US2922367A

US2922367A - Missile with trajectory affecting means

Info

Publication number: US2922367A
Application number: US669375A
Authority: US
Inventors: Dunzer Werner
Original assignee: Individual
Current assignee: Individual
Priority date: 1957-07-01
Filing date: 1957-07-01
Publication date: 1960-01-26
Anticipated expiration: 1977-01-26

Description

Jan. 26, 1960 w. DUNZER MISSILE wmx TRAJECTORY AFFECTING MEANS 2 Shets-Sheet 1 Filed July 1, 1957 Invmvr:

Jan. 26, 1960 w. DUNZER 2,922,367

MISSILE WITH TRAJECTORY AFFECTING MEANS Filed July 1, 1957 2 Sheets-Sheet 2 MISSILE TRAIECTURY AFFECTING MEANS Werner Dunzer, Ilanz, Switzerland Application July 1, 1957, Serial No. 669,375

3 Claims. (Cl. 102-64) The present invention relates to missiles.

More particularly, the present invention relates to a missile the direction of travel of which may be changed after the missile has been launched.

There exist various types of missiles which can be manually thrown or otherwise launched so as to travel along a certain trajectory. It has been found desirable, however, particularly in the case of hand grenades for use as a weapon of destruction in infantry combat, to provide a missile the trajectory of which may be changed after the missile has been launched. in this way, the missile can be used to destroy targets which cannot be reached by a missile the trajectory of which cannot be altered after it has been launched.

It is therefore an object of the present invention to provide a missile which will change its direction of travel after it has been thrown or otherwise launched.

It is another object of the present invention to provide a missile which can be deflected from an original trajectory by any desired amount.

The objects of the present invention also include the provision of various of types of missiles, such as bombshaped, bullet-shaped, rocket-shaped projectiles, etc., as well as a hand grenade type missile which are equipped with a mechanism for altering their direction of travel after they have been launched.

It is a still further object of the present invention to provide a hand grenade type missile which is capable of being deflected from its original trajectory after a certain predetermined time interval has elapsed.

It is yet another object of the present invention to provide a hand grenade type missile which is provided with a manually operable time delay device that can be held in an off position before the missile is thrown but which automatically moves to an on position as soon as the missile is released, and causes the missile to alter its direction of travel a predetermined time interval following its launching.

It is an additional object of the present invention to provide a missile which can easily be mass-produced at very low cost.

With the above objects in View, the present invention mainly consists in a missile which comprises a missile body adapted to be projected along a trajectory and propelling means on the missile body for propelling the same in a direction different from this trajectory while the missile body travels therealong, thereby causing the missile to continue traveling in this different direction.

According to one embodiment of the present invention the propelling means include a propulsive charge, detonator means for detonating this propulsive charge, and time delay means operatively associated with the detonator means for determining the instant at which the same detonates the propulsive'charge. In this way the time interval between the commencement of the travel v.of the missile body along its initial trajectory and the instant at which the detonator means detonates the pro- 2,922,36? Patented Jan. 26, 196i) 'ice pulsive charge, thereby propelling the missile body in this different direction, is determined.

The novel features which are considered as characteristic for the invention are set forth in particular in the appended claims. The invention itself, however, both as to its construction and its method of operation, together with additional objects and advantages thereof, will be best understood from the following description of specific embodiments when read in connection with the accompanying drawings, in which:

Fig. 1 is a sectional view of one embodiment of a missile according to the present invention taken on line II of Fig. 2;

Fig. 2 is a side view of the missile shown in Fig. 1 as seen from the left;

Fig. 3 is a side view of the other side of the missile shown in Fig. 1;

Fig. 4 is a fragmentary sectional view similar to Fig. 1 but showing certain structural details of a missile carrying an explosive charge; and

Figs. 5, 6 and 7 show differently shaped missiles in corporating propelling means according to the present invention.

Referring now to the drawings, and to Figs. 1 to 3 thereof in particular, there is shown a missile adapted to be manually projected. The missile comprises a substantially disk-shaped missile body 1 which is flattened at 2, 3 and 4 and has a handle portion 6 formed with two opposite recesses 5. Each recess is so shaped as to be adapted to receive the thumb or fingers of a hand so that the thrower may grip the missile and project the same along a trajectory.

The missile body is formed with an axial bore 7, within which a cup 11 is turnably arranged. The cup contains a propulsive charge 9 and a priming or detonator mechanism shown diagrammatically at 10. The latter, in turn, is operatively associated with a time delay mechanism shown generally at 8. As will be more fully set forth below, the cup cooperates with the time delay mechanism in such a manner that by turning the cup within the bore 7 the time interval between activation of the time delay mechanism and the explosion of the propulsive charge 9 may be adjusted. For this purpose, the cup carries an index mark 12 which cooperates with a number of radially spaced

stationary indexing marks

13, 14, 15 on the face of the missile body 1.

The time delay mechanism includes a handle 16 which is connected for movement between an off position, shown in solid lines in Fig. 1, wherein the arcuate gripping portion of the handle is within one of the recesses 5 and wherein the time delay mechanism is inoperative, and an on position, shown in dotted lines, wherein the gripping portion is spaced from the missile body 1 and the time delay mechanism is operative. The handle is continuously urged to its on position by a suitable spring (not shown in Fig. 1) so that the handle 16, which, prior to launching of the missile may be manually held in its off position by the hand holding the missile, will automatically be moved to its on position upon launchmg.

It will be seen from the above that if the missile is traveling along a certain trajectory while in an attitude wherein the axis of the missile body is transverse to the trajectory, explosion of the propulsive charge 9 will cause the missile to continue traveling in a direction which is at right angles to the original trajectory. With the arrangement of the propulsive charge as shown in Fig. 1, the missile will be propelled by the charge in the direction of the arrow A. Also, it will be seen that by 0 asymmetrically packing the cup 11 with an explosive charge, the direction in which the missile is propelled .ries a setting element or arm 34'.

will. form an angle other than 90 with the original trajectory. In practice, this angle may vary from near zero to 180.

Thus, by pre-setting the time delay mechanism to any desired value, which is accomplished by turning the cup 11 untilthe index' mark 12 is in registration with the appropriate stationary index mark, the time interval between the launching of the missile and the instant at which it is propelled in a different direction may be selected.

The above-described missile may be used as a toy in that no damage is inflicted by the missile upon the target which it strikes. It is possible however, to provide an explosive charge so that the missile may be used as a combat weapon of the hand grenade type. Such an arrangement is shown in Fig. 4 wherein the missile body is hollow and contains an explosive charge 39. Additionally, Fig. 4*shows the structural details of a time delay mechanism incorporated in one embodiment of the present invention. In this embodiment the handle 16 is pivotally mounted on a hub 17 which is turnably mounted on a stud 18. A suitable retaining disk 19 is provided which is welded or soldered onto .the stud 18 at 20 so as to prevent axial movement of the hub 17 relative to the stud.

A clock work 21 which is provided with a spring housing 22 serves to set a gear train 23 in motion. A spindle 25 which is rotatably mounted within the time delay mechanism housing 24 carries an eccentric cam member 26 which, when the spindle 25 is rotated, serves to actuate a switch '27. The latter lies in an electric circuit which includes a battery 28 and an ignition element 29, which ignition element is capable of igniting and detonating the propulsive charge 9.

A spring-loaded plunger 31 is provided for preventing movement of the gear train 23. This plunger is adapted to engage one of the gears of the gear train 23 and is formed with a collar 31', and a spring serves to bias the plunger into a position in which it is out of engagement with the gear in question. The plunger is slidably mounted and extendstthrough an opening 32 and is engaged by the handle 16. Consequently, when the handle is pressed toward the missile body 1 into its off position, the plunger 31 will be in engagement with the gear, thereby preventing rotation thereof. When the handle 16 is released, the plunger 31 will, under the influence of the spring 30, move out of engagement with gear, thereby freeing the gear train and activating the time delay mechanism.

The mechanism constituted by'the clock work 21 and gear train 23 is provided with a regulator 34 which car- The latter is adapted to cooperate with a positioning element 33 which is fixedly connected to the cup. 11 so that when this cup is rotated relative to the missile body, the positioning element 33 engages. the setting element 34 so as to turn the same. Inv this way, the starting position of the cam member 26 will be pre-set and this, in turn, determines the time interval which will elapse between the commencement of operation of the time delay mechanism and the closing of the switch 27. Thus, the time interval between the release of the handle 16 and the detonation of the propulsive charge 9 may bep're-adjusted.

If desired, the regulator may be provided 'with fan blades (not shown) so that it will act as a dynamic damping device which controls the operating speed of the gear train 23. The fan blades may be deformed to any desired configuration so that the operating speed of the gear train 23 can be pro-selected.

It will be seen from the above that when the cup 11 is filled with a propulsive charge, the latter may be detonated at a desired instant following launching of the missile. This may beaccomplished by turning the cup until the proper time interval is. indicatedQand by winding the clock work '21. To this end, the stud 1-8 is formed at its free end with a suitable slot 40 adapted to ings 36 and 38 has burned.

4 receive a screw driver or the like, thereby enabling the stud 18 to be turned until the clock work 21 is fully wound. The missile may then be thrown or otherwise caused to travel along its trajectory. Upon release of the missile, the handle 16 will be free to move to its on position and it will do so under the influence of the spring 30. The plunger 31 will thereupon move out of engagement with the gear which it previously blocked, and the clock work 21 will then be free to rotate the gear train 23 until the cam 26 closes the switch 27 This, in turn, will cause the ignition device 29 to detonate the propulsive charge 9.

As set forth above, the missile shown in Fig. 4 is adapted to be used as a weapon of destruction. To this end a detonating charge 10 may be arranged in a detonating chamber formed between the bottom cross wall of the time delay mechanism housing 24 and a cross wall 37a which is immediately adjacent the bottom cross wall of the cup 11. The cross wall 37a is formed with an opening 36 and the bottom of the cup is formed with an arcuate 'slot 35 so that interior of the cup and the detonating chamber will at all times be in communication with each other, irrespective of the angular position of the cup 11 relative to the missile body 1. The latter, in turn, is formed with an opening 38 which places the detonating chamber in communication with the space occupied by the explosive charge 39. Consequently, when the propulsive charge is detonated by the ignition device 29, the'charge 10 will be ignited and this, in turn, will detonate the explosive charge 39 as soon as that portion of the charge 10 between the open- In this way, the explosive charge will be detonated a certain time after detonation of the propulsive charge has altered the direction of travel of the missile.

Alternatively, entirely independent time delay means may be provided for exploding the explosive charge, or, if desired, a suitable percussion fuse may be provided for exploding the explosive charge upon impact of the missile with the target. In such an arrangement a suitable interlock may be provided for making the missile a live one only upon release of the handle 16.

It has also been found that instead of a clock actuated detonating device the projectile or centrifugal motion of the missile may be relied upon to detonate the propulsive charge at the proper instant. Alternatively, chemical or thermal means may be provided. Moreover, it is not essential that the propelling force be obtained by an explosive in that the propulsive charge may be in the form of a gas under pressure which is exhausted at the proper instant.

Figs. 5 to 7 show bomb-shaped, bullet-shaped and rocket-shaped projectiles, respectively, the direction of travel of which may be altered after launching. In each of these figures the time delay mechanism are indicated at 8, the propulsive charges at 9 and the detonating means at 10, so that upon detonation each propulsive charge will seek to expand in the direction of the short arrows thereby causing the missile to move in the opposite direction, as shown by the longer arrows.

It will be understood that each of the elements described above, or two or more together, may also find a useful application in other types of missiles difiering from the types described above.

While the invention has been illustrated and described as embodied in missiles incorporating a mechanical time delay mechanism, it is not intended to be limited to the details shown, since various modifications and structural changes may be made without departing in any way from the spirit of the present invention.

Without further analysis, the foregoing will so fully reveal the gist of the present invention that others can by applying current knowledge readily adapt it for various applications without omitting features that, from the standpoint of prior art, fairly constitute essential characteristics of the generic or specific aspects of this invention and, therefore, such adaptations should and are intended to be comprehended within the meaning and range of equivalence of the following claims.

What is claimed as new and desired to be secured by Letters Patent is:

1. A disk-shaped missile adapted to be projected in a trajectory substantially radial of said disk While rotating about an axis substantially perpendicular to said trajectory, said missile comprising a missile body; a propulsive charge arranged in said body and dischargeable therefrom in an axial direction for propelling said missile in a direction opposite to the direction of discharge of said propulsive charge and substantially perpendicular to said trajectory; first detonating means for detonating said propulsive charge; explosive means including an explosive charge and second detonating means for detonating the same; and time delay means operatively associated with said first and second detonating means for first activating said first detonating means and thereafter activating said second detonating means, whereby the time interval between the commencement of the travel of said missile along said trajectory and the instant at which said first detonator means detonates said propulsive charge, thereby propelling said missile in said substantially perpendicular direction is determined, and whereby also the time interval between the last-mentioned instant at the instant at which said second detonator means detonates said explosive charge is determined.

2. A disk-shaped missile adapted to be projected in a trajectory substantially radial of said disk while rotating about an axis substantially perpendicular to said trajectory, said missile comprising a missile body formed with an axially extending opening; a propulsive charge arranged in said body opening and dischargeable therefrom in an axial direction for propelling said missile in a direction opposite to the direction of discharge of said propulsive charge and substantially perpendicular to said trajectory; detonator means for detonating said propulsive charge; manually operable time delay means operatively associated with said detonator means for determining the instant at which the same detonates said propulsive charge; said time delay means including a setting element and adjusting means operatively associated with said time delay means for pre-setting the time interval between the commencement of travel of said missile body along said trajectory and the instant at which said detonator means detonates said propulsive charge, said adjusting means including a cup arranged in said axially extending opening and turnably mounted therein, said cup carrying a positioning element adapted to cooperate with said setting element for positioning the same in different positions depending upon the angular position of said cup, whereby said time delay means may be adjusted by turning said cup.

3. A missile as defined in claim 2 wherein said cup contains said propulsive charge.

References Cited in the file of this patent UNITED STATES PATENTS 1,102,732 Faber July 7, 1914 1,369,476 Semple Feb. 22, 1921 2,069,221 Coupland Feb. 2, 1937 2,203,640 Hines et al June 4, 1940 2,415,348 Haigney Feb. 4, 1947 FOREIGN PATENTS 301,603 Germany Sept. 23, 1920