Abstract: An air rescue assembly (20) having a balloon (110) adaptable to be filled with a gas to suspend an object (138) in the atmosphere for a predetermined amount of time is disclosed. The air rescue apparatus includes a shroud (120) substantially enclosing the balloon, a harness (136) selectively attachable to the object, and an attachment assembly (130) extending between the shroud and the harness.

Abstract: The present invention is a stabilizer ring for a sea anchor, in particular a parachute sea anchor. The preferred embodiment of the stabilizer ring comprises a ring supporting a domed arch. The domed arch has two arch supports that divide the ring into a plurality of sections. Each arch support has a vertex and the two arch supports are connected at their vertices. The domed arch is pivotally connected to a swivel. The swivel has two loops pivotally connected by a bolt.

Abstract: A balloon comprising an envelope, wherein the envelope has a multilayered structure comprising a gas-impervious sheet, and a liquid absorbent sheet overlaid on the inner surface of the gas-impervious sheet.

Abstract: A process for creating a flying light source including the steps of providing an inflatable balloon and associating a light source therewith. A retaining filament is attached to the inflated balloon. The light source may be a chemiluminescent lighting device which is attached to, or inserted into, the balloon. Alternatively, the light source may be a battery-operated light assembly attached to the balloon. The invention may be in the form of a rescue kit including the inflatable balloon, the chemiluminescent lighting device, the retaining filament and a lighter-than-air gas source. Alternatively, the invention may be in the form of a self-contained signaling device including a canister of lighter-than-air gas, a nozzle for dispensing the gas, the battery-operated light assembly, and the filament.

Abstract: A balloon kite is formed with a plurality of sized sheets of gas impervious sheet material that form one or more fillable interior chambers. The balloon kite is capable of being flown and deployed in the presence or absence of a critical level of wind. When the critical level of wind is present a balloon kite lifts and assumes an aloft position with the interior chamber or chambers filled with air. If the wind is below the critical level of wind, the balloon kite may be filled with a lighter-than-air gas and flown with a minimal amount of wind, and by an individual having minimal training. The balloon kite is structured with extended and folded portions that provide a simple and low cost reinforced attaching arrangement for securing a bridle and kite flying line to the balloon kite. One or more of the sized sheet is formed with a coiled tail portion. Each coiled tail portion is extendable when uncoiled and useful for stabilizing a balloon kite when in an aloft position.

Abstract: An apparatus for inflating and deploying an aerostat having a nose section and a tail section includes a cylindrical container for housing the deflated portion of the aerostat. The cylindrical container is formed with an open end and defines a longitudinal axis. A feed hose extends from a gas source, through the container to a hose end that projects axially from the open end of the container. The deflated aerostat is initially folded to juxtapose the nose and tail of the aerostat. Next, the nose of the aerostat is attached to the feed hose end and the remaining portion of the aerostat is folded and inserted into the container. As the tail section is inflated outside of the container, aerostat cloth is drawn from the container. A mechanism is provided to control the release of cloth from the container and maintain pressure in the inflating aerostat within a predetermined range.

Abstract: A lighter-than-air device comprises a buoyant element containing lighter-than-air gas, and a flexible surface having a length and height forming a usable area. The flexible surface has a bottom edge that is not connected to the buoyant element The length of the flexible surface is connected directly to the buoyant element. The flexible surface is operable to use an area defined by the buoyant element and the bottom edge of the flexible surface to, among other things, condense water, move a vessel, and block material from entering an area.

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: A device to provide control of the trajectory of a lighter than air vehicle, such as a balloon, is provided. A lifting device, such as a wing on end, is suspended on a tether well below the balloon to take advantage of the natural variation in winds at different altitudes. The wing can generate a horizontal lift force that can be directed over a wide range of angles. This force is transmitted to the balloon by the tether. Due to this force, the balloon's path is altered depending on the relative sizes of the balloon and the wing. A relatively small amount of power is needed to control the system, possibly with a rudder. As the energy of the wind provides most of the force, the wind's energy does most of the work. The balloon is able to avoid hazards, to reach desired targets, to select convenient landing zones, and to provide other operational advantages.

Abstract: An aperture-reinforcing device for flexible envelopes which are intended to be tensioned, and in particular for aerostat envelopes, includes adjacent first and second annular members. The envelope is passed successively over the inside parts of the surfaces of the first and second annular members, then the outside part of the surface of the second annular member, and then again over the inside part of the surface of the first annular member, between itself and that part.

Abstract: An autonomous stratospheric airship comprising a hull which contains an equipment bay, forward and aft ballonets, forward and aft air management sub-systems, a propulsion system, and a control system is described. The airship also comprises a regenerative solar energy power and storage sub-system which allows powered daytime and nighttime operations. Further, the control system of the airship enables autonomous operation between selected waypoints or along a specified line of sight. The solar arrays utilized by the airship are internally mounted within the bull and gimballed so as to provide maximum collection efficiency and not impede the aerodynamic profile of the airship. A greatly simplified and slightly less controllable version of the airship, which makes use of alternative solar array control and ballast management systems, while carrying the equipment bay on the exterior of the hull, is also disclosed.

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: A process for creating a flying light source including the steps of providing an inflatable balloon and associating a light source therewith. A retaining filament is attached to the inflated balloon. The light source may be a chemiluminescent lighting device which is attached to, or inserted into, the balloon. Alternatively, the light source may be a battery-operated light assembly attached to the balloon. The invention may be in the form of a rescue kit including the inflatable balloon, the chemiluminescent lighting device, the retaining filament and a lighter-than-air gas source. Alternatively, the invention may be in the form of a self-contained signaling device including a canister of lighter-than-air gas, a nozzle for dispensing the gas, the battery-operated light assembly, and the filament.

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 method of tracking airborne substances including the steps of detecting the presence of one or more airborne substances and releasing a tracking balloon into the path of the one or more airborne substances, the tracking balloon having a transmission means and a global positioning means adapted to communicate the latitude and longitude coordinates of the tracking balloon whereby the latitude and longitude coordinates of the tracking balloon are representative of the latitude and longitude of the one or more airborne substances previously detected.

Abstract: Based on a shape of gores of the Natural-Shaped Balloon, side edge parts of gores having a large width and a large length are connected to load tapes of a length equal to a circumferential length of a side edge part of the gores of the Natural-Shaped Balloon, in a state that wrinkles are formed uniformly and shortened on the side edge parts of the gores. As these gores are swollen out from between the load tapes from the beginning, the radius of curvature of the gores becomes small and the tension against the internal pressure of gas within a gas bag becomes small, so that higher pressure resistance is obtained. Further, a manufacturing method of the present invention is for connecting the side edge parts of the gores with the load tapes while shortening the length of the side edge parts. Thus, it is possible to efficiently manufacture this super-pressure balloon.

Abstract: An aperture-reinforcing device for flexible envelopes which are intended to be tensioned, and in particular for aerostat envelopes, includes adjacent first and second annular members. The envelope is passed successively over the inside parts of the surfaces of the first and second annular members, then the outside part of the surface of the second annular member, and then again over the inside part of the surface of the first annular member, between itself and that part.

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: An apparatus and method for floating such apparatus in the air, such apparatus having at least one cell containing air and a fluid. The fluid in one embodiment is heated to create steam which, in turn, makes the cell lighter than the surrounding air, thereby providing lift to the apparatus.

Abstract: A global communications network comprises a plurality of aerial platforms or vehicles deployed at an altitude in or near the stratosphere and permitted to drift in a controlled manner such that each platform adjusts its position relative to other aerial platforms. Each aerial platform has a propulsion system and control surfaces and preferably includes a lighter-than-air component to maintain lift in an economical manner. Each aerial platform also includes a payload, means for communicating with other aerial platforms and a control system including location-finding equipment and a processor adapted for directing the platform's propulsion system and control surfaces to effectuate changes in the aerial platform's position relative to other aerial platforms based on position information, and optionally on other factors such as terrestrial demand for services provided by the payload of the aerial platforms.

Abstract: A navigation system for spinning projectiles using a magnetic spin sensor to measure the projectile roll angle by sensing changes in magnetic flux as the projectile rotates through the earth's magnetic field is disclosed. The magnetic spin sensor measurements are used to despin a body reference frame such that position, velocity, and attitude of the projectile can be determined by using a strapdown inertial navigation system (INS) algorithm. More particularly, a multisensor concept is used to measure pitch and yaw angular rates, by measuring Coriolis acceleration along the roll axis and demodulating the pitch and yaw rates therefrom.

Abstract: An image guided weapon system employing passive optical terminal guidance d method which provides the precision strike capability without requiring the use of a designator or the presence of an additional designator aircraft, which can operate through the weather, which allows rapid attack of multiple targets, and which does not require any aircraft to remain in the target area after a weapon has been launch. A target area is designated and an image of the target area is generated. An aimpoint within the target area is selected and GPS coordinates of the aimpoint are determined. An image template is generated using flight orientation data, the image of the target area, and GPS coordinates of aimpoint. Image processing software creates an image template which is downloaded to a weapon. The weapon's seeker generates seeker images which are compared to the image template.

Abstract: The recoverable airborne instrument platform accurately determines its present position and uses this data to execute a predetermined flight plan and ultimately guide its descent to a predetermined landing site. This is accomplished by installing the instrument package payload in the aerodynamic exterior housing of the recoverable airborne instrument platform, which has a plurality of moveable control surfaces thereon to autonomously control the altitude, attitude and flight path of the recoverable airborne instrument platform. A navigation circuit contained within the aerodynamic housing determines the geographic location of the recoverable airborne instrument platform as well as the location of at least one predetermined recovery site. The determined position data is used to dynamically calculate a flight path which allows the guidance control circuit to both execute a predetermined flight plan and controllably descend the recoverable instrument platform to a selected predetermined recovery site.

Abstract: The scatterider guidance system is mounted on the flying object that is to e guided toward a more direct impact on the selected target. The system utilizes a designating beam of laser pulses that is emitted from the launch pad toward the target and atmospheric particles that scatter the laser pulses to calculate the guidance commands that lead the flying object to follow the laser beam closely. Upon detection by the scatterider sensors of the laser light that is scattered by the atmospheric particles, the perpendicular radial distance between the laser beam and the longitudinal axis of the object in flight is calculated by the onboard guidance electronics and subsequently used to generate the deflection commands. The deflection commands, in turn, are used to deflect aerodynamic control surfaces of the object such that the object approaches and stays close to the laser beam. This guidance system is activated as soon after launch as possible and continues until the object impacts on the target.

Abstract: A method for the autonomous guidance of a spin-stabilized artillery projectile (2; 25) toward a target (12). To ensure that an autonomously guided, spin-stabilized artillery projectile (2; 25) hits a target (12) with high precision, even at distances of .gtoreq.35 km, previously determined target data are transmitted to the projectile (2; 25) and stored therein before it is fired, and, following the firing of the projectile (2; 25), these stored data are compared with projectile position data, detected with the aid of a satellite navigational receiving station (23). The correction data resulting from this comparison are then used for the projectile (2; 25) guidance.

Abstract: A missile guidance system employs a strap down inertial measurement unit with a separate accelerometer and star sensor that are moved for preflight accelerometer initialization. During flight, light is directed on the accelerometer and inertial measurement unit to produce on the star sensor images of the light source, the accelerometer and the inertial measurement unit. The location of these images, which manifest the acceleration and position of the inertial measurement unit relative to the vehicle, are used to improve the accuracy of the inertial measurement unit data for vehicle guidance.

Abstract: A seeker head for target tracking missiles having an optical seeker de-coupled from the movements of the missile has a non-rotating platform (16), which is mounted in the missile for rotation about pitch and yaw axes about an origin (30), the platform carrying the optical seeker. A missile-fixed torquer assembly (74) for generating toques about mutually orthogonal axes (48,52) directly engages the platform (16). An inertial sensor unit (26) is mounted on the platform (16), the signals from the inertial sensor unit (26) being applied to the torquer assembly (74) to de-couple the platform (16) from the movements of the missile. A particular way of arranging the inertial sensorunit (26) and a particular design of the torquer assembly are described.

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 monopulse system generates sum (.SIGMA.), elevation difference (.DELTA..sub.EL), azimuth difference (.DELTA..sub.AZ), and double difference (.DELTA..sub..DELTA.) signals, and generates a covariance matrix. The covariance matrix is decomposed to produce at least the principal eigenvector. The location or angular direction within the main beam of a single target is determined from the real component of the quotient of elements of the principal eigenvector, by the use of a look-up table. In another embodiment of the invention, the eigenvalues are generated from the covariance matrix, and the number of significant eigenvalues determines the number of targets within the main beam. If a single target is found, its location is found as described above. If two targets are found in the main beam, the locations of the two targets are determined by a closed-form solution of quadratic equations.

Abstract: The invention is a material suitable for use as the wall of a pressurized container such as the gas bag of a lighter-than-air vehicle. In detail the invention includes a first flexible ply having filamentary material comprising unidirectional filamentary material at 0 and 90 degrees to each other. A second flexible layer is included having unidirectional filamentary material at 0 and 90 degrees to each other and at 45 degrees to the filamentary material of the first ply. The strain value at failure for the filamentary material of the second ply is greater than the 0 and 90 degree filamentary material of the first layer. The first and second plies are bonded together by a resin. Preferably, additional a film of gas impermeable material and a ultra violet radiation resistant material are bonded to the first two plies.

Abstract: A system for monitoring guiding and controlling an unmanned, unteathered flight vehicle, generally assumed to be moving through the atmosphere of the earth at a high rate of speed. The system comprised an on-board positional receiver and processing means coupled to a transceiver capable of combining such positional information with additional data relative to the health and status of the flight vehicle and transmitting the same to a ground station of compatible and simplified design. A preferred positional determination means is to utilize a form for GPS signal thereby affording one the opportunity to include appropriate processing software or additional componentry if necessary for base station purposes and thereby provide a relatively inexpensive system having a low probability of detection for intercept that simultaneously yields vastly improved operating performance characteristics over the mere translation of received GPS signals to down-link or to remote stations as known in the prior art.

Abstract: A protective ballute for a payload launched from an airborne platform includes an elongated shroud member, gas delivery apparatus for filling the shroud member with a lighter-than-air gas to inflate the shroud member. A payload as ballast is provided at one end portion of the shroud member for rendering the ballute heavier than air. Flight control and guidance apparatus is carried by said shroud member for determining a flight path and attaining a predetermined target landing site. A mechanism carried by the shroud member releases the payload from the shroud member upon reaching the landing site while maintaining said shroud member in its inflated state. The shroud member then rises or "floats" away from said landing site to another removed location, or if desired will self-destruct.

Abstract: A method and apparatus for directing a pursuing vehicle, such as a torpedo, on an intercept trajectory from a launching vehicle to a target vehicle th evasion capabilities. Models of the pursuing vehicle and evading target provide proposed trajectories based upon various environmental considerations. A guidance system uses estimates of initial operating parameter solutions, such as gyro angle, alertment time and intercept time, to begin a convergent, iterative process that defines final operating parameter solutions from which the guidance parameters are determined and transferred to the pursuing vehicle at launch. During each iteration, the solution determines an alertment time and an alertment bearing from the target vehicle to the pursuing vehicle at the alertment time. A selected evasive strategy includes a turn that is calculated relative to the alertment bearing.

Abstract: A stratospheric balloon comprising on the one hand an external flexible envelope (1) having a natural shape and made of transparent synthetic material and presenting an air inlet and, on the other hand, an internal screen (2) made of visible and infrared energy collecting material and having the shape of a surface generated by a mobile generatrix parallel to the longitudinal symmetry axis of the external envelope. The internal shield is connected to the envelope (1) by attachments arranged at the upper part of the envelope at a distance from the longitudinal axis of the latter, and extending longitudinally freely inside the envelope (1) without contacting it.

Abstract: A system and method for determining the angular orientation of a body moving in object space. The invention is usable to detect and identify the angular orientation of the body relative to the theoretical plane of gravity and thereby relative to any other theoretical plane between zero and three-hundred sixty degrees therefrom. The invention is operable regardless of whether the body is rotating with an angular velocity, either natural and/or induced. The invention may employ one or more analog and/or digital sensors. The analog sensor may be an accelerometer. The system may be used to provide real-time orientation data to permit the body to be guided or directed towards a desired destination or simply to permit the orientation of the body to be known, controlled or varied as desired.

Abstract: A supercavitating water-entry projectile having empennage on the aft end ch provides both aerodynamic and hydrodynamic stability and a supercavitating nose section is provided. A representative projectile is a subcaliber munition adapted for use in a 25 mm weapon using a sabot currently in use with the M919 round. The projectile has circumferential grooves around its center section to match these sabots. A key feature in the invention is the size and shape of the nose section. The projectile has a novel high strength extended blunt nose section followed by a truncated conical section which angles towards the body of the projectile in the range of five degrees. During underwater trajectory, the entire projectile is contained within the cavitation bubble formed by the blunt nose tip. The projectile's aft empennage, which provides both aerodynamic and hydrodynamic stability, fits within the bore of the weapon.

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: The present invention relates to a method and device for combating identified targets (F) using warheads (2) from a launching vehicle (1) flying over a target area, by separating from this launching vehicle (1) warheads (2) which act independently after separation, and including those targets which lie close to the flight trajectory of the launching vehicle (1) and those which lie well to the side of same flight trajectory. The invention is based on the use of that part of the kinetic energy of the launching vehicle (1) which the warhead (2) takes over from the same when it is separated in order to give the warhead (2) a looping trajectory or any other programmed flight trajectory, which carries it up to a starting height adapted to its active use, which lies considerably above the actual flight trajectory of the launching vehicle (1), and which, if so required, can carry the warhead (2) back to the geographical position where it was separated from the launching vehicle (1).

Abstract: A radiosonde balloon launching system including a silo for housing an array of radiosonde balloon modules and for sheltering radiosonde balloons during inflation, a base for containing radiosonde balloon inflation and launch apparatus and a device for shielding the silo until the radiosonde balloons are ready to be launched.

Abstract: A radiosonde balloon launching system including a silo for housing an array of radiosonde balloon modules and for sheltering radiosonde balloons during inflation, a base for containing radiosonde balloon inflation and launch apparatus and a device for shielding the silo until the radiosonde balloons are ready to be launched.

Abstract: In a method for determining the roll attitude of a rolling flying object having a radio receiver, in particular for guiding a ballistic flying projectile/rocket having roll compensation, the aim is to determine a line of sight between a transmitting source and the antenna and to determine the roll attitude therefrom.

Abstract: A module for automatically launching a radiosonde balloon having a battery powered radiosonde tethered thereto, the module including a housing for the radiosonde balloon and radiosonde; and an automatic balloon inflation and launch apparatus.

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: The balloon basket (1) according to the invention essentially comprises several pneumatic elements: an upper ring (2) and a lower ring (3), both advantageously segmented, are joined by a number of struts (4). The number of these struts (4) preferably corresponds to the number of corners of the polygonally formed rings (2, 3) and the number of their segments. Between the rings (2, 3) and the struts (4) side wall elements (5) are arranged so that they--apart from the holes (7) made in them--tightly seal the balloon basket (1) at the sides. In the lower ring (3) is fitted a floor (6). Side wall elements (5) and floor (6) are made with double walls and comprise at least in part of distance fabric such that the two corresponding walls of the side elements (5) and the floor (6) are held together by a plurality of threads and therefore retain their flat form on inflation with compressed air.

Abstract: A radiosonde balloon launching system including a silo for housing an array of radiosonde balloon modules and for sheltering radiosonde balloons during inflation, a base for containing radiosonde balloon inflation and launch apparatus and a device for shielding the silo until the radiosonde balloons are ready to be launched.

Abstract: A radiosonde balloon launching system including a silo for housing an array of radiosonde balloon modules and for sheltering radiosonde balloons during inflation, a base for containing radiosonde balloon inflation and launch apparatus and a device for shielding the radiosonde balloons until they are ready to be launched.

Abstract: A range correction module which is designed to fit onto a spin stabilized llistic projectile for correcting range error. The range correction module is a self-contained module within the fuze which screws into the forward portion of the projectile. The range correction module is designed such that changes are not required to the existing projectile. During the course correction phase, sixteen semi-circular plates will deploy from the module. The plates create a blunt cross-sectional area in front of the projectile, thus creating more drag and effectively slowing the projectile.

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: An integrated system and method for guiding an inflight missile during its boost phase to increase the accuracy of the missile flight and increase the probability that the missile reaches its intended target. The system includes four sub-systems that each perform a separate missile guidance function, but that each are integrated to form a single guidance system. The system includes a position rectified velocity wire guidance sub-system for steering the missile to maintain the same trajectory as determined in a prelaunch solution through measuring velocity error at a given position along the path of the missile. The system also includes an ignition delay sub-system for correcting missile position along the flight path by navigating position between burnout of the given missile stage and ignition of the subsequent stage, and modifying the ignition time to correct the missile position after all missile stages are burned.