US3421410A

US3421410A - Missile and hand held launcher

Info

Publication number: US3421410A
Application number: US663344A
Authority: US
Inventors: George Kayaian
Original assignee: Individual
Current assignee: Individual
Priority date: 1967-08-25
Filing date: 1967-08-25
Publication date: 1969-01-14
Anticipated expiration: 1986-01-14

Description

1969 e. KAYAIAN MISSILE AND HAND HELD LAUNCHER Sheet of 2 Filed Aug. 25. 1967 INVENTOR. GEO/2'65 KAYAIAN BY W17. aw,

AGENT.

Jan. 14, 1969 G y MISSILE AND HAND HELD LAUNCHER Sheet Filed Aug. 25, 1967 INVENT OR. GEORGE KAYA/AN AGE/V71,

United States Patent 3 Claims ABSTRACT OF THE DISCLOSURE This invention is a hand held, tube launched, two-stage projectile adapted to be fired initially by exploding a cartridge which propels the projectile out of the launching tube and ignites the main propellant in the projectile a safe distance from the launching location.

This invention relates generally to weapons and more particularly to a novel two-stage rocket and launcher.

Heretofore, hand held rocket launchers were generally of the single stage type, i.e. an initial firing launched the missile toward its intended target. The launcher or tube usually required a one man support and aim plus a second man for loading. Aiming of the launcher was limited to a substantially fiat trajectory in that the missile gravitationally rested within the tube in preparation for firing. When fired, the shock, recoil, or other physical effects associated with such weapons was generated to a maximum condition as the missile leaves the launch tube. These effects limited the size of the firing charge in the missile and accordingly limited the distance that the missile traveled to its target.

The present invention employs a novel two-stage firing system that initially produces minor physical effects upon firing the first stage to propel the missile out of the launch tube and automatically ignites and fires the second stage when the missile is a safe distance from the launcher.

Accordingly, one of the principal objects of the invention resides in the provision of a launcher type rocket missile having a primary propellant that when ignited ejects the missile from the launcher a predetermined distance and then automatically ignites the secondary propellant which propels the missile to its target.

Another object of the invention is to provide in a rocket type launcher means to secure the missile in firing position within the launch tube so that the firing angle of the tube may be selectively varied without regard to accidental gravitational ejection of the missile.

Still another object of the invention is to provide a means to automatically release said securing means upon the firing of the initial stage of the missile to permit normal egress of the missile from the tube.

Yet another object of the invention is to provide a second stage ignition system that is ignited by the initial first stage firing system a predetermined period of time after said first stage is ignited and the missile has traveled out of the launch tube.

Other ancillary objects will be in part hereinafter apparent and will be in part hereinafter pointed out.

In the drawings:

FIGURE 1 is a side elevation of the rocket type missile with a portion cut away to illustrate the first stage propellant system.

FIGURE 2 is an enlarged cross-sectional detail of the first stage in its static or pre-firing position.

FIGURE 3 is an enlarged cross-sectional detail of the first stage in its fired position and prior to the ignition of the second stage propellant charge.

FIGURE 4 is a perspective view taken from the rear of the missile with a portion cut away to more fully disclose the latching means that secures the missile within the launch tube; and

FIGURE 5 is a rear view of the missile with the arrows representing the thrust gasses.

Referring to FIGURE 2 of the drawing in detail, 20 generally designates the launch tube having a through there 22, a reduced diametrical portion 24 which forms an annular shoulder 26. Launch tube 20 is conventional and need not be described in detail. Such tubes are well known to those skilled in the art. It is suificient to state that the tube 20 has a front orifice, not shown, through which the missile 30 will eject, as will be hereinafter described.

Conversely, launch tube 20 has an enlarged diametrical portion 28 of bore 22 adjacent to shoulder 26 that secures the missile 30 thereagainst when the missile 30 is loaded in the launch tube 20 for a purpose hereinafter appearing.

Referring to FIGURES 1, 2, 3, 4, and 5, the missile 30, per se, comprises a cylindrical device having guidance fins 32 and 34. The diametrical dimensions between opposite fins 32-34 is substantially the same as the internal diameter of section 24 of bore 22.

Missile 30 comprises an initial firing section 36, a first propulsion section 38, a main propulsion section 40 and a conventional war head 42 with an impact fuse 44. Such fuses and war heads are conventional and well known to those skilled in the art and need not be described in detail herein.

The section 36 comprises a conventional blank cartridge 46 disposed within a chamber 48 formed in a cylindrical block 50 that is centrally secured in radial member 52. Member 52 is threadedly secured to the inner periphery 50 of missile 30. It will be noted that a thrust chamber 56 surrounds the radial member 52 for purposes hereinafter appearing. Aflixed to block 50, FIG- URE 2, is a hollow tube 58 of similar diameter having a rear orifice 60 communicating with chamber 48, a forward orifice 62 centrally located in the front wall 58a of tube 58, and a pair of diametrically disposed exhaust ports 58b. Disposed within tube 58 is .a hollow plunger 64 open at its rearmost end and secured to a fuse member 66 at its closed forward end. Fuse member 66 projects through orifice 62 in tube 58. Disposed within tube 58 and circumjacently disposed around fuse member 66 is a spring 70, normally urging plunger 64 rearwardly, such as shown in FIGURE 2.

When cartridge 46 is fired by conventional electrical means 72, the charge in cartridge 46 ignites and the gasses produced thereby enter plunger 64 and drive said plunger forwardly, thus compressing spring 70, and driving fuse member 66 forwardly to engage said fuse member with main propulsion section 40, as will be hereinafter apparent. Concurrently with the forward movement of plunger 64, latching means 74 releases missile 30 from its secured position within launch tube 20. Latching means 74 comprise a pair of diametrically opposed pins 76 that radially extend through radial member 52 and one pair of the rearmost fins 34. Pins 76 are urged inwardly by springs 78 and are retained in their radially extended positions by their engagement with the outer periphery of plunger 64 in its initial dormant position. With pins 76 in their most extended position, said pins engage shoulder 26 of launch tube 20 and secure the missile 30 in the launch tube.

When the cartridge 46 is fired and plunger 64 moves forwardly, springs 78 urge pins 76 radially inwardly releasing missile 30 from latched position within launch tube 20.

As previously set forth, the expanding gases generated by the exploding cartridge 46 drives plunger 64 forwardly 3 to the position shown in FIGURE 3 which exposes the exhaust ports 58b to the expanding gases. Further, as previously described, pins 76 are released from shoulder 26. Consequently, the released gases eject through thrust chamber 56 which thrusts the missile 30- from launch tube 20.

When plunger 64 moved forwardly, the heat generated by the gases of the exploding cartridge 46 ignited the fuse member 66- which was further driven into the main propulsion charge 40. Thus, after the missile 30 has ejected from the launch tube 20' a safe distance, the fuse member 66 ignites the main charge of propulsion section 40 which propels the missile 30 towards its intended target. The wall 80 of charge 40 being exposed to thrust chamber'56' burns away and provides the thrust required to propel the missile after the initial thrust provided by the cartridge 46 has dissipated.

It will be noted that the latching pins 76 permit launch tube 20 to be aimed at any desired angle of trajectory without accidental dislodging of the missile.

While there has been shown and described but a single embodiment of the invention, it will be understood that changes and modifications could be made without departing from the scope of the invention as set forth in the following claims.

The invention claimed is:

1. A missile adapted to be fired from a manually held launch tube comprising:

(a) an initial firing means adapted, when fired, to propel the missile a safe predetermined distance from the launch tube,

(b) a main propellant adapted to be ignited when said missile has traveled the predetermined distance from the launch tube,

(c) latching means to secure the missile in the launch tube prior to the initial firing to permit the launch tube to be aimed in any desired missile trajectory.

(d) said latching means comprises a pair of diametrically opposed pins radially extending from the missile adapted to engage the inner periphery of the launch tube,

(e) means to release said latching means upon the firing of the initial firing means,

(f) a plunger movable by the gasses generated by said initial firing means adapted to engage and retain said diametrically opposed pins in their respective radially extended position,

(g) spring means to urge said pins inwardly toward each other when said plunger has moved, upon the firing of the initial firing means,

(11) and main propellant igniting means carried by said plunger and adapted to engage said main propellant upon movement of said plunger.

2. A missile adapted to be fired from a manually held launch tube comprising:

(f) a plunger 'rnovable by the gasses generated by said initial firing means adapted to engage and retain said diametrically opposed pins in their respective radially extended position,

(h) main propellant igniting means carried by said plunger and adapted to engage said main propellant upon movement of said plunger,

(i) spring means normally retaining said plunger in its normal pin engaging position,

(j) and said spring means being compressible by the moving plunger when said plunger is moved by the gasses produced by the fired initial firing means.

3. A'missile adapted to be fired from a manually held launch tube comprising:

(b) a main propellant adapted to be ignited when said missile has traveled the predetermined distance from the launch tube, and

(j) said spring means being compressible by the moving plunger when said plunger is moved by the gasses produced by the fired initial firing means,

(k) fuse means carried by said plunger adapted to be ignited by the gasses generated by the firing of the initial firi-ng means,

(1) and said fuse means being adapted to engage the main propellant and ignite said main propellant.

References Cited UNITED STATES PATENTS 2,788,712 4/1957 Ku-ller et al. 89-1.807 2,944,486 7/1960 Vasse 10249.1 3,112,670 12/1963 Litz 89-l1.011 3,139,795 7/1964 Altschuler 89-1.818 3,282,161 11/1966 Mac-Donald et al. 89l.818

SAMUEL W. ENGLE, Primary Examiner.

US. Cl. X.R.