US3088698A

US3088698A - Vertical catapult for missiles

Info

Publication number: US3088698A
Application number: US49986A
Authority: US
Inventors: Ongaro Theodore
Original assignee: Individual
Current assignee: Individual
Priority date: 1960-08-16
Filing date: 1960-08-16
Publication date: 1963-05-07
Anticipated expiration: 1980-05-07

Description

May 7, 1963 1'. ONGARO vmzcm. CA'I'APULT FOR MISSILES 3 Sheets-Sheet J.

Filed Aug. 16. 1960 INVENTOR. Waaaee owmeo In [I 11 l 1111 May 7, 1963 'r. ONGARO VERTICAL CATAPULT FOR MISSILES 5 Sheets-Sheet 2 Filed Aug. 16. 1960 I N V EN TOR. 72/(aoafe 01 0440 y 7, 1963 T. QNGARQ 3,088,698

VERTICAL CATAPULT FOR MISSILES Filed Aug. 16, 1960 5 Sheets-Sheet 3 INVENTOR. rr/fowze am /e0 3fl8898 Patented May 7, 1963 3,ilh8,698 VERTICAL CA'IAPULT FUR MISHES Theodore Ougaro, 2303 Ahington Road, (Jolurnhus, Ohio Filed Aug. 16, 19nd, Ser- No. 49,936 10 Claims. (Cl. 244-63) This invention relates to vertical catapults and more particularly relates to a vertical catapult for launching missiles and the like.

Of the many considerations involved in achieving a successful missile launching, perhaps the most important is the relation of the weight of the payload to the total Weight of the missile. A balance must always be reached between the weight of the payload, made up, for example, of instruments, and the weight of the propellant which makes up the major portion of the remaining weight of the missile. Without sufficient instrumentation the missile cannot be correctly guided nor can it perform its appointed task; without sufficient propellant the missile is unable to span its desired range. It has been found that a high percentage of the propellant must be expended to overcome the initial inertia of the rocket caused by the force of gravity. Once the missile is off the ground and has achieved some slight velocity, the propellant is much more effective and efficient in achieving distance per unit weight of propellant.

According to the present invention, it has been found that a missile can be given an initial velocity without the consumption of any of its propellant, thereby allowing the same amount of propellant to drive the missile farther than could previously be achieved, or, conversely, enabling the missile to be driven the same distance with a larger payload.

It is therefore an object of this invention to provide apparatus to impart an initial velocity to a missile.

It is a further object of this invention to provide apparatus for imparting an initial velocity to a missile without drawing on any of the propellant carried by the missile.

It is a still further object of this invention to utilize the force of gravity for launching a missile.

It is another object of this invention to provide apparatus for overcoming the inertia of a body by utilizing the force of gravity acting on another body.

It is a further object of this invention to provide launching apparatus for a missile.

These and further objects and advantages of the invention will become more apparent upon reference to the following specification, appended claims and drawings, wherein:

FIGURE 1 is a front elevation View of launching apparatus constructed according to the present invention;

FIGURE 2 is a view taken partly in section along the line 22 of FIGURE 1;

FIGURE 3 is a view in section taken along line 33 in FIGURE 2;

FIGURE 4 is an enlarged view of the pulley system used in the launching apparatus of FIGURE 1;

FIGURE 5 is a view taken along line 55 of FIG- URE 4;

FIGURE 6 is a view taken along line 6-6 of FIGURE 1; and

FIGURE 7 is a view partly in section taken along line 7-7 of FIGURE 5.

Referring now to the several figures, and in particular to FIGURE 1, there is shown a launching apparatus generally indicated at 1 which comprises a catapult tower 4 and a force tower 38. The missile 2 to be launched is nested in position in the catapult tower 4 which is made up of any desired number of structure supports 6, shown in greater detail in FIGURE 6. These supports may be of any suitable construction but are preferably skeletal in nature and are suitably joined together by members 7 to form a rigid and sturdy structure. A number of guy cables 8 may be provided for retaining the tower in proper position.

The launching tower is provided with a number of pulley systems, preferably one for each supporting struc ture and one of these is illustrated in enlarged form in FIGURE 4. In this figure, a double pulley 10' is supported at the top of the tower by any suitable means such as a shaft 11 and bearing 12. A pair of

single pulleys

14 and 16 are located at the base of the tower and are mounted for rotation in any suitable manner, for example on

bearings

18 and 20 and shafts 21 and 23. One track of pulley 10 and pullley 14 are interconnected by a closed loop cable 22 carrying a shock coupling 24 and a lifting pad 26 which is located or clamped on the cable at a position halfway around the cable loop from the coupling 24. Due to this relative positioning of the coupling and the lifting pad, the coupling is at the uppermost point on one of the straight segments of the loop when the lifting pad is at the lowermost point on the other straight segment of the loop as seen in FIGURE 4.

A shock arrester or absorber 28 is arranged about the cable 22 for shock arresting engagement with the shock arrester 28 when the lifting pad 26 nears the uppermost portion of its straight segment of the loop.

Referring to FIGURE 5, which shows the lower pulley 14, the lifting pad 26 also clamps a second cable 30 which extends upwardly and over the second groove in the upper double pulley 14 As shown in FIGURES 5 and 7, the lifting pad 26 preferably consists of two

metal sections

27 and 29, one of which is formed with a horizontal flange 32 which serves as the lifting surface. The two

sections

27 and 29 are joined together in any suitable manner, such as by screw and nut assemblies, so as to firmly grasp the

cables

22 and 30. The lifting pad 26 is also provided with a plurality of wheels 34 that cooperate with guides 36 which extend up along the supporting structure 6.

Referring again to FIGURE 4, the capable 30 is passed around the second groove of the upper pulley 10 and thence beneath the lower pulley 16. While the pulley 16 is illustrated as being laterally offset from the axes of pulleys 10 and 14- this is for purpose of clarity only and this pulley axis would ordinarily be quite close to a vertical line through the axes of pulleys 10 and 14. It can be seen from this arrangement that when a downward force is exerted on the cable 30, the lifting pad 26 will be lifted or moved toward its uppermost position, while the coupling 24 is drawn down into contact with the shock arrester 28. While only one pulley system is illustrated in FIGURE 4, it will be recalled that it was previously stated that one such system is preferably provided for each support section 6.

Referring again to FIGURE 1, the force tower 38' may be of any suitable structural arrangement and is provided at its top with a number of pulleys 40 corresponding in number to the pulleys 10 at the top of the catapult tower 4. A like number of pulleys 42 is also provided at the base of the force tower.

The cable 30 after passing beneath the lower pulley 16 at the base of the catapult tower proceeds across beneath a suitable one of the lower pulleys 42 and thence upwardly to a corresponding upper pulley 40. After being crossed over this pulley, the cable is fixedly attached to the inner cylindrical wall 41 of an annular tank 44 at a point 46'. The inner wall 41 surrounds the tower 38 in such a manner as to be slidable thereover.

FIGURES 2 and 3 show the tank 44 in greater detail.

As can be seen from these figures the tank is arranged annularly around the tower 38 and is comprised of the inner cylindrical wall 41, an outer cylindrical wall 43 and a bottom 45. The bottom 45 is provided with a number of holes or openings 48 and the tank is provided with a suitable plastic liner 50 to prevent fluid from escaping through these openings. Further openings 47 are provided in the outer cylindrical wall 43.

Referring again to FIGURE 1, it may be seen that a circular open top tank 52 is provided around the base of the force tower 38 and has mounted therein a heavy anvil structure 3 9. Anvil structure 39 has mounted in the upper surface thereof a series of upwardly extending spindles 56 correspond in number and position to the holes 48 in the bottom 45 of the tank 44. A supply pipe 58 and a pumping station 60 are provided for filling the tank 44 with fluid stored in the tank 52.

The operation of the apparatus described above will now be discussed. The tank 44 is raised by any suitable means such as a puller 35 engaging the pad 26. A missile 2 is placed in the catapult tower 4 so that protruding sections 62 of the missile rest on the flanges 32 of the lifting pads 26 in the manner shown in FIGURE 4. At this time, the tank 44 is secured at the top of the force tower 38 by any suitable means such as releasable clamp 37 engaging the pad 26. Fluid from the tank 52 is now pumped through the pipe 58 and into the tank 44 under the action of the pumping station 60. A sufiicient amount of fluid is pumped into the tank 44 so that its total weight is considerably greater than that of the missile 2.

When it is desired to launch the missile, the tank 44 is released by the clamp 37 and the force of gravity causes it to drop toward its base. Cables 30 are thereupon hauled downwardly over pulleys 40 to move the loop cables 22 in the catapult tower 4 and thereby cause the lifting pads to move upwardly. The tank 44 accelerates rapidly due to the force of gravity and this accelerating force is substantially completely transmitted through the cable 30 and the lifting pad 26 to the missile. As the tank 44 approaches the bottom of its travel, the spindles 56 in anvil structure 39 pierce the plastic liner 50 through the holes 48 in the bottom 45 of tank 44, causing the plastic lining to shatter. In addition the impact bursts the lining immediately over the openings 47 in the outer wall of the tank so that the fluid contained in the tank is released causing the tank to lose most all of its kinetic energy. The fluid is retained in the tank 52.

Approximately at the same time that the tank 44 reaches the bottom of its travel the arrestor coupling 24 comes into contact with the shock arrestor 28 which acts to slow down and eventually stop the movement of the loop cable 22, thus preventing the lifting pad 26 from coming into contact with the pulley 10. At this time, the missile 2 is catapulted out of the launching tower and, with towers of practical height may be given a vertical velocity of about 100 feet per second.

By the apparatus described above, it can be seen that an initial velocity can be imparted to a missile without the need of consuming any of its propellant. By the use of the apparatus described, the force of gravity acting on one body can be transmitted through a cable system and applied to the missile, thus catapulting it from the ground. In this manner, greater efficiency of the missile can be achieved by providing it with either greater range for a given amount of propellant or a greater payload for the same range attained by comparable present missile launching system.

The invention may be embodied in other specific forms without departing from the spirit or essential characteristics thereof. The present embodiment is therefore to be considered in all respects as illustrative and not restrictive, the scope of the invention being indicated by the appended claims rather than by the foregoing description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein.

What is claimed and desired to be secured by the United States Letters Patent is:

1. Missile launching apparatus comprising, a launching tower, a first pulley means associated with said launching tower, a second pulley means associated with said launching tower, first closed loop cable means operatively connecting said first and second pulley means, means associated with said first closed loop cable means adapted to impart a force to the missile to be launched, a third pulley means associated with said launching tower, a force tower, force developing means movably associated with said force tower, second cable means connected to said force developing means and associated with fourth pulley means for raising said force developing means relative to said force tower, means for releasing the kinetic energy of said movable means as it approaches the lower end of its path of motion, said second cable means being operatively associated with said third pulley means and said second pulley means so as to transmit forces developed by said force developing means to said means associated with said first closed loop cable means.

2. The apparatus of claim 1 wherein the force developing means is a tank adapted to be filled with fluid and wherein the force is developed by reason of the force of gravity causing said tank to be lowered relative to said force tower.

3. The apparatus of claim 2 wherein the kinetic energy releasing means comprises means for emptying said tank of said fluid.

4. Apparatus for launching missiles comprising a launching tower for supporting a missile to be launched, a force tower, force transmitting means passing over support means in each of said towers, one end of said force transmitting means being adapted to engage a missile in said launching tower for imparting accelerating forces to said missile, fluid carrying weight means secured to the other end of said force transmitting means, means for suspending said weight above the base of said force tower, and means for releasing said weight whereby the falling forces of said weight pass by way of said force transmitting means to said launching tower to accelerate a missile, said weight including impact responill/1? means for discharging said fluid at the end of its 5. Apparatus for launching missiles comprising a launching tower for supporting a missile to be launched, a force tower, force transmitting means passing over support means in each of said towers, one end of said transmitting means being adapted to engage a missile in said launching tower for imparting accelerating forces to said missile, fluid carrying weight means secured to the other end of said force transmitting means, means to raise said fluid carrying means while no fluid is located therein to a position above the base of said force tower, means for suspending said weight in said raised position, means for filling said weight means with a fluid, and means for releasing said weight whereby the falling forces of said weight pass by way of said force transmitting means to said launching tower to accelerate a missile.

6. Apparatus for launching missiles comprising a vertical launching tower for supporting a propellant burning missile to be launched, a force tower, force transmitting means passing over support means in each of said towers, one end of said force transmitting means being adapted to engage a missile in said launching tower for imparting accelerating forces to said missile, fluid carrying weight means secured to the other end of said force transmitting means, means to raise said weight means while no fluid is located therein to a position above the base of said force tower, means for suspending said weight in said raised position, means for filling said suspended weight means with a fluid, and means for releasing said weight whereby the falling forces of said weight pass by way of said force transmitting means to said launching tower to accelerate a missile, said weight including impact responsive means for discharging said fluid at the end of its fall.

7. Missile launching apparatus comprising, a launching tower, first pulley means associated with said launching tower, second pulley means associated with said launching tower, closed loop cable means operatively connecting said first and second pulley means, first means associated with said closed loop cable means adapted to impart a force to the missile to be launched, third pulley means associated with said launching tower, a force tower, force developing tank means adapted to be filled with a fluid associated with said force tower, said tank means being of a porous construction, a rupturable membrane which is adapted to retain the fluid within said porous tank means substantially covering the inner surface of the tank, second cable means connected to said force developing means and associated with fourth pulley means for raising said force developing tank means relative to said force tower, means for rupturing said membrane thereby releasing the kinetic energy of said movable tank means as it approaches the lower end of its 6 path of motion, said second cable means being operatively associated with said third pulley means and said second pulley means so as to transmit forces developed by said force developing means to said first means associated with said closed loop cable means.

8. Missile launching apparatus according to claim 7 wherein, shock absorbing means is located on said closed loop cable means to prevent the said first means associated with said closed loop cable from coming in contact with said first and second pulley means.

9. Missile launching apparatus according to claim 7 wherein, said means for rupturing said membrane is a spiked surface located at the base of said force tower.

10. Missile launching apparatus according to claim 7 wherein, second tank means is so located in relation to the force tower as to receive and retain the fluid released by said first tank.

References Cited in the file of this patent UNITED STATES PATENTS 975,953 Hourwich Nov. 15, 1910 2,672,306 Doolittle et al Mar. 16, 1954 2,763,447 Carrau Sept. 18, 1956

Claims

1. MISSILE LAUNCHING APPARTUS COMPRISING, A LAUNCHING TOWER, A FIRST PULLEY MEANS ASSOCIATED WITH SAID LAUNCHING TOWER, A SECOND PULLEY MEANS ASSOCIATED WITH SAID LAUNCHING TOWER, FIRST CLOSED LOOP CABLE MEANS OPERATIVELY CONNECTING SAID FIRST AND SECOND PULLEY MEANS, MEANS ASSOCIATED WITH SAID FIRST CLOSED LOOP CABLE MEANS ADAPTED TO IMPART A FORCE TO THE MISSILE TO BE LAUNCHED, A THIRD PULLEY MEANS ASSOCIATED WITH SAID LAUNCHING TOWER, A FORCE TOWER, FORCE DEVELOPING MEANS MOVABLY ASSOCITED WITH SAID FORCE TOWER, SECOND CABLE MEANS CONNECTED TO SAID FORCE DEVELOPING MEANS MOVABLY ASSOCIATED WITH FOURTH PULLEY MEANS FOR RAISING SAID FORCE DEVELOPING MEANS RELATIVE TO SAID FORCE TOWER, MEANS FOR RELEASING THE KINETIC ENERGY OF SAID MOVABLE MEANS AS IT APPROACHES THE LOWER END OF ITS PATH OF MOTION, SAID SECOND CABLE MEANS BEING OPERATIVELY ASSOCIATED WITH SAID THIRD PULLEY MEANS AND SAID SECOND PULLEY MEANS SO AS TO TRANSMIT FORCES DEVELOPED BY SAID FORCE DEVELOPING MEANS TO SAID MEANS ASSOCIATED WITH SAID FIRST CLOSED LOOP CABLE MEANS.