Abstract: A multi-node Lambert Guidance System that controls missile velocity along a missile flight path through adjustment of missile attitude during guidance of the missile through an intercept point and one or more way points. The system utilizes a linear Lambert solution in that it is derived from a plurality of Lambert solutions each corresponding to a particular node along the prelaunch flight path solution and each including corresponding time varying weights on the accuracy at several flight path nodes. The present invention allows direct translation of guidance velocity corrections into vehicle attitude adjustment commands, and thereby avoids additional computation required in prior predictive integration guidance approaches.

Abstract: The invention monitors the driving range and tracks golf balls from users at the driving range and informs those users of characteristics such as driving distance. A solid state camera images the range, and preferably one or more tee-off positions, and collects frames of image data to track a ball's motion through space. Simulation routines augment that track and assist in isolating the start location as well as where the ball lands, or would have landed had it not been obstructed (e.g., by a net). Preferably, the invention also determines the ball's position in 3-D to increase the accuracy. In one technique, two or more solid state cameras are used, and synchronized, to specify stereoscopic imaging. In another technique, the ball's energy or physical extent is used to determine an absolute distance between the camera and the ball. A computer at the club house monitors the entire system and further manages a network including an array of displays at the several tee off positions.

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 ignition delay timing system, and corresponding method, for adjusting the position of an in-flight missile during its boost phase along its flight path according to a pre-launch flight path solution. The ignition delay system of the present invention is applied by navigating missile position between burnout of a given booster stage and ignition of a subsequent booster stage, and modifying ignition time of the subsequent boost stage so that the missile position along its flight path follows a pre-launch solution after all booster stages are burned. Nominal missile coast phases, which occur between burnout of one booster stage and ignition of subsequent booster stage are either increased or decreased for earlier or later booster stage ignitions to maintain the missile position along its flight path in accordance with the pre-launch solution.

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 missile intercept system using radiation sensors for guidance that can avoid intercept uncertainty due to unfavorable positions of intense radiation sources, like the sun, moon, or countermeasures flares. When the sensor viewing angle is close to such intense radiation sources, the optics on the kill vehicle may be substantially degraded or even destroyed. The potential for an "out of the sun" attack cannot be avoided when international treaties restrict each country to a single defense site while potential launch sites are proliferating about the globe. Therefore, two kill vehicles are launched when an intercept planner determines that the viewing angle from the kill vehicle to the target vehicle will be looking at or near the sun during the engagement. A surrogate kill vehicle is launched on a trajectory that will "fly-by" the target vehicle with viewing angles that will not "see" the sun.

Abstract: A system of articulation units is inserted between sections of a standard lindrical underwater vehicle, such as a torpedo, to provide a highly maneuverable vehicle. Each articulation unit consists of two bulkheads connected by a spherical joint which allows rotation about the joint. The bulkheads are connected to adjacent torpedo sections by means of standard joint bands. A number of hydraulic actuators are spaced radially about the spherical joint between the bulkheads. By selectively activating the actuators, the joint bends the vehicle about its longitudinal axis. The pressure of the surrounding medium against the moving vehicle causes the vehicle to turn in the direction of the bend. Depending on the actuators activated, the vehicle can be made to bend, or turn, in any direction, making for a highly maneuverable vehicle.

Abstract: An airship has a flexible gas storage tube which forms a frame that maintains an inflated condition of an envelope of the airship permitting the envelope to be charged with hot air. A pump and valve are provided for supplying gas such as air, helium, and hydrogen to the gas storage tube.

Abstract: A missile has a non-cylindrical fuselage over at least a portion of its length, with a non-cylindrical propulsion system contained within the non-cylindrical portion of the fuselage. The fuselage and propulsion system are preferably generally elliptical in cross section, with a dimensional ratio of the major axis to the minor axis of from more than 1:1 to about 1.5:1. The missile further includes a guidance system and guidance control features.

Abstract: To mitigate groove drag in a kinetic energy projectile, an intumescent maial is inserted in the grooves wherein the material will expand to fill the grooves once the sabot has been discarded. The groove material inhibits aerodynamic recirculation that can occur in the grooves, fills the groove and keeps out freestream gasses. The expanding groove material occupies the space previously filled by the sabot tooth. The groove-filling material expands quickly, because the flight of the projectile is typically on the order of one to two seconds. The groove filling material may also be an elastic material.

Abstract: A tail piece for a projectile includes at least three fins connected to either the projectile itself or a bracket connected to the projectile. Each fin is linked to the projectile/bracket by at least one fastening foot that cooperates with at least one recess of the projectile/bracket.

Abstract: A burner system for a radio-controlled hot air balloon. The frame that is connected to an envelope contains two fuel tanks. One fuel tank is disposed right side up and delivers fuel in vapor form to a pilot burner mechanism. The other fuel tank is inverted and delivers in liquid form to a burner coil means. The flame of the pilot burner mechanism partially heats the liquid fuel in the burner coil means so that when a valve member is opened, fuel in a vaporous mist form is discharged from an outlet orifice of the burner coil means for ignition by the flame of the pilot burner mechanism. A radio-controlled servo is connected to the valve member and operates the same.

Abstract: A fin stabilized projectile for combatting a tank from above of the type including a rotating control unit disposed at the front of the projectile and containing a sensor for scanning the area to detect a target, and wherein the final phase of flying into the target is initiated by a force which acts on the tip of the projectile, particularly on the control unit. Since the control unit rotates relative to the warhead of the projectile to enable its sensor to detect the target, the gyro effect of this rotary movement generates pendulum movements in the projectile and thus causes deviations from the target at different target distances. To avoid yaw angles and lateral displacements of the projectile during the rotating-descending phase, a drive arrangement is provided within the projectile between the control unit and the warhead to impart an angular momentum to the warhead corresponding to the angular momentum of the control unit but directed in the opposite direction.

Abstract: This invention provides improvements to flying toy models of hot-air balloons which use helium instead of hot air for lift.An object in the shape of an inverted receptacle is inserted into the mouth of the lifting envelope and serves to accurately replicate the shape of the neck and the open mouth of a full-sized hot-air balloon lifting envelope. A novel method of assembly incorporates the inverted receptacle into the lifting envelope and provides for the efficient attachment and detachment of the gondola to the lifting envelope.

Abstract: An expandable ogive is disclosed which incorporates a plurality of sections (20, 22, 24) which move into an extended position. The ogive is locked in the extended position by mating tapered surfaces on the piston sections of an actuator (44) which are tapered at an angle of less than about 2.degree. relative to the center line axis of the missile or rocket. The mating surfaces lock sufficiently tightly to resist the aerodynamic loadings on the ogive during missile or rocket flight and therefore maintain the proper ogive configuration independent of the gas pressure in the actuator (44) which initially moves the ogive sections into the extended position.

Abstract: The oxidation resistance of elastomeric balloons made from natural rubber is greatly improved by coating the exterior of the balloon with a film of uncured elastomer, preferably neoprene. The uncured elastomer coating maintains the clarity of the inflated balloons. These balloons are particularly useful as containers for gifts or in balloon sculpture.

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: An airborne monitoring system for measuring conditions in the lower atmospheric boundary layer of a tropical cyclone or other concerted atmospheric systems. The system flies on the wind. In the case of a tropical cyclone it flies over the sea, into the eye and tracks the storm, transmitting meteorological data and receiving commands from a remote base station. The system includes a hybrid lifting body tethered from a line contacting the surface of the sea. It is maintained in aerodynamic and hydrodynamic balance at a substantially constant altitude.

Abstract: The invention offers a novel way to enhance the time of a surveillance paad over a target area. It provides a relatively inexpensive way to position an unmanned reconnaissance payload over a potential target area, using a cargo projectile launched from a conventional tubed artillery piece, under all weather and environmental conditions. The use of tow line between the ejected reconnaissance payload and the ballistic cargo projectile allow the payload with its parafoil to achieve a greater height, enter an orbit and extend a longer time over the target area.

Abstract: A flexible, aerodynamic inflatable nose fairing for use in combination with flat nosed canister launched missiles having a wide circular cylindrical shape. The inflatable nose fairing is fabricated as a fiber-reinforced elastomeric membrane having a laminate construction which includes a silicone rubber inner or base layer as the gaseous pressure membrane or bladder, surrounded by two or more ply layers made up of resin-impregnated yarns. In a preferred embodiment, the silicone rubber bladder is applied to a generally conical shaped mandrel. The first ply layer is fabricated by hoop winding resin impregnated yarns on a constant diameter cylinder and then cutting to form gores. The gores are applied to the conical shaped mandrel such that the gore fibers are oriented in the axial direction of the conical shaped mandrel.

Abstract: A flexible, aerodynamic inflatable nose fairing for use in combination with flat nosed canister-launched missiles having a wide, circular, cylindrical shape. The inflatable nose fairing is fabricated as a fiber-reinforced elastomeric membrane having a laminate construction which includes a silicone rubber inner or base layer as the gaseous pressure membrane or bladder, surrounded by two or more ply layers made up of resin-impregnated yarns. Also disclosed is a deployable mass assembly and sensor for providing improved missile control. The deployable mass assembly includes a telescoping actuator which is effective to provide stabilization control to the missile by shifting the center of gravity of the missile forwardly to compensate for a change in the center of pressure of the missile due to the change in length of the missile which occurs as the nose fairing is inflated into its deployed position.

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: A gun launched projectile design which imparts forces to a subcaliber protile comprising: a subprojectile, a multi petal sabot, a pusher plate, and an obturator. The petals are of different length and have a scooped-out design on the face thereof, so as to induce a specific level of yaw to the projectile.

Abstract: A balloon distribution system that utilizes balloons retained within an elongated, tubular storage area. Upon receipt of a signal from a remotely located controller, the previously-placed inflated balloons are propelled from the storage container, and float down upon the people gathered below. The tubular body is mounted above the crowd in a manner such that the open end of the tube is slightly elevated in comparison with the adjacent section of the tubular body, preventing the stored balloons from spilling from the tube. A thruster housing is attached to the closed end of the tubular body, and the housing terminates in discharge face having a plurality of outlet nozzles extending into the cavity within the tubular body. A motor and fan supply the airflow, which flows through the thruster housing and into the tubular body through the plurality of nozzles. The motor is actuated via a signal received from a remotely mounted controller.

Abstract: A missile includes a missile body having a nose, a tail, and a center of gravity therebetween. A plurality of blades are arranged symmetrically around the missile body at a location between the nose and the center of gravity. The blades are deployable from a stowed position folded flat against the body of the missile to a deployed position extending outwardly from the body of the missile, and are mounted so as to be biased toward the deployed position. A retaining wire extends circumferentially around the body of the missile and captures the blades thereunder. The retaining wire may be controllably severed by a pyrotechnic device to release the blades to extend to the deployed position. The extended blades cause the missile to tumble from a first stable orientation to a second stable orientation, permitting it to be quickly pointed in the opposite direction without expenditure of fuel.

Abstract: The invention concerns a fastening arrangement between the hose-like neck (11) of a sonde balloon (10) and the closing piece or valve piece (13) of the balloon. The closing piece or valve piece (13) can be fitted inside the hose-like neck (11) of the sonde balloon (10) as gas-tight. The fastening arrangement comprises a fastening ring (12), which can be fitted onto the free mouth part of the neck (11) of the sonde balloon. Hereupon, the outer end (11a) of the mouth part of the neck (11) can be folded outside and over the fastening ring (12) onto the neck part (11) placed on the cylinder part (13b) of the closing or valve piece (13), the neck (11) thereby becoming two-fold. The inner diameter (D.sub.1) of the fastening ring (12) has been dimensioned smaller than the diameter (D.sub.2) of the cylinder part (13b) of the closing or valve piece (13).

Abstract: An integrated roll control and power supply system for a missile includes a pair of flywheel-motor-generator (FMG) units, a pair of power flow control (PFC) units coupled between the FMG units and a missile load, and a roll sensor coupled to the PFC units. The integrated system also includes a pair of resistance heaters and a pair of clutch-brake devices. The FMG units are axially aligned and displaced from one another. One FMG unit operates in a counterclockwise direction, while the other FMG unit operates in a clockwise direction. The two FMG units produce the bi-directional roll torque characteristic necessary to develop roll-dampening torques for the missile system roll control autopilot.

Abstract: A balloon member includes a plurality of partition walls coextensive within the balloon to divide the balloon into equal quadrants to accommodate safe descent and enhance inflation of at least a plurality of the quadrants during a leakage of air from the balloon.

Abstract: Polyvinyl alcohol coatings used to improve the bouyant life of elastomeric balloons include polyvinyl alcohol and a water soluble carbohydrate extender such as dextrose, at levels up to four times the weight of the polyvinyl alcohol. The improved coatings of the present invention typically give double the floating life of the balloon under a wide range of humidities.

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: An air floater comprises a balloon body which seals a gas therein and balancing means detachably attached to the balloon body. The balloon body comprises a film composed of a central layer made of ethylene-vinyl alcohol copolymer-resin, an aluminum evaporated layer provided outside the central layer, and a heated adhesive layer provided inside the central layer. The balancing means comprises a plurality of magnetic cards which are attracted by an attraction portion composed of a magnetic body attached to the balloon body. The plurality of magnetic cards includes one card having a reference weight matched with the buoyant force of the balloon body, first weight balancing cards having weight heavier by stages than the reference weight, and second weight balancing cards having weight lighter by stages than the reference weight. The balancing means may comprise sublimate sealed in a bag body.

Abstract: The subject device is a balloon weight and holding device having and storing a balloon tether means and adapted to be attached to a balloon and functioning to prevent a balloon filled with a lighter-than-air gas from rising above a given tethered length, such device comprising in general a spool member having a central cylindrical shaft flanked on each end by opposing circular plate members, each such plate having a circumferential rim. The spool member has the balloon tether wrapped around it to be unravelled at will. Integrally disposed between the inner face of such circular plate members are integrally affixed means to retard the process of unravelling of the balloon string so that the balloon string and thus the balloon do not become beyond the control of the person holding the balloon.

Abstract: The system may be used, for example, to initialize the inertial unit of a missile from the inertial unit of a vehicle carrying the missile. According to the invention, a servo-control circuit is provided for slaving data in the missile inertial unit on data from the carrier inertial unit, together with a Kalman filter connected in parallel with said servo-control circuit and designed to identify harmonization errors between the two inertial units.

Abstract: A radio controlled hot air balloon, particularly suitable for use by hobbyists, includes a balloon envelope, a burner assembly and a radio control system. The altitude of the balloon is remotely controlled by adjusting the amount of hot air produced by the burner assembly.

Abstract: A projectile which would ordinarily be a spinning artillery shell is segmented so that the forward segment can be deflected relative to the rear segment for aerodynamic directional corrections in flight. Fins provide the projectile spin and a motor in the rear segment rotates an angle drive means with a velocity equal and opposite to the rotation of the rear segment, so that the angle drive means can establish an angle which has a fixed orientation on an earth coordinate reference frame despite the spinning of one or both portions of the projectile. Ground or sea-based radio and radar communications or an on-board roll reference system continuously communicates with the projectile, informing it of its own rotation rate and providing command signals for the nose deflection needed to establish the proper real-time trajectory correction.

Abstract: A fuselage, particularly of a guided missile, having a rotatable nose body carrying a pair of similar strakes symmetricaly disposed about the body and for anchoring incidence generated vortices thereon.

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.

Abstract: A novel composite material in the form of a laminate is disclosed which has particular utility for forming gas-holding structures such as hull structures of aerostats. The laminate is composed of plies wherein a polyester fabric/strength member which is woven from a polyester yarn having low shrinkage, laminated to an amorphous, thermoplastic polyester film that provides distortion and shrinkage resistance during manufacture of the composite and fabrication into hull structures of an aerostat. The composite utilizes a thermoplastic polycarbonate polyurethane film on each side of the fabric to provide a dual gas barrier, weatherability, and a wear layer. The hull structure can be fabricated by radio frequency, thermal heating or adhesive cement techniques to provide structural seams on either side of the laminate material.

Abstract: The invention provides a double-walled, annular balloon which requires less gas to inflate than its volume would indicate. The balloon is formed of double-walled gores joined by continuous overlapping seams, in the longitudinal direction, with intermittent seams in the latitudinal direction, to divide each gore into a serious of connecting inflatable compartments. Each gore is connected to a common plenum which is connected in turn, to a compressed gas container. The gores are inflated at the same time from such common plenum and the balloon, when inflated, can appear as a globe having longitudinal and latitudinal seams therearound with the common plenum contacting the gores at proximate the north pole, thereof. Each gore terminates in a seam proximate the south pole, which seam defines a closed loop which forms an entrance port into such balloon.

Abstract: A tethered surveillance balloon having a relatively low lift-to-weight ratio (e.g., 1.1) and an aerodynamic device to help maintain the surveillance balloon elevation when subject to high velocity wind conditions at an altitude which is a high percentage of the altitude the surveillance balloon would assume if there was zero wind velocity and all other conditions were the same (e.g. temperature, air density). The surveillance balloon also includes a sensing device such as a TV detector for detecting objects and relaying information to a ground station and with possibly a target designation device, if so desired. The balloon is formed of a material which is virtually, if not entirely, radar and visibly transparent.

Abstract: A spooled optical fibre data transmission line arrangement, for providing communication between a missile and a missile launcher, comprising a rigid, fluid-tight, hollow body having first and second separable parts, the optical fibre being carried by one part and connected at one end via an opto-electric transducer to a terminal extending through the wall of that one part, and the other end of the fiber being connected via a second opto-electric transducer to a terminal extending through the wall of the other part. The two separable parts suitably meet at a tear line and tags extend from adjacent the tear line on one part to the other part ot assist in complete rupture along the tear line when the fibre is required to be extended.

Abstract: A high altitude, high pressure balloon comprised of a number of gores. The gores are made from a material and have a size, that are the results of an analysis of the anticipated stresses to which the balloon will be subjected. In particular, the gores are made from nylon and have dimensions that have been determined to result in stable creep characteristics. An alternate embodiment of the balloon uses multiple spheres.

Abstract: A closed-system hot gas device for flotation in the atmosphere having a rigid cap and flexible sides with an interior gas-heating element.

Abstract: In a launcher control system (12), a missile interface unit (29) for controlling a ground launched active radar guided missile (GLA) which is modular in construction. The missile interface unit (29) provides target position information and control signals for test and launch of the GLA, and power for activating the GLA, as well as determining the status of the GLA. It employs a plurality of cards (56-70), each card having a specific function and being interconnected by a backplane bus system (55) which also couples the cards (56-70) to other components of the launcher control system (12).

Abstract: A glide missile is provided with trimming devices for affording a positive ngle of incidence. The trimming devices are controlled by the combination of a fluidic element through which ram flows and a gyroscopically controlled shutter.

Abstract: The present invention is a balloon system for transporting a load wherein an aerostat is movable, both horizontally and vertically, throughout a working area defined by the guy lines that anchor the aerostat. Such area can include multiple pickup and discharge points. The balloon system is especially useful for logging in inaccessible or rugged terrain and transporting heavy loads between widely separated pickup and discharge points with intervening obstructions rendering group transport difficult. Individual loads may be picked up at any point within the working area for movement to a discharge point for unloading, after which conventional load handling equipment may be used to handle the load. A plurality of at least three guy lines radiating downwardly from the aerostat anchors the balloon to individual and separately controllable ground-based guy line control and storage apparatus. Each control apparatus is controllable to extend or retract its respective guy line.

Abstract: The invention relates to an aerostat of the double balloon type intended to travel in an autonomous and reversible manner between the ground of a planet having an atmosphere and a predetermined ceiling altitude. This aerostat is of the type comprising a first closed carrier balloon (1) for containing a gas lighter than the gas present in the atmosphere, and a solar hot air balloon (3) comprising a permanent opening (6) permitting its filling by the gas present in the atmosphere. According to the invention the solar hot air balloon is provided at its upper extremity with an opening defined by an annular border, and means for sealingly securing this annular border to the peripheral wall of the carrier balloon (1), such that said carrier balloon extends partially into the interior of the envelope of the hot air balloon (3).

Abstract: A radio-controlled flying apparatus comprising an annular buoyant body and having an overall center of gravity below the center of buoyant force of the buoyant body. The annular buoyant body contains a gas of lighter weight than air. A main body is supported by the annular buoyant body by means of a dual-axis gimbal. The main body is provided with a pair of propellers which are rotatably supported by the main body and are driven by variable-speed motors into rotation in opposite directions. The main body is further provided with a rocking mechanism for causing said main body to rock about the dual-axis gimbal. An electric circuit resides in the main body for receiving a radio wave from an external transmitter to control the rocking mechanism and variable-speed motors. The electric components in the electric circuit are supplied their power from a battery carried on the main body.

Abstract: A outer bail gimbal bearing having a closed loop filled with circulating ls is disclosed. The balls circulate about an axis parallel to the bail's axis of rotation. A shallow region within the loop allows the balls to emerge from the loop and engage a race made in the outer edge of the outer bail.