Abstract: A space launcher and method for launching satellites and other payloads into space, comprising multi-stage rockets with payload wherein the ratio of the weight of any lower stage rocket to the weight of the rocket stage directly above it is less than two and a half, and wherein the weight of each rocket stage can be defined as that weight of the space launcher, at the start of firing of this stage, minus the weight of the rocket and payload of the stage directly above it at the time when the latter stage rocket begins firing.

Abstract: A separable nose fairing assembly includes a forward, massive portion slidably coupled to a rearward, light portion. Forward sliding movement of the massive portion relative to the light portion is limited by a stop. An explosive actuator is operable to drive the forward portion forwardly until it reaches the stop, whereupon the momentum transferred to the rearward portion is sufficient to pull it off the missile. Due to the high ballistic coefficient of the assembly it follows a ballistic trajectory different from that of the missile, thus minimizing the possibility of damage to the missile.

Abstract: A crew capsule 2 is connected to the body 3 of a spacecraft by a releasable coupling comprising a housing 6 secured to the capsule, a sleeve 9 secured to the body 3, and clamps 11-15 engaging interrupted thread 10 on sleeve 9 and having hooked ends engaging a flange 7 on housing 6. In an emergency during launch, an hydraulic ram 21 energized by a pump 24 is actuated to rotate the clamps 11-15, which are circumferentially interconnected, relative to the sleeve 9 to disengage the clamp threads from the sleeve thread sections 10; then explosive charges 25 are fired to separate the capsule 2 from the body 3, the capsule subsequently descending by parachute.A similar releasable connection may be used between segments of a Solid Rocket Booster, or between the passenger cabin and other parts of a passenger-carrying aeroplane.

Abstract: The invention concerns a guided munition, fired from a launching system with a cannon effect. This munition comprising sub-assemblies is supported, during acceleration in the cannon, by a peripheral casing which rests on the first sub-assembly of the munition placed at the front of the munition and is fixed to an ejectable sub-assembly placed at the rear of the munition. The weight of this casing is necessary to withstand the forces due to acceleration and it enables the range of the munition to be increased during the ballistic phase. During the transition from the ballistic phase to the guided phase, the ejectable sub-assembly is ejected, taking with it the casing which thus frees the airfoil surfaces to open out. The casing thus positioned also provides sealing and protection of the sensitive parts and rigidity of the whole of the munition.

Abstract: A replacement for the conventional pyrotechnic separation device for large structural elements such as payload fairings on large missile systems is a sequence of nitinol wires or foil strips which, because of their high strength, will hold the structures together but, when heated electrically in sequence, will fuse in milliseconds to allow the structures to separate. The technique for fusing the wires sequentially is to provide wires of sequentially increasing lengths which will cause the shorter length, lower resistance wires to fuse first and the successively longer wires to fuse in sequence until all wires are fused.

Abstract: A booster retarding apparatus for an airborne vehicle such as a missile having a separable booster at its rear end, comprises a series of flaps with hinge assemblies for securing the flaps to the aft end of the booster for movement between an inner position extending rearwardly from the booster and an extended position projecting outwardly from the booster. The flaps are biased towards the extended position, and normally retained in the inner position by retaining devices. The retaining devices are released on booster thrust termination, and include a release mechanism responsive to booster thrust termination for releasing the retaining devices. The release mechanism includes a biasing device having a biasing force less than the acceleration forces developed on launch which oppose operation of the release mechanism so that the flaps are held in during booster thrust and are released and urged outwardly on booster thrust termination to brake the booster and separate it from the remainder of the missile.

Abstract: In order to fill the cryogenic engines of a launcher with propellents up to the time of launcher lift-off, an apparatus is proposed which has a tube section (20) connecting pipes on the ground and on board the launcher (12). A weakened zone (22) of said tube section is automatically broken during lift-off by a mechanism (24,38) applying a tensile stress to the section. This mechanism comprises several assemblies of links (26,28) bearing on the tube section on either side of the weakened zone and a bearing surface (38a,38b) formed in a sleeve (38) fixed with respect to the ground and with which is in contact a protuberance (26a) formed on one of the links of each assembly (26,28).

Abstract: Disclosed is a protective casing for ejectable munitions, having means enabling it to be broken through, this being a necessary operation for the sub-munitions to be ejected, in the next stage, without any difficulty of breaking through and ejection. The fracture lines are obtained by means of screens of high temperature resistant fibers arranged in a plane perpendicular to the internal and external surfaces of the casing. This casing is a part obtained, for example, by fusion and molding. The screen is integrated so that, during the casting of the metal, this metal links up all the fibers forming the screen together. The invention can be applied to protective casings, notably for rockets and munitions carriers.

Abstract: A rocket propelled missile assembly comprises an outer casing defining an internal solid rocket propellant chamber, the casing having an opening at its forward end aligned with an internal tube submerged in the rocket propellant chamber, and at least one exhaust nozzle at its rear end for venting exhaust gases from the propellant chamber. Solid propellant is contained within the propellant chamber surrounding the internal tube, and a separate terminal stage missile is partially or fully submerged in the tube with the capacity to separate from the tube forwardly through the front end of the casing. The missile separates from the remainder of the system on booster burn out.

Abstract: The invention relates to a multistage launch vehicle and method of multistage launch vehicle operation in which at least one subsequent motor stage is ignited following lift-off in partially overlapping relationship with its immediately preceding motor stage prior to shut-down and staging of the preceding motor stage in order to effect positive thrust control over the launch vehicle throughout shut-down and staging of the preceding motor stage. Preferably, each of the motors comprising the subsequently fired motor stage is provided with a thrust profile in which maximum thrust is attained prior to staging of the preceding stage.

Abstract: A traveling charge projectile utilizes a microprocessor and a plurality of sequentially fired igniting-priming-expelling charges to initiate respective charge segments containing propellant, such as granular propellant, of predetermined grain size, to produce a more nearly constant pressure against the projectile base. Traveling charge propellant segments attached to the projectile move with the projectile as it accelerates in the gun barrel. At appropriate intervals during barrel transit, a firing signal initiates a charge which propels the aft most propellant segment away from the projectile into the hot gases and flame behind the projectile to fully ignite the propellant charge and repressurize the expanding breech volume immediately aft of the accelerating projectile. This design maintains a higher average pressure on the base of the projectile during barrel transit, and results in a higher projectile muzzle velocity.

Abstract: This invention relates to an air missile comprising at least one temporary, releasable power unit, connected to the rest of said missile by a fit capable of allowing said power unit to slide parallel to its axis in the direction opposite said rest of the missile, wherein a communication is established between, on the one hand, the space inside said fit and disposed between the front of said power unit and said rest of the missile, and, on the other hand, the aerodynamic flow around said missile. The invention is more particularly applicable to the natural separation of said power unit from the rest of said missile.

Abstract: The invention relates to a projectile including a cylindrical receiving chamber (4) delimited by an interior wall (3) for a braking parachute (17) which can be ejected by way of a piston (9) that is longitudinally displaceable in the projectile, with the piston (9) being chargeable by an ignitable pyrotechnic charge (10). The braking parachute (17) is encased in a longitudinally divided sleeve (18) one side of which is in engagement with the piston (9). In order to completely or partially recover the projectile and not to impede deployment of the braking parachute (17), it is provided that the rear of the receiving chamber (4) is sealed by a cover (23) which can be ejected by way of the piston (9), is equipped with a rotational imbalance (26) and is in engagement with the other side of the sleeve (18). The braking parachute (17) is fastened to the piston (9).

Abstract: An in-flight jettisonable protective cover device for protecting fragile, accurate, radomes or signal-responsive components for the major portion of a flight which is capable of being jettisoned in one piece at supersonic speeds from a guided missile, other air vehicles, or space vehicles. The cover device is for use, for example, in combination with a guided missile having a shell structure, a nose portion, and a radome in the missile nose. The cover device is attached to the missile nose for covering the radome such that an inner space is defined. A plurality of shear pins or other quick-release mechanisms attach and retain the cover device to the missile shell. A source of low pressure gas pressurizes the inner space to approximately 50 psi. A rapid-discharging, high pressure gas cartridge produces a high pressure gas for exerting a pressure force on the aft face of the cover device.

Abstract: The disclosure is directed to a system for recovery of liquid fuel rocket engines used in space flight. The system comprises a sphere with a normally circumferential open portion for containing a rocket engine. The sphere is fixedly attached to the space vehicle. The engine is attached to the inner surface of the sphere in a manner allowing normal engine functions including but not limited to gimbaling. The normal engine hookup is provided via disconnects on the outer surface of the sphere. A pair of sphere closure sections are carried on rails within the sphere adjacent to the normally open portion of the sphere. When the use of the engine in space flight is completed generally prior to vehicle orbit, actuation devices translate the closure sections into the normally open portion of the sphere sealing the opening thereby forming an integral closed sphere, the sphere containing the engine is disconnected from the vehicle by explosive bolts or the like and then the sphere falls from the vehicle towards earth.

Abstract: An annular expulsion motor (14) is secured around the main nozzle casing (12) of a missile by means of shear bolts (28). The expulsion motor expels and spins up the missile prior to ignition of the missile main motor whereupon the expulsion motor is jettisoned from the missile by the efflux of the main motor.

Abstract: An improved rocket staging system for missiles and the like wherein a carriage borne rocket engine assembly is sequentially employed within separate, generally aligned oxidizer stages which are generally coaxially disposed about the central rocket engine and its associated carriage. A central fuel tank is surrounded by several separate, cooperating, generally ring-shaped oxidizer tanks generally coaxially disposed about the rocket periphery. A plurality of oxidizer delivery lines run through each of the outer tanks and up to the top of the fuel tank, where a flexible hose brings oxidizer down to the engine carriage. As fuel is consumed, the rocket motor carriage slides upwardly inside the fuel tank in response to thrust. When the carriage is firmly seated inside the next higher oxidizer tank and all of the propellant has been removed from the lowest tank, the lowest tank is jettisoned to discard unnecessary mass.

Abstract: An improved clamping connection assembly for separable parts of spacecraft is provided and includes a tension belt for securing a plurality of retainers against camming surfaces on flange members on separable spacecraft component parts. The other peripheral edges of the flange members have detents to respectively receive a single shear pin mounted on each of the retainers. The shear pins receive any shear and torsional forces and transmits them between the structural parts of the spacecraft components without creating additional forces on the tension belt.

Abstract: An enabling device 24 for a gas generator 42 of a forced dispersion munitions dispenser 10 includes a housing 58 in which and formed a bore 60, an outlet lead 88 and a detonator opening 68 in which is positioned an electrically initiated detonator 70. A piston 62 is located in the bore 60 and has a disabled position and an enabled position. A safety groove 64 is formed in the outer surface of the piston 62, and a safety passage 72, a safety aperture 74, 75 and a transfer lead 86 are formed in the piston 62. A gas generator 42 containing a quantity of pyrotechnic material 84 is mounted on the housing 58. The gas generator 42 is provided with a safety outlet 46, 47 and an inlet lead 44.

Abstract: A vane assembly for a projectile has a carrier carrying a plurality of pivots, having at the pivots respective carrier elements, and adapted to be secured to an end of the projectile. Respective vane elements are each pivotal on the pivots between an inner position lying immediately adjacent the respective carrier element and within a projection of the projectile and an outer deployed position projecting beyond the projection. Respective heat-destructible pins engaged between the vane elements and the respective carrier elements normally retain the vanes in the inner position and release the vanes for movement into the outer position when destroyed by heat. The carrier element is a rib of the carrier against which the respective vane lies when not deployed.

Abstract: A retainer mechanism for releasably securing a kinetic energy penetrator to he forward end of a missile while the missile is stored, transported and subsequently fired at a target such as a tank. The retainer releases the penetrator in flight responsive to acceleration acting on the missile, to reduce drag on the penetrator in its travel to the target.

Abstract: A projectile includes forward and rearward stage motors 12 and 10 respectively, and a boost separation device 11 releasably connecting the two together. The boost separation device includes an impingement plate 17 slidably mounted on the rearward stage motor 10, and a cruciform shaped locking strip element 20 is secured to the deflector plate. The free ends of the arms 21 of the element 20 are received in a groove 27 provided in a rearward portion of the casing of the forward motor. On ignition of the forward motor, its propulsion gases drive plate 17 rearwardly, thus drawing the ends of arms 21 out of the groove 27, thus to allow separation of the rearward stage motor.

Abstract: A pointed splitter is placed in the body of a soft, rocket-powered training issile with the point toward the rocket motor in the rear. Upon impact, the motor is split and fragments thereof spread transversely so that the force of impact of the motor is reduced.

Abstract: A free flight, impulse controlled missile system for directing a warhead to target. The system includes a small diameter weapon which relies on an accurate ballistic delivery to a point and attitude in space and a body fixed sensor for initiating a self forging fragmentation (SFF) warhead above a target such as a tank.

Abstract: A device for securing two missile sections together and allowing for quick ccess splice and separation of the missile sections.

Abstract: A short range trajectory round having an aerodynamic resistance which sharply increases at a predetermined time after discharge of the round from a barrel of a weapon. The round includes a body having a longitudinal axis and a forward tip portion and a rear base portion with at least one segment forming a part of the body and arranged for outward movement away from the longitudinal axis. The at least one segment at least partially delimits an inner cavity within the body terminating at a predetermined distance from the tip portion, and a plunger having a forward portion and a rearward portion is disposed within the cavity and arranged for movement in the longitudinal direction of the round between at least a rearward position and a forward position.

Abstract: An artillery shell is provided comprising two sections having complementary oupling members for connecting the sections together. The complementary coupling members include at least two locking assemblies which can be engaged to prevent relative axial movement of the coupled sections or disengaged to permit the disconnection of the sections. As a result, the sections can be connected and disconnected for different mission requirements and for inspection purposes.

Abstract: An apparatus for simulating the detonation, light flash and smoke development of ammunition, without the actual firing or impact of the real thing, is disclosed. A plurality of smoke and flash pyrotechnic charges contained in a replaceable support panel, each charge having its own detonator, simulates the smoke and flash of the ammunition. In addition to the smoke and flash simulation, means for generating a noise impulse is provided to simulate the detonation. A control unit, responsive to a firing command, controls the generation of the smoke, flash and detonation noise to simulate either the firing or the impact of the ammunition. The apparatus is adaptable for mounting on the gun barrel of an armored vehicle to give the crew as real a simulation as possible.

Abstract: A flare release system in which a plurality of flares are sequentially lahed from a submerged float. Launching apparatus for each flare comprises a compressed gas cylinder which is ruptured by a firing pin propelled by an electrically initiated squib. Compressed gas escaping from the cylinder powers an ejection piston to force a flare from the submerged float. An electric circuit distributes firing pulses to each flare launching mechanism according to a predetermined sequence.

Abstract: An electrically activated ignition circuit system for a gas generator to be used to inflate a gas bag in a motor vehicle.The system includes a bridge circuit including a first ignition filament for igniting gas-producing substances disposed in a gas generating bomb and a second ignition filament for exploding a detonator to break a seal for the bomb; a source to supply current to the bridge circuit; and a collision sensor to couple the current from the source to the bridge circuit when a collision occurs. The current first heats the second filament to explode the detonator and then heats the first filament to ignite the gas-producing substances.

Abstract: A modular buoy system in which a number of similar sonobuoys are housed in a common container. Associated with each sonobuoy is a launching mechanism. A circuit is provided for actuating these launching mechanisms separately so that the sonobuoys may be ejected from the container one at a time.

Abstract: A gas generator for inflating safety cushions in automotive vehicles has a tubular housing, closed at both ends except for a discharge orifice in one end. A hermetically sealed container in the completely closed end of the housing is divided by a consumable partition into two chambers containing gas generant material. Each of the two chambers is also equipped with an ignition means for igniting the gas generant. The remainder of the tubular housing is filled with the following elements, arranged in tandem series from the sealed container to the orifice of the housing: a filtering means, a first perforated plate, pH neutralizing material, a second perforated plate, cooling means, and a third perforated plate. An impact sensor, which is not a part of the present invention, determines whether one or both of the ignition means are fired on impact, depending upon the force of a collision; and, hence, the rate at which an inflatable structure is filled with gas.

Abstract: A pyrotechnic signal providing smoke and flame and which is launchable from nderwater. Launching of the signal from underwater arms the signal, however, the signal is not initiated until the ambient sea pressure reaches a predetermined pressure valve. When this predetermined pressure valve is reached, sea water enters a cavity and energizes a battery which detonates an electric squib. The squib, in turn, ignites a smoke composition in the signal housing.

Abstract: An apparatus for use in connection with vehicle safety systems of the type including an inflatable confinement which is inflated by the combined energy of a stored fluid under pressure and gas generated by the burning of a propellant. Two distinct propellant charges are provided which are sequentially ignited. The outlet from the reservoir storing the fluid under pressure is opened in response to the ignition of the first propellant charge. The sequential ignition of the propellant charges reduces the peak pressure in the reservoir.

Abstract: A rocket for firing from a tube having open ends wherein a rocket motor sed from a projectile is connected to the projectile by a frangible, ported collar, the front of the motor having a vent for allowing combustion products to flow into the tube between the motor and the projectile. The pressure of the combustion products between the motor and the projectile will break the collar to allow the projectile to exit from the tube at a high velocity.