Tube launched weapon system

• US 5,322,002 A
• Filed: 04/30/1993
• Issued: 06/21/1994
• Est. Priority Date: 04/30/1993
• Status: Expired due to Fees

• Current Assignee: Alliant Techsystems Incorporated (Northrop Grumman Corporation)
• Original Assignee: Thiokol Corporation (Howmet Aerospace, Inc.)
• Inventors: Miskelly, Herman L. Jr., Alldredge, Richard L.
• Primary Examiner(s): BROWN, DAVID
• Application Number:
  US08/056,426
• Time in Patent Office: 417 Days
• Field of Search: 89/7, 89/8, 89/1.7, 89/1.703, 89/1.704, 89/1.705, 89/1.816, 89/1.818, 89/1.813, 89/1.814
• US Class Current: 89/8
• CPC Class Codes: F41A 1/02 Hypervelocity missile propulsion using successive means for increasing the propulsive force, e.g. using successively initiated propellant charges arranged along the barrel length; Multistage missile propulsion

Abstract

A tube launched rocket system which uses a plurality of small propellant charges located within the tube to propel the rocket. The charges form part of the outer wall of a traveling propulsion chamber. The rest of the chamber is substantially defined by a propulsion housing, which includes a forward plate that abuts the projectile, and an aft nozzle for venting gases from the interior of the chamber. Alternative embodiments also contain baffles for directing the flow of combustion gases, and may employ an electronic ignition system for igniting the propellant charges in sequence. As charges adjoining the propulsion chamber are ignited, the resulting combustion gases thrust into the interior of the chamber, forcing the housing forward as they flow aftward through the nozzle. As the propulsion housing travels through the tube, additional propellant charges are ignited as they effectively become part of the outer wall of the propulsion chamber. The housing pushes the projectile ahead of it through the tube. Use of a sequence of small propellant charges in the tube rather than a conventional rocket motor in the projectile makes the system'"'"'s noise level manageable, permits the use of nontoxic propellant compositions, and eliminates the risk that a user will be burned by rocket motor exhaust as the projectile exits the tube. The teachings of the present invention also apply to closed breech systems.

Claims

1. An apparatus for accelerating a projectile in a tube, the projectile having a forward and an aft end, the tube having a forward end, an aft end, and an interior, the apparatus comprising:

a plurality of propellant charges disposed along the interior of the tube and configured such that when ignited, combustion products from the charges enter the interior of the tube;

means for igniting the propellant charges in sequence, commencing with a charge near the aft end of the tube and proceeding with successive charges approaching the forward end of the tube; and

a propulsion housing located at the aft end of the projectile and movable within the tube, the housing having a forward end, an aft end having an opening, and an interior located between the forward end and the aft end, the interior being in fluid communication with at least one of the charges, such that when the propellant charges are ignited while adjacent to the propulsion housing, combustion gases from the charges flow into the interior of the propulsion housing and out the opening of the aft end.

2. The apparatus of claim 1, wherein the propellant charges are generally toroidal in shape.

3. The apparatus of claim 1, wherein a portion of at least one propellant charge has a groove adjacent to the interior of the tube for providing a larger combustible surface area for producing a larger volume of combustion gases upon ignition of the charge.

4. The apparatus of claim 1, wherein the propellant charges are substantially non-toxic.

5. The apparatus of claim 1, wherein the propellant charges comprise a metal azide.

6. The apparatus of claim 1, further comprising a charge casing located between at least one of the propellant charges and the interior of the tube, the casing having a port permitting fluid communication between the charge and the interior of the tube.

7. The apparatus of claim 1, wherein the means for igniting the propellant charges in sequence comprises a plurality of proximity sensors, each of the propellant charges adjoining at least one proximity sensor, such that propellant charges are ignited in sequence in response to proximity of the propulsion housing to the charge as the propulsion housing moves through the tube.

8. The apparatus of claim 1, wherein the means for igniting the propellant charges in sequence comprises a plurality of igniters, each propellant charge adjoining at least one of the igniters, for igniting the propellant charges.

9. The apparatus of claim 1, wherein the propulsion housing is secured to the aft end of the projectile.

10. The apparatus of claim 1, further comprising a seal located near the forward end of the propulsion housing between the propulsion housing and a propellant charge for reducing fluid communication between the interior of the propulsion housing and the interior of the tube forward of the propulsion housing.

11. The apparatus of claim 1, further comprising an extension mechanism for extending the length of the tube by attaching a second tube, the second tube having a forward end, an aft end, an interior, and at least one propellant charge disposed in the interior of the second tube, the extension mechanism having a forward portion and an aft portion, the aft portion being located at the forward end of the tube and the forward portion being located at the aft end of the second tube.

12. The apparatus of claim 1, further comprising a closable breech door located at the aft end of the tube.

13. The apparatus of claim 1, wherein the means for igniting the propellant charges in sequence comprises an electronic ignition system configured such that propellant charges are ignited in sequence in response to an initial electronic ignition signal and following electronic ignition signals, the initial electronic ignition signal emanting from a portion of the electronic ignition system in response to a command signal from a user of the apparatus, and the following electronic ignition signals emanating from a portion of the electronic ignition system in a predetermined sequence at predetermined intervals of time.

14. The apparatus of claim 13, wherein the electronic ignition system comprises:

an electronic ignition power supply;

an electronic ignition controller; and

a plurality of wires, each wire electrically connecting the electronic ignition power supply and a propellant charge. PG,27

15. The apparatus of claim 1, wherein the propulsion housing comprises:

a forward plate located at the forward end of the propulsion housing; and

a nozzle having a throat, the nozzle being located at the aft end of the propulsion housing.

16. The apparatus of claim 15, further comprising a restraining member securing the nozzle to the forward plate.

17. The apparatus of claim 16, wherein the restraining member has slots placing the interior of the propulsion housing in fluid communication with at least one of the charges, such that when the propellant charges are ignited while adjacent to the propulsion housing, combustion gases from the charges flow into the interior of the propulsion housing and out the opening of the aft end.

18. The apparatus of claim 16, wherein the interior of the propulsion housing has a central longitudinal axis, further comprising a baffle attached to the restraining member, the baffle being generally planar in shape and disposed generally in a plane containing the central longitudinal axis of the housing, for directing the flow of combustion gases produced by the propellant charges.

19. The apparatus of claim 16, wherein the interior of the propulsion housing has a central longitudinal axis, further comprising a baffle attached to the restraining member, the baffle being disposed in helical fashion about the central longitudinal axis of the housing, for directing the flow of combustion gases produced by the propellant charges and imparting to the housing a spin about the central longitudinal axis.