Variable burn-rate propellant
AssigneeTechnanogy, LLC
InventorsJOE A. MARTIN, LARRY H. WELCH
Life of this patent
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Abstract
Disclosed are propellants such as may be used in solid rocket motors. In one preferred embodiment, the propellant comprises one high energy propellant composition comprising a homogeneous mixture of fuel and oxidizer having a predetermined fuel/oxidizer ratio, wherein individual fuel particles are generally uniformly distributed throughout a matrix of oxidizer, and a low energy propellant comprising a fuel and oxidizer. The amounts of the two propellants are present in amounts which achieve a preselected burn rate.
Claims17
A propellant, comprising
- a first propellant composition comprising a substantially homogeneous mixture of fuel particles distributed throughout a matrix of a first oxidizer;
- and
- a second propellant composition comprising a fuel and a second oxidizer.
A method of preparing a propellant having a preselected burn rate, comprising the steps of:
- providing a quantity of a first propellant composition comprising a substantially homogeneous mixture of fuel particles generally uniformly distributed throughout a matrix of a first oxidizer;
- providing a quantity of a second propellant composition comprising a fuel and a second oxidizer;
- and
- mixing the first and second propellant compositions to form a generally uniform mixture;
- wherein the quantity of the second propellant is sufficient to modify the burn rate of the first propellant to achieve the preselected burn rate.
A method of preparing a propellant, comprising a mixture of first and second propellants, having a preselected burn rate comprising the steps of:
- providing a quantity of a first propellant composition comprising a substantially homogeneous mixture of a first fuel and a first oxidizer, wherein the first fuel is generally uniformly distributed in the form of discrete particles throughout the first oxidizer, and wherein the relative amounts of the first fuel and the first oxidizer are preselected;
- providing a quantity of a second propellant composition comprising a second fuel and a second oxidizer;
- and
- mixing the first and second propellant compositions to form a generally uniform mixture;
- wherein the quantities of the first and second propellants are chosen to achieve the preselected burn rate according to the equation:
- 5 R = m total / t = ( m f + m s ) m f / R f + m s / R s .
A solid propellant, comprising:
- macroparticles of a composition comprising fuel particles distributed generally uniformly throughout a stoichiometric quantity of a first oxidizer;
- a binder and stoichiometric quantity of a second oxidizer.
A solid propellant comprising:
- a first propellant comprising an intimate, stoichiometric mixture of a first oxidizer and metallic fuel particles;
- and
- a second propellant comprising a fuel and a second oxidizer.
A solid propellant comprising:
- a first propellant comprising a mixture of a first oxidizer and metallic fuel particles wherein the average distance separating the metallic fuel particles is controlled;
- and
- a second propellant comprising a fuel and a second oxidizer.
A solid propellant comprising a metallic fuel and oxidizer, said propellant having a burn rate at near ambient pressure sufficiently high as to achieve adequate thrust to lift a payload.
Dependencies are inferred from the claim text.