US3160060A - Missile transporting and launching system - Google Patents

Description

Dec. 8, 1964 L. ZSOKA ETAL 3,160,060

MISSILE TRANSPORTING AND LAUNCHING SYSTEM Filed Dec. 21, 1961 s Sheets-Sheet i INVENTORS LORANT ZSOKA WALTON E. CLAUSON Dec. 8, 1964 L. ZSOKA ETAL 3,160,060

MISSILE TRANSPORTING AND LAUNCHING SYSTEM Filed Dec. 21, 1961 3 Sheets-Sheet 3 INVENTORS LORANT ZSOKA WALTON E. CLAUSON FIG- 70 United States Patent i 3,160,060 MISSEE TRANSPORTING AND LAUNCG SYSTEM Lorant Zsolra, Los Altos, and Walton E. illauson, Sunnyvale, Qalifl, assignors to Lockheed Aircraft (lorporation, Burbank, Calif.

Filed Dec. 21, 1961, Ser. No. 161,056 7 Claims. (Cl. 89-15) This invention relates generally tothe field of containers and is more specifically directed to a sleeve-like device capable of exerting inwardly directed pressure against an object placed therein which has considerable potential for use in connection with projectile launching systems.

As the development of ballistic and guided missiles, rockets, and the like has become increasingly significant, the importance of the ground support equipment utilized to transport and to launch these projectiles has increased. Heretofore, solid cylindrical tubes have generally been used to contain projectiles prior to launch, and it has even been suggested to utilize such a tubular container both as a launching device and as a conveyor for transporting the article from one place to another. These previously developed systems have suflered from a number of disadvantages, namely, the relatively high cost per unit, the great weight associated with mechanical structures of a sufficiency to support an object such as a missile, and the accompanying size of the structure.

As many contemporary long-range projectiles are relatively weak from the standpoint of internal structural support, it has been necessary to provide tubular containers of suflicient thickness to support their weight and maintain them in correct longitudinal alignment. These costly tubes have made access for purposes of main tenance and checkout to the missile contained therein a distinct problem.

Such systems have usually required special guidance and support apparatus between the projectile and the containing tube, which apparatus often causes complications and malfunctions as it falls back upon the launch pad just after blastotr.

With these problems in mind, it is a primary object of our invention to provide a container system which can be used to logistically transport and strategically launch rocket-powered projectiles and the like.

An additional object of our invention is to provide such a system which incorporates a significant saving in space together with a material reduction in weight and cost.

A further object of our invention is to provide a missile launching/transport system which is extremely practical and which has the advantage of providing accessibility to its interior at any desired point.

An additional object of the invention is to provide a transport/launch system which is compatible with a majority of ground handling facilities.

Yet another object of our invention is to provide a rocket launching system which is self-sealing in operation, provides full-length support for delicate missiles and the like, and which is vibration and shock resistant over a wide range of frequencies and amplitudes.

Other objects, features, and advantages of the invention will become apparent to those familiar with the art as the invention is more fully described hereinbelow in connection with the illustrative drawings in which:

FIG. 1 is an isometric representation of a projectile container/launcher constructed according to the teachings of our invention,

FIG. 2 is an isometric representation, shown partly in section, of a modification of the invention,

FIG. 3 is an isometric representation schematically showing the modification of FIG. 2 in an operational environment,

FIG. 4 is a diagram illustrating the structure and forces inherent in the operation of the invention,

FIG. 5 is a schematic elevational view of the operational characteristics of the invention,

FIG. 6 is a side elevational view of one modification of an access port forming a part of the invention,

FIG. 7a is a front elevational view of a second modification of such an access port, and

FIG. 7b is a view taken along line bb of FIG. 7a.

Referring first for purposes of general illustration to FIG. 1, it will be seen that a projectile 1 has been positioned in a launcher/supported assembly generally indicated at 2 which is adapted to provide support for missile 1 while it is being transported or prepared for launch and also during the actual launching thereof.

A feature of the invention resides in the use of a flexible sleeve 3 which forms the actual container for the projectile 1. It is important to note that this sleeve 3 is specifically prepared with the warp and woof fibers at an angle of approximately ninety degrees to each other, and the sleeve is arranged with its longitudinal axis at approximately forty-five degrees to these warp and woof fibers. Referring to FIG. 2 to illustrate this relationship, it is seen that warp fibers 4 are at generally right angles to woof fibers 5, each of which are in turn arranged at approximately forty-five degree angles to the longitudinal axis L of the assembly 2.

Referring again to FIG. 1, it will be seen that the ends of sleeve 3 are secured to an anchor base assembly 6 at the lower end thereof and to an anchor top assembly 7 at the upper end thereof.

Anchor base assembly 6 is comprised of a hollow cylindrical member 19 having a flange 11 at the base thereof which may be secured to a deck or the like by means of bolts as shown at 12. The upper end of hol low cylindrical member 10 terminates in an inwardly directed flange 14 to which is secured a retaining ring 13. Retaining ring 13 is desirably secured to the flange portion 14 by means of bolts 15 or the like.

Sleeve 3 is provided with an outwardly directed flare or flange 8 at either end thereof, the lower one of which is adapted to be positioned between retaining ring 13 and hollow cylindrical member 10 of the anchor base assembly 6.

In a similar manner the upper end of sleeve 3 is provided with an outwardly flared portion which is adapted to be secured to anchor top assembly 7, this flare being confined between a pair of clamping rings 20 secured one to the other by bolts 21 as shown.

Mounted about the periphery of anchor base assembly 6 and anchor top assembly 7 are a plurality of sleeves 30 threaded both internally and externally. These sleeves 3t fit, in the case of anchor top assembly 7, loosely through both clamping rings 20 and are adapted to receive nuts 31 to aid in tightly positioning the clamping rings together. Externally threaded sleeves 3% are freely inserted through over-sized apertures in retaining ring 13 and are threadedly received in or through the flange 14 in hollow cylindrical member 10, the retaining ring 13 then being tightened against hollow cylindrical member 10 by means of nuts 31 which are received upon the external threads of the sleeves 30.

In order to maintain anchor top assembly 7 in spaced relation from anchor base assembly 6, and to properly position and align the former with the latter, a plurality of control rods 4% are provided which are oppositely threaded at their respective ends and which are adapted to be received within the correspondingly threaded sleeves 30.

Intermediately situated between the anchor base and anchor top assemblies 6 and 7 and securely mounted on control rods 49 are gears 41 which are adapted to be rotated by means of worm gears 42, rotated by electric motors or the like. As control rods 40 are rotated in a uniform direction, the oppositely threaded sections tend to force anchor top and anchor base assemblies 6 and 7 apart which causes a stretching of the sleeve member 3. In a manner which will be hereinafter explained, this stretching effect causes a necking down or decrease in the diameter of the sleeve 3 which exerts a force radially inwardly upon the contents of the sleeve member. Although it is possible to operate the invention with only two control rods 49, it is desirable to have at least three such rods, it being noted that a larger number can be provided as desired.

In the modification shown, hollow cylindrical member 10 is adapted to include a gas generator G therein which, upon actuation, will generate gases resulting in an expulsion of the projectile ll. It should be noted that the invention may be utilized in connection with the hot firing of missiles, in which case it may be desirable to provide for a gas exit route through the hollow cylindrical member 1t and through the decking or flooring upon which it is mounted. Also the projectile may be launched by means of the application of compressed gas supplied from an outside source.

It is noted that a variety of materials may be used for the sleeve 3, the inventors having successfully reduced the invention to practice using a glass cloth, such as Irv-O- Glas, EFGN-1808 available from Irvington Varnish Company, Monrovia, California, which has been made air tight by impregnating the outside surface with a coating of neoprene or the like. Depending upon design considerations, other material would be equally acceptable, for instance neoprene coated glass cloth or cloth formed of Dacron, nylon, metallic fibers, or the like which may be impregnated or sprayed with polytetrafluoroethylene, graphite, or talcum to control the coefiicient of friction between the projectile skin and the inner surface of the sleeve.

One of the features of the invention resides in the fact that it is not necessary to provide a large, heavy, and expensive steel or other metallic tubular member to support the projectile and to contain high launching gas pressures. This is made possible by the interesting reaction of the various portions of the sleeve member 3. Before discussing the other modifications and figures of the invention, reference will now be taken to FIGS. 4 and 5 for a more detailed explanation of the operating principles.

Specifically, referring to FIG. 4, a schematic diagram is presented wherein the heavy black lines 50 represent the orientation of the warp and woof fibers of the sleeve member 3 in a relaxed position. It is noted these fibers are oriented so that an angle R of about forty-five degrees is formed between the fibers and the longitudinal axis L of the structure of the invention. As tension is applied to the sleeve 3 by operation of the control rods forcing anchor base assembly 6 and anchor top assembly 7 away from each other, the fibers of the sleeve tend to assume the position indicated by the dotted lines 51, depicting the orientation thereof under tension. It is noted that the original angle R of forty-five degrees has decreased to a lesser angle T, which angle will vary according to the tension applied to the structure. As the axis of the sleeve is elongated, the diameter will decrease, and the wall of the sleeve or cylinder will exert a lateral force inwardly against a body contained therein which is proportional to the force of elongation. By selecting a suitable diameter for the sleeve and adjusting the longitudinal tension, a projectile can be securely held into position and protected against both vertical and lateral shock, and as will be hereinafter explained, as the missile is ejected from the launcher, the sleeve also provides an effective sealing and guidance therefor.

Refcrringnow to FIG. 5, a sleeve 3 is schematically depicted in which a projectile 1 is positioned. As the projectile ll, shown in this figure to be partially ejected from sleeve 3, is originally contained completely therewithin, there will be very little noticeable change in the diameter of the sleeve. However, a force will, of course, be exerted upon the projectile 1. As the missile is fired, or as gas generator G is activated, pressure resulting therefrom would normally be expected to balloon or expand the portion of the sleeve 3 bet" ecn the base portion B of the departing projectile and the point A where the flare of the sleeve is secured :to the base. This effect would, of course, be undesirable in that it would tend to adversely alfect the seal which is obtained between the base of the projectile and the portion of the sleeve immediately surrounding the same. In operation, it has been observed that as the projectile travels the length of the sleeve 3, no such balloon effect takes place. This has been explained to be due to the fact that the missile, while ejecting and because of the necking down force exented thereon, develops a force which tends to counteract the drag developed thercagainst and which works against the tension in the sleeve along the whole length of the missile thus tending to relax :the sleeve. In other words, in that portion of the sleeve above the base B of the missile, the fibers in the sleeve tend to return, clue to the friction between the missile skin and the sleeve, to their originally relaxed position 51, thus tending to decrease the radially inwardly directed force against the missile, which aids in materially reducing the friction and in increasing the facility of ejection. That portion of the sleeve between the base B and the anchor point A will tend to elongate, and maintain or increase the tensioned position as indicated by the dotted lines 51 in FIG. 4, thus counteracting the effect of the gas pressure which would otherwise cause a ballooning eifect as noted. This action brings about a very effective seal in the base or skirt area of the missile. To test this balance of the system, actual launch tests were conducted with a carefully applied cross reference mark as shown at X in FIG. 5 on the sleeve 3. During the projectile launch, this reference mark X did not raise, lower, or deviate laterally from the reference lines at R as schematically depicted, thus adding emphasis to the balanced status described. The sleeve 3 of this invention is not a pressure vessel in the usual sense of the word because the projectile it not restrained in the sleeve.

We have conducted a large number of tests on the system of the invention wherein a large number of ejections of a projectile were made. These tests were fully instrumented, for example, by the use of highly sensitive strain gages being placed along the sleeve at strategic locations, the results indicating that there are not high concentrations of stress in the sleeve during ejection. The cloth or fibers of the sleeve remain substantially straight and apparently the internal ejecting pressure is balanced by the necking down force and tension in the sleeve as noted above.

A desirably high muzzle velocity is obtainable using this invention because of the relaxation in the sleeve along the projectile as it is launched. At the same time, static drag is beneficial for locking the missile in the sleeve and protecting it against shocks. We have additionally found that in almost every instance, less than twenty pounds of tension is necessarily injected into the system between the upper and lower anchor base assembles 6 and 7. In fact, we have found that there is very little relation between the efficiency of the launch and the tension exerted by the control rods 40. Also, we have concluded that it is not necessary to exert high tensions to secure the delicate projectiles against lateral loads. We have shown by vibration tests that there is no sign of resonance in the system under compatible circumstances. When the vibration amplitude was raised above normal and various frequencies were applied, it was found that some resonance did occur at thirty-three cycles per second which is substantially outside of the critical or operating range.

Reference Will now be taken to the modification of the invention depicted in FIG. 2. In this modification, a flexible sleeve 103 similar to sleeve 3 described in connection with FIG. 2 is provided between an anchor base assembly 106 and an anchor top assembly 107. Anchor base essembly 106 is comprised of a hollow cylindrical member 110 having a base mounting flange 111 secured thereto for purposes of mounting the assembly to a deck or the like and a. retaining ring 113 which is adapted to be bolted or otherwise secured to the hollow cylindrical member 110. Retaining ring 113 is provided with an inwardly overhanging bead 114 which, in cooperation with an annular depression 115 formed in hollow cylindrical member 110 to provide an annular cavity, opens at one side to receive and secure the end of sleeve 103 therein. In this modification, sleeve 103 is provided with a hoop 116 which may be a stranded cable or a solid wire, as desired, formed into the end of the sleeve 103, the ends of which are overlapped back upon themselves and secured together. This end of sleeve 103 is then inserted with the annular hoop 116 resting in the annular depression 115. The retaining ring 113 is then bolted or otherwise secured in place thus maintaining this end of sleeve 103 in a secured relation to the anchor base assembly 106.

At the other end of sleeve 103 a similar end retaining arrangement is provided consisting of an inner clamping ring 120 and an outer clamping ring 121. Inner clamping ring 120 is formed with an annular depression 122 therein which is adapted to cooperate with a complementary depression formed by an overhanging bead 123 in the lower portion of clamping ring 121. In a similar manner a hoop 124 is provided in the end of sleeve 103 which is adapted to nest into the annular groove 122, after which the clamping ring 121 is secured into place thus retaining the sleeve at this end in a secure relation.

In order to provide for an adjustable tensioning or stretching of the sleeve 103, a mechanical lever arrangement 130 is provided and will be seen to consist of a pivot block 131 welded or otherwise secured to the clamping ring 121 and of a similar pivot block 132 secured in a like manner to retaining ring 113. At least three of these pivot blocks are provided on the anchor top and anchor base assemblies respectively, equiangularly disposed thereabout. (Because of the cutaway view, the other two lever assemblies have not been shown.) A control rod 133 is attached to each of the pivot blocks 131 and 132 which in turn are pivotally connected to a central pivot block 134. Central pivot block 134 is additionally provided with a drive rod 135, pivotally connected thereto. Drive rod 135 has means for mechanically urging it substantially horizontally toward and away from the longitudinal axis L of the launcher assembly. As shown, this means may consist of a series of teeth 136 formed on drive rod 135 which are adapted to mesh with a motor driven gear 137. Obviously other means such as lead screws or hydraulic arrangements could be provided to effect the movement of this drive rod 135 in the manner indicated. The drive and control rods may be operated simultaneously or singly.

In operation, drive rod 135 is moved toward the longitudinal axis L of the launcher assembly and, because the combined lengths of control shafts 133 are more than the distance between the anchor top and anchor base assemblies, these assemblies will be respectively controlled to move toward or away from each other. Thus, a ten sion is applied to the sleeve 103 in a manner substantially the same as that described in connection with FIG. 1.

Applicants have discovered that a projectile being ejected from the container launcher of the subject inven tion may be given an initial guidance or tendency to slant in a desired direction by varying the tension applied to the various drive rods such as, for example, at 40 in FIG. 1. Using this figure as an example for purposes of illustrating this effect, it is noted that a missile ejected from sleeve 3 would be caused to veer to the left if the drive rod 40 on the left side of the structure was tightened so as to stretch the flexible sleeve on this side more than any other place on the circumference of the sleeve. This guidance function could, of course, be used to advantage especially in launching projectiles from surface ships, aircraft, and the like.

It is noted that an access opening 140 is provided in sleeve 103, this opening as shown consisting of a pair of zippers mounted at right angles to each other in a manner which wiil be described in greater detail in connection with FIG. 6. Obviously, sleeve 3 as well as sleeve 103 could be provided with such an access opening.

The invention has been described thus far in connection with modifications wherein the system was self-supporting. A third operating scheme is shown in connection with FIG. 3 inwhich the sleeve launching system is incorporated into a larger launching structure which would form the part of an overall launching complex as in a ship or submarine hull.

In this regard, it will be seen that a sleeve 203 is provided between an anchor top and an anchor base assembly denoted 207 and 206, respectively, in this figure. These anchor top and anchor base assemblies are substantially identical with those described in connection with FIG. 2. In this modification, however, anchor base assembly 206 is bolted to a deck or flooring 210 while anchor top assembly 207 is secured to an intermediate decking as will be described. In this modification, a plurality of pivot blocks 231 are provided at equiangularly disposed positions around the clamping ring 221.

ecured to these clamping rings 221 are control rods 233, the ends of which are adapted to be sealingly received Within hydraulic cylinders 234. Pivot blocks 232 are secured to an intermediate backing 211 and are provided with control rods 233 pivotally attached thereto. The free ends of control rods 233 are received in hydraulic cylinders 234, and hydraulic connection 235 is provided into the cylinder which will control the fluid forced thereinto which in turn determines the amount of tension placed in the sleeve 203 as anchor top assembly 207 is forced away from anchor base assembly 206. This modification, as Well as the modifications described in connection with FIGS. 1 and 2 could be utilized in connection with submarines, surface ships, and the like, the sleeve launcher extending, if necessary through :a number of deck layers as has been suggested in connection with decks 210 and 211.

It is a feature of the invention that it provides vibration and shock resistant support to a relatively delicate projectile while maintaining the projectile in positions other than vertical, e.g., in a horizontal position.

In connection with FIGS. 6 and 7, two modifications of access openings are disclosed and will be described in detail hereinbelow. Access openings in the sleeve are im portant for purposes of maintenance and checkout and can easily be incorporated into the sleeve design as in dicated in FIG. 2. In this regard, FIG. 6 shows a generally cylindrical sleeve 103 having a zippered access opening placed therein. In this modification, a pair of zippers are placed at substantially right angles one to another, along lines parallel to the warp and woof fibers, respectively, forming the sleeve structure itself. The generally triangularly shaped flap 140 thus created may be easily opened by unzipping the zippers. Zippers with very good sealing action, flexibility, and strength are commerically available and need not be described in detail. This zippered access can be provided at any position on the sleeve to expose large surface areas of a missile at any desired location.

Another access modification is shown in FIGS. 7a and 7b. Referring first to FIG. 7a, it will be seen that a front elevation view of an access opening 300 is provided in the sleeve 103. For this purpose, sleeve 103 is provided with a an annular ring 301 which may be either solid or cabled wire rope and which is adapted to be contained within the space formed by folding back upon the sleeve a flap portion N4. This annular ring 391 assures that the access opening 3% will be maintained at a desired size and that any undue stresses which might otherwise cause damage will be absorbed without harm.

To close opening 300, a curtain valve 303 is secured to the inner surface of sleeve 103 by sewing, dry adhesives, or the like. In the position shown in FIG. 7b, the inner surface of this curtain valve 393 is coated with crepe rubber or other material having a high coefficient of friction. Last minute access or hydraulic or electrical connection can be made through the access opening until the projectile begins to move out of sleeve 1% in its launch phase. The roughened surface on curtain valve 303 would then be forced into position over access opening 309 by the missile carrying it along thus closing the opening and maintaining a sufficient seal to complete the operation of the launch under the operating pressures desired.

Dynamic tests conducted by the inventors have shown that even when numerous holes have been worn through the sleeve, and even though some stiffness in seams was present, the efficiency of the launching device was in no way lowered. Obviously, a suflicient number of access openings may be installed in the sleeve without impairing either the static or dynamic effectiveness of the launching characteristics.

One of the features of this sleeve launch invention resides in the fact that it is not necessary to provide guide shoes around the projectile contained within a tube or the like. Consequently, upon launch, these shoes which are not, of course, connected to the projectile do not fall back upon the launching system giving rise to obvious difficulties.

Additionally, there are no close manufacturing tolerance requirements which consequently allow faster fabrication, lower costs and handling care.

While certain preferred embodiments of the invention have been disclosed, it should be understood that the invention is not limited thereby as many variations will be readily apparent to those skilled in the art, and the invention is to be given the broadest interpretation within the terms of the following claims.

Wherein we claim:

1. A container system for transporting and launching a missile comprising a flexible fabric sleeve adapted to contain such missile, the warp and woof fibers of said sleeve, when relaxed, forming angles of approximately ninety degrees one to the other and approximately fortyfive degrees to the longitudinal axis of said sleeve, at least the inner surface of said sleeve being coated with a lowfriction material which also renders said sleeve substantially impervious to fluid, a flange of fabric formed about the periphery at each end of said sleeve, and a top and bottom anchor assembly each of which are, respectively, secured to said flanges, at least two control rod assemblies rotatably journaled in said top and bottom anchor assemblies, respectively, by oppositely turned threaded portions, means for selectively rotating said control rod assemblies whereby, as said top and bottom anchor assemblies are separated, said sleeve is caused to decrease in diameter, and ac'cess means in said sleeve comprising at least one pair of zippers which are aligned, respectively, with the warp and woof fibers of said sleeve, the point of convergence of said zippers being at the operable ends thereof.

2. A container system for transporting and launching a missile comprising first and second spaced deck members rigidly secured in permanent parallel relationship, said first deck member being formed with an aperture therein, a flexible, fabric sleeve secured at one end to said second deck member, the other end of said sleeve extending through the aperture in said first deck member, the warp and woof fibers of said sleeve converging at angles of approximately ninety degrees to each other and at approximately forty-five degrees to the longitudinal axis of said sleeve when said sleeve is in a relaxed position, each end of said sleeve being secured, respectively, to a top and bottom anchor assembly, said bottom anchor assembly being firmly secured to said second deck member, at least two control rod assemblies on the side of said first deck member opposie to said second deck memher, one end of each of said control rod assemblies being pivotally secured to said first deck member, the other ends of said control rod assemblies secured to said top anchor assembly, and means connected to said control rods for controllably actuating said rods, whereby said top and bottom anchor assemblies may be made to move relative to each other causing a variance in the cross section of said sleeve and the pressure which said sleeve radially inwardly exerts against a missile placed therewithin.

3. A container system for a missile as claimed in claim 2 in which each of said control rods comprise a hydraulic cylinder having an actuating rod extending therefrom.

4. A container system for a missile as claimed in claim 2 in which said sleeve is provided with at least one access port, said access port comprising an aperture in said sleeve, a rod-like member contained in a fold of said sleeve surrounding said aperture, and a flexible fabric closure flap secured to the inner surface of said sleeve below said aperture.

5. A container system for transporting and launching a missile comprising a flexible tight mesh fabric sleeve open at both ends adapted to contain such missile, said sleeve being constructed so that the warp and woof fibers thereof form angles of approximately degrees to each other and approximately 45 degrees to the longitudinal axis of said sleeve when said sleeve is in a relaxed condition, and means operably connected to the portions of said sleeve surrounding the open ends thereof for longitudinally stretching said sleeve, thereby selectively causing it to tighten about said missile.

6. A container system for a missile as claimed in claim 5 in which at least the inner surface of said sleeve is provided with a coating of low friction material which renders said sleeve substantially impervious to fluid.

7. A container system for a missile as claimed in claim 5 in which said means comprises top and bottom anchor assemblies securing the respective ends of said sleeve, and at least two control rods operably secured to at least one of said anchor assemblies for increasing and decreasing the distance between said assemblies.

References Cited by the Examiner UNITED STATES PATENTS 875,266 12/07 Howe etal 217-52 987,162 3/11 Oglesby et al. 217-28 1,557,382 10/25 Sundback.

2,700,518 1/55 Ryno 61: a1. 206-46 2,971,643 2/61 Farley 20683.5

BENJAMIN A. BORCHELT, Primary Examiner.

SAMUEL FEINBERG, SAMUEL W. ENGLE,

Examiners.

Claims (1)

1. 5. A CONTAINER SYSTEM FOR TRANSPORTING AND LAUNCHING A MISSILE COMPRISING A FLEXIBLE TIGHT MESH FABRIC SLEEVE OPEN AT BOTH ENDS ADAPTED TO CONTAIN SUCH MISSILE, SAID SLEEVE BEING CONSTRUCTED SO THAT THE WARP AND WOOF FIBERS THEREOF FORM ANGLES OF APPROXIMATELY 90 DEGREES TO EACH OTHER AND APPROXIMATELY 45 DEGREES TO LONGITUDINAL AXIS OF SAID SLEEVE WHEN SAID SLEEVE IS IN A "RELAXED" CONDITION, AND MEANS OPERABLY CONNECTED TO THE PORTIONS OF SAID SLEEVE SURROUNDING THE OPEN ENDS THEREOF FOR LONGITUDINALLY STRETCHING SAID SLEEVE, THEREBY SELECTIVELY CAUSING IT TO TIGHTEN ABOUT SAID MISSILE.

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