US3106864A

US3106864A - Missile transporter-launcher

Info

Publication number: US3106864A
Application number: US72015A
Authority: US
Inventors: Walter F Seedlock; Jr Joseph Gurskis; Leslie C Coombs; Thomas P Buckman
Original assignee: Lockheed Aircraft Corp
Current assignee: Lockheed Corp
Priority date: 1960-11-28
Filing date: 1960-11-28
Publication date: 1963-10-15
Anticipated expiration: 1980-10-15

Description

Oct. l5, E963 Filed Nov. 28. 1960 w. F. sEEDLocK ETAL MISSILE TRANSPORTER-LAUNCHER 4 Sheets-Sheet 1 INVENToRs WALTER F SEEDLocK JOSEPH GURSKIS JR. LESLIE C. CooMBS THOMAS P BUCKMAN Oct. 15, 1963 w. F. sEEDLocK ETAL. 3,,64

MISSILE TRANSPORTER-LAUNCHER Filed Nov. 28, 1960 4 Sheets-Sheet 2 IGI INVENTORS WALTER E SEEDLOCK JOSEPH GURSKIS JR. LESLIE C. COOMBS THOMAS P BUCKMAN Filed Nov. 28, 1960 0d 15, 1953 w. F. sEEDLocK ETAL 3,l0@,6

MIssILE: TRANSPORTER-LAUNCHER 4 Sheets-Sheet 4 Filed Nov. 28, 1960 INVENTORS WALTER F. SEEDLOCK JOSEPH GURSKIS JR.

LESLIE C. COOMBS THOMAS P BUCKMAN mhd Patented Got., l5, 1963 f ice 3,106,864 MSSILE TRANSIERTER-LAUNCIHR Waiter F. Seedloclr, Palo Alte, Joseph Gurskis, lr.,

Sepulveda, Leslie C. Coombs, Burbank, and Thomas P.

Bushman, Sunland, Calif., assign'ors to Lockheed Aircraft Corporation, Burbank, Calif.

Fiied Nov. 28, 195i), Ser. No. 72,915 11 Claims. {'(l. {t9- 1.7)

This invention relates generally to ground-support equipment for missiles and is particularly directed to a mobile system for transporting and launching such vehicles.

Ballistic and guided missiles of a size and nature generally capable of functioning over intermediate and longer ranges are quite heavy and bulky and have consequently been launched from large complexes which are also adapted to sto-re, erect, `and service them.

Recent strategic requirements have necessitated the generation of a transporting and launching7 system which is highly mobile, low in weight, and fast in reaction time. One of the problems which has arisen in connection with the design of such a system is the necessity for providing a launching structure which is stable and which is capable of withstanding the tremendous forces `and pressures encountered upon tiring of the :missile engine.

It is therefore a primary object of this invention to provide a lightweight structural system for launching a longer range missile which will permit the engine forces at launch to be absorbed land reacted against the ground rather than the launch positioning structure, thus enabling the use of a much lighter weight launching structure.

I-t is an additional object yof this invention to provide such a launch system which is highly mobile and which may be used to readily transport a large missile over standard routes of strategic importance.

A further object of this invention is to provide a mobile transporter-launcher system for a missile which can be anonymously operated, which is highly reliable in operation `and which is relatively low in cost.

An Iaccompanying object is to provide a simplified transporter-launcher design which can be readily scaled down to provide a small vehicle having appeal as a toy which is at the same time highly demonstrative yet safe in operation.

These and other objects will become readily apparent to persons skilled in the art upon a consideration of the description hereinbelow wherein reference is made to the accompanying drawings in which;

FIGURE l is a side-elevational view shown partly in section showing the translauncher vehicle of the invention in a secured position, and in a partly erected position,

FIGURE 2 is a side-elevational view of va modiiication of the invention showing the released mechanism supporting the launch tube in an almost vertical position,

FIGURE 3 is a side-elevational view showing the launch tube and erecting mechanism or" FIGURE 2 in a vertical position, and including a dotted representation of the tube in a secured position,

FIGURE 4 is a front-elevational view shown partly in section, showing -a iirst modiiication of the launch tube firing mechanism,

FIGURE 5 is a lsectional-elevational View showing a second modication of the launch tube tiring mechanism,

FIGURE 6 is an elevational View, shown partly in section, of a modilication of the base or ground contact mechanism supporting an erected launch tube,

FIGURE 7 is a detailed view, shown partly in sect-ion, of the release mechanism utilized in the moditication of FIGURE 2 to maintain a launch tube in a horizontal position during the iirst portion of its positioning, and

FIGURE 8 is a side-elevational View of the bell crank arrangement shown in FIGURES 2 and 3 which allows lthe tube to be lowered vertically into cont-act with a supporting surface.

Referring speciically to FIGURE 1, a translauncher constructed in accordance with the teachings of the subject invention is seen to be associated with a readable vehicle consisting of a tractor 1 of conventional design and a trailer 2 upon which thc transporting and launching mechanism featured by the invention is mounted.

rllhis mechanism is `seen to consist of a launch tube 3 within which is positioned a missile Lt. Launch tube 3 is designed to enable the missile d contained therein to be launched directly therefrom so that the launch tube, in combination wit-h the tractor trailer 1, 2 and the mechanism co-associating these elements may properly be termed a transporter-launcher. In accordance with the weight distribution parameters of a Igiven missile, the launch tube 3 is pivotally mounted through pivot point 5 to an erecting mechanism attaching the launcher tube to the trailer 2. This erecting mechanism consists primarily of a quadripivotal parallelogram of levers, which is generally designated as assembly 6. This parallelogram of levers -assembly 6 consists of a pair of parallel levers 7 and 8 which are each pivotally mounted to the frame of trailer 2 at pivot points 9 and 10, respectively. levers 7 `and S are interconnected at their upper ends by a horizontal cross arm 11, the connection Ito horizontal cross arm 11 being made at pivot points 12 and 13 which are spaced apart a distance which is equal -to the distance between pivot points 9 and 1?. It is to be understood that a similar quadripivotal parallelogram of levers assembly is located on the other side of trailer 2, operating in conjunction with the assembly shown in the drawings. Launch tube 3 is suspended between these assemblies 6 and is pivoted as at pivot point S to the horizontal cross arm 11 of each assembly.

As shown in FIGURE 1, an extension 14 is integrally formed with horizontal cross arm 11 which extends upwardly therefrom to provide a pivot point 15 to which is attached a hydraulic cylinder 16. The actuating arm 17 of hydraulic cylinder 16 is pivotally attached as at pivot point 18 to a point on the launch tube 3 which is located above the center line thereof. Hydraulic cylinder 16y is a double actuating type having a pair of fluid pressure hoses 19 entering into the extreme ends thereof so that actuating arm 17 may be for-ceably moved or retained in a selected position as desired. Operation of hydraulic cylinder 16 and its associated mechanism will be apparent from the description completed hereinbelow in connection with the remaining figures.

In order to raise and -lower launch tube 3, the parallelogram of levers assembly 6 is actuated by means of hydraulic cylinder Ztl having an operating arm 21 pivotally attached to lever 7. The opposite end or base end of hydraulic cylinder 29 is pivotally secured to the frame of trailer 2 at point 22;, this pivotal connection being made to a crank assembly which will be defined and described in greater detail hereinbelow. As further shown in FIG- URE l, hydraulic cylinder 2G is provided with a pair of fluid pressure lines 23 which enable a firm control to be exercised over the movement and position of the parallelogram of levers assembly 6.

Obviously, hydraulic cylinders Ztly and 16 might be replaced as desired with other acceptable actuating means such as a lead screw/motor assembly, or `actuating springs. Such substitution has been made in fact in the modification or the invention shown in FIGURES 2 and 3.

With further reference to FIGURE l, it will be understood that the launch tube 3 and erecting mechanism is `contained within a trailer 2 which is provided with conventionally appearing front, back, and sides. The top por- -tion of trailer 2 also' appears conventional but in fact is adapted to open into two halves 24 which are hingedly is raised. As the launch tube 3 is attached to this assembly, it too is moved upwardly so that at least a portion thereof is completely without the coniines of the trailer 2, after roof halves 24 have been opened to allow this action. This extended position is shown in dotted line in FIGURE l While the launch tube remains horizontal. Desira-bly at this point hydraulic cylinder lo is actuated, extending arm l'7 therefrom, causing rotation of the launch tube 3 around pivot point where it is mounted to cross arm 11. ln this manner, Ithe launch tube is raised to a vertical or near vertical position. should be noted that the bottom portion of trailer 2 is open or has an openable section to allow base portion 2o of launch tube 3 to pass therethrough. Vlt is desirable,

as described hereinabove, to allow base portion 26 of launch tube 3 to come into contact with the bed over which the translauncher vehicle rests so that the forces and pressure generated by the launching of a missile from the tube can be absorbed by this supportive bed rather than the structure of the translauncher vehicle itself. Obviously, the translauncher invention can be adapted with equal utility to a railroad or automotive vehicle. It will be necessary, after the launch tube has been erected into a vertical or near vertical position, to lower the same so that the base thereof may come into contact with the supporting lbed. Otherwise, the corner or edge portion of the base portion Z6 of launch tube 3 would not allow the tube to assume a completely vertical position. This lowering may be easily accomplished by means of proper manipulation of hydraulic cylinder 2% to lower the parallelogram of levers assembly 6. After a missile has been tired from the tube, the reverse operation is accomplished and the translauncher vehicle proceeds anonymously. Actual ejection of the missile from launch tube 3 may be effected by hot firing, by

the separate generation of gas pressure which ejects the missile from its tube, or by spring7 members which, upon release, perform the same operation. Reference will be made in greater detail to each of the latter-mentioned systems in connection with the other iigures. It is noted in passing that FIGURE l also shows the side portion of a console 27 which is adapted to house control equipment as well as equipment for checking the state of readiness lof the translauncher and the missile which is contained therein.

Referring now to 1EIGURES 2 and 3, `a modiiication of the invention is shown which is operated primarily by spring power. Both of 4these figures show an actuating mechanism which supports a launch tube 1%3 upon a trailer frame which is designated 1G12 in each figure. Trailer frame 1412 includes, as shown in these views, side members as well as halved top cover members 12d which are hinged to the trailer frame as =by way of hinges 125.

Each of these ligures also shows a quadripivotal parallelogram of levers assembly which is designated lilo and Ywhich is seen to consist of a pair yof

parallel levers

197 and 108. These levers 167 and 103 are attached to the frame of trailer 102 as at pivot points 139 and 116i, and at their upper end are equidistantly connected at pivot points'112 and 113V to a horizontal cross arm 111. It is noted that launch tube 1h?) is connected to and is mounted between similar horizontal cross arms 111 at pivot points lllS located in each of the cross `arm members. Pivotally attached to an extension 114 at one end of horizontal cross arm 111 is an actuating cylinder 1d@ which has an actuating arm ldlextending from one end thereof. The opposite end of arm `141 is pivotally attached to a pivot point 118 above the center line of the launch tube 103.

The quadripivotal parallelogram of levers assembly 1% is raised, and consequently the launch tube 163 is rotated, by the actuation of the biasing compression spring 142 which is mounted within cylinder 143. Spring 142 contained within said cylinder energizes the actuating arm 144i extending from cylinder 1143, the end of the arm being pivotally connected to lever 167 at a pivot point 145. The lower or other end of cylinder 143 is pivotally immediately connected to the frame of trailer 162 by means of a bell crank 15o. Bell crank 15@ is connected directly to the frame of trailer 1li?, at a pivot point 151, with the lower end yof cylinder 143 being connected to an upper arm 15?. of said bell crank. Lower arm 153 of bell crank 153` is pivotally connected to one end of a bell rod 154 which is horizontally disposed along the frame of trailer 162. The opposite end of bell rod 154` is slidably received within a guide cylinder kILES which is pivotally connected at one end thereof to the frame of trailer (chassis) 102. This bell rod is adapted to reciprocate as noted above in a manner and for a purpose which will be described hereinbelow. lt is important to note at' this point, however, that a stop rod 156 is adiustably, securely positioned between bell rod `15d and its corresponding rod on the opposite side of trailer 1h?. in such a manner as to operate as a stop for the movement of launch tube 1&3 as it approaches a vertical position.

lt may be advisable to provide a tension spring 157 attached at one end to lever 103 and at the other to a point, not shown, on the frame of .trailer or chassis 162. This spring would, of course, act in unison with compression spring 142, aiding in raising the launch .tube out of its secured position in trailer `102.

In this particular modification, the actuation of parallelogram of levers ylilo is controlled by a latch assembly generally indicated at ldtl. Referring for purposes of explanation of the latch assembly 160 to FGURE 3, it is seen that `a catch rod 161 is provided between corresponding levers 163 on either side of trailer 162. This catch rod is adapted to be engaged by a latch dog 162 which is pivotally mounted to the frame of trailer or chassis 1%2 as at point 163. Latch dog `162 is preferably spring biased as by `a latch spring `164- into a position of engagement with catch rod 161 when the launch tube assembly 103 is in a secured position. As pressure is applied to the lower extension on latch dog 162, against the bias of latch spring 163, catch rod 161 is disengaged allowing parallelogram of levers 106 to raise launch tube 103 vertically. This latched or Secured position is best shown by the dotted representation of lFIGURE 3 in which a line through the longitudinal dimension of bell crank 154D is shown to be substantially in alignment with the axis of cylinder 143. This condition of the bell `crank is also shown in solid line in FlGURE 2.

One other feature of the mechanism which should be described before an operational sequence is set forth is the means by which the launch tube 103 is prevented from rotating to the vertical position until the upper portion of its flat vertical movement has been completed. In this regard, reference is taken to the cylinder 14) in FIGURES 2 and 3 and to the detent release mechanism which is shown in greater detail in FIGURE 7. Referring specifically to FIGURE 7 for purposes of description, actuating cylinder 140 is shown with actuating arm 141 in a retracted position, with the spring 170 therein in a compressed status. It should be noted that actuating arm 141 is provided in the lower surface thereof with a latch groove l171. Horizontal cross arm 111 is provided with a recess 172, the bottom portion of which is formed with an aperture leading through to the lower side of arm 111. Located within recess 172 is a detent 173l which consists of a head member of a diameter only slightly less than that of the recess 172 and a tubular member `174 the lower-portion of which is hollow and which is adapted to receive `a cable Vor the like 175 which may be crimped into permanent securement with the hollow tubular member 174 in a conventional manner. A detent compression spring 176 is also located within recess 172 and is adapted to rest on the shoulder formed at the lower end of said recess and at its upper end to abut against the lower portion of the detent head. The lower end of cable 175 is preferably fastened to lever 187 but may be fastened to a suitable position on the frame of trailer 162. It will be seen that as the parallelogram of levers 186 is released and moves launch tube 183 vertically, cable 175 will be placed in tension and is so adjusted as to act A brief operational description of the invention will now be undertaken. With the launch tube compressed into a secured horizontal position, the parallelogram of levers 106 is at its lowest point with compression spring 142 compressed and, if utilized, tension spring 157 extended. Latch dog 162 engages, as shown in FIGURE 3, the catch rod 1611 and in this position cable 175 is slack, allowing spring 176 to extend detent 173 into engagement with the groove 171 thus retaining the launch tube 183 in a horizontal relationship. Before operation, it should be assured that the bell rod 154 is moved in a direction against the arrow as far as possible to cock it, thus forcing the bell crank 150into the position of alignment with the axis of cylinder 143, for a purpose which will be described immediately hereinbelow. Upon release of the latch dog 162, the parallelogram of levers 186, actuated by compression spring 142 and tension spring 157 force the launch tube into a vertical movement while the turbe remains in a horizontal position and, as the maximum position is reached, tension on cable 175 will depress the detent 173 releasing actuator arm 141 causing a rotation of the launch tube 103 into a substantially vertical position as shown in solid line in FGURE 2. At this particular point, the outer surface of launch tube 183 cornes into contact with stop rod 156.

It is appropriate to note that, were bell crank 158 in the actuated or rotated position (shown in solid lines in FIGURE 3), the parallelogram of levers 186 would not be at a height which would permit the free rotation of the launch tube 103 into a completely vertical position, since one corner of the tube would impinge against the ground or base, thus preventing such vertical disposition.

In order to allow such a vertical disposition to be attained and to provide for such an attainment in a relatively rapid manner for purposes which will be hereinafter described, bell crank 158 has been provided.

The combination of the rotational inertia of launch tube 103 and the force of release of compression spring 178 in actuating cylinder 140 will, as stop rod 156 is contacted, force stop Irod 156 in the direction indicated by the arrows. This actuates bell rod 154, rotating bell crank 158 into the position shown in solid lines in FIGURE 3, with completion of rotation of the tube and contact thereof with the ground rapidly taking place so that tiring pin 188 extending from the base of launch tube 163 is tripped.

Referring now to FIGURE 4, it will be seen that a front view of the launch tube as described in connection with FIGURES 2 and 3 is shown in a vertical position, parts thereof being shown in section. Actuators s-3, with actuator arms 144 extending therefrom and connected to lever 1107 are shown which are in turn connected to the launch tube 103 at pivot points 112.

,ioeaes Referring specifically to the details of the launch tube itself, and the details of the missile which is to be ejected therefrom, it will be seen from a consideration of FIG- URE. 4 that the base portion :of launch tube 183 is provided with a central extension 181 extending up into the inner portion of the tube. An aperture 182 is provided in the base portion which is internally enlarged to form a chamber 183. A firing pin 1811 extends into the center extension y181 and is seen to be provided with a radial shoulder 184 at the lower end thereof which is adapted to impinge against the upper surface of the chamber 183, thus limiting the motion of the tiring pin 188. Adapted to abut against the lower surface of shoulder 184 is a compression spring 185 which tends to force firing pin 188 into a released or tired position. Firing pin 188 is cocked by means of the insertion of a cooking rod 186, preferably by threadably engaging said cocking rod with a suitable threaded aperture in the lower portion of ring pin 180. The `firing pin is then withdrawn so that the lower portion thereof extends from the bottom portion :of the launch tube 103 substantially as indicated in FIG- URE 2. The tiring pin is held in this extended or cocked position by means of the spring biased ball detent 18'/ which is adapted to engage groove 188 in the longitudinal surface of tiring pin 188. It will be seen that a substantial shock will release the ball detent 187 from this impression or groove 188 causing the tiring pin, under bias of compression spring 185 to assume a released position.

Center extension l181 -is also provided with a hollow, cartridge receiving tube 189 which may be secured to the center extension 181 as by soldering or by means of an internal shoulder as indicated at 198. Hollow cartridge receiving tube 189 may also be designated a breech tube.

A missile 4184i is adapted to be inserted into the launch tube 183, the outer diameter of missile 184 being only slightly less than the inner diameter of said launch tube. The inner portion of missile 104 is provided with a tubular recess `195 which extends from the base of the missile 184 substantially to the upper Iend thereof. This recess is adapted to receive the hollow cartridge receiving tube 189 which is connected as indicated to the tiring mechanism forming a part of the base of the launch tube 183. An inner blocking probe 196 is attached to the upper portion of the missile 104 and is adapted to be at least partially inserted within the cartridge receiving tube 189 after a gas containing metallic cartridge 197 has been inserted ther-cinto.

1n sequence of operation, a gas cartridge 197, commercially available and commonly filled with carbon-dioxide or other non-toxic gas, is inserted seal rst into the cartridge receiving tube 189. Cocking rod 186 is then threadably inserted into the lower threaded portion of ring pin 188, and the firing pin withdrawn ino a cocked position. A missile 184 is inserted into the launch tube 183 with the inner blocking probe 196 extending dow-n into the cartridge receiving tube 189. (The cooking rod 186 is, of course, withdrawn after the firing pin has assumed a cocked position.)

Referring now to FIGURES 2 and 3, it will be seen that, as the elevating mechanism as described above is operated, and as the bell crank 158l is caused to be rotated by the tube passing through the position shown in FIG- URE 2, the rotation of the bell crank will cause the tube to be lowered to the base surface as it is completing rotation to the approximately vertical position7 and the extension of ring pin will come into contact therewith. Such shock contact will cause the ball detent 187 to be released from the recession 188, allowing the firing pin to be forced by compression spring inwardly so that the point 198 makes rapid contact with and punctures the seal on the gas cartridge. The weight and inertia of the cartridge 197 is sufficient to maintain the same in position rotational release of the compression plate 253.

until the firing pin has punctured the cartridge. The reaction forces created -by the release of the gas from the cartridge 197 propels cartridge 137 upwardly and into contact with the inner blocking probe 96, forcing the probe and the missile 104 outwardly from the tube. Cartridge 19'/ is assisted in this operation by the pressure reated by the gas 'escaping from the cartridge which expands exerting force against cartridge li and against blocking probe 196, and, as the probe `leaves the cartridge receiving tube i8?, against the recess 195 in the missile 11.64, the combined operation of which forces the missile from the tube.

Referring now to FGURE 5, it will be seen that a mechanical arrangement has been substituted for the gas cartridge actuating mechanism described in FiGURE 4 which constitutes a second modification of this portion of the invention. In this modification, the launch tube 2%3 is provided with a ibase portion 249 having an aperture 259 therein. A missile 264 lis adapted to be inserted within launch tube 263. A compression spring l is provided at the base of launch tube 223 and is secured thereto as, for instance, by straps 252. The upper end of compression spring 25d is covered with a compression plate 253 having a radially inwardly turned shoulder receiving the last coil of spring 251. Compression plate 253 has an aperture 255 therein. Substantially vertically upstanding from the inner surface of the base of launch tube 203 is a latch support 260 which is preferably se* cured to ylaunch tube 263 by means of a ninety-degree ange at the base portion thereof, shown in dotted line in FIGURE 5.

Latch support plate 260 is provided at one side thereof with an ear 261 and a latch dog 27d is pivotally connected to the latching plate 266 at point 272. An extension lever 273 is pivotally connected to the latchdog 27th as at point 271, and at its lower end is pivotally connected to the firing lever 274. It is noted that firing lever 271i is itself pivoted to the latch plate Zoll* at pivot point 275.

In operation, a missile 264, provided with an indentation or recess 2d@ at the base portion thereof, is inserted into the launch tube 203. Pressure is exerted so that the missile 2&4 comes into contact with compression plate 253, in turn compressing-spring 251 to the point where the latch dog 27()` engages through the aperture 255 in compression plate 253, retaining the assembly in a cocked position. A retaining compression spring 231 should be provided, preferably encased in a small cylinder, to force latching dog 27u into engagement with the compression plate 253.

Manifestly, as the launch tube 203, lactuated by the mechanism `described in connection with FIGURES 2 and 3, assumes a substantially vertical position, the firing lever 274, com-ing into contact with the base `or ground, will be forced to pivot, moving extension lever 273 upwardly, which in turn will compress spring Zilli and cause latching dog 270 to be removed from engagement with compression plate 253. Thus the spring 251 is released, and the force thereof discharges the missile 204 located within launch tube 203. Another method of releasing said plate 253 is to provide a vertically reciprocable pin, the bottom portion of which extends through aperture 255i, the top portion terminating in a conical segment. As such a pin is pushed upwardly, the conical surface engages the lower surface of latch dog 27d` causing the Such a pin should, of course, be spring biased out of engagement with latch 270.

Referring to FGURE 6, it is seen that a launch tube 303 containing a missile 3M is shown in a substantially vertical position. This structure, especially useful in connection with the modification described in connection with FIGURE 1, is provided with a stabilizing mechanism generally indicated at th which will be seen to LYJ consist of a plurality of hydraulic or spring loaded cylinders 35i having actuating arms 352 extending therefrom. To the ends of actuating arms 352 are attached pads 353 adapted to engage the roadbed as the tubel assumes a vertical Iposition and to transmit the pressures and forces of launching from the tube to the roadbed thereby.

in this modiiication, it is usually desirable to provide a gas generator energy source 4generally indicated at 354 to provide pneumatic pressure to eject the missile 364 from the launch tube 3ll3, after which the missile continues by ignition and operation of its own engines.

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

We claim:

l. A transporter-launcher for a missile comprising a mobile vehicular chassis, a support tube adapted to contain a missile supported upon said chassis, elevating means connected to said chassis and said support tube for horizontally elevating said support tube above said chassis, said elevating means comprising at least one quadripivotal parallelogram of levers assembly having a pair of parallelly operable arms, the two base pivots of said assembly being secured to said chassis, and the remaining pivots secured to a horizontal crossarm a distance apart equal to the distance separating said first mentioned pivot points, erecting means connected at one end to said support tube and at the other to said quadripivotal parallelogram of levers assembly for erecting said support tube to an almost vertical position, and settling means connected to said chassis and to one of the arms of said quadripivotal parallelogram of levers assembly allowing said support tube to assume a substantially vertical position while lowering the base of said support tube into contact with the bed upon which said chassis member is situated.

2. A transporter-launcherrfor a missile as claimed in claim l in which said erecting means comprises an actuating cylinder having an actuating arm controllably extendable therefrom, one end of said cylinder being connected to said horizontal cross arm, and the other end of said actuating arm pivotally `attached to said support tube at a point above the center line thereof.

3. A transporter-launcher for a missile as claimed in claim l in which said support tube contains ejector means for at leastsubstantially completely ejecting `a missile therefrom, said ejector means being actuated as the operation of said settling means causes said l'launch tube to assume a substantially vertical position.

4. A transporter-launcher for a missile as claimed in claim 3 in which said ejector means comprises a breech tube inwardly `and upwardly extending from the base of said support tube and ladapted to contain a compressed gas capsule, a firing pin within said breech tube adapted to react against `a Iweakened portion of a gas capsule positioned in said tube to puncture said weakened portion of said capsule, and cooking means for maintaining said firing pin yin a distended position from fthe base of said launch tube.

Y 5. A transporter-launcher for a missile `as claimed in claim 3 in which said ejector means comprises a compression spring contained within the base portion of said support tube, detent means for retaining said spring in a compressed position as a missile is pushed into said support tube, and a firing pin extended through the base of said support tube `with means on the inner end thereof to release said detent, whereby, `as said firing pin is released, said spring is relieved ejecting the missile from said support tube.

6. A transporter-launcher for a missile comprising a mobile vehicular chassis, a support tube adapted to contain a missile supported upon said chassis, elevating means connected to said chassis and said support tube =for horizontally elevating said support tube above said chassis, said elevating means comprising at least one quadripivotal parallelogram of levers assembly, two of said pivots securing, respectively, two of said levers at one end thereof to said chassis, the remaining pivots securing the opposite end of said levers to a horizontal cross arm, erectino means connected to said support tube and said elevating means for erecting said support tube to an almost vertical position, and settling means actuable by said launch tube as said launch tube is rotated to an almost vertical position connected to said chassis and said elevating means, said elevating means allowing said support tube to `assume a substantially vertical position while lowering the base thereof into contact with the bed upon which said chassis member is situated, said settling means comprising a bel-l crank pivotally secured to said chassis and having upper and lower arms, said upper arm being pivotally linked to one of the l vers of said lever assembly, the lower arm being pivotally connected to a bell rod extending along and slidably journaled to the frame of said chassis, and a stop rod attached tto said bell rod extending substantially normally therefrom into the path of rotation or" said support tube, whereby as said support tube rotates to a substantially vertical position, said stop rod will be contacted, actuating said bell crank through said bell rod rotating said bell crank so as to lower said levers assembly.

7. A transporter-launcher for a missile comprising a mobile vehicular chassis, a support tube adapted to contain a missile supported upon said chassis, ejector means contained within said support tube for at least substantially completely electing a missile therefrom, elevating means connected to said chassis and said support tube for horizontally elevating said support tube above said chassis, said elevating means comprising at least one quadripivotal parallelogram of levers assembly, the two base pivots of which are secured to said chassis with the remaining two pivots secured to a common horizontal cross arm, said support tube being pivotally secured to said cross arm, erecting means connected to said support tube and said elevating means lfor erecting said support tube to a substantially vertical position, said erecting means comprising at least one cylinder having an actuating arm controllably extendable therefrom, one end of said cylinder being connected to said horizontal cross arm, and the end of said actuating arm pivotally connected .to said support tube at a point above the center line thereof, settling means connected to said chassis and said elevating means for lowering said support tube into contact with the bed upon which said chassis member is situated, said settling means comprising a bell crank pivotally connected to said chassis and having upper and lower arms, an actuating cylinder pivotally attached at one end to one of the levers of said lever assembly and `at the other to the upper arm of said bell crank, the lower arm of said bell crank being pivotally connected to a bell rod, the other end of said bell rod being slidably connected to said chassis, a stop rod extending substantially normally horizontally from said bell rod into the path of rotation of said support tube as said support tube approaches a vertical position, whereby as said support tube approaches a vertical position, said stop rod is Iforced in an opposite direction, moving said bell rod and rotating said bell crank, causing a lowering of said :lever assembly.

8. A transporter-launcher Ifor a missile as claimed in claim 7 in which said horizontal cross arm is provided with an aperture extending substantially vertically therethrough, a spring biased detent extending from said aperture and connected at its lower end to a cable, the other end of said cable being connected to said chassis, and a detent receiving groove in the lower surface of the actuating arm of said erecting means for receiving said detent.

9. A transporter-launcher for a missile as claimed in claim 8 in which said ejector means comprises a breech tube inwardly and upwardly extending from the base of said support tube and adapted to contain a compressed gas capsule, a firing pin mounted within the base of said breech tube adapted to react against the inertia of a gas capsule positioned in said tube rto puncture a weakened portion of said capsule, and cooking means yfor maintaining said tiring pin in a distended position `from the base of said support tube.

l0. A transporter-launcher for a missile as claimed in claim S in which said ejector means comprises a cornpression spring contained within the base portion of said support tube, detent means Vfor retaining said spring in a compressed position as a missile is pushed into said support tube, a tiring pin extending through the base `of said support tube, and means on the inner end of said tiring pin to cause a release of said detent, whereby, as said pin is actuated, said spring is relieved, ejecting the missile from said support tube.

11. A transport-launcher for a missile comprising a mobile vehicular chassis, a support tube adapted to contain a missile supported upon such chassis, elevating means connected to said chassis and said support tube for horizontally elevating said support tube above said chassis, erect-ing means connected to said support tube and said elevating means for erecting said support tube to an almost vertical position, and settling means connected to said chassis and said elevating means allowing said support tube [to assume la substantially vertical position while lowering the base of said support tube into Contact with Ithe 'bed upon which said chassis member is situated, said settling means including a bell crank pivotally connected to said vehicular chassis, Ian actuating cylinder pivotally connected at one end to an arm of said bell crank and at the other to said elevating means, |and means pivotally connected to the other arm of said bell crank for selectively causing the rotation of said bell crank at a predetermined position of said support tube.

References Cited in the tile of this patent UNITED STATES PATENTS 1,334,800 Schneider Mar. 23, 1920 2,588,184 Walsh Mar. 4, 1952 2,887,236 Mindrum May 19, 1959 2,964,032 Noble Dec. 13, 196() FOREIGN PATENTS 832,464 France luly 4, 1938

Claims

1. A TRANSPORTER-LAUNCHER FOR A MISSILE COMPRISING A MOBILE VEHICULAR CHASSIS, A SUPPORT TUBE ADAPTED TO CONTAIN A MISSILE SUPORTED UPON SAID CHASSIS, ELEVATING MEANS CONNECTED TO SAID CHASSIS AND SAID SUPPORT TUBE FOR HORIZONTALLY ELEVATING SAID SUPPORT TUBE ABOVE SAID CHASSIS, SAID ELEVATING MEANS COMPRISING AT LEAST ONE QUADRIPIVOTAL PARALLELOGRAM OF LEVERS ASSEMBLY HAVING A PAIR OF PARALLELLY OPERABLE ARMS, THE TWO BASE PIVOTS OF SAID ASSEMBLY BEING SECURED TO SAID CHASSIS, AND THE REMAINING PIVOTS SECURED TO A HORIZONTAL CROSSARM A DISTANCE APART EQUAL TO THE DISTANCE SEPARATING SAID FIRST MENTIONED PIVOT POINTS, ERECTING MEANS CONNECTED AT ONE END TO SAID SUPPORT TUBE AND AT THE OTHER TO SAID QUADRIPIVOTAL PARALLELOGRAM OF LEVERS ASSEMBLY FOR ERECTING SAID SUPPORT TUBE TO AN ALMOST VERTICAL POSITION, AND SETTLING MEANS CONNECTED TO SAID CHASSIS AND TO ONE OF THE ARMS OF SAID QUADRIPIVOTAL PARALLELOGRAM OF LEVERS ASSEMBLY ALLOWING SAID SUPPORT TUBE TO ASSUME A SUBSTANTIALLY VERTICAL POSITION WHILE LOWERING THE BASE OF SAID SUPPORT TUBE INTO CONTACT WITH THE BED UPON WHICH SAID CHASSIS MEMBER IS SITUATED.