US2953065A - High velocity accelerator - Google Patents

Description

Sept. 2U, 1960 M. P. BROWN HIGH VELOCITY ACCELERATOR 5 Sheets-Sheet l Filed March 14, 1958 Rw, VI mWV m N0 fc wf V m@ f p a M n n n M N v... @mt B `l. J J W1 f n.. JN l M. X WMWWWMM Mm@ ma ,w u @V M w M W MF WEQ L \\\\n\ L hbwv uwN NJ mi NNW. Y\\ (uw JW WMU.HMMhflllllllllllllllllM nu .UNH HUHHW Q Il uflm: m v P @i mi q l. wv S N v\ l h\ N` b\ NN.\V u N NAI Sept.. 20, 1960 l M. P. BROWN HIGH VELOCITY ACCELERATOR 3 Sheets-Sheet 2 Filed March 14, 1958 Sept. 20, 1960 M. P. BROWN HIGH VELOCITY ACCELERATOR 3 Sheets-Sheet I5 Filed March 14, 1958 R. N m 0&4 N TIL w N -JSM un TJ n.1

EHGH VELUCITY ACCELERATOR Martin ll. Brown, P.0. Box 27, Shalimar, Fla.

Filed Mar. 14, 1958, Ser. No. 721,618

9 Claims. (Cl. 89-1.7)

(Granted under Title 35, U.S. Code (1952), sec. 266) The invention described herewith may be manufactured and used by or for the United States Government for governmental purposes without payment to me of any royalty thereon.

This invention relates to means for increasing Ithe speed of land craft and more particularly to ltest apparatus for obtaining higher velocities of test vehicle on test tracks without an increase in the length of the track and has for an object a high speed catapult launching device for projectiles, rockets, and other air vehicles.

At the present time it appears that the maximum velocity which has been obtained by a test item launching vehicle on a test track is about 330i() feet per second. Increase in the velocities obtainable on test tracks using present techniques is limited by the specific impulse of available rocket propellants and in some cases by track length. An object of this -nvention is to materially increase these velocities with such available propellants and without increasing materially the length of the track.

Current practice in propelling test sled mounted test items is to employ single or two stage boosters which are mounted on the test item sled, or a pusher sled which disengages when the booster is expended. The iuse of additional booster stages and increase of the track length leads to a point of diminishing returns and for present propellants appear to be in the vicinity of 3300 ft. per second.

Velocities of launching aircraft plus velocities of projectiles or rockets totalling 7,000 ft. per second in the future are likely, and therefore t-he testing of ordnance at these velocities is desired, which is an object of the .present invention.

A further object of the present invention is to employ a closed breech launcher or tubular container into which the test vehicle track extends and mounting the test vehicle on the track in lthe rear end of the container with propelling means such as rockets and boosters facing rearwardly, the container being closed by a frangible closure at its forward end, adapted to be displaced by the forward movement of the test sled.

A still further object includes explosive means to remove the forward closure when the test item approaches near the forward end of the closed breech container.

Another object is the evacuation of the closed breech container to reduce air resistance in front of the test vehicle and test item or projectile as it is projected forwardly through the container toward the frangible forward closure.

A further object includes a plurality of pusher type acceleration vehicles disposed on the track behind the test vehicle for initial acceleration of the test vehicle and which disengages the vehicle when they are expended.

A further object is the provision of means for progressively tiring the rocket means on the proceeding booster vehicles as rear booster propelling rockets are expended.

A further object includes means for mounting a test 2,9535 Patented Sept. 20, 1960 projectile, such as a test rocket, on the test item supporting vehicle so that it will be projected forwardly in space upon abrupt deceleration of the test item supporting vehicle or sled.

A further object includes the possibility of venting the closed breech or launcher tube to keep the accelerations within the container within limits that will not exceed the stress that can be tolerated by the test item or sled assembly.

A further object is the provision of a gas sealing abutment means between the inner wall of the breech container and the auxiliary booster device disposed irnmediately in the -rear of the main rocket booster on the test vehicle to receive the blast therefrom when the rst or rear Ibooster device is expended.

A further object includes a mono-rail supporting system extending into the breech container and forwardly thereof for the test vehicle and booster devices to travel upon and a rear closure through which the test item, sleds and boosters can be inserted onto the mono-rail.

A further object includes a dual rail supporting system for the test vehicle and booster devices in which the tracks or rails are disposed outside of the breech loading container, and the container is slotted longitudinally at its top, with means supporti-ng a test vehicle on the rails outside and means extending through the slots connecting the test vehicle and booster device for travel on the rails.

Other -objects and advantages will become apparent from the following description and accompanying drawings in which like reference characters refer to like parts in the several figures of the drawing.

Figure 1 is a somewhat diagrammatic vertical longitudinal sectional view through a test vehicle launcher, parts being broken away to foreshorten the view.

Figure 2 is a transverse vertical section taken about on line 2 2 of Figure vl.

Figure 3 is a diagrammatic vertical longitudinal sectional view, on a smaller scale showing the test vehicle within the closed breech receptacle being projected forwardly by the tirst booster device, but before reaching the forward frangible seal, and showing the means for exhausting air from the interior of the closed breech container.

Figure 4 is a fragmentary diagrammatic sectional view of the device illustrating how the second or main booster takes over when the rst booster 4becomes expended.

Figure 5 is a further diagrammatic view illustrating the test vehicle at the end of its travel, where it leaves the end of the track or rail and strikes the deflector, with the test item, or projectile projected forwardly at maximum velocity.

Figure 6 is a slightly modified longitudinal vertical sectional view similar to Figure l in which more than one booster device is employed within the closed breech container.

Figure 7 is a view similar to Figure 3, but showing how the second booster can be fired while the rear or iirst booster is still i-n operation to further increase the velocity of the launching sled while it is within the closed breech launching tube.

Figure 8 is a further modification of the invention in which the launching device is supported on dual parallel guide rails located above and at opposite side of the launching tube, and in which the tube is slit longitudinally with means extending through the slit for connecting the booster devices to their slippers on the rails. In this form two booster rockets are disposed to function within the tube and the main booster rocket on the test vehicle is disposed to operate outside of the launching tube.

Figure 9 is a transverse vertical section taken about line 9 9 of Figure 8.

Referring rst to Figures `1 to 5 the reference numeral 1 denotes a prepared rigid support or base, such as the ground or a cement foundation on which my device is mounted. t

A closed breech container or launching tube 2v preferably of cylindrical form -i-s rmly supported on the base 1 and a mono-rail 3, preferably of T shape is suitably secured at the bottom of the tube -2 to its inner periphery. The track or rail 3 terminates at its rear end at 4 adjacent the breech end of the launching tube 2, this end of the tube being flanged at 5 with a removable breech closure or plate 6 secured over the loading endy of the Itube by suitable securing means, such as bolts 7. If desired any suitable quick, removable breech sealing closure can be employed.

The rail 3 extends forward materially beyond the mouth 8 of the launching tube 2 yand is rigidly supported by suitable supports yor brackets from the base 1 to maintain the track in a precise straight line.

In practice the closed breech launching tube or cylinder 2 may inclose a considerable portion of the track. In a 3000 foot track the ylaunching tube may incluse '1000. or more feet Vof track, if desired.

A frangible closure or cap 9 is provided to seal the mouth 8 of the container or tube 2. If desired an explosive 10 may be associated with the frangible vcap' 9 for the purpose of disintegrating or removing the cap just prior to the test vehicle or sled 11 reaching the cap.

The test item supporting vehicle is indicated generally at 11 and comprises a guide shoe forming a slipper base 12 as shown in Figures 1 and 2 to fit and slide on the guide rail 3.V The test vehicle is formed with a test item support 13 upstanding therefrom to receive and support a test item 14 such as a rocket, projectile shell or other aerodynamic item in spaced parallel relation to the guide rail 3. Suitable brackets 15 being provided on the support 13 for receiving and holding the test item 14, with release means for preventing rearward movement of the test item relative to the test itemsupporting 'vehicle 11 but permitting the test item 14 to continue forwardly at maximum velocity when the test vehicle is decelerated, such as shown in Figure 5, by a stop means or deector 26 in the path of the test vehicle 11.

Firmly secured to the test vehicle 11 in rear ofthe support 13 is the main test vehicle accelerating device such as a booster rocket or rockets 16 which are supported from the slipper base 12 of the test vehicle 11, by spaced supports 17.

Mounted on the rail 3 in rear of the guide support or slipper base 12 ofthe test vehicle 11 is a primary or first booster vehicle 18 comprising Va slipper base or iirst booster `sled 19 designed to yslidably fit the rail 3; The sled 19 :has upstanding standards or brackets 20 firmly fixed thereto into which is rm'ly fixed a primary or first booser device ysuch as a booster rocket 21.

Mounted at the forward end of the pri-mary booster rock-et 21 is an abutment disk in the form of a gas seal 22, the periphery of which is shaped to` conform to the inner shape of the breech launching container or cylinder 2, but in fairly closely spaced relation to the interior lof the container tube 2 so as to travel therein,V preferably Without touching.

Suitable tiring mechanismsuch as electric conductors 23 may be connected to the igniter of the booster rocket 21 from the exterior of the container`2. Also suitable tir-ing means may be provided `such as conductors 24 for tiring the main or primary booster rocket 16 when the first booster rocket 21 is Wholly or partly expended when separation of the rst booster device'ignites the main booster rocket 21. Also suitable contacts and conductors 25 may be provided for energization bythe test item sled 12 las the same approaches the frangible closure i cap or seal 9 to fire the explosive 10 to remove or disintegrate the closure cap 9 slightly before the test item sled 12 reaches the cap 9.

It is also contemplated that the cap 9 may be made rof lhighly frangible material so that the striking of the cap '9 by the test item 14 may disintegrate or remove the cap 9 to one side to permit the test item 14 and sled 12 to pass out of the tube 2 without material deceleration or dama-ge. Y

-In |loading the device for a test the closure cover 6 is removed by removing the bolts 7, although other quick release lsecuring means. for this breech plate 6 may be t provided.

Y per 12 maybe introduced ifdesired.F

The test item supporting sled 11 is now inserted through the breech of the container or cylinder 2 with the slipper base y12 slidably disposed on the rail 3 as shown. Suitable lubricants between the rail 3 and slip- The firing Iconductors 24 :are now connected yto asuitable, firing mechanism which preferably is carried on forward surface of the gas seal 22. The gas seal 22 and its associate booster sled 1S are now inserted through 26 located in the forward or muzzle portion 8 of the tube 2 for evacuatingl the air from within the tube.

Before tiring the rocket '21 the air within the tube 2 is preferably evacuated through the conduit 26 connected to suitable vacuum pump means 26a to provide a partial vacuum within the tube 2, ythis being maintained by the sealing closure 6 at the breech end and the frangib'le closure cap V9 at the forward or muzzle end 8.

Y With the booster sled 11 `and auxiliary booster sled 18 in the position approximately as sho-wn in Figure l the auxiliary or rst booster rocket 21 is fired in any convention'al way, such as energizing the conductors 23 to re a ysquibyin the rocket 21 Vto ignite the rocket proper.

The rocket 21 accelerates the auxiliary sled 19 for-y wardly, Vwhich in turn pushes the test vehicle sled 11 forwardly as shown in lFigure 3. The gas seal or shield 22 prevent an appreciable amountV of pressure generated by t'he rocket 21 behind the shield 22 from leaking for` wardly while the flow pressure area in the tube 2 ahead ofthe shield 22 assisted in increasing the acceleration and velocity of the test item sled 11 and the test item 14 carried thereby.

At `some point duringits forward travel, either Within the container 2 or after it has passed out of the container 2 the primary or main rocketv booster 16 is fired, preferably as the propellant forceof'the auxiliary booster 21 falls off or becomes expended.

Y The blast of the primary rocket booster 1e strikesthe gas shield' 22, decelerating the first booster 1S with a corresponding further increase in acceleration and velocity of the test `vehicle sled 11. Y A When the test item supporting vehicle sled 11 ap-A proaches the frangible muzzle sealing cap 9` the contacts 25 are closed, preferably, bythe test vehicle sled 11,` tol re" the explosive 10 to remove or disintegrate the cap 9 so thatit lwill not damage or'decelerate the test vehicle Y sled 11 or injure the test item 14.

, the way without vany appreciable' loss inV acceleration of the test item sled 11 in the event that the explosive '1u is not employed. It is also contemplated that beforetbe time when the test vehicle 11 reaches cap 9 the vacuum in the tube 2 will be decreased to provide a positive pressure ahead of the seal 22, which is sutcient to pop the closure cap 9 to one side out of the way of the test vehicle 11 and test item 14.

The main booster, or boosters 16 on the sled 11 continue to increase the velocity of the test vehicle 11 and test item 14 until the sled 12 nears or reaches the far end of the rail 3 as shown in Figures 4 and 5 where the test vehicle and test item have reached the maximum velocity possible for the system, length of track and amount of booster power provided.

The primary booster rocket 16 on the sled 12 preferably becomes expended as it leaves the far end of the rail 3, as shown in Figure and the test Vehicle is preferably quickly decelerated by a suitable deflector o-r yieldable abutment 27 but the test item 14 Vis projectedV freely lforwardly as shown, at the maximum velocity of the test item sled 11. It should be obvious that with the closed breech container or tube 2 and the removal of air from the interior of the tube 2 by suction through conduit 26 to reduce air resistance within the tube to a minimum, a very great increase in acceleration and velocity can be obtained without a material increase in the length of track required or in the propulsive force of the booster rockets that are employed.

The modification as shown in Figures 6 and 7 primarily involves the use of a plurality of secondary booster sleds each having a gas shield or seal similar to 22. In this form the main test item and sled are assigned similar reference numbers to those used in the preferred embodiment, as they are of the same type as in Figures l to 5. A plurality of booster sleds are indicated at 18a and 18b each having slipper supports or bases 19a and 19b and gas seal shields or partitions 222L and 22b carried on the front ends of the booster rockets 21a and 2lb which are supported on brackets 20a and 261. Any suitable firing means, for instance a timer device may be provided to fire booster rockets 20a and 20h successively in their desired tiring order and time, preferably the rear booster rocket 21a is iired iirst and as it becomes expended any suitable mechanism fires the intermediate stage booster 2lb, causing separation between the two booster stages, as seen in Figure 7. As the intermediate stage booster rocket 21b becomes expended the main booster rocket 16 on the test item support 11 is tired increasing the acceleration and velocity of the test item 14 to a greater degree than when a single auxiliary booster is employed. The operation and rocket tiring means may otherwise be 4the same as described in connection with Figures l to 5.

Referring to modiiication shown in Figures 8 and 9 the closed breech container is indicated generally at 2S, anged at its rear or breech end 29 to receive a breech closure plate or seal 30 which is removably secured thereon by any suitable quick removable securing means such as bolts 31.

The tubular container or elongated cylinder 28 is slit longitudinally to provide a narrow guide slot 32. The container or launcher tube 28 is also preferably held from spreading under internal pressure by retaining means 33 which in cross section almost surrounds the tube 28 leaving the slot 32 exposed.

The breech launching container 28 is, of course, rigidly supported on a suitably prepared base 34 which extends upwardly on opposite sides of the container 28 as indicated at 3S to support a pair of spaced rails 36 forming the track on which test items supporting vehicle 37 and the primary and intermediate booster devices 38 and 39 are slidably supported on slipper members or supports 40 which slidably engage and partly inclose the rails 36.

In this form the test item vehicle 37 is supported from its slipper members 40 by a transverse support or base plate 41:L between the slippers on which the test item support 41 -is rigidly carried. The support 41 carries 6 longitudinally spaced brackets 42, similar to the merribers 15 in Figures l to 5, in which the test item 43 is detachably carried for forward projection as in the preferred form of the invention and is releasable for free forward ight when the support 41 is materially decelerated after forward acceleration.

Mounted on the transverse support 41a immediately behind the test item support 41 is the main or No. 3 booster rocket 44 (or rockets if more than one is used and are placed side by side).

The booster rocket 44 is rigidly mounted on brackets 45 carried on the transverse supporting plate 41a just referred to.

In order to provide for maximum acceleration of the test item supporting vehicle a plurality of auxiliary boosters 38 and 39 are provided. These boosters each have a Vtransverse supporting plate 41ar and slipper channels 46-47, preferably C shape in cross section to slidably iit the spaced T rails 36. Projecting downwardly from the center of each of the plates 41a is a comparatively thin longitudinally disposed iin or supporting plate 48. The plate or iin 48 is disposed to guidingly t the slot 32. As seen in Figure 9 the lower end of the ns or plates 48 are each formed to provide a booster rocket holder or body 49 for rigidly supporting one of the iirst of intermediate booster rockets 50 in concentric relation to the central axis of the launcher tube 28.

Gas seals in the form of circular abutment partitions 51 and 52 are fixed to the rocket holder or body 49 at the rear and front ends of the body 49 to closely conform to the interior of the test vehicle launcher tube 28, in spaced relation to the inner periphery to provide a gas or pressure seal in a similer manner to the abutment partitions or disks 22 in the preferred forms shown in Figures 1 to 7.

The tinack or rails 36, of course, extend forward materially beyond the mouth of the launcher tube or cylinder 28 and a closure cap (not shown) of a frangible nature similar to the cap 9 and cap disintegrating or removing means such as an explosive (10 as Aseen in Figure l) may lbe provided if desired, also any suitable displaceable seal may be provided to close the slot 32 before and after the ns 48 of the booster devices pass along the slot. This sealing means, not shown, may be in the form of a resilient sealing strip carried by one or both longitudinal edges of the -tube 28 which define the slot 32, movement of the ns 48 displacing the sealing means progressively from end -to end las the boosters 3S are yaccelerated forwardly by the rockets 50, the resilient means, or springs may be provided for, returning the sealing strips across the slot 32 in sealing rela-tion as the ns 48 pass along the slit 22.

The tracks are maintained in straight longitudinal alignment and parallel relation beyond the outer end of the breech loading tes-t item launching tube 28, and as in the preferred `form shown in Figure 5 a yieldable abutment or deector such as 27 is placed beyond the forward end of the track to arrest movement of the test item supporting sled 37, as it leaves the end of the track so as to decelerate the sled and cause the test item 43 to be projected forwardly in space at the maximum velocity of the sled 37.

With .the construction shown in this modification it is also possible to load the device through the rear or breech 30 of the launching tube 28 as in the preferred embodiment since the rails 36-36 are displaced laterally out of alignment with the ilange 29 and seal plate 30. It is necessary however that the ange 29 be slotted to receive the fins 48, also that the supporting base plates 41a, of the boosters 38 and the base plate 411L of the test vehicle 37 be elevated sutiiciently at the center to clear the upper periphery of the ange 29.

After the breech `closure plate 30 is removed the runners or slippers 40 of the supporting sled 37 are irst slipped onto the rails 36 |and pushed forward as shown in Figure 8, the tt item 327 of cou-ree, being positioned in the brackets 42, and the rocket booster 44 placed in position in the braokets 4 5. v

'-.helinterrnediate acceleration booster 49; is now slipped through the breech of the launching tube 28v Iwith. the slippers 47 slidably engaging the rails 36 and is moved forwardly into contact with the slippers 40 of the test item supporting vehicle 37. This disposes the sealing partitions 1---5if in closely spaced relation tothe inner periphery of the launchingA tube 28, as. shown, one gasv s ealat each end of the rocket booster holder or body 49, providing a double gas seal. Y Y

` The iirst or initial auxiliary booster 38 is now inserted.

in the breechof the` launchingV tube with its lslippers 47 engaging the track 36 and the intermediate booster slippers 47. in a similar manner with the depending iins 48V in the guide slot 3,2.

It is to be understood that suitable means are provided for 4initially firing the first booster rocket 50, and subsef quently tiring the intermediate booster rocket S0` inthe desired time sequence, preferably as the forward thrust of the first booster stage diminishes. Likewise, in a similar manner the main `booster rocket 43 is fired'. In this form of the invention it might be desirableto -ire the main test item sled rocket 44. while the intermediate booster rocket is functioning. Also any suitable tiring means may be used such as shown in the. preferred form, where during inal acceleration of the first booster, suitable contacts rire the intermediate booster rocket, which in turn subsequently fires the main booster on the test item sled. It should be noted that a preset timing device m-ay be used and carried by the sled 37 to iire the two booster` rockets v49 and main booster rocket 44 in the desired order and time sequence.

It will be obvious that various changes may be made by 4those skilled in the art in the details of the embodiments illustratedin the drawings and described in detail within the principle and scope of the invention as expressed in the appended claims.

I claim:

l. A closed breech test item` launching device comprising an elongated launching4 tube having a closed breechl end, a test item supportingY vehicle, a track` extending in parallel relation to said tube from a point adjacent the breech end ofsaid tube toa point materially beyond the forward end orf saidtube, said vehicle having slippers. disposed on said track `for sliding engagement therewithl from end to end, test item supporting means rigidly iixed on said vehicle abovethe level of saidtrack to support a test item thereon, a booster rocket fixed on said test vehicle rearwardly of said test item supporting means for,

means iixed on said bodyin parallel relation to the axis of said tube includingra rocket fixed on said body `facing saidbreech end, la gas sealing partition carried bysaid auxiliary booster deviceA defining the interior of said launching tube in closely spaced relation, to retard thev p-assageY-of pressure gases from` said auxiliary booster rocketrpast said partition, removable closure means for` the breech end of said tube, and means for tiring saidy auxiliary booster rocket whilethe same is in said tube.

2. Apparatus as clraimedin claim l including a frangible.

sealingl closurecfor the forward end of said tube, and means for exhausting air` from the interior of said tube.

3. Apparatus as set forth inclaim, 2 in which the air exhausting means is.l located adjacent the yforwardwend `of the tube. v y

. 4..,A closed breech,launchingYdevice` comprisingnan Y elongated supporting base, ahtest vehicle` acceleratimv trkfatalities-Srbsfantially the'.lensthoffsaidf-base- .an

elongated closed breech test vehicle launching tube havinga central axis disposed in spaced parallel relation to said track throughout a material portion thereof,V a test item2 supporting vehicle havingY elongated slipper means slidAi ably engaging said track for acceleration thereon fron-r end to end, of the track, a test itemx support ixed on said slipper means above the level of said track, means for mounting a testitem on said test item support in spaced parallel; relation to Isaid track for free flightV forward uponrabrupt deceleration of said vehicle, booster rocket means fixed on said slipper means rearwardly of said' test item support for discharge rearwardly, a plurality of auxiliarybooster rocket devices each having slipper means slidably engaging said track rearwardly of said test iterrr supporting vehicle slipper meansv for pushing engagement therewith, said `auxiliary booster means each having a, body portiondisposedto travelwithin said launching tubein spaced relation to the inner periphery of said tube, an; auxiliary booster rocket fixed` on said body portion having;

a discharge nozzle facing the breech closure means of said? tube,` a gas seal disk xedon said auxiliary booster device in front of the forward end of said auxiliary booster; rocket device,A said disk deiining the inner periphery ofsaid tube in closely spaced relation thereto, a frangible.v closure forv the frontend ofsaid tube forsealing the sameagainst the entrance of outside air, and means for exhaustingthe airl from withinsaid tube adjacent the mouth thereof to provide apartial vacuum in said tube betweenI said ygas seal disk and said frangible closure when one of said auxiliary booster rockets is tired.

5. A closed breech test item acceleration and launching` device comprising an elongated test item launching cylinv der having a breech end for receiving said test item therethrough, removable closure means for closing and sealing,

said breech end, a highly frangible closure cap for closing and sealing the muzzle end of said cylinder, a test item vehicle supporting vehicle rail having a rear end disposed `adjacent said closure means in forwardly spaced relation thereto, said rail disposed in iixed parallel relation to said:

cylinder and terminating in a forward end disposed materially forward of said muzzle constituting an acceler-` ation track, a test item supporting vehicle comprising, elongated slipper means slidably engaging said rail, means` for Ireleasably supporting an elongated test item'on said slipper means above said rail, main booster rocket, means for fixing said booster rocket iny said cylinder on saidl slipper means in rearwardly spaced relation to said testv item and parallel to said rail -with itsdischarge end facing rearwardly toward said closure means, an auxiliary rocket booster device comprising an elongated supporting slipper `member slidably enga-ging said rail rearwardly of said' test vehicle slipper means, an auxiliary booster rocket` iixedly carried by said slipper member within said launching cylinder having a discharge end facing rearwardly toward said removable closure means, a lgas sealingV disk fixed on said auxiliary booster device in front of said auxiliary booster rocket, said disk having a periphery deiiningy the interior of said launching cylinder in closely` spa-ced relation thereto, Iand means for tiring said auxiliary booster device while the s-ame is in said cylinder.

6. A high accelerationV test item propelling apparatus comprising an elongated cylinder, having a breech endl and a muzzle end, a removable closure for sealing said breech end, a frangible closure cap for sealing said muzzle end, means connected to said cylinder for exhausting air from the interior of said cylinder, a straight elongated test vehicle supporting rail extending from a point adjacent said removable closure to a point materially beyondv said muzzle end in spaced parallel relation to the axis of said cylinder for a test item supporting vehicle to travel thereon, a test item supporting vehicle carried on said rail, main -boosterrocket means fixed thereon within saidV cylinder with its dischargeend facing in a Adirection to-.- ward said removableclosure, an auxiliary booster device. disposed lon .saidrail rearwardlyI of said test item sup` porting vehicle for accelerating said test item supporting vehicle forwardly on said rail, auxiliary booster rocket means fixed on said auxiliary booster device within said cylinder with its discharge end facing said closure means, and la gas ysealing disk carried on said auxiliary booster device within said cylinder having a periphery closely detining the inner periphery of said cylinder in spaced relation thereto perpendicular to the axis of said cylinder, said disk having a front surface facing the disch-arge end of said main booster rocket means, and means for tiring said yauxiliary booster rocket means and said main booster rocket means successively.

7. Apparatus as set lforth in claim 6 including means for removing said frangible closure cap out of the path of said `auxiliary -booster rocket means at a predetermined point during its travel toward said frangible closure cap.

8. A high acceleration device for test items comprising an elongated test item receiving cylinder having a breech end and la muzzle end, an elongated test vehicle supporting rail extending within said cylinder at the bottom thereof from a point adjacent said breech and to a point materially beyond the muzzle end for a test item supporting vehicle to travel thereon, a test item supporting vehicle disposed within said cylinder on said rail adjacent said breech end, a removable breech closure for inserting said vehicle through said breech end onto said rail, means on said vehicle for supporting a test item within said cylinder, rocket acceleration means carried by said test vehicle within said cylinder having its discharge end facing toward said breech closure, a frangible closure cap for sealing the muzzle end of said cylinder against the entrance of outside lair into the cylinder, means connected to the cylinder adjacent the muzzle end thereof for exhausting the air from within said cylinder to provide a partial vacuum within the cylinder, means for tiring said rocket accelerating means within said cylinder, and means for removing said closure cap from said muzzle end during the acceleration of said test vehicle by said rocket acceleration means toward said frangible closure cap, said closure cap removing means comprising an explosive for removing said closure cap, and means activated by said test item supporting Vehicle for exploding said explosive prior to said test item supporting vehicle reaching said closure cap to remove said closure cap from said muzzle prior to said test item supporting vehicle or said test item reaching Said closure cap during forward movement of said test item supporting vehicle in said cylinder, -an acceleration booster device disposed within said cylinder on said rail between the test vehicle and said breech closure for pushing said test vehicle tward said frangible closure cap, said booster device having a rocket motor xed thereon facing said breech closure, a gas sealing partition disk carried on said auxiliary booster device perpendicular to the axis of said cylinder with its periphery closely defining the inner periphery of said cylinder in closely spaced relation thereto, said gas sealing partition disk being positioned on said auxiliary booster device intermediate the auxiliary booster device rocket motor and the rocket acceleration means of the test item supporting vehicle with a front surface facing the discharge end of the rocket acceleration means for the test vehicle, and means for firing said auxiliary booster rocket motor within said cylinder while adjacent said breech end, and means for subsequently tiring said rocket acceleration means on said test vehicle.

9. A high acceleration device for test items comprising an elongated test item receiving cylinder having a breech end and a muzzle end, an elongated test vehicle supporting rail extending within said cylinder at the bottom thereof from a pointadjacent said breech end-to a point materially beyond the muzzle end for a test item supporting vehicle to travel thereon, a test item supporting vehicle disposed within said cylinder on said rail adjacent said breech end, a removable breech closure for inserting said vehicle through said breech end onto said rail, means on said vehicle for supporting a test item within said cylinder having its discharge end facing toward said breech closure, a rangible closure cap sealing the muzzle end of said cylinder against the entrance of outside air into the cylinder, means connected to the cylinder adjacent the muzzle end thereof for exhausting the air from within said cylinder 4to provide a partial vacuum within the cylinder, means for firing said rocket accelerating means within said cylinder, and means for removing said closure cap from said muzzle end during the acceleration of said test vehicle by said rocket acceleration means toward said closure cap, in which said closure cap removing means comprises an explosive for removing said closure cap, and means activated by said test item supporting vehicle for exploding said explosive prior to said test item suporting vehicle reaching said closure cap, to remove said closure cap from said muzzle prior to said test item supporting vehicle or said test item reaching said closure cap during forward movement of said test item supporting vehicle in said cylinder.

References Cited in the le of this patent UNITED STATES PATENTS 1,416,828 lHolmes May 23, 1922 2,385,051 Berlin et a1. Sept. 18, 1945 2,485,601 Hickman Oct. 25, 1949 2,734,702 Northrop et al. lFeb. 14, 1956 2,792,754 Walker May 21, 1957 2,792,755 Lahde May 21, 1957 2,817,272 Gunder Dec. 24, 1957 2,870,675 Salisbury Ian. 27, 1950

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