US1563979A

US1563979A - Airplane

Info

Publication number: US1563979A
Application number: US759081A
Authority: US
Inventors: Randolph F Hall
Original assignee: THEODORE P HALL
Current assignee: THEODORE P HALL
Priority date: 1924-12-31
Filing date: 1924-12-31
Publication date: 1925-12-01
Anticipated expiration: 1942-12-01

Description

R. F. HALL Dec. 1 1 935,

AIRPLANE Filed Dec. :51. 1924 4 ets-Shet 1 Dec. 1 192 F. HAL

AIRPLANE 4 Sheets-s 2 Filed Dec.. 31. 1924 R. F. HALL Dec. 1, 1925.

AIRPLANE Filed Dec. 31 1924 4 Sheets-Sheet 5 Maui 012 a F HM Wmm R. F. HALL AIRPLANE Patented Dec. 1, 1925.

UNITED STATES PATENT OFFICE.

RANDOLPH F. HALL, OF ITHAOA, NEW YORK, ASSIGNOR OF ONE-FOURTH IO THEO DORE P. HALL, OF WALLINGFORD, CONNECTICUT, AND ONE-FOURTH ,TOPAUL WILSON, OF ITHACA, NEW YORK.

Amrmim.

To all whom it may concern:

Be it known that I, RANDOLPH F. HALL, .a citizen of the United States of America, and a'resident of Ithaca, county of Tompkins, State pf New York, have invented certain new and useful Improvements in Airplanes, of which the following is a specification.

This invention relates to certain improvements in airplanes, and the nature and objects of the invention will be readily recognized and understood by those skilled in the arts involved in the light of the following explanation and detailed description v of the accompanying drawings illustrating what I at'present consider to be the preferred embodiments or mechanical and aerodynamical expressions of the invention from among various other forms, arrangements, combinations and constructions of which the invention is capable within the spirit and scope thereof.

In the arming of aircraft for offensive and defensive purposes it is an aim and desire to so mount suchordnance on the craft as to obtain therefrom as wide and as unrestricted a range of fire in all directions from the craft as is possible, in order to secure a maximum protection or offensive strength from the ordnance with a minimum of vulnerability in the defense of the craft. However, due to the design, construction and aerodynamical characteristics of aircraft, and particularly such craft of the heavier-than-air or airplane types, certain problems are encountered and disadvantages result in practically carrying out the above aim in the attempt to secure the desired wide and unrestricted range of fire from aircraft mounted ordnance and the resulting offensive and defensive efliciency of such ordnance. I

The conventional and prevailing manner of arming aircraft in general use and familiar in this art, embodies the mount ing of the ordnance in the form of machine guns, cannon or the like, hereinafter referred to in a broad generic sense as guns, at fixed locations on the craft by mounts which permit of adjustment of the guns in both a horizontal 'and a vertical plane. These mounts are generally located on an element of the aircraft, such as the fuselage, nacelle or wing thereof adjacent a cockpit or gunners station from which they are accessible for operation by 'a gunner, and are limited to the extent of exposed structure due to the prime. necessity in aircraft for maintaining head or parasite resistance at a minimum, as well as to maintain the mount within operating reach of the gunner, so that the range of adjustment of a gun so mounted is accordingly limited. With the foregoing mounting of a gun at a fixed location the range of fire thereof is materially restricted by interveningstructure of the aircraft with the result that blind angles are created through which it is not possible to fire the gun, and the offensive and defensive efiiciency thereof is lowered and the vulnerability of the craft to atack is increased. The correction of these so-called blind angles of an aircraft mounted gun by the mountingof additional guns on the craftvat locations to permit of their firing through such blind angles entails an increase in weight of the craft and the lowering of the general efficiency and performance thereof, while the elimination or reduction of these angles through structural and design changes in the craft is not generally possible or feasible for'aerodynamical and strength reasons, as will be readily understood by those familiar with the aeronautical art.

Hence, one of the fundamental aims and objects of the present invention is to increase the effective range of fire of ordnance mounted on aircraft, with a resultingjreduction in blind an les and increase in the offensive and defensive efiiciency of aircraft mounted and carried ordnance, without material increase in the parasite resistance or weight of the craft, or reduction in the general aerodynamic performance thereof."

A further object of the invention is the provision of an ordnance or gun mount for aircraft which is capable of movement to various positions on and with respect to the element of the craft on which mounted so as to increase the effective range of fire.

A further. object. of the invention is to provide an ordnance mount for aircraft which is movable to various locations on the craft to increase and vary the range of fire thereof, and in which provision is made for automatically operating control surfaces of the craft to compensate for the shift of the weight of the mount to different points and thus maintain the proper balance and equilibrium of the craft in operation.

A further object of the invention is the provision of an ordnance or gun mount for aircraft which is movable to different positions on the element of the craft on which mounted, and which embodies a novel gunners seat movable with the mount to the various positions on the aircraft element.

A further object of the invention is to provide an ordnance or gun mount for aircraft which is movable along and over an elongated open cockpit or passageway for a gunner formed in the element of the aircraft on which the mount is movably mounted, with a cover or closure for the passageway automatically operated by the mount to maintain the passageway closed in all positions of the mountand thus prevent material interruption in the surface or contour of the element and resulting loss in aerodynamic eiiiciency.

A further object of the invention is to provide an ordnance or gun mount for aircraft, movable to various positions on the craft and carrying a gunner's seat from which the ordnance on the mount is operable, and which mount is movable to the various positions on the aircraft by the gunner.

A further object of the invention resides in the design, construction and arrangement of an elongated or extended open gunner-s cockpit or passageway in an aircraft element without materially decreasing the factor of safety of the element or the aerodynamical efficiency thereof, and from which passageway ordnance mounted on the element can be operated.

Another object of the invention is to increase the useful load or weight carrying capacity of armed aircraft by providing gun mounts which will permit of a reduction in the total number of guns necessary to effectively provide the desired offensive and defensive strength of the craft.

Another object of the invention is to provide ordnance or gun mounts for aircraft which will permit of a concentration of the ordnance or guns carried thereby at the most effective points on the craft to meet the exigencies and conditions developed during combat with the aircraft on which mounted.

A further object of the invention is to provide an ordnance mount for aircraft which is capable of and adapted for mounting on an aircraft at any desired point on a major element thereof, such as the body,

mea re sustaining surfaces or the like, for movement to various positions on and with respect to the element on which mounted and installed.

Still further objects of the invention are to provide certain improvements in the detailsof design, construction and mounting of movable aircraft ordnance or gun mounts to increase the efiiciency of such mounts in operation and use on aircraft.

With the foregoing general objects and certain other objects and results in view, which other objects and results will be readily apparent from the following explanation, the invention consists in certain novel features in construction and in combination and arrangement of elements, as will be 7 more full and particularly referred to and specified ereinafter.

Referring to the accompanying drawings:

Fig. 1, is a view in side elevation, partly in section, of a portion of an airplane fuselage with the ordnance mount and gunner's seat of the invention mounted in operative position thereon, and showing more or less diagrammaticallythe gun mount actuating mechanism for operating a control surface of the airplane, the skin of the fuselage be ing partly removed.

Fig. 2, is a view in top plan of a portion of the fuselage of an airplane with the skin or covering removed, formed to provide the elongated open top gunners cock it, and showing the gun mount and seat 0 the invention mounted thereon.

Fig. 3, is a top plan view anore or less diagrammatical, of an airplane provided with a gun mount of the invention on the fuselage thereof, and further showing a mount of the invention mounted on a wing of the airplane and disclosing the mount actuated mechanism for operating lateral control surfaces on the wing.

Fig. 4, is a view in front elevation of the airplane of Fig. 3', showing the wing ordnance mount thereon.

Fig. 5, is a diagrammatical view in side view throu h the fusela e of Fi 2 showirw b b h a the construction and arrangement thereof to form the gunners cockpit and the gun mount receiving track with the mount and seat in operative position therein and thereon. p I

Fig. 9, is a longitudinal, vertical sectional portion of the fuselage of Fig. 2, showing the gun mount and. gun'ners seat n side elevation with the folded position of-the'seat indicated in'dotted outline.

'10, is a detail sectional View through 1 the gun mount of the invention showing, a form of operat1ngmechan1sm for moving ,fthe mount. a,

' ..Fig. 10.

.Fig. 11', is a detail section through the mount and form of operating mechanism of s Fig. 12,. is a view in top plan showing the gun mount of the invention mounted on the'airplane fuselage'with the mount oper ated cover or closure for the gunners cockv pit'or passageway formedinthe fuselage. 1 ,Fig. 13, is a diagrammatical view in edge or side elevation of thegun'mount with the and winding rolls is a detail sectional view showing therefor.

Fig. 15 is a detail sectional, view through aportion of'the' cockpit cover or closure showing one of the strengthening orlstiifening stays therefor.

' Fig. .16, 1s a. more or less diagrammatieal view in top plan of an airplane of ,the. .multiplane type provided with opposite I side gu'nners 'nacelles between the Wings invention mounte thereon.

thereof and 'havin ordnance mounts-of the 'Theinvention is disclosed in the accomipanyingdrawings and describedvherewith as 'mounted onand appliedto aircraftof the iheavicr-than-air or airplane types, but this disclosure is. purelyfor purposes of; example and not by wayvof limitation, as theinven- "general application to aircraft of bothf'the lighter-than-air and the heavier-thamalr types,-while certain features thereof are of tionand the several features thereof are of general application. for the mounting of 1 ordnance, aswill be recognized by those skilled in theartl: The'embod'iments' of the i invention shown herewith for application to aircraft of the airplane types, are presented because the several problems solved and disadvantages overcome are encountered in ahigh degree in "airplanes, and hence these embodiments and their application sci-re to more clearly bringforth 7 and exem-L plifyfthe principles and various features of thejinvention. i, c According to: the invention an ordnance or gun mount 18 installed and mounted on an element of anairp'lane for movement thereon to various positions, in'such a'man} ner that the gun-carriediby'the vmount is operable in all'pos'itions on the. element by u gunner; One embodiment oflthe invention ,is disclosed in the accompanying drawings as applied to and'installedjon,.the'body or fuselage of an airplane "for movementj in not so limited, embodies an annular struc- 9o a longitudinal or fore. and aft dirccliondo various positions thereon, the fuselage bemg formed to provide an extended cockpitor passageway through which a g-unncinpositions on the fuselage. In'this embodiment andapplication of the invention, referring now to F igs. 1, 3,-and 16 in-particib moves with the gunmount to the various lar, the fuselage or body 10 of an airplane of conventional or other design ortypc embodying the usual supporting surfaces 11, of the monoplane or multi-plane types,

and the empennage or tail unit 12, is formed with an elongated-or extended passageway or cockpit 14 disposed longitudinallyof the fuselage 10 between empennagc 12 and the supporting surfaces 11, "which cockpit:

opens through. the upper side of the fuselage. An ordnance or gun mount M is the passageway or cockpit 14 for movement therealorig to, various positions on the, fuse lage, and in the present example, although hire-extending across the, cockpit '14 am within and by'whiehthe gunner stands and I is surrounded to operate a gun mounted and carried thereon, in the usual manner.

A possible'design and arrangement ofthe'.

'movably mounted on the fuselage 10-over fuselage 10 to provide the gunners passage- .9

way 'oicoekpit 14 therein, which will be un-' obstructed from end to end thereof and open along and through the top or upper side of the fuselage,- while retaining in the fuselage the requisite strength and aerodynamic characteristics, is illustrated in detail by Figs; 1, 2, 8 and 9 of. the accompanying drawings. Inthis'instance and .as an example, the fuselage 10 is of the trussed' metal frame type and embodies the upper and lowertubrilar longrons or longitudinals 15 and 16, respectively, connectedand joined, at the opposite sides of the fuselage, respectively, by the spaced vertical; struts ,or compression members 17, with any suit able or desired arrangement of diagonal brace wires 17' (see Fig. 9) arrangetlbe- I tween the upper and lower longrons '15 and 16, and membersl'? at each side of the fuselage. The lower l'ongrons 16 are-conneeted and joined by the series of horizontal, I

spaced cross members or struts 18, and suitstead of the conventionalconstruction of the fusela e and frame at the upper side thereof with the usual series of spacedhorizontal cross members or struts, such as "the cross member20, at the rear or tail end of the fuselage between upper longrons '15 ee 'Fig. 2), the invent-ion provides. a

trussed frame arrangement and construction by which the unobstructed, open top 1c fairing 19 is provided .depending'from and forming the lower or under side 'of the fuselage, all in the more or less conventional manner familiar in this art; 1 However, in'-' side of the passageway 10, and in the present example extend froma point forward of the empennage 1.. on, the fuselage (cross member 20) to a point aft or to the rear of the supporting surfaces 10. Each rod 21is secured to and connected with the adjacent frame longron 15 by a series of spaced horizontall disposed members or bars 22 extending etween rod 21 and longron. 15, above and in substantially the same vertical plane as the cross members or struts 18,

respectively, between the lower longrons 18.

Vertically disposed diagonal brace members or struts 23 extend downwardly and inwardly from-the point of connection or juncture of each member 22 with the adjacent longron 15, to the substantial centers of the members 18 therebelow, respectively, so that spaced pairs of these brace members 23 are formed converging downwardly from the upper longrons 15 to the center of the respective member 18 therebelow, and form, with rods 21 and members 22, trusses supporting rods 21 and the upper side of the fuselage.

A series of spaced cross bars 24 are extended between and secured to the pairs of opposite vertical struts 17, respectively, spaced above and in substantially the same vertical plane as the cross members 18, respectively, opposite horizontally disposed longitudinal bars 25 being preferably interposed between the ends of cross bars 24 and the adjacent vertical struts 17 respectively, as particularly shown in Figs. 8 and 9. The cross bars 24 are intersected and joined by the vertical converged. struts 23 and thus form therewith, in effect a central, triangular truss beneath the bars 18 and connecting the same with and supporting such bars from the .cross members or struts 18 between the lower longrons. Additional truss members 26 are secured extending downwardly and outwardly from the point of connection of each strut 23 with a cross bar 24, to the point of connection of-the adjacent cross character disclosed can be and supported on the cross bars 24 and longitudlnal bars 25 to form a support for a gunner throughout the length or extent of V the cockpit or passageway 14.

The fuselage frame formed and constructed as above described is covered or enclosed by any suitable or desired material 23 v over and across the space between the rods 21 and the upper longrons 15 and terminatmg at and along rods 21 so as to leave the upper side of the cockpit or'passagewa'y 14:

open and unobstructed. By the ore oing construction of the fuselage 10 and rame therefor, the elongated or extended longitudinally disposed cockpit-1,14 is. formed, open at its upper side and unobstructed throughout its extent without structurally weakening the fuselage or decreasing the aerodynamic efiicien'cy thereof through interruptions or deformationsin the contour or shape thereof. -.The principles in design and construction exemplified by the fuselage 10 are not limited't'o such element of an aircraft, asa icockpit'or passa eway of the ormed in any aircraft element having the general characteristics of'an enclosed and trussed frame, such for example as the win or supporting surface of an airplane, and contemplates and includes such formation or its equivalent in any suitable element.

The ordnance or gun mount M for installation on the fuselage 10 for operation by a gunner from the cock it or passageway 14, in the example hereo embodies a lower or base ring 30 and an upper ring 31'rotatably mounted and superposed thereon as clearly shown by Figs. 8, 9, 10 and 11 of the drawings in particular. rotatably mounted on the lower ring 30in any well known or suitable manner, as by the interposition of anti-friction rollers,

The upperring 31 is.

the invention and 31 are horizontally disposed on'the up-- per side of fuselage 10 across cockpit-14;

for movement longitudinally, therealon'g,'

with the upper ring rotatable on the lower or base ring 30. Grooved rollers 32 are rotatably mounted and journaledv on suit-I ablepins or stub shafts de ending froi'n and carried by the lower or; use ring 30, and

are so disposed and located thereon wvith' respect to the opposite'side parallel 'rodsj 21 of fuselage 10- and cockpit 14, as tofit 1 onto and receive J-said rods, which form a supporting and guiding track. therefor" and "maintain the-rin iii-mounted posit-ion'on the fuselage; us,therings.30 31' are movably. or slidably= mounted and'confincd on the rods 21 av movement) thereon along and longitudinallyof the cockpit 14 -.-In.o rder to provide for locking or confine ing the rings -31 of the mount 17 in the desired'position on the rods 21 and over the cockpit 14, a manually operable, spring controlled lock lever 33 is pivotally mounted on the under side of base ring 30 adjacent one: of the cockpit side rails 21 for engagementwith any desired one of a series of bores or recesses 34 formed at spaced intervals along the inner side of such rod 21. The spring 35 of the lever "(see Fig. 2) normally forcesthe same into engaging position, so that to release the lever and permit movement of rings 30-31 along rails 21, the lever is manually swung against the tension of spring'35 away from rail 21 to non-engaging position, as will be clear by .reference to the accompanying drawings.

Any suitable or desired ordnance, such as themachine gun G shown in Fig. 1, is

mounted and supported on the upper ring 31 for rotation therewith by means of the usual adjustable mechanism G well known and in general use for this purpose to permit of vertical adjustment or raising or lowering of the gun G, the gun being adjustable in a horizontal plane by rotation with the ring 31 on the base ring 30, as will be readily understood by those familiar with this type of ordnance mounting. In operation and use of the movable mount M with gun G carried thereby, a gunneris stationed in the cockpit 14 and stands in position surrounded by

rings

30 and 31 with thegun G accessible for firing operations. WVhen the gunnerdesires to change the angle of fire of gun G to avoid, for example intervening structure of the airplane with respect to the objective, lever 33 is released and the gunner moves to the desired point in cockpit 14, sliding the gun mount M supported on rods 21 by rollers 32, to the desired location and then releasing. lever 33 to engage one of the recesses 34 and lock the mount in the new position on the fuselage 10. In Fig. 1 of the drawings the forward position of mount M is shown in full lines with possible lines of fire F, with respect to the wings 11 and empennage 12 shown by broken lines, while a rearward or aft position of mount M is diagrammatically indicated by dotted lines withpossible lines of fire F shown by broken lines. The mount M is of course movable to any desired point between the disclosed positions by the gunner, and it follows that with the mount so movable longitudinally along fuselage 10 and cook'- pit14 the range of fire of gun G'is material- 1y increased while the blind angles are substantially decreased with increased offensive and defensive efliciency from gun G or other ordnance carried by mount M.

The shifting or changing of the weight of the mount M and the weight of the gunner, to the different positions along the cockpit 14 longitudinally of the fuselage 10 in operation of the mount, will tend to upset or disturb the proper balance or equilibrium of the airplane on which mounted by this redistribution and changing of the weights along the fore and aft axis of the craft, and the invention provides for effectively com pensating for these conditions to maintain the roper longitudinal equilibrium of the airp ane. The empennage 12 includes the usual or any desired horizontal stabilizer surface 36, referring now to Figs. 1 and 2 of the drawings, and this stabilizer is pivotally mounted adajacent its leading edge by a pivotal mounting 37 to permit of vertical adjustment or raising and lowering of this stabilizer surface. The mount M is suitably operatively connected with stabilizer 36 so as to raise and lower the same to properly compensate for the shifting of weight in moving the mount along the fuselage. In the present embodiment of this feature, the

lower or base ring 30 of mount M is propulleys or rollers 40 mounted at the forward and after ends, respectively, of the cockpit 14 in the upper portion thereof, and operatively over suitable reduction mechanism or gearing 41 (see Fig. 1) mounted forwardly of and below the after pulley 40,- as will be clear by reference to Fig 1 of the drawings. An adjustment rod 42 depends within the tail of fuselage 10 from the stabilizer 36 and is pivotally coupled to the horizontal arm of a pivotally mounted bell crank lever 43. A cable 44 is operatively connected at its endsto the ends, respectively of the vertical lever of bell crank 43, and. extends rearwardly around and over a takeoff pulley 45 operated by the reduction gearing 41. With the foregoin ism, movement of the mount M in either a mechanforward or rearward direction along fuselage 10 will cause cable 39 to rotate the reduction gearing 41, which in turn will operate the pulley 44 to swing bell crank 43 through cable 44, and results in elevating or lowering the stabilizer 36 in accordance with 41 and elements operated thereby with respect to the movement of the mount M to properly adjust stabilizer 36. In this manner, the chan es in location of the center of gravity of tie airplane by shifting the weight of mount M and the gunner along the fuselage are automatically compensated for by stabilizer 36, and the balance of the airprlane maintained.

ith the elongated or extended open top or side cockpit 14 formed in the fuselage 10, the aerodynamic efiiciency of the fuselage may be lowered by this open cockpit, and the invention eliminates this condition through the medium of an automatically operated and controlled cover or closure which maintains the cockpit closed and substantially carries outthe shape or con-tour thereof irrespective and in any position, of the mount M thereon. A possible embodiment of this feature of the invention is di closed in Figs. 12 to 15, inclusive of the accompanying drawings. The gun mount M is provided with a forwardly extending flange 46 and a rearwardly extending flange 47, preferably although not necessarily, formed of sheet metal and secured to the lower or base ring 30 of mount M. A strip or length of fabric or other suitable material 48 is secured at one end to the forward flange 46 of mount M and extends forwardly therefrom over and covering the portion of cockpit 14 forward of the mount, and a similar strip of fabric 49 is secured to rear flange 47 and extends rearwardlytherefrom over and covering the portion of the cockpit aft of mount M. These strips ofmaterial 48-49 extend over and close the cockpit 14 from end to end thereof, with the exception of that part over which mount M extends and through which the'cockpi-t is open and accessible, and form and provide the cockpit cover or closure 50.

At each end' of cockpit or passageway 14, a roller 51 is mounted within the fuselage and disposed horizontally and transversely thereof. The rollers 51 are preferably of the well known and understood springactuated self-winding curtain roller type, although any other suitable type of roller or winding mechanism may be' employed.

The free ends of the

strips

48 and 49 of.

cover 50 are attached to and wound on these rollers 51, so that the strips are maintained taut and without slack, stretched between the mount M andthe rollers, and covering and closing the cockpit 14. Suitable opposite edge guide members or flanges 52 (see Fig. 14) are provided for the cover 50 and in the present example are secured to the

members

21 and 22 of the fuselage frame and extend over and confine the edge portions of the cover 50 against displacement, the cover freely sliding under and along these guides 52, as will be clear from Figs.

12 and 14 of the drawings. Preferably, where the cover 5O is formed of fabric material suitable transverse stays 53 are secured at spaced intervals along the lower or under side of the cover in order to stiffen and strengthen the same while permitting the cover to freely wind and unwind from the rollers 51. A possible manner of securing and mounting these stays is disclosed by and will be readily apparent from Fig. 15 of the drawings.

In operation of the cover 50 formed and mounted as above described, as "the mount M is moved along and over cockpit 14, the ends of the

strips

46 and 47 of the cover are wound or unwound from the rollers 51, and in all positions of the mount M the cockpit or passageway 14 is covered and closed by this cover, except the portion beneath the mount itself, as will be clear. The cover 50 thus forms in effect, with the fuselage covering at the sides of cockpit 14, the upper covering or skin for that portion of the fuselage occupied by the cock pit 14, and presents the desired substantially unbroken continuous surface carrying out the contour and shape of the fuselage. In this manner the aerodynamic efiiciency of the fuselage is maintained, notwithstanding the formation of the elongated or extended cockpit 14 therein, and further the movement of the mount M along this cockpit 14 is possible while maintaining the latter closed.

A further feature of the invention provides a gunners or occupants chair or seat movable with mount M and from which the mount and ordnance carried thereby are operable. The construction, arrangement and mounting of this seat or chair is disclosed in Figs. 1, 2, 8 and 9 of the accompanying drawings. A pair of spaced opposite side bars are secured at their upper ends to the rearward or after side of the base ring 30 of the mount M, and depend downwardly therefrom into the cockpit 14 a distance above the floor 27 of cockpit 14. The side bars 60 are converged inwardly and downwardly to and terminate at the floor 27 to form the chair supporting legs or base members 61. Any suitable or desired material is mounted between the side bars 60 above members 61 to form with side members 60, the chair or seat back 62. At the lower ends of s ide members 60 above and adjacent members 61, aseat orchair bottom 63 is pivotally mounted to and between the forwardly extending ears or lugs 64 (see Fig. 9), and extends horizontally and forwardly from members 60in normal seat forming position. A support is pro vided for and between the forward portion of the seat 63 and the lower converged portion of the members 61 to support the seat in normal position, and in the present example embodies the telescopic-members 65. and v66 (see Figs. 8 and 9). The member 65 is'formed by a tube 65 pivotally coupled or spring means (not shown) .is'mounted in' tube 65 upon which the rod 66 bears to form a resilient or spring mounting permitting movement of the seat in normal position to absorb shocks and jars and add 'to the comfort of an occupant seated thereon. .lVith the foregoing seat construction and mounting, the seat or chair-bottom 63 can be folded or swung upwardly .and

rearwardly on the pivots of ears 64 to a substantial .vertical position against the seat back 62 and side bars 60, as shown in dotted outline jinFig. 9, the

telescopic supportforming members

65 and 66 being extended as shown. :In folded position the seat bottom 63 is removed, from position obstructing the cockpit space below mount M and the freedom of the gunner or occupant of this spaceis unhampered thereby.

of the drawings.

A- track. or 'guideway 67 is provided extending centrally and longitudinally of and along the floor 27 of the cockpitor passagewayl, and in the example hereof embodies a channel member having the side'fianges bent-over to provide a central opening or 'slot therealong. The converged end of the members 61 0 th e seat are extended downwardly through theslot of and into the track or guideway 67 and rollersor wheels 68 are mounted at opposite sides thereof within and bearing on and confined by the guidev way 67, as clearly shown by Figs. 8 and 9 Floor cleats or the like 69 are secured to the floor 27 of cook it v 14 along opposite sides ofthe track or gui eway 67- for engagement by the feet of a gunner oroccupant of the seat 637-62. In use and operation, a gunner in the seat can readily propel or move the same as a unit with the mount M, along the fuselage 10 and through cockpit l by engaging the floor cleats 69 and pushing or drawing the seat and mount to'the desired-position.

- The mount M during movement thereof" slides or rolls along the rails or'rods 21, and the seat is guided and'the lower end supported by the rollers 68 in the track or guideway67. I

Whererelatively heavy ordnance such as a cannon or relatively large caliber gun vis mounted 'on and carried by the mount M, mechanism may be provided for moving or propelling the movement wM along thecockpit 71- and fuselage-1109A possible formof such mechanism is illustrated in Figs. 10 and 11 'of the accompanying drawings, and embodies a rack, bar or the like secured along the under side of one of of a shaft 73 rotatably journaled in and;

disposed transversely of the hanger 72. A

hand operating wheel 74 is mounted and fixed on the inner end of shaft 73 disposed within cockpit 14'and accessible for operation by a gunner in the cockpit. In oper- 'ation, the hand wheel 7-1 ,is rotated by a gunner in'the cockpit, or from the seat 63-62,- which rotates pinion 71 in engagement with rack bar 70 and, propels'the mount- M along the fuselage 10 and cockpit 14. \Vith such propelling mechanism the mount,M is readily moved to the desired position, irrespective of the weight or type of ordnance which may be carried thereby.

The invention contemplates and includes the mounting and installation of the gun mount with the various features of the invention herei'nbefore described and explained, on other elements of aircraft than a fuselage or body, such as the fuselage 10, and in F igs. 3, 4 and 7 of the accompanying drawings a possible mounting on the wing of an airplane is disclosed. Referring now to Figs3 and 4, an airplane 'is shown of the 'monoplane type, althoughthe invention is not limlted to monoplanes,-having the monoplane wing 11 of therelative- 1y thick or deep section type, including and provided with theusual ailerons 11, or other desired lateral 'control surfaces. An elongated cockpit or extended passageway 14' is formed at thecentral portion ofwing, 11, disposed longitudinally thereof and transversely of the fore and aft axis of the airplane, This passageway 14" is similar to that described as formed in the fuselage 10, in that it'provides an open top and optudinally of, wing. 11 and of the passageway 14/. The structure of the wing can formed in any suitable or desiredmanner to provide the unobstructed, open top "passageway or cockpit 14', without structurally weakening the wing or lowering its efiicien- J cy, as for example inaceordauce with the construction of the fuselage cockpit He, and

further if desiredorH found expedient-can .be curved as shown in dotted outline in Fig. 3 to form the arcuat-epassageway 14:".

A gun mount M. of the invention, in-

on the wing cockpit 14 for movement mof - weight of mount M and the gunner laterally of the airplane, flaps or control surfaces 12 are provided at opposite sides of wing 11 for automatic operation by mount M;

Each flap 12' is provided with the usual control mast or horn 75, the opposite ends of which are connected to the ends of a cable 76 extending over and around va pulley 45 carried by suitable reduction earing tively are operativcly connected and coupledby a cable 77 extending therearou'nd and therebetween. One side or ply of cable 77 is connected with the movable gun mount M, so that, as the mount is moved to one side or the other of wing 11,

-* 'fiaps 12' will be operatedto compensate for the shift in weight and maintain-the desired lateral equilibrium or balance of the airplane.

In Figs. 5, 6 and 16 of the drawings another manner and arrangement for mounting the movable gun mount M is shown. In this adaptation of the invention, an open top cockpit forming nacelle 80, referringparticularly to 'Figs. 5 and 6, is formed on and extending transversely across a wing 11 or other member or element of an aircraft, and the mount M of the invention is installed and movably mounted on the upper side'of the nacelle across the open top of the cockpit formed therein fonmovement longitudinally thereof. An airplane of the biplane or multiplane ty e is shown in Fig. 16, in which a pair o nacelles 80 with mountsbf mounted thereon, are disposed between the wings 11 at opposite sides of fuselage 10 and extending forwardly and rearwardly of the Wings 11.

With an alrplane equipped with the mounts M of the invention on the body or fuselage thereof and also on the wings, as shown more or less diagrammatically by Figs. 3, 4 and 16 of the drawings, it is possible 'to secure an effective concentration of ment over one cockpit or passageway and mounted at the forward end of cockpit 14 I which are operable by a gunner from the seat of the mount when the latter is. in its' normal forward osition onthe fuselage, as shown by full ines in Fig. 1.

Additional guns can be mountedfor firing through openin s formed in the bottomv of the-fuselageo'i? ody '10 of the airplane if desired to increase the defensive and offensive strength thereof and may be'operated independently of the ordnance carried by the gun mount,;as"willbe obvious tothose skilled in the art.

\Vhile the invention is disclosed and intended primarily as an ordnance or gun mount, it is to be understood that the mount can be employed for various other purposes as a support or'mount for other devices and instrnmentalitiesthan ordnance, and the term gun or ordnance mount as employed in the appended claims is intended to cover and include such other uses and the mounting of other devices thereon.

It is also evident that .various changes,

modifications, variations andv substitutions might be resorted to without departing from the spirit and scope of my invention and hence I do not desire to limit my invention to the exact and specific disclosures hereof.

Desiring to protect my'invention :in the broadest manner legally possible, what I claimis: v

1. In combination, an airplane element formed with an extended substantially horizontally disposed passageway thereinjand 119 a mount for ordnance mounted on said? ele= ment for movement as a unit horizontally along said passageway.

2. Ii) combination, an aircraft element.

formed with a substantially horizontally disposed passageway therein, and an ordnancemount movably mounted on said element over said passageway for movement therealong to. various positions on and with respect to said element. 1

3.-In combination, an aircraft, elementformed with an open top passageway therein,,and an .ordnance'mount on said element above said passageway and movable there-- along and thereover on said element. 7 y I 4. In combination, anaircraft elementformed with an extended open passageway therein, disposedsubstantially parallel to the axis thereof,-an ordnance mount movable along said passageway, and

gunnei s I seat carried by and movable with said mount. v v

5..In combination, an aircraft element formed with an extended open passageway 7 within said passageway and movable therealong with said mount.

7. In combination, an aircraft element, an ordnance mount movablymounted for movement thereover in a substantiall horizontal plane to various locations t ereon, anda seat carried by and movable with said 3 ing said passageway.

mount.

8. In combination, an aircraft element. "formed with an extended passageway theremount, and the said seat foldable to position unobstructing said passageway beneath said mount.

10. In combination, an aircraft element formed with an extended passageway therein, an ordnance mount mounted oversaid passageway and movable therealong, a gunners seat within said passageway beneath said mount and foldable to position with respect to the mount unobstructing said passageway beneath the mount.

11. In combination, an aircraft element formed with an extended passageway thereners seat carried b in, a mount for ordnance mounted over said passageway and movable therealong, a unand depending rom said mountto position within the passageway, and ide means within the passage- 7 way for said seat.

12. In combination, an aircraft element formed with an extended open passageway therein, a mount. for ordnance mounted for movement along said passageway, a gunners seat supported by said mount within the passagewa and movable therewith, and

guide means or the seatwithin said passageway, the said seat foldable to position unobstructing that portion of the passageway in line with said mount.

13. In combination, an aircraft element formed withan open passageway therein,

along said passageway, a gunners seat carried by and movable with said mount within the passageway, said mount accessible from the seat, and means operable from said seat for moving said mount.-

14. In combination, an aircraft element formed with a substantially horizontally disposed passageway therein, a mount forordnance movable along said passageway, a seat within the passageway carried by and movable with said mount, and said mount and seat movable by a gunner in position in the seat.

15. In combination, an aircraft formed with a substantially horizontally disposed gunners passageway therein, a mount for ordnance movable along said passageway, a seat within the passageway carried by and movable with said mount, and means within the passageway for engagement by a gunner 1n the seat for moving said mount along the passageway.

' 16. In combination, an aircraft element formed with a passagewa therein, a mount for ordnance movable a ong said passageway, a seat within the passageway carried by and movable with said mount, and members within the passageway for engagement by the feet of a gunner in the seat for fore-- ing said mount and seat along the passagevway.

17. In combination, an aircraft element formed with an elongated open passageway therein, a mount for ordnance mounted over and across said passageway for movement therealong, a gunners seat within said passageway having the back thereof secured to and depending from one side of said mount, a guideway for the lower end of said seat within the passageway, a. bottom for said seat pivotally mounted from the seat back and foldable to position unobstructing the passageway below said mount, and said seat movable as a unit along the passageway with said mount.

18. In combination, an aircraft including a control surface therefor, and a movable ordnance mount operatively connected with said controlsurface. r

19. In combination, an aircraft, an Oldnance mount movably mounted thereon, and

means operated by movement of said gun mount for maintaining the balance of said craft by compensating for the shift in position of the mount thereon.

20. In combination, an aircraft, an ord-. nance mount movably mounted for movement to various locations thereon, and means for compensating for the change in location of said mount to maintain the balance of the craft.

21. In combination, an aircraft, an ordnance mount capable of movement to various locations on the craft, and means for autoa mount for ordnance movable over andmatically compensating for'the change in S location of the mount to maintain the balance of the craft.

22. In combination, an aircraft, an ordnance mount capable of movement to various locations on the craft, and means for compensating for the shift in location of the weight of said mount on the craft.

23. In combination, an aircraft, an ord nance mount capable of movement to various positions on the craft, and means operated in fdr the shift in location of the weight of the mount on the craft. e

24. In combination, an aircraft including control surfaces therefor, and an ordnance mount capable of movement to various locations on the craft, the said mount connected with said control surfaces to operate the same to compensate for the change. in location of the weight of the mount on the craft.

25. In combination, an aircraft including a control surface therefor, and an ordnance mount capable of movement to various locations on the craft, the control surface operated by the mount to maintain the balance'of the craft with the mount moved to different positions thereon.

26. In combination, an aircraft including a body and a control surface thereof, and an ordnance mountca able of movement longitudinally along said body, the control surface operated by the mount to maintain the longitudinal balance of the body and craft.

27. In combination, an airplane includin a fuselage and a horizontal stabilizer, an an ordnance mount capable of movement longitudinally of the fuselage, the horizontal stabilizer operated by movement of the mount to maintain the longitudinal balance of the craft.

28. In combination, an aircraft including a control surface, and an ordnance mount capable of movement along the fore and aft axis of the craft, the control surface operated by movement of the mount to maintain the fore and aft balance of the craft.

. 29. In combination, an aircraft including control surfaces therefor, and an ordnance mount capable of movement laterally of the craft, the control surfaces operated by movement of the mount to maintain the lateral balance of the craft.

30. In combination, an aircraft includin a supporting surface and lateral eontro surfaces therefor, an ordnance mount capable of movement laterally of the craft, the lateral control surfaces operated by movement of the mount to maintain the lateral balance of the craft.

31. In combination, an aircraft includin a supporting surface and lateral contro surfaces therefor, an ordnance mount caable of movement on the supporting surace laterally of the craft, and the control movement of the mount to compensate surfaces operated by movement of the mount to maintain the lateral balance of the craft.

32. In combination, an aircraft includin a supporting surface and lateral contro surfaces therefor, an ordnance mount on the supporting surface movable thereon laterally of the craft, and said mount connected with said control surfaces and operating the same during movement of the mount to maintain the lateral balance of the craft.v

33. In combination, an aircraft including longitudinal and lateral control surfaces therefor, an ordnance mount capable of movement laterally of the craft, the lateral control surfaces operated by said laterally movable mount to maintain the lateral balance of the craft, an ordnance mount capable of movement longitudinally of the craft, and the longitudinal control surfaces operated by said longitudinally movable mount to maintain the longitudinal balance of the craft.

34. In combination, an aircraft element formed with an open passageway therein, an ordnance mount movable along said passage- Way, and means for maintaining said passageway closed in all positions of said mount therealong.

35. In combination, an aircraft element formed with an open passageway therein, an ordnance mount movable along said passageway, and means operated by said mount for maintaining said passageway closed in all positions of said mount thereon.

36. In combination, an aircraft element formed with an open passageway therein, an ordnance mount movable along said passageway, and a cover for maintaining that portion of the passageway unoccupied by said mount closed.

37. In combination, an aircraft element formed with an open passageway therein, an ordnance mount movable along and over said passageway, and a movable cover operated by said mount for maintaining the passageway closed irrespective of the pos1tion of said mount thereon.

38. In combination, an aircraft element formed with an open passageway therein, an ordnance mount movable along and over said passageway, and a cover connected to opposite sides of said mount and drawn thereb over and covering said passageway in a1 positions of the mount thereon.

39. In combination, an aircraft element formed with an open passageway therein, an ordnance mount movable over and along said passageway, a cover connected to opposite sides of said mount and extending over the passageway to opposite ends thereof, respectively, and means for automatically windin and unwinding said cover at opposite ends of the passageway as the said mount is-moved thereover.

40. In combination, an aircraft element formed with an open passageway therein, an ordnance mount movable along and over said passageway, automatically winding rollers at opposite ends of the passageway, and a cover for the passageway extending thereover from opposite sides of and attached to said mount, to and attached on said rollers, respectively.

41. In combination, .an aircraft element formed with an open passageway therein, an ordnance mount movable along and over said passageway, and a flexible cover for said passageway, said cover connected to and operated by said mount to maintain the passageway at opposite sides of the mount cllosed in all positions of the mount therea ong.

42. In combination, an aircraft element formed with an open passageway therein, an ordnance mount movable along and over said passageway, an automatic windin roller at each end of said passageway, flexible strips connected to opposite sides of said mount and extending and connected to said rollers, respectively, said strips extending over and covering the passageway between the mount and the opposite ends of said passageway to form a cover therefor operated by movements of the mount to wind and unwind from said rollers.

43. In combination, an aircraft element formed with an open passageway therein,

and a cover for said passageway formed of flexible strips extending thereover and substantlally carrying out the contour of said element, the said strips mounted for moveing a 'body ment over said passageway.

44. In combination, an aircraft element formed with an open passageway therein, and a cover for said passageway formed of flexible strips extending thereover and clos ing the same, said strips mounted at opposite ends of said passageway for movement over and across the passageway.

45. An aircraft element formed of a trussed frame providing an elongated interiorly unobstructed passageway therein, a series of transverse, spaced trusses across said member below said passageway, flooring for the passageway mounted on said trusses, one side of said element above said passageway formed with opposite spaced trusses providing an unobstructed opening for said passageway through the side of the member, and trusses between said side trusses and the said transverse trusses, re-

I spectively.

46. In combination, an airplane includand control surfaces, said body formed with an elongated open passageway therein, an ordnance mount'movableover and along said passageway on the body, a gunners chair in the passageway carried by and movable with said mount, and mini rol means for operating the control surfaces -mounted in said passageway, and accessible and operable from saidzontally disposed passageway therein and an ordnance mount embodying an annular base and annular ordnance support rotatably mounted thereon, said mount supported on said element by said base for movement unit.

48. In combination, an aircraft element formed with an extended substantially horizontally disposed passageway therein, and an ordnance mount of the centrally open type adapted to surround a gunner located in said passageway, said mount disposed on the element for movement longitudinally along said passageway.

49. In combination, an aircraft element formed with an extended open-top passa eway therein, and an ordnance mount of t e centrally open type mounted over and across the open top of said passageway and adapted to surround a gunner therein, said mount movable as a unit longitudinally of said passageway to different positions on said element.

50. An aircraft element formed with an extended open top passageway, rail forming members along opposite sides of said passageway, and an ordnance mount supported on said rail forming members for movement along said passageway.

51. An aircraft element formed with an extended 0 en top passageway therein, OPPOf site rail orming members along and defining the o 11 top of said passageway, said rail fdi'ming members providing structural members of the aircraft element,

and an ordnance mount supported on said longitudinally along said passageway as ,'a

ing a base ring mounted over and across the passageway, and rollers mounted on the base ring of said mount in engagement with said rail forming members and sup orting said mount for movement over and along the passageway.

54. In combination, an. airplane element,

an ordnance mount including-a base and an ordnance support adjustably carried thereon, memberson said base for movably engaging the airplane element, and said base mounted and supported 'on the element in av substantially horizontal plane by said en-' gaging members with the ordnance mount.

movable as a unit on and over a surface of the element to different locations there- 55. In combination, an airplane element,

an ordnance mount including a base, said base movably mounted on the element, and the said ordnance mount movable as a unit over a surface and longitudinally of the 1 said airplane element.

Signed at Ithaca, New York, this 20th day of December, 1924.

RANDOLPH F. HALL.