Abstract: A swing arm includes a tubular arm main body and an axle support member configured to support an axle of a rear wheel, wherein a fixing surface for fastening and fixing the axle support member in the arm main body together with the axle is provided at an inner side-surface of the arm main body in a vehicle width direction, and an opening for inserting the axle support member is provided at an outer side-surface of the arm main body in the vehicle width direction.

Abstract: A transmission for a system, in which a directed force is introduced eccentrically with respect to a main shaft of the transmission, comprising the main shaft which is rotatably mounted in relation to a stationary housing by a main shaft bearing, a sun gear which is fixedly connected to the housing being arranged concentrically around the main shaft, and at least one control housing that rotates around the housing, wherein the first section thereof acts on the main shaft in a rotationally fixed manner and a planetary wheel is rotatably mounted by a first rotary bearing on the second section thereof, said planetary gear meshing with the sun gear. According to the invention, a force transmission means is fastened to the control housing and a drive crank rigidly engages the first end on the planetary wheel, wherein a second end of the drive crank is mounted in an articulated manner on a crank arm, said crank arm being supported in relation to the control housing by a movable coupling means.

Abstract: A bicycle gearshift comprising first and second moveable bodies, a rocker arm rotatably connected to the second body on a rotation axis, an elastic element that rotates the rocker arm about the rotation axis, and a unidirectional damping device operatively arranged between the rocker arm and the second body. The unidirectional damping device comprises a first ring nut arranged coaxially to the rotation axis and rotatable with the rocker arm and a second coaxially arranged positioned axially adjacent to the first ring nut. The first and second ring nuts have matching saw-toothings. An actuator for the unidirectional damping device acts on one of said ring nuts to axially push that ring nut towards the other ring nut so as to mutually engage the saw-toothings when the rocker arm is moved about the rotation axis in a second direction of rotation.

Abstract: Contemplated herein is an adjustable positive restraint docking system, the system having a latching assembly, the latching assembly being configured to be affixed to a docking point on a dock so as to act as a mooring point for a watercraft to said docking point. The latching assembly can also include a latching head assembly, the latching head assembly wherein in the embodiments shown the latching head assembly can also be provided with a receiving channel having an open portion being configured to receive a secondary locking component provided about the watercraft. A linkage assembly can be provided which within or about the channel, which can selectively block or open the open portion of the receiving channel. In some embodiments, the linkage assembly can be configured to pass through a toggle point between an open state and a locked state.

Abstract: The present invention is related to a gravitation anchor for offshore anchoring of ships and platforms, comprising a main body (10) with a longitudinal axis of revolution (11), comprising a means of stabilization (14), whereby the means of stabilization (14) comprises a means of automatic activation (140). Optionally, the means of stabilization comprises at least one stabilizer (14), whereby each stabilizer (14) comprises an end pivotally attached (141) to the gravitation anchor (1), and a free end, whereby when the stabilizer (14) is in a retracted position, the free end is positioned closer to the main body (10) of the gravitation anchor (1), and whereby when the stabilizer (14) is in an extended position, the free end is positioned away from the main body (10) of the gravitation anchor (1).

Abstract: An observation platform device, including a platform deck, an observation mechanism disposed on the platform deck, a primary swing reduction and self-righting mechanism, and a secondary swing reduction mechanism. The primary swing reduction and self-righting mechanism includes a hollow upper support rod, a solid lower support rod, a buoyant cabin, and a counter weight cabin. The lower support rod includes a lower end fixedly connected to the counter weight cabin, and an upper end fixedly connected to the buoyant cabin. The secondary swing reduction mechanism includes a water pond, a plurality of wing-type supports, and a plurality of spaced fan-shaped floating cabins. The plurality of wing-type supports each includes an upper end fixedly connected to a lower plane of the platform deck, and a lower end fixedly connected to an upper plane of the fan-shaped floating cabins.

Abstract: A multi-position user-support device for a stand-up paddle board includes a base configured to mount on a stand-up paddle board, and a support post with a pad connected thereto to support a user's weight while leaning or sitting thereon. The support post is rotatably mounted to the base, with a spring component configured to maintain a return force on the support post when rotated toward a rear of the stand-up paddle board in a stored position. A spring-activated latch retains the post in the stored position until released by the paddler. The post may include a telescopic portion to adjust its length. The device may also include a seat attachment.

Abstract: The present disclosure relates to an unmanned floating production unit (300) and method of installing a floating production unit comprising a deck structure (301) for mounting equipment for processing hydrocarbons, and a hull structure (302) formed from a first section (303) and a second section (306), wherein the second section (306) is wider than the first section (303). The floating production unit (300) according to the present disclosure can provide a compact unit, which has dimensions which can lead to a heave natural period outside an area of significant wave energy, and as a result, it has substantially reduced and improved hydrodynamic responses. The floating production unit is configured to be small and lightweight, and can be fabricated, launched and towed to the installation site in two parts, without the requirement for heavy lifting or construction machinery, thus lowering manufacturing costs.

Abstract: There is provided a storage system for storing and retrieving watercraft or other items to or from a storage position in a storage area as part of an enclosure having a plurality of storage areas. The storage system may include at least one carrier to support the item during movement to or from a storage position, and a positioning system to move the carrier system. An elevator system is usable to move the positioning system and carrier system to and from a storage area, and a control system is usable to control the positioning system to move the carrier system and item into and out of its storage position.

Abstract: A connection system, in particular for a pressure reducer of a diving regulator, the system comprising a connector (1) having a first end (2) adapted to be fastened to a pressure reducer and a second end (2?) adapted to be fastened to a valve of a compressed air cylinder, said connector (1) having an internal passage (4) extending substantially axially between said first and second ends, said internal passage (4) including a filter (5), preferably made of sintered stainless steel, and a retaining member (6a; 6b; 6c; 6c?; 6d; 6e) fastened to said second end (2?) and supporting firstly said filter (5) and secondly a main O-ring (7; 9e), said retaining member (6a; 6b; 6c; 6c?; 6d; 6e) forming an inlet opening, said system including a shutter device comprising a shutter member (9a; 9b; 9c: 9c?; 9d; 9e) that is deformable and/or movable between a shut position in which it shuts said inlet opening, and an open position in which it does not shut said inlet opening, said shutter member (9a; 9b; 9c: 9c?; 9d; 9e) being

Abstract: Autonomous underwater vehicles are described that are stackable with other like autonomous underwater vehicles on a suitable launch platform, such as within a vertical missile launch tube of a submarine, waiting to be deployed into the water. The underwater vehicles can be deployed or launched individually, in groups, or all together into the water. While stacked together, the stacked autonomous underwater vehicles can connect to one another or to external structure of the launch platform. In addition, the underwater vehicles can be positively buoyant or can be made to have controllable buoyancy to allow the underwater vehicles to float up and out of the launch platform during deployment without an external deployment force.

Abstract: A propellable aquatic board includes a main body that is at least partially buoyant. The propellable aquatic board also includes a flexible member secured to the main body by a fastener. The flexible member extends away from the main body in a longitudinal direction. The flexible member is configured to selectively deflect to propel the aquatic board through water.

Abstract: A process of printing an image or images on the sails of a watercraft or other wind powered vessel without altering or compromising the efficacy of the sails is described. The process employs a method of printing large-scale, single or multiple panel, continuous, high-resolution photographic and graphic images on sails. The dynamics and curvatures of a sail are integrated into manufacturing process when employed for sails, though the process may be applied to any large-scaled fabric print. The process of the present invention produces printed sails providing for the highest resolution photographic, art, and graphic printing with virtually no weight gain, nor effect on the sail's original performance. Modern equipment is employed to achieve printing of realistic, high quality images directly on to the fabric of sails without compromising flexibility or durability, as well as without infringing on the speed and agility of the sailing craft.

Abstract: A universal mounting bracket for outboard marine equipment is provided. The universal mounting bracket includes a first member mounted to one end of an arm, and a second member mounted to the other end of the arm. The first and second members mate with the arm to define respective first and second adjustment axes. The arm is adjustable relative to the first member about the first axis. The second member is adjustable relative to the arm about the second axis. Adjustment about the first and second axes allows a user to govern the distance of marine equipment mounted to the second coupling relative to a watercraft.

Abstract: A power steering system for a watercraft includes an electromechanical rotary actuator mounted within a cylindrical housing. The electromechanical rotary actuator includes a motor and a gearing system. The housing, along with a stern bracket and an output flange, are sized and arranged to permit steering movements and trim/tilt movements of an outboard motor. The power steering system may include one or more of a redundant linear actuator, a trim/tilt mechanism, and a control system.

Abstract: A method of operating a steer-by-wire steering system on a marine vessel includes receiving an initial component position of a steerable component and receiving an initial wheel position of a manually rotatable steering wheel with respect to a zero position. An initial normalized steering value is then calculated based on the initial component position, and the initial normalized steering value is correlated to the initial wheel position. The correlation between a subsequently received wheel position and a subsequently calculated normalized steering value is then adjusted by a recovery gain until the steering wheel reaches an aligned position with the steerable component.

Abstract: A system for elevation control. The system comprises a substantially gastight envelope containing lifting gas wherein the envelope further comprises a plurality of envelope segments in fluid communication with one another. At least one tension cable connects at least two of the envelope segments. A control device including a motor adjusts the length of the tension cable to change the pressure within the envelope to thereby facilitate ascent and descent of the system. The control device causes the system to operate in ascent, descent, or vertically stationary modes.

Abstract: An external part of an aircraft (such as a fairing) comprising a skin made with flexible materials attached to rigid supporting elements (such as longerons and frames) arranged in, at least, two directions. The skin comprises inner inflatable panels in all bays delimited by the rigid supporting elements and/or an external inflatable panel. The skin is joined to the supporting elements so that its external surface complies with aerodynamic requirements.

Abstract: A stretchable mesh material extends across the opening of a cavity of the landing gear of an aircraft when the landing gear is in the deployed position. The mesh material alters the flow of air across the opening of the landing gear cavity and significantly reduces the amount of noise produced by the wheel well at low-to-mid frequencies.

Abstract: A rib structure for use in an aircraft is provided. The rib structure includes a web portion, a plurality of hat stiffener portions coupled to the web portion, and at least one chord portion coupled to the web portion. The plurality of hat stiffener portions extend substantially parallel, and the at least one chord portion extends substantially perpendicularly relative to the plurality of hat stiffener portions. Moreover, the web portion, the plurality of hat stiffener portions, and the at least one chord portion are fabricated from composite material, and include features such that the rib structure has a buckling ratio of at least about 4.

Abstract: A wing pivot apparatus for rotating a wing between a flight orientation and a stowed orientation relative to a fuselage of a tiltrotor aircraft. The apparatus includes a stow ring that is rotatably mounted to the fuselage. Forward and aft wing attach assemblies are coupled respectively to forward and aft spars of the wing and are coupled to the stow ring. Forward and aft connecting assemblies are coupled respectively between the forward and aft wing attach assemblies and the stow ring and are selectively securable respectively to first and second fore-aft beams of the fuselage. A plurality of lock assemblies selectively secures the connecting assemblies to the fore-aft beams of the fuselage when the wing is in the flight orientation. An actuator coupled to the fuselage is operable to reversibly rotate the wing between the flight orientation and the stowed orientation.

Abstract: An aircraft wing is disclosed having a wing tip device configurable between a flight configuration for use during flight and a ground configuration for use during ground-based operations to reduce the span. The wing includes an actuator and an actuation assembly having an articulation mechanism having a master bell crank connected to the actuator and a slave link connecting the master bell crank with the wing tip device. The slave link is pivoted, at one end, to the master bell crank about a first pivot, and at the other end, to the wing tip device about a second pivot. The master bell crank being pivotably mounted, at its base, about a third pivot.

Abstract: Two element aerofoils are provided, having an aerofoil chord, a primary element having a first leading edge and a first trailing edge, a secondary element having a second leading edge and a second trailing edge, a gap between the primary element and the secondary element, and an axial overlap between the first trailing edge and the second leading edge. The secondary element is deflectable with respect to the primary element about a fixed hinge point by a flap deflection angle. The secondary element is configured to operate in airbrake mode when deflected by a respective the flap deflection angle corresponding to a design airbrake deflection angle wherein to generate an airbrake drag. In at least some examples, the axial overlap is numerically greater than ?0.5% of the aerofoil chord, at least for the design airbrake deflection angle. Also disclosed are methods for operating air vehicles, and methods for designing two-element aerofoils.

Abstract: An adjustable and rotary rudder bar for a rotary wing aircraft. The rudder bar comprises a pedal bar, a main body, two pedals connected to the pedal bar on either side of the main body, a slider device enabling the pedal bar to slide relative to the main body, a structure fastened to a floor of the aircraft, and a shaft having a first axis (A1). The shaft is secured to the main body, and the main body is movable in turning relative to the structure about the first axis (A1) thus causing the main body, the pedal bar, and the pedals to turn simultaneously.

Abstract: A hydraulic system of an aircraft may include a system pump configured to provide hydraulic fluid to the hydraulic system at a first working pressure. The hydraulic system may further include a booster pump configured to supply hydraulic fluid to at least one boostable actuator at a second working pressure higher than the first working pressure. The boostable actuator may be operatively coupled to and configured to actuate at least one flight control surface of an aircraft.

Abstract: An aircraft landing gear assembly having a main strut configured to move between a deployed condition and a stowed condition, a damping device to oppose movement of the main strut as it approaches the deployed condition, a retraction actuator and a mechanical retraction linkage coupled between the aircraft and the main strut, and a locking device. The locking device is operable to change the retraction linkage between a locking condition in which the retraction actuator can apply a stowing force to the main strut through the retraction linkage to move the main strut from the deployed condition to the stowed condition, and an extensible condition in which the retraction linkage permits the main strut to be deployed by way of gravity.

Abstract: A method for accelerated power push back of an aircraft equipped with a pilot-controlled engines-off taxi system that drives the aircraft without reliance on the aircraft's main engines or tugs is provided. An aircraft is quickly and efficiently moved out of a gate where it is positioned in a nose-in orientation. The pilot controls the taxi system to drive the aircraft in reverse along a perpendicular path away from the terminal to a location where there is sufficient space for the aircraft to stop and turn, and the aircraft is turned and driven in a forward direction to a takeoff runway. Pilot reliance on ground personnel guidance during push back maneuvers is minimized by providing a monitoring system designed to monitor gate and ramp areas around the aircraft in any visibility or environmental conditions and provide feedback to the pilot.

Abstract: A drive system for rotating a wheel of an aircraft landing gear is disclosed including a motor operable to rotate a drive pinion via a drive path; and a driven gear adapted to be attached to the wheel so as to be capable of rotating the wheel. The drive system has a drive configuration in which the drive pinion is capable of meshing with the driven gear to permit the motor to drive the driven gear via the drive path. The drive path includes a first compensating gear mounted on a common drive shaft with the drive pinion so as to be capable of rotating in tandem with the drive pinion, and a second compensating gear which is meshed with the first compensating gear. One of the drive pinion and the driven gear includes a roller gear having a series of rollers arranged to form a ring, each roller being rotatable about a roller axis, and the other of the dive pinion and the driven gear comprises a sprocket.

Abstract: An aircraft undercarriage leg having an orientation control for wheels that causes a sliding rod to pivot. The orientation control has a rotating member mounted on the strut assembly having a toothed sector forming a pinion and is rotationally coupled to the sliding rod, and a rack mounted to slide on the strut assembly along a sliding axis perpendicular to the pivot axis to mesh with the pinion, the rack being moved by drive means. The drive include a rotary drive inside the rack adapted to turn about the sliding axis and to cooperate via a helicoidal coupling with the rack, The rotary drive is immobilized axially by two opposite axial thrust bearings allowing angular tilting of the rotary drive. The thrust bearings are carried by at least one elongate support inside the rack having a proximal end fixed to an end of a cylinder in which the rack slides.

Abstract: Some examples of a cable cutting system include a first cutting apparatus that includes a recess to receive a cable. The system includes a second cutting apparatus separate from and attached to the first cutting apparatus. The second cutting apparatus includes multiple cutting surfaces arranged to cut the cable received at the recess.

Abstract: The present invention provides methods and apparatus for unmanned aerial vehicles (UAVs) with improved reliability. According to one aspect of the invention, interference experienced by onboard sensors from onboard electrical components is reduced. According to another aspect of the invention, user-configuration or assembly of electrical components is minimized to reduce user errors.

Abstract: Systems, methods, and devices for propelling self-propelled movable objects are provided. In one aspect, a rotor assembly for a self-propelled movable object comprises: a hub comprising a first fastening feature; a drive shaft comprising a second fastening feature and directly coupled to the hub by a mating connection of the first and second fastening features, wherein the drive shaft is configured to cause rotation of the hub such that the mating connection of the first and second fastening features is tightened by the rotation; and a plurality of rotor blades coupled to the hub and configured to rotate therewith to generate a propulsive force.

Abstract: An apparatus comprising a drivelink comprising a housing including a socket, wherein the socket comprises a cross-sectional area, and a bearing cartridge disposed within the socket, wherein a cross-sectional area of the cartridge is less than the cross-sectional area of the socket. An apparatus comprising a drivelink comprising a housing having a socket, and a bearing cartridge positioned within the socket and comprising a first portion and a second portion, wherein the first portion is configured to undergo compression when a load is applied to the drivelink, and wherein the second portion is configured to not be in tension when the load is applied to the drivelink.

Abstract: A rotor blade disassembly method includes applying spanwise support to a rotor blade body and heating a bond disposed on an end of the rotor blade body. The method also includes removing the spanwise support from the rotor blade body and exerting shear stress on the bond using weight of the rotor blade body. A blade disassembly system is also described.

Abstract: A method, device, and system for detecting transparent elements in a vehicle environment are described. In some examples, this may include accessing a first image depicting a scene. The first image may include a first polarization characteristic. A second image depicting the scene may also be accessed. The second image may include a second polarization characteristic. It may be determined that the scene includes an element having transparent properties based at least in part on the first image and the second image.

Abstract: A method for adaptive mission execution by an unmanned aerial vehicle includes receiving a set of pre-calculated mission parameters corresponding to an initial UAV mission; collecting UAV operation data during flight of the unmanned aerial vehicle; calculating a set of modified mission parameters from the set of pre-calculated mission parameters and the UAV operation data, the set of modified mission parameters corresponding to a modified UAV mission; and executing the modified UAV mission on the unmanned aerial vehicle.

Abstract: A modular Unmanned Aerial System (UAS) has first and second flight configurations, and includes an Unmanned Aerial Vehicle (UAV) parent module and a plurality of UAV child modules. The parent module may have a fuselage, forward and aft wings connected to the fuselage, and a first plurality of flight propulsion devices. The child modules have a corresponding second plurality of flight propulsion devices. Each child module docks wingtip-to-wingtip with the parent module or an adjacent edge of a child module using the docking mechanisms. The child modules undock and separate from the forward wing and each other, and achieve controlled flight independently of the parent module while in the second flight configuration. A method for controlling the modular UAS is also disclosed.

Abstract: A fact checking system utilizes social networking information and analyzes and determines the factual accuracy of information and/or characterizes the information by comparing the information with source information. The social networking fact checking system automatically monitors information, processes the information, fact checks the information and/or provides a status of the information, including automatically modifying a web page to include the fact check results. The fact checking system is able to be implemented utilizing a drone device.

Abstract: A system for affixing a gatebox to an aircraft includes a first type of gatebox operable to release material from an aircraft, a second type of gatebox operable to release material from the aircraft, a frame coupled to the aircraft operable to receive a selected one of the first type of gatebox and the second type of gatebox; and a plurality of fastenings operable to secure the selected one of the first type of gatebox and the second type of gatebox to the frame.

Abstract: A cargo management system may include an air cushion cargo shuttle, an air cushion cargo shuttle, an air blower configured to blow air beneath the air cushion cargo shuttle and a shuttle drive unit that interacts with a linear guide rail and configured to cause linear motion, wherein the shuttle drive unit is configured for self-propulsion.

Abstract: Described is a stowable display apparatus (200) suitable for stowing a display, such as an in-flight entertainment monitor, in a storage module (110) located above a spreader or a seat bottom of a passenger seat (102). The stowable display apparatus can include an arm (228, 236) pivotally coupled to a mounting plate (222) at a pivot point (250) that is located above the spreader or seat bottom and proximate the forward end of the seat (102), thus enabling a display bracket of the arm to pivot upwards and out of an armrest assembly before rotating into a deployed position. The display arm (228, 236) can provide an easy, safe, and low-cost mechanism for stowing and deploying a display. The thin profile of the display arm allows a storage module (110) two inches wide or less to stow both a display and a table surface, each independently deployable and stowable irrespective of the other's position.

Abstract: An aircraft ram air channel assembly having: a first ram air inlet with a deflector protruding from the aircraft outer skin, the deflector guiding an air flow into a first ram air inlet channel; a second ram air inlet having a cross-sectional area flush with the outer skin, the second inlet being coupled to a second ram air inlet channel and arranged proximate to the first inlet upstream of the first inlet; and a flap pivotable about an axis between first and second operating positions. The axis is upstream of the first and second inlets and extends perpendicular to the air flow. The flap in its first position projects into the second inlet channel to control air flow through the second inlet into the second inlet channel, and in its second position projects into the air flow to prevent foreign objects from entering the first and second inlets.

Abstract: A second stage turbine nozzle includes a second stage disk portion having a central axis, and a plurality of second stage vanes positioned radially around and attached to the second stage disk portion. Each second stage vane extends a vane height H away from the second stage disk portion and each second stage vane has a first end positioned at a diameter D away from the central axis. The second stage turbine nozzle also includes a plurality of second stage throats defined between radially adjacent second stage vanes. Each second stage throat has a throat width W between radially adjacent second stage vanes. The second stage turbine nozzle also includes a coating on a sidewall of each second stage vane, wherein a surface roughness of the sidewall is between 125 microinches Ra and 200 microinches Ra.

Abstract: A motor assembly that includes a motor (102) having a rotatable shaft, a hub coupled to the rotatable shaft, the hub having a propeller indexer to receive a propeller (104), when the propeller is present, a sensor trigger rotatable with the shaft (100) and positioned at a propeller offset angle ?PROP from the propeller indexer, and a sensor coupled to the motor and positioned to detect the sensor trigger so that the propeller indexer may be positioned at the propeller offset angle ?PROP from the sensor through rotation of the shaft so that said sensor is proximate to the sensor trigger.

Abstract: A rotorcraft includes a fuselage having a fuel tank receiving assembly with a fuel tank positioned therein. The fuel tank including a plurality of interconnected fuel bags operable to contain liquid fuel. A network of straps is disposed about the fuel tank forming a restraint assembly. The network of straps includes at least one perimeter strap extending at least partially about at least two fuel bags and at least one surrounding strap extending at least partially about the at least two fuel bags. The at least one perimeter strap has at least two intersections with the at least one surrounding strap.

Abstract: A sensor system and method includes first and second sensing elements, digital sensors, a host computer and a digital bus. The first sensing element is configured to collect first sensor data and the second sensing element is configured to collect second sensor data. The digital sensor includes a controller that is configured to receive the first and second sensor data and process the first sensor data together with the second sensor data to generate processed data. The host computer is configured to receive the processed data from the digital sensor over the digital bus.

Abstract: The method allows to monitor a composite material comprising an epoxy resin filled with electrically conductive nanoparticles, wherein at least one electrical property i.e. impedance of the composite material is influenced by being subjected to a mechanical deformation. The method provides for inserting the composite material in an electric circuit emitting an electric signal whose value depends on the electrical property, so that, when the value of the signal overcomes a given threshold value, a warning message is delivered.

Abstract: In some embodiments, a system is provided that includes a portable electronic device; and an application executable on the portable electronic device, the application including computer program code that (a) monitors acceleration data during a flight of an airplane; and (b) displays a representation of the acceleration data in relation to a threshold acceleration of the airplane. Numerous other aspects are provided.

Abstract: An unmanned aerial vehicle delivery system utilizes an unmanned aerial vehicle (UAV) to deliver packages between an initiation point and multiple delivery points at a raised elevation. The UAV flies between points in an organized manner, using logistical, maintenance and safety software, commands from a delivery organization, and guidance tools to coordinate deliveries. One advantage of the system is that the UAV engages the delivery points at a raised elevation, rather than the ground level. The UAV docks through an elevated structure at the delivery point for delivering the package and replenishing a power source. The package is conveyed from a docking end and through a central shaft of the elevated structure by means of an elevator. The package then travels to a lower structure, such as a house or office, for pickup. After completion of the delivery, the UAV replenishes its power source and/or continues on the delivery route.

Abstract: Embodiments of the present invention relate to composite materials for use as a vehicle arresting system (also referred to as an Engineered Material Arresting System (EMAS). Specific embodiments may use modified polymeric foams composites. The polymeric foams may include additives, coatings, combinations of both, or other features than render them useful for an EMAS. The polymeric foams may also have one or more modified surfaces that provide a protective crust. For example, the one or more surface may be modified by application of heat in order to help close the polymeric foam cells and/or to create an encapsulative surface. These features can provide enhanced weather resistance, fire resistance, moisture absorption, jet blast resistance, improve their energy absorbing properties, or other desired features.