Abstract: A crankset for a pedal-driven vehicle has a frame with a bottom bracket shell. The crankset includes a crank arm rotatably mounted to the bottom bracket shell of the frame; a spindle operatively connected to the crank arm at an end spaced-apart from the bottom bracket shell and rotatable about a spindle rotation axis. A stationary member fixedly mounts to the bottom bracket shell. A rotatable member operatively engages the spindle and is configured to engage the spindle in rotation. A connecting assembly operatively engages the stationary member and the rotatable member. The connecting assembly is configured to engage the rotatable member in rotation upon rotation of the crank arm about the bottom bracket shell. A pedal angular control assembly operatively connects to the spindle and is configured to control an angle of a pedal according to an angular position of the crank arm during rotation.

Abstract: A bicycle pedal comprises a pedal axle, a main pedal body, a coupling mechanism and a cleat movement restricting member. The main pedal body is rotatably supported on the pedal axle. The coupling mechanism includes a first cleat securing member and a second cleat securing member. The first cleat securing member is configured to be coupled to a front portion of a cleat. The second cleat securing member is configured to be coupled a rear portion of the cleat. The cleat movement restricting member is configured to restrict movement of the cleat in at least one direction between a frontward direction and a rearward direction. The cleat movement restricting member is further configured and arranged relative to the coupling mechanism such that the cleat movement restricting member guides the cleat during a cleat disengagement operation in which the cleat detaches from the coupling mechanism.

Abstract: An electric bike comprises a front wheel, a rear wheel, a seat for a rider to sit on, a frame that supports the front wheel, the rear wheel and the seat, a driving device that provides moving energy to the electric bike and a braking device that reduces the speed of the electric bike. The driving device comprises one or more electric motors. The electric bike further comprises a pedal assembly that receives muscle power from the rider. The pedal assembly comprises a pedal axis and two pedals fixed to the pedal axis. The torque from the pedal assembly is not mechanically transferred to the front wheel or the rear wheel.

Abstract: A sprocket wheel for a bicycle includes a first main surface, which is flat in one or more sections, and a second main surface, which is situated opposite the first main surface. The second main surface is flat in one or more sections and extends parallel to the first main surface in one or more sections. The sprocket wheel also has an outer circumferential surface, which connects the first and the second main surface to one another and on which toothing is provided.

Abstract: A snow bike track assembly includes a frame assembly, at least one strut, an endless track, a plurality of top and bottom rollers, a skid rail assembly, a drive assembly, and a swing arm assembly. The frame assembly is configured to connect to a frame of a motorcycle in place of a rear wheel of the motorcycle. The at least one strut is connected to the frame assembly and configured to connect to the motorcycle frame in place of a rear shock of the motorcycle. The plurality of top rollers are mounted to the frame assembly and arranged to support the endless track. The plurality of lower rollers are mounted to the skid rail assembly and arranged to support the endless track. The drive assembly is configured to drive the endless track. The swing arm assembly is coupled between the frame assembly and the skid rail assembly.

Abstract: An inflatable boat with a motor mount for use in shallow water conditions. The inflatable boat with the motor mount has a U-shaped hull in plan view, which is formed by open outline of inflatable boards and nose, as well as a transom installed on the boat stern and an inflatable bottom attached to the hull from below, and which bottom has an axissymmetric groove laying longitudinally from the stern end. The groove is V-shaped in cross-section. The depth of the groove is reduced uniformly in direction to the bottom nose. The inflatable boat according to the present invention allows expansion of usage specifications of the inflatable boats with motor mount, provides an additional guard for the outboard motors installed on them against possible mechanical damages and lowers fuel consumption in comparison with the boats of similar design.

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. The closure can also be extracted from the disc slot in an open state to allow the mooring line to be removed from the aperture through the slot past the disc periphery.

Abstract: An autonomous watercraft with a waterproof container that houses a satellite communication terminal. The waterproof container includes a first shell mounted on a deck of the watercraft and that has a sealed first interior space that contains satellite communication circuitry of the terminal. The waterproof container also includes a second shell mounted under the deck of the watercraft and that has a sealed second interior space that contains the processing circuitry of the terminal. The first and second shells include ports configured to receive connectors for communication signaling and/or power. The first shell can also include a pressure port to pressurize the first interior space for use in leak detection. The shells can also include heat sinks to cool the satellite communication terminal.

Abstract: A bunkering marine vessel has an elongated, multi-deck accommodation structure extending along a portion of the length of one hull side and spaced apart from a centerline extending from bow to stern. Positioned within the vessel hull is at least one LNG pressure vessel filling at least 50% of the hull volume and extending from adjacent a lowermost deck to adjacent the main deck. At least one marine gasoil tank is positioned along an opposing hull side to counter the weight of the accommodation structure. The bow and stern ends of the vessel are substantially the same in shape, and each end includes a marine propulsion system.

Abstract: The present disclosure relates to a vessel that comprises at least one super structure configured to at least in part translate relative to said hull between a first position and at least one other position. The at least one superstructure in said first condition at least in part defines a first zone suitable for accommodating at least one person and/or vehicle, and the at least one superstructure in said second condition at least in part defines a second zone suitable for accommodating at least one person and/or vehicle. Preferably the at least one superstructure at least in part separates the first and second zones. Preferably the vessel's centre of mass is aft of mid-ship in the first condition and forward of mid-ship in the second position.

Abstract: A watercraft with improved safety and stability is provided. The watercraft includes a shell defining a plurality of raceways for receiving water during certain maneuvers of the watercraft, thereby excerpting force upon the watercraft in a first direction. The shell is configured so as to prevent or otherwise inhibit the water from excerpting an opposed second force upon the watercraft. An intermediate panel of the shell provides increased flexibility, thereby serving as a shock absorber for the watercraft.

Abstract: A keel canting mechanism for a sailing vessel having a hull, a keel and a mast is disclosed. The mechanism comprises a worm gear co-axial with the longitudinal axis of the vessel about which the keel rotates during a canting movement. There is a double enveloping worm in mesh with the worm gear and means for driving the worm. The worm gear is fast with the keel and, when rotated by the worm, displaces the keel through a canting movement. The gear has a plurality of holes in it into which pins can be inserted to lock the gear, and hence the keel, in the position to which it has been moved by the worm.

Abstract: A marine propulsion system for shallow waters, swamps, savannahs and the like includes a rotating propeller shaft supporting a propeller. An anti-cavitation body defines a partial cylinder having a longitudinal axis adjacent to the propeller. The propeller generates a vacuum between the anti-cavitation body and a surface of a water body. First and second wings adjacent to edges of the anti-cavitation body are generally planar and operatively angled towards the bottom of a water body. The first and second wings are adjusted to run below the water body surface and seal the anti-cavitation body to maintain generated vacuum. A first thread is cut in a first helical direction at an end of the rotating propeller shaft adjacent the propeller, and slightly more distal therefrom a second thread is cut in a second helical direction opposed to the first thread helical direction. The second thread drives matter away from the bearing.

Abstract: A front propeller on a main shaft communicated from one end to an engine transmission; the propeller having a hub and a plurality of blades extending radially outwardly from the hub; a rear propeller co-axially to, and spaced apart from, the front propeller rearwardly in an axial direction having a hub and a plurality of blades extending radially outwardly from the hub. An adaptor is coaxial with the main shaft and comprising a second shaft for supporting the rear propeller. A plurality of pitched-formed seating surfaces having ramps, are spaced apart from the second shaft in an axial direction. An adaptor communicates with the rear side of the front propeller in the axial direction; a plurality of locking elements are movable in the axial direction, each being in contact with the seating surfaces of the adaptor, and communicate with the rear propeller from the other end.

Abstract: A marine propeller includes a plurality of blades attached to a hub, with a disk area ratio of approximately 50%, a blade area ratio of approximately 61%, a blade rake angle of approximately 26.5 degrees, a blade skew angle of approximately 0 degrees, and wherein the angle between the chord line at any given radius r on said blades with a line that is parallel to the propeller axis of rotation and intersects the chord line, is equal to tan?1(2?Nr/Vo)??, where N is the rotational speed of the propeller at a selected design condition, Vo is the speed of the water entering the propeller (i.e.

Abstract: A power generation method and device utilizes fluid currents to generate power by rotating a rotation element which in turn rotates a cable which turns components within a power generator to generate the power. The rotation element is positioned within the fluid and is able to move to different depths as desired. The power generator is positioned inside or outside of the fluid. The rotation element is able to be a helix, helix-propeller, propeller or any other practical design. The rotation element is also able to implement additional components.

Abstract: This power system for mounting on a marine vehicle includes a propulsion unit, means for securing the propulsion assembly to a hull element of the vehicle and a rudder bearing mechanically connecting the propulsion unit with the fittings. The fittings are configured so that once the power system is mounted on the hull element; the plane of the rudder bearing is inclined relative to a plane containing one longitudinal axis and one transverse axis of the marine vehicle.

Abstract: A marine drive includes an engine; a cowl having first and second cowl portions. The first cowl portion is movable with respect to the second cowl portion into an open position in which the engine is manually accessible and a closed position in which the engine is enclosed; and a rigging port in the second cowl portion. The rigging port provides a passageway for rigging connectors extending from the engine to a component located remotely from the engine. A rigging opening provides manual access to the rigging connectors and the engine, including when the first cowl portion is in the closed position. A removable access door covers the rigging opening and prevents manual access to the engine and rigging connectors via the rigging opening. The removable access door is fastened to the second cowl portion by a removable fastener that is hidden from view.

Abstract: The present invention relates to an apparatus and method of protecting a boat motor powerhead or cowl or cowling and preventing damage to the powerhead, cowl or cowling when a boat is docking or backing into a bulk head. More particularly, the present invention relates to a protective device that easily attaches to and slips over the boat motor, allowing for easy positioning of a protective pad on the outside of the motor which protects it from impact and prevents damage to the motor while the boat is docking or backing into a bulk head.

Abstract: A fuel tank arrangement in a marine vessel has a tank container, a first fuel line having a first fuel line port opening into the tank container so as to provide a flow path exclusively for a first fuel, a second fuel line having a second fuel line port opening into the tank container so as to provide a flow path exclusively for a second fuel. The first fuel line port and/or the second fuel line port is provided with a plug or alike to close the flow path from the tank container into the fuel line.

Abstract: The drive unit is designed to be mounted on a marine vessel, including a mobile housing, and is able to pivot around an axis against the hull of the marine vessel. A drive shaft mounted rotary is against the mobile housing and is supported by two roller bearings. A propulsion element rotates in solidarity with the drive shaft. The propulsion unit has, at the front, at least two braking and locking systems of the drive shaft located in an area between the upstream rolling bearing and propulsion element.

Abstract: Innovative new systems and method of operating the systems, wherein the system comprises an airborne platform comprising an unmanned balloon comprising a gas enclosure; a geographic locator or tracking system configured to determine geographical coordinates of the unmanned balloon; a payload comprising a transceiver, wherein the transceiver is capable of communicating with communication devices that are separate from the unmanned balloon; first and second flight-termination devices each configured to cause termination of a flight of the unmanned balloon; and at least two power sources each configured to provide power to at least one of the first and second flight-termination devices.

Abstract: The present invention relates to the technical field of UAV (unmanned aerial vehicle), and more particularly to a UAV with linkage foldable arms, which includes a linkage mechanism, a fuselage body and multiple aircraft arms. The multiple aircraft arms are connected with each other through the linkage mechanism and are connected with the fuselage body; a locating part is located in a middle of the fuselage body; the locating part comprises a positioning structure, a fixed structure which plays a limit role is located on one of the multiple aircraft arms, the fixed structure is buckled with the positioning structure. When the aircraft arms are unfolded or folded, only one aircraft arm needs to be operated to drive other aircraft arms to move under the action of the linkage mechanism, so that multiple folding steps are simplified into a folding process, which is convenient in operation and strong in practicability.

Abstract: An aircraft interior lining component is formed at least partially of a thermoplastic foam material and includes a first surface which faces an interior of an aircraft cabin when the aircraft interior lining component is mounted in an aircraft, and a second surface which faces away from the interior of the aircraft cabin when the aircraft interior lining component is mounted in an aircraft. The second surface of the aircraft interior lining component includes at least one supporting section and at least one surface section adjacent to the supporting section and recessed relative to the supporting section. The supporting section is dimensioned and arranged so that it is supported, when the aircraft interior lining component is mounted in an aircraft, on an element of a primary structure of the aircraft at least when a predetermined load acts on the first surface of the aircraft interior lining component.

Abstract: A set of machines and related systems build structures by the additive assembly of discrete parts. These digital material assemblies constrain the constituent parts to a discrete set of possible positions and orientations. In doing so, the structures exhibit many of the properties inherent in digital communication such as error correction, fault tolerance and allow the assembly of precise structures with comparatively imprecise tools. Assembly of discrete cellular lattices by a Modular Isotropic Lattice Extruder System (MILES) is implemented by pulling strings of lattice elements through a forming die that enforces geometry constraints that lock the elements into a rigid structure that can then be pushed against and extruded out of the die as an assembled, loadbearing structure.

Abstract: A fluid connection system for fluidly connecting a pair of fluid reservoirs, such as fuel cells, includes a bellowed portion surrounding a connection portion through which fluid can flow between the two reservoirs. The bellowed portion allows for relative movement between the two reservoirs without breaking the fluid-tight connection between the two reservoirs. Also, a guard member surrounds at least some of the outer periphery of the bellowed portion. The guard member serves as a shield around the fluid-tight connection and bellowed portion, and thereby helps prevent damage to the fluid-tight connection in the event of a crash or hard landing.

Abstract: An airframe (10) for an air vehicle comprising an outer skin layer (12) and a support layer (13) defining a fuselage of said air vehicle, wherein said outer skin layer (12) is magnetically coupled to said support layer (13).

Abstract: A foldable multi-rotor UAV includes: a fuselage; and a plurality of arms, wherein a first end of each of the arms is connected to a side face of the fuselage through a rotating mechanism; a motor and foldable blades connected to the motor are provided on a second end of each of the arms; each of the arms rotate relatively to the fuselage through the rotating mechanism; wherein the arms comprises a front arm and a rear arm; during a folded state, the rear arm upwardly rotates towards the fuselage for folding, in such a manner that the rear arm is contained at a lower portion of the side face of the fuselage; then the front arm upwardly rotates towards the fuselage for folding, in such a manner that the front arm is contained at an upper portion of the side face of the fuselage.

Abstract: An apparatus and method are provided for a shape adaptive airfoil configured to be coupled with a tip of an airplane wing. In one embodiment, the shape adaptive airfoil is a blended winglet comprised of a base section coupled with the airplane wing, a blade section projecting in a vertical direction above the base section, and a radius section interconnecting the base and blade sections. Adaptive control structures may be incorporated into leading and trailing edges of the base section and the blade section. The adaptive control structures of the base section may facilitate changing a camber profile of the shape adaptive airfoil. The adaptive control structures of the blade section may enable changes to a toe angle of the blade section.

Abstract: Systems, devices, and methods for an extruded wing protection and control surface comprising: a channel proximate a leading edge of the control surface, a knuckle disposed about the channel, a leading void, a trailing void, and a separator dividing the leading void and the trailing void; and a plurality of notches disposed in the extruded control surface proximate the leading edge of the control surface.

Abstract: A fairing ring for a bladed wheel is disclosed. The fairing ring includes an annular wall extending axially, the wall presenting a plurality of notches extending axially, each notch being configured to receive a leading edge or a trailing edge of a blade.

Abstract: An open rotor airfoil apparatus includes: an airfoil body having pressure and suction sides extending in span from a root to a tip, and in chord between leading and trailing edges. A majority of the leading edge in an outer portion of the airfoil body has a sweep equal to or greater than a predetermined sweep profile, selected to produce a blade-relative velocity component perpendicular to the leading edge, at a tip radius, of Mach 0.75 or less, and to produce a blade-relative velocity component perpendicular to the leading edge, at 65% of tip radius, of Mach 0.87 or less, with the blade-relative velocity component perpendicular to the leading edge varying linearly between the two limits, in the presence of transonic or supersonic relative velocity conditions. Each of the blades has a leading edge thickness greater than 0.45% of the chord, measured at a 0.5% chordwise location.

Abstract: A self-adjusting flight control system is disclosed. In various embodiments, an input interface receives an input signal generated by an inceptor based at least in part on a position of an input device comprising the inceptor. A processor coupled to the input interface determines dynamically a mapping to be used to map input signals received from the inceptor to corresponding output signals associated with flight control and uses the determined mapping to map the input signal to a corresponding output signal. The processor determines the mapping at least in part by computing a running average of the output signal over an averaging period and adjusting the mapping at least in part to associate a neutral position of the input device comprising the inceptor with a corresponding output level that is determined at least in part by the computed running average.

Abstract: An unmanned aerial vehicle includes: a vehicle body, where the vehicle body includes a first positioning device; and a landing gear, where the landing gear can be detached from the vehicle body, and when the landing gear is detached from the vehicle body, the vehicle body determines a position of the landing gear by using the first positioning device. Because the landing gear can be detached from the vehicle body and the vehicle body can determine the position of the landing gear by using the first positioning device, the unmanned aerial vehicle, when performing a flight mission, is not affected by the weight of the landing gear, avoiding that the landing gear blocks an image capture device and implementing convenient takeoff and landing.

Abstract: A landing gear includes a fixing mechanism, a driving mechanism disposed on the fixing mechanism, a translating member connected to the driving mechanism and configured to move relative to the fix mechanism whey being driven by the driving mechanism, and two supporting feet disposed opposite to each other. The two supporting feet are pivotally connected to the fixing mechanism and movably connected at two ends of the translating member. The driving mechanism is configured to drive the two supporting feet through the translating member to rotate relative to the fixing mechanism.

Abstract: A mechanical system for transmitting rotary motion between at least two shafts movable in rotation respectively about a first axis and a second axis, the first and second axes intersecting, the mechanical system including a bevel gear set made up of a first bevel gear having teeth and movable in rotation about the first axis and a bevel wheel having teeth and movable in rotation about the second axis, the teeth of the first bevel gear and of the bevel wheel respectively being suitable for co-operating in complementary manner with one another, the first bevel gear, referred to as a “power” gear, presenting a first defining pitch surface of conical shape, and the bevel wheel presenting a second defining pitch surface of conical shape.

Abstract: A computer-implemented method for controlling an unmanned aerial vehicle (UAV) includes: receiving, by a computer device, UAV data from a UAV; displaying, by the computer device, a representation of the UAV on a map based on the UAV data; receiving, by the computer device, a user input to control the UAV; and transmitting, by the computer device, an authenticated control signal to the UAV based on the received user input, wherein the control signal is configured to override control of the UAV from a UAV remote controller associated with the UAV.

Abstract: An unmanned aerial vehicle (UAV) (200, 300, 400, 700, 800, 1000, 1200, 1500) can include a central body (202, 302, 402, 702, 802, 1002, 1202, 1502), a plurality of rotors, and a plurality of arms (204, 306, 406, 706, 806, 1006, 1206, 1506) extending from the central body (202, 302, 402, 702, 802, 1002, 1202, 1502), where each arm of the plurality of arms (204, 306, 406, 706, 806, 1006, 1206, 1506) is configured to support one or more of the plurality of rotors.

Abstract: An afterbody for a rotor blade of a rotorcraft is unitarily formed of a single material of construction. The afterbody includes an upper surface disposed from a lower surface, a concave leading edge connected to the upper surface and the lower surface, and a trailing edge formed at an intersection of the upper surface with the lower surface.

Abstract: A vertical take-off and landing (VTOL) aircraft is provided comprising a fuselage (12) defining a forward end and an aft end, the fuselage accommodating at least one engine (56), a left wing (18) and a right wing (20) extending from either side of the fuselage, a lift fan drive system (22) accommodated within each wing, a forward thrust fan drive system (24) fitted proximate the aft end of the fuselage, and a stabiliser arrangement (26) proximate the forward thrust fan drive system. In an embodiment, each wing comprises a rotor housing portion (18.1, 20.1) extending away from the fuselage and a wing tip portion (18.2, 20.2) extending away from the rotor housing portion, the wing tip portion being angled towards the rear and side of the aircraft. In an embodiment, the rotor housing portion comprises two rotor housings, one forward of the aircraft's centre of gravity and one aft of the aircraft's centre of gravity.

Abstract: An autonomous flight vehicle capable of both rotary wing flight and fixed wing flight may include a pair of rotary wing flight thrusters used during rotary wing flight and a smaller pair of hybrid flight thrusters used during both rotary wing flight and fixed wing flight. The larger rotary wing flight thrusters are skewed at an angle to reduce an apparent torque and improve the controllability of the autonomous flight vehicle, while using smaller, and so more efficient, thrusters during fixed wing flight.

Abstract: A heavy payload, autonomous UAV able to deliver supply by way of airdrop with more precision and at a lower cost. The UAV is equipped with two movable wing systems that rotate from a stowed position to a deployed position upon jettison of the UAV from a mothership. The UAV can be controlled remotely or it can operate autonomously and the movable wings can include ailerons to effectuate flight control of the UAV. The UAV can be reusable or can be an expendable UAV.

Abstract: Devices for inhibiting a cable coupling drones from being entangled in the propellers of the drones, and associated systems and methods, are described herein. For example, a device can include a first weight coupled to the cable and configured to direct the cable at least partially away from the propellers of the drones. In some embodiments, the first weight can be coupled to the cable proximate to one of the coupled drones, and the device can include a second weight coupled to the cable proximate to the other of the coupled drones and configured to direct the cable at least partially away from the propellers of the drones.

Abstract: A multirotor aircraft and a method for controlling the multirotor aircraft are disclosed. The multirotor aircraft comprises a body and a H-shaped frame, wherein, the body is mounted with a bearing, a first person view camera and a servo mechanism, the end of each arm of the H-shaped frame far away from a lateral shaft thereof is mounted with an actuator assembly, the lateral shaft of the H-shaped frame is connected with the body by the bearing, and the servo mechanism is coupled with the lateral shaft of the H-shaped frame and is configured to control the rotation of the lateral shaft of the H-shaped frame, in order to control the angle between the body and the H-shaped frame. The method comprises a first mode and a second mode, wherein in the first mode, keeping the horizon within the camera view of the aircraft; and in the second mode, generating control command on the basis of the camera aligned axis.

Abstract: A personal flight vehicle including a platform base assembly that provides a surface upon which the feet of an otherwise free-standing person are positionable, and including a plurality of axial flow propulsion systems positioned about a periphery of the platform base assembly. The propulsion systems generate a thrust flow in a direction substantially perpendicular to the surface of the platform base assembly, where the thrust flow is unobstructed by the platform base assembly. The thrust flow has a sufficient intensity to provide vertical takeoff and landing, flight, hovering and locomotion maneuvers. The vehicle allows the pilot to control the spatial orientation of the platform base assembly by the movement, preferably direct, of at least part of his or her body, and the spatial movement of the vehicle is thus controlled.

Abstract: Deployable navigation beacons can be deployed from a vehicle, such as an unmanned aerial vehicle (UAV), in an event of a loss of position or orientation of the vehicle. After deployment of the navigation beacons, the vehicle may detect locations of the navigation beacon, which may define a surface that may include surface features. The vehicle may then perform control operations based on the resolved locations. For example, UAV may maneuver to land proximate to the navigation beacons after resolving locations of the navigation beacons as a continuous surface. The navigation beacons may output a visual signal (e.g., a light), a auditory signal (e.g., a sound), and/or a radio signal. In some embodiments, each navigation beacon may include a different or unique signal.

Abstract: Described herein are apparatuses for passively releasing a payload of an unmanned aerial vehicle (UAV). An example apparatus may include, among other features, (i) a housing; (ii) a swing arm coupled to the housing, wherein the swing arm is operable to toggle between an open position and a closed position; (iii) a spring mechanism adapted to exert a force on the swing arm from the open position toward the closed position; (iv) a receiving system of a UAV adapted to receive the housing, wherein the receiving system causes the swing arm to be arranged in the open position; and (v) a spool operable to unwind and wind a tether coupled to the housing, wherein unwinding the tether causes a descent of the housing from the receiving system, and wherein winding the tether causes an ascent of the housing to the receiving system.

Abstract: An airborne store support assembly includes an ejector housing assembly that receives a fluid-actuated ejector piston. Extension of the piston pushes apart an airborne store from an aircraft for separation after release. A selectable force gas generator (SFGG) includes a total number of more than one gas-generating unit in fluid communication with the ejector housing assembly to actuate the fluid-actuated ejector piston with a selected amount of force. A communication interface in communication with the SFGG supplies at least one firing signal that causes a selected subset of the more than one gas-generating unit that corresponds to the selected amount of force that is dynamically determined by a controller based on flight parameters of at least one of an attitude, a rate of motion, and a rate of acceleration of the aircraft.

Abstract: An unmanned aerial vehicle (UAV) is disclosed that includes a retractable payload delivery system. The payload delivery system can lower a payload to the ground using a delivery device that secures the payload during descent and releases the payload upon reaching the ground. The location of the delivery device can be determined as it is lowered to the ground using image tracking. The UAV can include an imaging system that captures image data of the suspended delivery device and identifies image coordinates of the delivery device, and the image coordinates can then be mapped to a location. The UAV may also be configured to account for any deviations from a planned path of descent in real time to effect accurate delivery locations of released payloads.

Abstract: An entertainment and connectivity system includes a processor for transferring information between a vehicle based user device and a server to validate a user's government identity before granting the user device access to the internet. The vehicle based server has an internet protocol address and communicates with user devices. The user devices each have an onboard internet protocol address mapped to the internet protocol address of the vehicle based server. A processor associated with the vehicle based server receives requests for internet service originating from the user devices. The requests include travel information or internet subscription plan information for a user of each of the user devices. The vehicle based server, or a ground based server that receives the request, generates an internet connection authorization decision based on validation of the user's government identity or the user's internet subscription plan information.