Abstract: A swimming board having a buoyant board body having an upper surface defining, with a continuous body sidewall, a channel recessed into the board body and disposed proximal to the second end of the board body and having a strap fastening assembly coupled to the board body and with a groin strap and a waist strap that define apertures for receiving a user's legs and retaining the user to the board body.

Abstract: A hydrodynamic intelligent robot and a control method thereof, the robot includes a moving platform, a hydrodynamic system and a dynamic intelligent system. The hydrodynamic system includes at least one nozzle mounted on the moving platform and a hydrodynamic device electrically connected to the dynamic intelligent system and connected to the at least one nozzle by a pipeline for spraying water so that the moving platform is rotated and moved by spraying water through the nozzle; the dynamic intelligent system is configured to control the hydrodynamic device according to input instructions, so as to indirectly realize vector control of the nozzle's water quantity and control the moving platform to move autonomously and intelligently. The present disclosure can monitor states of the moving platform by pre-inputting control instructions, and automatically determine numerical parameters needed to be adjusted by algorithm, so as to realize autonomous intelligent motion of the moving platform.

Abstract: A variable use pontoon boat configured to operate in both a high speed condition and an improved wake-profile condition is provided. The boat includes a pair of outer pontoons that flare outward in the rearward direction. A rear section of the outer pontoons has a width that is greater than its height. An inclined bottom surface is defined by the outer pontoons. The bottom surface is inclined upward in the rearward direction, and may be inclined laterally upward. The system may include a center pontoon that flares outward in the rearward direction. The center pontoon and the outer pontoons may be spaced apart at a decreased distance at the rear of the boat relative to the front of the boat, such that water is blocked at the rear of the boat and displaced downward. A pair of wake panels may be disposed at the rear of the outer pontoons, and the wake panels may be individually and selectively actuated downward into the water to enhance the wake profile and retracted upward at high speeds.

Abstract: A tubular installation apparatus (1) including a lay tower (2) mounted to a support structure (4). The lay tower (2) is configured to lower a tubular section along a firing line (L) extending along the lay tower (2). A magazine (3) is removably mounted to the lay tower (2) and configured to be pre-loaded with a plurality of tubular sections. A feed mechanism (23, 25) is configured to feed one or more tubular sections from the magazine (3) to the firing line (L) of the lay tower (2) for connection to the end of a catenary.

Abstract: A watercraft safety flag assembly comprising a flexible planar visibility-enhancing element having a forward edge and a rear edge spaced from the forward edge by a width, and a rigid planar stiffening element secured to the flexible planar visibility-enhancing element, where the planar stiffening element substantially spans the width of the flexible planar visibility-enhancing element and is configured to provide maximum stiffening proximate the forward edge, minimal stiffening proximate the rear edge, and decreasing stiffening with increasing distance from the forward edge. There is also provided a header element joined to the forward edge of the flexible planar visibility-enhancing element and which forms a cylindrical sleeve for receiving a mast, where the rigid planar stiffening element extends into the cylindrical sleeve formed by the header element.

Abstract: An inflatable rescue attachment includes at least a U-shaped bladder that is adapted to be secured around the outer perimeter of the head and side portions of a rescue backboard and can be inflated rapidly using an inflation fluid source. A rigid, inflatable backboard includes a central portion with drop stitch material enclosed in an airtight chamber which, when inflated, provides a flat, rigid surface for securing and transporting a rescuee. The inflatable rescue attachment may be used with a rigid, inflatable backboard, as well as with a standard wood, plastic, or fiberglass rescue backboard.

Abstract: An inflator including in combination an inflator body having at one end an input for receiving the neck of a gas cartridge, a manifold assembly intended to be fluidly connected to an inflatable, a combination automatic and manual actuator assembly including a spring-loaded actuator including a pierce pin for fracturing a frangible seal of the gas cartridge, a bobbin with a dissolvable pill that retains the spring-loaded actuator in a cocked position and a hood connected onto the end of the inflator body, said hood including an inwardly-extending tab that engages the actuator to securely retain the hood onto the end of the inflator body by means of the inwardly-extending tab being grasped by the forked end of the actuator.

Abstract: A sponson attachment for an airboat allows the airboat to increase its safety and stability very quickly. A method for attaching a sponson to an airboat hull includes attaching first and second flexible tethers to a side of the sponson. The method also includes removably securing the first flexible tether to an exterior of the airboat hull adjacent a gunnel, and removably securing the second flexible tether below the first flexible tether on the exterior of the hull.

Abstract: A harness system includes a spreader bar having first and second elongate end portions at its respective ends. A curved support member is interconnected to the spreader bar by way of a plurality of straps. The straps include first and second adjustment straps connected to the first elongate end portion and to the curved support member. The first and second adjustment straps are arranged at a non-parallel angle to one another. Fixed straps may be located on a side opposite the adjustment straps. The arrangement and configuration of the spreader bar, curved support member, and adjustment straps provides an improved adjustable harness.

Abstract: A pump assembly includes an electric motor including a rotor having a shaft extending from the electric motor, the shaft including a substantially single unit of material and having an end rotationally couplable to an impeller that when the shaft is rotatably displaced by the electric motor, the impeller displaces a fluid to create a jet of fluid. An enclosure having a cavity arranged between a front surface and a back surface of the enclosure, and the electric motor being arrangeable in the cavity of the enclosure. The enclosure protecting the electric motor arranged in the enclosure from a fluid, and a dielectric fluid is containable in the cavity of the enclosure to immerse the electric motor in the dielectric fluid for preventing corrosion of the electric motor from the fluid.

Abstract: A marine propulsion unit includes a motor driving force transmission shaft, a propeller shaft, and a shaft including one of a switching shaft and a drive shaft, and one of the motor driving force transmission shaft and the shaft includes a hollow member, and the other of the motor driving force transmission shaft and the shaft is disposed inside the hollow member.

Abstract: An outboard motor comprising a first propeller shaft and a second propeller shaft, wherein the second propeller shaft is arranged concentric with the first propeller shaft, and wherein the first propeller shaft is connected to a first power transfer arrangement to rotate the first propeller shaft in a first direction, and wherein the second propeller shaft is connected to a second power transfer arrangement to rotate the second propeller shaft in a second direction opposite to the first direction. The outboard motor comprises a first electric motor having a first motor shaft, and a second electric motor having a second motor shaft, wherein the first motor shaft is connected to the first power transfer arrangement, and wherein the second motor shaft is connected to the second power transfer arrangement. Disclosed is also a method for driving propeller shafts of an outboard motor.

Abstract: An outboard motor includes an engine, an electric motor, a propeller that rotates due to a driving force from the engine and a driving force from the electric motor, and an anti-cavitation plate disposed above the propeller. At least a portion of the electric motor is disposed above the anti-cavitation plate and below a waterline of an outboard motor body.

Abstract: A navigation controller for a watercraft powered by an engine is comprises a grip member with a facing portion, and a reverse portion opposite the facing portion. The grip member is configured and dimensioned to be gripped by a hand of a user in such a manner that when the user is gripping the grip member, (i) the palm of the hand may engage the facing portion of the grip member, (ii) the tips of one or more of the fingers of the hand, other than the thumb, may simultaneously engage the reverse portion of the grip member and (iii) the thumb of the hand is free to perform another action. A control support is secured to the grip member. The control support has a switch support portion. A plurality of control switches are provided for generating control output signals for controlling at least the speed of the watercraft. The control switches are positioned at points on the switch support portion of the control support.

Abstract: A polymer film assembly includes a stack of two or more polymer films. At least one of the polymer films includes directionally oriented molecules. The stack includes a first polymer film and a second polymer film layered with the first polymer film. A contracted bond assembly couples the first and second polymer films of the stack. The contracted bond assembly includes heated and contracted configurations. In the heated configuration the contracted bond assembly includes a bond fusion zone and a film interface having directionally disoriented molecules and an interface width between the bond fusion zone and the remainder of the first and second polymer films. In the contracted configuration the film interface is a contracted film interface having a contracted interface width less than the interface width and a contracted thickness greater than one or more of film thicknesses of the first or second polymer films.

Abstract: An interior panel for an aircraft, an aircraft including an interior panel, and a method for making an interior panel for an aircraft are provided. In one example, the interior panel includes a support substrate that has a substrate surface. A first trim section is coupled to the support substrate. The first trim section has a first exposed surface that extends to a first edge portion. A second trim section is coupled to the support substrate. The second trim section has a second exposed surface that extends to a second edge portion that is disposed adjacent to the first edge portion. The first edge portion is offset from the second edge portion to define a gap. A light source is substantially covered by the first exposed surface and generates light that passes through the gap and illuminates at least a portion of the second exposed surface.

Abstract: An expanding pin system is described that can provide automated and/or power controlled locking and unlocking of an expanding pin assembly in a mechanical joint. For example, the expanding pin system can include an actuation assembly that includes a single actuator (e.g., motor) to control an expanding pin assembly for locking and unlocking a mechanical joint.

Abstract: An airfoil arrangement which allows an increased reliability and increased aerodynamic performance of airfoils. A catching bracket is provided which is mounted in a track device opening to reduce the area of the track device opening and, when there is a failure of at least one support roller, the catching bracket engages the track device.

Abstract: A propeller assembly of an aircraft includes a hub, a plurality of propeller blades extending from the hub and secured thereto and a propeller blade pitch change system located at at least one propeller blade of the plurality of propeller blades. The propeller blade pitch change system includes a pitch change actuator located in the propeller blade, and a drive mechanism operably connected to the pitch change actuator and to the propeller blade to urge rotation of the propeller blade about a propeller blade axis.

Abstract: A system for an aircraft that includes a plurality of zones including: a first fiber optic cable routed through a zone of the plurality of zones. The first fiber optic cable is attached to a landing gear of the aircraft in the zone of the plurality of zones; and a first controller configured to provide a first optical signal to the first fiber optic cable and obtain a first optical response signal from the first fiber optic cable. The first controller is further configured to determine at least one temperature within the zone of the plurality of zones based on the first optical response signal, the first optical signal, and coherent optical frequency domain reflectometry (COFDR).

Abstract: Aircraft wheel and brake assembly, including: a wheel (20) and a brake (21) comprising at least one friction member (31), an actuator bracket (24), and at least one brake actuator (25) held by the actuator bracket; a first measuring device arranged to measure a rotation speed of the wheel (20); a second measuring device arranged to measure a temperature of the friction member (31); a data concentrator (40) arranged to acquire measurement signals produced by the first measuring device and by the second measuring device, and to process and transmit the measurement signals to the outside, the data concentrator (40) being mounted on the actuator bracket (24).

Abstract: A landing gear includes a pair of skids, a cross tube and a stiffening portion. The pair of skids is arranged in parallel with a front-rear axis of an airframe of a rotary wing aircraft. The cross tube is attached to the airframe and coupling the pair of skids to each other. The cross tube includes curved portions located closer to end portions of the cross tube than to portions of the cross tube attached to the airframe. The stiffening portion suppresses flattening of the cross tube and is arranged in at least one of internal spaces of the curved portions or a stiffened portion located between a pair of curved portions. The stiffening portion includes an enlarged diameter portion which increases in diameter by an axial fastening power acting in an axial direction of the cross tube, and a fastening portion configured to generate the axial fastening power.

Abstract: A shock strut is provided that includes a first energy absorption stage or load limiter and a second energy absorption stage or load limiter. The second energy absorption stage or load limiter can include one or more disc springs. The shock strut can be employed on both fixed and retractable landing gear alike, while providing design adjustability for obtaining load-deflection curves that accommodate a range of descent or impact velocities.

Abstract: An unmanned aerial vehicle (UAV) including a fuselage frame and a propulsion system coupled to the fuselage frame. The propulsion system includes a first propulsion device and a second propulsion device. The first propulsion device includes a first rotor blade assembly and a first rotor mount assembly, and the second propulsion device includes a second rotor blade assembly and a second rotor mount assembly. The first rotor mount assembly is configured to not allow the second rotor blade assembly to be assembled to the first rotor mount assembly.

Abstract: An example of a hub for a tail rotor includes a body configured to couple to a mast of a rotor system, a trunnion disposed within the body, first and second shafts disposed on opposite sides of the trunnion, first and second end plates secured to the body, and first and second end bearings, the first end bearing disposed between the first shaft and the first end plate and the second end bearing disposed between the second shaft and the second end plate.

Abstract: A collapsible flying device is provided having a housing including first and second housing sections forming an enclosure, and a motorized assembly that includes a drive motor and a drive shaft driven by the drive motor. The drive shaft matingly receives the first housing section and is coupled to the second housing section, wherein operation of the drive motor drives the drive shaft to move the first housing section from a closed position adjacent the second housing section to an open position spaced from the second housing section. A rotor hub is rotatingly driven by the drive motor. At least two rotor blades are coupled thereto and positioned within the enclosure in a collapsed position when the first housing section is in the closed position, and extend beyond the enclosure in an expanded position when the first housing section is in the open position.

Abstract: A rotary wing aerial vehicle including: first and second rotary wings including fixed pitch propellers. A rotational frequency of the first wing has a lower limit, which is controlled at or above the lower limit while flying. A rotational frequency of the second wing is decreasable to or below a frequency where gyro effect or lift force is lost. Also: a plurality of horizontal rotary wings with fixed pitch propellers; and a controller including: all driving mode wherein the vehicle flies with all horizontal wings; and partial driving mode wherein: a rotational frequency of one or more of the horizontal wings is decreased to or below a frequency where gyro effect or lift force is lost; and the vehicle flies using the other wings. If the rotational frequency of a horizontal wing becomes less than a predetermined threshold in all driving mode, the controller automatically switches to partial driving mode.

Abstract: The present disclosure relates to a vertical takeoff and landing (VTOL) aircraft (100) and a propulsion system (600) thereof. The propulsion system (600) comprises a primary rotor (108) configured to couple to an airframe (102) and oriented to generate a vertical thrust relative to the airframe (102), a drivetrain (626) operably coupled to an engine (602) and configured to mechanically drive the primary rotor (108), and a plurality of tiltable secondary rotor assemblies (114) configured to be disposed about the primary rotor (108). The primary rotor (108) comprises a plurality of collective-only variable-pitch blades. Each of the plurality of tiltable secondary rotor assemblies (114) may have a secondary rotor (116) and an electric motor (608) to drive the secondary rotor (116). An electric generator (606) operably coupled to the engine (602) or to the drivetrain (626) may be configured generate electric power for each electric motor (608) of the plurality of tiltable secondary rotor assemblies (114).

Abstract: A tethered aerial vehicle, connected to an anchorage system in the ground level through a cord, comprising a pair of fixed wings; and a drive assembly. The drive assembly comprises actuators configured to tilt the propeller's axle. The fixed wings define a center hole located close to a gravitational center of the aerial vehicle. Within the edges of the center hole located close to the gravitational center of the aerial vehicle is a gimbal anchored to the fixed wings structure. The drive assembly is located within the edges of the center hole and attached to the gimbal in a manner that the gimbal interfaces the connection between the fixed wings and the drive assembly. The drive assembly consists of coaxial propellers mounted on the same axle driven by a counterrotating motor. The coaxial propellers are configured to rotate in opposite directions with respect to each other.

Abstract: The present invention relates to a fixed wing drone for delivering objects, a takeoff and landing device for a fixed wing drone, a system made up of a drone and a takeoff and landing device, and an approach method for said system. The fixed wing drone comprises wing control surfaces, at least two drive units, at least one tail assembly, at least one structure element which protrudes to the rear and is accessible from the rear, an object holding device, a receiving unit, and a control unit. The takeoff and landing device permits a fixed wing drone to land silently on a vertical structure.

Abstract: An antenna system for an unmanned aerial vehicle (UAV) includes one or more antennas, a reflector, and a control system. The control system is configured to determine a density of antenna towers near the UAV, determine a position for an active antenna of the one or more antennas based on the density, and adjust the active antenna to the determined position. In some embodiments, the antenna system further includes one or more switches, each of the one or more antennas is a different distance from the reflector, and the switches are used to adjust the active antenna to the determined position by selecting a one of the one or more antennas closest to the determined position as the active antenna. In some embodiments, the antenna system further includes an actuator and the active antenna is moved to the determined position using the actuator.

Abstract: Method for inspecting and/or manipulating a beam at a lower side of a roof or deck, the beam including a strip, the method comprising the steps of: providing an unmanned aerial vehicle, UAV, wherein the UAV comprises a body, a number of rotors, a first arm; and an inspection and/or manipulation tool; while the first arm is in the first position, flying the UAV towards the beam; when the UAV contacts the beam, moving the first arm from the first position to the second position such that the end of the first arm is moved to a position vertically above the strip; reduce the propulsion force until the UAV hangs from the beam with the end of the arm in contact with and supported by the strip; and inspecting and/or manipulating the beam, using the inspection and/or manipulation tool, while the UAV hangs from the beam.

Abstract: A multirotor aircraft that includes a chassis, at least three engines that are equipped with propellers, and one or more axial free wings that are connected to the chassis by axial connections. The leading edges of the one or more axial free wings are designed to face constantly same direction when the multirotor flying, and the attack angles of the one or more axial free wings are designed to be changed relatively to the chassis due to flow of air over the one or more axial free wings.

Abstract: A manifold attached to the UAV and a cartridge removably and replaceably attached to the manifold. Inside the cartridge is a removable insert for drawing contents out of the cartridge with a suction tube selectively positioned in fluid communication with a pump for removing chemicals from the cartridge for application by the UAV. The suction tube comprises a plurality of baffles around its circumference for dampening movement of the chemicals in the cartridge while the UAV is in motion.

Abstract: A system for consumer goods management includes at least one sensor and at least one processor. The at least one sensor is configured to identify consumables and provide tracking information corresponding to the consumables. The at least one processor configured to acquire consumption information for a trip to be performed; determine a meal plan based on the consumption information, the meal plan specifying a plurality of types of consumables, quantities of the types of consumables, and a storage arrangement of the types of consumables; and acquire the tracking information from the at least one sensor to implement the meal plan.

Abstract: A table apparatus includes a table device and a table support structure that is connected to the table device. The table support structure includes a carrier structure and a table support linkage. The carrier structure is connected to the table support linkage via a single pivot connection. The table device is pivotable about only the single pivot connection.

Abstract: A headrest for a seat having a backrest frame and a base. The headrest includes a displacement member mountable to the backrest frame to position a lower end of the displacement member in front of the backrest frame and above the base. The displacement member is displaceable relative to the backrest frame to adjust a height of the headrest. A tilt member extends between a pivot end pivotably mounted to the displacement member at a joint, and a head support end disposed above the pivot end to support a rear portion of the head. The joint defines a pivot axis and is positioned in front of the backrest frame and above the base. The tilt member is pivotable about the pivot axis to displace the head support end toward and away from the displacement member.

Abstract: An armrest for a seat may comprise paneling and an easy hook assembly. The easy hook assembly may include a flange and a keyhole protrusion. The flange and the keyhole protrusion may each extending beyond an exterior surface of the paneling. The flange and the keyhole protrusion may allow the armrest to be installed after the paneling is attached.

Abstract: A compressor temperature control system and method for an aircraft air cycle machine is presented. The system prevents overheating of the compressor using a low limit valve positioned between a turbine outlet and a bleed air source. The low limit valve directs the air to an air cycle machine, or bypasses the machine, in regards at least in part to the air temperature measured in the cabin supply duct.

Abstract: An anti-ice system is disclosed, including an airfoil structure having a leading-edge portion facing a wind direction. The airfoil structure includes an outer skin and an inner skin which form a plurality of channels, each channel having an air inlet and an air outlet. An air delivery duct inside the airfoil structure extends transverse to the wind direction and has a plurality of openings directed toward the air inlets of the channels. A heat exchanger is configured to provide hot air to the air delivery duct.

Abstract: A leading edge member, an airfoil and an aircraft using the leading edge member to improve de-icing capacity by recirculating hot bleed air in a spanwise direction and to increase the mass and heat flow within the leading edge member. The hot bleed air is injected via an inlet arrangement into a forward hot air chamber defined by the outer skin of the leading edge member and the front spar. Subsequently, the hot air flow travels through a connecting passage opening from the forward hot air chamber through the front spar into the aft hot air chamber. Subsequently, the hot air flows along the entire spanwise length within the aft hot air chamber and splits into an exhaust flow and a recirculation flow. The recirculation flow passes through a recirculation opening and mixes with new hot bleed air, to take another round trip within the leading edge member.

Abstract: An aircraft safety apparatus removably disposed on at least a portion of an aircraft, the aircraft safety apparatus including a parachute canister, including a main body to store at least one item therein, and at least one parachute disposed within at least a portion of the main body to reduce a rate of descent of the aircraft in response to extraction from the main body, and a rocket canister removably connected to at least a portion of the main body to at least partially fill at least a portion of the main body with a combustible gas, and a gas canister removably connected to at least a portion of the main body to at least partially fill at least a portion of the main body with a non-combustible gas.

Abstract: A method of electrically powering a non-voltage-regulated electricity network, and also to an electrical architecture. The electrical architecture comprises: a plurality of sources of electrical energy including both at least one rechargeable electrical energy storage device and also an electrical power generation advice a main electricity network electrically connected directly to the sources of electrical energy; and pieces of electrical equipment electrically powered by the main electricity network. The method comprises both a first powering step for electrically powering the main electricity network by the rechargeable electrical energy storage device and also a second powering step for electrically powering the main electricity network by the electrical power generation advice, followed by a regulating step for regulating an internal voltage of the electrical power generation advice as a function of the first power delivered by the rechargeable electrical energy storage device.

Abstract: Disclosed are systems, methods, and non-transitory computer-readable medium for automatically capturing and recording anomalies and vehicle operator interaction data. For example, a method may comprise receiving external operational data associated with operation of a vehicle, detecting loading of one or more applications associated with the operation of the vehicle, capturing one or more interactions between an operator of the vehicle and the one or more applications at the vehicle, logging anomalies data associated with the operation of the vehicle, based on any anomaly identified from the received external operational data, the detected loading of the one or more applications, or the captured one or more interactions, recording the received external operational data, the detected loading of the one or more applications, the captured one or more interactions, and/or the logged anomalies data, to generate recorder data, storing the generated recorder data in one or more vehicle data recorder databases.

Abstract: Installation for powering and controlling a plurality of signalling lights (1), arranged in series, each comprising at least one light source (L1,L2), the installation comprising at least:—a unit (100) for remotely programming/managing the operation of the installation, with a primary power supply (110) situated upstream (M);—a primary series circuit (110) for powering the lights, with a transformer (200) for each light (1), the transformers being connected in series with the primary power supply (110);—a control module (300) for each light (1), arranged between a respective transformer (200) and the associated light (1);—a secondary power supply circuit (140) for powering the control modules (300), independent of the primary circuit (110) for powering the lights (1);—a first optical cable (131a) for bidirectionally connecting the first upstream module (300) of the series to the programming/management unit (100);—a second optical cable (132a) for bidirectionally connecting the last downstream control module (

Abstract: The present invention includes an apparatus for preventing aircraft rollover upon a water landing comprising: a deployable first and/or second boom affixed by a first end to the aircraft and capable of deployment substantially perpendicular to a longitudinal axis of the aircraft; and a first and/or second air bladder attached to a second end of the first and/or second boom, wherein the first and/or second air bladders are configured to inflate when an aircraft lands in the water, wherein deployment of the first and second boom and air bladder prevents aircraft rollover upon water landing; or a deployable keel affixed by a first end to the aircraft and capable of deployment substantially perpendicular to a longitudinal axis and opposite a rotor of the aircraft upon a water landing, wherein the keel is sized to prevent aircraft rollover upon deployment; or both.

Abstract: To provide a workload calculation system capable of suppressing the possibility of the cargo handling work not being performed as planned in the work schedule at the arrival airport. A workload calculation system according to the present disclosure includes: an image pick-up unit configured to acquire an image of a cargo loaded aboard an airplane prior to the arrival of the airplane at an arrival airport; a characteristics detection unit configured to detect characteristics of the cargo by recognizing the image of the cargo acquired by the image pick-up unit; and a workload calculation unit configured to calculate a workload required to convey the cargo at the arrival airport by checking the characteristics of the cargo detected by the characteristics detection unit against pre-recorded workload information.

Abstract: Examples for relational time-series classification method for corrosion maintenance dispatch. A method may involve generating a self-organizing map for each parameter that corresponds to a group of aircraft. The self-organizing map organizes time-series data associated with a parameter into a two-dimensional representation. The method may further involve, for each map, identifying polar coordinates that represent a location of a particular node, in a grid of nodes within the self-organizing map, that is located closest to the time-series data organized in the two-dimensional representation. The method may then involve providing polar coordinates identified from each self-organizing map, along with indications of corrosion levels corresponding to the aircraft, as inputs into a classification model to train the classification model to determine trends between the parameters.

Abstract: An interface assembly for connecting an on-board propulsion system to a testing facility includes a support member configured for coupling to a manipulation system and a mounting member configured for coupling to the on-board propulsion system. A plurality of channels extends between and couples the mounting member to the support member.

Abstract: Systems and methods are described herein for mounting a thruster onto a vehicle. A thruster mounting structure may comprise a first, second, and third rotational joint, a boom, and thruster pallet, and a thruster attached to the thruster pallet. The first rotational joint may be attached to the vehicle and configured to rotate in a first axis. The first rotational joint may be connected to the boom and configured to pivot the boom about the first axis. The boom may be connected to the second rotational joint, which is connected to the third rotational joint and configured to rotate the third rotational joint in the first axis. The third rotational joint may be connected to the thruster pallet and configured to pivot the thruster pallet in a second axis that is perpendicular to the first axis.