Dec. 3l, 1946. R. A. woLF ETAL SEAL FOR AIRCRAFT CONTROL RODS Filed Aug- 15.1942 2 Sheets-Sheet 1 mgl, @G1435 WM 4 De¢.'31, _1946. R. A. woLF Er Al. _ 2,413,671» SEAL FOR AÍRCRAFT CONTROL RODS Filed Aug. 1:5, 1942. ` ` 2 sheets-snee; 2' A 48 Y NEYS lilìtll Íâatented Dec. 31, 1946 UNITED STATES PATENT-OFFICE 2,413,671 SEAL FOR AIRCRAFT CONTROL RODS Robert A. Wolf and Herbert'L. Bowers, Kenmore, N. Y., assignors to Bell Aircraft Corporation, Buffalo, N. Y. Application August 13, 1942/, Serial No. 4545630 2 Claims. (Cl. 286-15) l 2 c . Fig. 3 is a cross sectional view through an air~ This invention relates to improvements in air craft body and control structure. craft wall showing a modified form of sealing means in elevation; and In aircraft constmction it is necessary to ar- ‘ range control means in such fashion that they Fig. 4 is a fragmentary, longitudinal cross sec~ may be manipulated from within the aircraft to accomplish control functions exteriorly there~ of. To this> end it is required that certain por tional View through the right-hand end of the sea-ling means of Fig. 3. Like characters oi reference denote like parts throughout the several iigures' of the drawings and in Fig. -1- the numeral lil designates a portieri tions of the control means extend through the aircraft wall' structure in such fashion as to be movable with respect tov such wall. In aircraft designed to be used at high altitudes= or under anyl conditions where the atmosphere is sufñ ciently rariiied as to require the maintenance of of an- aircraft wall and numeral It indicates a control element extending therethrough. The opening of the wall lll through which the control element Il extends (not shown) is- considerably >larger than the. control element itself. a pressure higher than that of thesurrounding atmosphere within the -aircraftbodu the problem 15 A collar I2 is disposed against the inner side of the wall Il) and has -av basey flange ,-l-S which is 'riveted to the wall' or otherwise secured in fluid tight relation. A ilexible tube lél- has one of its of extending control means through the wall of the aircraftA body is complicated by the necessity for preventing fluid passage thereabout. The »present invention provides an arrangement - ends disposed about the outer end ci' the collar l2 and may» be secured in position by a conven whereby aircraft control means may be projected ' tional hose clamp iii, or the like. through the-wall of an aircraft-fuselage or other The opposite endy of theI tube' it’ is disposed body portion in such fashion as to insure against about a collar Il and. a second hose cla-mp lli-- is ñuid leak through such wall, while at the same providedv for maintaining» the' proper assembly'. time providing- a» construction affording- the ut most in ease, sensitivity and facility of move 25 If desired, the collars l2 and l? may be formed with peripheral ridges as at t9, to insure against ment- of the control element. It is desi-red' that axial displacement of the parts; rIfhe coliar il’ such control element be movable both axially to has inner annular formations for receiving and and fro in said wall and bodily about» axes ap-> seatinga pair of` spaced annular bearing elements proximately in the plane of the aircraft wall. It is4 further desired ythat thevv control element be 30 20 and 2l having clamped therebetween a. sealing assembly designated generally 22. The bea-rings freely rotatable about its own-l axis; 2|l`»and 2|»y and., the sealing assembly 22 are re According tothe present invention the sea-lling tained inthek collar I-lby a screw-threadedv gland element'which prevents fluid passage through the 231 aircraft wall at the point oi control emergence is so arranged as not to be subject to loads or 35 As-appears fromr'g». 2, the sealing assembly comprises a pair of complementary annular cage deiiections of any sort, regardless oi the kind of elements 2e, and 25 whichl retain a flexible an movements or forces which may be applied to nular ring 2t which may be of a material having the control element itself. the characteristics of leather or rubber. It wili be Several forms of the improved aircraft control supporting and wall-sealing structure are shown 40 noted that the inner portion of the sealing ring 26 is disposed obliquely against the `control ele and described in detail herein but it is to be un ment Il and the desired form of the sealing derstood that various mechanical modiñcations element 26 is insured by the presence of an en- are within the province of those skilled in the circling coil spring, 2l. art and that the invention is not to be consid It will be noted from the foregoing that the ered limited otherwise than as defined in the 45 bearing elements 20 and 2l insure permanent and appended claims. accurate concentricity as between the collar ll In the drawings: and the control element il. At no time can ma Fig. 1 is a fragmentary cross sectional view nipulative forces applied to the control element through an aircraft body wall showing a control Il dellect or in any other way affect the sealing element extending therethrough and one form relationship of the flexible annulai- element 26. of the improved’ means forJ supporting the control In the form shown in Figs. 1 and 2, the tube ffl element and sealing the aircraft wall; is formed of rubber or the like and has embedded Fig. 2 is a fragmentary, longitudinal cross sec therein a helical coil spring the convolutions of tional view through the left--hand portion of the Àwhich appear at 30 in Fig. 2. The spring 3e sealing means of Fig. 1; 2,413,671 prevents collapse of tube I4 due to fluid pressure forces exerted against the exterior surface there of. In the form shown in Fig. 2 the tube I4 is of increased thickness at the convolutions of spring 33 as indicated at 3l. ing the aircraft body will urge the inner periph ery of the sealing rings into more intimate sealing contact with the surfaces of the associated con» - In the form of the invention illustrated in Figs. 3 and 4 the control element sealing means is functionally the same as in Figs. 1 and 2, the chief diiîerence being in the structure of the ñexible tube, designated generally by the numeral 10 35 in Fig. 3. In Fig. 3 the numeral 31 designates ' an aircraft Wall portion and numeral 38 desig nates a control element in the form of a shaft having operative connection with an arm 39 dis posed outside the aircraft body. 15 Here, again, the opening in the wall 31 is not shown but is considerably larger than the control trol elements. We claim: 1. An aircraft structure comprising an aircraft wall having a control aperture formed therein, an elongated control element disposed Within said aperture and adapted to have a limited amount of movement in substantially all direc tions, said aperture being of a size considerably greater than the size of said element whereby the latter may be free to have unrestricted iioating movement within said aperture, an elongated flex ible tubular member ñxed at one end to said Wall in registration with said aperture, said member projecting only forwardly from said aperture and having an inner diameter substantially equal to the diameter of said aperture, sealing means spaced from said wall and carried by the end oi said member which is remote from said Wall, said means comprising packing means in sealing en gagement with said member, and bearing iianges carried by said tubular member independently of said packing means and axially spaced from each other and from said packing means for support ing said element centrally Within the remote end of said tubular member and for relatively guiding said element in its reciprocating movement therein. parts which are to extend therethrough. Over such opening at the inner side of the Wall 31 there is a collar 40 which is secured to the aircraft 20 wall 31 by means of a base flange 4I which in this instance seats against the outer surface of the wall 31. In Figs. 3 and 4 numeral 43 desig~ nates a collar which is the counterpart of the collar l1 of Fig. 2 and which is connected to the collar 40 by a tube section 43 having ears 43 at its opposite ends for pivotal connection with com plementary ears 41 and 48 formed on the collars 43 and 43, respectively. Pivot pins 50 provide articulated connection between the collars 43 and 30 43 and the tube section 45 and the joints therebe 2. An aircraft structure comprising an aircraft tween are sealed by ñexible sleeves 53, each of wall having a control aperture formed therein, which has an intermediate annular accordion an elongated control element disposed Within said pleated portion 54, to permit free articulation of aperture and adapted to have a limited amount the joints between the collars 43 and 43 andthe o1“ movement in substantially ali directions, said tube section 45. The opposite ends of each sleeve aperture being of a size considerably greater than 53 are disposed about the collars 40 and 43 and . the size of said element whereby the latter may the tube section 45 and may be secured by means be free to have unrestricted ñoating movement of conventional hose clamps 51. The collar 43 isy stepped and formed at its inner 40 within said aperture, an elongated flexible tubular member ñxed at one end to said wall in registra periphery to receive a pair of spaced annular tion with said aperture, said member projecting bearing elements 63 and 3| having a fluid sealing only forwardly from said aperture and having an assembly 62 engaged therebetween. A screw inner diameter substantially equal to the diame threaded gland 63 is provided for retaining the ter of said aperture, sealing means spaced from bearings 60 and 6| and the sealing assembly 32. said Wall and carried by the end of said member The fluid seal of Fig. 4 is the same as that of which is remote from said Wall, said means com Fig. 2 save that a resilient ring 34 is provided prising a collar secured to and in sealing engage for giving shape to a flexible sealing ring 35 and ment within said member, packing means car for urging it into sealing engagement with the ried by said collar, and bearing ñanges secured control element 33. in said collar independently of said packing It will be noted that in both forms of the in means and axially spaced from each other and vention the inner portion of the annular sealing from said packing means ior supporting said ele rings 26 and 35 are directed obliquely along the ment centrally` Within the remote end of said control elements Il and 33, respectively, in a tubular member and for relatively guiding said direction toward the interior of the aircraft body. element in its reciprocating movement therein. By virtue of this construction, fluid pressure with ROBERT A. WOLF. in the aircraft body in excess of those surround HERBERT L. BOWERS.