Abstract: The invention relates to a drone-type missile for combatting ground targets from the ground, particularly for the use against targets which emit electromagnetic rays, such as radar stations; with built-in target-seeking head, guidance system, self-propulsion and take-off assist, preferably a booster rocket.

Abstract: A reaction-jet torquer system carried in a projectile to aim the projectile o a target. The torquer system uses the thrust of sonic nozzles to control a gyro rotor inertial frame of reference. The reaction force applied to the gimbal gives the rotor the capability of tracking the target. A sensor carried by the gyro provides logic which identifies and activates the appropriate nozzle or nozzles of the system to generate the required gimbal force.

Abstract: A balloon or airship having a hull of flexible material is provided with a deflation opening in the hull and a rigid frame permanently fastened to the edge of the opening. A ring of flexible sheet material has its peripheral edge removably clamped to the rigid frame. A disc of flexible sheet material larger than the central opening in the ring is fastened by an adhesive to the ring all around the central opening in the ring. A deflation tape sewed to the disc near the edge of the upper half thereof has a central free end to be pulled for peeling the adhesive-held disc from the ring to rapidly deflate the balloon.

Abstract: A toy hot air balloon constructed of a plurality of elongated gores fashioned from light-weight, thin material. Each of the gores has an opposed pair of long and short edge portions. The gores are sealed in side-by-side configuration at the long edge portions to form an enclosure having a top portion and bottom portion. The bottom portion includes an opening for the admission of hot air. The balloon further includes a mouth area which is reinforced and possesses a higher stiffness than the remaining portion of the enclosure. Each of the ends of the gores are fastened to the mouth of the enclosure. A support permits the suspension of the toy hot air balloon while filling the same with hot air.

Abstract: An inflatable envelope surrounding a compression beam, at least one flexible traction beam associated with the compression beam and surrounding envelope. The traction and compression beams are coplanar and at least one flexible diagonal mechanical network is interposed between the beams integral therewith. The envelope, the compression and traction beams and the diagonal network are connected together so that the inflation of the envelope maintains the assembly of these elements in shape.

Abstract: A solar powered hot air balloon with a maneuvering system is disclosed. The balloon is formed of an envelope with an opaque portion and a transparent portion arranged so as to utilize solar heating to heat air within the envelope. The opaque portion of the envelope has a substantially black inner surface and a light reflecting outer surface with the black inner surface being positioned so as to receive a maximum amount of sunlight through the transparent portion for a given location of the sun. Ascent and descent maneuvering is accomplished by changing the rotational position of the balloon relative to the position of the sun so that more or less portions of the black inner surface receive sunlight to thus generate heating within the envelope. The maneuvering system includes a pair of propulsion units positioned on opposite sides of the balloon. In one embodiment, two light sensors may be provided which are connected to a control unit.

Abstract: An aircraft is constructed of an airfoil shaped inflated involucrum of lightweight gas-impervious plastic film. The airfoil is maneuverable to attain forward self-propulsion upon ascent as well as descent. The gases contained in the involucrum are heated by solar radiation to reduce craft density with the upper surface of the airfoil being translucent and the lower surface of the airfoil interior mirrored for concentration of the radiant energy upon an interior cylindrical black spar. A honeycomb reradiation barrier is provided beneath the translucent surface. In one embodiment a large volume involucrum is changeable in camber to maximize forward propulsion. The craft may be utilized to suspend a large fog broom for the purpose of condensation of water vapor. In a further embodiment a manpowered inflatable craft is formed with a flexible longitudinal medial fold which separates the airfoil into wing segments. Each segment includes a passive trailing zone.

Abstract: An infantry projectile includes an elongated projectile body having a cylindrical or frusto-conical surface concentrically arranged about its longitudinal axis. The projectile body has a leading end and a trailing end each extending transversely of the longitudinal axis. The leading end is disposed at an oblique angle to the longitudinal axis for affording a trimming action on the projectile when it is in flight. A flow control projection is provided on the surface of the projectile body between its ends so that the aerodynamic center of the projectile is located below its center of gravity when the flow control projection is located on the lower surface of the projectile body and in a vertical plane extending through the longitudinal axis of the body.

Abstract: A solar powered hot air balloon is disclosed having an envelope with an opaque portion and a transparent portion arranged so as to utilize solar heating to heat air within the envelope. The solar heating air may either by sufficient to provide the entire free lift or may be combined with air from a hot air generating system carried by a gondola supported by the envelope. The opaque portion of the envelope has a substantially black inner surface and a light reflecting outer surface with the black inner surface being positioned so as to receive a maximum amount of sunlight through the transparent portion for a given average position of the sun.

Abstract: A balloon filled with a gas mixture of ammonia and n-hexane will stay at a onstant altitude due to condensation at altitude of the n-hexane. Since both components are liquid below about 50 meters in the ocean and together with the load are buoyant, the aerostat may be submarine launched and rise to the surface at which point the ammonia and n-hexane evaporate and take the balloon and load to its preset altitude.

Abstract: There is disclosed a limited range, high-speed projectile with a flat trajectory. The range is limited by controlling the air resistance of the projectile, so that the air resistance increases markedly when the projectile speed drops below a certain value.

Abstract: A simplified guidance system for air-to-air missiles where the pilot adjusts his helmet sight to compensate for missile errors and this information is fed to a computer which computes correction data from error information, aircraft position information and missile position information, correction data is then sent via a radio link to the missile control system which changes the flight path accordingly.

Abstract: 10. A method for use in controlling the travel of a vehicle comprising the steps of first deriving two narrow band noise signals of different frequencies, then delaying one of said signals by an amount which constitutes the information which will control the path of the vehicle, next adding the delayed and undelayed signals to form a composite signal, subsequently transmitting the composite signal to a receiver in the vehicle, then applying the composite signal to a non-linear device in said receiver along with a duplicate waveform of itself which has been delayed in time, subsequently deriving from the non-linear operation through the step of filtering a signal at the difference frequency between the two original noise signals, which signal is a function of the correlation between said composite signal and its delayed duplicate waveform, and lastly applying said difference frequency signal to a non-linear device to generate control signals which are proportional to said correlation.11.

Abstract: An automatic balancing concept including two annular containers used to dmically balance a rocket during flight. The containers are partially filled with a high density fluid and are installed forward and aft of the longitudinal CG of the rocket. When spin is induced in the rocket the radial CG will shift to the spin axis and the fluid will couple itself to the outside diameter of the ring.

Abstract: Lighter-than-air apparatus includes a thin, pliable air-tight outer envelope disposed in overlying relationship over a light-weight, coarse-opening inner frame of a spherelike shape. The envelope includes a sealable opening therein, so that the envelope can be at least partially evacuated to render the apparatus lighter than air. A vacuum pump is provided and is connected in fluid communication with the opening for controlling the quantity of air contained in the envelope to determine the amount of lifting energy. In one form of the invention, an outer frame is disposed within the envelope and surrounding the inner frame, and the outer frame is composed of a stiff, rigid open-mesh material with the openings in the inner frame being smaller in size than the opening in the outer frame.

Abstract: A ballistic missile guidance apparatus for compensating the trajectory of a allistic missile just prior to thrust termination by comparing the nominal trajectory with the actual flight parameters encountered during the powered stage of the flight and introducing compensating corrections to provide for an accurate ballistic flight. The comparison is made by storing the nominal kinematic parameters and comparing thereto the actual flight parameters obtained from the inertial guidance system.

Abstract: An anti-missile missile employing an accelerator of the Van de Graaff or linear type which is carried by the missile to propel particles, such as gamma aluminum oxide, at hypervelocities, the particles being as small as about 10.sup.-7 cm in diameter.

Abstract: In a hot air airship including an elongate gas envelope aerodynamically shaped for horizontal flight with a pressure hot air generator for pressurizing the envelope and tail members on the envelope, a gondola below the envelope and power driven member for propelling the envelope horizontally, a method and structure for releasing over pressure from the airship envelope and for regulating its ascent and descent by a variably controllable first vent in the front end of the airship and a second variably controllable vent at the aft end of the airship, each of which functions to release air at a controlled rate to cause heated air to move toward either end and cause either end to ascend.

Abstract: An aerostat comprising a closed envelope carrying a nacelle which accomodates a ventilator for driving in air through an appropriate device is disclosed. A burner is movably placed inside the envelope, together with an ignition device and a shield, the envelope further including a valve operable from the nacelle which is fitted with railings so that a cable and various other components can be attached to the aerostat.

Abstract: A substantially permanently buoyant balloon suitable for use as a toy or in advertising, for example, is provided which includes an envelope containing a lighter than air gas such as helium, which envelope is made from attached panels of a nonelastomeric polymer sheet material carrying a continuous metal layer on at least one side thereof. The metal layer can either be a thin metal film contiguously bonded to the polymer, or can be metal which is vapor deposited over the surface of the polymer. The balloon itself is constructed so that the ratio of its volume taken to the two-thirds power divided by its surface area is in the range of from about 0.21 to about 0.01, and the weight of the envelope can range from about 2.6 .times. 10.sup.-4 gm/cm.sup.2 to about 1.7 .times. 10.sup.-2 gm/cm.sup.2. The envelope is preferably manufactured in two dimensional "lay-flat" form in any desired two dimensional shape unlike conventional balloon envelopes which are inherently three dimensional surfaces.

Abstract: An assembly which is an energy absorbing system for supporting the nose c of a missile in a position extended from the guidance section prior to eject (launch) of the missile. This extended position exposes internal umbilical connectors to permit internal missile components to be connected to external sources of power (electrical, pneumatic, etc.). Gravitational forces during eject (launch) displace the nose cone rearwardly against the guidance section. The assembly controls impact velocity of the nose cone and guidance section during closure thereof. At closure, a smooth aerodynamic surface is formed at the junction of the nose cone and guidance section.

Abstract: Aerostats and aquastats are described in which a sealed envelope of flexible material impervious to the passage of gas therethrough is mounted on a flexible frame forming a permanent part of the device and which can be caused to expand the envelope after it has been wholly or very substantially evacuated of internal gas, thereby setting up a vacuum or partial vacuum condition in the envelope. In the case of a partial vacuum, the gas at reduced pressure may be hydrogen or helium. The lift or buoyancy of the device may be controlled when in use by altering the volume of the envelope by adjusting the shape of the frame by acting mechanism carried by the device. The frame may comprise flexible rods connected together at opposite ends so that by forcing the opposite ends of the rods towards one another they are bowed outwards distending the envelope towards a globular form.

Abstract: A glass balloon that floats in air. An assembly of glass balloons that form a slab of foam that floats in air. A process for making glass balloons employing: two nested furnaces, pre-heated helium, a moving furnace, and a refrigerated seal-off chamber.

Abstract: A projectile having mainstream air flow directed to its surface region of rmal air non-attachment during operational flight and in which drag frictional forces in the laminar flow boundary layer region are minimized to produce maximum range. The projectile conical nose has a forward air intake nozzle in fluid communication with a plurality of internal passageways that terminate in outlet ports circumferentially spaced along the rearmost edge of the nose member adjacent the forwardmost external or lateral surface of the projectile main body portion.

Abstract: A tethered aeroform balloon having an inflated toroid tail structure secured to the balloon hull by means of a plurality of rope lines for supporting the drag forces and the weight and steering forces of the tail structure. The inflated tail structure has a substantially symmetrical air foil section with support diaphragms secured inside the tail structure. The tail structure is inflated by an electric motor powered fan supported on the tail structure. A pressure switch prevents over inflation of the tail structure. A check valve prevents the escape of air from the tail structure when the fan is not running.

Abstract: 1. The method of determining the trajectory of a ballistic missile having trajectory substantially defined by the formula:y = - g + .rho..infin. g(y).sup.2 /2 .beta. sin .gamma.x = .rho..infin. g (x).sup.2 /2 .beta. cos .gamma.comprising the steps of measuring the velocity and flight path angle of the missile at a reference altitude, measuring the radiation emitted by the gases in the proximate environment of the missile, measuring the time required for the missile to travel from the reference altitude to the occurrence of maximum radiation, measuring the altitude at which maximum radiation occurs, computing the value of "a" from the following formula: ##EQU1## COMPUTING THE VALUE OF ".beta." FROM THE FORMULA:A = .rho..sub.O G/2 C .beta. SIN .gamma.whereV = velocity at altitude yV.sub.e = velocity at altitude y.sub.o.gamma. = flight path anglee = base of natural logarithmsc = constanta = .rho..sub.o g/2 c .beta. sin .gamma..rho..sub.o = density of the atmosphere at sea level.rho..infin.

Abstract: A sighting and laying system to properly aim the missile gyro axis to a petermined elevation and to orient this same axis in any desired horizontal direction. These functions are performed without any preleveling of the launcher elevating and slewing mechanism and permits the missile launcher to be located on up to a 6.degree. slope in any direction.

Abstract: A projectile of the type to be stabilized by rotation is formed with an asymmetrical point. In one embodiment a pair of unequal, diametrically opposed recesses are provided and apportioned so that the center of gravity of the projectile is located along the projectile's axis of rotation.

Abstract: A hot air balloon of conventional construction with a balloon envelope having an inlet aperture for hot air received from a heat generating device coupled with the envelope and directed into the aperture is provided with a hood coupled with the envelope adjacent the aperture. The hood extends part way round the aperture and is of scoop form extending outwardly from the aperture and partially around the heat generating device and serves to direct wind and hot air into the aperture to facilitate inflation when the scoop is directed windwardly.

Abstract: Equipment for playing hoop ball comprises a hollow inflatable balloon of toroidal shape having a central circular opening of sufficient diameter for passing a ball through it. A basket which may be somewhat similar to a basket used in playing basketball is attached to the balloon around the central opening and a tether is attached to the basket and secured to a suitable anchoring device which may be placed on the ground so that when inflated with a gas lighter than air, the balloon floats upward to an extent permitted by the length of the tether and in a position such that the central toroidal axis is in a vertical position so that a ball thrown upward can drop through the central opening and into the basket.

Abstract: A radial arm tracker with a constant drive ratio for use in monitoring the osition of a guidance platform during the firing azimuth alignment phase. One end of the radial arm is mounted to the rotor of an encoder and a telescope is pivotally mounted at the free end of the radial arm through a constant ratio drive system to a stator of an encoder. The stator of the encoder is coupled to a north seeking device. The missile firing azimuth is referenced to the output of the north seeking device through the radial arm tracker.

Abstract: An apparatus and method for reducing the launch disturbance of a weapon se on a supersonic aircraft is disclosed. The apparatus comprises a flywheel rotatably mounted within the store. The flywheel is pre-spun before launch using internal rockets or ram air. The spining flywheel produces a gyroscopic effect which appreciably reduces launch disturbance and therefore increases accuracy.