# US 8,465,607 B1 · Higher-performance solid-rocket propellants and methods of utilizing them > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 8,465,607 B1 - Document ID: US8465607B1 - Status: Granted - Kind: B1 - Application number: 12/284,476 - Filed: 2008-09-18 - Granted: 2013-06-18 - Earliest claimed: 2008-09-18 - Assignees: The United States of America as represented by the Secretary of the Navy - Applicants: John M. Kelley - Inventors: John M. Kelley - Web page: https://patentgrep.com/patent/US8465607B1 ## CPC - C06B 45/10: the organic component containing a resin - C06B 21/0041: {by compression} - C06B 45/00: Compositions or products which are defined by structure or arrangement of component of product (explosive charges of particular form or shape F42B1/00, F42B3/00) - F02K 9/18: of the internal-burning type having a star or like shaped internal cavity - B64G 1/403: {Solid propellant rocket engines} - C06B: EXPLOSIVES OR THERMIC COMPOSITIONS (blasting F42D); MANUFACTURE THEREOF; USE OF SINGLE SUBSTANCES AS EXPLOSIVES (compounds in general C01, C07 or C08; {demolition agents based on cementitious or like materials C04B41/0009}) - F02K: JET-PROPULSION PLANTS (features of jet-propulsion plants common to gas-turbine plants, air intakes or fuel supply control of air-breathing jet-propulsion plants F02C7/00, F02C9/00) - B64G: COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR ## Abstract A method, and a related material, for utilizing high performance solid rocket propellants, which are molding powders. A propellant molding powder are selected to have a design burning rate and a tailored compaction profile. A morphology of a center-port of a rocket is selected for the design burn rate and a spin-rate. The molding powder is compacted isostatically around a core through application of triaxial pressure therein forming a solid rocket propellant charge with the selected center-port shape. The solid rocket propellant charge is placed in a cartridge or a case. The cartridge is selected from various types of cartridges and specialty charges. The solid rocket propellant molding powders are highly filled with metallic fuels, and have a binder in the range of 4% to 18%, which at least partially coats the surface of the molding powder. ## Claims ### Claim 1 A solid rocket propellant material, comprising: a metallic fuel filled propellant that is a moulding powder including from about 4 percent to about 18 percent by volume of a binder, wherein the moulding powder comprises a surface, said surface includes a coating of the binder, wherein a center port, which includes a twisted geometric shape, is surrounded by the moulding powder where said twisted geometric shape influences a spin-rate for a rocket. ### Claim 2 (depends on 1) The solid rocket propellant material according to claim 1, wherein the metallic fuel filled propellant is filled with aluminum. ### Claim 3 (depends on 2) The solid rocket propellant material according to claim 2, further comprising at least one of oxidizers and nitramines. ### Claim 4 (depends on 2) The solid rocket propellant material according to claim 2, wherein the metallic fuel filled propellant is filled with substantially an equal volume of an oxidizer. ### Claim 5 (depends on 1) The solid rocket propellant material according to claim 1, further comprising an oxidizer, wherein the oxidizer is ammonium perchlorate. ### Claim 6 (depends on 1) The solid rocket propellant material according to claim 1, wherein the binder is selected from the group consisting of fluoroelastomers, polyoelfins, thermoplastic elastomers, fluoroolefins, polyisobutylenes, and polyisobutylene derivatives. ### Claim 7 (depends on 1) The solid rocket propellant material according to claim 1, wherein the metallic fuel comprises up to 25% by volume of the propellant material. ### Claim 8 (depends on 1) The solid rocket propellant material according to claim 1, wherein the energy density by volume is greater than 370 Ns/ml. ### Claim 9 (depends on 1) The solid rocket propellant material according to claim 1, wherein the solid rocket propellant material is a solid-fueled ramjet highly solids-loaded, where the metallic fuel is boron. ### Claim 10 A method for utilizing a high performance solid rocket propellant, comprising: selecting a first solid rocket propellant moulding powder having a first tailored burning rate; selecting a tailored compaction profile for the propellant moulding powder; selecting a center-port shape, wherein the center-port shape influences a propellant's burn rate and a spin-rate for the rocket; compacting isostatically the first solid rocket propellant moulding powder around a core through the application of triaxial pressure therein forming a solid rocket propellant charge having a center-port with a selected said center-port shape, wherein the center-port shape is substantially a mirror image of a surface of said core; and removing and reusing said core. ### Claim 11 (depends on 10) The method according to claim 10, wherein said center-port includes a star shaped geometry. ### Claim 12 (depends on 10) The method according to claim 10, wherein said center-port includes a twisted star shaped geometry, and wherein said twisted star shaped geometry imparts a tangential velocity component to gaseous combustion products formed during burning, which cause the rocket to spin, therein stabilizing the rocket. ### Claim 13 (depends on 10) The method according to claim 10, further comprising selecting a second solid rocket propellant moulding powder including a second tailored burning rate; and compacting isostatically the second solid rocket propellant moulding powder, wherein the second solid rocket propellant is concentrically-layered and axially-positioned in tandem to produce a boost-sustain burn profile. ### Claim 14 (depends on 10) The method according to claim 10, wherein said center-port is rifled. ### Claim 15 (depends on 10) The method according to claim 10, further comprising machining the propellant charge to predetermined dimensions; and correcting any asymmetry being produced by isostatic compaction, wherein said core is a mandrel core situated on a lathe to turn the propellant charge. ### Claim 16 (depends on 10) The method according to claim 10, further comprising selecting an inhibiting material; and compacting isostatically the inhibiting material on areas for preventing said areas from burning. ### Claim 17 A method for utilizing a high performance solid rocket propellant, comprising: selecting a first solid rocket propellant moulding powder including a first tailored burning rate; selecting a tailored compaction profile for the propellant moulding powder; selecting a center-port shape, wherein the center-port shape influences a propellant's burn rate and a spin-rate for the rocket; compacting isostatically the first solid rocket propellant moulding powder around a core through an application of triaxial pressure therein forming a solid rocket propellant charge comprising a center-port with the selected center-port shape, wherein the center-port shape is substantially a mirror image of a surface of said core; removing and potentially reusing said core; and placing the solid rocket propellant charge in a cartridge. ### Claim 18 (depends on 17) The method according to claim 17, further comprising selecting a second solid rocket propellant moulding powder including a second tailored burning rate; and compacting isostatically the second solid rocket propellant moulding powder, wherein the second solid rocket propellant is concentrically-layered, axially-positioned in tandem to produce a boost-sustain burn profile. ### Claim 19 (depends on 17) The method according to claim 17, wherein said center-port is rifled. ### Claim 20 (depends on 17) The method according to claim 17, wherein cartridge is selected from one of the group consisting of aircraft stores eject cartridges, solid rocket cartridges, and specialty charges.