US1200697A - Aerial projectile and launching mechanism therefor. - Google Patents

Description

F, M. Bm. AERIAL PRUJECNLE AND LAUNCHNG MECHANISM THEREFOR.

WPLICATION FILED NOV. l1, 19H.

1,200,697. Fatemi om. w, ma.

F. M. BELL.

AERIAL PROJECTILE AND LAUNCHING MECHANISIVI THEREFOR.

APPLICATION FILED NOV. Il. |911.

Iaztmml Orf. 10, 1916.

3 SHELTSWSHEET 2.

APPUCATION FILED NOV. II, 1911.

Patented Oct. 10, 1916 3 SHEETS-SHEET 3.

l NMEA/701e fiorney I ratus.

1 saires! .PATE

oon. l

iRANK M. BELL, or EL raso, TEXAS.

AERIL PROJ ECTILE AND LA UNCHING MECHANISM THEREFOR.

Syeeitcation of Letters Patent` Patented oet. 1o, 1916.

:Application ledve'vember 11, 1911. Sen'al No. 659,808.'

'be struelt.ipdependently'of the speed or height df the'aeroplane or the wind1or air currents between 'the aeroplane and the ob- Jeci" With the 'above object in view my in vention compiji'sesla projectile-having self contained or attached guiding `meansiand a launching mechanism therefor whereby the projectile will strike the spot which is directly under the aeroplane atA the moment the projectile is launched irrespective of the height or speed of the aeroplane.

It is well known that the trajectory-of anl ordinary projectile or weight dropped from a moving support isinfluenced by atleast three factors, viz: the height of the support, its'speed and direction of movement and the resistance of the atmosphere. Therefore to cause an ordinary projectile to strike a desired object it is necessary for the aviator to maintain his aeroplane in a certain fixedcourse and to determine by elaborate calculations4 the exact 'point in Space at which the resultant trajectoryof a released projectile will give the desired result. Fax:- haustive experiments vhave demonstrated that by this method accurate results are impossible. With my invention. however, it

is only necessary for t-b'e aviator to direct his aeroplane over the object to be struck and release' his projectile at the moment the bbject is directly under him.v To better determine the point-'directly beneath him; he may if desired employ a telescope mounted in the usual manner on a universal joint to maintain it vertical, but quite accurate results may be obtained without such appaby its impact with the object struck.

A 'farther Object of.A my invencioniS to provide a projectile of the class. described l with means for preventing its accidental discharge -under all circumstances but which -will not interfere with'its discharge when properly launched or projected.

A preferred embodiment of'my invention is illustrated in the accompanying drawings and willnow be described.V

In the said drawingszFigure 1 is a side elevation of an aeroplane equipped .with my improved launching apparatus.l Fig.v 2 is a plan view of the: launching lscreen showing the position in which the V-projectileis -suspended. Fig. 3 is an enlargeddetail showing the manner ofsup'porting the-` projecis avertical section of the projectile on an enlarge-d scale. Figs. 6, 7 and 8.are transverse sectionaljviews on the correspondingly numbered lines 'of F ig. 5 looking inthe direction of the respective arrows7 and, Fig. 9 is a diagrammatic lview show-ing the action of ythe projectile in the air and its trajectory.'

Referring now ,to the drawings in which like characters indicate like parts throughout the several views, and particularly. toFigs. 4 and 5, 10 indicates the outer shell of the projectile which is substantially cylindrical in cross section for the major portion of its length and is provided with an integral conical point 11. 1 Extending from end to end of the outer surface .of the cylindrical portion of the shell are spiral grooves 12, here shown as three in number and of a pitch to extendabout half way around the projectile. The grooves 12 are preferably cut so that their upper edges are at right :angles to the surface of the projectile while end of the shell 10 to a distance somewhat below its upper edge as Shown in Fig. 5. Projecting upwardly from the bottom ot the cavity of the projectile are three ribs or webs 16 which engage the outer surface of the tube 14; to hold it in/place, and in the center tile. Fig. 4 'is an elevation Aof the projectile 1n flight. Fig. 5

of the bottoni is guide pin 17, also integral With the outer shell 10, which projects into the tube 14. Centered on the pin 17 and supported by three rods 18-from the top cap 19 of the projectile is a plate 20 having three countersunk holes 21 in which the percussion caps 22 for igniting the explosive charge are placed with their ends projecting into the portion of the charge which lies between the guide webs 16.

Slidingly mounted on the rods 18 and normally maintained at the top of tube 14 by a mechanism which willnow be described, is a firing plate 23 carrying three firing pins 24 which register with the holes 21 and when the plate is driven to the bottom of the shell by the impact of the projectile with the object struck, strike and explode the caps 22 th'ereby exploding the charge. The plate 23 is provided with a central projection 25 terminating in conical point 26 which centers in a similar recess 27 in the center of the cap 19. The projection 25 is provided with an annular groove in which engage the curved ends of two small arms 28 pivoted to the under face of the cap 19 as shown in Fig. 6, which arms are held in the groove by means of light springs 29, also attached to the cap 19. Iivoted to the under side of the cap 19 near its outer edge are two levers 30 having weighted ends 31, and connecting the levers 30 and the arms 28 are links 32 so that outward movement of the weights 31 will withdraw the arms 28 from engagement with the groove. The ends of the levers 30 opposite the weights 31 are sector shaped and provided with ratchet teeth'33 with which pawls 34 pivoted on the cap 19 engage, the arrangement of the pawls and ratchet's beingr such that the weights can move freely outward but cannot be again drawn inward by the springs 29. Also supporting the plate 23 are two small brittle wires 35 set in the cap 19 and provided with hooked ends which engage under the edge of the plate 23. The wires 35 are strong enough to sustain the Aplate while the projectile falling but are readily broken by theI momentum of the plate when the projectile is checked by striking an object.

Attached to the upper surface of the cap 19` at its middle point, by means of a ball and socket joint 3G preferably provided withY bearing balls to reduce friction, is a stem or tail 37 provided at its outer end with three Yanes 3S. -The joint 3(5'permits the stem 37 to move relatively to the shell in any direction to an angle of about 120 degrees and also permits free relative rotation of the shell and stem 'in any position. Also attached to the upper face of the cap 19 near its outer edge are three short chains 39 of equal length terminating in rings by which the projectile is suspended beneath the aeroplane. l

For properly launching the projectile the mechanism illustrated in Figs. 1, 2 and 3 is provlded which mechanism will nowbe described. Attached to the underside of the aeroplane in any suitable manner isa hook 40 of the type commonly known as a snatchbloek hook. As shown in Fig. 3 this hook comprises a body portion attached to the aeroplane and provided with a pivoted, curved 'piece 41 which is slipped through the 'j i'pgs of the chains 39.l The free end of the pice 41 is caught by a hooked latch 42 also pivoted to the bodyportion of the hook. The weight of the projectile holds the piece 41 and latch 42 in engagement. For releasing the latch, a pull cord 43 is provided, which may, if desired', be connected to a lever y44 arranged adjacent the operators seat.

Also attached to the underside of the aeroplane in a position to inclose the projectile when it is suspended by the hook 40 is a V- shaped screen 45 of fine mesh wire cloth arranged with its apex toward the front of the machine and with its sides projecting belowiand to the rear of the suspended projectile. the force of the air against the projectile so that it will hang vertically in proper position for launching when the machine is in motion as will be hereinafter described. It has beenA found by experiment that a solid screen causes a vacuum or rarecation of the air behind the screen which also interferes with the proper launching of the projectile, whereas with the wire mesl Screen the air is practically still or rather carried along with the aeroplane.

The operation of the device will now be described. In Fig. 9 I have illustrated diagrammatically the course of the projectile through the air. Let it be assumed that the aeroplane is moving in the direction indicated by the arrow and that the projectile has been released in a vertical posikion by means of the lever 44. The projectile 'is moving forward at a speed proportional to the speedaof the machine due to its inertia and as soon as its lower end emerges from behind the screen 45 it meets the resistance of the comparatively still airv and the projectile is deiected from its vertical position to an inclined position, the angle of which is proportional to the speed of the aeroplane. The de` ilection of the projectile by the resistance of the air is augmented, as will be readily un dei-stood by the deflection of ther air from its tapered lower end. As soon as the tail 37 comes from behind the screen it will be caught yby the air and as it is very light compared with the shell it will be swept back as far as the joint 36 will permit and will thereafter tend to maintain a position in line with the movement of the projectile relative The purpose of this screen is to breakv to the air. In Fig. 9 I have shown at a the l position thel prdjectile assumes when it has entirely emeged from behind the screen 45,

' iii/creasing velocity` out the air und by the dotted linea indieated the paths of movement ol' the lower and upper ends of the shell and the end of the Stein or tail. After the iu'ojeetile has heen launrhed :is (leseril'ied it is aeted upon h v two lireem one its momentum in the dlreetion of movement 0f the aeroplane whieh l'oi'ee ist rapidly di niinishing dueto the renistfinle ol' the air and the other, the attraetinn ot gravity' lxieh euiseS the projeetile to drop with a i'anhllvv acting in the spiral grooves 2T in they sur/fare ot the Shell. Causes the shell to rotate on its longitinlinal :iXis after the manner of a 'projeetile tired from a ritled gun harrel. and the rotation ol' the projectile :faunes it movement ilne to the factor of gravit)v to tend toward the line ot its longitudinal axis instead o1" straight downward. 'hen the inereaing rear/ wardl)v aeting torre heeoines greater than the, diminishing tru-wardlv :meting torre the projeetile will begin to move rearwardlx' an indicated at and l in Fig. t) and thereafter the projectile will he :lll'eeted onlir hv the loreel of gravit}Y and the resistanre ot' the atlnopl'iere. The joint 3G between the #hell and the tail permits the khell to rotnte relatively to the tail und thereby not interfere with the retarding;f elleet. ol the tail on the upper end of the shell`r #o that the tail :iets as a guide and pre ents the, proiertile turning over or being otherwiSe ileller'ted from its course h." any nnevenness in its loading' or other eause. rl`he retardation ot the upper end of the lShell h v the action of the t- `l also Causes the proiettile to gfadualhv :issuing a vertieal position and h v properlyY pi( i ortion ing the lenyil il ilu:- tall and size ot the vanen to the Size ..L'l weight of the shell the proie ftile will assume a vertieal pobition at a 1point directly under the point at whieh it was re leased. fter the projeetile assume a vi-rti al position it Will drop in a .'ertieal liney nnatleeted liv Wind or air eux-rents. 'the rapid rotation ot the Shell will envelopnt nentrnll :tir in exaetlv the saine manner is a proiettile tired from a rilled (nunon und i ie guiding stein will maintain it verti1`ili il'\'ioii.f1 1n the :ihove that the i'iroiift'tile vwill always. trike at a point liiertlv under the g o rele-ane xrrepettive ot the speed ot the aeroi'aianeA The `greater the speed, the, greater will he the 3.1i-- elinntion given the nroieetile h v the re" t-l anee ot' the air 'when it llnveQ the surfen and tY refore althohgfh iti-i lore-mtl momentum is greatervit will 'return a eolie-1iondioW greater distanee hetore it :romaines a verliral i =o1-3il,.ioii.

l have shown the #hell explosive rharge hut it i" shell muy he, employed L il ex'iloding shell if: 'il il` li he provided with :i @inten devi/ff develoil an i tallv, All, i@ nell known afmgilai'iw not inlinqoentlj; tall 'from von?! he-,Qhtl

the eiiillofdve Lwojel/ie not y sonnfneran# for frovt im' .e dim'. from impart .zione their a menare not milj: to the al lauf-r mit lo the entire winxp. lilith ny iznj-zofefl ll 'i vie# ille th'irg Edah wine:

until the projwile han t( ai enowh for the projeetle to develop :i itly rapid 75, rotation tor the em'ritu;;' l torre lthe weights ill to ovei'eonie the z'genezinn et' the s'uinfrs i5 and driivv the firing ont (if the groove in the pvojeeti-iin 25. fx lter the arios 28 release the firing! plate it is snp artful h v Q the brittle wires and the point Lil prevente` its tilting und binding the rolls lh no that when the projeftile, ,strikes and the tiring plate breaks the wires it wilt nur Y l'reeljv' in the rods: to the hottoln of the @sli-,ill and explode the ra 'lllo pavvls Ill :ire not neversrlrv to hold the arnin' t .Y l gement mn are provided to in fnl the a; wing 4iarred into engagement hythe impart ot the `ahell lle'lire the tiringv ilntewrealin the mires X5. lf it lie deired that the 'nroieetile peut trate the ohieet Strurk before explodii'ig, the loing-,r portion nl' the rhell. het 'en the Wohn lo n av he, lllleffl with :i low hin ing mwtlegz `While l have shown inv invent' in in fionnertion with an noronlai'ie, it is at fou@4 that it equally applicable to halloons and zliriggr lrl nir ships. It is also ulivi; "is that my ini proved tiring 1ue :l'mini$ in while mipeeially ahplieahlo to aerial proiee'rtiles nia,r he i, .l mi in ordinair;v projeetilen tl' he. tired from rilled cannon, lit iS also to lie underntooil that, while l ,have illustrated the pretem'ed torni ot in v inventi/on, the detalla ot cnnstrnrtion herein disait f`:ed muy he widely varied With- 113i. ont departing; from the spirit i ntl scope of my invention. llor instance inn xl of the groove in 'he outer Surface of the shell l may employ spiral rihn.

l elain: 11() and rotative movements of said body portion and stem.`

5. A projectile comprising a body portion having a spiral air engaging face formed on its outer surface, a guiding stem and a joint between said stem and said body portion permitting relative angular and rotative movements of said stem and body portion.

6. A projectile comprising a substantially cylindrical body portion having a pointed end and spiral groove in its cylindrical surface, a stem provided with guiding vanes and a joint between said stem and body portion in line with the longitudinal axis of said body portion and permitting relative angular and rotative movements of said body portion and said stem.

7. A projectile comprising a shell containing an explosive charge, means actuated by the impact of one end of said shell for eX- ploding said charge, a stem provided with guide vanes, and a joint between said stem and the opposite end of said shell permitting relative angular and rotative movements of said shell and stem. 4

8. A projectile adapted to be discharged from moving air craft, comprising a body portion, means for rotating the same and guiding means for causing the rotation of said projectile to direct it in an opposite direction to its movement from its bodily momentum.

9. A projectile adapted to be discharged from moving air craft, comprising a body portion, means for rotating the same and guiding means for causing the rotation of said projectile to direct it in an opposite direction to its movement from its bodily momentum, and to an extent proportional to its momentum.

In testimony whereof I have hereunto set my hand this 10th day of November, 1911.

FRANK M. BELL.

Witnesses W. B. MoRToN, C. V. MoR'roN.

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