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(10) Patent No.: US 8545646 B1

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(10) Patent No.: US 8545646 B1 USOO8545646B1 (12) United States Patent (10) Patent No.: US 8,545,646 B1 Sanford et al. (45) Date of Patent: Oct. 1, 2013 (54) HIGH-DENSITY ROCKET PROPELLANT (58) Field of Classification Search USPC .................. 149/37, 42, 75, 77, 78,79, 108.2, (75) Inventors: Matthew J. Sanford, Bel Alton, MD 149/109.2, 109.4, 109.6 (US); Randolph T. Johnson, Waldorf, See application file for complete search history. MD (US); Paul G. Wallman, Indian Head, MD (US); Diana O. Bragunier, (56) References Cited Indian Head, MD (US); Stephen N. Stiles, Indian Head, MD (US) U.S. PATENT DOCUMENTS 3,528.864 A * 9/1970 Weinland ........................ 149,92 (73) Assignee: The United States of America as 3.353- - - A : 2. Raddell et. .al. list tests by the Secretary of the 4,798,636 A * 1/1989 Strecker ......... ... 149, 19.9 avy, Washington, DC (US) 5,910,638 A * 6/1999 Spencer et al. ................. 149.18 - 6.558.488 B2 * 5/2003 Wanninger et al. .......... 149.19.1 (*) Notice: Subject to any disclaimer, the term of this 7,384,060 B2 * 6/2008 Bisogninet al. ........... 280,728.3 patent is extended or adjusted under 35 7,387,060 B1 6/2008 Sanford U.S.C. 154(b) by 53 days. * cited by examiner (21) Appl. No.: 12/587,319 Primary Examiner — James McDonough (22) Filed: Sep. 24, 2009 (74) Attorney, Agent, or Firm — Fredric J. Zimmerman Related U.S. Appl D (57) ABSTRACT t e AV pplicationicati Uatat The present disclosure relates to a high-density rocket pro (63) Continuation-in-part of application No. 1 1/151,169, pellant and associated recoilless launching systems and meth filed on Jun. 10, 2005, now Pat. No. 7,624,668. ods with tungsten powder added providing Substantial mass to the propellant for additional impulse, absorption of sound, (51) Int. Cl. optimization of backblast and carry weight, and the like. In an DO3D 43/00 (2006.01) exemplary embodiment, the high-density rocket propellant (52) U.S.AV e. Clwe includesinclud tungsten mass percentages offb between aboutbout 70%O USPC ................... 149/42; 149/37; 149/75; 149/77; about 80%, equivalent to about 17%-about 26% by volume. 149/78; 149/79; 149/108.2: 149/109.2: 149/109.4: 149/1096 17 Claims, 5 Drawing Sheets 23. 22. 24 20 25 21 N. \ - w) 2 CXXXXXXXXXXX XXXXXX K KXXXXXXXXXXXX SRSSS&SRS&S &S XXXXXXXXXXXY8X 2 U.S. Patent Oct. 1, 2013 Sheet 1 of 5 US 8,545,646 B1 120 112 10 12.5 15 17.5 20 22.5 25 27.5 30 32.5 35 Time, msec F.G. 1 U.S. Patent Oct. 1, 2013 Sheet 2 of 5 US 8,545,646 B1 33 S-ETESTIT:IVAJI FIG 2 U.S. Patent Oct. 1, 2013 Sheet 3 of 5 US 8,545,646 B1 10000 9000 8000 7000 8000 5000 4000 or mu-mi. rim rumour. 3000 2000 1000 Time, msec FIG. 3 U.S. Patent Oct. 1, 2013 Sheet 5 of 5 US 8,545,646 B1 S&S& S O O O O O O Sex XXX XXXXX XXXX XXXX XXX XXXXXX XXXX XXXXxxxxx S SXXXXXXXXXXXXXXXXXXXXX2SXXXXXXXXXXXXXXXx. S 55 57 FIG. 8 US 8,545,646 B1 1. 2 HGH-DENSITY ROCKET PROPELLANT ing stage, while the launch tube no longer guides the motors thrust. They are also slower at close range because top speed CROSS-REFERENCE TO RELATED is not achieved until both burn stages are complete. APPLICATION(S) In an urban battlefield environment, it is desirable to fire from confined spaces in order to limit exposure to hostile fire. This application is a continuation-in-part of U.S. patent The propulsion method most commonly used for this purpose application Ser. No. 1 1/151,169 filed Jun. 10, 2005 now U.S. is the Davis Gun. The original Davis Gun originated around Pat. No. 7,624,668, and entitled “RECOILLESS LAUNCH World War I, patented by Commander Cleland Davis (U.S. ING, the contents of which are incorporated in full by ref Pat. Nos. 1,108,715 through 1,108,717 issued to Davis on erence herein. 10 Aug. 25, 1914). He attached two gun barrels together at their breeches and launched two bullets in opposite directions with STATEMENT OF GOVERNMENT INTEREST no recoil forces to the launch barrel. This concept applied to a shoulder-launched device includes a propelling charge The present invention described herein may be manufac between the warhead and a dispersible countermass, which tured and used by or for the Government of the United States 15 exits to the rear. The Davis Gun uses much less propellant of America for government purposes without the payment of than a rocket for the same warhead weight and exit Velocity. any royalties thereon or therefor. However, the carry weight of a round is nearly doubled because the countermass typically weighs as much as the FIELD OF THE INVENTION projectile. The Davis-Gun has the disadvantage of requiring signifi The present invention relates generally to high-density cantly more weight and length than a Smokeless propellant rocket propellant. More particular, the present invention based rocket motor. Added weight and length is simply not an relates to a high-density rocket propellant with tungsten pow option due to the increasingly heavy load-out weight carried der added providing Substantial mass to the propellant for by today’s troops. The smokeless rocket motor has the disad additional impulse, absorption of Sound, optimization of back 25 Vantage of emitting a tremendous amount of Sound and back blast and carry weight, and the like. In an exemplary embodi blast, and performing very badly in Insensitive Munitions ment the high-density rocket propellant includes tungsten (IM) tests. All of the smokeless propellant based rocket mass percentages of between about 70%-about 80%, equiva motors (such as SMAW and M72 LAW) fail IM bullet impact, lent to 17%-26% by volume. fragment impact, and slow cook-off testing with explosive 30 reactions. These motors have historically been granted IM BACKGROUND OF THE INVENTION waivers to enable their in-service use in the short-term; how ever, they will ultimately require an IM compliant charge in Shoulder Launched rockets were first demonstrated at the order meet Navy requirements. The Smokeless propellants end of World War I and have been widely used since World used in shoulder-launched ordnance are typically double base War II. Their development was driven by the need for light 35 formulations of nitrocellulose and nitroglycerin. SMAW and infantry to engage armored threats and by the development of M72 LAW use a well-known MIL-SPEC formulation called shape charge-based anti-tank warheads. Although grenade M7, which is widely used in various weapons systems. launching devices working off the barrels of rifles were also A similar motor is used in some two-stage missiles such as used, they were relatively lightweight and low velocity to TOW. The TOW launch motor also uses M7 propellant and limit the amount of recoil or kickback to the gunner. To get 40 has the disadvantage of emitting extremely high acoustic around this limitation, larger recoilless concepts were devel emissions in the free-field launch environment. A common oped. Two well-known propulsion methods used in these disadvantage of many Smokeless propellant applications is devices are the rocket and the Davis Gun. Simple rocket that there is a limited volume available for propulsion. When versions include a warhead mounted on the nose of a rocket higher launch Velocities are desired or additional payload motor. They were shot out of a hollow aiming tube that was 45 weight is needed, there is no way to get additional impulse open on both ends. The appearance resembled a musical without incurring unacceptable tradeoffs. For example, if the instrument called a bazooka. Some launch tubes had a proportion of nitroglycerin is increased, than the IM proper reduced area at the rear to form a flow restriction, and a nozzle ties get worse. If additional high-energy materials are added behind that to counter recoil caused by the restriction. The to the propellant (Such as aluminum powder) to increase total widely used Carl Gustaf gun is an example of this variation. 50 impulse per unit volume, the resulting clouds of oxide Smoke Rockets used by the Marine Corps include the Shoulder after the launch give away the position of the gunner. The launched Multipurpose Assault Weapon (SMAW) and M72 requirement that the propellant be relatively Smokeless and Light Anti-Tank Weapon (LAW). These rockets burn out prior fast burning compositions severely limits the options avail to leaving the launch tube. The rocket nozzles have a rela able. tively large throat area and they use a plastic blowout plug to 55 aid ignition. The propellant Sticks have a high Surface area, BRIEF SUMMARY OF THE INVENTION producing high pressure and short burn times. These charac teristics result in considerable back blast, and form a lethal In an exemplary embodiment of the present invention, a Zone behind the gunner. The resulting high sound levels and rocket propellant includes propellant material and tungsten overpressure precludes them from being fired from enclo 60 powder mixed with the propellant material at a time of manu sures (FFE) and confined spaces (CS) under all but the most facture, wherein the tungsten powder includes a mass per desperate situations. Another common propulsion method is centage relative to the propellant material of about 70%–80%, a two-stage rocket, used by many popular low-budge foreign equivalent to 17%-26% by volume of the propellant material.
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