Abstract: A bicycle sprocket comprises a first sprocket body, first sprocket teeth, a first side surface, a second side surface, at least one shifting facilitation projection, at least one guide portion, and at least one recess. The at least one guide portion is provided on a first side surface to guide a bicycle chain from the bicycle sprocket toward a smaller sprocket in a second shifting operation. The at least one recess is provided on the first side surface so as to be adjacent to the at least one guide portion in a circumferential direction defined about a rotational center axis. At least one of the at least one recess is provided in an upstream angular area defined from the at least one shifting facilitation projection to an upstream side in a driving state and within 90 degrees in the circumferential direction.

Abstract: A bicycle gearshift mechanism has a base element, a pivot mechanism, a movable element, and a chain guide arrangement. The pivot mechanism connects the base element to the movable element. The chain guide arrangement is connected, rotatably about a rotary axle, to the movable element.

Abstract: A bicycle front derailleur is provided that can be easily coupled to a bicycle frame. The bicycle front derailleur includes a base member, a chain guide and a link mechanism. The base member is configured to be coupled to a bottom bracket hanger of the bicycle frame. The chain guide is configured to guide a chain. The link mechanism connects the chain guide to the base member to move the chain guide between a retracted position and an extended position. The base member includes a recess configured to accommodate a part of the chain guide in a state where the chain guide is located at the retracted position.

Abstract: An apparatus for supporting cables, lines, and/or hoses that connect a moored boat to shore-based services includes a flexible rod and at least one guide. The flexible mod is mountable to a shore anchor, and the at least one guide is attached to the flexible rod. The at least one guide retains the at least one cable so that the at least one cable extends substantially parallel to the flexible rod.

Abstract: There is disclosed a retrieval system for retrieving a vessel from water to a deck of a recovery vessel, comprising: a lifting device mounted on the deck of the recovery vessel, the device comprising a substantially vertically extending structure and a lifting hook mounted to said substantially vertically extending structure so as to be raised and lowered therefrom by way of a first winch; a connection lead having a free end configured to detachably connect to a connection link of the vessel to be retrieved from the water an opposing end of the connection lead being located on the recovery vessel; a capture member mounted with respect to the lifting hook to capture the connection link of the vessel when the free end of the connection lead is raised towards the lifting hook; and a control member mounted with respect to the lifting hook of the lifting device and configured to receive at least a portion of the connection lead so as to direct the connection link to the capture member to be captured thereby as the

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 fin for use on a surfboard, the fin comprising: a leading edge, a trailing edge, and a base, the base comprising at least one mount for mounting the fin onto a surfboard; a first and a second outer fin surface which meet along the leading edge and the trailing edge and abut the base; and a first ridge protruding laterally from the first outer fin surface, and/or a second ridge protruding laterally from the second outer fin surface; wherein the shape and configuration of the fin creates an area of lower water pressure around and in front of the fin, as well as disrupting and/or reducing the size of trailing vortices, resulting in additional forward thrust for the board on which the fin is mounted.

Abstract: A device comprises a spring and a sleeve. The spring is configured to form a closed loop. The spring is moveable between a coiled configuration when the spring is collapsed and an uncoiled configuration when the spring is expanded. The spring defines a circumference while in the uncoiled configuration. The spring is disposed within the sleeve.

Abstract: A pressure reducing second stage for underwater use includes a case provided with a breathing gas inlet, with an inhalation/exhalation port and with an exhaled gas exhaust outlet with a non-return valve, the gas inhalation/exhalation port being connected to a mouthpiece tube, the breathing gas inlet in the case being connected to a breathing gas pressure reducing device provided with a hollow cylindrical element or pipe, which has a breathing gas inlet port communicating with a gas supply conduit through a valve which is interposed between the supply conduit and the mouthpiece tube, the case being provided with a pressure sensitive means device for controlling the opening/closure of the valve. The breathing gas inlet in the case is provided in its lower portion and the hollow cylindrical element is connected to the inlet on the case such that its axis is substantially vertical, when used in the upright position.

Abstract: A naval azimuth propulsion system including an electric motor, a propeller operatively connected to the electric motor to rotate about a relative central axis, an annular nozzle positioned coaxially around the propeller, elements for supporting the motor and the propeller, these elements being connectable to the hull of a ship, first magnetic shielding means designed to shield the magnetic field generated by the electric motor during its operation.

Abstract: The present invention provides a paddle for a personal watercraft, the paddle comprising: a paddle end, with the paddle end comprising a shaft and a blade and the blade engaging the shaft at an angle between 15 and 35 degrees from a major axis of the shaft. The paddle further comprises an arm support, the arm support comprising a bracket for engaging a user's forearm, and an extension connecting the bracket to the shaft.

Abstract: Systems and methods for mounting and controlling a motor on a kayak are disclosed. A motor may be mounted to a kayak by a single interface on the kayak and rotated using foot pegs. The control system provides for responsive input and automatic directional stabilization of the motor.

Abstract: A portable propulsion system for a watercraft may include a shaft, a propeller, an outer casing, and a flexible strap. The shaft may have a prop end section, a drive end section, and a rotational axis extending from the prop end section to the drive end section. The propeller may be connected to the prop end section of the shaft. The drive end section may be configured for removable connection to a driver for rotation of the propeller via rotation of the shaft about the rotational axis to propel the watercraft. The outer casing may be disposed around the shaft. The flexible strap may have first and second end sections connected to the outer casing in respective first and second regions.

Abstract: An aircraft spinner assembly includes collar stud joints connecting spinner to forward flange connected to fan rotor disk. Collar stud joint is operable to push out spinner when stud is un-torqued. Collar may be attached to stud disposed through spinner bolt hole in spinner and collar disposed in counterbore of spinner bolt hole. An aft stud thread on collar stud may be threaded into aft nut which may be swaged into flange bolt hole in forward flange. A washer may be in counterbore between collar and spinner and made from low friction and/or sacrificial material. A forward radial clearance may surround stud between stud and spinner. A forward nut may be threaded onto forward stud threads on forward end of the collar stud and abut spinner. External aft stud threads may be on collar studs and threaded into internal flange threads within flange bolt holes in forward flange.

Abstract: A bistable pitch propeller includes a ball, a spring, and a clutch module where the clutch module has a range of rotational movement between a locked end position and a released end position. The clutch module includes a detent, where the ball sits inside and outside of the detent when the clutch module is in the locked end position and released end position, respectively. In response to an input torque and a spring force from the spring, the clutch module rotates toward the released end position and the locked end position, respectively. The bistable pitch propeller also includes an aircraft blade where the aircraft blade is at the first pitch angle and the second pitch angle when the clutch module is in the locked end position and the released end position, respectively.

Abstract: An aerodynamic device for enhancing lift and reducing drag on a body, comprising a plurality of raised members, each having a symmetric profile and including a central portion having an elongated profile, and first and second outer portions having elongated profiles and arranged substantially parallel to and on opposing sides of the central portion, wherein the plurality of raised members are situated adjacent one another to form a continuous structure on or defining at least a portion of a surface of the body and oriented such that the raised members are substantially aligned with a direction of localized flow on the body. An aerodynamic device for enhancing lift and reducing drag of a flying disc, wherein the plurality of raised members are situated adjacent one another to form a continuous structure and the raised members are oriented in a substantially circumferential direction on the surface of the flying disc.

Abstract: An aircraft landing gear assembly including a structural load bearing beam arranged, in use, to react torsional loads applied to it. The beam has a tubular box section main body having four straight sidewall portions, adjacent sidewall portions being orthogonal to one another and connected by rounded corner portions. Each corner portion has a radius of between 10% and 40% of the width and/or height of the tubular box section main body.

Abstract: An aircraft landing gear assembly having a shock strut with an outer cylinder and a sliding tube, a bogie beam pivotally coupled to a first one of the outer cylinder and the sliding tube via a bogie pivot pin, and a set of torque links arranged to inhibit rotation of the sliding tube relative to the outer cylinder about the shock absorber travel axis. The torque links include a first torque link and a second torque link movably coupled to the first torque link. The first torque link is movably coupled to a second one of the outer cylinder and the sliding tube, which is distinct from the first one of the outer cylinder and the sliding tube, and the second torque link is pivotally coupled to the bogie pivot pin to pivot about the bogie pivot pin.

Abstract: A vibration isolation system for an advancing blade concept rotorcraft having a pylon assembly and an airframe. The vibration isolation system includes one or more pylon links each having first and second ends with the first end coupled to the pylon assembly and the second end coupled to the airframe. Each pylon link includes a vibration isolator, such as a Liquid Inertia Vibration Eliminator unit, that is interposed between the pylon assembly and the airframe. The vibration isolator system is operable to reduce or eliminate transmission of the pylon assembly vibration to the airframe.

Abstract: A suspension device provided with at least one suspension means. The suspension means comprise a tuned mass damper, the damper comprising an inertial mass carried by a mass support. The suspension means include at least a first actuator generating a dynamic force for acting on the swinging motion of the damper. The inertial mass being movable longitudinally in translation relative to the mass support, the suspension device including a second actuator connected to the inertial mass to move the inertial mass longitudinally relative to the mass support.

Abstract: A rotorcraft having an antivibration system, the antivibration system being arranged at the interface between a fuselage of the rotorcraft and a casing of a main power transmission gearbox, or “MGB”, in order to transmit rotary motion generated by an engine of the rotorcraft to a main rotor providing the rotorcraft at least with lift, and possibly also propulsion, the antivibration system including calculation means for analyzing as a function of time the dynamic excitation and the resulting vibration transmitted to the fuselage of the rotorcraft.

Abstract: A multirotor aircraft with an airframe and a thrust producing units arrangement, wherein the thrust producing units arrangement comprises a predetermined number of thrust producing units for producing thrust in a predetermined direction, and wherein a flexible suspension unit is rigidly mounted to the airframe, wherein the flexible suspension unit comprises at least one bearing that mechanically couples the thrust producing units arrangement to the airframe such that the thrust producing units of the predetermined number of thrust producing units are inclinable in relation to the airframe.

Abstract: In accordance with an embodiment of the present invention, a method of operating a rotorcraft includes operating the rotorcraft in a heading control mode that includes activating a yaw channel path of a heading controller and deactivating a roll channel path of the heading controller when a speed of the rotorcraft is less than a first speed threshold or a heading error is less than a heading error threshold, and activating the roll channel path of the heading controller and deactivating the yaw channel path of the heading controller when the speed of the rotorcraft is greater than a second speed threshold and the heading error is not less than the heading error threshold.

Abstract: An aircraft includes propellers at a center of the airframe; a first power source; a pitch adjuster to change pitch angles of the propellers; a plurality of attitude control propellers; a second power source lower in output than the first power source; and a control circuit to control attitude of the airframe. The control circuit includes a first yaw rotation generation control unit to control first yaw rotation generated by torques of the propellers with the pitch adjuster; and a second yaw rotation generation control unit to control a second yaw rotation generated by torques generated by a difference in rotation speed between the attitude control propellers. The control circuit is configured to control the first yaw rotation generation control unit and the second yaw rotation generation control unit in accordance with a magnitude of a command value of yaw rotation.

Abstract: An aerial vehicle operation system includes an unmanned aerial vehicle in which a cable is connected, a processor, a fulcrum position adjustment mechanism, and a cable winding device. The processor determines a fulcrum position at which to support the cable to be above the unmanned aerial vehicle and to be on an extended line in a direction within a prescribed scope of angles with respect to a reference extension direction in the unmanned aerial vehicle. The processor determines control information about an operation of an arm of a crane that changes a position of a cable support included in the crane, and a length of a cable from the fulcrum position to the unmanned aerial vehicle. The fulcrum position adjustment mechanism controls an operation of the arm using the control information. The cable winding device changes a length of the cable using the determined length of the cable.

Abstract: A manned/unmanned aerial vehicle adapted for vertical takeoff and landing using the same set of engines for takeoff and landing as well as for forward flight. An aerial vehicle which is adapted to takeoff with the wings in a vertical as opposed to horizontal flight attitude which takes off in this vertical attitude and then transitions to a horizontal flight path. An aerial vehicle system which has removable wing sections which allow for re-configuration with different wing section types, allowing for configurations adapted for a particular flight profile. A method of customizing a configuration of an unmanned aerial vehicle based upon flight profile factors such as duration, stability, and maneuverability.

Abstract: A method is provided for sending a drone to a user on request. The method includes providing software, an instance of which is installed on a plurality of mobile technology platforms, wherein each mobile technology platform is associated with a user and is equipped with a tangible, non-transient medium having an instance of the software installed therein. The software contains suitable programming instructions which, when executed by a processor, perform the steps of (a) displaying, on a display associated with the mobile technology platform, a graphical user interface (GUI) having a user selectable object displayed thereon, (b) determining when the user selectable object has been selected by a user, and (c) when the user selectable object has been selected by the user, (i) determining the current location of the user via the location awareness functionality, and (ii) transmitting a request for a drone, wherein the request includes the determined current location of the user.

Abstract: The presently disclosed technology is directed generally to unmanned vehicle systems and methods configured to satisfy a first set of export control regulations, such as those within the jurisdiction of one government entity or international body (e.g., the U.S. Department of Commerce) without falling within the purview of a second set of export control regulations, such as export control regulations within the jurisdiction of another government entity or international body (e.g., the U.S. Department of State). Through limited range of operation, limited payload types, limited capabilities, and tamper-proof or tamper-resistant features, embodiments of the unmanned vehicle system are designed to fall within the purview and under control of one agency and not within the purview and under control of another agency.

Abstract: A quick-deploying portable unmanned aerial system/unmanned aerial vehicle (UAV) pad that provides a landing zone in a variety of different environments. The pad includes a flexible basal platform, a flexible band, a plurality of electronic accessories, and an operations management hub. The flexible basal platform outlines a landing zone and is composed of a non-permeable fabric. The flexible band is concentrically aligned with a central axis of the flexible basal platform and is tensionably mounted to the flexible basal platform. The plurality of electronic accessories includes a plurality of light-emitting diodes (LEDs) and a wireless communication device for facilitating landing procedures. The plurality of LEDs is distributed and adjacently connected about the flexible basal platform for increased visibility. The wireless communication device allows for wireless connection with a user and or a UAV. The operations management hub electrically and electronically controls the electronic accessories.

Abstract: A remote control unit of an unmanned vehicle comprises a first communications subsystem, a processor, and a graphics processor. The first communications subsystem may be operable to receive sensor data via a first communication link between the remote control unit and the unmanned vehicle. The processor may be operable to determine a position and orientation of the unmanned vehicle based on the sensor data. The first communication subsystem may be operable to receive, via a second communication link between the remote control unit and the unmanned vehicle, a live first-person view from a camera of the unmanned vehicle. The graphics processor may be operable to generate a virtual first-person view from apriori data based on the sensor data. The processor may be operable to determine whether to present said live first-person view or said virtual first-person view based on signal quality of said second communication link.

Abstract: An automatic degradable sphere distributing device for an unmanned aerial vehicle, relating to the technical field of plant protection mechanism. Said distributing device comprises a ranking portion, an adjustment portion and a distributing portion. The ranking portion consists of a rotating shaft (2), blades (1a, 1b), a rolling bearing (12), a sphere cabinet (3), a coupling (9b), a motor support (11b) and a motor (10b). The adjustment portion consists of a housing (501), a bevel gear transmission group (502, 503) and adjustment sheets (504a, 504b, 504c). The distributing portion consists of circular wheels (8a, 8b), a spur gear group (6a, 6b), a guide rod (13), a coupling (9a), a motor support (11a) and a motor (10a). Said distributing device may rank the degradable spheres vertically in sequence, being adaptable to spheres of different volumes, being highly universal, and being capable of distributing the spheres at intervals, with high precision and automation degree.

Abstract: Apparatus for releasing a payload from an air vehicle (14), the apparatus comprising a generally tubular holding device (10) mounted on, or formed integrally with, said air vehicle, said holding device (10) having an open end facing in a direction substantially opposite to the direction of travel (16) of said air vehicle(14), in use, the apparatus further comprising a container (18) for housing said payload and configured to be at least partially received within said holding device (10), at least one releasable retaining device (20) for releasably retaining said container (18) within said holding device (10), and an actuation device for selectively actuating said at least one releasable retaining device to release said container from said holding device, said container (18) having thereon at least one drag inducing device (22) configured to induce drag in a direction substantially opposite to that of said direction of travel (16) of said air vehicle, in use, so as to act to drag said container (18) from said

Abstract: A method of installing an aircraft overhead stowage system includes installing a plurality of bin support rail fittings onto a plurality of bin support rails disposed above a ceiling of a cross-aisle galley complex; positioning a stowage compartment housing supported by a stowage support structure above the ceiling of the galley complex, the stowage compartment housing including a first stowage compartment and a second stowage compartment each movably engaged with and disposed inside the stowage compartment housing; aligning the stowage compartment housing and the stowage support structure with the bin support rails; and fastening the stowage support structure to the bin support rails using the bin support rail fittings such that the stowage compartment housing is structurally supported above the ceiling of the galley complex.

Abstract: Passenger accommodation systems are described. An example passenger accommodation system can be disposed in an aircraft and can include a passenger seating deck, a plurality of passenger seats disposed within the passenger seating deck, and a partition wall disposed within the passenger seating deck so as to separate the plurality of passenger seats into a first set of passenger seats and a second set of passenger seats. The partition wall can be aligned with a longitudinal axis extending in the direction of travel of the aircraft. Movement of passengers between the first set of seats and the second set of seats may not impeded by the partition wall.

Abstract: A waste bin device of an aircraft lavatory unit is provided. A chute, waste flap, and waste container are formed from a material having fire resistance performance. A fire spreading prevention space that prevents fire from spreading to the outside of a waste bin device main body due to a flame occurring when inserted waste catches fire is formed inside the waste bin device main body at a storing position of the waste container positioned with regard to a lower portion of the chute. A maintaining portion maintains the waste container at a storing position. The maintaining portion includes a first maintaining portion that maintains from a vertical direction a condition where an upper portion of the waste container and lower portion of the chute are aligned, and a second maintaining portion that maintains the condition from a direction orthogonal to the vertical direction, at the storing position.

Abstract: A system and method for deplaning and boarding airplanes. The system is comprised of a track that provides a loop for transferring seats from the airplane, to a deboarding area, to a boarding area, and back to the airplane. Seats with integrated storage compartments lower onto the track via a connector for transporting the seat along the track and through the system.

Abstract: An environmental control system (ECS) includes an air conditioning pack that receives outside air; a regenerative treatment subsystem, wherein the treatment subsystem includes a treatment bed configured to cycle between an adsorption phase and a desorption phase; and a fan that receives recirculated air from the environment and moves the recirculated air to a mixing manifold.

Abstract: An aspirator may include an aspirator body that defines an annular cavity, a central channel, and an annular slit. Fluid communication between the annular cavity and the central channel may be via the annular slit. The aspirator body may include an entrainment opening through which ambient air is configured to be entrained into the central channel in response to gas flowing from the annular cavity through the annular slit and into the central channel.

Abstract: A system for hybrid propulsion for an aircraft includes a gas turbine engine having a power shaft. A motor generator is operatively connected to the power shaft of the gas turbine engine and configured to produce electric power. An electric propulsion motor is configured to receive the electric power and be selectively driven at an operational speed independent of a rotational speed of the power shaft.

Abstract: One example aspect of the present disclosure is directed to a method for implementing modularized logic. The method includes accessing, by one or more processors, control software implemented on a controller to control operation of an aircraft engine. The method includes accessing, by the one or more processors, at least one of a plurality of propeller configuration parameters. The method includes modifying, by the one or more processors, the accessed at least one of the propeller configuration parameters independently of the control software.

Abstract: An aircraft design using an air intake structure for reducing drag and assisting aerodynamic control surfaces in controlling the aircraft. The air intake structure comprises an outer skin including a plurality of perforations, a plurality of closing plates for covering corresponding perforations and an actuator operatively connected to the plurality of closing plates. The outer skin creates a chamber between the outer skin and a fuselage of the aircraft and extends to cover engines of the aircraft and adapted to restrict airflow into the engines. The plurality of closing is movable between a closed position covering the corresponding perforations and, an open position, uncovering the corresponding perforations. The actuator is used for positioning the plurality of closing plates between the closed position and the open position. The aircraft design also includes a wing for minimizing an airfoil boundary layer separation and de-icing a leading edge of the wing.

Abstract: Methods and apparatus for distributing electric power from a power source of an aircraft to a plurality of electrical loads of the aircraft during a limited power availability condition are disclosed. An exemplary method comprises: distributing electric power from the power source of the aircraft to the plurality of electrical loads; receiving one or more signals indicative of a demand for electric power by one or more of the plurality of electrical loads; and adjusting the power distribution to the plurality of electrical loads based on the demand for electric power by the one or more plurality of electrical loads. The power distribution is also adjusted to maintain an overall power consumption of the plurality of electrical loads at or below a threshold.

Abstract: An embodiment fluid recovery structure includes a body having an interior cavity, ports integrally joined to first walls of the body and having port walls that extend away from the body, with each of the ports having a port opening that is contiguous with the interior cavity, and a drain structure integrally joined to a second wall of the body and having a drain hole that extends from the interior cavity through the drain structure.

Abstract: A high altitude vehicle is brought to a desired altitude above sea-level prior to the transfer of fuel and/or oxidant from an airplane to the high altitude vehicle. The high altitude vehicle may be towed to the desired altitude by a tow airplane or may reach the desired altitude under its own power. At the desired altitude, the high altitude vehicle is connected to the tow airplane via a tow cable. Alternatively, the high altitude vehicle may be mechanically carried by the tow airplane. Fuel and/or oxidant is transferred to the high altitude vehicle from the tow airplane via respective fuel and/or oxidant lines. The high altitude vehicle then separates from the tow airplane and proceeds to high altitude under its own power.

Abstract: Systems, apparatus, and methods may control movement of an object through a fluid. The systems, apparatus, and methods may utilize a rotatable control unit including a pair of fins to generate a control force at least partially perpendicular to a direction of travel of the object through the fluid. One fin may be configured to generate a different amount of rolling moment than the other fin to provide rotational acceleration and energy production.

Abstract: Disclosed is a system for generating power for an aircraft. The system includes a boundary layer ingestion propulser that includes a propulsion fan configured to receive torsional energy from a boundary layer airstream, and a motor generator in operable communication with the propulsion fan and configured to generate power in response to rotation of the propulsion fan.

Abstract: Systems and methods are described herein for automatically monitoring a status or position of a vehicle component. Both powered and non-powered (or passive) systems are contemplated. The systems and methods utilize a sensor that signals when a vehicle component, such as an arm rest, a tray table, a seat back, or a window shade is in a predetermined position. The signal can be received by a processor and transmitted to a central server that can provide a report of the status of the various vehicle components to an attendant or crew member to quickly apprise them of the status of the various components without requiring manually checking each component.

Abstract: Methods and apparatus for determining seatbelt status are disclosed. An example system includes a plurality of seats including seatbelts. Each of the seatbelts includes a sensor to detect a position of a respective seatbelt, the position including at least one of a fastened position or an unfastened position, and a transceiver to wirelessly communicate the position of the respective seatbelt. The system includes a remote monitoring unit to receive the positions of the seatbelts. The remote monitoring unit is to determine if one or more seats are occupied and, in response to determining that one or more seats are occupied, the remote monitoring unit is to display an overview the seats and the respective positions of the seatbelts for the one or more occupied seats.

Abstract: An aircraft and system of doors for providing security to a flight deck of the aircraft, and methods for operating the same, are provided. A passenger cabin is separated from a flight deck by an aisle that includes doors at either end. The doors are locked by a controller and one of the doors may only be unlocked, during a flight, if the remaining door is locked. As a result, a pilot can access a lavatory in the aisle in a secure manner. Additionally, the door closest to the passenger cabin may include a window that allows the pilots to view the passenger cabin through a peephole in the flight deck door. The controller may selectively dim or block a view through the window to prevent monitoring of the pilots' movements onto and off of the flight deck.

Abstract: Components having fibre-reinforced composite structures are disclosed. The component comprises a plurality of structural fibres embedded in a cured matrix material and a plurality of nanostructures such as carbon nanotubes extending from one or more of the structural fibres. In some embodiments a density of the nanostructures is at least 107 nanostructures per cm2 of surface area of the one or more structural fibres. In some embodiments, the nanostructures extend from an outer fibre proximal to an outer surface of the component but not from an inner fibre distal from the outer surface. In some embodiments the one or more structural fibres from which the nanostructures extend are free of a sizing agent.