USH684H - Vented in-tube burning rocket - Google Patents

Vented in-tube burning rocket Download PDF

Info

Publication number
USH684H
USH684H US07/256,796 US25679688A USH684H US H684 H USH684 H US H684H US 25679688 A US25679688 A US 25679688A US H684 H USH684 H US H684H
Authority
US
United States
Prior art keywords
motor
projectile
tube
rocket
collar
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.)
Abandoned
Application number
US07/256,796
Inventor
Jerrold H. Arszman
Albert R. Maykut
John M. Tate
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
US Department of Army
Original Assignee
US Department of Army
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by US Department of Army filed Critical US Department of Army
Priority to US07/256,796 priority Critical patent/USH684H/en
Assigned to GOVERNMENT OF THE UNITED STATES, THE, AS REPRESENTED BY THE SECRETARY OF THE ARMY reassignment GOVERNMENT OF THE UNITED STATES, THE, AS REPRESENTED BY THE SECRETARY OF THE ARMY ASSIGNMENT OF ASSIGNORS INTEREST. Assignors: ARSZMAN, JERROLD H., MAYKUT, ALBERT R., TATE, JOHN M.
Application granted granted Critical
Publication of USH684H publication Critical patent/USH684H/en
Abandoned legal-status Critical Current

Links

Images

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
    • F42B5/10—Cartridges, i.e. cases with charge and missile with self-propelled bullet
    • F42B5/105—Cartridges, i.e. cases with charge and missile with self-propelled bullet propelled by two propulsive charges, the rearwardly situated one being separated from the rest of the projectile during flight or in the barrel; Projectiles with self-ejecting cartridge cases

Definitions

  • This invention relates to in-tube burning rockets.
  • the recoilless rifle is a very efficient means of accelerating a payload to high velocities in relatively short launch tube lengths because only the payload is accelerated, with the propellant combustion products being expelled rearwardly from the tube.
  • the conventional in-tube burning rocket is essentially without recoil but is less efficient since both the payload and the rocket motor must be accelerated to the final velocity.
  • a rocket for firing from a tube wherein a rocket motor spaced from a projectile or payload is connected to the projectile by a frangible, ported collar, the front of the motor being provided with a vent for allowing combustion products from the motor to flow into the space between the motor and the projectile.
  • the pressure of the combustion products between the motor and the projectile causes the collar to break to allow the projectile to exit from the tube at a high velocity.
  • FIG. 1 is a schematic cross-sectional view showing the rocket of the present invention in a launching tube.
  • FIG. 2 is a schematic cross-sectional view showing the positioning of the rocket motor and projectile immediately after the breaking of the frangible collar interconnecting the motor and the projectile.
  • FIG. 3 is a schematic cross-sectional view showing the positioning of the motor and the projectile at an intermediate stage of the launch.
  • FIG. 4 is a schematic cross-sectional view showing the positioning of the motor and the projectile as the projectile exits from the launch tube.
  • the rocket consists of a rocket motor 12 of a known type, which contains a solid propellant 13, and a payload or projectile 15.
  • the projectile 15 is spaced from the rocket motor 12 to provide a space 16 in the tube 11 between the motor 12 and the projectile 15.
  • the motor 12 and the projectile 15 are connected by a frangible collar 20 which is provided with a plurality of spaced ports 21 (FIG. 1).
  • the rocket motor 12 is provided with a conventional nozzle 21 extending from the rear of the motor and containing a plug 22 (FIG. 1).
  • the purpose of the plug 22 is to allow pressure to increase to a certain point inside the motor 12 after the propellant 13 is ignited. When the pressure in the motor 12 has reached a predetermined value, the plug 22 will be blown out of the nozzle 21 and the motor 12 will begin to move alone the tube 11. This increases the velocity of the rocket motor 12.
  • the front of the motor 12 is provided with a vent opening 23 through Which the products of combustion of the propellant 13 can pass into the collar 20 and through the ports 21 into the space 16 between the motor 12 and the projectile 15.
  • the collar 20 is made up of a material which is adapted to break to separate the motor 12 from the projectile 15 when the pressure of the combustion products between the motor and the projectile reaches a predetermined level.
  • a material which is adapted to break to separate the motor 12 from the projectile 15 when the pressure of the combustion products between the motor and the projectile reaches a predetermined level.
  • One skilled in the art will be familiar with materials from which the collar 20 can be made.
  • FIG. 2 shows the positioning of the motor 12 and the projectile 15 immediately after the collar 20 breaks.
  • the projectile 15 will be accelerated by virtue of the high pressure of the combustion products in the space 16.
  • FIG. 3 shows the projectile after it has accelerated away from the motor 12 and
  • FIG. 4 shows the positioning of the motor 12 and the projectile 15 as the projectile exits from the tube 11. At this point, all of the propellant has burned from the motor 12.
  • the rocket In operation, the rocket is placed in the tube 11 and the solid propellant is ignited in a known manner.
  • the pressure of the combustion products formed from the boring propellant 13 reaches a predetermined level, the pressure inside the motor 12 will blow out the plug 22 and combustion products exiting from the motor 12 through the nozzle 21 will cause the motor and the projectile to begin to move alone the tube 11.
  • combustion products will pass through the vent opening 23 and the ports 21 into the space 16 between the motor 12 and the projectile 15.
  • the collar 20 will break and allow the projectile to begin to accelerate away from the motor, which begins at this time to decelerate. This continues until the motor 12 reaches full thrust and once again begins to accelerate. At some point in the launch the propellant 13 is expended, with the projectile continuing to accelerate and the motor to decelerate because of the pressure of the combustion products between the motor and the projectile.
  • the motor 12 continues to decelerate until the projectile exits from the tube 11, at which time the motor retains its velocity until it exits from the tube 11 either fore or aft, depending on its final velocity.
  • the motor 12 traveling behind the projectile 15 creates a closed breech launch by maintaining a relatively high pressure behind the projectile to accelerate the projectile, i.e., the motor behind the projectile simulates a closed breech without the recoil encountered with a closed breech launch.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • General Engineering & Computer Science (AREA)
  • Toys (AREA)

Abstract

A rocket for firing from a tube having open ends wherein a rocket motor sed from a projectile is connected to the projectile by a frangible, ported collar, the front of the motor having a vent for allowing combustion products to flow into the tube between the motor and the projectile. The pressure of the combustion products between the motor and the projectile will break the collar to allow the projectile to exit from the tube at a high velocity.

Description

DEDICATORY CLAUSE
The invention described herein may be manufactured, used, and licensed by or for the Government for governmental purposes without the payment to me of any royalties thereon.
BACKGROUND OF THE INVENTION
1. Field of the Invention
This invention relates to in-tube burning rockets.
2. Prior Art
It is known that higher rocket velocities can be achieved when a rocket is launched from a tube having a closed breech. In this approach, the propellant is confined at high pressures and the pressure of the combustion products behind the projectile provides the force to accelerate the projectile.
The primary disadvantage of using a closed breech tube for rocket launching is that substantial recoil is produced. This large amount of recoil makes it impractical to use the conventional closed breech launch concept with shoulder launched weapons such as some antitank weapons.
The recoilless rifle is a very efficient means of accelerating a payload to high velocities in relatively short launch tube lengths because only the payload is accelerated, with the propellant combustion products being expelled rearwardly from the tube. The conventional in-tube burning rocket is essentially without recoil but is less efficient since both the payload and the rocket motor must be accelerated to the final velocity.
SUMMARY OF THE INVENTION
A rocket for firing from a tube wherein a rocket motor spaced from a projectile or payload is connected to the projectile by a frangible, ported collar, the front of the motor being provided with a vent for allowing combustion products from the motor to flow into the space between the motor and the projectile. The pressure of the combustion products between the motor and the projectile causes the collar to break to allow the projectile to exit from the tube at a high velocity.
BRIEF DESCRIPTION OF THE DRAWING
FIG. 1 is a schematic cross-sectional view showing the rocket of the present invention in a launching tube.
FIG. 2 is a schematic cross-sectional view showing the positioning of the rocket motor and projectile immediately after the breaking of the frangible collar interconnecting the motor and the projectile.
FIG. 3 is a schematic cross-sectional view showing the positioning of the motor and the projectile at an intermediate stage of the launch.
FIG. 4 is a schematic cross-sectional view showing the positioning of the motor and the projectile as the projectile exits from the launch tube.
DESCRIPTION OF THE PREFERRED EMBODIMENT
Referring now in detail to the drawing, there is shown an open-ended tube 11 from Which the rocket of this invention is to be launched. The rocket consists of a rocket motor 12 of a known type, which contains a solid propellant 13, and a payload or projectile 15. The projectile 15 is spaced from the rocket motor 12 to provide a space 16 in the tube 11 between the motor 12 and the projectile 15. The motor 12 and the projectile 15 are connected by a frangible collar 20 Which is provided with a plurality of spaced ports 21 (FIG. 1).
The rocket motor 12 is provided with a conventional nozzle 21 extending from the rear of the motor and containing a plug 22 (FIG. 1). The purpose of the plug 22 is to allow pressure to increase to a certain point inside the motor 12 after the propellant 13 is ignited. When the pressure in the motor 12 has reached a predetermined value, the plug 22 will be blown out of the nozzle 21 and the motor 12 will begin to move alone the tube 11. This increases the velocity of the rocket motor 12.
The front of the motor 12 is provided With a vent opening 23 through Which the products of combustion of the propellant 13 can pass into the collar 20 and through the ports 21 into the space 16 between the motor 12 and the projectile 15.
The collar 20 is made up of a material which is adapted to break to separate the motor 12 from the projectile 15 when the pressure of the combustion products between the motor and the projectile reaches a predetermined level. One skilled in the art will be familiar with materials from which the collar 20 can be made.
FIG. 2 shows the positioning of the motor 12 and the projectile 15 immediately after the collar 20 breaks. The projectile 15 will be accelerated by virtue of the high pressure of the combustion products in the space 16. FIG. 3 shows the projectile after it has accelerated away from the motor 12 and FIG. 4 shows the positioning of the motor 12 and the projectile 15 as the projectile exits from the tube 11. At this point, all of the propellant has burned from the motor 12.
In operation, the rocket is placed in the tube 11 and the solid propellant is ignited in a known manner. When the pressure of the combustion products formed from the boring propellant 13 reaches a predetermined level, the pressure inside the motor 12 will blow out the plug 22 and combustion products exiting from the motor 12 through the nozzle 21 will cause the motor and the projectile to begin to move alone the tube 11. During this time, combustion products will pass through the vent opening 23 and the ports 21 into the space 16 between the motor 12 and the projectile 15.
When the pressure between the motor and the projectile reaches a predetermined vale, the collar 20 will break and allow the projectile to begin to accelerate away from the motor, which begins at this time to decelerate. This continues until the motor 12 reaches full thrust and once again begins to accelerate. At some point in the launch the propellant 13 is expended, with the projectile continuing to accelerate and the motor to decelerate because of the pressure of the combustion products between the motor and the projectile. The motor 12 continues to decelerate until the projectile exits from the tube 11, at which time the motor retains its velocity until it exits from the tube 11 either fore or aft, depending on its final velocity.
In effect, the motor 12 traveling behind the projectile 15 creates a closed breech launch by maintaining a relatively high pressure behind the projectile to accelerate the projectile, i.e., the motor behind the projectile simulates a closed breech without the recoil encountered with a closed breech launch.
In this approach the recoil advantages of a tube launched rocket are combined with the recoilless rifle advantage of accelerating only the payload. This combination provides a highly efficient means for imparting velocity to a projectile without the problem of recoil control.

Claims (3)

What is claimed is:
1. A rocket for firing from a tube having open ends, comprising
(a) a motor containing a propellant and having in a rear end thereof a nozzle for discharge of combustion products formed when the propellant is burned, said motor having a front end containing a vent for venting a portion of said combustion products into the tube in front of the motor,
(b) a projectile positioned in front of and spaced from the motor, and
(c) a frangible collar secured to and positioned between the motor and the projectile, said collar surrounding said vent and being provided with a port for allowing vented combustion products to flow into the tube between the motor and the projectile.
2. The rocket of claim 1 wherein the collar breaks to separate the motor and the projectile when a predetermined pressure is reached in the space between the motor and the projectile.
3. The rocket of claim 2 wherein the collar is provided with a plurality of ports.
US07/256,796 1988-10-11 1988-10-11 Vented in-tube burning rocket Abandoned USH684H (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
US07/256,796 USH684H (en) 1988-10-11 1988-10-11 Vented in-tube burning rocket

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US07/256,796 USH684H (en) 1988-10-11 1988-10-11 Vented in-tube burning rocket

Publications (1)

Publication Number Publication Date
USH684H true USH684H (en) 1989-10-03

Family

ID=22973612

Family Applications (1)

Application Number Title Priority Date Filing Date
US07/256,796 Abandoned USH684H (en) 1988-10-11 1988-10-11 Vented in-tube burning rocket

Country Status (1)

Country Link
US (1) USH684H (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7347146B1 (en) 2005-04-25 2008-03-25 The United States Of America As Represented By The Secretary Of The Navy Supercavitating projectile with propulsion and ventilation jet
US20120097144A1 (en) * 2008-06-02 2012-04-26 Causwave, Inc. Explosive decompression propulsion system

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7347146B1 (en) 2005-04-25 2008-03-25 The United States Of America As Represented By The Secretary Of The Navy Supercavitating projectile with propulsion and ventilation jet
US20120097144A1 (en) * 2008-06-02 2012-04-26 Causwave, Inc. Explosive decompression propulsion system
US8181561B2 (en) * 2008-06-02 2012-05-22 Causwave, Inc. Explosive decompression propulsion system
US20120204709A1 (en) * 2008-06-02 2012-08-16 Causwave, Inc. Projectile propulsion system
US8327747B2 (en) * 2008-06-02 2012-12-11 Causwave, Inc. Projectile propulsion system

Similar Documents

Publication Publication Date Title
US7938067B2 (en) Reduced firing signature weapon cartridge
US4932306A (en) Method and apparatus for launching a projectile at hypersonic velocity
US5952601A (en) Recoilless and gas-free projectile propulsion
US4676136A (en) Apparatus for recoilless firing of projectiles from a lauching tube
JPS628720B2 (en)
US4539911A (en) Projectile
US3167016A (en) Rocket propelled missile
WO1999024774A3 (en) Variable velocity weapons system having selective lethality and methods related thereto
US7051659B2 (en) Projectile structure
US2924174A (en) Combustible pre-spin turbine for spinner rockets
US3024729A (en) Ram jet projectile
US2946261A (en) Peripheral nozzle spinner rocket
US5099764A (en) Propulsion unit fireable from an enclosure
US2681619A (en) Rocket projectile
US3750979A (en) Rocket assisted projectile
US3326128A (en) Rockets and combinations of rockets and cases
GB2086548A (en) Projectiles
US4553480A (en) No flash, very low noise howitzer round and tube
US3380340A (en) Recoil-free weapon
US4073213A (en) Assembly for launching a projectile
USH684H (en) Vented in-tube burning rocket
US4038903A (en) Two stage telescoped launcher
EP0622603A1 (en) Launching tube with multi-stage missile propulsion
US3610093A (en) Recoilless gun
US4012987A (en) Dual combustion missile system

Legal Events

Date Code Title Description
AS Assignment

Owner name: GOVERNMENT OF THE UNITED STATES, THE, AS REPRESENT

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST.;ASSIGNORS:ARSZMAN, JERROLD H.;MAYKUT, ALBERT R.;TATE, JOHN M.;REEL/FRAME:005036/0238

Effective date: 19881005

STCF Information on status: patent grant

Free format text: PATENTED CASE