Abstract: The lightning rocket system of this invention comprises a rocket launcher that is in communication with a detection device that measures the presence of electrostatic and ionic change in close proximity to the rocket launcher that also fires the rocket launcher. This system is designed to control the time and the location of a lightning strike. The lightning rocket can be comprised of solid propellant that has cesium salts added which produces a conductive path when the exhaust gases are discharged from the rocket that is expelled to the static layer of a thundercloud. A conducting lightning rod which is grounded and positioned along side the launch tube for the solid propellant is in communication with the conductive path to thereby control the time and location of a lightning strike from the thundercloud. In a liquid expelled rocket a solution of calcium chloride is used to form a conductive path from a thundercloud.

Abstract: The lightning rocket system of this invention comprises a rocket launcher that is in communication with a detection device that measures the presence of electrostatic and ionic change in close proximity to the rocket launcher that also fires the rocket launcher. This system is designed to control the time and the location of a lightning strike. The lightning rocket can be comprised of solid propellant that has cesium salts added which produces a conductive path when the exhaust gases are discharged from the rocket that is expelled to the static layer of a thundercloud. A conducting lightning rod which is grounded and positioned along side the launch tube for the solid propellant is in communication with the conductive path to thereby control the time and location of a lightning strike from the thundercloud. In a liquid expelled rocket a solution of calcium chloride is used to form a conductive path from a thundercloud.

Abstract: A donor charge detonator is disclosed which has a donor charge case for caining a main explosive with means for initiating the main charge of explosive. The case design comprises a plurality of flutes formed around the outer surface of the case, and the plurality of flutes comprise valley members or grooves separated by peaks between successive grooves. The grooves and peaks of the flutes function after initiation of the main charge of explosive to cause the formation of particles from the donor charge case and the resulting explosive force to follow along the valleys of the flutes thereby forming a plurality of jets similar to linerar lines whereby the resulant shock is enhanced in a specific direction. The resulting force and the resultant shock are transferred at a higher magnitude because of the jet effect of the fluted configuration of the donor charge case.

Abstract: A gun launched rocket motor is provided with a filler material to fill all f the free volume in the rocket with a void-free incompressible "filler". The described filler material is selected from a solid, semi-solid, or liquid having many properties closely comparable to the rocket propellant, especially match the density, chemical compatibility, coefficient of thermal expansion, and thermal stability. The filler material functions to provide the required physical support to various propellants to survive gun launch. A preferred filler material is a completely fluorinated organic material which is a liquid which is compatible with various solid rocket propellants and can readily be ejected from the chamber by pressurization from conventional igniters or combustible cords such as Rapid Deflagrating Cord, RDC. These completely fluorinated perfluoro compounds, which are designated as C5-18 compounds, are marketed as Fluorinert Brand Electronic Liquids by 3M Corporation, St. Paul, Minn.

Abstract: A laser actuated thru-bulkhead initiator for transmission of detonation within the initiator without destroying the pressure integrity of the initiator and the seal of the pressure vessel in which the initiator is installed comprises a body portion having an aperture extending throughout the length thereof. This aperture provides an optical path from a laser source to a detonable explosive material positioned within the aperture. The body portion provides a housing for retaining in a first section of the aperture, a primary window element, an attenuator for an explosive shock wave, a second window element, and an explosive material within the aperture and the optical path. A second section of the aperture of the body portion which extends from the outer surface of the second window performs the function of receiving the explosive shock wave energy dissipated from an explosive force released by the detonable explosive composition.

Abstract: A process for mapping the path of an electric arc through a sample of resive material whereby the magnetic field propagated by the arc is recorded on a sleeve of magnetic sensitive material which surrounds the sample, with the intensity of the recorded field at different points on the sleeve indicating the path of the arc.

Abstract: A safe ordnance initiation system which is safe for normal handling, expoe to strong electromagnet fields, and electrostatic discharge comprises a firing circuit which provides a method for rapidly and efficiently connecting (switching) a charged capacitor to an electrical discharge inititation element; an enclosed and environmentally protected electrical discharge initiation element which provides a means of rapidly dissipating the capacitor charge and converting it to a shock wave and thermal/plasma energy output; a transmission line shock tubing which is connected to the electrical discharge initiation element at one end which is terminated in a target element at the other end thereof; and a target element having the capability for interacting with a predetermined output energy level of shock charge and thermal/plasma energy transmitted through the transmission line shock transfer tube to achieve a desired result for igniting or detonating the target element depending on the type of end termination employe

Abstract: A laser actuated thru-bulkhead initiator for transmission of detonation within the initiator without destroying the pressure integrity of the initiator and the seal of the pressure vessel in which the initiator is installed comprises a body portion having an aperture extending throughout the length thereof. This aperture provides an optical path from a laser source to a detonable explosive material positioned within the aperture. The body portion provides a housing for retaining in a first section of the aperture, a primary window element, an attenuator for an explosive shock wave, a second window element, and an explosive material within the aperture and the optical path. A second section of the aperture of the body portion which extends from the outer surface of the second window performs the function of receiving the explosive shock wave energy dissipated from an explosive force released by the detonable explosive composition.

Abstract: A high impulse, non-detonable solid propellant grain is prepared from a cd detonable proepllant composition having a small critical diameter of less than one inch and an uncured detonable propellant composition having a large critical diameter of several inches. The method of preparation comprises grinding or cutting the cured detonable propellant composition into granules less than its critical diameter in any direction. An uncured propellant composition, in a predetermined amount of les than its critical diameter, is prepared, and the granules of the cured propellant are added and blended with the uncured propellant composition (which serves as the propellant binder) to form a homogeneous propellant blend. The homogeneous propellant blend is cured to yield a high impulse, non-detonable solid propellant grain having a critical diameter less than the critical diameter of the uncured propellant composition.

Abstract: An explosive planar shock wave generator produces a planar wave that trav down a shape charge cone to give amplified force on the jet. In all embodiments radial waves are converted to planar waves which react with an explosive shape charge. A planar wave shaper is comprised of a conically shaped planar charge having a predetermined diameter at the base and slant heights terminating at an apex. A cylindrically shaped fast detonating charge which is positioned above the cone shaped planar charge is detonated by a detonator positioned on the surface of the cylindrically shaped fast detonating charge. A sloweer cone shaped detonating shape charge intersecting along the base of the conically shaped planar charge receive the planar shock wave as transformed by the conically shaped planar charge.

Abstract: A self consumable initiator is comprised of a consumable material selected from pyrotechnics, propellants, exothermic alloys, and primary explosive compositions, and one or more lengths of a fiber optic material in physical contact with or embedded in the consumable material. Uniform density of laser energy is transmitted through the fiber optic material to the consumable material in sufficient amount to stimulate the consumable material to its respective ignition point. The consumable material self consumes as it serves to ignite a larger quantity of material such a solid propellant grain. The consumable material is in the form of pellets powders, or castable shapes. When installed in a rocket motor case, the self consumable initiator is bonded or installed as a castable pyrotechnic which conforms to the contour of the front end of a solid rocket motor case. Subsequently, a solid propellant grain is bonded or cast in place in intimate contact with the initiator.

Abstract: A recoilless rocket launcher including a rocket launch tube which is resintly coupled to a support member. Points of contact to the gunner who fires the rocket from a rocket launch tube are to the shoulder and the hand which grips a hand grip which is part of the firing mechanism integrally attached to the support member. The resilient coupling for support member is comprised of a resilient material selected from the group consisting of a butene-diolefin copolymer, rubber, plastic, leather, or fiberous paper. The resilient material disposed in spaced relation adjacent opposite ends of the support member resiliently couples the support member to the launch tube. The nonrigid coupling effects the transfer mechanisms to result in a time offset, extended reaction time, and a reduced total impressed impulse transferable to the gunner prior to rocket exiting the rocket launch tube.

Abstract: An improvement is disclosed in the method of initiating an explosive charge arried to a target site by a rocket launched toward a target whereupon striking a soft target the performance functioning of a percussion primer to a spotting charge is improved by an impactor-cap device in communication with the percussion primer whereby the impactor will indent the primer with sufficient energy and depth to cause functioning. The impactor-cap device is comprised of a cap portion and an impactor portion. The cap portion is in the form of a thin plastic cup of a material selected from polyethylene, nylon, mylar, or cellulose acetate. The impactor portion is in the form of a ball or spike of hard material such as a steel ball, glass ball, or high impact strength plastic such as polycarbonate, methyl methacrylate (Plexiglas), or nylon.

Abstract: A rocket motor that has a fast burning propellant therein with a dispenser rrangement for dispensing a fluid chemical suppressant into the exhaust gases of the solid propellant for reducing the flash signature.

Abstract: A method and design are disclosed for the introduction of ammonia gas into he rocket motor gas environment wherein the ammonia gas functions to suppress the flash signature.The firing and pressurization of a sealed container having suppressant vents results in the rupturing of one or more seals for the container containing clathrate means from which adsorbed liquid or gaseus ammonia is boiled out and discharged and mixed with combustion gases prior to being discharged through the exhaust nozzle of a rocket motor.The design for the container for containing clathrate means include as part of one embodiment a toroidal shaped container for installing within the rocket motor exhaust nozzle wherein the container functions as the throat of the exhaust nozzle of the rocket motor. Other embodiments feature the clathrate means in a sealed container which additionally houses the ignitor means.

Abstract: A device in which a solid suppressant is ablated and dispensed into the gs of a main burning rocket motor in which a fast burning smokeless type solid propellant is burning to allow the suppressant to control afterburning of the gases from the burning solid propellant and the suppressant being dispensed by a sustained action igniter pyrotechnic that is also used to ignite the main motor solid propellant.

Abstract: A rocket motor is disclosed which employs a Class 1.1 detonatable composition which is both a propellant and explosive. One grain design is configured to give a high boost acceleration during the burning phase of a perforated portion of the grain. The internally burning grain subsequently changes to an end-burning grain which provides a sustaining thrust burning period. The rocket motor flies to target with the burning surface progressing towards the head end. The rocket burns to target, but the design always provides some remaining propellant which serves as the warhead explosive on impact with the target. Detonator means cause the remaining unburned propellant to denonate at target impact or prior to target impact. This rocket motor design does not provide for separation between the warhead and the motor case. Therefore, the complete rocket motor travels to the target area.

Abstract: A safety container for transporting small quantities of explosives that iude a metal bottle that has a bottom and top section that are secured together with seal means therebetween and a cavity of the bottle has antistatic foam plastic material therein with a cavity at the geometric center of the foam plastic material for mounting or containing an explosive and the cap section has a relief valve for relieving any pressure that may be in the cavity of the bottle.

Abstract: An aging gauge comprising a container having a fixed or a variable sized t opening with a cap which can be opened to control the sublimation rate of a thermally sublimational material contained within the container. In use, the aging gauge is stored with an item to determine total heat the item is subjected to and also the maximum temperature to which the item has been exposed. The aging gauge container contains a thermally sublimational material such as naphthalene or similar material which has a low sublimation rate over the temperature range from about 70.degree. F. to about 160.degree. F. The aging products determined by analyses of a like item aged along with the aging gauge for which the sublimation amount is determined is employed to establish a calibration curve for future aging evaluation. The aging gauge is provided with a means for determining the maximum temperature exposure (i.e., a thermally indicating material which gives an irreversible color change, Thermocolor pigment).

Abstract: In a method for determining and evaluating nozzle erosion rate, an eroding ozzle and a non-eroding nozzle are employed in a dual nozzle arrangement to receive a balanced thrust and flow rate from a common solid propellant grain of a solid propellant rocket motor when initially fired. When erosion of the eroding nozzle begins an increase in throat area results and the mass discharged through throat increases thereby causing an imbalance in thrust. The erosion is correlated to the mass flow rate of the solid propellant rocket motor by the mathematical relationships, F.sub.2 P.sub.C.sbsb.2 (A.sub.t.sbsb.2 +.DELTA.A.sub.t.sbsb.2)C.sub.F.sbsb.2, wherein F.sub.2 is force, P.sub.C.sbsb.2 is chamber pressure, A.sub.t.sbsb.2 is throat area, .DELTA.A.sub.t.sbsb.2 is change in throat area due to erosion, and C.sub.F.sbsb.2 is the thrust coefficient.