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Publication numberUS3130575 A
Publication typeGrant
Publication dateApr 28, 1964
Filing dateJun 19, 1961
Priority dateJun 19, 1961
Publication numberUS 3130575 A, US 3130575A, US-A-3130575, US3130575 A, US3130575A
InventorsRogers James W
Original AssigneeRogers James W
Export CitationBiBTeX, EndNote, RefMan
External Links: USPTO, USPTO Assignment, Espacenet
Impact test apparatus
US 3130575 A
Abstract  available in
Images(1)
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Claims  available in
Description  (OCR text may contain errors)

April 28, 1964 J. w. ROGERS IMPACT TEST APPARATUS Filed June 19, 1961 INVENTOR. JAMES W. ROGERS w\\\& 2 mm mm m 2 JL $5 0; w mm s s a VW 9 a V 4w 0; mm 5 7. ATTORNEY.

( Granted under Title 35, Us. Code (1952), sec. 266) The invention described herein may be manufactured and used by or for the Government of the United States of America for governmental purposes without the pay ment of any royalties thereon or therefor.

The present invention relates to a gun device for use in research, testing and the like, to shoot a projectile under accurately controlled conditions. The improvement of the present invention relates more particularly to controlling the release of the pressurized propellant gases present Within a gun barrel as the projectile emerges from the gun. V A i For purposes of this specification, a gun is hereby definedas a projectile-impelling system including a tubular gun barrel along which the projectile is impelled by the. sudden application of pressurized propellant gases behind the projectile. The gases may be provided by the ignition of an explosive gas, as in the case of a 'conventional gun, or by a mechanism for releasing or producing a charge of highly compressed gases, as in the case of the so-called gas guns. The energy to'impel the projectile is furnished by the expansion of the propellant gases in the gun barrel.

There has been a continuing need for an apparatus to stage high velocity impact experiments under accurately controlled conditions in the velocity range extending upward from 5000 feet per second. Prior art methods are chiefly methods in which the elements to be impacted are placed in the field. of explosive force of a generally unconfined explosive charge. Only very rough control of the conditions of the experiment, such as the alignment ofthe elements to be impacted and their fragmentation are possible with these methods. Furthermore, these methods are expensive in that the explosive charges must be especially manufactured and in that the experiments must be conducted at ordnance test facilities. V Solution of this problem has been made mere diflicult by -the exacting and critical control of the conditions of experimentwhich may be .required. Exemplary of a type of experiment having exacting requirements is a Monroe effect observation in which a metal specimen having a conical cavity is impacted against the surface of'ametal'plate. In certain instances, the penetration bf the'conical cavitied element into the plate produces a ,gasified jet of metal which emerges from the other suriace of the plate. Fundamental information as to the properties of metals, such as equation of state data, may be. obtainedby investigating the critical configuration of the impacted element and the critical velocity of impactting which form the boundary conditions separating the instances when the gasified jet is produced and when it' is notproduced. The success of such investigations de- Staging impact experiments by" shooting a projectile United States" Patent IO from from a gun are known. However, in prior art guns the presence of the pressurized propellant gas in the gun barrel behind the projectile asit leaves the muzzle has severely limited the accuracy and reproductibility of the projectile flight trajectory. These gases are under extremely high pressure and travel at high velocities, and upon the sudden unsealing of the muzzle when the projectile leaves the muzzle, the gases emerge from the muzzle in a blast which causes the projectile to yaw in flight rather than follow a true bore sight trajectory. As a result, such prior art guns are limited in practical use to the firing of projectiles which restore themselves to a rectilinear trajectory after leaving the gun, such as where the projectile is made to spin in flight by provision of rifling along the gun barrel bore and therefore spin stabilizes itself, or where the projectile has an aerodynamic shape which produces restoring moments during the flight. it therefore has been a hitherto unobtained objective to provide a gun which launches the projectile along a true non-yawing trajectory in the absence of such trajectory restoring means,

It was then considered that impact experimentsin which a stationary target element is to be penetrated and passed through, such as for observing the aforesaid Monroe effec could be staged by placing the target element in abutting relationship against the muzzle of a smooth bore gun so thatthe gun barrel is in effect used as a sliding way to rigidly guide the projectile into impact with the target. This can be shown to be impractical; again because of the presence of the pressurized propellant gases behind the projectile. Apparently, the abutting target element constitutes such an obstruction as to prevent the proper relieving of these gases that the gun barrel would deform or burst under the tremendous pressure that is built up within. Another prior attempt proposed placing the target sufficiently far away from the muzzle of the gun to avoid damaging the barrel, but sufficiently close that the impact occurs before the motion of the projectile is significantlylaltered by the muzzle blast; However, it has been shown by test that, at best, this approach yields results in which only a very small proportion of rounds fired achieve the desired accuracy. Also proposed, was modifying the gun with a conventional small bore weapon muzzle blast device of the type consisting of an extension to the gun barrel having a series of perforations along its length. This has not pend onaccuracy of alignment of the impacted elements proved satisfactory because a shattering or breaking up of the projectile occurred before it hits the target. Although the reason for this shattering effect is not fully understood, it is believed that the projectile is subjected to thrust transients of such character as to cause high fre quency vibrations, which in turn shatter the projectile.

Y The problem of accurate control of experimental conditions is further aggravated by presence of any air or gaseous medium ahead of the projectile in the barrel it self, or along its flight trajectory after leaving the barrel. This was partially overcomein the prior art by sealing the muzzle of the gun barrel with a diaphragm and evacuating the barrel so thatv the projectile motion in the gun barrel, at least, is unimpeded by the presence of such air.

- Nevertheless, existence of air medium along the subsequent flight lines of the projectile reduced the reliability of velocity measurements, and in some instances caused a shock wave to be attached to the projectile which ad-,

of the projectile with the same effect as in the case of firing into a normal atmosphere.

As distinguished from these and other unsuccessful prior attempts, the objects of the present invention include:

l) The provision of a gun device for use in research, testing, and the like to provide high velocity impacts under accurately controlled conditions.

(2) The provision of a gun device by which a projectile may be impelled along a non-yawing flight trajectory.

(3) The provision of a gun device by which a projectile may be accurately guided into direct impact with a stationary target.

(4) The provision of a gun device capable of launching a projectile along a flight trajectory which is substantially under a vacuum.

The provision of a gun device in which provision is made to: (a) relieve the propellant gases present in the gun barrel behind the projectile prior to the projectile leaving the gun, and (b) to retard the dispersion of the propellant gas to permit the projectile to travel ahead of the gases.

Other objects, features and attendant advantages of this invention will be readily appreciated as the same become better understood by reference to the following detailed description when considered in connection with the accompanying drawing wherein:

FIG. 1 is a partial longitudinal section through a gun device embodying the present invention taken along line 1-1, of FIG. 2;

FIG. 2 is an enlarged transverse section taken along line 22, FIG. 1;

FIG. 3 is an enlarged section taken along line 3--3, FIG. 1;

FIG. 4 is an enlarged fragmentary detail section taken along line 44, FIG. 1;

FIG. 5 is a fragmentary detail section indicated by arrow 5, FIG. 1;

FIGS. 6, 7A, 7B, 8A and 8B are diagrammatic views showing projectile and target fragmentation in certain impact experiments; and

FIG. 9 is an enlarged fragmentary detail section of FIG. 1.

Referring to FIG. 1, a gun device embodying the present invention is comprised of a gun 10 for shooting a projectile, the gun including a breech chamber 12, a gun barrel 14 and a muzzle opening 16 from which the projectile is discharged. Gun barrel 14 is provided with a smooth cylindrical bore 18 having an axis A. A projectile 19 is initially disposed at the breech or rear end of bore 18 and breech chamber 12 contains means (not shown) such as an explosive charge or other gas source for suddenly applying pressurized propellant gases to the base of projectile 19. Gun barrel 14 is of such length that an efl'icient expansion of gases is obtained to impel projectile 19 along bore 18 and out through muzzle opening 16.

Attached to the muzzle end 16 of gun barrel 14 is a tubular unit 20 provided with an internal surface or bore 22 which forms an aligned extension of bore 18 and slidingly receives the projectile after it leaves the gun and guides it in continued rectilinear motion along axis A. Tubular unit 20 is provided with four equiangularly spaced slots 24 extending the length of the unit for venting or releasing the pressurized gases present in the gun barrel behind the projectile as the projectile travels along the unit. The aperture area provided by the slots is such that substantially all the pressurized gases are relieved by the time the projectile reaches the front end 26 of the tubular unit. It is to be noted that such longitudinally extending slots continuously vent the region immediately behind the projectile throughout its movement along the tubular unit 20, so that the gases are relieved without application of thrust transients to the projectile.

A series of annular baifie plates 28, 28 extend laterally from tubular unit 20 at regularly spaced intervals along the length of unit 20, forming a series of annular chambers or compartments 3%, 3%) into which the gases venting through slots 24 may expand. It will be apparent that adjoining compartments are communicated by the passageway area of bore 22 and slots 24. This aperture area is of such physical relationship to the volume of the compartments that a very large proportion of the gases flowing into each chamber are entrapped in same for a residence time which is long relative to the time it takes the projectile to traverse its trajectory. This provides a delay of propagation of the gases in the direction of projectile travel to permit the projectile to travel ahead of the dispersing gases. (There are also small staggered openings 32, best shown in FIG. 4, formed in the periphery of annular baffle 28, but these openings have a negligible effect on the residence time of the gases since they are disposed at the outer extremity of each compartment where the gases have lost their pressure, openings 32 being provided for difierent purpose to be subsequently described).

The walls of tubular unit 20 are formed from separable quarter circle or quadrant sections 34, 34 secured together by suitable means, such as threaded fasteners 36. Associated with annular plates 28 are triangular boss sections 38 which are integrally formed at spaced intervals along one of the radial edges of each quadrant section 34 for maintaining the confronting radial edges in spaced relationship to provide the aforementioned slots 24. As best shown in FIG. 9 each triangular boss portion 38 has a base side 39 which abuts the inner periphery of an associated plate 28, and a side 40, the surface of which is in the plane of the rear surface of the batfle plate. This additionally closes the aperture area communicating adjoining compartments and thus assists in increasing the residence time of the gases in the compartments. It is to be noted, however, that the passageway. area of slot 24 is not fully restricted since boss portions 38 are radially spaced from bore 22 by a distance D, FIGS. 1, 2 and 9, so that in actuality slot 24 extends continuously along the length of unit 20. The surface of the remaining side 42 of each boss portion 38 is inclined at a relatively sharp angle to the surface of side 40. This sharp inclination angle reduces the likelihood of any of the expanding gases, which travel at a velocity substantially greater than the velocity of the projectile, being deflected around and ahead of a traveling projectile by the surface of boss portions 38. It will be apparent that the baflies 28 and associated bosses provide labyrinth gas seal means between the gas compartments and a traveling projectile.

The forward portion of gun 10, the majority of the length of tubular unit 20 and the baflle means 28 are enclosed by a large diametered pressure tight cylindrical housing 44; and the forward end of unit 20 and a portion of the flight path of the projectile ahead of the unit are enclosed by small diametered pressure tight cylindrical housing 45, which is closed at its front end by a rupturable diaphragm 46. Housings 44 and 45 are communicated through bore 22 and slots 24, and also through a series of apertures 47 formed in the transverse wall at the front end of portion 44. Larger diameter housing 44 is provided with a connection 48 adapted to be connected to a vacuum pump, the previously described openings 32 in the baffle and apertures 47 between the housings being provided to assist in communicating all the spaces within housings 44 and 45 and the connection 48 for fast evacuation. This provides for the evacuation of air from housing 44, housing 45, gun barrel 14, unit 20 and compartments 30. However, breech chamber 12 is not included in such evacuable zone, there being an O-ring 49, FIG. 5, in a recess formed in the outer surface of projectile 19 to assure a gas tight seal between the projectile and bore 18. A flange 50, FIG. 5, is formed in the base of projectile 19, which flange seats against a shoulder 51 formed at the rear end of bore 18 and restrains the projectile against being pulled along the bore by the force of the vacuum. When the gun is fired and the force of the propellant gases are applied to the projectile flange 50 bends back and permits the projectile to proceed down the gun barrel. It is to be understood, however, that the gas relieving and gas retarding features of this invention have also proved successful in a normal atmosphere, so that it is not intended that the invention be limited to operation in such evacuated housing.

Formed in small diameter housing 45 is a pair of diametrically opposite windows 52, which are disposed a short distance ahead of front end 26 of tubular unit 20 and which are aligned with a pair of slots 24 to provide a line of sight for optical instruments. Another pair of windows 54 disposed near the front end of housing 45 are additional optical instrument stations. The time of transit of projectiles and target fragments between these instrument stations may be measured by directing a narrow beam of light, such as may be produced by a point light source, through each pair of windows and thence by means of prisms into a high speed camera 56, in which a strip of film moves continuously at a known speed. There the respective light beams are recorded as independent continuous streaks on the film. Passage of the projectile or target through the beams of light produce interruptions in these streaks permitting calculation of time of transit by direct measurements on the film. If desired, optical instrument vwndows (not shown) may be provided in the wall of large diameter housing 44 and aligned with slots 24 in order to observe projectile velocity prior to impact. After the projectile passes through the housing 45 it penetrates diaphragm 46, and is then caught in a box 60 containing cotton or other soft material.

The operation of the above described invention can best be understood by again referring to the drawing. For example, to observe Monroe effect jets, a target plate T may be positioned slightly ahead of the front end 26 of tubular unit 20 by a suitable target support 61. Housing 44 is evacuated and the gun is then actuated impelling the projectile 19 down bore 18 and along surface 22 of tubular unit 29, which guides it into impact with target T. If desired, an expansible sleeve (not shown) of brass or other relatively soft material having a bore forming a further extension of bore 18 may be interposed between end 26 of unit 20 and the target to provide rigid guidance directly to target to thereby obtain maximum accuracy of alignment upon impact. The pressurized propellant gases present behind the projectile are fully dissipated through slots 24 before the projectile reaches end 26 of tubular unit 24 and the dispersion of the gases in the direction of travel of the projectile is impeded by the arrangement of baffles 28 and compartments 30. Thus, by the time the projectile strikes target T there are substantially no pressurized gases in the region immediately behind the projectile which obviates the problem of deforming or bursting the gun barrel and causing yaw in the subsequent trajectory. These gas relieving and retarding features have been found to be so eifective that front end 26 of unit 20 is under a substantial vacuum at the instant the impact takes place, and small diameter housing 45, or at least the portion of it ahead of the progressing projectile, remains under vacuum conditions also. Where the Monroe efifect is exhibited the test projectile and target are fragmented forming a jet of gasified metal 62, FIG. 6, which travels down range at a velocity many times the velocity of the projectile, followed by a fragment 64 of plate T which was plugged out by the penetration of the plate by the projectile and which moves at about the velocity of the projectile. These fragments follow a substantially rectilinear trajectory aligned along axis A and are caught in box 60.

FIGS. 7A and 7B show sequential conditions before and after impact in a penetration experiment in which a projectile 66 having a predetermined configuration is shot at a stationary short length of wire 68 which may be held in place at end 26 of tubular unit 20 by a pair of prepunctured diaphragms 69. The impact produces a crater 6 70 in the projectile. It is to be noted that in this case a determination of the penetration into the projectile is sought so that in effect the target is being impelled against the wire.

FIG. 8A and 8B show sequential conditions in a novel use of the apparatus as a wind tunnel in which a model 72 having a predetermined configuration is inserted in the path of a jet 62 of gasified metal produced by impact. When the jet of metal strikes the model it forms a luminous shock wave 74 which may be recorded by a camera.

Obviously many modifications and variations of the present invention are possible in the light of the above teachings. It is therefore to be understood that within the scope of the appended claims the invention may be practiced otherwise than as specifically described.

What is claimed is:

1. In apparatus for determining the elfect of impact of a test projectile upon a target of type including;

(a) a gun of the type having a smooth bored barrel along which the test projectile is impelled under force of propellant gases behind the projectile, and

(b) a barrel extension having its rear end abutting the muzzle of said barrel,

(0) said barrel extension having a plurality of co-extensive elongatedgas relieving slots extending through its wall and longitudinally aligned with the axis of the barrel extension and equi-angularly spaced about said axis,

the improvements comprising,

said barrel extension having disposed therealong between the front and rear ends of the slots,

(d) a longitudinally extending sequential series of gas expansion chambers surrounding the barrel extension and communicating with the bore through said slots,

(:2) said series of chambers having in cooperative association therewith a series of restricted slot sets disposed at a transverse station located between pairs of adjacent chambers to restrict forward propagation of gas through the slots,

said restricted slot sets comprising a restricted slot 1111621118 disposed in each of said equi-angularly spaced s ots,

each of said restricted slot means forming an extension of the wall separating the chambers of the adjacent P whereby emergence of gases from the front end of the barrel extension prior to emergence of the test projectile is substantially inhibited.

2. Apparatus in accordance with claim 1,

(g) each of said restricted slot means forming a radially inwardly directed transverse edge,

to thereby prevent damage to the test projectile from vibratory shocks experienced under sudden fluctuations in force of the propellant gas acting against the test projectile as the rear end of the test projectile passes each station containing a restricted slot set.

3. Apparatus in accordance with claim 1,

(h) each of said restricted slot means having its rear edge forming a continuation of the rear face of said wall separating the chambers and having its front edge forming a frontwardly divergent face inclined to the axis of the barrel extension.

4. Apparatus in accordance with claim 1, including (g) an observation chamber into which the projectile is discharged from the barrel, and

(h) means for maintaining the series of chambers and the observation chamber under substantial vacuum.

References Cited in the file of this patent UNITED STATES PATENTS 2,537,096 Shreeve et al. Jan. 9, 1951 2,780,962 Ressler et a1 Feb. 12, 1957 2,810,288 Herron et al Oct. 22, 1957 2,998,719 Rubin Sept. 5, 1961

Patent Citations
Cited PatentFiling datePublication dateApplicantTitle
US2537096 *Feb 4, 1949Jan 9, 1951John H ArmstrongHigh acceleration shock testing air gun
US2780962 *Mar 23, 1953Feb 12, 1957Halpern Howard SBlast suppressor
US2810288 *Aug 5, 1954Oct 22, 1957Bendix Aviat CorpImpact tester
US2998719 *Sep 21, 1955Sep 5, 1961Rubin Robert JShock tube for studying warhead combination damage
Referenced by
Citing PatentFiling datePublication dateApplicantTitle
US3326033 *May 20, 1964Jun 20, 1967Chapler Robert SShock tube screen choke
US3343400 *Jun 2, 1965Sep 26, 1967Marvin E BackmanImpact test apparatus
US3479857 *Jul 20, 1965Nov 25, 1969Daniel Edgar Bloxsom JrMicrometeorite shower creating apparatus and method
US3577764 *Aug 14, 1969May 4, 1971Us ArmyTarget holding control unit
US4681016 *May 2, 1984Jul 21, 1987Ga Technologies Inc.Rail gun barrel with gas containment means
US4932239 *Sep 1, 1988Jun 12, 1990Jet Research Center, Inc.Standard target for explosive charge testing
US5179022 *Feb 11, 1992Jan 12, 1993E. I. Du Pont De Nemours & Co.Biolistic apparatus for delivering substances into cells and tissues in a non-lethal manner
US5240855 *Jun 30, 1992Aug 31, 1993Pioneer Hi-Bred International, Inc.Particle gun
US5357796 *Oct 1, 1993Oct 25, 1994Jamison John RBallistics measuring system
US5371015 *Jan 9, 1991Dec 6, 1994Cornell Research Foundation, Inc.Apparatus for transporting substances into living cells and tissues
US5478744 *Aug 12, 1994Dec 26, 1995Cornell Research Foundation, Inc.Method for transporting substances into living cells and tissues and apparatus therefor
US5531113 *Sep 22, 1994Jul 2, 1996Jamison; John R.Ballistics measuring system
US5606110 *Sep 13, 1994Feb 25, 1997Aero Systems, Engineering, Inc.Diaphragm construction for free piston shock tube/tunnel
US5879918 *Nov 24, 1993Mar 9, 1999Pioneer Hi-Bred International, Inc.Pretreatment of microprojectiles prior to using in a particle gun
US6769287Dec 17, 2002Aug 3, 2004Haag Engineering Co.Apparatus for testing structural component samples by impacting with ice balls
US7421893May 30, 2006Sep 9, 2008Mann Ii Richard ABullet test tube and method
DE3128711A1 *Jul 21, 1981Feb 10, 1983Zwick Gmbh & CoStriking mechanism for material testing
Classifications
U.S. Classification73/12.5, 73/12.7, 73/167, 89/14.5
International ClassificationF42B35/00
Cooperative ClassificationF42B35/00
European ClassificationF42B35/00