Abstract: Methods, systems and apparatus for the deploying of buoyancy and impact reduction measures during operation of a UAV in the event of a failure, malfunction or collision. One or more airbags or bladders may be inflated to reduce the force transferred to the UAV as a result of a crash or collision. The bladders may both be used in the impact reduction as well as being used as a floatation device in the event a water landing/crash. The airbags may be configured to keep the UAV afloat so as to allow for the recovery of the UAV.

Abstract: Apparatus and associated methodology contemplating an emergency flotation system for floating a flying machine on a body of water. The system includes a water sensor mounted to the flying machine. An inflation device is configured to produce an appropriate amount of pressurized gas in response to the water sensor detecting a presence of water. An inflatable flotation device is in fluid communication with the inflation device, to receive the pressurized gas and thereby become inflated. The flotation device is configured, when inflated, to impart a buoyant force to the flying machine in the water.

Abstract: A small flying vehicle flown by radio control or autonomously by an auto pilot is equipped with an airbag device. The small flying vehicle has a main body part including a controller and a battery, a frame, a propeller, a motor, and a transmitting and receiving antenna. The airbag device has a gas supplier, a sensor, a controller, and an airbag. The airbag device is attached to the main body part, and the gas supplier is provided with a gas cylinder that releases a compressed gas when a closure member sealing the gas cylinder is broken, a breaker, including an electric igniter, that breaks the closure member, and introduction device that introduces the gas discharged from the gas cylinder and providing the pressurized gas into the airbag to inflate the airbag.

Abstract: A landing inflation system may include a compressed gas source, an airbag assembly fluidly coupled to the compressed gas source and configured to receive compressed gas, and a command processor configured to: (1) generate an inflation initiation command signal in response to an initiation signal, (2) generate an inflation cessation command signal in response to a nominal fill pressure signal, and (3) generate a vent command signal in response to an impact pressure signal.

Abstract: A buoyancy method for deploying a plurality of floats of a buoyancy system of an aircraft. The plurality of floats comprises a plurality of main floats and a plurality of secondary floats that are folded in flight. The method comprises a step of deploying the main floats in flight prior to ditching, and a step of deploying the secondary floats after ditching.

Abstract: A multicopter with boom mounted rotors is disclosed. In various embodiments, a multicopter includes multiple rotors, each mounted substantially horizontally on a distal end of a boom. The multicopter further includes a plurality of boom extensions, each boom extension being associated with a corresponding boom and each boom extension being configured to extend an associated distal end of said corresponding boom by an amount determined based at least in part on a swept area associated with a rotor mounted at or near said associated distal end. The multicopter includes a material, such as netting, secured to the aircraft and of a size sufficient to reach a far end of one or more of said boom extensions.

Abstract: The purpose of this invention, which is referred to as a vacuustat, is to generate buoyancy in the atmosphere by means of an evacuated or partially evacuated container, rather than by using a lighter-than-air lifting gas such as hydrogen or helium. This particular vacuustat design comprises a flexible airtight membrane supported by a fractal tensegrity internal structure consisting of a relatively small mass of compressive members forced into higher-order buckling modes through use of tension members. The advantages of such a design over conventional aerostats include superior buoyancy control for ascent and descent, greatly increased flight endurance, and cost-effectiveness in operation. This particular vacuustat design has a much greater lifting efficiency than previous designs, and should also be easier and more cost-effective to manufacture.

Abstract: A landing inflation system may include a compressed gas source, an airbag assembly fluidly coupled to the compressed gas source and configured to receive compressed gas, and a command processor configured to: (1) generate an inflation initiation command signal in response to an initiation signal, (2) generate an inflation cessation command signal in response to a nominal fill pressure signal, and (3) generate a vent command signal in response to an impact pressure signal.

Abstract: An aircraft including a wing, the end of the wing having a wing tip device, wherein the wing tip device includes a moveable region that is rotatable, about an axis of rotation extending out of the plane of the wing tip device, between: (i) a high-altitude cruise configuration in which the moveable region extends downwardly below the wing; and (ii) a ground-operating configuration in which the moveable region extends rearwardly behind the wing such that the ground clearance of the wing tip device is increased.

Abstract: A device for absorbing impacts of a parachutist or airdropped package upon landing, which can equip a harness, and/or a skydiver or dropping pallet for performing the aircraft jump without any risk of interferences, allows, during the aircraft exit and free fall, to hold, neutralized in a reduced volume, an air-inflatable airbag, for deployment during the canopy descent. It includes a container back pad hooked to the harness and/or to the user or to the dropping pallet, which can be made removable by straps and bridles, in which an airbag is arranged such that its air scoop is closed by flaps locked by a cutaway cable. When the user exerts an action on the opening handle or when the parachute opens, the cable separates the flaps, allowing to unballast the airbag and open the air scoop to the air flow from the movement of the harness during the descent.

Abstract: A buoyancy system for an aircraft, the buoyancy system being provided with at least two floats, said buoyancy system including a connection device for each float, each connection device attaching each float to a structure of an aircraft. Each connection device includes at least one stretchable connection and at least one non-stretch connection that are fastened to the float and that are suitable for being fastened to said structure, each non-stretch connection being folded while the float is against the fuselage so as to enable it to be lengthened, each non-stretch connection limiting the amplitude of the movement of the float under the effect of buoyancy thrust, and each stretchable connection exerting a return force on the float.

Abstract: A crash attenuation system has an airbag inflatable generally adjacent to an exterior of the aircraft. The system includes a gas generator in fluid communication with an interior of the airbag. The system also includes a vent system having a vent passage supported by the aircraft, the vent passage being configured to allow gas to escape from within the airbag during an impact to a second set of airbags for flotation. The vent system also includes an actuator door for sealing the vent passage, thereby preventing gas from leaving the airbag. The actuator door is actuated by an actuator, the actuator being in fluid communication with the gas generator through an actuator duct. The system operates such that deployment of gas from the gas generator causes the actuator to inflate, thereby causing the actuator door to seal the vent passage. The gas generator is configured to re-inflate the airbag after the actuator door seals the vent passage.

Abstract: Actuator for gas-operated emergency opening of an openable element of an aircraft, having the ability to vent the gas. The actuator for emergency opening of an openable element of an aircraft includes a thrustor, a pressurised-gas reservoir where the gas reservoir having a membrane capable of being perforated in order to actuate said thrustor, a movable perforator arranged to perforate said membrane of said reservoir in order to release the gas into the thrustor via a first fluid circuit, and a venting circuit that vents, away from the thrustor, the gas contained in the reservoir, in the event of accidental rupture of said membrane, via a second fluid circuit which does not actuate said thrustor.

Abstract: An aircraft fuselage has an integrated energy-absorbing deformation structure. The fuselage includes annular frames, longitudinal fuselage beams interconnecting the annular frames, and a covering forming a fuselage skin. A lower floor structure is disposed in an interior of the fuselage. The lower floor structure includes a plurality of transverse beams connected to an assigned frame and longitudinal floor beams which interconnect said transverse beams. The deformation structure is formed in a lower fuselage region disposed below the lower floor structure. The deformation structure includes a first inelastically deformable central region and, on a left-hand side and a right-hand side, respective second inelastically deformable regions of greater stiffness in the vertical direction than the central region.

Abstract: A buoyancy system (2) includes at least one float (3), a deployment assembly (30) having at least one deployment member (34) for deploying the float (3), an engagement controller (5) which activates the deployment assembly (30), and at least two immersion sensors (20) for issuing an order for automatic deployment of the float (3) to the deployment assembly (30). The deployment assembly (30) is provided with a memory (31) containing a pre-established list of events. The deployment assembly (30) deploys each float (3) when a predetermined event occurs.

Abstract: An impact protection apparatus is provided, comprising a gas container configured to hold a compressed gas and an inflatable member configured to be inflated by the gas and function as an airbag of a movable object, such as an aerial vehicle. A valve controls flow of gas from the container to the inflatable member in response to a signal from a valve controller. The valve and valve controller are powered by an independent power source than one or more other systems of the movable object. A safety mechanism may also be provided that, unless deactivated, prevents inflation of the inflatable member.

Abstract: The present invention relates to an aircraft (1) provided with at least one rotary element (10) provided with blades (11) liable to come into contact with a liquid surface (100) on ditching, said aircraft including a buoyancy system. The aircraft includes a fairing (15) surrounding at least part of said rotary element (10), the fairing (15) including an inflatable emergency float (20) of the buoyancy system for preventing said blades (11) from coming into contact with the liquid surface when in an inflated position.

Abstract: A method of automatically triggering an emergency buoyancy system (10) for a hybrid helicopter (20) having a fuselage (21), two half-wings (23, 23?), and two propulsive propellers (24, 24?). During the method, said emergency buoyancy system (10) is primed, and then if a risk of said hybrid helicopter (20) ditching is detected, two retractable wing undercarriages (28, 28?) are deployed, each wing undercarriage (28, 28?) being fastened under a respective half-wing (23, 23?) and being provided with at least one immersion sensor (16). Finally, if the beginning of said hybrid helicopter (20) ditching is detected, at least one main inflatable bag (11, 11?) 7B suitable for being arranged under such fuselage (21) and at least one secondary inflatable bag (12, 12?) suitable for being arranged under each half-wing (23, 23?) are inflated so as to ensure that said hybrid helicopter (20) floats in stable manner.

Abstract: An apparatus comprising a float bag comprising an air bladder configured to inflate when an aircraft lands in the water, a girt coupled to the air bladder and configured to attach the air bladder to the aircraft via at least one airframe fitting, and a load attenuator coupled to the girt and configured to be positioned between the girt and the airframe fitting when the float bag is attached to the aircraft.

Abstract: A buoyancy system (10) for an aircraft (1), said buoyancy system (10) comprises an inflatable float (15) and a cover (20). Said buoyancy system (10) includes at least one extensible connection means (25) fastened to the cover (20) to connect the cover (20) to a compartment (3) of an aircraft (1), while enabling the cover (20) to be retained and to be moved transversely during inflation of the float (15).

Abstract: The present invention provides an aircraft buoyancy system (14) for providing positive buoyancy to an aircraft (15) to keep it afloat at the surface of a body of water (16) after crashing, ditching or landing into a body of water (16). The aircraft buoyancy system (14) comprises at least one inflatable body (1) which, when inflated, increases the buoyancy of the aircraft (14), and a gas generation system (4) to inflate the at least one inflatable body (1). The aircraft buoyancy system (14) also comprises a sensor and activation system (3) to activate the gas generation system (4). Upon activation of the sensor and activation system (3) the gas generation system (4) causes a gas to flow to the at least one inflatable body (1), causing the aircraft (15) to float and remain at the surface of a body of water (16).

Abstract: A crash attenuation system for an aircraft includes an airbag carried by the aircraft that is inflatable generally adjacent an exterior of the aircraft. The airbag is in fluid communication with at least one vent passage for channeling gas from within the interior of the airbag to a region external to the airbag that allows the gas to escape without being obstructed by the airbag. A gas source is in fluid communication with the interior of the airbag for inflating the airbag. A vent valve is provided within the vent passage for controlling a flow of gas through the vent passage, thereby controlling deflation of the airbag. The vent valve is continuously adjustable to and between an open state, a closed state, and any number of partially open states.

Abstract: The present invention relates to an aircraft (1) provided with at least one rotary element (10) provided with blades (11) liable to come into contact with a liquid surface (100) on ditching, said aircraft including a buoyancy system. The aircraft includes a fairing (15) surrounding at least part of said rotary element (10), the fairing (15) including an inflatable emergency float (20) of the buoyancy system for preventing said blades (11) from coming into contact with the liquid surface when in an inflated position.

Abstract: A crash attenuation system for an aircraft, the system having an airbag carried by the aircraft and inflatable generally adjacent an exterior of the aircraft. The airbag has at least one vent for releasing gas from the interior of the airbag. A first gas source is in fluid communication with the interior of the airbag for inflating the airbag with gas generated provided by the first gas source. A vent valve is provided for controlling a flow of gas through each vent, each vent valve being selectively configurable between an open state, in which gas can pass through the associated vent from the interior of the airbag, and a closed state, in which gas is retained within the interior of the airbag. A second gas source is provided for at least partially re-inflating the airbag after venting of gas through the at least one vent.

Abstract: An emergency flotation device for an aircraft comprising a housing (9) containing an inflatable balloon (1) and a solid propellant cool gas generator (4) arranged to inflate the balloon when the aircraft ditches into water. The device is arranged so as to be optionally removable from the aircraft.

Abstract: An emergency floatation system for attachment to a helicopter that includes a support frame, a float pack assembly and an inflation system. The float pack assembly includes a float in a packed configuration, a sleeve integrated into the float and a rigid support that at least partially extends through the sleeve. The float pack assembly is configured so that it may be installed and/or removed from the support frame separate from the inflation system.

Abstract: Actuators, principally for inflating emergency-usage objects such as floats and rafts, are detailed. Two opposite positive actions may be required to effect complete inflation of the objects, inhibiting inadvertent deployment of, particularly, the rafts while readily permitting deployment when intended.

Abstract: A door pod assembly includes a housing that defines a cavity for emergency equipment, a pod door, and a latch retaining the pod door in a closed position relative to the housing. The assembly is configured such that the latches, upon activation free the release door thereby exposing the emergency equipment and allowing it to be deployed. The door pod assembly maybe coupled to an interior surface of a baggage compartment door and is configured so that the baggage compartment may continue to be used for its originally intended purpose.

Abstract: An emergency floatation system for attachment to a helicopter that includes a support frame, a float pack assembly and an inflation system. The float pack assembly includes a float in a packed configuration, a sleeve integrated into the float and a rigid support that at least partially extends through the sleeve. The float pack assembly is configured so that it may be installed and/or removed from the support frame separate from the inflation system.

Abstract: A floatation system for attachment to a helicopter landing skid includes a girt dimensioned to be attached to a landing skid and a plurality of floats attached to the elongate girt, wherein the plurality of floats are adapted to be converted from a packed configuration to an deployed configuration, and wherein at least one of the plurality of floats extends beneath the elongate girt when the plurality of floats is in the deployed configuration.

Abstract: An emergency floatation system associated with a landing gear of a rotorcraft comprising at least a float unit and a raft module. The float unit is formed by a base and a float cover with an inflatable float being positioned therebetween. The raft module is formed with a raft compartment adapted to receive an inflatable raft in the packed condition thereof. The raft module is supported on the float by the base. The raft is adapted for inflation and deployment from the raft module independently of the float deployment.

Abstract: An emergency floatation system for a helicopter includes a safety trigger device for inflating at least one raft during the course of an emergency. The safety trigger device includes a plurality of handles such that pulling any one of the plurality of handles triggers the inflation of the at least one raft.

Abstract: A flotation device for maintaining an aircraft in a floating and stable condition is provided. The flotation device comprises at least one flotation bladder mounted to the aircraft and an inflation mechanism for inflating the flotation bladder. A method for maintaining an aircraft in a floating condition is also provided.

Abstract: A floatation system for attachment to a helicopter landing skid includes a girt dimensioned to be attached to a landing skid and a plurality of floats attached to the elongate girt, wherein the plurality of floats are adapted to be converted from a packed configuration to an deployed configuration, and wherein at least one of the plurality of floats extends beneath the elongate girt when the plurality of floats is in the deployed configuration.

Abstract: A floatation system for attachment to a helicopter landing skid includes a girt dimensioned to be attached to a landing skid and a plurality of floats attached to the elongate girt, wherein the plurality of floats are adapted to be converted from a packed configuration to an deployed configuration, and wherein at least one of the plurality of floats extends beneath the elongate girt when the plurality of floats is in the deployed configuration.

Abstract: An emergency floatation system includes at least one inflatable float and an inflatable emergency life raft contained within a single cover, wherein the system is adapted to be converted from a packed configuration to a partially deployed configuration by use of a first actuating member, and wherein the system is adapted to be converted from the partially deployed configuration into a fully deployed configuration by use of a second actuating member.

Abstract: A safety system is provided on a helicopter by mounting a parachute within a cylinder located in a hollow drive shaft of the propeller or in an external container. Four auxiliary parachutes are located in front and behind, and to the left and right of the propeller. The propeller may be locked in a predetermined angular position by a braking system of the drive shaft when the helicopter is disabled in an air accident such that the auxiliary parachutes are located in the spaces between the propeller blades for their safe deployment for suspending the helicopter in air. Speed reducing jets are provided for reducing the falling speed of the helicopter and for landing it safely on the ground. Inflatable bags are provided for maintaining the helicopter afloat when it falls on to a body of water or to cushion its landing impact on the ground.

Abstract: Inflation of impact absorbing bags is effected on a portable platform positioned on an emergency landing zone after jettisoning of damaged landing gear from a helicopter fuselage. The impact absorbing bags when inflated form a cradle shape conforming to the bottom of the helicopter fuselage.

Abstract: A process for preventing overturning during the landing of an aircraft or spacecraft using an air bag type landing impact-damping system, which is inflated with gas before the landing and from which gas is discharged via discharge valves during the landing. The process includes using as the air bag type landing impact-damping system a system that is divided into a plurality of chambers that can be inflated with gas and from which gas is released independently from one another, and that a pressure difference is generated during landing in the individual chambers of the air bag type landing impact-damping system.

Abstract: An aircraft landing assist system comprised of a preformed and prepacked parawing-bag and fuselage housing and deployment is described. In case of emergency the system can be deployed automatically, manually, or by means of explosive charge. After deployment the open doors and the self inflated parawing-bag catch the on rushing air forcing the nose of the aircraft up. This helps increase the glide ratio and decrease the velocity of the aircraft. Control of the aircraft remains through the use of the upper wing surfaces and tail assembly. Upon landing the system helps extend the time of, and surface area of impact. Drains are provided in the aft section of the parawing-bag(s) to release rain or snow.

Abstract: A landing shock absorber for aircraft including brake parachutes and comprising a landing cushion for creating damping upon impact of the aircraft, the landing cushion having an inflatable inner bag including a pressure-tight, plastically deformable sheet. The inner bag defines a plurality of inflatable air chambers, and at least one opening between the chambers for establishing communication between the chambers. The landing cushion further includes an outer bag enclosing the inner bag and having a greater internal volume that an internal volume of the inflatable air chambers of the inner bag when the chambers are inflated, the outer bag including a tear-resistant fabric defining a plurality of throttle openings therein.

Abstract: A combined flying machine comprises a fuselage (1) in the form of a central hick wing with a vertical open tunnel (2), in which there is mounted a lifting rotor (4). Said machine is also provided with outboard wings and a tail unit (8). The machine is equipped with a landing device on an air cushion (19) that surrounds an outlet from the tunnel. A power plant of said flying machine comprises two engine modules (13), disposed from two sides of the tunnel (2) and connected with the lifting rotor (4) and the propulsion propellers (12). The area of the tunnel cross-section in the plane of the lifting rotor rotation amounts to 0.3 to 0.8 of the area of the landing device air cushion, which ensures a safe landing of the flying machine on an unprepared landing site even with a failure of one of the engine modules.

Abstract: An air-chute safety system (10) for an aircraft (12) having a fuselage (14) with a cockpit (16) and a tail end (18), and a pair of wings (20) with engines (22). The system (10) comprises a plurality of drag parachutes (24) stored in and deployed from the tail end (18) of the fuselage (14), in conjunction with an aerodynamic braking apparatus in the aircraft (12), which will shut down the engines (22) during an emergency when in flight, so that the aircraft (12) will slow down. A plurality of top parachutes (26) are provided. A structure (28) is for storing each of the top parachutes (26) in vertical spaced apart relationships below a top surface (30) of the fuselage (14) between the cockpit (16) and tail end (18) thereof.

Abstract: An aircraft which is capable of safely landing during an emergency landing is disclosed. The aircraft has a safety device which includes a plurality of auxiliary engines. Each auxiliary engine is movable so as to vary the thrust axis in a range between a substantially horizontal direction and a substantially vertical direction. The safety device also includes a plurality of gas bags contracted and disposed at a lower portion of the aircraft body so as to be instantly expandable at a necessary time, such as during an emergency landing.

Abstract: An energy absorbing structural unit is attached outside the fuselage belly of an aircraft having at least two decks arranged one over another. At least the lower deck, of which the floor is adjacent to the fuselage belly, includes passenger cabin compartments and/or service facilities. The energy absorbing structure is an energy absorbing structural unit (5) that is attached outside of the existing aircraft fuselage (2) approximately vertically below the passenger cabin compartment (9) and/or service facilities provided on the lower deck of the aircraft. The energy absorbing structural unit absorbs impact energy arising in a crash or emergency landing of the aircraft. Because impact energy is absorbed by the external structural unit rather than or in addition to the structure of the aircraft fuselage and air frame, it is possible to provide lower deck passenger cabin space that may be continuously occupied by passengers and crew even during the take-off and landing phases of a flight.

Abstract: An aircraft includes a cockpit permanently connected to a fuselage base. At least one fuselage segment is detachably mounted to the support. In case of an imminent crash the segment is detachable from the remainder of the aircraft and can float to safety after being detached by having at least one parachute and an airbag secured to the segment.

Abstract: A device for protecting a helicopter and its occupants from damage during a crash or difficult landing. The device includes an inflatable bag attached to the bottom fuselage which covers a totality of the surface of the helicopter's bottom fuselage. The bag is inflatable into a trapezoidal shape having a very large volume, exceeding the helicopter's internal volume, for substantially cushioning the helicopter upon impact with the ground during a crash. The bag is equipped with distortion-control reinforcements for preventing toppling of the helicopter after a landing and bag air-pressure controlling and limiting devices.

Abstract: An arrangement which permits installation of an inflatable aircraft evacuation slide in an enclosure disposed in a non-pressurized cavity beneath an aircraft exit. The enclosure is opened when activated by the gas used to inflate the slide and the arrangement provides a more rigid and positive attachment of the inflated slide to the aircraft than has heretofore been the case.

Abstract: Auxiliary landing equipment for aircraft which comprises a plurality of inflatable cushions arranged in a predetermined array relative to each other and structure for securing them to the aircraft so that, in an inflated state, the cushions can contact the ground during landing or on take-off and so that, in a deflated state, the equipment can closely follow the contour of the aircraft part to which it is attached.

Abstract: The cylindrical shape tube consists of a pressure valve and a safety valve. Whether the tube's contents be made of metal, expandable or non-stretchable materials, it has the ability to retain low air pressure. For safety purposes, any excess air pressure is released through the safety valve when the belts are made of metal content, the lengthwise belts have flares and grooves, the crosswise belts have oblong holes. When the belts are made of expandable or non-stretchable materials, snap head and grooves are cast within the lengthwise belts, the crosswise belts have round holes. The metal crosswise belts with their oblong holes can be engaged onto both the snap heads of the expandable lengthwise belts and flares of metal lengthwise belts. The expandable crosswise belts with their round holes can be snapped onto the snap heads of the expandable lengthwise belts and flares of the metal lengthwise belts.