Abstract: The present invention relates to a boat with an improved buoyant body, comprising: a buoyant body, which is an U-shaped tube, consisted of a cladding and foam material filled therein; a bottom plate, set on the bottom of the buoyant body; a tail plate, set at the rear of the buoyant body and the bottom plate; wherein the cladding of the buoyant body is consisted of an inner layer and two outer layers, cladding the said inner layer; wherein the inner layer is a net, while the outer layers are sheets; thereby it is achieved, that the buoyant body possesses the features of low weight, high strength and high friction resistance.

Abstract: The present invention relates to a boat with an enhanced buoyant body and a foam filling method for the buoyant body, wherein a first material of polyether polyol as well as a second material mixed by polymethylene polyphenyl polyisocyanate and methylene bisphenyl isocyanate build up the foam material of the buoyant body, whereby it is achieved, that safety is improved while filling the foam material.

Abstract: A marine mooring line vermin shield to prevent the passage of vermin crawling along a marine mooring line from land to a pleasure craft, including a disc with a centrally located aperture through the disc, and a slot extending from the aperture to a periphery of the disc. The vermin shield also includes a closure that is urged to insert into the disc slot in a closed state compressing the mooring line against the aperture to secure the vermin shield against the mooring line. The closure may also be locked in the closed state.

Abstract: The invention relates to a water sports device comprising an inflatable body component (1) having a longitudinal direction (L) and inflatable arms (8a, 8b) on a rear end, the arms being distanced from one another and orientated in the longitudinal direction (L), between which arms a receptacle (2) having an inner contour is formed, and comprising a drive component (7) having a tread surface (4) and an underwater surface (3), which drive component is formed with a complimentary contour (10a, 10b, 11) on two longitudinal sides (10a, 10b) that are distanced from one another and which component can be inserted into the receptacle (2) from the rear end, wherein the inner contour and the complimentary outer contour (10a, 10b, 11) form a connection to one another and a position of the inserted drive component (7) in the receptacle (2) is secured in the direction of the tread surface.

Abstract: A catamaran oil production apparatus is disclosed for producing oil in a marine environment. The apparatus includes first and second vessels that are spaced apart during use. A first frame spans between the vessels. A second frame spans between the vessels. The frames are spaced apart and connected to the vessels in a configuration that spaces the vessels apart. The first frame connects to the first vessel with a universal joint and to the second vessel with a hinged connection. The second frame connects to the second vessel with a universal joint and to the first vessel with a hinged or pinned connection. At least one of the frames supports an oil production platform. One or more risers or riser pipes extends from the seabed (e.g., at a wellhead) to the production platform (or platforms). In one embodiment, the production apparatus includes crew quarters.

Abstract: A boat stabilization system includes a first radar unit constructed and arranged to be associated with a port side of a boat so as to obtain wave data of a port side wave prior to the port side wave contacting the port side of the boat. A second radar unit is constructed and arranged to be associated with a starboard side of the boat so as to obtain wave data of a starboard side wave prior to the starboard side wave contacting the starboard side of the boat. A control unit is connected with each of the first and second radar units and constructed and arranged to develop, based on the wave data of the port side wave and the starboard side wave, a three-dimensional wave map. The control unit is constructed and arranged to control a boat stabilizing device based on the wave map.

Abstract: Methods and system for creating dynamic maps are disclosed. A system for map creation for bodies of water may comprise an application server associated with a plurality of navigation devices, wherein the application server is configured to: (a) receive data from said plurality of navigation devices, the data including water-site information, time, and location: (b) perform statistical analysis on the data received by said plurality of devices; (c) determine the existence of bodies of water based at least on the statistical analysis; and (d) generate a dynamic map including one or more of the water depth charts and heat maps based at least on the statistical analysis.

Abstract: A laser-powered ice-penetrating communications payload delivery vehicle for sub-ice submarine missions enables under-ice operations to exchange information with terrestrial facilities or satellite networks with communications methods otherwise blocked by an ice cap. The vehicle comprises an electronics bay, a payload bay, optics bay, and a melt optic with laser. The system and method of establishing communication where the vehicle, tethered to a sub-ice vessel, is released. The vehicle ascends to the bottom of an ice sheet and uses a laser to melt the ice, forming a borehole through which the vehicle continues to ascend. When buoyancy no longer advances the vehicle beyond sea level, the vehicle continues to melt a conical opening through the ice until unobstructed atmosphere is reached and bi-directional communication is established.

Abstract: It is an object of the present invention to provide a means of constructing an Autonomous fully-Submersible Offshore Marine Platform (ASOMP) of considerable warfighting or commercial capability which is mobile and can autonomously transport to a hazardous operating area in a low-observable reduced vulnerability manner, fully submerge to avoid the military or environmental threat hazard, hibernate until needed, perform fully submerged mobility and mission operations, surface and provide Barge and SWATH surface ship mobility and mission operations, resubmerge if the hazardous threat appears and relocate to a new operating area. Another object of the present invention is to provide a fully autonomous and submersible low-cost “lily-pad” that surfaces when called and provides a main deck platform at appropriate freeboard and seakeeping motions to function as a refueling landing zone and pier to extend the range of aircraft and marine vehicles operating in a high-threat environment.

Abstract: A device (100) has surfaces (21, 22, 23, 24) and an anti-biofouling system (10) comprising at least one light source (11, 12) for performing an anti-biofouling action on at least a majority of the surfaces (21, 22, 23, 24), the at least one light source (11, 12) being adapted to emit rays of anti-biofouling light. The surfaces (21, 22, 23, 24) are configured relative to each other and to the at least one light source (11, 12) such that during operation of the at least one light source (11, 12), at least a majority of the surfaces (21, 22, 23, 24) is free from shadow with respect to the rays of anti-biofouling light from the at least one light source (11, 12), wherein it may be possible for the rays of anti-biofouling light to reach the surfaces (21, 22, 23, 24) by skimming along the surfaces (21, 22, 23, 24).

Abstract: The present technology is directed generally to electric marine propulsion systems with drive trains, and associated systems and methods. In representative embodiments, the disclosed technology includes pre-assembled transmission cartridges, gear reduction planetary gears, and/or component support arrangements that can increase the life of the system and/or reduce manufacturing costs.

Abstract: A boat speed control device for a boat including a manual shifter and an outboard motor, includes an actuator and a controller. The outboard motor is operably connected to the manual shifter. The manual shifter includes a shift lever shiftable between a sailing position and a neutral position. The actuator is connected to the shift lever. The controller is configured or programmed to control the actuator to shift the shift lever to the sailing position and the neutral position.

Abstract: A propulsion control system for a marine vessel includes a plurality of propulsion devices steerable to propel the marine vessel, at least one proximity sensor that determines a relative position of the marine vessel with respect to an object, wherein the at least one proximity sensor has a field of view (FOV). A controller is configured to identify a trigger condition for expanding the FOV of the at least one proximity sensor and control thrust and/or steering position of at least one of the plurality of propulsion devices to expand the FOV of the at least one proximity sensor by inducing a roll movement or a pitch movement of the marine vessel.

Abstract: A method for controlling low-speed propulsion of a marine vessel powered by a marine propulsion system having a plurality of propulsion devices includes receiving a signal indicating a position of a manually operable input device movable to indicate desired vessel movement within three degrees of freedom, and associating the position of the manually operable input device with a desired inertial velocity of the marine vessel. A steering position command and an engine command are then determined for each of the plurality of propulsion devices based on the desired inertial velocity and the propulsion system is controlled accordingly. An actual velocity of the marine vessel is measured and a difference between the desired inertial velocity and the actual velocity is determined, where the difference is used as feedback in subsequent steering position command and engine command determinations.

Abstract: A method of operating a marine vessel hybrid propulsion system having a propulsion shaft and a propeller, an internal combustion piston engine in force transmission connection with the propulsion shaft, and an electric motor-generator in force transmission connection with the propulsion shaft and/or with the piston engine. The internal combustion piston engine can be started by applying electric power from an on-board power source to the electric motor-generator and rotating the internal combustion piston engine by the electric motor-generator and rotational speed of the internal combustion piston engine is accelerated to a predetermined limit rotational speed without attempting to start the internal combustion piston engine, and only after the rotational speed of the internal combustion piston engine reaches the predetermined limit rotational speed, the internal combustion piston engine is started.

Abstract: A plugged stringer on a surface of a part, and a method and assembly for production of the plugged stringer. The plug has opposite first and second axial end faces. The plug also has a radially outer margin defined by a radially outer bottom face, radially outer first and second opposite side faces, and a radially outer top face. The plugged stringer also includes a covering overlaying the radially outer top face and the first and second opposite side faces of the plug and extending away from the plug along an axis to form a stringer having first and second segments delineated by the plug. The radially outer margin of the plug is at least partly covered by an adhesive. The radially outer bottom face is adhered to the surface of the part, and the covering is adhered to the radially outer first and second opposite side faces and the radially outer top face. The first and second segments of the stringer respectively define first and second fluid passages separated by the plug.

Abstract: There is disclosed an emergency door positionable in an exit opening of an aircraft. The door has door supports mountable to the lower wall and each having a pivot point. A first pivot axis is defined between the pivot points. A block is mountable to the lower wall and is offset from a center of the lower wall. A door body is mountable within the opening to the door supporting structure and pivotally mountable to the door supports. The door body is pivotable about the first pivot axis from an initial position in which the door body is within the opening, until the door body is disengaged from the door supports. A bottom portion of the door body abuts against the block to define a removal pivot point. The door body is pivotable about the removal pivot point to remove the door body from the exit opening.

Abstract: A block and bolt connector comprises a block having an aperture with a lower opening and an upper opening which is smaller than the lower opening. The aperture extends through the block from the lower opening to the upper opening, and has a first portion and a second portion. A bolt has a head portion which passes through the lower opening but not the upper opening, and a shaft which may pass through the lower opening and the upper opening. The head portion of the bolt is received within aperture of the block and the shaft extends at least partially outside of the block beyond the upper opening. The first and second portions of the aperture are configured so as to permit selected movement of the bolt within the aperture relative to the block.

Abstract: An unmanned aerial vehicle includes a plurality of propellers and an airframe. The airframe includes a body having a hollow portion, and a plurality of through holes connected to the hollow portion and formed on an outer peripheral surface of the body. The airframe also includes a plurality of arms supporting the plurality of propellers, and each arm of the plurality of arms includes a base end portion disposed at a body side in a longitudinal direction of the respective arm. The base end portion is inserted in a corresponding through hole of the plurality of through holes and supported by the body. Each arm of the plurality of arms is configured to be stored in the hollow portion of the body by being retracted into the body via the through hole, and expanded out of the body by being pulled out of the body via the through hole.

Abstract: An electronic speed controller (ESC) assembly for an unmanned aerial vehicle includes a first ESC for driving a first motor, a second ESC for driving a second motor, and a heat sink assembly disposed between the first ESC and the second ESC. The first motor is configured to drive an upper propeller to generate a lift, and the second motor is configured to drive a lower propeller to generate a lift. The first ESC and the second ESC are alternately disposed. The heat sink assembly includes a heat sink main body, and a thermally conductive metal and a heat dissipation pipe disposed on the heat sink main body. The thermally conductive metal is connected to the heat dissipation pipe. The first ESC and the second ESC are respectively in contact with the thermally conductive metal on the heat sink main body to transfer generated heat to the thermally conductive metal.

Abstract: A wing assembly is disclosed. The wing assembly includes a main structure having a first contact face and a first recess arranged to receive a portion of a tension bolt; and a modular edge having a second contact face and a second recess arranged to receive a portion of the tension bolt. The modular edge is pivotally mounted on the main structure for rotation between an installation position and an operational position in which the modular edge is aligned with the main structure to form at least part of an edge of the wing assembly. The wing assembly is arranged such that, when the modular edge is in the operational position, tension in a tension bolt received in the first and second recesses acts to press the first and second contact faces together, thereby forming a tension joint that resists pivoting of the modular edge relative to the main structure.

Abstract: A wing deployment mechanism and a design method using a pneumatic cylinder with transmission spring system (assembly) are provided. The deployment mechanism comprises frame, wing, deployment cylinder, gas canister, rotation shaft, bolts, groove, locking pin, dowel pin, flange, first spring, second spring, dowel pin hole, looking pin hole, slider, third spring. The design method includes step 1: determining the problem's specifications; step 2: constructing the equations of motion; step 3: designing a primary scheme for a system of pneumatic cylinder with transmission spring. Step 4: determining the parameters for the system; and step 5: validating the design.

Abstract: Linkage assemblies for aircraft wing hinged panels are described herein. An example linkage assembly includes a flap follower arm coupled between a spoiler support beam and a flap, a rocker, a panel link coupled between the hinged panel and the rocker, and a cross-bar link coupled between the flap follower arm and the rocker. The flap follower arm, the rocker, the panel link, and the cross-bar link are configured to coordinate adjustment of positions of the hinged panel and the flap relative to each other.

Abstract: A propulsion system for a vehicle comprises at least one propeller and at least one ducted fan. Each of the propellers is mounted on a respective duct of the ducted fan's outer perimeter and is adapted to be driven by a first electric motor. Each of the ducted fans is mounted within the duct and is adapted to be driven by a second electric motor. The rotation speeds and the blade pitch angles of the propellers and of the fans are controllable to achieve optimized efficiency of the propulsion unit, reduction of the noise of the system and minimization of combined torque of the system on the vehicle, by independently controlling the ducted fan RPM, the propeller RPM, and the propeller blades pitch angle.

Abstract: Systems and methods are provided for a hydraulic stabilizer trim actuator (HSTA). The HSTA may operate one or more movable control surfaces.

Abstract: A system and method for deploying a flight control surface. The method includes displacing actuators engaged with the flight control surface during an initial period wherein each actuator displaces from zero speed to a deployment speed, and during a deployment period after the initial period. The method includes during the deployment period, controlling displacement of at least one of the actuators in response to actuator status information received therefrom. The method includes during the initial period, limiting an acceleration of said actuator from the zero speed to the deployment speed. The system has a control unit with a force fight controller and an acceleration limiter.

Abstract: An aerodynamic structure for use on an upper surface of an aircraft wing is disclosed. The wing includes a slat operable between a stowed configuration in which the slat is stowed in a slat recess of the wing, and a deployed configuration in which the slat extends out of the slat recess. When the slat is in the deployed configuration, an end face of the slat recess is exposed, the end face intersecting with the upper surface of the wing at a recess edge. The aerodynamic structure, adjacent to the recess edge, has a volume shaped to encourage air flowing over the recess edge onto the upper surface during flight, to remain attached.

Abstract: A breakaway support configured to selectively release an actuator from a fitting and a method of providing the breakaway support. The breakaway support includes a race positioned between the actuator and the fitting. The second end of the actuator is connected to the fitting via a ball joint is positioned within the race. The ball joint permits the actuator to pivot about the ball joint in a vertical plane between a first position and a second position. The breakaway support includes a first knuckle that causes the actuator to release from the fitting when the actuator moves in a first direction beyond the first position. A portion of the fitting or a second knuckle may cause the actuator to release from the fitting when the actuator moves in a second direction beyond the second position. A portion of the actuator may break to release the actuator from the fitting.

Abstract: A support frame includes a locking assembly including a first locking frame and a locking block. The support frame also includes at least two support rods disposed on the first locking frame, the at least two support rods including at least one first support rod and at least one second support rod. The first locking frame is slidable relative to and along at least one of the support rods. The locking block is configured to be movable in a direction perpendicular to an axial direction of the second support rod and to press tightly on the second support rod, to lock the second support rod at a current location relative to an axial direction of the first support rod.

Abstract: An aircraft landing gear comprising: a shock-absorbing main leg having a sprung part for attachment to an aircraft and an un-sprung part including a slider and an axle carrying at least one wheel, the wheel having a toothed ring gear; a drive transmission mounted externally on the sprung part, or on the un-sprung part, of the main leg, the drive transmission having at least one motor and a drive pinion for meshing with the toothed ring of the wheel; and an actuator for lifting the drive transmission into and out of driving engagement with the toothed ring and for maintaining the driving engagement as the landing gear deflects during a ground taxiing operation. Also, a method of operating the aircraft landing gear.

Abstract: According to one embodiment, a clutch may be coupled between a rotor system and a power train of a rotorcraft. The clutch may be operable to disengage the rotor system from the power train during operation of the power train. A clutch control system in communication with the clutch and include a rotorcraft condition sensor operable to sense an operating condition of the rotorcraft and a control unit operable to prevent the clutch from disengaging the rotor system from the power train if the operating condition of the rotorcraft fails to satisfy a predetermined criterion.

Abstract: Embodiments herein disclose an aerial vehicle (AV). The AV comprises a body and a propulsion system. The propulsion system includes at least one primary rotor placed at a center of the AV and one or more auxiliary rotors mounted at a distance from the center of the AV. The distance of the one or more auxiliary rotors from the center of the AV can vary. Each of the auxiliary rotor are mounted to the AV at an adjustable angle from the center rotor of the vehicle. By adjusting the angles, the amount of lateral force that each auxiliary rotor exerts in the vertical direction and the horizontal direction is changed. In this way, the AV can be caused to move about in the horizontal direction without changing the attitude or vertical position of the AV.

Abstract: An aerial platform having motive devices for obtaining and maintaining loft of the aerial platform, the motive devices being pivotable relative to a wing of the aerial platform for aerial maneuvering of the aerial platform while generally maintaining stable disposition of the wing relative to the ground. The motive devices may include blades having selectively adjustable pitch for varying output force of respective motive devices. The aerial platform may further include one or more bladed turbines outwardly coupled to the wing and drivable by wind for generating power for the aerial platform. In some cases, the aerial platform may be tethered via a flexible power cable to a power source.

Abstract: A compound helicopter with a fuselage and at least one main rotor that is at least adapted for generating lift in operation, the at least one main rotor being arranged in an upper region of the fuselage, wherein at least one propeller is provided that is at least adapted for generating forward and/or backward thrust in operation. The at least one propeller is mounted to a fixed wing arrangement that is laterally attached to the fuselage, the fixed wing arrangement comprising at least one upper wing and at least one lower wing. An upper stub wing arrangement is provided in the upper region of the fuselage, the at least one upper wing of the fixed wing arrangement being mounted to the upper stub wing arrangement.

Abstract: Systems and methods related to passive variable pitch propellers are described. For example, an aerial vehicle may include one or more passive variable pitch propellers, and such propellers may include one or more passively movable propeller blades having respective hinges, flexible joints, or torsionally flexible joints. Based at least in part on current flight configurations, required thrust, and/or desired advance ratios, the passively movable propeller blades may modify their coning angles and/or pitches, such that the passive variable pitch propellers may operate with improved efficiency in two or more flight configurations. For example, in a VTOL flight configuration, the passive variable pitch propellers may have increased coning angles and decreased pitches, whereas in a horizontal flight configuration, the passive variable pitch propellers may have decreased coning angles and increased pitches.

Abstract: A for providing control input adjustment for an aircraft, including one or more mode sensors disposed on an aircraft, a mode analysis system, the mode analysis system operable to receive mode sensor data from the one or more mode sensors, and operable to decompose the mode sensor data into decomposed mode data associated with fundamental modes of structural elements of the aircraft associated with the one or more mode sensors, and a flight control computer (FCC) disposed on the aircraft and connected to one or more actuators, the FCC operable to provide a control signal to the one or more actuators according to an association between the decomposed mode data and one or more rotorcraft parameters associated with the one or more actuators.

Abstract: Aerial vehicles may be configured to control their attitudes by changing one or more physical attributes. For example, an aerial vehicle may be outfitted with propulsion motors having repositionable mounts by which the motors may be rotated about one or more axes, in order to redirect forces generated by the motors during operation. An aerial vehicle may also be outfitted with one or more other movable objects such as landing gear, antenna and/or engaged payloads, and one or more of such objects may be translated in one or more directions in order to adjust a center of gravity of the aerial vehicle. By varying angles by which forces are supplied to the aerial vehicle, or locations of the center of gravity of the aerial vehicle, a desired attitude of the aerial vehicle may be maintained irrespective of velocity, altitude and/or forces of thrust, lift, weight or drag acting upon the aerial vehicle.

Abstract: A series of heated control sticks for rotorcrafts, tiltrotors, and helicopters. The heated collective and cyclic sticks feature several heater assemblies to provide localized heating for pilots and co-pilots. The heater assemblies are formed from several layers of fabrics and resistive materials designed to generate heat while current is provided to conductive materials in the resistive material. A controller provides individualized control for users to adjust the temperature of various zones associated with either the collective stick or the cyclic stick. The heater assemblies can be installed entirely external to the stick like in a retrofit or partially internally.

Abstract: A bidirectional aircraft rotor for a rotorcraft tail rotor. The rotorcraft tail rotor uses a hub and a first tail rotor blade affixed to the hub. A pitch of the first tail rotor blade is fixed, and a profile of a leading edge of the first tail rotor blade is identical to a profile of a trailing edge of the first tail rotor blade. The tail rotor is driven by a torque source, such as an electric motor or an engine. The tail rotor uses variable RPM and reversible rotational direction to provide rotorcraft with yaw control.

Abstract: A compact Vertical Take-Off And Landing (VTOL) aircraft unit includes a duct fan including a propeller having a rotational axis which extends substantially vertically and discharges air downward to generate thrust sufficient for VTOL, an electric motor disposed above the duct fan and including an output shaft operatively connected to the propeller for rotating the propeller, and a cover disposed above the motor which is configured to support a load thereon. A gap is defined between the cover and the duct fan around an outer circumferential periphery of the aircraft and forms an opening of a primary flowpath for ambient air to the propeller, the primary flowpath for ambient air being non-parallel to the propeller's rotational axis.

Abstract: An aircraft is described and includes an airframe including first and second wings each having first and second oppositely disposed wing tips; first and second booms respectively extending longitudinally between the first and second wings and having forward and aft ends; first and second tail assemblies respectively coupled to aft ends of the first and second booms; first and second forward propulsion assemblies respectively coupled to the forward ends of the first and second booms, wherein the first and second forward propulsion assemblies are tiltable between a vertical takeoff and landing (“VTOL”) flight mode orientation and a forward flight mode orientation; first and second aft propulsion assemblies respectively coupled to upper ends of the tail assemblies, wherein the first and second aft propulsion assemblies are tiltable between a VTOL flight mode orientation and a forward flight mode orientation; and a payload module removably coupled to the airframe.

Abstract: A multirotor aircraft that includes a chassis, at least three engines that are equipped with propellers, and a free wing that is axially connected to the chassis. The attack angle of the free wing is changed relatively to the chassis due to flow of air. When the aircraft is hovering then the free wing is free to rotate, when wind flows over the wing during hovering then the tilt angle of the wing is changed by forces of the wind to a position in which a drag force on the wing is reduced, and by that enables a precise hovering relative to a ground point and precise control over the aircraft. The free wing provides lift force in horizontal flight and in situations of front horizontal wind during hovering and by that reducing the amount of energy required to operate the aircraft.

Abstract: A universal aerial platform (11, 41) supports lift elements (13, 14), thrusters (15), landing gear (21, 22) and a fuel supply (16) and has a coupling mechanism (17) external to the aerial platform for coupling to a terrain vehicle (20) so as to convert any suitably adapted terrain vehicle to a flying vehicle (10, 40). The terrain vehicle forms the cockpit of the flying vehicle. The terrain vehicle (20) includes flight controls that are automatically coupled to the airplane structure either wirelessly or by wires when the terrain vehicle is coupled thereto.

Abstract: Various embodiments of the present disclosure provide a parasail-assisted system for launching a fixed-wing aircraft into free flight and for retrieving a fixed-wing aircraft from free flight.

Abstract: A movable vehicle includes a main body, a first arm and a second arm each connected to the main body, a first pair of propulsion units positioned at opposite ends of the first arm, and a second pair of propulsion units positioned at opposite ends of the second arm. At least one of a longitudinal length of the first arm or a longitudinal length of the second arm is adjustable between an extended configuration and a retracted configuration.

Abstract: The present disclosure provides an unmanned aerial vehicle (UAV). The UAV includes a main body; an inertial measurement unit (IMU) disposed in the main body; a mounting bracket for fixing the IMU; and a circuit board fixedly disposed at the main body and integrated with a plurality of functional modules. The IMU is fixed on the circuit board through the mounting bracket.

Abstract: An unmanned aerial vehicle (UAV) includes a central body having a lateral dimension substantially less than a vertical dimension, and one or more propulsion units supported by the central body. The one or more propulsion units include rotor blades configured to rotate to generate lift for the UAV.

Abstract: Methods and systems are presented for making good use of recently obtained biometric data, for configuring propagule capsules (e.g. containing seeds or spores with growth media and other helpful materials) for deployment via drones so that each has an improved chance of survival, and for configuring drones or piloted craft for safe fleet deployment in remote locations.

Abstract: Presently disclosed subject matter integrates a method of using thousands of semi-autonomous unmanned aerial vehicles, herein called drones, to deliver vastly superior amounts of fire retardant over substantially larger and variably-shaped drop patterns. Each drone is able to swap its own batteries with freshly charged batteries and each drone is able to refill its container with water or fire retardant. Once launched, a swarm of drones can perform repeated trips from the water/retardant source to the fire without human involvement other than the high-level tasking of where to drop the retardant. Once a general drop destination and drop pattern shape is designated, the swarm can transport retardant to that location, form itself into the desired drop shape, and deploy retardant. The drone body is designed to be modular so different components can be attached with ease and no special training or knowledge required.

Abstract: A cargo handling system is disclosed. In various embodiments, the cargo handling system includes a power drive unit having a drive roller configured to impart movement to a unit load device; a first restraint; and a first sensor configured to detect movement of the unit load device with respect to a parked location following deployment of the first restraint and activation of the drive roller.