US3704549A

US3704549A - Auxiliary door fuselage closure

Info

Publication number: US3704549A
Application number: US126449A
Authority: US
Inventors: Everette G Mcghee
Original assignee: Individual
Current assignee: Individual
Priority date: 1971-03-22
Filing date: 1971-03-22
Publication date: 1972-12-05
Anticipated expiration: 1989-12-05

Abstract

The present invention contemplates a closure having primary utility for creating a snug fit between a hangar door and the tail section of an aircraft which projects through the door. In one embodiment, the invention includes carrier support means which are fixed to the hangar door on two opposing sections thereof. Secured to the carrier support means on each side of the opening in the hangar door are aperture carriers, each of which is mounted for movement on the support means toward and away from the other aperture carrier. A slot is formed in the abutting edges of each of the carriers so that when the carriers are adjacent each other, a continuous opening of generally circular cross-sectional configuration is created. Sliding vertically along support means mounted on each of the aperture carriers is an aperture frame which has a semicircular cutout formed thereon to register with the slot formed in the aperture carriers. As in the case of the aperture carriers, the semicircular cutouts formed in the aperture frames are so situated in each of the frames that when the frames abut a circular opening through the planes thereof is formed. Motive means are provided for moving the aperture frames vertically upward and downward with respect to the aperture carriers while similar motive means are provided for moving the aperture carriers toward and away from each other.

Description

United States Patent .McGhee [451 Dec. 5, 1972 [54] v AUXILIARY DOOR FUSELAGE CLOSURE [72] Inventor: Everette G. McGhee, 4917 N.W. 34th Street, Oklahoma City, Okla. 73122 [22] Filed: March 22, 1971 [21] Appl. No.: 126,449

[52] US. Cl ..49/370, 49/168 [51] Int. Cl. ..E 06b 3/42 [58] Field of Search ..49/163, 168, 170, 169, 370;

[56] References Cited UNITED STATES PATENTS 2,739,645 3/1956 Urquhart ..49/l63 X 2,666,962 1/1954 Tripp ..49/370 X Primary Examiner-Kenneth Downey Attorney-Dunlap, Laney, Hessin & Dougherty [5 7] ABSTRACT The present invention contemplates a closure having primary utility for creating a snug fit between a hangar door and the tail section of an aircraft which projects through the door. In one embodiment, the invention includes carrier support means which are fixed to the hangar door on two opposing sections thereof. Secured to the carrier support means on each side of the opening in the hangar door are aperture carriers, each of which is mounted for movement on the support means toward and away from the other aperture carrier. A slot is formed in the abutting edges of each of the carriers so that when the carriers are adjacent each other, a continuous opening of generally circular cross-sectional configuration is created. Sliding vertically along support means mounted on each of the aperture carriers is an aperture frame which has a semicircular cutout formed thereon to register with the slot formed in the aperture carriers. As in the case of the aperture carriers, the semicircular cutouts formed in the aperture frames are so situated in each of the frames that when the frames abut a circular opening through the planes thereof is formed. Motive means are provided for moving the aperture frames vertically upward and downward with respect to the aperture carriers while similar motive means are pro vided for moving the aperture carriers toward and away from each other.

I 15 Claims, 7 Drawing Figures PATENTED HEB 5 3, 704 549 sum 2 or 3 PATENTEHnzc 51912 3. 704.549

sum 3 OF 3 AWE/V702 51/5957? 6. MCGHEE- AUXILIARY DOOR FUSELAGE CLOSURE BACKGROUND OF THE INVENTION Since the beginnings of the aircraft industry, it has been traditional practice to maintain and, in some cases, store aircraft in closed structures of various types generally referred to as hangars. In the early days of the industry, hangaring aircraft was not characterized by the complexities of todays practice inasmuch as the aircraft themselves were relatively small when compared to the size of ordinary buildings. With the advent of the larger aircraft, however, it has been found impractical to completely enclose a large aircraft within a hangar, even though the reasons for enclosing the aircraft for service continue to exist. It is therefore now common practice to park the forward portions of the aircraft in a hangar and leave the tail sections projection outwardly from the hangar. This affords the opportunity for mechanics to work on the aircraft engines which are in the forward portion of the craft while leaving exposed those parts of the aircraft which in general require less maintenance than the enclosed portions of the structure.

In many circumstances, however, it is not adequate simply to leave the hangar door open and allow the tail section of the aircraft to project. Under inclement weather conditions, either cold or dusty, it has been found extremely desirable, if not absolutely necessary, to seal the hangar against the encroachment of the elements. This obviously presents the problem of sealing the hangar door against the projecting fuselage, and this problem of sealing is compounded by the fact that aircraft come in different configurations, so that if a hangar door were designed to meet the specifications for a particular aircraft, it would not be readily convertible to service a different type of aircraft having a smaller, larger, higher or lower fuselage without special modifications to the door.

In view of the necessity for an easily adjustable closure, a number of types of structure have been designed and, in some cases, built. However, until the present invention, such a structure which was relatively simple to build and operate, inexpensive to maintain and reliable remained an elusive desideratum.

DESCRIPTION OF THE DRAWINGS Apparatus embodying one form of the present invention is disclosed in the following written description which is to be read in conjunction with the accompanying drawings wherein like reference characters designate like parts in the individual figures and wherein:

FIG. 1 is an elevational view of a portion of an aircraft hangar showing an auxiliary fuselage closure embodying the present invention in place thereon;

FIG. 2 is an enlarged top view taken along line 22 of FIG. 1 showing the elements of the closure door in the extended position;

FIG. 3 is an enlarged fragmentary view of the aperture carrier of FIGS. 1 and 2, with portions thereof cut away to reveal the relationship of the carrier to associated door mechanism and support means;

FIG. 4 is an enlarged view of the aperture frame indicated in FIGS. 1 and 2 mounted upon an aperture carrier, showing the structural relationship between these two elements;

GENERAL DESCRIPTION OF THE APPARATUS Turning now to the drawings and, in particular, to FIG. 1, there is shown one form of aircraft hangar 10 having opposed movable doors 12 which are formed from a plurality of horizontally movable, interleaving sections. Doors 12 are mounted so as to move toward and away from each other and to meet at approximately the center line of hangar 10.

Closure apparatus comprising one embodiment of the present invention is mounted on the outer, adjacent sections of each of the doors 12. Support means for the closure apparatus are indicated generally by the number 14 and are mounted on adjacent sections of each of the doors 12. A separate aperture carrier 16 which forms a portion of the present invention is mounted on each of the support means 14 and engages the support means in such a way as to allow relative motion of aperture carriers 16 toward and away from each other. To illustrate such motion, in FIG. 1 the right-hand aperture carrier 16 is shown in its extended position with relationship to the right-hand door 12, while the aperture carrier on the left is shown in its retracted position in relationship to the left door 12.

On the outer surface of each of the aperture carriers 16 is secured support means 18 on which an aperture frame 20 is mounted for vertical motion relative to its associated aperture carrier.

The aperture carriers 16 are moved toward and away from each other by motive means indicated generally by the number 22, while aperture frames 20 are similarly moved up and down by motive means indicated generally by the number 24. It may be seen that with this configuration the opposing doors 12 can be moved relatively together and thereafter the aperture frames 20 may be adjusted in both the horizontal and vertical direction to engage a portion of the tail section of an aircraft which projects outwardly from hangar 10. Such engagement may be maintained without regard to the vertical height of the aircraft fuselage.

SPECIFIC DESCRIPTION OF THE APPARATUS In the foregoing discussion of the elements of the present invention, attention was given to the method of cooperation of two substantially identical portions into which the structure is divided. Since these portions are, as stated, substantially identical, the following discussion will be directed to but a single one of these elements. It is to be understood, however, that the description thus given is applicable to either the right or the left-hand portion of the special closure structure.

From FIG. 2 the general relationship between aperture carrier 16 and aperture frame 20 may be better understood. It may be seen, for instance, that frame 20 is mounted on the outside surface of aperture carrier 16 by means of parallel, vertical H-beams which form a portion of aperture frame support means 18. Similarly carrier support means 14 comprises a plurality of relatively movable H-beams, half of which are secured to aperture carrier 16 and the other half of which are solidly fixed to the outer section of door 12.

Further details of support means 14 may be obtained from an examination of FIG. 3 which reveals that means 14 includes a pair of H-beams 26 which are spaced on and carried by the outer section of door 12 at a position at the top and bottom of aperture carrier 16. Slidingly cooperating with each of the H-beams is a second H-beam 28 secured to the interior surface of aperture carrier 16. A plurality of force transmitting rollers 29 of standard design serve to connect pairs of

beams

26 and 28 so that the aperture carrier 16 can easily move in a horizontal direction along H-beams 26.

Aperture carrier 16 has formed therein an enlarged slot 30 which is substantially larger than the cross-sectional area of the fuselage of any aircraft with which the present invention is intended for use. Slot 30 is shown as being shaped generally as one-half of an octagon, although other geometric forms can be used if deemed desirable. Along the lower edge of carrier 16 is provided a pair of horizontally spaced roller assemblies 32 which may be formed from hard rubber, steel, or any other suitable material, and which function to bear the weight of the combined apparatus.

The action of roller assemblies 32 is not entirely passive. Rather, it is through these roller assemblies that I the motive force for movement of aperture carrier 16 is provided. More particularly, roller assemblies 32 are included within carrier motive means 22 which also includes a crank operated spur gear 34 and a pair of horizontally spaced idler rollers 36 (FIG. 3). A looped drive chain 38 passes over spur gear 34, around the idler rollers 36 and into driving engagement witha portion of each of the roller assemblies 32 to provide rotation thereto. Thus, by moving the crank operated spur gear in one direction or the other, aperture carrier 16 may be moved toward and away from its counterpart aperture carrier due to the reaction of roller assemblies 32 with the ground.

The structural details of aperture frame 20 can best be understood by reference to FIG. 4. In FIG. 4 it may be seen that the frame itself, in the embodiment shown, is shaped as half of an octagon along its periphery, while a semi-circular cutout 40 is formed along the edge of the frame adjacent to its counterpart frame on the other door. Around the periphery of cutout 40 a resilient strip 42 is provided to give a positive sealing surface between cutout 40 and the tail of an aircraft while at the same time preventing damage to the aircraft due to its engagement with the closure.

As stated above, frame 20 is mounted on aperture carrier 16 by means of aperture frame support means 18. These support means comprise a plurality of parallel, vertically oriented H-beams 44 secured to the outer surface of aperture carrier 16. As best shown in FIGS. 4 and 5, a plurality of load bearing roller assemblies 46 are mounted on frame 20 and engage the interior portions of the legs of H-beams 44 whereby wind loads are transmitted from frame 20 to aperture carrier 16 and thence to door 12. One form of load bearing roller assembly 46 is shown in detail in FIG. wherein it may be seen to include a pair of brackets 48 held on the upper surface of frame by securing means such as bolts or the like. Each of the brackets 48 carries on its outer end a stub shaft 50 which projects toward a corresponding stub shaft on the opposed bracket. A load bearing roller 52 is rotatably secured at the outer end of each of the stub shafts 50 and engages the interior surfaces of the legs of H-beam 44 to reduce relative motion between frame 20 and carrier 16 and transmit loads from he frame 20 to the carrier 16.

In FIG. 6 of the drawings, guide roller assemblies 54 mounted on the inside surface of each of the aperture frames 20 are illustrated as they appear when viewed from above. The guide roller assemblies 54 function to track the aperture frames 20 on the web of the H- beams as the aperture frames move upwardly and downwardly on their respective aperture carriers 16. Each guide roller assembly 54 includes a pair of sup porting brackets 56 secured to the respective aperture frame 20, and each supporting bracket carries a stub shaft 57 upon which is rotatably mounted a guide roller 58 which bears against the'web of the respective l-lbeam 44.

As best shown in the schematic drawing presented in FIG. 7, frame motive means 24 includes a pair of

windup drums

60 and 62 which are mounted on a shaft 64 driven from a bidirectional, locking, gear reducer 68. Gear reducer 68 is provided to increase the mechanical advantage from a hand crank 70 and may be chosen from any of a number of gear reducers of standard design readily available on the market.

A pair of

parallel cables

72 and 74 are secured to the

drums

60 and 62, respectively, and pass upwardly therefrom over a plurality of

identical idler rollers

76 and 78, respectively. From roller 76 cable 72 passes over an additional roller 80 and thence to a point on top of frame 20 near its inner edge. Similarly, cable 74 passes from roller78 to a similar roller 82 and from thence descends downwardly to a point near the outer edge of frame 20. Since two-way locking means are provided within gear reducer 68, it is possible to move frame 20 either up or down depending upon the direction of rotation of crank 70 thereby making possible the positional adjustment of frame 20 to accommodate aircraft tail sections of various heights.

OPERATION In considering the operation of the apparatus described above, let it be assumed that hangar doors 12 are open with an aircraft partially inside hangar 10. Under these circumstances, aperture carriers 16 will be in their retracted position with relationship to the outer edges of doors l2 and the doors may then be moved into position adjacent the tail of the aircraft. When the closure is thus positioned, the cranks 70 are rotated to move frames 20 either up or down to align the frames with the projecting portion of the aircraft. With frames 20 thus properly aligned carrier motive means 22 are activated by moving the crank operated spur gears 34 whereby aperture carriers 16 are moved relatively together to engage the aircraft tail within the cutouts 40.

When it is desired to withdraw the aircraft, the above procedure is reversed with the two sections of the closures first being moved away from each other to discontinue engagement with the aircraft. Thereafter, if desired, aperture frames 20 may again be adjusted vertically to accommodate a portion of an aircraft of different height.

It will be obvious that a number of changes and alterations may be made in the structure shown in the drawings and described in the specification without departing from the spirit and scope of the present invention. The embodiment described herein is presented by way of example only and the invention is to be limited only by the appended claims.

What I claim is:

1. ln combination with a cooperating pair of aircraft hangar doors:

a. carrier support means fixedly secured to each of said hangar doors;

b. an aperture carrier slidably secured to said support means for horizontal movement thereon in a direction toward and away from the respective door upon which said carrier support means is secured;

c. carrier motive means operatively connected to said carrier for moving said carrier in a horizontal direction toward and away from the hangar door to which said carrier support means is secured;

d. frame support means fixedly secured to said carrie. an aperture frame slidably secured to said support means for vertical movement thereon in a direction normal to the direction of movement of the aperture carrier; and

f. frame motive means operatively connected to said frame for moving said frame along said frame support means.

2. The apparatus defined in claim 1 wherein said aperture carrier has formed therein, a slot along the edge thereof spaced farthest from the respective door upon which said carrier support means is mounted, whereby said aperture carrier has a generally bifurcated configuration.

3. The apparatus defined in claim 1 wherein said aperture frame has formed therein, a generally semicircular cutout along the edge thereof farthest away from the respective door upon which said carrier support means is fixedly secured.

4. The apparatus defined in claim 3 wherein said aperture carrier has formed therein, a slot along the edge thereof spaced farthest from the respective door upon which said carrier support means is fixedly secured whereby said aperture carrier has a generally bifurcated configuration, said slot being generally aligned with said semi-circular cutout formed on the aperture frame and being substantially larger than said semi-circular cutout.

5. The apparatus defined in claim 4 wherein said carrier support means comprises a plurality of pairs of horizontal H-beams in sliding engagement with each other.

6. The apparatus defined in claim 4 wherein said frame support means comprises:

1. a plurality of parallel, horizontally spaced, vertically aligned H-beams carried by said aperture carrier; and

2. a plurality of rollers in operative engagement with said H-beams and with said aperture frame.

7. The apparatus defined in claim 4 wherein said semicircular cutout formed on the aperture frame is lined with a quantity of resilient material.

8. The apparatus defined in claim 4 wherein said carrier motive means comprises:

l. a plurality of roller assemblies mounted at the bottom of said aperture carrier and projecting from the bottom thereof;

2. a continuous looped drive chain in operative engagement with said roller assemblies; and

3. a driven gear also in operative engagement with said drive chain for providing motive power thereto.

9. The apparatus defined in claim 4 wherein said frame motive means comprises:

1. a pair of cables, one end of each of which is" secured at spaced positions along the upper portion of the aperture frame;

2. a wind-up drum secured to the other end of each of said cables; and

3. two-way power input means drivingly connected to said wind-up drums.

10. The apparatus defined in claim 9 wherein said carrier motive means comprises:

1. a plurality of roller assemblies mounted at the bottom of said aperture carrier and projecting from the bottom thereof;

11. The apparatus defined in claim 10 wherein said semicircular cutout formed on the aperture frame is lined with a quantity of resilient material.

12. A closure for a two-part aircraft hangar door which comprises:

a. a first closure element which includes:

l. first carrier support means fixedly secured to one part of said door;

2. a first aperture carrier slidably secured to said first support means for horizontal movement thereon in a direction toward and away from a second closure element hereinafter defined;

3. first carrier motive means operatively connected to said first carrier for moving said carrier in a horizontal direction toward and away from the second closure element hereinafter defined;

4. first frame support means fixedly secured to said first carrier;

5. a first aperture frame slidably secured to said first support means for vertical movement thereon in a direction normal to the direction of movement of the first aperture carrier; and

6. first frame motive means operatively connected to said first frame for moving said frame vertically along said frame support means; and

b. a second closure element which includes:

1. second carrier support means fixedly secured to the second part of said door;

2. a second aperture carrier slidably secured to said second support means for horizontal movement thereon toward and away from said first closure element; v

3. second carrier motive means operatively connected to said second carrier for moving said carrier in a horizontal direction toward and away from said first closure element;

4. second frame support means fixedly secured to said second carrier;

relationship along said edges.

14. The apparatus defined in claim 12 wherein each of said aperture frames has formed therein a generally semi-circular cutout, said semicircular cutouts being formed in adjacent edges of said aperture frames to form an opening in the resulting structure when said aperture frames are in abutting relationship along said edges.

15. The apparatus defined in claim 12 wherein each of said semicircular cutouts formed on the aperture frames is lined with a quantity of resilient material.

Claims

1. In combination with a cooperating pair of aircraft hangar doors: a. carrier support means fixedly secured to each of said hangar doors; b. an aperture carrier slidably secured to said support means for horizontal movement thereon in a direction toward and away from the respective door upon which said carrier support means is secured; c. carrier motive means operatively connected to said carrier for moving said carrier in a horizontal direction toward and away from the hangar door to which said carrier support means is secured; d. frame support means fixedly secured to said cArrier; e. an aperture frame slidably secured to said support means for vertical movement thereon in a direction normal to the direction of movement of the aperture carrier; and f. frame motive means operatively connected to said frame for moving said frame along said frame support means.

2. a second aperture carrier slidably secured to said second support means for horizontal movement thereon toward and away from said first closure element;

2. a wind-up drum secured to the other end of each of said cables; and

3. two-way power input means drivingly connected to said wind-up drums.

4. second frame support means fixedly secured to said second carrier;

4. first frame support means fixedly secured to said first carrier;

5. a second aperture frame slidably secured to said support means for vertical movement thereon in a direction normal to the direction of movement of the second aperture carrier; and

6. second frame motive means operatively connected to said second frame for vertically moving said frame along said second frame support means.

6. first frame motive means operatively connected to said first frame for moving said frame vertically along said frame support means; and b. a second closure element which includes:

6. The apparatus defined in claim 4 wherein said frame support means comprises:

9. The apparatus defined in claim 4 wherein said frame motive means comprises:

12. A closure for a two-part aircraft hangar door which comprises: a. a first closure element which includes:

13. The apparatus defined in claim 12 wherein each of said aperture carriers has formed therein a slot, the slots being formed at adjacent edges of their associated aperture carriers to form an opening in the resulting structure when said aperture carriers are in abutting relationship along said edges.