Abstract: A method and system for aerially transporting loads between a loading site and a discharging site. A lift balloon is ballasted with liquid ballast at a discharging site and propelled to a loading site, where a load is suspended from the balloon. The liquid ballast is removed from the balloon in an amount corresponding to the weight of the suspended load. The ballast is recirculated from the loading site to the discharging site through a conduit. At the discharging site, the balloon is reballasted and the load is removed therefrom. The liquid ballast may also be moved through an aerial conduit connecting the lift balloon to a ballast site. In a further aspect of the invention, an elongated envelope houses a plurality of pear-shaped balloons to reduce the aerodynamic drag thereon.

Abstract: A modular improved forward section and improved aft section containing an tive-control package are disclosed which can be retrofitted to existing sphere-cone geometry reentry bodies (RBs) and which will provide improved aerodynamic performance and deployment accuracy of the RBs independent of missile error sources and drop sequence. An aft section containing control electronics, a propulsion system and steering jets permits the improve RB to actively correct for attitude and velocity dispersions occurring throughout the flight profile.

Abstract: A gondola for a hot air balloon utilizes a rigid carriage with external and internal walls forming an enclosure with a central opening sized for accommodation of crew members. A platform extends across and closes a bottom of the central opening. The external and internal walls are spaced and form an internal and integral reservoir for the carriage for storage of fuel for powering the hot air balloon. In one embodiment, a crew module accompanies the carriage, and the carriage is arranged for jetisoning in emergencies.

Abstract: A missile for airborne and seaborne use in which directional control about a flight axis comprises a nose (2) deflectable angularly in relation to the flight axis of the body (1) of the missile to form steering means by changing the fluid flow involve over the body (1) and means (4,5) between the nose (2) and the body (1) to effect angular deflection about a universal pivoting point (3) between the nose (2) and the body (1).

Abstract: A guidance system for small spinning projectiles which is mechanically simple, has low power requirements, uses relatively unsophisticated electronics, and is capable of withstanding large gas pressures and accelerations. The system uses a one-piece fin assembly which is de-spun so that its guidance fins maintain a constant attitude with respect to the ground. The guidance fins and their hub can be nutated simultaneously and independently in two orthogonal planes by pivoting and translating a single control rod. The hub cooperates with the projectile body to reduce its base drag and thereby extend its range.

Abstract: A system for automatically filling and launching balloons which may be used, for example, for cloud seeding. The system includes a balloon launching station frame, a nozzle mounted on the frame onto which the narrow end of a balloon can be attached so that gas can flow through the nozzle into the balloon, a conduit coupled to a source of gas and to the nozzle for delivering gas through the nozzle into the balloon, gas flow control apparatus responsive to first signals for controlling the flow of gas through the conduit, and a release mechanism responsive to second signals for disengaging the balloon from the nozzle to thereby release the balloon to the atmosphere. For launching a series of balloons, the system may include a plurality of nozzles, conduits, gas flow control mechanisms, and release mechanisms arranged so that after one balloon is filled and released, a second balloon may be filled and launched at a selectable time thereafter, etc.

Abstract: A naval harrassment missile for autonomously flying to a designated target area such as an enemy naval warship. The missile designed for searching, finding and harrassing the target. The missile may send a homing signal to guide other missiles to the target or by a homing signal attack the target using either a high explosive or a self-forging fragmentation warhead.

Abstract: A control system for rolling airframes utilizing variable pitch control surfaces includes a variable inertia device within the control system connected to the servo control motors that control the control surfaces, with the variable inertia device selectively controllable to optimize the inertia of the control system for optimizing the power requirements of the control system. The variable inertia means includes a rotatable mass with means for moving the effective position of the mass radially inwardly and outwardly from the rotary shaft of the control system for selectively varying the inertia of the control system.

Abstract: A projectile adapted to be given a rotation on being fired which makes the projectile spin-stabilized.With the object of facilitating the terminal guidance of the projectile or increasing the effect of an explosive charge with a hollow-charge effect carried by the projectile, the projectile is provided with stabilizing fins (6-9) which are extended at a desired point in the trajectory of the projectile and brake the rotation of the projectile. The projectile is so dimensioned that its center of pressure (C2) is situated behind the center of gravity (G) of the projectile in the extended position of the fins (FIG. 2) and so that the center of pressure (C1) lies in front of the center of gravity of the projectile in the retracted position of the fins (FIG. 1), so that, with braked rotation, the projectile changes over from being spin-stabilized to being fin-stabilized.

Abstract: A method and system for delivering ordnance to a target via a remotely piloted or programmable aircraft including a yaw-to-turn guidance system, a deployment and launching system and packaging for the aircraft are disclosed.

Abstract: A balloon-inflation and load-lowering device which comprises an inverted cup-shaped member containing one or more side-opening ports operative when covered by the neck of a balloon to cooperate therewith and form a one-way valve effective to trap the lifting gas inside the balloon once the latter is inflated and the inflation pressure released. Spaced-parallel disk-supporting arms journal a shaft mounting a notched disk. A load-letdown device is operative to slowly lower a load to the end of a tether.

Abstract: A spin-stabilized training missile is equipped with a stabilizer device for reducing spinning in order to decrease the flight range. The training missile is designed so that its stabilization attainable solely by the spin upon firing is not sufficient for a stable flight in the practice range. The required additional stabilizing in the practice range is obtained by a stabilizer device or control airfoil effecting simultaneously, after leaving the practice range, such a spin reduction that the training missile becomes unstable and the range of flight is controlled.

Abstract: In ammunition, preferably for machine cannons, including a subcaliber stabilized projectile equipped with a body of tracer material and a stabilizing element, the heat released during combustion of the tracer material is utilized to drastically change the strength of the material of an element used to fasten the stabilizing element to the projectile. By being able to set the time of combustion and of the change in the material, the stabilizing element changes its position with respect to the projectile. The system or ammunition in question becomes unstable and drops to the ground.

Abstract: A terrain-following transient surface contact vehicle for transporting a load from a surface starting point to a surface end point has a structure for carrying the load from the starting point to the end point. A vehicle support extends from the structure and abuts the surface and thereby supports the vehicle at a predetermined distance above the surface. An acquisition sensor mounted on the structure initiates surface operations. A sensor is mounted on the structure and cooperates with the acquisition sensor to sense and track a target at the end point upon initiation of surface operations. A power source is mounted on the structure and cooperates with the sensor to energize upon tracking of the target and to move the vehicle along the surface to impact with the target at the end point. A position control mounted on the vehicle produces a negative pitching moment to maintain the structure in terrain-following contact with the surface.

Abstract: A transient surface contact vehicle for transporting a load from a surface starting point to a surface end point has a structure for carrying the load from the starting point to the end point. A vehicle support extends from the structure. A buoyancy control device mounted in the structure is coupled to the vehicle support for selectively making the support buoyant and non-buoyant whereby when the support is buoyant it abuts the surface of a body of water thereby supporting the vehicle at a predetermined distance above the surface of the body of water. An acquisition sensor mounted on the structure initiates water surface operations. A sensor is mounted on the structure and cooperates with the acquisition sensor to energize upon tracking of the target and to move the vehicle along the water surface to impact with the target at the end point. A position control mounted on the vehicle produces a negative pitching moment to maintain the structure in surface-following contact with the body of water.

Abstract: A gun-launched ramjet projectile follows a classical vacuum ballistic trajectory by maintaining a thrust-drag balance. The thrust of the ramjet is varied by an air door which bleeds air from the duct that leads from the supersonic diffuser at the front of the projectile to the combustion chamber. The control system for the air door includes an actuator and a pair of accelerometers, the output of which is integrated to provide an indication of velocity. The first accelerometer operates during the launching of the projectile in the gun to measure the launch velocity. A second, and more sensitive, accelerometer measures in-flight velocity changes due to atmospheric conditions. Both of the measured velocities are compared with prerecorded standards and error signals are derived representing any velocity deviations. These error signals are combined and then used to drive the air doors which varies the thrust of the ramjet so that it follows the classical vacuum ballistic trajectory.

Abstract: A method of stabilizing flight of a flying body having a circular cross-section by the use of a plurality of tripping wires, when the flying body flies in an air current at a high angle of attack with respect to the air current. And also a flight-stabilized flying body having a circular cross-section, comprising at least two tripping wires attached to the periphery of said flying body. The tripping wires are attached to the outer periphery of the flying body, by which an asymmetric side force acting on the flying body is reduced, thereby suppressing bad motion of the flying body, such as, rotation around the center of gravity of the flying body in a plane of an attack angle, i.e. the flat spin, yawing and the like motion. In a case of attaching two tripping wires to the flying body, an optimal angle of wire attachment for suppressing the undesirable motion resides in a region from 60.degree. to 45.degree. for the non-dimensional wire height of a region from 0.007 to 0.014.

Abstract: Apparatus for transferring azimuth alignment with modest accuracy to the dance systems of individual missiles in a pod configured for vertical launch. The apparatus includes a mechanical interface between two rods (attached to the missile and oriented to the missile's guidance system) and two v-groove elements (attached to the launch tube and oriented to a northfinder mounted on the pod).

Abstract: The system for aiming of a missile strapdown Inertial Measurement Unit for ases in which the IMU does not possess the capability of self-aiming involves no mechanical link between northfinder and IMU which would require uncoupling prior to launch to avoid expending the northfinder. The technique maintains an automatic, hands-off capability by use of a laser link for azimuth transfer rather than a manual, optical link. The northfinder and laser system are launcher mounted and are therefore not expended with the missile.

Abstract: A fragile, movable apparatus such as a rotatable infrared optical prism assembly is mounted in a projectile housing on a crushable support pad. When the projectile is launched, the fragile, movable apparatus crushes the pad and receives effective support from the pad. After launch, a resilient member positions the fragile, movable apparatus away from the crushed pad and provides the necessary freedom of movement for the fragile, movable apparatus.

Abstract: A system for automatically filling and launching balloons which may be used, for example, for cloud seeding. The system includes a balloon launching station frame, a nozzle mounted on the frame onto which the narrow end of a balloon can be attached so that gas can flow through the nozzle into the balloon, a conduit coupled to a source of gas and to the nozzle for delivering gas through the nozzle into the balloon, gas flow control apparatus responsive to first signals for controlling the flow of gas through the conduit, and a release mechanism responsive to second signals for disengaging the balloon from the nozzle to thereby release the balloon to the atmosphere. For launching a series of balloons, the system may include a plurality of nozzles, conduits, gas flow control mechanisms, and release mechanisms arranged so that after one balloon is filled and released, a second balloon may be filled and launched at a selectable time thereafter, etc.

Abstract: A process for altitude-stabilizing an atmospheric balloon comprising ballast jettison mechanism to vary the balloon's specific weight, and using a balloon provided with an interpole link for actuating said ballast jettison mechanism so that an increase in the tension in the link causes a reduction in the specific weight of the balloon by jettison of ballast is disclosed.

Abstract: Apparatus for fast, accurate aiming of a missile from a launch vehicle. The pparatus permits fast accurate aiming of a missile inertial measurement unit for cases in which the inertial measurement unit does not possess required performance capability for self-aiming. The apparatus involves no optical link and is not expended with the missile.

Abstract: This invention relates to an improvement in an apparatus for advancing or retracting a flexible pay-out connection in a controlled manner, for instance a pay-out cable fixed to a satellite body with a pay-out means mounted thereon, in particular for a spin-imparted satellite, the improvement comprising at least one groove means at the periphery of the satellite body to receive the pay-out connection, and at least one elastic holding means to hold the pay-out connection at the groove opening.

Abstract: The invention concerns a spheroid container flattened at either pole. The structure is made from gores assembled along their edges. Meridional mono-directional reinforcements are fixed at intervals to the connecting lines of the gores. The gores are made of a material with a low elastic modulus and a high capacity for plastic elongation and the meridional reinforcements from a material with a high elastic modulus. An overpressure inside the structure causes it to take on the shape of a lobed spheroid, flattened at either pole. Application for closed balloons and pressurized containers.

Abstract: A gas leak proof sealing panel system is disclosed for a non-rigid airship such as a gas balloon. The sealing panel system is especially useful as a rip panel for rapid deflation of the airship. The rip panel covers an aperture in an envelope of the airship and is held in position by hook-loop releasable fastening type strips. Grease is applied to at least one of the strips such that when they are aligned and mated, a gas leak proof seal is formed.

Abstract: A projectile body has a gyro mounted therein including a rotor and a mechanism for supporting the rotor for rotation about a spin axis initially coincident with the longitudinal axis of the projectile body and pivotable away from the longitudinal axis of the projectile body. The rotor is initially locked to the projectile body so that it is spun with the projectile body during launch. Thereafter, the rotor is unlocked and the projectile body is de-spun to a relatively slow rate of rotation while transferring angular momentum to the free spinning rotor which continues to rotate at a high rate relative to the projectile body. Rotationally phased steering commands, which are generated from on-board homing sensor signals or up-link data signals received from a remote error sensor, are applied to a linear actuator within the projectile body. The actuator pivots the spin axis of the rotor away from the longitudinal axis of the projectile body.

Abstract: This invention relates to a method and equipment for fire fighting and rescue in conjunction with high rise buildings. A balloon having a capacity for lifting objects is coupled with a gondola for transporting people and equipment to and from an elevated location. The balloon is movable vertically relative to the gondola so that the balloon may be positioned out of the way once the gondola reaches a desired working height. Also, the balloon is compartmentalized so that, if one or more compartments become deflated, the remaining compartments will have sufficient lifting capacity to hold the gondola and its cargo. Elevator means on the gondola is provided for raising and lowering people and equipment to and from the ground so that the gondola and balloon need not be raised and lowered on a continual basis. A water gun and harpoon gun disposed on the gondola along with other necessary fire fighting equipment provide for complete fire fighting and rescue from the elevated location.

Abstract: A stress control mechanism for a space balloon is comprised of an axial tie member extending from the upper pole of a load carrying space balloon envelope, the tie member passing from the upper pole of the space balloon envelope through the balloon to an aperture located in a slideable member attached to the lower pole of the space balloon, a stopping member positioned at a pre-selected point on the axial tie member as a member for stopping the slideable member and thereby permitting the space balloon to assume a pre-selected shape upon inflation of the space balloon.

Abstract: A turbulence generator is provided on the forward end of a free flight ornce device to induce a turbulent boundary layer over the surface of the device. The turbulent layer generated is thicker than the normal boundary layer and helps reduce drag disparity between similar ordnance devices.

Abstract: The present invention relates to a method of providing thrust and added lift to a vehicle by accelerating fluid heated by solar energy. The present invention also relates to apparatus for carrying out the aforementioned method. Accordingly, the present invention relates to a method of providing initial acceleration and propulsion or enhancing the initial acceleration and propulsion of a vehicle in an environment having at least some fluid, the vehicle being of the type having at least one member, at least a portion of which is treated for absorbing solar radiation for heating fluid adjacent the member for use in propelling the vehicle through the environment. By use of direct and/or focused solar radiation, fluid is heated, accelerated and deflected away from a vehicle by natural or forced convection to provide thrust and lift of the vehicle.

Abstract: A lighter-than-air (LTA) aircraft having a valve structure affording the rapid removal of the lifting gas. The valve comprises a circular panel sewn within the envelope about an upper opening in the envelope for approximately one-third of its periphery and sealed thereabout by a releasable fastening tape. The sewn portion and tape portion of the valve being spaced 5 to 10 inches from the opening. A drape may extend beyond and depend from the fastening tapes. Gas may be exhausted from the aircraft in flight by collapsing opposed sides to force gas from a lower opening as is present in hot air balloons.

Abstract: For exploring the high density high temperature atmosphere of a planet at a stabilized altitude, a buoyant assembly comprising an inflatable envelope is used. A container connectable with the envelope and containing a liquid selected to vaporize in the planet atmosphere to an extent which decreases above the stabilized altitude and increases under the stabilized altitude, is launched into the planet atmosphere with the envelope in folded condition.

Abstract: A balloon envelope is disclosed which has the ability to minimize and isolate destructive tears, and which comprises a latticework of interconnected vertical and lateral reinforcing tapes which form open areas therebetween, and with a fabric panel overlying and covering each open area. The fabric panels are sewn to the surrounding tapes in a manner such that there is no direct interconnection between adjacent fabric panels. The envelope is fabricated by a procedure wherein the vertical gores, which are each composed of a vertical array of the fabric panels, are initially formed by sewing adjacent side edges of adjacent panels to intermediate laterally directed tapes, and then sewing a vertical tape component along each side of the resulting array of panels. The vertical side edges of the thus formed gores are then sewn together to form a sphere-like configuration.

Abstract: An unguided projectile achieves a flat trajectory by generating gravity-ctering aerodynamic lift. The lifting device is stabilized in roll by a displacement-type gyroscope which is mounted directly to the lifting section of the projectile. Both the lifting device and the gyroscope are mounted on bearings to permit free rotation of the projectile body relative to the roll-stabilized lifting section. Lift vector orientation is maintained irrespective of projectile roll.

Abstract: A method for steering solid propellant ballistic vehicles during powered flight which eliminates the requirement for cutoff control by allowing simultaneous fuel depletion and velocity-to-be-gained, V.sub.G, nulling. The vehicle booster is steered along a velocity trajectory of length equal to the remaining velocity capability, V.sub.CAP, which results in a fuel-inefficient trajectory. The trajectory is divided basically into three phases--an exit phase, a fuel-depletion guidance (FDG) phase and a short phase of constant attitude thrusting just prior to final stage burnout. For the exit phase the launch azimuth and the pitch-over magnitude can be varied from their usual fuel-efficient values. During fuel-depletion guidance the additional degree of freedom is the angle, .theta., between V.sub.G and the desired thrust direction, U.sub.S, where: ##EQU1## a.sub.T being the sensed acceleration vector.

Abstract: The method of the invention for launching especially large-volume space balloons consists in using a space balloon (8) equipped with a non-stretching or slightly stretching axial tie (9) to which is fastened the upper pole of the balloon and alongside which the lower pole may slide, in using an auxiliary carrier balloon (1) of a lesser volume and provided with a non-stretching axial tie (2) between its upper and lower poles, in fastening the collapsed space balloon (preferably housed in a protective sheath 22) underneath the carrier balloon by connecting the axial ties of the two balloons, and in arranging a transfer duct (7) between these, in partially inflating the carrier balloon (1), and, after transferring a given amount of gas into the space balloon, in inducing the sealing of the transfer duct (7), the separation between the space balloon (7) and the carrier balloon (1) and the locking of the power pole of the space balloon on the axial tie (9) of same.

Abstract: A projectile for use with a smooth bore barrel is disclosed wherein longitudinal stability is provided by an oscillating mass within the projectile. A mass is disposed inside the projectile and attached and secured to the projectile by means of a bi-convex spring or equivalent flexible structure so that the mass is set off in oscillation upon the sudden acceleration due to the firing of the projectile. The inertial forces developed by the oscillating mass provide stability throughout the projectile's trajectory.

Abstract: An aerodynamic lift-generating adapter assembly secures to the nose of an guided projectile to provide a capability for flat-trajectory flight. The adapter assembly comprises a rotatably-supported, roll-stabilized lift-generating section coupled to an actuator section containing inertia means to initiate gyroscope rotor spinning. The control gyroscope is directly linked to the lift-generating device to maintain fixed orientation of the lift.

Abstract: A propulsion system for airbreathing vehicles having a ducted inlet for a supersonic powerplant and incorporating means in the vehicle for momentarily changing the normal flight attitude of the vehicle for obtaining high inlet pressure recovery for the propulsion powerplant and thereafter returning the vehicle to a normal flight attitude.

Abstract: A vehicle for the exploration of the atmosphere comprising an infra-red and olar montgolfier (hot-air balloon) capable of being piloted reversibly. The vehicle comprises a gas-tight envelope in which the upper part of the envelope is either transparent to or slightly absorbent of infra-red radiation, the outer face of the upper part of the envelope is slightly emissive in the infra-red region of radiation and the inner face of the upper part absorbs infra-red radiation so that ascending forces which act on the montgolfier are only obtained as a result of the heating of the gas contained in the envelope which is produced by the absorption of infra-red radiation.

Abstract: An inflatable ornament suitable for hanging on a Christmas tree limb or the like is formed from a pair of flexible plastic sheets joined along their periphery to define a collapsible, substantially fluid-tight envelope. The envelope includes a reduced neck portion having a valve therein for filling the ornament with a suitable fluid such as air. The valve comprises a stem extending laterally outward from one of the sheets and a removable plug for sealing the stem. A hook member connected to the stem, or formed integral with the plug, is adapted to suspend the ornament from the limb. A reflective metal coating applied to the envelope gives the appearance of a glass ornament.

Abstract: A target acquisition and designation system is disclosed which enables an aircraft to perform aerial reconnaissance and surveillance, strikes of fixed or mobile targets, and other defense missions while at an altitude below which detection by enemy radar is effective. The system utilizes a very small, stealthy, unmanned glider equipped with a Forward Looking Infrared (FLIR) image sensor and a laser designator. The glider is towed by the aircraft and remotely controlled to fly at an elevation high above the aircraft where the FLIR and laser designator can be effectively utilized. A lightweight towline comprising one or more load-bearing tension members surrounded by a flexible member having a symmetrical streamlined exterior shape substantially reduces drag and allows the glider to be deployed from conventional aircraft.

Abstract: A method and apparatus are disclosed which are particularly adapted to quickly de-spin a rapidly rotating object or projectile. Weights are released from the object in a series of distinct stages, thus discarding enough momentum to reduce the spin of the object to a desired minimal value. The weights are released simultaneously by a single release means thereby assuring perfectly symmetrical and synchronized release of the respective weights. The result is a pure de-spin of the object without imparting other motion to the object.

Abstract: A decoy missile having a high moment of inertia with a corresponding reduction of the natural oscillation frequency for simulating reentry of a ballistic nose cone into the earth's atmosphere. High density ballast material disposed in the forward section is in proportional relationship to similar ballast material in the base section such that the distance between the center of pressure and the center of gravity is equal to one-half the base diameter.

Abstract: A non-spinning projectile for combat use against battlefield targets has a tapered paramidal shape with a sharply pointed nose. A supersonic launch speeds the nose causes formation of a generally conical shock wave. Along its length aft of its nose, the projectile has two fin-like projections spaced apart on each side of a symmetrical undersurface and adapted to capture the shock wave so that its pressure effects provide lifting force to the projectile undersurface.

Abstract: A combustion device for use with pressurized and zero pressure hot air balloons or other hot air appliances, which comprises in general, a coanda-type inlet nozzle, a diffuser, a flame-arrestor screen, and a fuel preheater means for supplying required fuel vapor at a desired pressure to the inlet nozzle. The combustion device may be used with any suitable fuel, but it is primarily applicable to propane. The combustion device is a fuel pressure driven-nozzle-mixer-diffuser-arrestor screen burner combustion device which generates a stream of heated air for the transfer of thermal energy to a load.

Abstract: A technique for sensing both the earth generated electromagnetic and electrostatic fields is employed on board a remotely guided spin-stabilized projectile or missile in order to accurately determine a vertical reference direction and provide for proper response to received guidance information during the entire flight trajectory.

Abstract: An unconventional advanced air-to-surface weapon of monowing configuration, and having a symmetrical, high lift fuselage of lenticular (i.e., biconvex or oblate) cross section, with a width-to-thickness fineness of approximately 2.5. The longitudinal profile is modified Sears-Haack in two dimensions, truncated at the base for a rocket nozzle. The weapon comprises a nose portion modular forebody, a weapon payload portion modular midbody, and an aft boattail modular portion which are combined into one unit that is selectively separable into its modular components when used. A variation of this weapon is also taught which features a semi-lenticular fuselage cross section (i.e., one flat side) and a width-to-thickness fineness of approximately 2.1.

Abstract: The launch mode for a cruise missile utilizes a solid propellant booster ket to propel the missile from the launch platform to a speed and altitude sufficient to enable the missile to transition to the cruise flight mode. Immediately following booster burnout the missile jettisons the booster and transitions to cruise flight by deploying aerodynamic lifting surfaces and starting its cruise engine. The shaped trajectory launch mode significantly reduces the required booster motor impulse by deploying the cruise missile wings during boost flight. The aerodynamic wing lift enables the missile to fly a flatter trajectory reducing performance lost in climb and results in higher booster burnout velocity and significant improvement in launch performance.