart assisting device, by adding the anti-load clothes and the pulsating and blood pumping functions of the anti-load pants, the standing anti-load pants during cruising are changed into pulsating pressurizing pants with time control air valve pulsating type inflation and deflation or left and right air bags alternately inflated and deflated; the thick and long blood vessels of the lower limbs and the one-way valves on the inner walls of the thick and long blood vessels of the lower limbs are extruded to pump blood to become a second external heart; a simplified air bag heart assisting device is a pulsating anti-load pants reduced configuration scheme, outer-layer clothes and pants of anti-load pants are removed, and the simplified air bag heart assisting device is simplified into a crus air bag or a thigh and crus communicated air bag sewed nylon fastener tape device, and left and right leg air bag air conveying rubber pipes are connected with two electromagnetic three-way valves respectively and then are combined through rubber pipes to be connected with an air pump. Two-way power-on and power-off of a time relay are used for controlling left and right electromagnetic valves or improved valves to be connected with air bags, an air pump and an external tee joint, so that left and right leg air bags are inflated and deflated in turn; the invention can be used as heart-aiding anti-load trousers and heart-aiding fitness equipment, and can improve the blood circulation of the human body.

A breathing gas supply system (10), potentially for combat aircraft, operative to decrease hypoxia and asynchronous breathing and to conserve breathing gases. An input valve (26) selectively permits breathing gas to fill a flexible gas reservoir (34) through a fluidic connector (28). Breathing gas can be maintained at an elevated pressure. The fluidic connector (28) delivers gas to an output interface (14), such as an oxygen mask (14). An inspiratory valve (30) is permitted to open when inspiration is sensed by an inspiratory sensor (32), and an expiratory valve (48) is permitted to open when expiration is sensed by an expiratory sensor (32). The inspiratory and expiratory sensors (32) can be separate or embodied as an inspiratory-expiratory sensor (32). A sensor reservoir (58) fluidically open to a volume between the output interface (14) and the face of the user can expand or compress to indicate inspiration or expiration. The inspiratory and expiratory valves (30, 48) can be electromagnetically operated.

Apparatus for supplying oxygen to a vehicle user, comprising a source of pressurized respiratory gas containing oxygen-enriched air, a flow-regulating and / or pressure-regulating unit, and at least one mask provided for supplying gas to the respiratory tract of said user, the regulating unit comprising at least one inlet connected to the source and at least one outlet connected to the mask, the regulating unit being configured to regulate the flow and / or the pressure of the respiratory gas supplied to the mask according to the respiratory demand of the user, the apparatus comprising at least one sensor measuring the pressure and / or the flow of respiratory gas delivered by the regulating unit to the mask, and an electronic data storage and processing unit configured to receive the measurements from the at least one sensor and to calculate, from these measurements, the frequency of the gas flows supplied to the mask and corresponding to the respiratory frequency of the user, to compare this calculated frequency against a threshold frequency and, when this calculated frequency is greater than the threshold frequency, to generate an audible and / or visual and / or vibratory warning signal.

The invention relates to the technical field of aviation, and provides a preparation method of impact-resistant aviation protective clothing with an aramid fiber honeycomb interlayer, which comprises the following steps: step 1, preparing an aramid fiber honeycomb core material, soaking aramid fiber paper in a polyimide resin solution with the mass concentration of 5-15%, taking out, and carrying out gradient curing molding at 120-180 DEG C to obtain the aramid fiber honeycomb core material; and 2, modifying the aramid honeycomb core material, immersing the aramid honeycomb core material prepared in the step 1 into a flame-retardant impact-resistant synergistic modification solution, carrying out ultrasonic-assisted immersion treatment for 2-4 hours, then carrying out microwave-assisted drying, and drying for 20-40 minutes under the condition that the microwave power is maintained at 300-500W. Through a synergistic enhancement mechanism of the aramid fiber honeycomb core material and the shear thickening gel, breakthrough improvement of the protection performance is achieved, the self-adaptive rigidity effect is formed by restraining holes and grids of the gel through the honeycomb structure, and the problem of light weight, namely weakening, is effectively solved.

A flightsuit (100) is disclosed having one or more suit sections (112, 114, 116, 118) that can be worn by a user. One or more constriction devices such as ropes (124) are wound around the one or more suit sections and one or more mechanical actuators (126) are configured to tighten the one or more ropes and thereby to apply pressure to body parts of the user within the one or more suit sections. A controller (120) is configured to receive a g-force measurement and to receive heartbeat information of the user. The controller (120) is further configured to control the one or more mechanical actuators, based on the g-force measurement and the heartbeat information, in order to apply pressure to body parts at respective positions of the suit. In an alternative configuration the constriction devices may be fluid bladders that can be filled with fluid to constrict the body parts.

An embodiment provides a protective suit system that is configured for protecting an occupant in extreme environments. The system may comprise a base layer to be worn on the occupant that is configured for thermal regulation of the occupant, the base layer including a biomarker sensor network for monitoring one or more biomarkers of the occupant. The system may also comprise an outer layer to be worn over the base layer, the outer layer including an exoskeleton structure sized so that the occupant can fit within the exoskeleton structure, and an exoskeleton covering that covers and is secured to the exoskeleton structure. The system may also comprise a data storage system that can store data generated by the biomarker sensor network.

A piezoelectric actuator controlled smart flow regulator (300) is provided. The piezoelectric actuator controlled smart flow regulator includes an inlet chamber (302) and an actuator chamber (304). The inlet chamber includes an inlet port (310). The actuator chamber includes an exit port (312), a sealing disc (316, 416), and at least one piezoelectric actuator (318). The at least one piezoelectric actuator is coupled to the sealing disc. In a deactivated state, the sealing disc is in contact with the inlet port such that oxygen is prevented from flowing through the actuator chamber. In an activated state, responsive to receiving a voltage, the at least one piezoelectric actuator is configured to restrict thereby translating a center of the sealing disc away from the inlet port and provide an oxygen flow through the inlet port to the exit port.

A breathing gas supply system, potentially for combat aircraft, operative to decrease hypoxia and asynchronous breathing and to conserve breathing gases. An input valve selectively permits breathing gas to fill a flexible gas reservoir through a fluidic connector. Breathing gas can be maintained at an elevated pressure. The fluidic connector delivers gas to an output interface, such as an oxygen mask. An inspiratory valve is permitted to open when inspiration is sensed by an inspiratory sensor, and an expiratory valve is permitted to open when expiration is sensed by an expiratory sensor. The inspiratory and expiratory sensors can be separate or embodied as an inspiratory-expiratory sensor. A sensor reservoir fluidically open to a volume between the output interface and the face of the user can expand or compress to indicate inspiration or expiration. The inspiratory and expiratory valves can be electromagnetically operated.

A non-full-cover manned aircraft landing emergency method, comprising: when the control system receives an emergency signal, it jumps out of the auxiliary landing process, triggers the emergency process, and records the current trigger time t0 and the current flight height H0; the control system makes a height determination in each communication period, and according to the flight environment in which the aircraft is currently located: when in low-altitude or ultra-low-altitude flight condition, if the flight height is determined to be higher than the second preset threshold Ht, the parachute pack determination guide process is executed, otherwise the control system triggers the opening of the airbags of the wearable airbag vest and guides the expansion of the support mechanical foot assembly; when in the flight condition dominated by the parachute, if the flight height is determined to be higher than the preset parachute opening height H1, the height determination of the next period is made, otherwise the parachute pack is guided to open, and the airbag and mechanical foot guide process is entered. The method can realize safe landing and emergency landing in low-altitude or ultra-low-altitude flight, and is compatible with landing guided by the parachute.

The present invention relates to a training system for training of a forward controller. The training system utilises a pod housing that can be attached to a hardpoint under an 5 aircraft wing. The pod is configured to receive communications from the forward controller on the ground (or in another aircraft) and communicate wirelessly with an HMD and / or electronic device in the cockpit of the aircraft. This allows cheaper, less expensive aircraft to be used for training purposes.

The invention relates to a cockpit control system comprising a computing unit (3), a virtualization unit (5), and two exoskeleton arms (7) with position measurement, wherein the computing unit (3) controls the virtualization unit (5) to display virtual cockpit controls such that the current position of a virtual control stick correlates with the position of one exoskeleton arm (7) and the current position of a virtual throttle lever correlates with the position of the other exoskeleton arm (7), and transmits information about this as command signals to a flight computer.

A system may include a first connector side configured to engage with a second connector side, the first connector side comprising: an inner plug ring comprising a first set of first connector elements configured to engage a first set of second connector elements of the second connector side; and an outer plug ring comprising a set of contacts, wherein the set of contacts is configured to close a safety circuit with at least one of the first device or the second device when the first set of first connector elements engage the first set of second connector elements, whereupon disengaging the first connector side from the second connector side, the safety circuit is opened by a movement of at least one contact of the set of contacts before the first set of first connector elements disengage the first set of second connector elements.

A device for regulating breathing gas delivered to a user, comprising a gas circuit comprising a main line (2) having at least an upstream end intended to be connected to at least one gas source (6, 5) and a downstream end intended to be connected to at least one user station (7) such as a mask (7), the main line (2) comprising at least one electromechanical control valve (3) configured to regulate the gas pressure between the upstream and the downstream, the circuit comprising a secondary line (8) comprising an upstream end intended to be connected to at least one gas source (6, 5) and a downstream end intended to be connected to the same user station(s) (7), the secondary line (8) comprising at least one auxiliary member (10) for regulating the gas flow, the device comprising a switching system (11, 4) configured to control the flow of gas between the upstream and the downstream of the circuit via the main line (2) or via the secondary line (8), characterised in that the auxiliary member (10) for regulating the secondary line (8) is a pneumatic pressure regulator.

The application provides a landing and lifesaving system for a non-fully covered single-person aircraft, which comprises a helmet for wearing, a flight suit connected with the aircraft and used for wearing, and a plurality of mechanical feet installed on the aircraft; the helmet comprises a shell and a non-triggered air cushion arranged in the shell, and a visual window is arranged on the front side of the shell; the flight suit comprises a vest, a back air bag installed on the back of the vest, a chest and abdomen air bag installed on the front of the vest, and a gas generator connected with each air bag through a pipeline, the gas generator is installed on the vest or the aircraft, and a trigger switch for inflating each air bag is arranged on the gas generator; the mechanical foot comprises a support rod, a rotating rod and a mounting block, the mounting block is connected with the aircraft, one end of the rotating rod is rotationally connected with the mounting block or the aircraft, one end of the support rod is rotationally connected with the other end of the rotating rod, and the other end of the support rod is used as a support foot. The system is used for assisting normal flight landing of the non-fully covered single-person aircraft for manned flight, and realizes forced landing and lifesaving.

The present invention relates to a training system for training of a forward controller. The training system utilises a pod housing that can be attached to a hardpoint under an aircraft wing. The pod is configured to receive communications from the forward controller on the ground (or in another aircraft) and communicate wirelessly with an HMD and / or electronic device in the cockpit of the aircraft. This allows cheaper, less expensive aircraft to be used for training purposes.

The present invention relates to a training system for training of a forward controller. The training system utilises a pod housing that can be attached to a hardpoint under an 5 aircraft wing. The pod is configured to receive communications from the forward controller on the ground (or in another aircraft) and communicate wirelessly with an HMD and / or electronic device in the cockpit of the aircraft. This allows cheaper, less expensive aircraft to be used for training purposes.