|Publication number||USH203 H|
|Application number||US 06/695,499|
|Publication date||Feb 3, 1987|
|Filing date||Jan 28, 1985|
|Priority date||Jan 28, 1985|
|Publication number||06695499, 695499, US H203 H, US H203H, US-H-H203, USH203 H, USH203H|
|Inventors||William B. Thomas, Robert E. Betts|
|Original Assignee||The United States Of America As Represented By The Secretary Of The Army|
|Export Citation||BiBTeX, EndNote, RefMan|
|Non-Patent Citations (1), Referenced by (7), Classifications (12), Legal Events (3)|
|External Links: USPTO, USPTO Assignment, Espacenet|
The invention described herein may be manufactured, used, and licensed by or for the Government for governmental purposes without the payment to us of any royalties thereon.
Present State-of-the-Art of Rocket Ordnance incorporates a rocket motor which propels a missile containing a desired warhead with such designs isolating the warhead from the rocket motor. The warhead uses explosives such as RDX, PETN, and Octol, while the rocket motor uses double base propellants and composite propellants for the propelling charge.
Inherent with a warhead designed to be separated from the rocket motor in present State-of-the-Art missiles are additional cost, additional complexities, and additional processing and handling procedures. Also, additional components, such as bulkheads between the motor and the warhead, are required for a missile system employing a separable warhead.
For simplicity of design, reduction of costs, improved processing and handling procedures, and elimination of extra component parts, a unitary propellant composition which serves as the propulsion system in flight and which is detonated as a warhead explosive on impact with the target would be a welcomed addition to the rocket ordnance field.
Therefore an object of this invention is to provide a detonatable composition which is both a propellant and a warhead explosive in a single rocket motor case.
Another object of this invention is to provide a propellant grain configured to give a high boost acceleration, a sustaining thrust, and a remaining propellant portion which serves as an explosive warhead on impact.
A further object of this invention is to provide a single rocket motor case loaded with a combination propellant grain and explosive composition having a burning surface progressing towards the head end as the rocket flies to the target with some explosive propellant composition always remaining which serves as the warhead explosive on impact with the target.
A Class 1.1 detonatable composition which is both a propellant and explosive is contained in a rocket motor case. The propellant grain is configured to give a high boost acceleration, a sustaining thrust and a burning surface progressing towards the head end with some propellant grain always remaining which serves as the warhead explosive on impact with the target.
One embodiment provides for a serrated rocket motor case which results in case breakup upon detonation to give a controlled sharpnel effect. Another embodiment employs an explosive propellant grain having the effect of a shape charge at the front end. In this design, the explosive propellant grain is shaped to control the direction of the explosive force after detonation by detonator means located within the propellant charge to insure that the explosive acts in the right direction to produce the right shaping effect.
In the drawing,
FIG. 1 is a rocket motor containing an explosive propellant grain having an exposed surface for burning after ignition to provide a boost thrust phase,
FIG. 2 is a rocket motor containing an explosive propellant grain having an exposed surface for burning after boost phase to provide a sustain thrust phase, and
FIG. 3 is a rocket motor containing an explosive propellant grain having an exposed surface for burning, a shape charge at the front end, and a set back base fuze.
Referring now to FIG. 1, rocket 10 is illustrated that has a forward motor case section 12 and a rear nozzle section 14. Between the rear nozzle section 14 and forward motor case section 12, there is a continuous rocket motor case 16 which may be serrated for shrapnel effects. Contained within the rocket motor case 16 is a detonatable Class 1.1 composition 18 which is both a propellant and explosive. Positioned at the forward motor case section and in contact with the explosive 18 is a detonation fuze 20. The burning surface area is designated 22 during boost phase, and the designation is changed to 24 when the boost burning phase is completed and during the sustaining thrust phase as further explained below.
In the design of FIG. 1, the grain is configured to give a high boost acceleration, then a sustaining thrust. As for example, in FIG. 2, the remaining Class 1.1 propellant charge 18 after boost phase depicts a burning surface 24 which progresses at a slower rate due to a change to an end burning grain having less burning surface area as compared with burning surface 22 of FIG. 1. Thus during the sustaining thrust period, (as a result of the continuation of burning of propellant 18), the rocket flies to the target with the burning surface progressing towards the head end. The rocket burns on way to target with some propellant 18 always remaining which will be detonated on impact or prior to impact after activation of detonation fuze 20 by appropriate activation means well known in the art.
The uniqueness of design of FIG. 1 is that there is no separation between the warhead and the motor case. With such a simplicity of design i.e., integral rocket motorwarhead, cost is greatly reduced, the ability to load the rocket in processing and handling is also greatly reduced, and components such as the bulkheads between motor and warhead are no longer needed. Also in this specific design, the motor case 16 may be serrated to give a controlled shrapnel effect. This allows all the motor case to act as controlled warhead shrapnel which is also unique. Another design of this invention is shown in FIG. 3 wherein like numerals are shown for like parts as shown in FIG. 1 but containing a shape charge 26 at the front end. The same similar concept is used in which the propelling charge 18 and the explosive charge 18 are one and the same thing, i.e., Class 1.1 detonatable propellant. In FIG. 3 design, the front of the rocket is left hollow to hold the shape cone 26, and the detonator fuze 20 is located within the propellant charge 18 to insure that the explosive acts in the right direction to produce the right shaping effect.
Class 1.1 detonatable propellants can be selected from formulations to meet requirements for burning rates and explosive needs for the rocket motor structures illustrated and disclosed for use in accordance with this invention.
|1||Kirk-Othmer, Encyclopedia of Chemical Technology, Third Ed., vol. 9, John ley & Sons, New York (1980), pp. 564, 628, 629.|
|Citing Patent||Filing date||Publication date||Applicant||Title|
|US5000094 *||Dec 17, 1985||Mar 19, 1991||Sullivan Leroy J||Shotgun cartridge with explosive shell|
|US5886289 *||Jul 16, 1993||Mar 23, 1999||The Secretary Of State For Defence In Her Britannic Majesty's Government Of The United Kingdom Of Great Britain And Northern Ireland||Long range artillery shell|
|US8387538||Oct 5, 2010||Mar 5, 2013||Raytheon Company||Projectile having casing that includes multiple flachettes|
|US8410413||Oct 16, 2008||Apr 2, 2013||Bae Systems Bofors Ab||Method of varying firing range and effect in target for shell and shell configured for this purpose|
|US20100224719 *||Oct 16, 2008||Sep 9, 2010||Bae Systems Bofors Ab||Method of varying firing range and effect in target for shell and shell configured for this purpose|
|EP0790476A2 *||Feb 7, 1997||Aug 20, 1997||Dynamit Nobel GmbH Explosivstoff- und Systemtechnik||Selfpropelled missile|
|WO2009051544A1 *||Oct 16, 2008||Apr 23, 2009||Bae Systems Bofors Ab||Method of varying firing range and effect in target for shell and shell configured for this purpose|
|U.S. Classification||102/374, 102/288, 102/473, 102/490|
|International Classification||F42B15/00, F42B12/20|
|Cooperative Classification||F42B15/00, F42B12/20, F42B12/204|
|European Classification||F42B12/20B4, F42B15/00, F42B12/20|
|Nov 24, 1986||AS||Assignment|
Owner name: UNITED STATES OF AMERICA, AS REPRESENTED BY THE SE
Free format text: ASSIGNMENT OF ASSIGNORS INTEREST.;ASSIGNORS:THOMAS, WILLIAM B.;BETTS, ROBERT E.;REEL/FRAME:004636/0391
Effective date: 19850109
|Feb 24, 2011||AS||Assignment|
Owner name: KRATON POLYMERS U.S. LLC, TEXAS
Free format text: RELEASE BY SECURED PARTY;ASSIGNOR:UBS AG, STAMFORD BRANCH;REEL/FRAME:025845/0795
Effective date: 20110211
|Dec 16, 2015||AS||Assignment|
Owner name: KRATON POLYMERS U.S. LLC, TEXAS
Free format text: CORRECTIVE ASSIGNMENT TO CORRECT THE INCORRECT PATENT NUMBER 7720798 AND REPLACE WITH PATENT NUMBER7220798 PREVIOUSLY RECORDED ON REEL 025845 FRAME 0795. ASSIGNOR(S) HEREBY CONFIRMS THE RELEASE BY SECURED PARTY;ASSIGNOR:USB AG, STAMFORD BRANCH;REEL/FRAME:037312/0070
Effective date: 20110211