Abstract: An electrically assisted street scooter includes a handlebar, a deck, front and back wheels, a battery pack integral with the deck, an electrical motor for driving at least one of the wheels, and a drive circuit for controlling electrical supply to the electrical motor from the battery pack. The drive circuit includes a switch for setting the drive circuit in a low power-mode where the electrical motor is not powered when the switch is off, or for setting the drive circuit in a drive mode where the electrical motor can be powered when the switch is on. An auto-power on circuit automatically switches the switch on when a user pushes the street scooter. An auto-power off circuit automatically switches the switch off when the scooter is not used during a predetermined duration. The level of electrical assistance is determined based on the peak value after each leg push.

Abstract: The invention relates to a bicycle (100) having a frame structure (200) that comprises a swingarm structure (225) including a first substantially U-shaped sheet metal part for holding a wheel (103), the frame structure further comprising a frame bridge (219) consisting of a second substantially U-shaped sheet metal part. The first U-shaped sheet metal part is bent substantially in a first bending plane (P) to form a first U-shape, and the second U-shaped sheet metal part is bent in a second bending plane (Q) to form substantially a second U-shape. The first bending plane extends substantially perpendicular to the second bending plane.

Abstract: The present invention discloses a bicycle shaft transmission assembly including a bottom bracket engaged with a crank in a front part and a wheel hub in a rear part, a front main gear mounted on the bottom bracket, a rear main gear mounted on the wheel hub, a transmission shaft eccentrically arranged between the front main gear and the rear main gear. The front main gear is matched with a front end gear, and the rear main gear is matched with a rear end gear. The front main gear is externally provided with a front housing, the transmission shaft is externally provided with a transmission shaft housing, the rear main gear is externally provided with a rear housing, a front end of the transmission shaft housing is engaged with the front housing, a rear end of the transmission shaft housing is engaged with the rear housing.

Abstract: A bicycle operating device includes a base member, a positioning ratchet, a positioning member, a release member and a release pawl. The positioning ratchet pivots about a pivot axis in first and second directions. The positioning member moves between a holding position that prevents pivoting of the positioning ratchet in the first direction, and a releasing position that releases the positioning ratchet to pivot in the first direction. The release member moves the positioning member from the holding position to the releasing position as the release member moves with respect to the base member. The release pawl is movably mounted with respect to the base member to move the release member. The release pawl includes first and second pawl parts that selectively contact the release member as the release pawl moves with respect to the base member. The first and second pawl parts are different from each other.

Abstract: A snow vehicle is disclosed comprising a vehicle frame, a propulsion unit coupled to the frame, and at least one front ski steered by a steering mechanism. The front of the vehicle includes a first front suspension and a second front suspension coupled to the ski. The rear suspension includes a bumper assembly preventing bottoming out of the rear suspension. The rear suspension is coupled to the vehicle frame such that the longitudinal spacing between the vehicle frame and rear suspension is adjustably controllable.

Abstract: A catamaran (100) which has a center tunnel (102), the opposite sides (105a, 105b) of which form asymmetrical pontoons (106a, 106b), which are mirror images of each other, and which pontoons (106a, 106b) have buoyancy, which has been adapted so that when the catamaran (100) moves in water, the center tunnel (102) functions as a combined water and air tunnel. When the catamaran (100) is stationary in water, the ceiling (108) of the center tunnel (102) is in water. The ceiling (108) of the center tunnel further curves in a cylindrically convex manner downwards when going from the bow (116) to the direction of the stern (118) only after an essentially horizontal portion (401) of a distance (d), which essentially horizontal portion (401) is located between the pontoons (106a, 106b).

Abstract: An improved rig is provided for sailing craft, in which two sails are provided in the general shape of tapered tubes encircling each of two adjacent masts arrayed in an A-frame configuration. In the course of a tack, the sails may be swung pendulum-like either towards or away from the bow (one in each direction). The two sails therefore effectively alternate between serving the role of a jib (with sail-area mainly forward of a mast), and the role of a mainsail (with sail-area mainly aft of a mast). The same set of sails on the same masts may also advantageously be deployed for use in high winds, running downwind, heaving-to, and running before a storm.

Abstract: The present invention relates to a pontoon boats that may couple and be driven by a PWC. The invention further relates to pontoon boats having a portion that moves into an open water recess at the rear of the pontoon boat. The invention further relates to an engagement assembly for securing a PWC to such a pontoon boat.

Abstract: A pressure activated time-delayed release device and method. The device includes a body having a drive chamber and a compression chamber disposed therein, a drive piston disposed within the drive chamber of the body, and a compression piston disposed within the compression chamber of the body. A throttle mechanism is disposed between the drive piston and the compression piston. The throttle mechanism controls a release of viscous fluid from the drive chamber into the compression chamber. The drive piston and compression piston are connected so as to cause the compression piston to move substantially simultaneously with the drive piston to compress a compressible element disposed within the compression chamber. The device moves from an un-actuated state to an actuated state when the device is exposed to a predetermined water pressure for a predetermined period of time.

Abstract: A system for launching and recovering a marine or submarine device from a support vessel. The system includes a carriage and at least one protective component. Each protective component is connected to the carriage by a pivot connection of which the axis, when the device is secured to the vessel, is parallel to the surface of the water. The at least one protective component is suitable for raising the marine or submarine device partially out of the water during recovery and for placing the marine or submarine device in the water during a launch, by rotation of the protective component(s) about the carriage.

Abstract: A chocking system, which is both removable and readily adjustable, for providing additional transverse restraint to cargo during transit. The chocking system may be utilized when the size and weight of the cargo requires additional restraints beyond the typical lashing gear, for example, the transportation of barges on a ship.

Abstract: An arrangement, a system and a method relating to a well boat- and service vessel (1) for transporting or storing fish or other aquatic organisms. There are provided, inter alia, a well boat- and service vessel (1) that includes a self-floating, exchangeable well unit (2), a propulsion unit (3), wherein the propulsion unit includes propulsion elements (4), steering and positioning elements, a dock (5) for the well unit, positioning and attachment elements for positioning and securing the well unit (2) in the dock (5).

Abstract: A board carrier uses a belt configured for wearing around a person's waist. A hook bag in the belt has a downwardly facing entry with a closure. Proximal and distal ends of the hook are joined to the belt by length adjustable straps. The board is positioned within the hook with three-points of mutual contact between the board and the interior of the hook. The hook may have a spring clamp for securing a paddle. When not in use the hook and straps are placed within the hook bag.

Abstract: According to one or more embodiments disclosed herein is a method of transporting equipment between sea-surface and seafloor by providing a structure with a subsea equipment package mounted thereon. The structure is used for installation and recovery in a subsea environment by changing the buoyancy of the structure or ballasting the structure to effect a controlled sinking motion.

Abstract: A recovery device can include a bladder, a canister, an opening mechanism, and a tether. The bladder can be disposable in an inflated configuration and an un-inflated configuration. The canister can contain a compressed fluid and be coupled with the bladder. The opening mechanism can be configured to selectively open the canister and direct the compressed fluid into the bladder. The tether can extend between a first end coupled to the bladder and a second end engageable with a vehicle. The bladder in the inflated configuration can define a volume of less than one-tenth of a cubic meter.

Abstract: A thruster assembly that in addition to propulsion provides water flow to/from compartments and systems on board a vessel. In a first position, the thruster assembly provides propulsion/steering. Pivoted to a second position, operation of the thruster in a first direction draws a flow into the vessel and in a second direction draws a flow out of the vessel. The flows may be conveyed to/from compartments/systems on board the vessel via conduits in communication with a chamber having an opening through which the thruster drives the flows. The flows may be used to submerge/surface the vessel, or to provide systems cooling or serve other functions. Pivoted to a third position the thruster assembly is retracted and enclosed within the chamber to form a hydrodynamically clean exterior.

Abstract: The present disclosure is directed to a gear system/reversing gearbox that allows reversing the direction of pivotal rotation between first and second shafts (i.e., about a pivot axis transverse to long axis of the shafts) while also translating at least some axial rotation between the shafts. In one exemplary application, the gear system is utilized in forward rowing system that allows a rowing motion substantially identical to a rearward rowing system.

Abstract: A marine drive for propelling a marine vessel includes a lower gearcase, a propeller shaft laterally extending through the lower gearcase and configured to support a propeller, a propeller shaft bearing hub supporting the propeller shaft in the lower gearcase, and an exhaust passage that conveys exhaust gas through the lower gearcase to an underwater discharge outlet. The exhaust passage includes a first leg that conveys the exhaust gas downwardly in the lower gearcase and a second leg that redirects the exhaust gas laterally from the first leg to the underwater discharge outlet. The propeller shaft bearing hub comprises curved vanes that laterally redirects the exhaust gas from the first leg towards the underwater discharge outlet.

Abstract: An engine control device includes an obtaining unit, a determining unit, and a control unit. The obtaining unit obtains model information on an engine based on a signal from a sensor, the sensor detecting a rotation of a camshaft unit. The determining unit determines whether the model information obtained by the obtaining unit matches stored model information. The control unit gives a warning to a user when the determining unit determines that the model information is not matched and controls the engine corresponding to the stored model information when the determining unit determines the model information is matched.

Abstract: A method for steering a marine vessel powered by a marine engine and having a steerable marine device includes initiating a docking mode, and in response to initiation of the docking mode, reducing a steering ratio between input signals corresponding to steered positions of a steering wheel and output signals corresponding to desired steering angles of the marine device, such that the steering ratio is less than the steering ratio would otherwise be were the vessel in a non-docking mode. Input signals are accepted from the steering wheel, and output signals are generated based on the input signals and the reduced steering ratio. The output signals are sent to a steering actuator coupled to the marine device, which controls a position of the marine device to the desired steering angles.

Abstract: A process for manufacturing an integrated shell element including: providing a shell element lay-up tool with an upper tool surface; laying-up a resin impregnated fibers on the upper tool surface to form the shell element; providing on the resin impregnated fibers a stiffener element layup tool having surfaces to support a stiffener element structure; laying-up resin impregnated fibers on the stiffener element lay-up tool to form the stiffener element; curing in a single step the resin impregnated fibers such that the fibers forming the shell element and the fibers forming the stiffener element are laminated into an integrated shell element having a longitudinal or transversal stiffener element; and separating the integrated shell element from the shell element and stiffener element lay-up tools.

Abstract: A signal-initiation device for initiating control signals in an aircraft fuselage, an aircraft fuselage including a signal-initiation device of such a type, an aircraft including such a fuselage, and the use of a signal-initiation device of such a type. The signal-initiation device for initiating control signals in an aircraft fuselage comprises a switching area configured to generate at least one control signal for controlling at least one orifice shutter present in the aircraft fuselage; and an initiating component connected to the switching area, configured to introduce the at least one control signal into the aircraft fuselage.

Abstract: A fillable stowage container for placement in a cargo hold area of an aircraft is provided. The stowage container comprises a housing structure, a first stowage segment accommodated in the housing structure, and an access opening for manually loading and unloading of the first stowage segment. The housing structure comprises an outer contour, which is configured to place the stowage container in a cargo area of an aircraft. The housing structure is accessible via the access opening from a cabin area above the cargo area, in which the stowage container can be placed. A second stowage segment is arranged within the housing structure and an access opening is provided for manual loading and unloading of the second stowage segment. Further, the first or the second stowage segment is designed as a waste container for placement of trash and the other stowage segment is designed as stowage compartment.

Abstract: A rotary wing aircraft includes a fuselage having a plurality of surfaces, at least one engine mounted in the fuselage, and a rotor assembly including a rotor shaft and plurality of rotor blades operatively connected to the rotor shaft. The rotor assembly includes a plurality of surface portions. A rotor shaft fairing extends between the fuselage and the rotor assembly and about at least a portion of the rotor shaft. The rotor shaft fairing includes an outer surface. A plate member is mounted to and projects proudly of the at least a portion of the rotor shaft fairing. The plate member is configured and disposed to increase an aspect ratio of and reduce induced drag on the rotor shaft fairing as well as reduce rotor hub wake size.

Abstract: In order to reduce the risks of movable nacelle cowlings opening, the invention provides a nacelle for an aircraft engine assembly comprising a fixed nacelle structure as well as at least one jointed movable cowling on the fixed structure, the cowling being jointed at its front end on the fixed structure so that, upon closing the movable cowling, a rear end of this cowling moves towards the rear and radially towards the inside.

Abstract: Aerial vehicles may be operated with discrete sets of propellers, which may be selected for a specific purpose or on a specific basis. The discrete sets of propellers may be operated separately or in tandem with one another, and at varying power levels. For example, a set of propellers may be selected to optimize the thrust, lift, maneuverability or efficiency of an aerial vehicle based on a position or other operational characteristic of the aerial vehicle, or an environmental condition encountered by the aerial vehicle. At least one of the propellers may be statically or dynamically imbalanced, such that the propeller emits a predetermined sound during operation. A balanced propeller may be specifically modified to cause the aerial vehicle to emit the predetermined sound by changing one or more parameters of the balanced propeller and causing the balanced propeller to be statically or dynamically imbalanced.

Abstract: A high stiffness hub assembly for a proprotor system operable to rotate with a mast of a tiltrotor aircraft having helicopter and airplane flight modes. The hub assembly includes a yoke and a constant velocity joint assembly. The yoke has four blade arms each adapted to hold a proprotor blade. The constant velocity joint assembly provides a torque path from the mast to the yoke that includes a trunnion assembly, four drive links and four pillow blocks. The trunnion assembly is coupled to the mast and has four outwardly extending trunnions. Each drive link has a leading bearing coupled to one of the trunnions and a trailing bearing coupled to one of the pillow blocks. Each pillow block is independently mounted between an upper surface of the yoke and a hub plate with two connection members that extend through the yoke and the pillow block.

Abstract: Multiple propeller blades may be joined by tip connectors to form a closed propeller apparatus. The tip connectors may create continuous structure between adjacent tips of a first propeller and a second propeller. Use of the tip connectors may reduce vortices created near the tips of the propeller blades, which cause drag and slow the rotation of the propeller blades. The tip connectors may also reduce noise caused by rotation of propeller blades. Further, the tip connectors reduce or eliminate deflection of the propeller blades by creating a support structure to counteract forces that would otherwise cause deflection of the propeller blades, thereby improving propeller blade loading. In some embodiments, the tip connectors may be formed of a malleable material and/or include one or more joints that enable at least one of the propellers to modify a pitch of blades of the propeller.

Abstract: A wing tip designed for attachment to a winglet of an aircraft, the winglet coupled to a wing of the aircraft and having a leading edge and a trailing edge continuously transitioning from a leading edge and trailing edge of the wing. The wing tip may include a curved leading edge from the winglet leading edge to a leading end point, a curved trailing edge from a winglet trailing edge to a trailing end point, and an end segment connecting the leading end point and the trailing end point. The end segment may be swept back from the trailing end point to the leading end point at an end segment angle.

Abstract: Aircraft landing gear strut (1) comprising a main part (1a) extending along a main axis (X-X) of the strut and comprising an axle shaft (1b) extending in a plane (P) perpendicular to the main shaft (1a) of the strut, this axle shaft (1b) being designed to support at least one landing gear when (2a, 2b) equipped with brakes (3a, 3b) for braking the wheel, said axle shaft (1b) being made of steel. The axle shaft (1b) bears at least one layer of zinc-nickel alloy coating (C), this zinc-nickel alloy comprising, as a mass percent of the alloy, between 12% and 18% or nickel, at most 0.5% of elements other than nickel and zinc, the rest being zinc.

Abstract: The present invention includes a damper assembly, method and kit to provide dampening to an airframe comprising: a mass to dampen the vibration of the airframe; one or more wire rope isolators having a first and a second portion, wherein the mass is attached to the one or more wire rope isolators and the mass is isolated from the airframe by the one or more wire rope isolators; and a first fastener and a second fastener, wherein the first fasteners attaches to the first portion of the wire rope isolator to the mass, and the second fastener attaches the second portion of the wire rope isolator to the airframe to dampen vibration of the airframe.

Abstract: A supersonic aircraft having unique structural, geometrical, electromagnetic, mechanical, thermal and aerodynamic configuration is described. Its design characteristics maximize aerodynamic performance, speed, efficiency, comfort and range in the operational affect of carrying passengers over long distances at very high flight speeds and Mach numbers, generally above Mach 4.0+. It has fully integrated-mated fuselage twin engine nacelle structures which reduce and stabilize wave drag, wherein engines sit forward of the sonic boom electrode swept aerospace but are integrated right through the sub-wing, the aero-spike and inlet just above the top surface of the central wing, and above and the major wing mating join, attached via a massive composite titanium keel structure, through the central wing box and fuselage.

Abstract: A heavy payload, autonomous UAV able to deliver supply by way of airdrop with more precision and at a lower cost. The UAV can be equipped with a movable wing system. The UAV can include a removable storage box. The UAV can be equipped with a drogue parachute for deploying the wings upon jettison of the UAV from a mothership. The UAV can be controlled remotely or it can operate autonomously. The UAV can include canard wings. The canard wings and the movable wings can include ailerons to effectuate flight control of the UAV. The UAV can be reusable or can be an expandable UAV. The UAV's wings can be configured to automatically separate from the UAV during the landing sequence.

Abstract: An aerial seeding system that may be installed in an aircraft in a modular form with minimal modification to the existing aircraft configuration, and, in particular, without any structural modifications that would adversely impact the integrity of the aircraft structure or its overall air worthiness. Exemplary embodiments include an active and controllable seed distribution mechanism to ensure continuously controllable and even distribution of seeds. Basic system components include a modular seed hopper, a seed broadcasting head and a hydraulic system driven by a pump connected to an aircraft accessory drive.

Abstract: Described herein are methods and systems for picking up, transporting, and lowering a payload coupled to a tether of a winch system arranged on an unmanned aerial vehicle (UAV). For example, the winch system may include a motor for winding and unwinding the tether from a spool, and the UAV's control system may operate the motor to lower the tether toward the ground so a payload may be attached to the tether. The control system may monitor an electric current supplied to the motor to determine whether the payload has been attached to the tether. In another example, when lowering a payload, the control system may monitor the motor current to determine that the payload has reached the ground and responsively operate the motor to detach the payload from the tether. The control system may then monitor the motor current to determine whether the payload has detached from the tether.

Abstract: A method of providing an audio signal containing flight-related information to passengers on board the aircraft, a computer program product for carrying out such a method, an apparatus for providing an audio signal containing flight-related information to passengers on board an aircraft, and an aircraft comprising such an apparatus. A method embodiment comprises receiving a trigger to provide the audio signal, obtaining one or more predefined data fragments, obtaining flight-related information corresponding to a current flight of the aircraft, generating the audio signal based on the one or more predefined data fragments and the flight-related information, and providing the audio signal to one or more of the passengers on board the aircraft.

Abstract: A modular aircraft closet including a structural frame having a top, a bottom, an inboard sidewall, an outboard sidewall, an open forward face and an open aft face. A forward panel attaches to the structural frame to cover the open forward face and an aft panel attaches to the structural frame to cover the open aft face. The forward and aft panels can be equipped with an exterior panel feature to customize, brand, reconfigure or retrofit the closet.

Abstract: An aircraft passenger seat (100) is fixed to a floor via a seat track fitting (110), and a reclining assembly of the seat is supported by pipes (130, 132) passed through left and right legs (120) and spreaders (170). A linear actuator (300) operates a reclining motion. A curved arm for deformation is provided to a mount (320) on which the actuator (300) is mounted, and a slit (145) is provided in a link plate (140) to which a rod is connected, and in a state where a forward force F is applied, the curved arm deforms and absorbs the impact. An impact absorbing structure is also provided to the legs (120).

Abstract: The present invention relates to an aircraft seat having a seat base, a seat unit, and a floor attachment assembly, where a first side of the seat base is configured to be fastened to the seat unit, and a second side of the seat base is configured to be fastened to the floor attachment assembly, and the floor attachment assembly is configured to be mechanically connected to a floor structure of an aircraft in order to fasten the aircraft seat to the aircraft, where the seat base is formed by at least one flexurally rigid shell component, where the shell component has a cavity for receiving at least one functional element, with the cavity being closed.

Abstract: Disclosed is a seat intended in particular for a passenger transport vehicle, the seat including a seating part, a backrest that pivots relative to the seating part, a headrest, and an active noise control device including: at least one error sensor capable of sensing a minimization acoustic field and generating a reference signal; a reference sensor able to capture an undesirable acoustic field; a processing unit able to generate a cancellation signal from the reference signal and from a signal representative of the undesirable acoustic field; and at least one speaker able to emit a cancellation acoustic field from the cancellation signal. The headrest includes a support and a first deformable casing carried by the support. The at least one error sensor is arranged on the first deformable casing.

Abstract: A passenger seat module, a tray table deployable from within the module, and a drawer deployable from within the tray table. The tray table drawer is accessible regardless of the stowed or deployed position of the tray table to provide a stowage solution independent of tray table deployment. A module adapted to be positioned in proximity to a passenger seat and including a tray table coupled to the module through a support arm, the tray table movable between a stowed position within the module and a deployed position outside of the module.

Abstract: An aircraft air supply system may include a primary duct to supply a primary air flow to a flight deck of an aircraft. A nitrogen generating system may be configured for generating nitrogen enriched air and oxygen enriched air. A secondary duct may be provided for channeling the oxygen enriched air from the nitrogen generating system to the primary duct. The flow of the oxygen enriched air into the primary duct and to the flight deck may be controlled to reduce an effective altitude of the flight deck.

Abstract: An air conditioning system for an aircraft is provided. The air conditioning system includes a first rotating component and a second rotating component. The first rotating component includes a compressor and a turbine. The compressor pressurizes a first medium. The first turbine receives a mixture of a second medium and a pressurized form of the first medium. The second rotating component includes a fan.

Abstract: An ice-protection system has first and second zones of a leading edge of an aerodynamic or streamlined aerodynamic component, each zone having a de-icing apparatus and an ice-detection sensor positioned behind an elongated convex window as to be aero-conformal with the leading edge. The ice-detection sensor is in the form of a module and has a sensor head having a front face and abutments at ends of the window. The ice-detection sensors may have a central light emitter and a plurality of sensor elements peripheral to the light emitter. The ice-protection system also has a control system responsive to the ice-detection sensors to control the respective de-icing apparatus, and may activate automatically a sequence of operation.

Abstract: In some embodiment, an aircraft includes a flying frame having an airframe, a distributed propulsion system attached to the airframe, the distributed propulsion system including a plurality of propulsion assemblies and a flight control system operably associated with the distributed propulsion system. The flying frame has a vertical takeoff and landing mode and a forward flight mode. The flight control system is operable to independently control the propulsion assemblies. The flight control system is also operable to detect faults in individual propulsion assemblies and to perform corrective action responsive to detected faults at a distributed propulsion system level.

Abstract: There is provided a method and a system for controlling an inlet door of an auxiliary power unit provided on an aircraft. Input data indicative of whether the aircraft is on ground or airborne is received. If the aircraft is on ground, a first control signal comprising instructions to command the inlet door to a fully open position is output. If the aircraft is airborne, a second control signal comprising instructions to command the inlet door to a partially open position. When a current value of a rotational speed of the auxiliary power unit reaches a predetermined threshold indicative of an end of a start sequence of the auxiliary power unit, a third control signal comprising instructions to transition the inlet door from the partially open position to the fully open position is output.

Abstract: The general field of the invention is that of the methods for three-dimensional graphic representation of at least one landing runway on a display device of an onboard display system for aircraft, said graphic representation being displayed in a synthetic of an outside landscape, said runway comprising a coloured rectangular form, an outline surrounding said form and markings the position of the aircraft in relation to said runway being known in a horizontal plane with a first accuracy and in a vertical axis with a second accuracy. When the first accuracy is above a first threshold and/or when the second accuracy is above a second threshold, the appearance of the rectangular form or of the outline or of at least one marking is modified.

Abstract: A monitoring system is disclosed for use with a mobile platform being operated by an operator. The system may make use of a database for containing operational information and procedures relating to the operation of the mobile platform by the operator. A processor may also be used that communicates with the database and with at least one subsystem of the mobile platform for monitoring operational information concerning operation of the mobile platform against stored information contained in the database. The processor may determine if the operation of the mobile platform is proceeding in accordance with predetermined standards.

Abstract: Apparatuses and methods are described for use of an ultraviolet (UV) light source, such as in a cleaning device, in which ozone creation due to reaction of the UV light with oxygen in the air is reduced. An example method includes dispersing, by a gas outlet, oxygen-depleted gas over a UV light source, and directing UV light from the UV light source to pass through the oxygen-depleted gas onto an area. An example apparatus includes a UV light source to direct UV light onto an area, and a gas outlet to disperse oxygen-depleted gas over the UV light source, such that the UV light passes through the oxygen-depleted gas onto the area.

Abstract: A portable launch rig (PLR) may include a support structure including two side supports defining an interior space for lifting and filling a balloon envelope of a balloon. Wheels on each of the side supports enable the PLR to be moved in various directions in order to prepare the PLR for launching the balloon. The side supports are connected by a lateral support beam having a pair of cranes arranged thereon. Each crane has an arm arranged over the interior space that is connected to a spreader beam. The spreader beam includes a lift assembly configured to lift and inflate the balloon envelope within the interior space. The PLR includes a platform and perch for supporting and moving the balloon envelope. A door assembly of the PLR includes a plurality of hangar doors configured to block wind from a respective direction of each hangar door entering the interior space.