US3459100A - Mechanism for locking a missile retainer to a launching apparatus - Google Patents

Description

F. PFISTER MECHANISM FOR LOCKING. A MIssILE RETAINER TO A LAUNCHING APPARATUS Filed April 25, 1968 v 3 Sheets-Sheet 1 In van/0r:

z P/I'Sfer Eon MM awd/ Zmw by Attorneys Aug. 5, 1969 F. PFISTER 3, I

MECHANISM FOR LOCKING A MISSILE RETAINER TO A LAUNCHING APPARATUS Filed April 2s,v 1968 5 Sheets-Sheet 2 Fig. 5

ll'HMMmtW by Alla/ways F. PFISTER Aug. 5, 1969 MECHANISM FOR LOOKING A MISSILE RETAINER TO A LAUNCHING APPARATUS Filed April 25, 1968 3 Sheets-Sheet 3 In van/0r: Franz p/is/er MA/WM am W Attorneys United States Patent 3,459,100 Patented Aug. 5, 1969 Int. Cl. Fins 3/04 US. Cl. 89-1.8 18 Claims ABSTRACT OF THE DISCLOSURE Mechanism for locking a missile retainer to a launching apparatus includes a missile retainer arranged to hold at least one jet-propelled missile and having first and second abutments spaced longitudinally thereof and formed with locking surfaces. Launching apparatus includes two pairs of claws spaced apart longitudinally thereof a distance equal to the spacing of the abutments on the retainer. The claws are mounted on torsionally elastic pivots and adjusting means are operable to pivot the claws between open and locking positions, with an accumulator being operative at least temporarily on the adjusting means to move the claws initially to an intermediate position in which one pair of claws forms a stop engageable with an abutment with the other pair of claws aligned with a second abutment, to align the container on the launching apparatus. The adjusting means is thereupon operable to move both pairs of claws into locking engagement with the container. Releasable latch means hold the adjustment means in a first position in which said claws have been moved to an intermediate position, and the adjustment means is manually operable to disengage said releasable latch means. The adjustment means further includes means for engaging an electrical connector element on the launching apparatus with a mating electrical connector element on the retainer.

BACKGROUND OF THE INVENTION Missiles started from a container, such as a launching tube, and guided to the target in accordance with a so-called target-covering method, are guided by a tracking device forming a part of a launching apparatus supporting the launching tube until such time as the missiles reach their target. This tracking device, which comprises a periscope containing a position finder, forms a unit with an aiming device that can be moved only as a Whole. A mechanism forming a so-called mount is rigidly connected with the launching apparatus, and the launching tube is locked on this mechanism before takeoff of the missile and is removed only after the missile has reached its target.

Since the pick-up range of the position finder arranged in the periscope, and which provides the guiding signals for the flight of the missile after locating the fired missile, is very small, the missile must be so aligned on its mount that it arrives in the pick-up range of the position finder very shortly after the start of missile travel. This is necessary in order that the conditions for a guided flight of the missile can be met.

Due to the rigid connection of the mount and the launching apparatus, the missile to be inserted into the mount, irrespective of whether the latter is or is not a launching tube, must be aligned accurately on the mount. Thus, it must be so attached that the longitudinal axis of the missile and the longitudinal axis of the launching tube as well as the longitudinal axis of the mount are all parallel to each other. After alignment with the mount, the launching tube must therefore be so locked to the latter that the assumed aligned position remains unchanged. At the same time, the necessary electrical connections for igniting the missile engines, for starting the gyroscopes acting as reference transmitters during the flight, and for signal transmission between the launching apparatus and the missile must be established.

For logistic reasons, it is finally desirable to keep the locking mechanism, which is arranged on the exterior of the launching apparatus, as small as possible in its dimensions. It is also desirable to provide a self-contained unit which is insensitive to weather influences, for example. The locking mechanism should be so designed that it permits the use of a launching tube from different sides, the reloading being effected manually or automatically depending on the type of use and on the missile.

SUMMARY OF THE INVENTION This invention relates to mechanism for locking a missile container to a launching apparatus and, more particularly, to an improved such locking mechanism effective to automatically align the container and its missile with the launching apparatus in advance of locking of the container to the launching apparatus.

The purpose of the invention is to provide a locking mechanism for locking a missile holding container to a launching apparatus which is adjustable in elevation and direction, the missile holding container or retainer holding at least one jet-propelled missile. The invention is also designed to provide such a locking mechanism which can be manually operated free from trouble or can be likewise operated using a power amplifier, and which has a low overall height and a closed form meeting the above-mentioned requirements. The missile retainer or container is furthermore ejected after the missile has been fired.

The locking mechanism of the invention is particularly applicable to a launching apparatus which is adjustable as to elevation and traverse and includes relatively adjustable missile retainer locking claws and means for 'automatically establishing an electrical connection. In

accordance with the invention, two pairs of claws, engageable with locking surfaces of the missile retainer to lock the latter to the launching apparatus, are spaced apart serially of the longitudinal centerline of the retainer and of the launching apparatus. These claws are mounted on torsionally elastic pivots, and adjusting means are operable to pivot the claws between open and locking positions. An accumulator, such as coil spring means, is operable at least temporarily on the adjustingmeans to move the claws initially to an intermediate position in which one pair of claws forms a stop engageable with a first abutment on the retainer, with the other pair of claws being aligned with a second abutment on the container, the two abutments being spaced apart longitudinally of each other a distance equal to the longitudinal spacing of the two pairs of claws. This 'alines the container on the launching apparatus, whereupon the adjusting means is manually operable to disengage a releasable catch and further move the pairs of claws into locking engagement with the container while also establishing the electrical connection automatically, this connection being established only after the container has been properly aligned on the launching apparatus by means of the adjusting means and the claws.

This surprisingly simple locking. mechanism has the effect that, after the missile retainer has been placedon the launching apparatus, only one of the two pairs of claws, and particularly the forward pair of claws considered in the launching direction can be moved into a position forming a stop for the abutment on the missile retainer. Thereby, the position of the missile retainer on the launching apparatus and relative to the launching mechanism is positively fixed both longitudinally and laterally of the launching apparatus. At the same time, there is established an exact correlation of the locking elements and the claws relative to the abutments, and an exact correlation of the electrical connector element on the launching apparatus with an electrical connector element on the missile retainer. It is only upon subsequent manual actuation of the adjusting means that both pairs of claws simultaneously engage the associated locking portions of the missile retainer, thus locking the container or retainer to the launching apparatus.

In accordance with the invention, the adjusting means for the locking elements can be actuated either by a manual adjusting member or by hydraulic means, depending on the type of missile used, so that the operation of the locking mechanism can be effected both manually and by using a power amplifier.

The two pairs of claws, operating in the same directions at all times, are arranged on the end faces of a tub-shaped receptacle forming a bearing surface for the missile retainer. Respective eccentrics are disposed on the free ends of torsion bar springs extending symmetrically with respect to the longitudinal axis of the missile retainer and serving as pivots for the claws. The claws are mounted on the torsion bar springs through the medium of these respective eccentrics. The claws of one pair are arranged, with respect to the claws of the other pair, on the torsion bar springs at a different angle. Each torsion bar spring has a cylinder mounted eccentrically thereon, and these cylinders can be moved conjointly by the axially displaceable adjusting means, with an electrical connection being completed in dependence on the movement of the adjusting means.

The mounting of the claws on the torsion springs through respective eccentrics provides for adjustment, in a simple manner, of the holding forces of the individual claws on the associated abutments, so that each of the claws or a pair acts uniformly. The different angular positions or orientations of the two pairs of claws on the torsion springs, in the starting position, permits different lateral engagements of the two pairs of claws on the retainer abutments. In order to attain the same contact pressure for all four claws, the cylinders transmitting the movement of the adjusting means to the respective torsion bar springs rigidly connected therewith are arranged eccentricaly, with respect to the longitudinal extent of the associated torsion bar springs, so that that portion of each torsion bar spring connected with the pair of claws initially engaging the missile retainer is longer, and thus more flexible, than the shorter part of each torsion bar spring connected to the claws of the other pair. The abutment on the missile retainer cooperating with the initially engaging pair of claws, as well as the holding surfaces of the claws of this pair, must be designed, in correspondence with the angular displacement of the claws of this pair in dependence on the elastic properties of the respective torsion springs or bars.

The cylinders can be operated in a simple manner when each cylinder has two diametrically opposed grooves extending therealong and having predetermined equal but oppositely directed slopes, and each cylinder has its ends positioned in bearings on the launching apparatus, and with pins secured on the axially displaceable adjusting means engaging the grooves in the cylinders. The rotation of the cylinders, and thus the angular displacement of the torsion bar springs carrying the claws, thus can be elfected in dependence on the longitudinal movement of the respective adjusting means and in accordance with the predetermined slope of the cylinder grooves.

In accordance with a further feature of the invention, the automatic movement of the pair of claws, forming a stop for the missile retainer, into a position intermediate the open and locking position, is effected by compression coil springs. These springs surround the torsion bar springs 4 between a bearing secured on the launching apparatus intermediate its ends and a bearing block secured on an end surface of the launching apparatus, a pressure plate being interposed and moved by the adjusting means on that side facing the hearing. In their prestressed position, the compression coil springs are held by a catch connected with the axially displaceable adjusting means and cooperating with the manual adjusting member. In this position of the compression springs, the claws of the two pairs are completely open. When the catch is released, the compression springs relax and extend and thus effect a closing movement of both pairs of claws through a small angle. Thus, the pair of claws which is more nearly closed in the initial position prevents further displacement of the container.

In order to effect interconnection of the electrical connectors during the locking operation, the adjusting means is preferably associated with a pair of guide rods each having, adjacent one end, a sloping slot engaged by a pin connected with the electrical plug which constitutes the electrical element mounted on the launching apparatus. These grooves are preferably steep and short, and have the eifect that the pins on the plug engage the sloping portions of the grooves only toward the end of the locking operation of the adjusting means. Thus the plug is rapidly lifted from a retracted position, in which latter it is protected against damage, into an extended position establishing the electrical connection with the socket constituting the other electrical connector element on the missile retainer.

If large operating forces are required, or if an automatic or remote-controlled operation of the locking mechanism is required, the mechanism preferably comprises an arrangement within the adjusting means are centrally arranged on a piston bar having pistons on opposite ends thereof, these pistons being reciprocable in cylinders arranged between the mentioned bearing blocks and bearings along the longitudinal centreline of the tub-shaped receptacle. The ends of the cylinders facing the bearing blocks are connected, by respective lines, to a source of fluid under pressure. In this embodiment of the invention, each guide rod carries a cam bar for actuating microswitches cooperating with the pessure source. Additional drop levers can be connected with the locking claws, which make it possible to drop the empty container or, in case of trouble, a container containing a missile.

Satisfactory operation of the locking mechanism requires a suitable design of the abutments on the missile retainer cooperating with the locking claws on the launching apparatus. In accordance with the invention, the missile retainer is consequently formed with a longitudinally extending bulge or projection protruding from the container configuration and extending from one end face of the retainer to the other. The form of this projection and bulge, and particularly its cross section, is such that the abutments or locking elements interrupt its exterior surface. The projection terminates, in a portion extending from one locking element to one end face of the retainer, in a wedge-shaped part, so that the locking elements flexibly engaging the same, which comprise the claws associated with the locking mechanism, can lock into the associated locking elements of the retainer when the latter is attached on the locking mechanism.

In addition to functioning as abutment means for the locking elements of the locking mechanism, this longitudinal projection or bulge serves also as a container for all accessories required for the launching and guided flight of the missile, such as a capping device for the wire connection for transmitting guiding signals, electrical plug connections, ratchet elements, and a pyrotechnically releasable mechanical unlocking mechanism. Thus, not only are the accessories housed in a retainer having a smooth exterior contour and a low overall height, and thus protected against damage, but also the sensitive connecting elements, such as the electric plug connections, are within the longitudinal projection and thus protected against damage during the handling of the retainer until it is locked on the locking mechanism. The projection furthermore represents an orientation feature which makes it easy for an operator, during manual reloading, always to position the missile retainer in the approximately desired correlation with the locking mechanism, thereby insuring immediately at least a rough alignment of the retainer with the launching apparatus.

An object of the present invention is to provide an improved mechanism for locking a missile retainer, holding at least one jet-propelled missile, with a launching apparatus which is adjustable in elevation and direction.

Another object of the invention is to provide such a locking mechanism, which can be operated, free from trouble, either manually, or by using a power amplifier.

A further object of this invention is to provide such a locking mechanism which has a low overall height and a closed form.

' Yet another object of the invention is to provide such a mechanism in which the missile retainer can be ejected after a missile has been fired.

A further object of the invention is to provide such a locking mechanism including two longitudinally spaced pairs of claws, one pair acting as a stop to engage an abutment on a missile retainer at which time both pairs of claws are aligned with associated locking surfaces of the missile container.

Still another object of the invention is to provide such a locking mechanism in which an electrical connection between the missile and the launching apparatus is established automatically after alignment of the container by adjusting means operating the locking claws.

A further object of the invention is to provide such a locking mechanism including torsionally elastic pivots mounting the claws.

Another object of the invention is to provide such a locking mechanism including simple means for adjusting the pressure to be exerted by the claws on the locking surfaces of the missile retainer.

A further object of the invention is to provide such a locking mechanism in which the missile retainer is formed with a projection laterally thereof extending longitudinally between its opposite ends, and providing abutments and locking surfaces cooperable with the two pairs of claws.

Another object of the invention is to provide such a locking mechanism in which this projection serves to house and protect accessories for firing and controlling the flight of the missile.

Another object of the invention is to provide such a locking mechanism in which such projection forms an orientation feature facilitating at least a rough alignment of the missile retainer with the locking mechanism.

BRIEF DESCRIPTION OF THE DRAWINGS For an understanding of the principles of the invention, reference is made to the following description of typical embodiments thereof as illustrated in the accompanying drawings.

In the drawings:

FIG. 1 is a perspective view, partly in section, illustrating the locking mechanism of the invention with the locking elements in their locked end position;

FIG. 2 is a front elevation view of the locking mechanism as associated with a tubular missile retainer;

FIG. 3 is a partial top plan view of the locking mechanism in an intermediate position;

FIG. 4 is an enlarged partial sectional view of releasable catch means included in the locking mechanism;

FIG. 5 is a view similar to FIG. 1 illustrating schematically an embodiment of the locking mechanism including hydraulically actuated adjusting means;

FIG. 6 is a plan view of a missile retainer formed with a longitudinally extending projection acting as an abutment for the locking element; and

FIGS. 70, 7b and 7c are sectional views taken along lines II, II-II and IIIIII of FIG. 6.

DESCRIPTION OF THE PREFERRED EMBODIMENTS As best seen in FIG. 1, the locking mechanism generally indicated at 1 and arranged to be connected with a launching apparatus which is adjustable in elevation and traverse and which has not been shown, comprises a tub-shaped receptacle 2 having a bottom plate 3, a cover plate 4, and bearing blocks 8 and 9 at its ends. Each of these bearing blocks has a leg 1043 extending outwardly and upwardly from each narrow end thereof, only the legs 10, 11 and 12 being shown in FIG. 1. The legs on opposite ends of the tub-shaped receptacle 2 are interconnected by a pair of rods or bars 15 which reinforce the construction and serve as a support for a missile retainer or container 14, as shown in FIG. 2.

The essential elements of locking mechanism 1 are arranged in tub-shaped receptacle 2 symmetrically with respect to the longitudinal axis or centerline of receptacle 2. These elements include two torsion bar springs 16 extending longitudinally of receptacle 2, and having their ends extending through bearing blocks 8 and 9. At points spaced from opposite ends of torsion bar springs 16, by a distance equal to substantially one third the length of the springs, springs 16 are anchored in bearings 18 and 20 extending transversely of the longitudinal axis of receptacle 2. Between bearings 18 and 20, each torsion bar spring 16 has secured thereto a respective cylinder 22, and each cylinder has two diametrically opposite grooves 23 and 24 of opposite but equal inclinations. Each cylinder 22 further has end collars 25 and 26 engaged in corresponding recesses 27 and 28 in bearing blocks 18 and 20, respectively.

The opposite ends of torsion bar springs 16 projecting externally of bearing blocks 8 and 9 carry respective claws. Thus, the rear torsion bar spring 16 in FIG. 1 carries the claws 30 and 32, and the forward torsion bar spring of FIG. 1 carries the claws 31 and 33. These claws are fixedly mounted on the respective torsion bar springs, and are arranged in pairs with one pair including the claws 30 and 31 and the other pair including the claws 32 and 33. The claws of one pair are arranged on their respective torsion bar springs at a different angle than the claws of the other pair. Thus, the claws 32 and 33 which constitute the forward pair of claws, considered in a launching direction and which are at a right end face in FIG. 1, are already closed somewhat more than the claws 30 and 31 in the starting position.

As can be seen from FIG. 2, the individual claws are arranged on their respective torsion bar springs with the interposition of an eccentric bush 34, a guide sleeve 35, and a clamping bush 36, this arrangement being illustrated, in FIG. 2, for the claws 32 and 33. Thereby, manufacturing tolerances can be compensated by adjustment of the claws by means of the eccentrics and, in addition, the holding force of each individual claw with respect to its associated abutment on the missile retainer can be adjusted.

A bridge 40 extends transversely of the longitudinal axis of receptacle 2, and is located between the bearings 18 and 20 and is longitudinally displaceable between these bearings, the cylinders 22 extending through apertures in the bridge 40, with clearance. Bridge 40 carries pins 42 and 44, each of which engages a groove 23 or 24 of the cylinders 22. As best seen in FIG. 3, bridge 40 has a journal 45, with a ring-shaped collar 46, positioned at its midpoint and serving ao secure bridge 40 on the vent pipe 47 which is part of a manual adjustment means 62 described more fully hereinafter. The end of vent pipe 47 on bridge 40' it slit as at 48 and, at the end of slit 48, a limiting pin 50 extends parallel to pins 42 and 44 and projects at both ends beyond vent pipe 47. Pin 50 is so dimensioned that it can move freely between cylinders 22, and its function is to limit movement of vent pipe 47 in an axial or longitudinal direction.

A pressure plate 52 is mounted on that side of bearing 18 remote from cylinders 32, to serve as a stop for limiting pin 50. Pressure plate 52 can be displaced against the bias of compression coil springs 53. One end of each spring 53 is seated in a respective recess 49 on pressure plate 52, while the opposite end of each spring 53 engages a cylindrical bush 84 of a respective claw 30 or 31. Torsion bar springs 16 extend through bores 55.

In the terminal position represented in FIG. 1, wherein missile retainer 14 is locked to receptaacle 2 as best seen in FIG. 2, the adjusting means are retained by a cubic catch 56 having a wedge-shaped beveled recess 57. Catch 56 is mounted on the free end of a leaf spring 59 in turn mounted in an additional slit 58 in vent pipe 47, slit 58 lying in a plane perpendicular to that of slit 48. Catch 56 protrudes through an opening '60 in vent pipe 47, and leaf spring 59 has a double offset approximately midway of its length.

FIG. 3 illustrates limiting pin 50 engaged against pressure plate 52, with the position of pin 50 when compression springs 53 are compressed being indicated by dot and dash lines.

Referring again to FIG. 1, actuation of the pairs of claws is effected through a manual adjusting element 62 comprising a grip 63 connected, through a grip holder 64, with vent pipe 47 and thus with bridge 40. Vent pipe 47 encloses a push rod 66, biased by a spring 65, which is held in grip holder 64 by a pressure catch 67. In addition, vent pipe 47 is enclosed by a guide tube 68 connected with vent pipe 47 and push rod 66 through a bearing bush 70 arranged in pipe 47. On its end facing receptacle 2, but exteriorly of the latter, there is a guide ring 72 engageable with catch 56 on leaf spring 59, extending through an opening 73 in guide tube 68 in the position of the adjusting means indicated by broken lines. The free end of push rod 66 carries a wedge-shaped beveled pawl 74 cooperable with catch 56.

In order to establish electrical connection between the launching apparatus and the missile holding container, which is not shown in FIG. 1, an electrical plug connector 75 is mounted in receptacle 2 to extend through the upper surface of bearing block 9. In accordance with the movement of vent pipe 47, plug 75 can be moved through guide rods 76, each arrag-ed on bridge 40, from a retracted position into an extended position. For this purpose, each of the guide rods 76, which are guided in recesses 77 of bearing 20, has a groove 78 at its free end, and these grooves have a relatively steep slope. Pins 81, connected with a support 80 for a plug 75, project into grooves 78 of guide rod 76.

In order to temporarily lock the adjusting means in a disengageable manner when limiting pin 50 engages pressure plate 52, as shown in FIG. 3, a catch is provided as represented somewhat schematically in FIG. 4. This catch comprises spring loaded ball detents 82, each associated with guide rod 76. These detents are arranged in bearing 20, and, when vent pipe 47 is displaced into the position of FIG. 3, engage a recess 83 provided on the underside of each guide rod 76 controlling movement of plug 75.

FIG. illustrates an embodiment of the locking mechanism wherein actuation of the adjusting means for the claws is effected by hydraulic means. As the construction and method of operation of the embodiment of the invention shown in FIG. 5 resemble substantially those of the embodiment shown in FIGS. 1 through 4, identical parts have been designated with the same reference characters.

Referring to FIG. 5, bridge 45, carrying pins 42 and 44 engaging grooves 23 and 24 of cylinders 22, is rigidly connected to the midpoint of a piston rod 89 extending along the longitudinal centerline of receptacle 2. At its opposite ends, piston rod 89 has pistons 90 and 91 engaged in respective cylinders 92 and 93. One end of each cylinder 92 and 93 is arranged in a bearing block 8 or 9, and the other end of each cylinder is arranged in the bearing 18 or 20. Cylinders 92 and 93 are connected by respective lines 96 and 97 with a hydraulic pressure source which has not been shown, and lines 96 and 97 terminate in respective cylinders 92 and 93 through openings 94 and 95, respectively, provided at those ends of the cylinders 92 and 93 fixed in bearing blocks 8 and 9. Thus, two oppositely acting hydraulic servomotors are provided.

In this embodiment of the invention, guide rods 76 connected with bridge 40 and actuating electric plug 75 have, on their sides facing torsion bar springs 16, cam bars 98 and 99 for actuating microswitches 100, 101 and 102 mounted on bottom plate 3. In dependence on the degree of movement of piston rod 89 in the direction of the then existing hydraulic pressure gradient, cam bars 98 and 99 also move to actuate the microswitches. These microswitches control magnetic valves connecting the pressure source with lines 96 and 97, and these valves block the supply and discharge of pressure medium into and from the system, respectively, so that the respective position attained by the adjusting means is maintained. Through the microswitches 100, 101 and 102 there are thus defined individual locking positions corresponding to the positions determined by all detents 82 and catch 56 of the embodiment of the invention shown in FIGS. 1 through 4.

In order to eject retainer 14 after firing of a missile, this embodiment of the invention provides an ejector comprising a lever 105 connected, in a suitable manner, with only those claws arranged on one respective torsion bar spring, or either with claws 31 and 33 or with claws 30 and 32, lever 105 forming an integral part with the claws which it operates. The ejector must be so connected with the respective claw that it releases, in the intermediate position of the claw, or when a new container 40 is loaded into the launching mechanism, the latch engaging portion of the locking mechanism for the retainer. This means that the ejector lies in the plane of cover plate 4. During opening movement of the claws, container or retainer 14 is thus ejected.

Also connected with receptacle 2 is a bracket 103 by means of which the locking mechanism can be secured, for example, on an aiming and tracking device. Such a bracket can also be used in a manually operated embodiment of the locking mechanism, as shown in FIGS. 1 through 4.

FIG. 6 is a plan view of that surface of a tubular missile retainer 14 facing receptacle 2 during locking thereof. This surface has longitudinally extending projection or bulge 120, which extends over part of its circumference. This longitudinal bulge or projection, which represents the abutment mentioned in connection with FIG. 2, extends from one end of container 14 to the other, and is divided, by openings in its surface, into three sections 122, 124, and 126. That part of the longitudinal projection which is the forward part considered in the firing direction, namely the part 122, is formed, with respect to the cross section of the adjoining sections 124 and 126, with two recesses 127, as shown in FIG. 7a. The offset part 128 between these recesses serves as a guide for the spring biased claws 32 and 33 constituting the forward pair of claws, when the latter are in the intermediate position. Offset part 128 terminates in a wedge-shaped part 121 at its forward end, so that centering surfaces between the forward pair of claws and the bulge are thus formed.

Identical openings along the lines II-II, in the surface of longitudinal bulge 120, form the locking elements or recesses proper 130 and 132, for engagement by claws 32, 33 and 30, 31, respectively. As best seen in FIG. 7b. bulge 120 has, at these locking recesses, a substantially T-shaped cross section. In their locking positions, as also seen in FIG. 2, the holding surfaces of the claws bear on the head of the T-sh-aped strap 131.

The longitudinal spacing between the two locking elements 130 and 132 corresponds, naturally, to the distance 9. between the front and rear pairs of claws on the locking mechanism, so that, as the forward end part 124 of bulge 120 engages thefront pair of claws, in the intermediate position of the latter, as will be described more fully hereinafter, both pairs of claws are in exact correlation to their respective locking elements 130 and 132.

Apart from serving as an abutment for the locking ele- 'rnents, bulge 120 serves also to receive all accessories required for initiating and guiding the flight of the missile. These include the capping device 135 for the wire connection conducting the guiding signals to the missile during its' flight and a plug receptacle 138 which forms, with multi-prong plug 75 of FIG. 1, an electrical connection such as described, for example, in copending application Ser. No. 722,070, filed Apr. 17, 1968, and over which the connection is established to all signal circuits necessary for launching and guiding the flight of the missile. Longitudinal bulge 120 also contains a pyrotechnically releasable mechanical unlocking mechanism 140 which disengages a ratchet 142, not described in detail, which fixes the missile and which is indicated in FIG. 70 by broken lines, this fixing being with respect to tubular container 14 and being maintained until the missile is fired. Ratchet or catch 142 is disengaged after closing of the missile electrical circuits, and reference is made herein to copending application Ser. No. 729,189, filed May 15, 1968.

Throughout its entire length, bulge 120 also forms a cable duct in which all cables connecting the guiding wire, the capping device 135, the receptacle 138, the mechanical unlocking mechanism 140, and the signal circuits until the missile is launched, are combined to a common central cable 136. The method of operation of the locking mechanism will now be described with respect to the embodiment of the invention shown in FIGS. 1 through 4. With the claws 30, 31 and 32, 33 in the completely open position, the adjusting means, that is the bridge 40 with its pins 42, 44 and vent pipe 47 connected to bridge 40 through channel 45, are in the position illustrated in broken lines in FIG. 3, and are held in this position by catch 56 engaging guide ring 72. After the missile retainer or holder is mounted from the top, or inserted from the front side, pressure catch 67 is actuated so that the two pairs of claws can be moved into their intermediate position. For this purpose, catch 56 is disengaged from guide ring 72 by pawl 74, when pressure catch 67 is actuated. Compression springs 53' therefore relax or expand abruptly. Pressure plate 52, which hitherto has been displaced against the bias of compression springs 53, now moves back until it strikes bearing 18, after which ball detents 82 lock into recesses 83. Simultaneously, however, the claws of both pairs have been turned inwardly. The front pair of claws 32, 33, which is already more fully closed than the rear pair in the starting position, has been turned so far inwardly into an intermediate position that the wedge-shaped part 121 of bulge 120 on retainer or holder 14, and which is at the front and considered in the launching direction, can be pushed easily between the claws of the front pair. During further displacement of missile holder or retainer 14, claws 32, 33 bear resiliently against surfaces 129 of recesses127, the cross section of the parts being shown in FIG. 7a. Thus, canting of the longitudinal bulge 120, with inaccurate bearing on the locking mechanism, is avoided. The container can now be advanced so far into the locking mechanism until the rear surfaces of locking elements 130, which are the forward ends of the bulge section 124, engagethe inner faces of the front pair of claws 32, 33. The aligned position of container 14 is thus indicated to the operator.

Both the front pair of claws, and the rear pair of claws which does not yet bear on the longitudinal bulge 120, are now in positions exactly aligned with the associated locking elements 130 and 132, respectively. In this position of the parts, and due to the construction, plug 75 of the locking mechanism, retracted along with bearing piece 80, is aligned exactly with receptacle 138 of retainer or holder 14. The pairs of claws are still held in this position by the catch comprising the ball detents 82 and the recesses 8-3, until the operator pushes in the manual adjustment element 62.

Upon such pushing in of adjustment element 62, the lightly holding ball detent catch is disengaged and bridge 40, connected with vent pipe 47, is advanced until it strikes bearing 20. Pins 42, 44 of bridge 40, engaging grooves 23, 24 of cylinders 22, thus turn cylinders 22 so that both pairs of claws are closed into their locking elements 130, 132. Catch 57 now protrudes, as seen in FIG. 1, into opening 60 of vent pipe 47 and blocks the claws, held by pawl 74, in their locking position. Toward the end of the locking movement, plug 75 is extended by pins 81 on mount 80 riding upwardly in the grooves 78 to engage receptacle 138. For this purpose, the slope of grooves 78 is so selected that the extending movement of plug 75 starts only when holder or retainer 14 is already locked immovably by both pairs of claws, even though the claws are not yet fully closed.

During the unlocking of the retainer or holder, the above procedure takes place in a reverse order. By actuating pressure catch 67, catch 56 is disengaged from opening 60 and bridge is pulled out so far by manual adjusting element 62, until limiting pin 50 and journal strike pressure plate 52, as shown in FIG. 3. Ball detents 82 now again engage recess 83 and permit removal of the retainer o'r holder from the locking mechanism. Subsequently, the manual adjusting element 62 can be pulled out sufliciently far that catch 56 again engages guide ring 72 and compression springs 53 are loaded to move the claws into their intermediate position for loading a new retainer or holder in the locking mechanism.

While specific embodiments of the invention have been shown and described in detail to illustrate the application of the principles of the invention, it will be understood that the invention may be embodied otherwise Without departing from such principles.

What is claimed is:

1. In mechanism for locking a retainer, holding at least one jet-propelled missile, to a launching apparatus, adjustable as to elevation and traverse, including relatively adjustable retainer locking claws and means for automatically establishing an electrical connection: the improvement comprising, in combination, said retainer having first and second locking elements spaced longitudinally thereof; two pairs of claws engageable with said retainer to lock the latter to said launching apparatus, said two pairs of claws being spaced apart serially of the longitudinal centerline of said retainer a distance equal to the spacing of said locking elements; torsionally elastic pivots mounting said claws; adjusting means operable to pivot said claws between open and locking positions; and accumulator means operative at least temporarily on said adjusting means to move said claws initially to an intermediate position in which one pair of claws forms a stop engageable with an abutment of said first locking element on said retainer, with the other pair of claws aligned with the second locking element on said retainer, to align said retainer on said launching apparatus; said adjusting means thereupon moving said pairs of claws into locking engagement with said locking elements.

2. In mechanism for locking a missile retainer to a launching apparatus, the improvement claimed in claim 1, including means operable to establish said electrical connection automatically only after such alignment of said retainer by said adjusting means and the claws operable thereby.

3. In mechanism for locking a missile retainer to a launching apparatus, the improvement claimed in claim 1, including a manual adjusting element selectively actuable to operate said adjusting means.

4. In mechanism for locking a missile retainer to a launching apparatus, the improvement claimed in claim 1,

including at least one fluid pressure actuator operable to actuate said adjusting means.

5. I11 mechanism for locking a missile retainer to a launching apparatus, the improvement claimed in claim 1, in which said launching apparatus includes a tubshaped receptacle providing a bearing surface for said retainer; said torsionally elastic pivots comprising a pair of torsion bar springs extending longitudinally of said receptacle and symmetrically with respect to the longitudinal centerline thereof; means anchoring said torsion bar springs to said receptacle intermediate their ends; said pairs of claws being arranged at the end surfaces of said receptacle, with each claw mounted on a respective end of a respective torsion spring.

6. In mechanism for locking a missile retainer to a launching apparatus, the improvement claimed in claim 5, including respective adjustable eccentrics interposed between each claw and its associated torsion bar spring for adjustment of the associated claw.

7. In mechanism for locking a missile retainer to a launching apparatus, the improvement claimed in claim 6, in which the claws of one pair diverge at a different angle from the angle of diversion of the claws of the other pair.

8. In mechanism for locking a missile retainer to a launching apparatus, the improvement claimed in claim 7, including a pair of cylinders each secured to a respective torsion bar spring and located intermediate the ends of the respective torsion bar spring but nearer to one end thereof than to the other end thereof; said adjusting means being displaceable parallel to the areas of said cylinders and cooperable therewith to rotate said cylinders during such axial displacement of said adjusting means.

9. In mechanism for locking a missile retainer to a launching apparatus, the improvement claimed in claim 8, in which said means for automatically establishing an electrical connection comprises an electrical connector mounted on said receptacle for movement between a retracted position and an extended position; said adjusting means including means operatively connected to said electrical connector and operable, during axial displacement of said adjusting means, to extend said electrical connector.

10. In mechanism for locking a missile retainer to a launching apparatus, the improvement claimed in claim 8, in which each cylinder is formed with a pair of diametrically opposite grooves having preselected equal but oppositely directed slopes; said means anchoring said torsion bar springs comprising a pair of longitudinally spaced hearings on said receptacle; said cylinders having axially opposite ends rotatably supported in said bearings; said adjusting means including pins engageable in said grooves of said cylinders to rotate said cylinders upon longitudinal displacement of said adjusting means.

11. In mechanism for locking a missile retainer to a launching apparatus, the improvement claimed in claim 10, in which said accumulator means comprises a pair of compression springs each embracing a respective torsion bar spring between one of said bearings and a bearing block on the adjacent end of said receptacle; and a pressure plate movable by said adjusting means and interposed between said compression springs and said one bearing.

12. In mechanism for locking a missile retainer to a launching apparatus, the improvement claimed in claim 11, including a catch connected with said longitudinally displaceable adjusting means and operable to latch said compression springs in their prestressed condition; said adjusting means including a manual adjusting element cooperable with said catch to release the latter.

13. In mechanism for locking a missile retainer to a launching apparatus, the improvement claimed in claim 2, in which said adjusting means is displaceable longitudinally-relative to said claws; said means for automatically establishing an electrical connection including an electrical connector mounted on said launching apparatus for movement between a retracted position and an extended position; guide rods connected to said adjusting means for movement therewith and having sloping cam slots adjacent one end; and pins on said electrical connector engaged with said slots to eifect the extension of said electrical connector upon displacement of said adjusting means through a predetermined range.

14. In mechanism for locking a missile retainer to a launching apparatus, the improvement claimed in claim 4, in which said launching apparatus includes a tubshaped receptacle forming a bearing surface for said retainer and having a bearing block at each end thereof; a pair of bearings fixed to said receptacle in spaced relation thereto and intermediate said bearing blocks; said hydraulic actuator means including a piston rod extending along the centerline of said receptacle, and said adjusting means being secured to substantially the midpoint of the length of said piston rod; said piston rod having a pair of pistons thereon, one at each end, and each piston. being reciprocable in a respective cylinder; each cylinder being supported between a respective bearing block and the adjacent bearing; and lines connected to those ends of the cylinders facing said bearing blocks, for connection to a source of fluid under pressure.

15. In mechanism for locking a missile retainer to a launching apparatus, the improvement claimed in claim 14, including plural microswitches mounted in said receptable and controlling application of fluid pressure to said cylinders; said adjusting means being displaceable longitudinally of said receptacle; guide rods extending from said adjusting means and operable to establish said electrical connection upon a predetermined displacement of said adjusting means longitudinal of said receptacle; and cam bars carried by said guide rods and operable to actuate said microswitches.

16. In mechanism for locking a missile retainer to a launching apparatus, the improvement claimed in claim 5, including means for ejecting a retainer from said receptacle; said ejecting means comprising a lever secured to only two claws mounted on the same torsion bar spring.

17. In mechanism for locking a missile retainer to a launching apparatus, the improvement claimed in claim 1, in which said retainer is formed with a bulge extending longitudinally thereof from one end of the retainer to the other end thereof; said bulge being formed with two pairs of oppositely laterally opening recesses, each pair constituting one of said locking elements; said bulge having a portion extending forwardly from the forward locking element, considered in the firing direction, formed with a wedge surface engageable with one pair of claws in the intermediate position of the latter for movement of said claws along said wedge surface toward the forward locking element for engagement with said abutment; the other pair of claws being laterally aligned with the rearward locking element upon engagement of said one pair of claws with said abutment.

18. In mechanism for locking a missile retainer to a launching apparatus, as claimed in claim 17, in which said bulge is formed as a container to receive all accessories required for launching the missile and guiding the flight of the missile.

References Cited UNITED STATES PATENTS 2,972,933 2/1961 Guthrie et a1. 89--1.817 3,389,637 6/1968 Beier et a1. 89-1.815

SAMUEL W. ENGLE, Primary Examiner.

US. Cl. X.R.

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