US2603437A - Highly sweptback wing for flying machines - Google Patents

Description

July 15, 1952 P. H. SATRE HIGHLY SWEPTBACK' WING FOR FLYING MACHINES '7 Sheets-Sheet 1 Filed Dec. 2, 1947 Fie P. H. SATRE HIGHLY SWEPTBACK WING FOR FLYING MACHINES July 15, 1952 7 Sheets-Sheet 2 Filed Dec. 2, 1947 July 15, 1952 P. H. SATRE 2,603,437

HIGHLY SWEPTBACK WING FOR FLYING MACHINES Filed Dec. 2, 1947 7 Sheets-Sheet 3 E T. Z M m new ,w i 1 W! n m z ,4 M F f H Al N fia/ 7 q! 6 n m n F a w a U & a N F. .1M

July 15, 1952 I P. H. SATRE 2,603,437

I HIGHLY SWEPTBACK WING FOR FLYING MACHINES Filed Dec. 2, 1947 '7 Sheets-Sheet 4 FIGS 9 71a 52a 31 V V P. H. SATRE HIGHLY SWEPTBACK WING FOR FLYING MACHINES 7 Sheets-Sheet 5 Filed Dec. 2, 1947 I lnrexfor 2 /0995 27m: 5/1 7796' July 15, 1952 Flled Dec 2 1947 July 15, 1952 P. H. SATRE HIGHLY SWEPTBACK WING FOR FLYING MACHINES 7 Sheets-Sheet 7 Filed Dec. 2, 1947 5 MMQ w I @{exfa Patented July 15, 1952 I HIGHLY SWEPTBACK WING FOR FLYTNG MACHINES I Pierre Henri Satre, Toulouse, France, assignor to- Societe Anonymecalled: Societe Nationale de Constructions Aeronautiques vdu Sud-Est Application Decemberz,1947,,SerialNo.-7$9,151

' 'Iri FranceApril23,194 7 a The present invention relates to' back swept wings,i. e. wings which have a very pronounced V shape as seen in plan. Such wings are used to particular advantage in fast aircraft, in-particular aircraft the speedofwhich approaches or exceeds'that of'sound. Such wings are very heavily loaded, so they have to withstand very considerable forces and their construction sets problems the difiiculty of which is well known. The present invention provides 'a particularly advantageous solution of those problems in'asmuch as it provides a simple and lightweight construction of such'wings. It is moreover applicable to any sweptback surface having a shape similar'to wings such as the fins, empennages or like members. a

It is well known that a cantilever wing can be constructed either by forming the entire wing assembly as an integralwhole which is subsequently assembled with the fuselage, or alter natively forming the wing in two overhanging parts, each of which is then secured-to the fuselage. In the case of abacksweptwing struc-' ture, it issomewhat difflcult to obtain a simple and lightweight construction throughthe use of the first one of the above mentioned methods because of the crooked line formed by resistingelements of the wingcomprising box-spars or spars.

The method involving two half wings is con-" sequently advantageously applied to backswept wing forming the subject matter of thepresent invention. i l

'In such conditions, the wing forming the sub ject matter of the present invention is comprised of a pair of half wings each of which essentially includes a main spar obliquely directed with respect to the axis of the fuselage and secured to the fuselage through a deformable connection, said half wings being furthermore deformably connected with a strong transverse beam rigidly secured to the fuselage and attached at itsends to the main spar of each of said half wings at a point intermediate of its length.

Figuref2b is an elevational view, to a larger scale, of the fittings for assembling the transverse beam with the main wing spar.

Figure 3a shows, partly in section, in a plane perpendicular to the longitudinal axis, of;;the

I 8 Claims. (01. z44.-.-1'17) 2 o. fuselage, the various parts of the attachment-tot the main spar with the fuselage which are" see cured to said fuselage.

Figure 3b is a cross-section, on line AA oni the right hand side and on line 3-3 onlthe left hand sideof the drawing of Fig. 3a. .7

Figure 3cis a cross-section on line C -C o Fig. 3a. I

Figure 3d is a plan view corresponding-to Fig'u're5a is a view of the fitting for assembling the main wing-spar with the fuselage.

Figure 5b is a side view of said fitting. "L Figure 5c is a plan view of :said fitting.

- for said fitting on line D-D of Fig. 5b;

Figure 5c is a section, on line E'E of- Figjb, of said fitting.

Figurefi shows the pin for assembling'vthe transverse beam with the oblique or mainiwing spar.

Figure 7 shows the assembly of the beamwith the fuselage.

' Figure 8 is'half an" elevational view' of the transverse beam.

Figure 9 is a plan view corresponding to Fig. 8. Figure10 is a transverse cross-section of" the transverse beam at any intermediate point of its length, except at the points of attachment of 7 said eam with other' elements or the aircraft,

and for exampleat F--Fof Fig. 8.

The sweptback wingfA forming the object-of; this invention comprises two overhanging-elements symmetrically secured on each'side of the fuselage B. Said wing is one of, the so-called I single-spar-typ'e, including a main spar l extending in the area of maximum thickness of the. wing contour. and forming owing to the general sweepback of the wing, a suitable angle with ythe normal to the axis of the aircraft. Shear stresses are transmitted to said spar through the foremost and rearmost parts of the wing which are connected in a known manner with the spar in a well known manner by box elements comprising a skin 5 supported by ribs 4. They form box elements adapted to be stressed torsionally. The rearmost part may comprise rearwardly a false spar 6, and carries ailerons I and hypersus-- tentation devices-1b. The transverse beam. 10 receiving ashearing stress from the main spar at 9 makes itpossible'to attach the latter by a pair of supports only. I a

Figure 5d is a section through the ball-socket transverse (a) It reduces the maximum bending moment consequently reduces the section of the section for which the main spar is to be designedand material forming the booms;

(b) It avoids the necessity of'providing fin tricate connection devices for connecting together the booms of a spar and a beam when said spar must transmit big bending; moments, since ac- 4 The portion of the attachment structure 8 which is rigid'with the-oblique spar is shownin detail in Figs. 5a to 5e. '11; comprises a single fitting 29b terminated by a socket 29 and secured on the otherhand to the ribs 35 and 35 of the 'main'spar' I and the web 3'! thereof (Figs. 1 and 5CL-5CZ).

The sections shown in Figs. 5d and'5e showthe contour of the fitting 29b firstly 5 through the socket 29 and secondly in the portion of said fitting which is secured to the web 31 and 'the ribs 35 and 36, of the oblique main spar I.

cording to the invention the stresses applied' to the connection are shearing stresses only.

(0) It enables the provision of straight spars and beams.

'Ihe torsional stressesi are transmittedtolthe which has up to this point :beendescribed in. a

is now about to be described in general manner its details. r

The fitting 8' serving as .an attachment of the main oblique sparjiof the wing in overhanging condition is securedtoa particularly strong ringframe of the fuselage." Saidring-frame ;(see in Between both those sections, the cross-section of the fitting is varied gradually.

The ball element 29 contains an hemispherical recess designed to receive the half ball element 33,1;ItiS also formed with'a bore '38 through which the pin 3l is adaptedtoextend. Between the bore 38 and the pintkf here; is provided a clearanceto enable the part -29b.to pivot slightly; with respectftothepart 2|.- iFixation of the fitting 29b to the main spar l. issecuredthrough rivets and bolts provided with lock nuts; I

The transverse beam H1 includes a web :39 (see Figs. 7; to 10) and twobooms '40 and "M. The. web is lightened by'circular recesses 4'2. The

Y beam lB-carr-ies-atits ends twoznttings 43 adapted particular Fig. sens formed by two thicksections f I2 and I3 riveted to the skin sheathing;li ljand.

tially an attachment fitting riveted-about the webof' the spacer 23 illustrated incrossesection in Fig. 3b. In Fig. 3a there is shownaat the bottom of said figure a longitudinal cross-section of the fitting 2'2 and its mode of attachment to,

the part 23. The part 23 is reinforced by two plates 24 and 2 5 riveted thereto. It is to (the, assembly. formed by the part 23 and both plates 24;. and .25 that the flanges 2B and 21: of the fitting 22 are secured. The spacers 23 and 230, which,

are U-shaped co-operate with two flat plates 28 and28a to form .a box structure extruding transversely. of the fuselage. providing f-Qr the rigidity of said fuselage in a transverse direction.

The 7 part 2 l' secured by means of four lugs Z'hl 'and Zlb to the pins and ZBa acts to transmit thereto the stresses it receives from the main spar through the ball and socket joint shown in- Figs. 5a to 5d. To that end it comprises a hemispherical socket recess 30 formed in its center. A threaded pin 'BIfis engaged centrally of said hemispherical recess and is locked through a" tapered cotter pin 32. It carries a half ball-- element 33- concentric with the hemispherical socket and adapted-to be looked through alockable nut 34.

to insure its connection 'withithe mainsparwl. At the-points where it; extendsthroughxthe, fuselage, said beam. is connected with the-latter. by an assembly including two connectingfittings 44 and 45. -.Thejunction of the transverse beam M with the fuselage is shown in Fig. '7.- Bothfittings n l-and 45 secured on either side of the-web 39,

are; rigidly connected jthrough expansible' pins 5| with press-formed parts 49 and 50 secured to the fuselage B-J Saidparts are adaptedto bridge two longerons; of the fuselage-andmake itpossible' to restrict to a certain extent they resistance with which it is necessary to provide the ring-frame at that point; They serve as-a reinforcement for saidring-frame between said two longerons and? at the same time as working points for :the

The. two.

stresses transmitted from the wing. expansible pins j5l are each surrounded with a slotted sleeve 56,'the'.inner surface of which is. formedwith a taper complementary-to thatzof the parts 5|. A bolt 46 provides for clamping the assembly through the, medium of edomeshaped washers 52 and 5 3. .;The vdiameter'of: the

I bolt 48 issrnaller than the inner diameter of the pins-5i, so astomaintain a certain amount of clearance. Clamping of thebolt is provided for by the lock, nut 54. The whole assembly is designed to provide for easy mounting or removal of the .pins even if there is misalignment in the axes of the bores. The fitting 43 terminating the ID at each end thereof is made of steel., Itis shown in detail in Figs. 2d and 2b. Said fitting,

which is adapted to concentrate the stresses in;

assembly. It provides for assembly ofthe fitting 43 withboth fittings 5a and 59 carried y the main oblique spar I and secured. on either side of its web to the web and to esteem thereof,' v

as shown more'particularly in Fig. 2a.

i It will be seen in Fig. 2a, at Bl andjfil'a. that lateral clearance is provided between the fitting transverse beam 43. and ;both;fl.ttings 58 and :59. Such clearance makes; it possible; .in:, co-operation with the ball 51.,3to': compensate, onthei-onehand, for any errors-effectediinl positioningzthe" device and, on the otherhand; any; slight errors in. angular'die rectionj which-smay- .re'sult;- during construction, and: thereby toensure that :themembers i-of the aircraft are interchangeable; Another function ofgsaidrclearance ,is;to-:avoid.'the .transverse beamhere or: the connection 8'; the largererrorsuin volve the :position; which, the::parts assume at the point I l. Such an arrangement is desirable because:such,an-assembly. should be provided at a point where there arenotgreat' stresses ,to be transmitted since otherwise the fitting required atqthat point Wouldhave to be unduly heavy.

Suchis precisely; the case of the false sparzwhich transmits at l stresses considerably. lowerthan those-transmitted at 8zbythe-imain span: The fitting-formed at 1 i3; is an adjustable fitting; I It bears-- ontwo pins 62 and. 63 rigid with the fuselage B.;' Twoaco'nnecting. links adjustable-in length-64 and 6 5:a-re pivoted withrespectato each other-yon a: single, pin ,66 and are pivotedby' means f a ball-and-socketjointnot shown, with respect;tortheifittingwfilytcrminatingithe false spar -6; "Adjustment in length of the linksB-i and 65; isprovided f0r by means of a system including 7 oppositely threadedsleeves; Adjustment thereof iszadapted to :modifythe positions of the pin 66;

inqthe planecontaining-said links." To avoid misadjustment of the links in service, means may be, provided for locking said'sleeves. Thealinks 6! and .65aremoreover-articulatedwith the pins- 62 and .63 by means. of .yokes including ball and socket joints'whereby-said links may execute movements outside: of their theoretical. plane of mounting, These; arrangements make it possibleto meet errors. in longitudinal alignment; and correspond with the clearance, 6 I provided in the fitting of the main=,sparwith the transverse beanrto ensure'zin' all cases'that the wingsand fuselagesare interchangeable: a

It will of course be understood that the con struction described above in'detail'may; without exceeding the scope of the present invention,

be {subjected to modifications of detail in accordance with the particular structures to be built. Thus, for supersonic aircraft having a very high angle of sweepback'the transverse beam will be located more rearwardly-than in the embodiment described. above, and saidltransverse beam may be made to bear upon the oblique main'rsp'ar at a point correspondingly morei'emote from itsconnection with'the fuselage.'

:Ihe idescribedconstruction is capable-of perf'ectly generalapplication which inparticular may be-extehdedto all backswept wing structures',ineluding empenna'ges and fins of flying machines of any type, such as aeroplanes, rockets,ggu ide,d projectiles, regardless of the method of propl lsionor launching used. i

What I claim as my invention and desire to secure by Letters Patent is: I

1. In a sweptback wing construction for an pin's 'se'c'ured on" the fuselage, two yokes respe aerodyne; having a ;fuselage;v a.';transverser;beam rigidly secured ,on .the'1 fuselage and-equally pres jecting from-:7: each side: thereof; andztwoyisingle sparf sweptbiacke3wings; ;eacrnof said-*wi-ngsiecom-a' prismg raamainsspanrearwardly"inclineihfromits inboard totits outboard; ends: :with 18513301,

sa-icrgfuselagegsaids main spar. being-1 articulated and a marginal rib flanging I the ends of said *box elements which are adjacent to the fuselage, saitl marginal rib beingsecured on said fuselage-at a plurality of points. g 2. 'A' sweptback wing construction, according to cl'aim '1, further comprising, for'eachwing, a false spar substantially parallel to the main spar,- said false spar being disposed at the rear 'ofthe transvers'ebeam and'articulated onthe fuselage at its inner end, rear box elements cam-1 prising ribs =pivotally mounted at the 'rearbf said false sparand-a skin supported by: said ribs; r "3, 'A sweptback wing constructionfaccording to' claim 1, 'further comprising; for each-wing, a false; spar substantiallyparall'el to the main spar and disposedat thereaior the transverse beam; an adjustable fitting connecting the fuselage at-theirear-of said" transversefbeamand the inner end of said'false span' means-for adjust'f in'g said fitting-for correcting errorsfinalignment of said false spar, an -rear box elernents o'ni-. prisingribs pivotally mountedat the 'rear k said'false spar-and a skin supported by sa ribs, the adjustable*fittings{respectively* Ori-eQ spending to both false spars of the" aerodynebeing symmetrically mounted on the fuselage" withrespectto the longitudinal axis thereof; ,7 '4; A sweptback wing construction, according to claim-'3, whereineach adjustable f ttingiand the corresponding adjusting means comprise a pirr'a ball and' socketjoint articulating s'ailclffpiri at the innereiidof the'corresponding false spar, two links adjustable inlength; one endof each of' s'aid links being 'articulatedfonsaid pin, twp

tively fmounted at the o'the ends" and articulated -respectiyel Q1 sai adiusting' the ball and so'cketffoin s; means j fof lengthsfof said links; and means for; locking said v length adjus'ting"means.

5; In a -sweptback wing constru'ctio aerodyne-havingya fuselageya tr a rigidly secured on the fusela e,arndj'eqllally pmg jectingfrom each side thereoLfandftwo single sparsweptback Wingseach offsaid fwi'ngsi m;

prising amainsparrearwardly inclined frOm its inboard to itsoutboard ends with respect to said fuselage, saidmainsp'ar being 'looatedf in the;

area of maximum' thickness of the wing contour, front and rear box] elements comprising 11' s: se-.'

cured on said main] spar and a skin 'si p p ortecl' by-- said ribs, and-Gaf'm arginal rib flang'i'ng the ends of "said "box "elements which are; a acen -to;

v the fuselageysaid marginal 'ribfbe ing securedj'on;

said fuselage at a plurality of a firstpair', of mountings each of which pomp 'sie's a ball; and socket 3 1m, 1 the-ball l ments-pr "said, we, joints "being respectively'conhected withsaid fuse lage at locations in front of said transverse beam symmetrically with respect to the longitudinal axis of the aerodyne while the socket elements thereof are respectively connected with the inner ends of the main spars, whereby said main spars may pivot respectively around the centers of said ball'elements, and a second pair of mountings each: of which comprises a ball and socket joint,-

thereof are respectively connected with interme-v diarypoints of the main sparsfor allowing small relative'movements of said main spars with respect to said beam,

,1: 6, A sweptback wing construction, according toplaim 5, wherein the supports for the ball elements of the first pair of mountings comprise a common reinforced box spar forming a ringframe for the fuselage and comprising on each side of said fuselage an inner yoke having two flanges which are formed with two pairs of holes longitudinally aligned two by two;a second common reinforced box spar locatedbetween said yokesto stiffen said fuselage in-the transverse direction, said second reinforced boxspar having. on each of its ends facing said yokes two super; posed fittings located betweenthe flanges ofthe corresponding yoke, each of said fittings being formed with a hole registering with a pairof longitudinallyalign d, holes -of said; corresponding'yoke andfor each ofsaid firstpair of mountings, a part formed with a central hemispherical recess and having a tapped bore centrally opening in said recess andfour lugs forming two forks respectively locatedlbetween the'fianges f the corresponding yoke and respectively straddling the two superposed; fittings locatedion the corre spending, end of said second box spar, said lugs, being formed with holes longitudinally aligned twofb'y two. w ith the pairs oflongitudinally aligned vholes of the corresponding yoke, two pivots each extending through the holes-of the corresponding fittings and ,the pairs 'of longitudin'ally aligned holes of said lugs and, of the corresponding yoke for securing together said yoke, fittingsand part on the corresponding side of the fuselage; and wherein each socket element fixed to ,theinner end of the corresponding main spar is formed withv a bore and-a spherical recess, a pin traversing with a small clearance .the bore of said socketelement andjormed with a thread end for engaging in ,thetapped bore ofsaid part,

, alhem'isphe'rical ring mounted on said pininthe spherical recessof "said socket element, and means for securing said hemispherical ring-on said pin;

17. Aisweptback wing construction, according to claim 5, wherein each socket of the second pair of, mountings his longitudinally limited bytwo transverseplane surfaces and is formed witha spherical recess opening atsaid surfaces, two bentfitting's mountedon the corresponding 'main spar in order to present two transverse faces parallel to saiditransverse plane-surfaces, each one of said bent fittings being formed with a hole normal to the related face thereof, a ball element mounted in this spherical recess andformed with a bored the same diameter as. said holes, and an expansible pin passing through said bore -and socket elements of said second pair of mountings being respectively carried by the ends of said transverse beam while the ballelements thereofwhen mounting may be corrected, and wherein the means for securing the transverse beam on formed with aligned holes of the same diameter;

two internally conical slotted sleeves formedwith heads and adapted to berespectively arranged in the aligned holes of the adjacent parts and-:fit-= tings, said heads respectively abutting against: the outer surface of said parts, two hollow expan'-- sible pins respectively arranged in said rings, saidexpansible pins having "outer-surfaces" formed with tapers complementary to those -of said sleeves, a connecting pin the diameter of which is less than those of the bores of said hollow 'ex pansible pins for securing the latter opposite toeach other, and means for securing said pinby pressing on said hollow expansible pins-i I 8.: In a sweptback' wing construction; for 'an aerodyne having a-fuselage,- a transverse beam rigidly secured on said fuselage'andequally projecting from each side thereof, a box element comprising a pair ofpieces laterally secured'on' said fuselage infrontof said transverse beam and a. transverse" spacer connecting said twopieces 'for withstanding the drag strains, two singlespar s'weptback wings, eachofsaid wings comprising a main spar inclined with respect to said'fuselage, saidmain' spar being located in the areaof maximum thickness of'the" wing contour, front and rear box elements comprising 'ribs 's'ecured to said mai'n'spar anda-skin' supported by said ribs, and a marginal *rib'fianging the endsof said box elements which areadjacent to the fuselage, said marginal rib being secured to said" fuselage at a plurality ofpoints, a firstpair of mountings each of which'comprises aball and socket joint-the ballelementsofsaid first pair of mountings being respectively connected'withj said pieceswhile the socket elements thereof are respectively connected. with the inner ends of the main spar, whereby said main spars may respec*- tively pivot around the centers of said ball ale-' ments, and a second-pair of mountings each of which comprises a ball and socket joint, the

- are respectively connected" with intermediary said holes for securingtogether said fittings and said ball element, the longitudinal distances existing between said two transverse; parallel faces being'greater than the longitudinal thickness of said socket, whereby any error resulting from the construction of the main spar or'the transverse beam as well as from their relative positioning points of the main spars for allowing smallrelative movements of said main spars with respect to said beam.

REFERENCES CITED,

The following references are of recordin file of this patent: M a UNITED STATES PATENTS Number 2,425,099 Klose Aug.15;-=1947 PIERRE HENRI SAI'IRE. I

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