US2925966A - Folding fin or wing for missiles - Google Patents

Description

INVENTOR SVERRE KONGELBEGK ATTORNEYS 5 Sheets-Sheet 1 %m0'&-

5 KONGELBECK FOLDING FIN 0R WING FOR MISSILES Feb. 23, 1960 Flled Oct 8, 1957 Feb. 23, 1960 s. KONGELBECK FOLDING FIN OR WING FOR MISSILES 5 Sheets-Sheet 2 Filed Oct. 8. 1957 INVENTOR- SVERRE KONGELBEGK Feb. 23, 1960 s. KONGELBECK FOLDING FIN OR WING FOR MISSILES 5 Sheets-Sheet 3 Filed Oct. 8. 1957 FIG. 5.

INVENTOR 5 Sheets-Sheet 4 S. KONGELBECK FOLDING FIN OR WING FOR MISSILES Feb. 23, 1960 Filed Oct. 8. 1957 INVENTOR SVERRE KOIVGELBEOK Feb. 23, 1960 s. KONGELBECK 7 2,925,966

FOLDING FIN OR WING FOR MISSILES Filed Oct. 8, 1957 5 Sheets-Sheet 5 INVENTOR Sl/ERRE KONGELBECK ATTORNEYS United States Patent V FOLDING FIN OR WING FORMISSILES Sverre Kongelbeck, Silver Spring, Md., assignor to the United States of America as represented by the Secretary of the Navy Application October 8, 1957, Serial No. 689,020 6 Claims. (Cl. 244-14) The present invention relates to a latching mechanism. More particularly it relates to a latching mechanism especlally suited to locking in a rigid operative position hinged rocket fins or guided missile wings.

Rockets, guided missiles and the like are customarily fitted with fins or wings for stabilizing and controlling their flight through the atmosphere. vehicles it may very well be found that vehicles assembled with fins or wings require double or triple the amount of space necessary to house the vehicle bodiesalone. In applications of limited space, for example, on shipboard, the past practice has been to stow vehicle bodies and fins separately and to provide an assembly area Where'the fins and bodies are assembled prior to launching. This practlce, however, limits the number of vehicles in the ready-to-launch status, and thus seriously lengthens the firing cycle. It is further disadvantageous in that space 1s wasted and time and manpower are consumed in the assembly area. l

The present invention contemplates the provision of a vehicle having its wings arranged to fold against its body and thus consume only slightly more stowage space than the body alone. It further contemplates a vehicle having folded wings which can be erected rapidly by hand or a mechanical device after the vehicle is in position upon a launcher, or mechanically, after the vehicle is in flight.

In stowing such' The provision of a locking mechanism for folding wings attached to a supersonic vehicle is complicated by the fact that supersonic airfoils are necessarily thin structures which are subjected to unusually high panel loads. .A satisfactory locking mechanism must fulfill the requirements of strength, rigidity and reliability. At the same time, the locking mechanism must be so devised as to-be capable of being completely contained within the airfoil since projecting hinges, latches, etc. spoil the How over the airfoil surface and induce excessive amounts of drag.

Accordingly, it is the principalobject of the present invention to provide a means "for collapsing or folding aerodynamic surfaces. v T

Another object of the presentfinvention is to provide a folded fin or wing having means for insuring rigid and accurately aligned surfaces upon erection thereof.

An additional object of the present invention is to provide a folding mechanism contained internally of a thin wing or similar aerodynamic surface so as to present no interfering structures to the airstream.

A further object of the presentinvention is to provide a mechanism for use with pivotally movable wings to prevent pivotal movement of the wings while in a folded condition. y H

Still another object of the presentlinvention is to provide a wing or fin folding mechanism which permits easy and rapid erection of the folded structure and, which is releasable from a locked erected condition by means of a special tool.

Other objects and many of the attendant advantages of this invention will be readily appreciated as the same becomes better understood by reference to the following 2,925,966 Patented Feb. 23, 1960 'ice .detailed description when considered in connection with the accompanying drawings, wherein:

Fig. 1 is a perspective of the rear portion of an aeria vehicle provided with pivotally moveable steering wings and illustrating the wings in an erected condition;

Fig. 2 is a perspective view of the vehicle illustrated in .;Fig. 1,;illustrating the wings thereof folded transversely by means of the present invention;

Figs. 3 and 4 are perspectives, respectively, illustrating (the locking mechanism of the present invention in a locked or erect condition and in an unlocked or folded condition, the wing surface containing the mechanism being shown in outline form; I Fig. 5 is an exploded perspective illustrating the assembly of the wing and the locking mechanism of the present invention;

' Fig; llis a section taken along the line 11-11 of Fig. 10.

In Figs. 1 and 2, a guided missile or similar aerial vehicle is illustrated as being provided withfour pivotallymoveable steering wings 20. For the purpose of conserving stowage space, thewings 20 are arranged to be folded in opposite directions so as to .provide the overlapped pattern shown :in Fig. 2, or if desired, the folding direction maybe the same for all wings Without departing from the scope of the invention.

As seen in Figs. 3 and 4, the basic elements of the present invention include abolt 22 loaded by acompression spring 23 so as to be forced outward along the wing axis. Thewing 20 folds oncylindrical hinge pins 24 and 25 each of which are rabbeted at their inner ends to 'prov'ideaxially extending flat'surfaces 26. The upper center portion 27 ofbolt 22 is milled flat across its entire width. Thelower center portion 28 is milled flat only across half the diameter ofbolt 22, thereby providing detent shoulders 29 and flatvertical clearance surfaces 32. As will be readily understood, in the folded condition (Fig. 4), the detent shoulders 29 bear on the outer surfaces ofpins 24 and 25 and hold thebolt 22 securely against the expansive force ofspring 23. Upon rotation of thewing 20 to an upright or erected condition (Fig. 3), the rounded surfaces ofpins 24 and 25 run off the detent shoulders 29 permitting theclearance surfaces 32 to pass thesurfaces 26 of said pins. 'Thebolt 22 is then free to be driven upward byspring 23.

In Fig. 5 the details of construction of the presentinvention are illustrated. Thewing 20 includes ahub 35 having transversely extendingtongues 36 to which are securedroot sections 37 and 37, Hub 35is provided withaxial bore 38 receivingbolt 22 and spring '23 and atransverse bore 39 for receivinghinge pins 24 and'25. The fin-portion 40 of wing20 is suitably re cessed to'receive'a channeledinsert member 41 which may be secured thereto by rivets. Hingepins 24 and 25 are secured inapertures 42 and 43 .providedin insert 41 bytaper pins 44 and 45. Avertical bore 46 extends axially throughinsert 41 to receive the upper portion ofbolt 22 whichstrikes'thereinto upon releaseof said bolt by rotation ofhinge pins 24 and 25.Bolt 22 fits intobore 46 with a close sliding fit thereby insuring alignment of the erectedfin surface 39 withroot sections 37 and 37'.

3 As best seen in Fig. 9, the upper end of bolt "22 is domed and protrudes slightly above the surface ofhub 35 when said bolt is held in a retracted position byhinge pins 24 and 25. The domed surface ofbolt 22 prevents binding athinge pins 24 and 25 during wing emotion,

as will shortly be described.

Again referring to Fig. 5, abolt depressor 47 and abuffer 48 are carried in the upper portion ofbore 46 and function, as hereinafter described, to releasebolt 22 to allow the folding of an erected wing. To prevent over-travel offin 40 in moving from a folded to an erected condition, the upper face ofhub 35 is bevelled and provided with a pair ofstop lugs 50. The surface ofinsert 41 engaging the bevelled surface ofhub 35 is likewise bevelled and is provided with recesses for receivinglugs 50. The bevelled surface ofinsert 41 performs an important supplementary function in that as the'fin40 is moved from a folded to an erected position, the leading edge of said surface engages the domed upper end ofbolt 22.Bolt 22 is thus slightly depressed relievinghinge pins 24 and 25 against binding at the bolt detent shoulders 29.

As best seen in Fig. 3, a slot 49 is cut in the upper end ofbolt depressor 47. Agroove 51, extending vertically along the outer surface ofdepressor 47, receives aguide pin 52 which serves to maintain slot 49 aligned with a slot 53 (Fig. extending transversely throughinsert 41.

Figs. 7 and 8 illustrate the operation of thebolt depressor 47 in releasing thebolt 22 from a locked position. A tapered drift pin 54, shown in outline form, is inserted inslot 53 to forcedepressor 47 downward. Thebolt 22 is thereby released from locking engagement withbore 46 andsurfaces 26 and 32 are disengaged. Thefin 40 is then freed to swing to the folded position illustrated in Figs. 2 and 9.

Referring to Fig. 6, astub shaft 55, having a keyway therein, extends fromhub 35 and is secured to a suitable servo-actuator (not shown) carried within the vehicle. Rotation ofshaft 55 moves thewing 20 pivotally and thereby supplies control movements to the vehicle mounting the wing. To prevent pivotal movement of the wings in their folded condition a pivotally mountedlatch bar 56 is mortised into the root section 37' ofwing 20. A compression spring 57 biases latchbar 56 into akeyway 58 formed in the vehicle surfaceadjacent root section 37. Upon erection of thefin 40, apush rod 59, mounted to bear on the end oflatch bar 56 opposite spring 57, is depressed to move the latch bar out of engagement withkeyway 58. The erectedwing 20 may then be freely pivoted uponshaft 55.

Referring to Figs. 5, and 11, and particularly to Figs. 10 and 11, thefin 40 is maintained folded by a. generally U-shaped spring detent 61. Detent 61 is recessed into the sidewall ofhub 35 and carries anelevated portion 62 at its outer end. Upon folding the fin 4'3, theelevation 62 snaps into a socket-like depression 63 (Fig. 5) formed ininsert 41. Thewing 20 is thus maintained folded until sufiicient erecting force is applied tofin 40 to cause theelevation 62 to recede from the socket 63.

While the invention has been illustrated and described with reference to a wing embodying but a single locking mechanism, wings having exceptionally long chord lengths can be provided with a plurality of locking mechanisms extending in serial fashion along the chord. The problem of properly aligning the bolts could be readily solved by the provision of floating center bolt receivers, as is well understood in the art.

Obviously many modifications and variations of the present invention are possible in the light of the above teachings. It is therefore to "be understood that within the scope of the appended claims the invention may be practiced otherwise than as specifically described.

What is claimed is:

l. A wing for an aerial vehicle, comprising a rotatable hub, a bolt slidably mounted in said hub so as to act along the axis of saidhub, an aerodynamic surface, hinge means on said hub for mounting said surface to swing about an axis transverse to theaxis ofrotation of said hub, and means controllable by said hinge means for driving said bolt into engagement with said-surface to lock said surface in a fixed position relative .to said hub.

2. A wing as claimed in claim 1, with-additionally means for latching said hub against rotation, and means for releasing said latch means upon engagement of said bolt.

3. A pivotally moveable control wing for an aerial vvehicle, comprising anaerodynamic surface, said surface being divided into .a root portion 'and a fin portion, said root portionincluding. a shaft for :pivotally mounting the wing on the vehicle, means including a hinge pin for joining said fin portion to said root portion, means in said root portion for locking said fin and root portions into an aligned wing-structure, means in said root portion for latching .said root portion against pivotal movement,

.and means for releasing saidrlatching means upon the locking of said fin-and root portions into analignedwing structure.

4. A wing as-claimed in claim 3, wherein saidmeans for locking said fin and root portions into an aligned wing structure comprises the eombination'of a bolt having a detent surface engageable by said hinge pin'and a tions are moved into alignment.

5. A pivotally moveable-control wing for an aerial vehicle, comprising, an aerodynamic surface,said surface being divided into'a root'portion and a fin portion, said root portion including a shaft for pivotally mounting the Wing on the vehicle, a hinge "pin'hfor, hinging said fin portion to said root portion, said hinge pin being rotatable with said fin portion and "having a rabbeted end portion, a bolt slidably mounted'in said root sectionfor locking said fin section into "alignment with said root section, said bolt being provided with'a .first flat surface running axially of said bolt and a 'second flat surface running transversely so as to intersect said first surface, said hinge pin and said bolt being arranged so'that the end portion of .said hingepin rests upon said second'flat surface of said bolt and restrains said'boltuntil said.hinge pin is rotated to allow said 'rabbet to clear said'first surface of saidbolt, :and a. spring for urging said "bolt into locking position. p

6. A wing as claimed in claim '5, with additionally a pivotally mounted latch bar in said root portion and arranged to project from said root portion for preventing pivotal movement of 'said wing, anda push rodin said root portion and arranged to retract -said latch 'barupon rotation of said fin portion into alignment with said root portion.

References Cited in the file of this patent UNITED STATES PATENTS 17,407 Sibley May'26, 1857 772,293 Reese 'Oct. 11, 1904 1,879,840 Brandt Sept. 27, 1932 2,594,533 Baker Apr. 29, 1952

Images