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An end-burning grain of a solid rocket motor or other gas-generating device is supplemented with one or more sticks of high-burn-rate propellant embedded in a matrix of a relatively low-burn-rate propellant. The sticks increase the burning surface area as the grain burns by forming conical indentati

An end-burning grain of a solid rocket motor or other gas-generating device is supplemented with one or more sticks of high-burn-rate propellant embedded in a matrix of a relatively low-burn-rate propellant. The sticks increase the burning surface area as the grain burns by forming conical indentations in the surface.

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1. An end-burning grain of a solid gas-generating composition, said grain having an ignition end and a longitudinal axis, said grain comprising: a matrix propellant having a matrix propellant burn rate, wherein said matrix propellant is devoid of metallic fuels and halogen-containing, additives, and

1. An end-burning grain of a solid gas-generating composition, said grain having an ignition end and a longitudinal axis, said grain comprising: a matrix propellant having a matrix propellant burn rate, wherein said matrix propellant is devoid of metallic fuels and halogen-containing, additives, anda rod of ballistic control propellant embedded in said matrix propellant, wherein said ballistic control propellant comprises nitrocellulose an energetic plasticizer, and a high-nitrogen burning rate modifier and is devoid of ammonium perchlorate,wherein the ballistic control propellant and the matrix propellant are devoid of metallic ballistic modifiers,said ballistic control propellant having a ballistic control propellant burn rate that is substantially greater than said matrix propellant burn rate,said rod terminating at said ignition end of said grain, wherein the matrix propellant and the ballistic control propellants are solid propellants. 2. The end-burning grain of claim 1 wherein said rod is substantially parallel to said longitudinal axis. 3. The end-burning grain of claim 1 comprising a plurality of said rods, all substantially parallel to said longitudinal axis. 4. The end-burning grain of claim 1 wherein said ballistic control propellant burn rate is from about 1.3 times to about ten times said matrix propellant burn rate. 5. The end-burning grain of claim 1 wherein said ballistic control propellant burn rate is from about 1.5 times to about three times said matrix propellant burn rate. 6. The end-burning grain of claim 1 wherein said ballistic control propellant burn rate is about 1.9 cm/sec to about 12.7 cm/sec at 2,000 psi, and said matrix propellant burn rate is about 0.64 cm/sec to about 5.1 cm/sec at 2,000 psi. 7. The end-burning grain of claim 1 wherein said ballistic control propellant burn rate is about 2.2 cm/sec to about 7.6 cm/sec at 2,000 psi, and said matrix propellant burn rate is about 1.0 cm/sec to about 2.5 cm/sec at 2,000 psi. 8. The end-burning grain of claim 1 wherein said ballistic control propellant burn rate is about 0.64 cm/sec to about 5.1 cm/sec faster than said matrix propellant burn rate. 9. The end-burning grain of claim 1 wherein said ballistic control propellant burn rate is about 1.0 cm/sec to about 2.5 cm/sec faster than said matrix propellant burn rate. 10. The end-burning grain of claim 1 wherein said ballistic control propellant comprises nitrocellulose, an energetic plasticizer, and a high-nitrogen burning rate modifier. 11. The end-burning grain of claim 1 wherein said ballistic control propellant comprises (i) nitrocellulose, (ii) a member selected from the group consisting of cyclotetramethylene tetranitramine, butyl nitratoethyl nitramine, butanetriol trinitrate, bis-dinitropropylacetal/formal, and methyl/ethyl nitratoethyl nitramine, and (iii) a member selected from the group consisting of triaminoguanidinium azotetrazolate, guanidinium azotetrazolate, 1,1-diamino-2,2-nitroethene, 3,3′-diamino-4,4′-azoxyfurazan, and 2,6-diamino-3,5-dinitropyrazine-1-oxide, and said matrix propellant is a member selected from the group consisting of bis-nitrofurazanyl furoxan,3,3′-dinitro-4,4′-furazanyl oxamide, methylene-bis-aminonitrofurazan, 2,4,6,8,10,12-hexanitro-2,4,6,8,10,12-hexaazaisowurtzitane, and ammonium 2-oxy-5-nitrotetrazolate. 12. The end-burning grain of claim 1 wherein said matrix propellant is devoid of metallic fuels and halogen-containing additives. 13. The end-burning grain of claim 1 wherein said matrix propellant is devoid of lead, lead compounds, and lead salts. 14. The end-burning grain of claim 1 wherein said ballistic control propellant and said matrix propellant are both devoid of cyclotrimethylene trinitramine. 15. The end-burning grain of claim 1 wherein said ballistic control propellant and said matrix propellant are both devoid of cyclotrimethylene trinitramine, lead, lead compounds, and lead salts. 16. The end-burning grain of claim 1 wherein said grain has a (ballistic control propellant):(matrix propellant) cross section area ratio of from about 1×10−4 to about 3×10−3. 17. The end-burning grain of claim 1 wherein said grain has a (ballistic control propellant):(matrix propellant) cross section area ratio of from about 3×10−4 to about 1×10−3.