369results about "Floats" patented technology

An airbag configuration for braking the landing impact of flying payloads has a central airbag (17) and at least one torus ring (11, 12, 13) surrounding the central airbag. A payload (L) is attachable on the central airbag (17). A stabilizing device (19) is provided which extends from the lowermost portion of the at least one torus ring (11, 12, 13) to the central airbag (17). The central airbag provides primarily vertical braking of the landing impact while the torus ring provides primarily horizontal braking of the landing impact.

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.

Airframes configured for stable in-flight transition between forward flight and vertical takeoff and landing are described herein. In one embodiment, an aircraft can include a fuselage, opposed wings extending from opposed sides of the fuselage, and a plurality of engines. At least one engine can be mounted to each of the opposed wings and at least a portion of each opposed wing including at least one of the plurality of engines can rotate relative to the fuselage around a rotation axis that is non-perpendicular and transverse to a longitudinal axis of the fuselage. Rotating portions of the wings including at least one of the plurality of engines in the described manner can provide a stable and smooth transition between vertical and forward flight.

There is provided an Unmanned Air Vehicle (UAV) including an engine and an airframe, including means for performing a deep stall maneouvre; at least one inflatable sleeve connected or connectable to the airframe, and means for inflating the sleeve during flight, wherein the inflated sleeve extends along the lower side of the airframe so as to protect same during deep stall landing. A method for operating an Unmanned Air Vehicle (UAV), including an engine and an airframe is also provided.

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.

A robust amphibious air vehicle incorporates a fuselage with buoyant stabilizers and wings extending from the fuselage. At least one lift fan is mounted in the fuselage. Movable propulsion units carried by the wings are rotatable through a range of angles adapted for vertical and horizontal flight operations.

There is provided an Unmanned Air Vehicle (UAV) including an engine and an airframe, including means for performing a deep stall maneuver at least one inflatable sleeve connected or connectable to the airframe, and means for inflating the sleeve during flight, wherein the inflated sleeve extends along the lower side of the airframe so as to protect same during deep stall landing. A method for operating an Unmanned Air Vehicle (UAV), including an engine and an airframe is also provided.

A hybrid air vehicle having a gas-filled contoured flattened hull including a pair of longitudinally extending side lobes defining, on the underside of the hull, a longitudinally extending central recess, a payload module received in the central recess and air cushion landing gear units on the underside of the side lobes of the hull. The landing gear units are spaced apart on either side of the payload module. The hybrid air vehicle has characteristics of an airplane, a lighter-than-air airship and a hovercraft.

A thrust reverser system actuator assembly is provided that includes a torque limiter to limit the number of torque that may be applied to the actuator assembly. The actuator assembly includes an actuator and a torque limiter assembly. The actuator is adapted to receive a drive force and is configured, in response to receipt of the drive force, to move between a stowed position and a deployed position. The torque limiter assembly is coupled to an end of the actuator and is configured to limit torque applied to the actuator assembly upon a torque magnitude being reached in at least the actuator.

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.

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.

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.

An emergency flotation device for crashed small airplanes which can be retrofited on most small airplanes as well as come preinstalled on new small airplanes, is self contained in a small container; has several independent triggering means; and has a visual as well as an RF beacon system integrated within to call for rescue.

A system for deploying an airbag when an unmanned aerial vehicle (UAV) has failed or is no longer able to sustain flight, comprising a triggering means which releases compressed air into a bag or bags which are configured to expand around the UAV for the purpose of reducing the deceleration forces of the UAV on impact. UAV's are provided that are configured with a system that includes a triggering mechanism that deploys one or more bags when there is a failure or when flight is no longer sustainable.

Disclosed is a drone capable of operating in an aqueous environment. The drone may include a buoyant structure configured to provide buoyancy. Further, the drone may include one or more propulsion units configured to propel the drone. Furthermore, the drone may include an upper camera disposed on an upper side of the drone. Additionally, the drone may include a lower camera disposed on a lower side of the drone. Further, each of the upper camera and the lower camera may be configured to capture images. Furthermore, one or more legs configured to enable the drone to stand on a solid surface. Additionally, the drone may include one or more leg-actuators coupled to the one or more legs. Further, the one or more leg-actuators may be configured to change a state of the one or more legs to one of an extended state and a retracted state.

A pressurized actuator system for simultaneously deploying a plurality of inflatable floatation devices or other structures for a rotorcraft or other mobile or stationary devices includes a plurality of primary sources of pressurized fluid adapted for deploying a corresponding number of inflatable structures, a plurality of primary valves that are each operatively associated with one of the primary sources, a plurality of pressure-responsive primary transducers operative to open a different one of the primary valves, and a secondary source of pressurized fluid adapted for simultaneously operating the primary transducers to thereby open the primary valves and simultaneously deploy the plurality of inflatable structures.

A search and rescue drone system includes a buoyant body member, a frame attached to the buoyant body member for carrying a motor and propeller, and an electronic array including a camera, GPS, an EPIRB radio distress beacon, and a transmitter / receiver for remote control flying the drone and communicating with an operator. A laser guidance system may provide coordinates for landing near a swimmer in distress. The search and rescue drone may also be programmed to simply fly to the location of an electronic wearable device, like a bracelet, that is worn by a man overboard. In another embodiment, the search and rescue drone includes pivoting motor mounts, so that it can take off and land vertically with propellers rotating in a horizontal plane, and then the propellers may pivot to rotate in a vertical plane for propulsion across water similar to a fan boat with rescued people aboard.

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 gas source is in fluid communication with the interior of the airbag for inflating the airbag with gas generated provided by the 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. The gas source is provided for at least partially re-inflating the airbag after venting of gas through the at least one vent.

An occupant protection system for an aircraft comprising a sensor system for sensing flight condition information and a control system, which includes an impending crash detection system and an impact detection system. The impending crash detection system receives flight information from the sensors determines whether a crash is likely to occur. If an impending crash is detected, the impending crash detection system activates impact modes of a first group of aircraft systems. The impact detection system receives flight information from the sensor system and determines whether an impact has occurred or is occurring. If an impact is detected, the impact detection system activates impact modes of a second group of aircraft systems.

A multi-wing, multi-engine, multi-hull amphibious aircraft is disclosed. In the illustrative embodiment, the aircraft has an open frame structure without a fuselage.

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.

The invention discloses a miniature multi-rotor aircraft capable of taking off from and landing on water and land and being self-charged in the technical field of small-size aircrafts. An inflating module, a charging module and a release module are installed on the miniature multi-rotor aircraft, wherein the inflating module is installed on a landing gear at the bottom of the multi-rotor aircraft and consists of a gas generator, miniature electronic valves, gas transmission pipes and airbags which are installed on landing gear bottom rods; the charging module consists of miniature solar energy receiving panels arranged on the surface of the rack of the aircraft, an energy management and a battery; and the release module is connected with the landing gear bottom rods and the airbags. The miniature multi-rotor aircraft capable of taking off from and landing on water and land and being self-charged has the characteristics of light weight and small resistance during flying in air and high stability of landing in water, can be widely used for image pickup, environmental detection, field rescue and the like in spaces above water surfaces, and has a wide prospect.

The present invention relates to an unmanned vehicle including:—a vehicle chassis (2) that has at least one actuator (3) involved in the driveability of the vehicle (1);—a set of on-board electronic components, namely at least one on-board electronic / computer control system;—a telecommunication unit; and—a geolocation unit. According to the invention, the on-board electronic components are arranged within a carrier so as to form, together, a removable technical unit (5) that is removably mounted on the vehicle chassis (2). The technical unit (5) and the vehicle chassis (2) include a mechanical / electrical interface unit (7) that are suitable, on one hand, for the releasable mechanical attachment of the removable technical unit (5) to the vehicle chassis (2) and, on the other hand, for the releasable electrical connection of the technical unit (5) to the at least one driveability actuator (3).

The invention relates to a salvage unmanned aerial vehicle capable of being remotely controlled. The salvage unmanned aerial vehicle comprises a fuselage, a flight control module, a flight mechanism and a delivery mechanism, wherein the flight mechanism comprises a plurality of flight assemblies which are uniformly arranged at the periphery of the fuselage, each flight assembly comprises a support arm, a flight motor and a rotor wing, the delivery mechanism comprises a shell body, a rising and falling assembly and life buoys, and the rising and falling assembly comprises a first lead screw, a loop bar, a first circular gear, a second circular gear and a driving motor. The salvage unmanned aerial vehicle capable of being remotely controlled is ingenious in structure and is applied to sea surface patrol and life buoy delivery during salvaging, the specific delivery mechanism is used for throwing the prepared life buoys at locations of trapped people, and a specific vertical delivery mechanism can be used for preventing the trapped people from drowning and can also be used for accurately delivering the life buoys to the locations of the trapped people.

An unmanned vehicle includes a vehicle body having an accommodating space, an arm assembly coupled to the vehicle body, and a floating member connected to a bottom surface of the vehicle body. The arm assembly includes a first rotating member, a second rotating member coupled to the first rotating member, and a propeller. The propeller includes a rotatable axle coupled to the second rotating member and extending along a rotating axis. The second rotating member can turn the propeller by rotating the rotatable axle about the rotating axis. The first rotating member can rotate and effect a movement of the second rotating member so as to selectively adjust the rotatable axle to align the rotating axis with a first axial direction and a second axial direction. The arm assembly can rotate relative to the vehicle body to selectively rotate into or out of the accommodating space.

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).

The invention relates to an unmanned aerial vehicle (UAV) used for clearing trash in water. The UAV comprises a fuselage, a flight control circuit, a flight mechanism and a fire extinguishing mechanism, wherein the flight mechanism comprises a plurality of flight assemblies evenly arranged on the periphery of the fuselage; each flying assembly comprises a cantilever, a propeller and a flight motor; the fire extinguishing mechanism comprises a casing, water tanks, a lifting and lowering assembly and a folding assembly; the lifting and lowering assembly comprises a first lead screw, a first gear, a second gear, a lifting and lowering motor and a folding base; and the folding assembly comprises a supporting rod, a rotating shaft, a nozzle and a folding motor. The UAV used for forest fire extinguishing is ingenious in structure; the unique fire extinguishing mechanism is used for watering and extinguishing fire above on-fire ground; the folding mechanism can adjust the spraying angle and range of water, thereby improving the fire extinguishing ability; and a unique water pumping mechanism can replenish the water tanks of the UAV in the fields, thereby improving the continuous fire extinguishing capability of the UAV.

Transformation method of hybrid transportation vehicle for ground and air includes the following transformation and reciprocal steps: Tilting the compensation cover (7) on. Expansion of both whole wings (1) from the transportation vehicle longitudinal position around two vertical axes (2) into the flying position. Expansion of rear parts of wings (1) from the top front parts of wings (1) into the spread flying position by tilting the rear of each wing (1) around a horizontal axis (3). The take-off and landing tilting of wings (1) by an angle of attack alpha=0 to 40° of the wings onset. Front wheels track (5) is reduced by axially shifting the front wheels (5) towards the fuselage. Furthermore, a corresponding hybrid transportation vehicle for ground and air is described which contains reciprocal transformation mechanisms for transformation from a sterling double or four-track automobile into a sterling aircraft for take-off and landing on the ground or water, and vice versa.