US2404895A - Variable wing construction - Google Patents

Description

July 30, 1946. E. F. ZAP 2,404,895

VARIABLE WING CONSTRUCTION Filed Jan. 19, 1942 2 Sheets-Sheet 1 /NVENTO/Q/ EDV/4R0 ZAP omda u.,

Fm? THE F/ 2 Sheets-Sheet 2 /NVENTo/@J Eoin/ARD F ZAP /A faQ/.5, MECH] FOSTER HAR/WJ b k'" TH: HKM

E. F. ZAP

VARIABLE WING'` CONSTRUCTION Flled Jan 19, 19212 July 3o, 1946.

Patented July 30, 1946 .i

UNITED STATES PATENT oElElcEN VARIABLE WING CONSTRUCTION Edward F. Zap, Los Angeles, Calif.

Application January 19, 1942, Serial No. 427,237

8 Claims.

My invention relates to the construction ci airplane wings and more particularly relates to mounting and controlling relatively movable parts of variable wings. By way of example, the present invention will be described as directed specically to improvements on the structure disclosed in my copending application Serial No. 352,516, entitled Airplane wing construction," and the present invention will therefore have the objects set forth in that application. It will be understood,A however, that the principles exemplified herein may-be applied to other types of wings and features of the new construction may be employed apart from the arrangementas a whole.A

` The particular wing construction under consideration here is of the high lift or variable lift type that is changed in conguration in accord with changing operating conditions. Thus, such a wing may be varied temporarily to provide relatively high` lift for take-oit and again may be varied to provide both increased lift and increased drag for landing. Asset forth in said copending application the variable wing of the present type has a hollow portion lying between trailing flap is mounted in this hollow portion for extension and retraction rearwardly and downwardly from the wing. Preferably the ap is of curved conguration and is mounted for the wing and hence will involve no necessity for openings through the rear spar. It is contemplated that the means for actuating and controlling the aileron of the wing as well as the means for actuating andcontrolling the extensible flap of the wing will be restricted to the wing space rearward of the rear spar, neither mechanism interfering with the other.

One ofthe problems in the described wing arrangementis to provide in the confined rearward space a structurally ecient and thoroughly reliable mechanism for actuating and controlling the iiap, such mechanism to bezfully effective at all positions of the flap. It is difficultA to design a mechanism or linkage that does not at some point of operation become unwieldy or develop unfavorable leverage. One of the objects is to provide a mechanism that meets this problem and `the rearward spar and the trailing edge, and a I movement outward alonga curved path from a 7;

retracted position largely, if not entirely, inside the wing, to various positions of extension. To provide for an adequate range of flap movement and yet require relatively little space for mounting means, the ap is movably orretractably y mounted on a support that is itself movably or retractably mounted on the wing. The range of movement oi the flap in such a construction is the range'of relative movement provided between the flap and the support plus' the range of relative movement provided between the support and the wing. The contemplated wing construction as set forth in said copending application also includes a novel aileron that is adapted to extend into or retract from the air stream above the t? wing.

One of th'e objects of the present improvement is to provide compactness or efficient utilization of space in an airplane wing and at the same time to 'achieve eiiiciency and dependability in the mechanism for actuating and controlling the relatively movable parts of the wing. An arrangement is sought that may be conned enyet is adapted to the peculiar space limitations of an airplane wing. In this aspect the invention is characterized by a new combination of pulleys, cables, and'guide means for flap actuation.

A group of objects relating to the means for movably mounting the ap'in the wing includes the following: to reduce` the number of movable flap supports required in my earlier structure; to simplify the construction of such movable supports; to avoid' loading such movable supports in any manner tending to develop undesirable torques in the supports; to provide an arrangement in which the movable supports are efciently related to the rib structure of the wing for transmitting loads thereto; and to provide means for movablymounting the iiap on the movable supports in an efficient manner.

The above and other objects of the invention will be apparent in my following detailed description, taken with the'accompanying drawings.

illustrative only:

Fig. 1 is a diagrammatic view of an airplane in perspective showing the principal elements in the system for actuating and controlling the wing flaps;

Fig. 2 is a fore-and-aft section through a wing of the airplane, both the ap and the aileron being retracted;

Fig. 3 is a similar view with theiiap and aileron extended;

Fig. 4 is an enlarged view partly in section taken as indicated by the line 4-4 of Fig. 2;

- Fig. 5 is a section on an enlarged scale taken as indicated by the irregular line 5- 5 of Fig, 2;

In the drawings, which are to be considered as surface of the panel.

Fig. 6 is a section on an enlarged scale taken as indicated by the line 6 6 of Fig. 2; and

Fig. '1 is a section on an enlarged scale taken as indicated by the line 1-1 of Fig. 3.

The drawings show an airplane having a fuselage I6 and a pair of wings II, the framework of each wing including a rear spar I2 (Fig. 2) and a number of ribs generally designated I3 (Figs. 5 and 6). In each wing the rear spar I2 and the various ribs I3 form what maybe termed hollow portions or wing compartments I5.

An aileron,

generally designated I6 is mounted in each wing Il to move upward through an opening I1' (Fig. 3) in the upper skin I6 of the wing, and a flap -generally designated is mounted in the wing to move rearward through an opening 2I in the trailing edge ofthe wing. A ,y

Each of the ailerons I6 comprises a plurality of aileron panels 22 mounted in successive wing `compartments I5, the panels being connectedin a unitary manner by al common end plate or deecting plate 23. Each aileron panel 22 may be of hollow construction with a l-ower wall 25 and van upper curved wall 26. The upper wall 26 provides what may be termed the curved effective In the present arrangement it is contemplated that normally each of the ailerons I6 will be sbstantially entirely inside the corresponding wing II, with the deecting plate 23 substantially flush with the wing skin I8. For rolling control of the airplane each aileron I6 is movable upward in a curved path having one or more centers or axes of curvature lying above the wing and forward of the aileron. Since the wings I'I shown in Fig. 1 are of tapering planform, the aileron panels 22 may likewise be tapered.

sides of each aileron panel in moving engageri' ment .with four ro-llers 36 mounted on one of the wingiribsl I3. For actuation of the aileron I6 each of the panels 22 may be provided with a small bracket plate 3l to which is p-ivotally connected one end of an adjustable operating rod 62,

the other end of the operating rod being pivotally connected to an arm 33 on an operating shaft 35. .Any suitable mechanism may be employed to control the aileron-operating shafts 35 in the two Wings.

' The flap 26 may comprise a'series of flap panels 36 that are individually mounted in successive wing compartments I5, the various panels being connected in a unitary manner by a common trailing member 31 having an air-deflecting surface 38. The flapv 2l) is curved incross-.sectional configuration and since the wings l l are tapered in plan form the iiap may have the o-verall configuration of a longitudinal section of a truncated cone. The flap 20 may be adapted to move in a curved path concentric to the cross-sectional configuration of the flap, the common axes rof the flap and the flap path being below the wing. Each of the flap panels 36 is movably'm'ounted on two supp-ort members 40 and the support members varein turn movably supported by' ribs I3 in the wing.

As indicated in Fig. 6, each flap'panel 36 has 42, and an vupper wall or skin `43 having a marginal portion 45 overhanging each of the side supports 4i) (Fig. 6). Ytion shown in-the drawings there are three flap 4 walls 4I. Mounted on the face of each side wall 4I is a suitable track or guide 46 of the same curvature as the aileron panel, the track being movably engaged by a forward pair of rollers 41 and 46 (Fig. 2) and a rearward pair of rollers 49 and 56 (Figs. 2 and 6). Each of the lower rollers 48 and 5i) may be plain, while each of the upper rollers 41 and 49 may be flanged for engaging opposite sides of an upper rib 52 formed in the track or guide 46. The four rollers 41 to 50 are carried by the trailing end of one of the movable nap In the particular construcpanels 36 on each side of the fuselage I Il. Two intermediate support members 46 are between Vsuccessive ap panels each having two sets of rollers I1-56 supporting two adjacent ap panels, while two support members 40 are at opposite sides of the flap assembly each carrying a single set of rollers 41-5Il. There is substantially no tendency for the flap load to develop torque in i the intermediate support members 40. Fig. 6 shows one of the intermediate support members 46, and the side support members areof identical construction except in having only a single set of the rollers. It will be noted that each ap panel issupported in a stable manner by two spaced support members 40.

As indicated in Fig. 6 each support member 40 may be of hollow metalconstruction square or rectangular in cross section and eachof the'ribs I3 of the wing structure may be hollow to enclose the corresponding support member. The hollow rib I3 shown in Fig. 6, for example, comprises two spaced plates 53. At the outer trailing end of each support member 40 is a suitable bracket 55 (Fig. 3) having spindles' for the rollers41-50, each of the brackets being formed with a hollow shank 51 that extends into the support member and is secured thereto, for example, by lwelding 58 applied through apertures in the Wall-of the support member. l

Each of the support members 4I)v for the Hap panels 36 may be slidingly mounted in the corresponding hollow rib VI3 in any suitable manner. In the particular construction indicated inFigs. 2 and 6 leach support member 40 is in rolling engagement with a forward pair of rollers 6U and a rearward pair of rollers 6I, eachiroller being flanged to engage opposite sides ofthe support member thereby to confine the support member against lateral movement. Each of the `rollers 66 and 6I may be mounted by aneedle bearing 62 on an eccentric sleeve 63s the eccentric sleeve being mounted in turn on a bolt 65,. A nut 66 on` the bolt 65 may be loosened to permit rotation of the eccentric sleeve 63 so that the various rollers 60 and 6I (Fig. 2) may be readily adjusted for snug fit against the support member 40.

It is apparent that thedescribed arrangement for mounting the flap 2E) willpermit the flap to move from a retractedposition shown in Fig. 2 to an extreme extended position shown in Fig. 3, and it will be noted that the 4relatively extensive range of movement on the part of the flap corresponds to the range of relative movement; provided between the flap and the various support `members 46 plus the range of relative movement provided between the support members: 40 and the airplane wing II. As indicated invFig 3, the inner end of each support member. 49 may be provided with a stop 61 to engage the forward l pairof rollersill'for the purpose of limiting the vutiavard movement of the support member, vand each of the curved tracks or guides 46 may be `formed withlintegral stops 68 and 69 to cooperate with the rollers 41-50 for cooperation with the corresponding set of rollers I1- 50. The pairs of rollers ISU and 6I may be termed primary rolling means andV the sets of rollers lil-50 may be termed secondary rolling means.

The ap 20 may be actuated by any suitable mechanism including the control arrangement set forth in my previously mentioned copending application Serial No. 352,516. The present construction, however, is characterized by the use of pairs of cable spools 1li and 1| for each of the iiap panels 3G, the pairs of spools being so arranged that one spool plays out a flexible means such as a cable 13 while the other spool winds in the cable. The various pairs of cable spools 1|) and 1I in each wing may be mounted on a flap-operating shaft 15 that is divided into sections by universal joints 16. To operate the two shafts 15 in the two wings of the airplane the pilot may turn a crank 11 (Fig. 1) on a stub shaft 18 carrying a sheave 8B. An endless cable 8| engaging the sheave Se passes under various idlers 82 and around a driven sheave 83 on a gear box 85. A suitable worm (not shown) and cooperating worm gear (not shown) in the box 85 drive the two shafts 15.

Fig. 5 shows a section 85 of one of the flapoperating shafts journaled in a bearing 81 inside one of the hollow ribs I3, the section of shaft carrying a pair of cable spools 1E) and 1| on opposite sides of the rib. Each of the cable spools Il and 'II has a screw 88 (Fig. 3) engaged by a loop 90 on the end of the cable 'i3 and the cable p-asses around the hub of the spool and through an aperture to the spool periphery. Inside the rib I3 below the shaft section 86 (Fig. 5) a bracket 92 is mounted on a base 93 by one or more bolts S5. The bracket 92 carries a spindle 55 extending through the rib and two vertical pulleys 91 and S8 are mounted on opposite ends of the spindle. Finally, a substantially horizontal pulley |08 (Figs. 2 and 6) is mounted on a bracket IIiI near the trailing edge of the wing, the bracket being secured by one or more bolts |62 to a base |63 lying inside the rib. The cable 13 from the cable spool 1|) in Fig. 5 passes under the vertical pulley 91, around the horizontal pulley ISI), under the vertical pulley 98, and onto the second cab-le spool 1|, rotation of the shaft causing one spool to play out the cable 13 and the other spool to wind up the cable at a corresponding rate.

For the purpose of operatively connecting a flap panel 36 with a cable 13, the cable may be attached to a pivot member |95 (Figs. 2 and 5) that is movable along a track or guide |95, the track or guide H36 being mounted one one side of the rib I3 to conform with the cable path between the vertical pulley 98 and the horizontal pulley |00. One end of an adjustable link or operating rod Il (Fig. 5) is mounted on the pivot member |55 and the other end of the operating rod is pivotally connected to a stud |08 on a side wall 4I of the nap panel.

It is apparent that rotation of the crank 11 by the pilot will cause the three operating cables 13 in each wing (Fig. 1) to shift the corresponding pivot members |05 forward or rearward to cause corresponding forward or rearward movement of the panels of the flap 2|). Since the wing is of tapered configuration and since I prefer to have the nap 20 always extend the wing configuration at each wing station in proportion to the chord of the wing itself at the station, the three -iiap panelsiwill range over'operating paths of Adifferent lengths and the three pairs of cable spools 10 and 1I for operating the three flap panels will be correspondingly of `different diameters.

A feature of the present invention readily apparent in Figs. 2 and 3 is that both the means for mounting and controlling the aileron` I6 and the means for mounting and controlling the flap 20 are contained in the portion of each wing between the rear spar I2 and the trailing edge of the wing, none of the operating and controlling mechanism extending through the spar. It will be noted that the aileron and associated mechanism are complementary to the flap and associated mechanism in the sense that complementary zones of the hollow portion of the Wing are occupied by the two combinations.

Since the specic arrangement describedherein for the purpose of disclosure suggests various changes and substitutions under my basic concepts, I reserve the right to all such departures from my description that properly lie within the scope of the appended claims.

I claim as my invention:

1. In an aircraft, the combination of: a main wing with a rear spar and spaced ribs forming rearward wing compartments; a plurality of flap panels mounted in said compartments, said flap panels being interconnected at their rearward portions to form a unitary flap assembly; support means at an end of said flap assembly; and intermediate support means between successive panels in said ap assembly, each of said support means being mounted on one of said ribs for movement between aretracted position largely inside the wing and an extended position largely outside the Wing, the panels of said flap assembly being mounted on said side and intermediate support means for fore-and-aft movement relative thereto and relative to the wing between positions largely inside the wing with the support means retracted and positions largely outside the wing with the support means extended, each of said intermediate support means movably supporting two successive panels in the ap assembly.

2. In an aircraft, the combination set forth in claim 1 in which the means for mounting each flap panel on a support means includes rolling means carried by the support means and cooperating guide means carried by the panel in engagement with and guided by said rolling means.

3. In an aircraft, the combination of: a main wing with hollow ribs spaced to form rearward wing compartments; a plurality of flap panels mounted in said compartments, said flap panels being interconnected at their rearward portions to form a unitary flap assembly; support means at an end of said flap assembly; intermediate support means between successive panels in said flap assembly, each of said support means being mounted in one of said hollow ribs for movement between a retracted position largely inside the rib and an extended position largely outside the wing; and means mounting said panels on said side support means and said intermediate support means for fore-and-aft movement relative thereto and relative to the wing between positions largely inside the wing with the support means retracted and positions largely sutside the wing with the support means extended, the adjacent sides of two of said panels being supported by one of said intermediate support means.

4. In an aircraft, the combination of: a wing with a spar and spaced ribs, said ribs extending longitudinally of the aircraft toadjacent the trailingedge of'said wing and with; saidA spar formingcompartments closed at the bottom by said wing and open at the trailing edge of vsaid wing; a plurality of ap panels, one of saidpanels being mounted in each of said compartments and said panels being interconnected at their rearward portions to form a unitary ap assembly; end support means at an end ofl said assembly; intermediate support means between adjacent of said panels; ymeans .mounting each of said end and rintermediate' supportmeans on one of said ribs forfore-and-aft movement relative tosaid associated rib; and means mounting said panels on said end and intermediate support means for fore-and-aft movement relative thereto,reach of said intermediatel support means supporting the adjacent ends of adjacent panels.

AV5. In an aircraft, the combination of: a wing with spaced ribs, said ribs extending longitudinally of the aircraft to adjacent the trailing edge of saidwing and forming compartments therein closed at the bottom by said wing and having an opening in the trailing edge of said wing; an aerodynamic member mountedgin leach of said compartments for movement through. saidppening; a exible meansvin veach'of said compartments operatively connected to one of said aerodynamic members for inducing fore-and-aft movement of said member; Va shaft mounted on each of said ribs; a pair of spools mounted on each o f saidshafts, said spoolsof each pair being in adjacent of said compartments and said spools being adapted to wind and unwindsaid iiexible means; means to rotate one of the spools in a direction to wind in the flexible meansand simultion to play outtneexible moans Vand vice versa;

andinearisincluding apulley near said opening to guide said vexible means inanoperating Path.

of said lwing andrforming compartments therein closedat the bottomA by said Wing and having an opening-in the` trailing edge of said wing; an aerodynamicmember mounted in each ofl said compartments for movement through said opening;Y a'exible means in eachof said comparte ments operatively connected to one of said aerodynamic members for inducing fore-and-aft movement of said member; a shaft mounted on each of'said ribs; `a pair of spools mounted on each of said shafts, said spoolsof each pair being in adjacent of said compartments and said spools being adapted to wind andunwind said exible means; means to4 rotate one of the spools vin va direction torwnd in the flexible means and simultaneouslyto rotate the other spool in a directionA to playout the flexible means and vice versa;

`and means including a pulley near said opening to guide said exibie means in an oper-atingpath, said pulley being spaced fromsaid spools a distanceat least equal to the extent of movement of the associated aerodynamic member.

'7. A combination according to claim 1 wherein said spaced ribs lie between said panels when said panels are in retracted position.

8. A combination according to claim 3 wherein said hollow'spaced ribs lie between said panels when said panels are in retracted position.

EDWARD F. ZAR

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