US3199406A - In-line launching - Google Patents
In-line launching Download PDFInfo
- Publication number
- US3199406A US3199406A US118684A US11868461A US3199406A US 3199406 A US3199406 A US 3199406A US 118684 A US118684 A US 118684A US 11868461 A US11868461 A US 11868461A US 3199406 A US3199406 A US 3199406A
- Authority
- US
- United States
- Prior art keywords
- rocket
- launching
- rockets
- miniature
- tube
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Lifetime
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B5/00—Cartridge ammunition, e.g. separately-loaded propellant charges
- F42B5/02—Cartridges, i.e. cases with charge and missile
- F42B5/03—Cartridges, i.e. cases with charge and missile containing more than one missile
- F42B5/035—Cartridges, i.e. cases with charge and missile containing more than one missile the cartridge or barrel assembly having a plurality of axially stacked projectiles each having a separate propellant charge
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41A—FUNCTIONAL FEATURES OR DETAILS COMMON TO BOTH SMALLARMS AND ORDNANCE, e.g. CANNONS; MOUNTINGS FOR SMALLARMS OR ORDNANCE
- F41A9/00—Feeding or loading of ammunition; Magazines; Guiding means for the extracting of cartridges
- F41A9/61—Magazines
- F41A9/64—Magazines for unbelted ammunition
- F41A9/72—Tubular magazines, i.e. magazines containing the ammunition in lengthwise tandem sequence
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
- F41F3/00—Rocket or torpedo launchers
- F41F3/04—Rocket or torpedo launchers for rockets
- F41F3/042—Rocket or torpedo launchers for rockets the launching apparatus being used also as a transport container for the rocket
Definitions
- This invention relates to a method and apparatus for launching miniature rockets.
- Rockets of major dimensions are launched singly by means 4of aiming tubes, guiding rails, or launching carriages.
- the miniature rockets to which this invention relates are extremely small in size wherein the rocket has a diameter of Iabout 1.5 to 3 millimeters and a length of 8 to 35 millimeters.
- Individual rails or carriages for launching said miniature rockets would be impractical, lparticularly in conguration Where a plurality of miniature rockets are launched simultaneously or in rapid sequence.
- the launching apparatus hold said miniature rockets with an exact degree of security wherein the rocket may be transported safely to its place or use, and further to insure that full ignition and steady burning of the propellant has been effected before releasing said rocket for llight.
- FIGURE 1 is an enlarged view of miniature rockets mounted in a launching tube, showing a section View of one of said rockets.
- ⁇ FIGURE 2 is an enlarged front View showing the holding method.
- FIG. 3 is an enlarged front View of an alternative holding method.
- the launching tube 1 contains spacing tubes 2 to separate the holding diaphragms 3.
- the rocket shells 4 are supported concentrically within the tubes by the outer eid-ges of their rectangular tins 5. Flame from the nozzle of the preceding miniature rocket ignite-s the external bead of fuze material 6. Flame is conducted by additional fuze material through the tube 7 to ignite the thermite bead 8.
- Suitable fuze materials are pyrotechnics such Ias Sb2S3 and Ba(NO3)2, boron and KNO3, aluminum and KC104, lead mononitroresorcinate and KClOS mixed with a small amount of binder of plastic or nitrocellulose.
- the tubing may be nylon, polyethylene, or polyvinyl plastic or of metal, such yas hypodermic tubing.
- Burning of the thermite ignites the propellant grain 9, and melts the inner end of the tube 7 shut to form a gas-tight seal.
- the first miniature rocket in each tube must be ignited externally from a fuze or electric bridge Wire 10.
- a mounted miniature rocket is seen from the front, projecting through the holding diaphragm 3.
- Said diaphragm is constructed of material of low shear strength such as onion-skin paper.
- the rocket Upon ignition, the rocket must reach sufficient impulse to cut through the diaphragm 3 with its tins 5, insuring that the propellant is fully ignited and has reached a steady burning state before the rocket takes off.
- FIGURE 3 shows an alternate method of mounting miniature rockets 4 in launching tubes 1.
- the ltins 5 are slightly larger than the tube diameter and have been bent clockwise to allow the rocket to enter.
- the friction caused Iby the spring-like pressure of the bent tins holds the rocket securely for transportation and allows it to launch only after the propellant is fully ignited.
- three fins are illustrated, a langer number might be used.
- a rocket launching and ignition device comprising in combination an elongated tube, a plurality of rockets Within said tube including at le'ast a foremost rocket and ⁇ a second rocket immediately behind said foremost rocket, each of said rockets having a propellant grain with a central burning port running the length thereof, means for igniting the foremost rocket in the tube, and a pyrotechnic fuse in the nose of the second rocket said fuse protruding beyond the nose of said second rocket, passing through the nose .and terminating inside the rocket, whereby the nozzle blast from the foremost rocket will ignite the fuse and thus cause ignition of the second rocket.
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Measuring Volume Flow (AREA)
Description
Aug. 10, 1965 B. B. GouLD IN-LINE LAUNCHING- Filed June 21. 1961 INVEN TOR.' 55er 5. 600m United States Patent O 3,199,406 IN-LINE LAUNCHING Bert B. Gould, Berkeley, Calif., assigner, by mesne assignments, to MB Associates, San Ramon, Calif. Filed .lune 21, 1961, Ser. No. 118,684 1 Claim. (Cl. Sti-1.7)
This invention relates to a method and apparatus for launching miniature rockets.
Rockets of major dimensions are launched singly by means 4of aiming tubes, guiding rails, or launching carriages. The miniature rockets to which this invention relates are extremely small in size wherein the rocket has a diameter of Iabout 1.5 to 3 millimeters and a length of 8 to 35 millimeters. Individual rails or carriages for launching said miniature rockets would be impractical, lparticularly in conguration Where a plurality of miniature rockets are launched simultaneously or in rapid sequence. Further, it is desirable that the launching apparatus hold said miniature rockets with an exact degree of security wherein the rocket may be transported safely to its place or use, and further to insure that full ignition and steady burning of the propellant has been effected before releasing said rocket for llight.
According to the present invention, it has been found that a plurality of such miniature rockets can be launched in sequence from a single tube.
In the drawings forming part of this application:
FIGURE 1 is an enlarged view of miniature rockets mounted in a launching tube, showing a section View of one of said rockets.
`FIGURE 2 is an enlarged front View showing the holding method.
-FIGUR'E 3 is an enlarged front View of an alternative holding method.
Turning now to a description of the drawings by reference characters, in FIGURE 1 the launching tube 1 contains spacing tubes 2 to separate the holding diaphragms 3. The rocket shells 4 are supported concentrically within the tubes by the outer eid-ges of their rectangular tins 5. Flame from the nozzle of the preceding miniature rocket ignite-s the external bead of fuze material 6. Flame is conducted by additional fuze material through the tube 7 to ignite the thermite bead 8. Suitable fuze materials are pyrotechnics such Ias Sb2S3 and Ba(NO3)2, boron and KNO3, aluminum and KC104, lead mononitroresorcinate and KClOS mixed with a small amount of binder of plastic or nitrocellulose. The tubing may be nylon, polyethylene, or polyvinyl plastic or of metal, such yas hypodermic tubing. Thermite material such as aluminum and Fe2O3, or aluminum and =Fe304, may be used alone with a binder or mixed With one of the said pyrotechnics.
ice
Burning of the thermite ignites the propellant grain 9, and melts the inner end of the tube 7 shut to form a gas-tight seal.
The first miniature rocket in each tube must be ignited externally from a fuze or electric bridge Wire 10.
In .FIGUREl 2 a mounted miniature rocket is seen from the front, projecting through the holding diaphragm 3. Said diaphragm is constructed of material of low shear strength such as onion-skin paper. Upon ignition, the rocket must reach sufficient impulse to cut through the diaphragm 3 with its tins 5, insuring that the propellant is fully ignited and has reached a steady burning state before the rocket takes off.
FIGURE 3 shows an alternate method of mounting miniature rockets 4 in launching tubes 1. In this view the ltins 5 are slightly larger than the tube diameter and have been bent clockwise to allow the rocket to enter. The friction caused Iby the spring-like pressure of the bent tins holds the rocket securely for transportation and allows it to launch only after the propellant is fully ignited. Although three fins are illustrated, a langer number might be used.
I claim:
A rocket launching and ignition device comprising in combination an elongated tube, a plurality of rockets Within said tube including at le'ast a foremost rocket and `a second rocket immediately behind said foremost rocket, each of said rockets having a propellant grain with a central burning port running the length thereof, means for igniting the foremost rocket in the tube, and a pyrotechnic fuse in the nose of the second rocket said fuse protruding beyond the nose of said second rocket, passing through the nose .and terminating inside the rocket, whereby the nozzle blast from the foremost rocket will ignite the fuse and thus cause ignition of the second rocket.
References Cited by the Examiner UNITED STATES PATENTS 412,670 10/89 Ross 102-49 694,674 3/ 02 Scott 102-38 863,514 8/07 Del Grande 10233 1,288,883 12/ 18 Harvey 102-51 2,114,214 4/ 38 Damblanc 102-345 2,313,030 3/43 Tauschek 102-49 X `2,870,7.11 1/59 Barr et al. 102-50 2,930,288 3/-60 Jonah 89-1.7 I2,938,430 5/60 Pion 89-1.7
BENJAMIN A. BORCHELT, Primary Examiner.
ARTHUR M. HORTON, SAMUEL BOYD,
Examiners.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US118684A US3199406A (en) | 1961-06-21 | 1961-06-21 | In-line launching |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US118684A US3199406A (en) | 1961-06-21 | 1961-06-21 | In-line launching |
Publications (1)
Publication Number | Publication Date |
---|---|
US3199406A true US3199406A (en) | 1965-08-10 |
Family
ID=22380120
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US118684A Expired - Lifetime US3199406A (en) | 1961-06-21 | 1961-06-21 | In-line launching |
Country Status (1)
Country | Link |
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US (1) | US3199406A (en) |
Cited By (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3277825A (en) * | 1963-11-07 | 1966-10-11 | Brevets Aero Mecaniques | Self-propelled armor-piercing shells |
US3342104A (en) * | 1964-10-22 | 1967-09-19 | Robert Roger Aime | Guide tube magazine for carrying and launching airplane rocket-bombs |
US3348452A (en) * | 1965-03-03 | 1967-10-24 | Mb Assoc | Miniature rocket defense system |
US3486451A (en) * | 1967-12-26 | 1969-12-30 | Alvin E Moore | Electrically-fired missile |
US5245927A (en) * | 1992-04-28 | 1993-09-21 | Northrop Corporation | Dual-tandem unmanned air vehicle system |
US6659012B1 (en) * | 1999-03-08 | 2003-12-09 | Buck Neue Technologien Gmbh | Ejection device for ejecting a plurality of submunitions and associated discharging unit |
US20060016360A1 (en) * | 2003-10-03 | 2006-01-26 | Giat Industries | Anti-bunker ammunition |
Citations (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US412670A (en) * | 1889-10-08 | Projectile | ||
US694674A (en) * | 1899-08-08 | 1902-03-04 | Louis N D Williams | Firing multishot guns. |
US863514A (en) * | 1907-01-03 | 1907-08-13 | Nicholas Del Grande | Fire-cracker. |
US1288883A (en) * | 1918-06-24 | 1918-12-24 | Louis B Harvey | Projectile. |
US2114214A (en) * | 1935-03-09 | 1938-04-12 | Damblane Louis | Self-propelling projectile |
US2313030A (en) * | 1937-10-22 | 1943-03-02 | Tauschek Gustav | Firearm and ammunition therefor |
US2870711A (en) * | 1953-05-14 | 1959-01-27 | Aircraft Armaments Inc | Projectile carrying vehicle |
US2930288A (en) * | 1955-05-09 | 1960-03-29 | Chance Vought Aircraft Inc | Tandem rocket launcher and firing system |
US2938430A (en) * | 1954-05-17 | 1960-05-31 | North American Aviation Inc | Screw retained spin rocket |
-
1961
- 1961-06-21 US US118684A patent/US3199406A/en not_active Expired - Lifetime
Patent Citations (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US412670A (en) * | 1889-10-08 | Projectile | ||
US694674A (en) * | 1899-08-08 | 1902-03-04 | Louis N D Williams | Firing multishot guns. |
US863514A (en) * | 1907-01-03 | 1907-08-13 | Nicholas Del Grande | Fire-cracker. |
US1288883A (en) * | 1918-06-24 | 1918-12-24 | Louis B Harvey | Projectile. |
US2114214A (en) * | 1935-03-09 | 1938-04-12 | Damblane Louis | Self-propelling projectile |
US2313030A (en) * | 1937-10-22 | 1943-03-02 | Tauschek Gustav | Firearm and ammunition therefor |
US2870711A (en) * | 1953-05-14 | 1959-01-27 | Aircraft Armaments Inc | Projectile carrying vehicle |
US2938430A (en) * | 1954-05-17 | 1960-05-31 | North American Aviation Inc | Screw retained spin rocket |
US2930288A (en) * | 1955-05-09 | 1960-03-29 | Chance Vought Aircraft Inc | Tandem rocket launcher and firing system |
Cited By (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3277825A (en) * | 1963-11-07 | 1966-10-11 | Brevets Aero Mecaniques | Self-propelled armor-piercing shells |
US3342104A (en) * | 1964-10-22 | 1967-09-19 | Robert Roger Aime | Guide tube magazine for carrying and launching airplane rocket-bombs |
US3348452A (en) * | 1965-03-03 | 1967-10-24 | Mb Assoc | Miniature rocket defense system |
US3486451A (en) * | 1967-12-26 | 1969-12-30 | Alvin E Moore | Electrically-fired missile |
US5245927A (en) * | 1992-04-28 | 1993-09-21 | Northrop Corporation | Dual-tandem unmanned air vehicle system |
US6659012B1 (en) * | 1999-03-08 | 2003-12-09 | Buck Neue Technologien Gmbh | Ejection device for ejecting a plurality of submunitions and associated discharging unit |
US20060016360A1 (en) * | 2003-10-03 | 2006-01-26 | Giat Industries | Anti-bunker ammunition |
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