US2206057A - Rocket projectile - Google Patents

Rocket projectile Download PDF

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Publication number
US2206057A
US2206057A US292841A US29284139A US2206057A US 2206057 A US2206057 A US 2206057A US 292841 A US292841 A US 292841A US 29284139 A US29284139 A US 29284139A US 2206057 A US2206057 A US 2206057A
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United States
Prior art keywords
body
tube
lining
rocket
melting point
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Expired - Lifetime
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US292841A
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Leslie A Skinner
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Leslie A Skinner
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    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F42AMMUNITION; BLASTING
    • F42BEXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
    • F42B15/00Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02KJET-PROPULSION PLANTS
    • F02K9/00Rocket- engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/80Rocket- engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof characterised by thrust or thrust vector control
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02KJET-PROPULSION PLANTS
    • F02K9/00Rocket- engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
    • F02K9/97Rocket nozzles
    • F02K9/974Nozzle- linings; Ablative coatings
    • YGENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10STECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10S60/00Power plants
    • Y10S60/909Reaction motor or component composed of specific material

Description

y 2, 1940- L. A. SKINNER 2,206,057

ROCKET PROJECTILE Filed Aug. 51, 1939 Fig] -1- L invenigi:

E A v I E 1; 598% l IT'LE r factured and used by or for Patented July 2, 1940 srArsS PATENT FFlC ,206,051 nocxa'r raomc'rrw Leslie A. Skinner, United Calll'., assignor to the Government of the United States Army, Berkeley,

A ppllcation August 31, 1939, Serial No. 292,841 a cam (01. 102-23) (Granted under the act of amended April 30, 1928;

The invention described herein may be manuthe Government for governmental purposes, without the payment to me of any royalty thereon.

This invention relates to a rocket projectile.

In a projectile of the type shown in my Patent 1,994,490'of March 19, 1935, an external propelling charge initiates the flight of the projectile and an auxiliary propelling charge carried by the projectile'iunctions during flight in the manner common to rockets to continue propulsion.

In pyrotechnic rockets employing black powder as a driving charge it has been customary to employ a discharge orifice of a fixed size which has a certain definite relation to the speed at which the gases are liberated in order that these gases should be forcibly expelled, thus lifting the rocket by their impact with the air.

Where the driving charge consists 'of a composition, such as nitrocellulose or a double base powder, having the characteristics of a requirement of pressure to initiate ignition and an increased burning rate under pressure, it becomes necessary to provide a means for regulating or controlling the pressure within the driving charge container.

The purpose of this invention is .to regulate the pressure and the velocity of efliux of the gases by means of an exhaust orifice which increases in cross-sectional area as the driving charge is consumed.

' The specific nature of other objects and advantages thereof will clearly appear from a description of a. preferred embodiment as shown in the accompanying drawing in which:

Fig. 1 is a view in side elevation in section of a rocket projectile.

Fig. 2 is a longitudinal sectional view of the discharge tube.

Referring to the drawing by characters of reference there is shown a projectile comprising a body 5 having a partition 8. The space in front of the partition is adapted to contain any desired element such as an explosive, signalling, or incendiary charge I or it may be used to house a parachute or carry a message. The space in rear of the partition contains a driving charge 8 which preferably consists of nitrocellulose or a double base powder which requires a certain amount of pressure to insure ignition and whose burning rate increases as the pressure increases.

A discharge tube 9 of a metal having a high melting point is attached to the rear of the body and partly the invention as well as,

March 3, 1883, as 370 0- G.

and is formed with a forwardly flared entrance In and a rearwardly flared exit passage ll to provide a constricted throat. The throat of the passage is further constricted by a lining I2 of a lowmelting point material such as Wood's metal, solder, Babbitt and the like. The lining which is similarly formed with a. forwardly flared entrance I; and a rearwardly flared passage i l, extends rearwardly an appreciable distance from the front edge of the entrance III of the tube. The thickest part of the lining which establishes the constricted throat I5 is positioned a relatively short distance from the front edge of the entrance lll, this distance being approximately equal to the radius of the tube and being substantially at the constricted throat of the tube.

The particular manner of igniting the driving charge forms no part of this invention but as an example it may be accomplished by conventional methods employed in rockets or as shown in the patent previously referred to. At the commencement of combustion of the driving charge the quantity of gas developed will be small but because the throat I5 is relatively small the pressure within the driving charge chamber will build up rapidly. when ignition is well established and the pressure increases, the outrushing hot gases will cause the lining to be melted and the molten metal will be forced rearwardly. In this manner the discharge criflce will be gradually enlarged until the predermined entrance IB and exit passage II is reached.

I claim:

1. A rocket comprising a body, a driving charge in the body, a tube fixed to the rear of the body, said tube formed of a metal having a high melting point and having a forwardly flared entrance and a rearwardly flared exit passage to provide a constricted throat, a lining of a low melting point metal in the tube with its thickest portion spaced from the front edge of the tube and having a forwardly flared entrance and a rearwardly flared passage to provide a constricted throat.-

, 2. A- rocket comprising a body, a. driving charge in the body, a tube 'of a high melting point metal flxed to the rear of the body, a lining of a low melting point metal in the tube, said lining having its thickest portion spaced from the front edge of the tube and having a forwardly flared entrance and a more gradual rearwardly flared passage to provide a constricted threat.

3. A rocket comprising a body, "a driving charge in the body, a tube of a high melting point metal flxed tothe rear of the body, a lining of a low melting point metal in the tube, said lining having its thickest portion spaced from the front edge 01 the tube and having a forwardly flared entrance and a rearwardly flared passage to provide' a. constricted throat.

4. A rocket comprising a body, a driving charge in the body, a tube ofahigh melting point metal fixed to the body, and a lining of a low melting point metal in the tube and having a constricted throat spaced from the front edge of the tube.

5. A rocket comprising a body, a driving charge in the body, a tube of a high melting point metal fixed to the body, and a lining'of a low melting point metal in the tube and having a constricted throat.

.6. A rocket comprising a body, a driving charge in the body, a tube of a high melting point metal fixed to the body and having a constricted throat spaced from the entrance end, and a lining of a low melting point metal in the tube and having a constricted throat in the throat-of thetube.

'7. A rocket comprising a body, a' driving charge in the body, a tube fixed to the body, and a lining in the tube removable by heat, said liner having asharply flared entrance and a gradually flared exit passage providing a constricted throat.

8. A rocket comprising a body, a driving charge in the body, a tubefixed to the body, and a lining in the tube removable by heat, said liner having a fiared'entrance and a flared exit passage providing a constricted throat...

' LESLIE A. SKINNER.

US292841A 1939-08-31 1939-08-31 Rocket projectile Expired - Lifetime US2206057A (en)

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Cited By (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2447200A (en) * 1943-09-03 1948-08-17 Aerojet Engineering Corp Exhaust nozzle for rocket motors
US2460289A (en) * 1945-03-16 1949-02-01 Clarence N Hickman Rocket projectile
US2596644A (en) * 1946-12-10 1952-05-13 Us Sec War Automatically detachable flashless nozzle for rockets
US2912820A (en) * 1953-07-31 1959-11-17 Quentin R Whitmore Combined ram jet and rocket engine
US2952972A (en) * 1957-09-09 1960-09-20 Norman A Kimmel Rocket motor and method of operating same
US2984972A (en) * 1958-05-28 1961-05-23 Gen Electric Variable area nozzle arrangement
US3032970A (en) * 1957-01-25 1962-05-08 Phillips Petroleum Co Disposable rocket motor
US3079752A (en) * 1961-02-23 1963-03-05 Thompson Ramo Wooldridge Inc Variable expansion ratio nozzle
US3080714A (en) * 1960-03-01 1963-03-12 Olin Mathieson Gas generating cartridge containing liquid propellant
US3134223A (en) * 1961-03-06 1964-05-26 Lockheed Aircraft Corp Tape shielded nozzle
US3137995A (en) * 1960-01-26 1964-06-23 Chemical Engineering Dept Ablation resistant reaction propulsion nozzle
US3235183A (en) * 1963-05-29 1966-02-15 United Aircraft Corp Ablation cooled rocket nozzle
US3237402A (en) * 1963-11-14 1966-03-01 Steverding Bernard Variable thrust nozzle
US3253403A (en) * 1962-05-24 1966-05-31 Kelsey Hayes Co Nozzle having ablative coating
US3300142A (en) * 1963-06-25 1967-01-24 Whittaker Corp Rocket nozzle capable of inducing flow separation
US3300975A (en) * 1955-06-13 1967-01-31 Garrett Corp Protective apparatus for a rocket motor
US3309874A (en) * 1965-02-04 1967-03-21 Bert B Gould Ablative nozzle
US3334485A (en) * 1962-07-26 1967-08-08 Barry V Rhodes Ramjet powered craft
US3468127A (en) * 1965-09-10 1969-09-23 Secr Defence Brit Rocket projectiles
US4102270A (en) * 1951-05-08 1978-07-25 Martin Marietta Corporation Disposable booster
FR2473630A1 (en) * 1979-11-30 1981-07-17 Messerschmitt Boelkow Blohm Tapering tube for reaction engines, particularly for stato-reactors of flanges

Cited By (21)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2447200A (en) * 1943-09-03 1948-08-17 Aerojet Engineering Corp Exhaust nozzle for rocket motors
US2460289A (en) * 1945-03-16 1949-02-01 Clarence N Hickman Rocket projectile
US2596644A (en) * 1946-12-10 1952-05-13 Us Sec War Automatically detachable flashless nozzle for rockets
US4102270A (en) * 1951-05-08 1978-07-25 Martin Marietta Corporation Disposable booster
US2912820A (en) * 1953-07-31 1959-11-17 Quentin R Whitmore Combined ram jet and rocket engine
US3300975A (en) * 1955-06-13 1967-01-31 Garrett Corp Protective apparatus for a rocket motor
US3032970A (en) * 1957-01-25 1962-05-08 Phillips Petroleum Co Disposable rocket motor
US2952972A (en) * 1957-09-09 1960-09-20 Norman A Kimmel Rocket motor and method of operating same
US2984972A (en) * 1958-05-28 1961-05-23 Gen Electric Variable area nozzle arrangement
US3137995A (en) * 1960-01-26 1964-06-23 Chemical Engineering Dept Ablation resistant reaction propulsion nozzle
US3080714A (en) * 1960-03-01 1963-03-12 Olin Mathieson Gas generating cartridge containing liquid propellant
US3079752A (en) * 1961-02-23 1963-03-05 Thompson Ramo Wooldridge Inc Variable expansion ratio nozzle
US3134223A (en) * 1961-03-06 1964-05-26 Lockheed Aircraft Corp Tape shielded nozzle
US3253403A (en) * 1962-05-24 1966-05-31 Kelsey Hayes Co Nozzle having ablative coating
US3334485A (en) * 1962-07-26 1967-08-08 Barry V Rhodes Ramjet powered craft
US3235183A (en) * 1963-05-29 1966-02-15 United Aircraft Corp Ablation cooled rocket nozzle
US3300142A (en) * 1963-06-25 1967-01-24 Whittaker Corp Rocket nozzle capable of inducing flow separation
US3237402A (en) * 1963-11-14 1966-03-01 Steverding Bernard Variable thrust nozzle
US3309874A (en) * 1965-02-04 1967-03-21 Bert B Gould Ablative nozzle
US3468127A (en) * 1965-09-10 1969-09-23 Secr Defence Brit Rocket projectiles
FR2473630A1 (en) * 1979-11-30 1981-07-17 Messerschmitt Boelkow Blohm Tapering tube for reaction engines, particularly for stato-reactors of flanges

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