Abstract: The present invention is an apparatus to counter normal gravitational force in order to provide a personnel lifting device. The personnel lifting device is a lighter-than-air gas-filled balloon having a harness to suspend a user therefrom. The balloon further includes a weighted tether to automatically control the height of any ascent and the speed of any descent—wherein the balloon may be used as a component of an amusement.

Abstract: A wind harnessing system using a plurality of self supporting airfoil kites 50 for production of useful power. The system comprising multiple airfoil kites 50 in tandem attached to a pivotal control housing 32 by control lines 58L and 58R and support lines 60L and 60R. Control lines 58L and 58R can change length with respect to the length of support lines 60L and 60R to control the airfoil kites' 50 angle-of-attack, pitch angle, direction of flight, and flight speed. The length of control lines 58L and 58R are controlled from ground station 30 by a movable pulley system in control housing 32 to adjust the airfoils' direction to follow a specific flight path 140. Control lines 58R and 58L and support lines 60R and 60L are also wound on a power shaft and pulley system in control housing 32. As the airfoil kites are propelled by the wind at very-high speed, the airfoils generate a powerful AXIAL force.

Abstract: A system and mechanism for the movement of large, outsized and heavy cargo includes a tow cable connectable at a first end to a towing vehicle, a buoyant lift vehicle comprising an inflatable member, a tether cable linked to the buoyant lift vehicle and having a connection with the tow cable, and a payload connector linked to at least one of said payload tether cable and said tow cable. The tow cable has a tow vehicle connector at a first end. A connector links the tether cable and the tow cable.

Abstract: A towed airborne array system has a balloon that supports appropriate instrumentation packages overhead and is tethered to a towing ship to improve line-of-sight sensing and communication capabilities to up to about 100 nautical miles. These improved capabilities can benefit relatively small surface combatant ships (CG, DD, FFG) and might provide an alternative location for having countermeasures placed on a warship.

Abstract: The present invention is an apparatus to partially counter normal gravitational force. The personnel lifting device is a paraballoon, a lighter-than-air gas-filled balloon having a harness to suspend a user therefrom. The paraballoon further includes a plurality of flaps extending therefrom in order to allow the paraballoon to be maneuvered during descent, wherein the paraballoon may be used as a component of an amusement. In addition, various applications and attachments and embodiments are described.

Abstract: A system and method for illuminating hot air balloons is claimed. The system includes a activating a burner assembly on multiple hot air balloons from a central location. As the burner assemblies are activated, the hot air balloons become illuminated. Consequently, the illumination of multiple hot air balloons can be synchronized and otherwise choreographed from a single control station.

Abstract: Disclosed is a helium balloon of sufficient volume and buoyancy to allow a human pilot to float above the ground and to glide over the ground. The balloon incorporates several safety features that permit it to be used for recreation, including tethers for keeping the balloon moored to the ground or controlled by a ground crew and various means for deflating the balloon in case of an emergency.

Abstract: A power generation, transmission and distribution system for an aerostat using a tether, includes a ground-based power delivery system for generating a multi-phase power signal having a frequency at least greater than 400 Hz, an aerostat-based power distribution system for receiving the multi-phase power signal, and a tether for delivering the multi-phase power signal from the ground-based power delivery system to the aerostat-based power distribution system. The base power system generates a 3, 6, or 12 phase base power signal having a nominal frequency signal received by a rectifier to generate a high voltage DC output. A converter/inverter receives the high voltage DC output and generates the multi-phase power signal transmitted by the tether. A transformer aboard the aerostat steps down the multi-phase power signal and a rectifier processes the stepped-down multi-phase power signal into a DC power delivery signal.

Abstract: A tethered balloon having a spherical balloon proper inflated with a gas whose specific gravity is lower than that of the outside air, a gondola attached to the bottom of the balloon proper, a vertical stabilizer attached to the balloon proper, a connecting assembly attached to the balloon proper, a tether connected to the connecting assembly, and a tether holder having a drum to take up and pay off the tether and placed on the ground. The connecting assembly is positioned opposite to the vertical stabilizer with the gondola disposed in between. A straight line connecting the center of the balloon proper and the connecting assembly is inclined with respect to the central axis of the balloon connecting the center of the balloon proper and the center of gravity of the whole balloon. The balloon is transversely stable because little force acts on the balloon in a direction perpendicular to the wind.

Abstract: A lighter than air lighting device is disclosed comprising a dual envelope balloon providing an inner, gastight, elastic, transparent, expandable polymeric envelope such as polyurethane, containing a lighter than air medium such as helium, and a replaceable lighting device such as a halogen or arc lamp. The helium thus functions to both elevate and cool the lighting device. The inner, transparent envelope is surrounded by an outer envelope such as a colored silk or nylon which functions as a diffuser to provide sufficient illumination without dazzling the user. The outer envelope may also be used to carry information and advertizing messages.

Abstract: An aerodynamic device, such as a projectile includes an elongated forebody, and an aft section secured to the forebody. The aft section acts as a d control device, and includes a connecting member that extends integrally in a conically shaped flared section, for generating a lift force to help stabilize the projectile during forward flight. The aft section further includes a flange that extends from the flared section, and that provides velocity decay and optimal drag, in order to limit the projectile flight and descent within a predetermined safety or emergency range. The flared section is defined between an innermost edge positioned adjacent to the connecting member, and an outermost edge positioned adjacent to the flange.

Abstract: A suspended utility space designed as a captive balloon comprises a carrier balloon which is filled with lifting gas and into which an accessible inner space is incorporated. The carrier balloon is a vertically oriented ellipsoid. The accessible inner space is arranged in the lower part of the carrier balloon. The vertical orientation of the ellipsoidal carrier balloon and the arrangement of the inner space in the lower part of the carrier balloon result in a suspension behavior which is stable under calm conditions. The suspended utility space according to the invention has a larger advertising area visible from the ground and a more effectively utilizable inner space than a spherical airship of comparable size.

Abstract: A penetrator having a plurality of stacked penetrator segments is disclosed. Each penetrator segment has a nose portion and a rear portion. The rear portion of each penetrator segment has a rearwardly opening cavity therein and a plurality of fins pivotally mounted thereon. The penetrator segments are stacked such that the cavity of the forwardmost penetrator segment secureably contains the nose portion of the following penetrator segment such that there is a press-fit between the cavity and the nose portion. The following penetrator segments are similarly positioned such that the nose portion of each following penetrator segment is secureably positioned in the cavity of the immediately preceding penetrator segment. The fins of each penetrator segment are restrained in a stowed position when the cavity of the respective penetrator segment contains the nose portion of a following penetrator segment. An explosive element is located between each of the penetrator segments.

Abstract: A penetrator having a plurality of stacked penetrator segments is disclosed. One or more of the segments contains an explosive element Each segment has a nose portion and a rear portion. The rear portion of each segment has a rearwardly opening cavity therein and a plurality of fins pivotally mounted thereon. The segments are stacked such that the cavity of the forwardmost segment contains the nose portion of the following segment, and the following segments are similarly positioned such that the nose portion of each following segment is positioned in the cavity of the immediately preceding segment. The fins of each segment are restrained in a stowed position when the cavity of the respective segment contains the nose portion of a following segment.

Abstract: In an air balloon (1) comprising a leak-tight casing (2) consisting of one or more layers containing an inert gas (3) that is lighter than air and provided with a part (4) designed to be opened reversibly to enable deflation of the said balloon (1), this part (4) is positioned such that the axis (K--K) perpendicular to its aperture (4a) is inclined to the horizontal at an angle between 0.degree. and 180.degree., but perferably at an angle equivalent to 90.degree..

Abstract: A tube launched projectile having a shaft member at the aft section is slidably mounted on a boom extending aft from the body of the projectile. The boom has a cavity in its aft end which receives some combustion gas from the projectile propellant burn and retains this gas at elevated pressure until the projectile exits the tube. Upon reaching atmospheric pressure, the stored cavity gas expands and drives the slidable shaft aft, elongating the projectile to its flight configuration.

Abstract: A helium balloon transport system comprised of two separate helium balloon clusters (31) with underslung framing (2, 3, 4, 21) for use with two separate balloons (15) of comparable size, the entire system being interconnected (19) with moorings (16) to the ground (20) and having a gross lift of roughly 10,000 pounds. Power is provided by photovoltaic cells (5) augmented by rechargeable batteries (23). Travel is normally realized by throwing out grapples (26) and by winching (24) toward these fixed points (20). Free flight is reserved for emergency situations. The underslung framing (4) is rotatable to give a level configuration which when close to the ground in a jungle or forest allows for the avoidance of the damaging effects of high winds. The configuration is capable of use for travel upwind.

Abstract: Disclosed herein is a method and device which provides for the capability of functional illumination by a balloon. This invention includes one or more fiber optic elements within a balloon which are configured to disperse substantial light at its (their) ends. This invention further provides for reliable retraction of signal or illumination balloons during hazardous wind conditions by including a sensor for detecting the presence of such conditions, and providing for retraction of the balloon via its tether, wherein such retraction is either under operator control or automatic.

Abstract: A penetrator having a plurality of stacked penetrator segments is disclosed. Each penetrator segment has a nose portion and a rear portion. The rear portion of each penetrator segment has a rearwardly opening cavity therein and a plurality of fins pivotally mounted thereon. The penetrator segments are stacked such that the cavity of the forwardmost penetrator segment contains the nose portion of the following penetrator segment, and the following penetrator segments are similarly positioned such that the nose portion of each following penetrator segment is positioned in the cavity of the immediately preceding penetrator segment. The fins of each penetrator segment are restrained in a stowed position when the cavity of the respective penetrator segment contains the nose portion of a following penetrator segment.

Abstract: The balloon support apparatus for a hot air balloon ride comprises a doughnut shaped sleeve engaged within a crown area of an envelope of the hot air balloon. The sleeve contains a lighter than air substance, such as helium, in an amount sufficient to elevate the balloon envelope, the sleeve having a volume which will accommodate expansion of the lighter than air substance when heated to approximately 350.degree. F.

Abstract: A jet vane control system and method for a missile in which the system is compact, rugged, lightweight and detachably connected to the aft end of a missile. The system provides for very quick pitch over and roll control during launch. The system then detaches from the missile so as not to burden the missile during its flight to target. The vanes of the system are divided into quadrants, each having its own, mounting support and gear train assembly. Each vane is also connected through a, detachable coupling to the steering control system of the missile such that actuation of the steering control system simultaneously actuates the jet vane control system.

Abstract: An undersized kinetic-energy practice projectile of the dart type includes a penetrator and a tail unit that can be dissociated from one another while the projectile is in flight. The penetrator and the tail unit can be separated after a predetermined flight duration, by relative rotation of the tail unit with respect to the penetrator in response to the aerodynamic forces being exerted on the tail unit. This can be achieved by an element that is integral with the penetrator and is screwed onto a threaded part of the tail unit.

Abstract: An ammunition projectile of enhanced flight characteristics, having a boat tail portion and including a circular land provided on the rear surface of the boat tail portion and concentric with the longitudinal centerline of the projectile, the land having a circular concave wall extending from the flat rear face of the boat tail portion to a circular flat surface of the land. Among other things, the projectile exhibits a lesser rate of velocity deceleration along its flight path to a target than like projectiles that do not include the land.

Abstract: An installation for landing a tethered balloon comprises a balloon which is brought back down towards the ground (9) by means (11) of a return cable (2), and which has a gondola (6) which is hollow in its center to allow the return cable (2) to pass therethrough, and it also includes means for winding the return cable (2) out and in, which means are mounted in a cavity (10) in the ground. According to the invention, the installation also includes a landing platform (3) covering the cavity (10) and including an opening (12) through which the return cable (2) passes, which opening is centered on the vertical outlet axis (12a) of the return cable (2).

Abstract: A two-piece inflatable kite is made from configured, mirror imaged top and bottom polyester films which are heat sealed about their peripheral edge. Integrally extending from the edges forwardly and rearwardly are string connecting tabs formed from the top and bottom films. The tabs support reinforced apertures for attaching the kite string bridle. The top and bottom film portions also form a valve for adding air into and out of an air tight compartment within the kite. The air tight compartment also forms the wings of the kite.

Abstract: A sensor mount apparatus includes a loop for carrying a sensor payload. An upper portion of the loop includes at least one upper attachment point for receiving at least one upper tether line. A lower portion of the loop includes at least one lower attachment point to connect the sensor mount apparatus to a lower tether line. The sensor mount apparatus further includes an upper plate mounted to the loop, a lower plate for carrying a sensor payload, and a slide mechanism mounted between the two plates. The slide mechanism operates to slidably move the lower plate relative to the upper plate so that the lower plate and sensor payload attached to the lower plate move to a position where the sensing device of the sensor payload is not obstructed by the loop. Where the sensor payload is an optical sensor, such as a camera, the camera may be positioned to see an unobstructed, three hundred sixty degree field of view.

Abstract: A projectile includes a mechanism which allows the fin position to be reved after the projectile leaves the launch tube thus allowing the fins to have reversed leading edges, which avoids the costly weight of the one-piece design in the prior art, which is a parasitic weight that will result in a lower velocity, and consequently lower kinetic energy, from the same propellant charge. This mechanism also avoids having extra pieces falling from the muzzle and near the firing team or troops near the gun, and has the advantage of a simple, low-weight deployment mechanism which results in the least aerodynamic resistance after full deployment. The mechanism has at least one small winglet on each reversible fin which generates an aerodynamic lifting force to provide reversal of the fin after the projectile leaves the launch tube. These winglets are positioned and designed to cause the least increase in aerodynamic drag.

Abstract: A method and apparatus for automatically releasing a gas from a pressurized cartridge of the gas is provided, especially for the purpose of inflating an emergency balloon. The apparatus includes an automatic signal balloon inflator, having a support structure, an upper surface and a bottom plate. The bottom plate has at least a single cartridge mount, each with a vent and a pin port. The pin port connects to the cartridge mount. At least a single pressurized cartridge, containing a gas stored under pressure, is received into each cartridge mount in the support structure. A spring loaded piston is mounted upon the support structure. A plunger with a piston contact surface and a puncture pin is forced by the spring loaded piston to depress and penetrate the pressurized cartridge, releasing the gas contents of the pressurized cartridge through the vent. A firing spring forces the piston to engage the plunger.

Abstract: A projectile to be, fired from a non-rifled tube includes an elongated foody and a stabilizer secured to the tail end of the forebody for enhancing the projectile flight stability and for imparting spin to the projectile. The stabilizer includes a threaded member that extends integrally into a forward section, a peripheral channel and a grooved aft section. The forward section has a generally smooth cylindrical shape. The peripheral channel extends along the entire peripheral contour of the stabilizer and has a generally semi-circular cross-section, for generating an expansion wave and for directing air flow toward the grooved aft section. The grooved aft section is cylindrically shaped relative to a longitudinal axis, and has a predetermined number of identical, equally spaced, circumferentially positioned grooves which traverse the entire axial length of the aft section, and which are angled relative to the longitudinal axis. Each angled groove is defined by two substantially parallel side walls.

Abstract: A deployment device for stabilizing fins of a projectile includes at least one pallet and a holding device for each fin. The pallet is oriented to receive an aerodynamic flow when the projectile is fired and thus transfers a resultant strain to the fin to deploy it away from the projectile. The deployment device can be used for fins of a projectile fired from smooth barrelled weapons.

Abstract: A projectile includes a mechanism which allows the fin position to be reved after the projectile leaves the launch tube thus allowing the fins to have reversed leading edges, which avoids the costly weight of the one-piece design in the prior art, which is a parasitic weight that will result in a lower velocity, and consequently lower kinetic energy, from the same propellant charge. This mechanism also avoids having extra pieces falling from the muzzle and near the firing team or troops near the gun, and has the advantage of a simple, low-weight deployment mechanism which results in the least aerodynamic resistance after full deployment. The mechanism has at least one small winglet on each reversible fin which generates an aerodynamic lifting force to provide reversal of the fin after the projectile leaves the launch tube. These winglets are positioned and designed to cause the least increase in aerodynamic drag.

Abstract: The facility for preparing and deploying atmospheric sounding devices of the present invention, makes use of a structure with a retractable cover and a wind deflecting member circumscribing the shelter, to provide a transportable, reliable, and cost effective facility to prepare and deploy lighter-than-air balloons as the vehicle for carrying sounding devices. The facility permits preparation and deployment in any weather condition including, but not limited to, light to heavy winds that would otherwise cause down drafts through the roof opening in the structure.

Abstract: An apparatus comprises a deformable structure surrounding a volume, and means for suspending a fragile cargo in spaced relationship above an impact zone on said deformable membrane. The apparatus is designed to: prevent damage to fragile cargo therein; lengthen a duration of the cargo impact period; reduce terminal vertical freefall velocity of the cargo relative to a terminal vertical freefall velocity of the cargo alone; and lengthen a duration of a cargo/craft fall period for falls from extreme heights. Preferably, the apparatus is spherical in shape, substantially transparent, and has a plurality of flexible strut members for suspending the fragile cargo in spaced relationship above an impact zone of said apparatus.

Abstract: An underwater vehicle has a generally longitudinally extending housing terminating in at least one blunt end. Adjacent to and inboard of the blunt end of the longitudinally extended housing there is provided a compartment, and disposed in the compartment there is provided a folded, flexible bladder secured to a portion of the housing adjacent the blunt end and having a tapering configuration when pressurized or inflated. At or after launch of the underwater vehicle, or selectively at any other time in which it is desired to do so, an inboard mounted water pump which communicates with the interior of the bladder is operated to pressurize the bladder with regard to the surrounding ambient water, causing the tapered bladder to unfold and be extended outboard of the housing blunt end, thus streamlining the underwater vehicle.

Abstract: A statically stable limited range projectile utilizes a fin assembly combd with a cylindrical body and low drag ogival front end to ballistically match the limited predetermined range flight characteristics of a standard round.

Abstract: Improved collapsible roll or spin-stabilizing fin subassembly means of reively lightweight molded construction for missile means and the like that is generally made up of base or hub means, a series of four interconnecting fork means and a series of four fin means. The base means is suitably affixed in concentric fashion to the trailing end of the missile means. Each one of the interconnecting means is hingedly connected to its associated radially aligned bifurcated means of the series of four bifurcated means. At the same time, each fork means is biasingly interconnected to its associated bifurcated means so that any fork means is biasingly urged in a trailing or rearward direction, once the missile means is launched, to an outward and inward extended partially rotated position as limited by stop means provided on the base means.

Abstract: The invention is an attachment fitting for use on the flexible wall of a structure. In detail, the fitting includes a slot in the wall of the structure. A first flexible member is included having a center portion folded over its self forming a loop extending through the slot from a first side of the wall and out from the second side, and outer fan shaped portions on each end of the center portion bonded to the first side of the wall of the structure adjacent to the slot. The first flexible member further includes a plurality unidirectional reinforcing filaments in a matrix material with the filaments being parallel to each other in the center portion and fanning out from each other in each of the outer portions. A second flexible member having a periphery extending about the slot and the outer portions of the first flexible member is bonded thereto and to the first side of the flexible wall of the structure.

Abstract: A projectile for small firearms has an inner sealed container containing an impact charge of a mixture of pellets and a liquid or a mixture of pellets and a gel. This impact charge may be a mixture of dense metallic powder and a liquid or a mixture of dense metallic powder and a gel. The inner sealed container is rupturable upon impact with a target. An outer load distributing cover receives the inner sealed container and is shaped to provide a target impact surface greater than the target impact surface of the inner sealed container for reducing the force per unit area upon impact with a target. The outer load distributing cover is not penetrable by the impact charge upon impact with the target.

Abstract: The hot air balloon ride includes a balloon envelope having a basket attached thereto. The balloon is engaged by tether lines extending from grounded weights, the tether lines limiting extent of rise of the balloon. The basket includes an entryway and has further been modified to allow a gas tank for same to be engaged thereto, outside the basket. Further, the bottom surface of the basket is cushioned, and a pair of rip panels have been incorporated into the crown of the balloon, one of which is manually operable and the other of which would operate automatically if the balloon becomes disengaged from the tether lines.

Abstract: An aerial marker device includes a bracket to attach the device to an elevated structure such as a power line. A body is attached to the bracket and includes an outer envelope which is inflatable to provide the desired shape of the aerial marker device.

Abstract: A cylindrical device connected to the nose of a projectile for imparting n to the projectile fired from a non-rifled bore of a cannon. The device has at least two coaxial, adjacent, and integrally connected cylindrical segments of different diameter. The segment having the larger diameter is positioned most rearwardly of the projectile, relative to the nose of the projectile, and the periphery of this segment has circumferentially spaced angled slots for catching air moving past the projectile to spin the projectile. The segment with the smaller diameter attaches the cylindrical device to the aft end of the nose of the projectile and directs the flow of air to and through the angled slots of the segment having the larger diameter.

Abstract: A process for applying particles to a geographic region. The process involves flying a balloon over the region. The balloon carries a nozzle with a pipe communicating the nozzle with a ground supply of air and a source of particles. A mixture of air and particles can be forced up the pipe to the nozzle. The particles are then discharged over the region according to a pre-determined pattern. The process permits the accurate measured application of fertilizers and the like to a forest region.

Abstract: A missile (20) comprises a missile body (22) and a plurality of (typically four) body flaps (28) located around the circumference of the missile body (22). Each body flap (28) is independently pivotable to an extended position wherein the body flap (28) is pivoted outwardly from a pivot axis along the leading edge (34) of the body flap (28). The forward edge (34) of the body flap (28) is displaced outwardly from the body (22) of the missile (20) by a distance no less than a boundary layer thickness of the body (22) of the missile (22) at the maximum operating speed and altitude of the missile (20), and preferably about the boundary layer thickness, which thickness typically is about 1-3 inches for a high-velocity missile.

Abstract: Apparatus in kit form for the assembly of a model rocket having a body tube, fins, and propellant mount, wherein each fin has a root portion at a radially inner-most end for mountingly extending through slots apertured in the body tube and for mounting engagement with the propellant mount. The body tube is apertured with slots for mountingly receiving the root portions of respective fins. The propellant mount telescopically mounts within the body tube and mountingly seats the fin roots. In one embodiment, a plurality of mounting brackets is arranged for assembly with one another for forming the propellant mount. The mounting brackets have radially-extending mounting recesses for engaging and positioning a fin root.

Abstract: A device is provided for reducing the rate of rotation of a spinning submunition unit having a tail end provided with a deployable braking device, from a time after the submunition unit is ejected from a spin stabilized carrier projectile until the braking device is deployed. The device includes a plurality of bands arranged to form a star-shaped symmetrical band structure for placement around the braking device. Each of the bands has a free end provided with a wind pocket.

Abstract: An active flight control arrangement for an air vehicle that includes a split span vee fin tail control arrangement whereby inner and outer spans of each fin are independently operable to provide yaw, roll, and pitch control for an air vehicle in flight. The inner and outer spans of each fin are preferably not, but may be, in the same plane. An intermediate controllable span may also be provided between the inner and outer spans of each fin.

Abstract: A flechette is disclosed comprising a rod-shaped steel body having a blunt generally conical penetrating point, a separate resinous plastic fin component securely mounted on the rear end portion of the body, and a generally conical gradually tapering resinous plastic nose piece securely mounted on the penetrating point for reducing air drag when the flechette is fired at high velocity. Interlocking annular flanges are formed on the penetrating point and the nose piece for securing the nose piece to the body. The fin component has an axial sleeve received around a rear pin portion of the body and securely retained thereon by annular flange and groove members on the sleeve and the rear pin portion. A modified flechette is disclosed having a separate, hardened steel penetrator component securely mounted on a reduced front pin member on the body by a press fit between the front pin member and a rearwardly opening bore in the penetrator component.

Abstract: A balloon storage system which is disclosed wherein comprises at least one cylinder-like or bag-like storage for storing balloons packed therein, which is formed by locking meshes at any places of a pet having meshes of a diameter smaller than the diameter of the balloon, so that the balloons packed in the storage can be released off to the outside by releasing the locking of the openable locations of the locked portions of the net to open the storage. In this balloon storage system, the openable locations of the net is releasably locked by chain-binding with a knot smaller in diameter than the diameter of the balloon by means of a locking element.

Abstract: The effectiveness of randomly indexed randomly ejected decoys/aerobodies is improved by flying lifting glide instead of ballistic trajectories. Elements matching body contours are deployed to locate the neutral point above and behind the center of gravity. These elements are oriented to generate strongly cross-coupled forces and moments in pitch and yaw, provide favorable aerodynamic rolling moments and trim the configuration at positive lift. Various layouts are discussed. Means of achieving desirable stability levels, even at supersonic speeds, improve trimmed lift/drag ratios, minimize induced roll and inertial cross-couplings, etc., are also described.

Abstract: A limited range training projectile utilizes a two strake and flare combination or two slots with flare combination design to ballistically match a service round to a predetermined range. The design permits statically stable flight at a selected limited range and includes instability at a predetermined range to greatly limit the total range.