US Government As Represented by the Secretary of the Army

Other

Robert E Betts

Lawrence B Thorn

Albert R Maykut

Samuel Zeman

William S Melvin

John F Crawford

Jerrold H Arszman

David R Dreitzler

Nathan P Williams

Jacqueline C Meador

William F Meagher

Arnold T Stokes

Robert E McNeill

William B Thomas

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. As the rocket flies to the thundercloud this liquid is expelled aft forming a column in the air of particles that are more electrically conductive than the surrounding air. In a similar fashion to the system employing a solid propellant as the conductive producer this conductive path conducts a lightning strike to ground to thereby control the time and location of a lightning strike from the thundercloud.

Lightning rocket

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. The specific direction is directed to a point on an explosive acceptor charge when in combination therewith to achieve a greater output and efficiency as compared with spherical shock waves and particle velocities from a conventional detonator.

Omni-directional detonator

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. More specifically, the Fluorinert liquid compound, which is designated as FC-77, has a density of 1.78 g/ml which matches highly aluminized composite rocket propellants. FC-77 has a desirably high boiling point (97.degree. C.), low temperature pour point (-110.degree. C.), and a coefficient of thermal expansion of 0.0014 ml/ml.degree. C. which is lower than many organic liquids and comparable to solid propellants. The family of Fluorinert compounds available from 3M Corporation have properties that cover a wide area providing matching properties such as densities of solid propellants for most, if not all gun boosted applications.

Gun launch rocket propellant support filler

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. In use, when laser light of a minimum threshold energy level, capable of achieving detonation of a primary detonable explosive composition, is transmitted through the optical path, the primary detonable explosive composition detonates. The primary window is protected from failure by the attenuator which is either an air gap or a material selected from an epoxy resin, epoxy resin mixed with an elastomeric material, acrylic resin, polycarbonate, and combination of the materials. The second section of the aperture can contain a pyrotechnic material which yields an extremely fast-acting pyrotechnic initiator. For an application wherein it is undesirable to house the pyrotechnics in the second section of the aperture, a transmission line explosive shock tube is employed to conduct the explosive force to a distant location from the primary detonable explosive composition.

Laser actuated thru-bulkhead initiator for detonable explosive material,

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.

Spark map for a resistive material using magnetic field detection

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 employed for an ordnance initiating system.

Safe ordnance initiation system

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. In use, when laser light of a minimum threshold energy level, capable of achieving detonation of a primary detonable explosive composition, is transmitted through the optical path, the primary detonable explosive composition detonates. The primary window is protected from failure by the attenuator which is either an air gap or a material selected from an epoxy resin, epoxy resin mixed with an elastomeric material, acrylic resin, polycarbonate, and combination of the materials. The second section of the aperture can contain a pyrotechnic material which yields an extremely fast-acting pyrotechnic initiator.

Laser actuated thru-bulkhead initiator

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.

High impulse, non-detonable propellant

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. An additional explosive charge which has intersecting surfaces with the faster cylindrically shaped detonating charge and the slower cone shaped detonating shape charge functions to direct the resultant shock wave inward at a perpendicular angle to the cone angles of the slower cone shaped detonating shape charge. This function results in a faster closing of the intersecting surfaces to yield a higher jet velocity directred along the center of the cone. Another embodiment provides for a shape of a slower cone shaped detonating shape charge to converge to an apex beneath the base of the conically shaped planar charge. The additional explosive charge for this embodiment results in directing the resultant shock wave inward at a more perpendicular angle which causes the intersecting surfaces to close at even a higher rate. This high closing rate results in a higher jet velocity and more efficiency to permit a reduction in overall weight, length, and diameter of the shape charge to achieve the same effect. If a greater resultant force is needed a larger diameter can be employed without an increase in length which is advantageous where lengths restriction to a warhead is a factor.

Planar shock wave generator and enhancer device

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. After being stimulated to its ignition point with laser energy the consumable material serves to ignite the solid propellant grain. The consumable material is in the form of pellets, powders, or castable shapes. When installed in a rocket motor 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. After being stimulated to its ignition point with laser energy the consumable material serves to ignite the solid propellant grain.

Self consumable initiator

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. Thus, the erosion rate of the eroding nozzle is determined and evaluated as a result of the increase of thrust and the flow rate which causes an imbalance in the thrust due to erosion products discharged and a change in value of the A.sub.t.sbsb.2 plus .DELTA.A.sub.t.sbsb.2.

Erosion rate determinator: rocket nozzle

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). Because of the relationship of doubling reaction rates for increases of 10.degree. C., equivalency of item used in accelerated aging evaluation can be obtained by referring to a calibration curve depicting storage temperature on the abscissa scale and multiplier on the ordinate scale.

Aging gauge

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.

Safety container for transporting small quantities of explosives

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. The impactor-cap device is designed to form a contoured fit with the ogive of the spotting head, and a small amount of adhesive is applied to the inside surface of the cap to hold the cap whereby the impactor is retained within the cap portion wherein orientation is achieved to align and hold the impactor in proper position to the percussion primer whereupon striking a soft target increased performance and reliability is achieved.

Impactor cap

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. This described action is accomplished by the resilient coupling, and in an advanced embodiment, sliding means to allow the rocket launch tube to freely slide in the support member also permits a significant delay and a reduction in the forces that can be transferred directly to the gunner to thereby derive benefits including improved personal comfort to the gunner, enhancement of confidence level in system, and a significant improvement in the expected accuracy of the rocket launched to a target from a shoulder fired rocket launcher.

Growing community of inventors

Huntsville, AL, United States of America

Robert E Betts