Abstract: The present application discloses an improved electrically controlled propellant wherein the electrically controlled propellant comprises at least one compound selected from the group comprising organosilanes, siloxanes, and poly(dimethylsiloxane)s.

Abstract: The present application discloses a variety of improvements that enhance at least one of the mechanical, chemical/energetic, ballistic, or adhesive properties, of a class of ECPs, regardless of whether said ECPs are in solid phase or gels, singly or in combinations thereof.

Abstract: A liquid electrically initiated and controlled composition comprising an oxidizer, soluble fuel additive(s), and other optional additives to enhance the chemical or ballistic properties, or a combination thereof is disclosed. The liquid composition further comprises stabilizers to enhance thermal stability, sequestrants to minimize deleterious effects of transition metal contaminants, and combustion enhancers maximizing efficiency. Buffers and heavy metal sequestering or complexing agents may be used in combination to achieve the highest degree of thermal stability. Additional ionic co-oxidizers may be added to the liquid composition to stabilize the liquid oxidizer and further depress freezing point. The liquid phase of matter allows flow via pipes or tubes from tanks, reservoirs, or other containers, through metering valves, followed by ignition or combustion modulation when stimulated by electrodes, statically or dynamically.

Abstract: The present application discloses a variety of improvements that enhance at least one of the mechanical, chemical/energetic, ballistic, or adhesive properties, of a class of ECPs, regardless of whether said ECPs are in solid phase or gels, singly or in combinations thereof.

Abstract: A liquid electrically initiated and controlled composition comprising an oxidizer, soluble fuel additive(s), and other optional additives to enhance the chemical or ballistic properties, or a combination thereof is disclosed. The liquid composition further comprises stabilizers to enhance thermal stability, sequestrants to minimize deleterious effects of transition metal contaminants, and combustion enhancers maximizing efficiency. Buffers and heavy metal sequestering or complexing agents may be used in combination to achieve the highest degree of thermal stability. Additional ionic co-oxidizers may be added to the liquid composition to stabilize the liquid oxidizer and further depress freezing point. The liquid phase of matter allows flow via pipes or tubes from tanks, reservoirs, or other containers, through metering valves, followed by ignition or combustion modulation when stimulated by electrodes, statically or dynamically.

Abstract: The present application discloses a variety of improvements that enhance at least one of the mechanical, chemical/energetic, ballistic, or adhesive properties, of a class of ECPs, regardless of whether said ECPs are in solid phase or gels, singly or in combinations thereof.

Abstract: A composition capable of producing either solid propellant grains, liquid or gel monopropellants, all of which are electrically ignitable and capable of sustained controllable combustion at ambient pressure. Additional compositions capable of sustained controllable combustion at elevated pressures are described. Applications for the compositions disclosed herein are provided, and include among other applications use in small micro thrusters, large core-burning solid propellant gains, shaped explosives charges for military application, and pumpable liquids and gel monopropellants or explosives for military, commercial mining or gas and oil recovery. In alternative embodiments the above compositions may also incorporate an energetic nitrate polymer, bum rate modifiers, and/or metal fuel(s). The HIPEP formulation makes it possible to ignite and sustain combustion at ambient and vacuum conditions (a) without continuous electrical power and (b) while providing faster bum rates.

Abstract: Apparatus for providing electrically initiated and/or controlled combustion of electrically ignitable propellants is provided. In one example, the apparatus includes a volume of electrically ignitable propellant (liquid and/or gas) capable of self sustaining combustion, and electrodes operable to ignite the propellant. The apparatus may further include a power supply and controller in electrical communication with the electrodes for supplying a potential across the electrodes to initiate combustion of the propellant and/or control the rate of combustion of the propellant. Various configurations and geometries of the propellant, electrodes, and apparatus are possible. In one example, the electrodes are supplied a direct current, which causes combustion of the propellant at the positive electrode. In another example, the electrodes are supplied an alternating current, which initiates combustion of the propellant at both electrodes.

Abstract: A liquid electrically initiated and controlled composition comprising an oxidizer, soluble fuel additive(s), and other optional additives to enhance the chemical or ballistic properties, or a combination thereof is disclosed. The liquid composition further comprises stabilizers to enhance thermal stability, sequestrants to minimize deleterious effects of transition metal contaminants, and combustion enhancers maximizing efficiency. Buffers and heavy metal sequestering or complexing agents may be used in combination to achieve the highest degree of thermal stability. Additional ionic co-oxidizers may be added to the liquid composition to stabilize the liquid oxidizer and further depress freezing point. The liquid phase of matter allows flow via pipes or tubes from tanks, reservoirs, or other containers, through metering valves, followed by ignition or combustion modulation when stimulated by electrodes, statically or dynamically.

Abstract: The present invention is an electrically controlled propellant comprising a binder, an oxidizer, and a cross-linking agent. The boric acid (the cross-linking agent) has been found to function as a cross-linking agent for the high molecular binder used to make the propellant, thereby improving the composition's ability to withstand combustion without melting. The present invention also may include 5-aminotetrazole (5-ATZ) as a stability-enhancing additive. The binder of the present invention may include polyvinylalcohol (PVA) and/or the co-polymer of polyvinylalcohol/polyvinylamine nitrate (PVA/PVAN).

Abstract: The present invention relates to a solid rocket motor control system that uses state of the art electrically ignited, extinguishable and throttleable propellants. In embodiments, the control system is implemented by a software algorithm embedded in missile flight controllers and contains all control system elements and control compensation that performs thrust control for many defense and space rocket motor applications, for example.

Abstract: A thruster stack assembly and method for manufacturing the same is provided. The thruster stack assembly includes a plurality of grain elements having a common core region (e.g., a channel or passageway), where each grain element comprises a volume of electrically ignitable propellant. The thruster stack assembly further includes electrodes associated with the plurality of grain elements, the electrodes adapted for selectively igniting the plurality of grain elements. In one example, one or more of the grain elements may be ignited and combusted without igniting or damaging adjacent grain elements of the stack. The core region serves to channel combustion gases and exhaust from the thruster stack. Multiple stacks may be assembled together to form three-dimensional thruster arrays.

Abstract: A new process for forming MICs as well as three exemplary categories of MIC formulations is disclosed. MICs disclosed herein include a first exemplary category for which combustion can be initiated and sustained by either a heat (flame) source or electrical power, a second exemplary category of formulations that can be ignited and that sustain combustion at low pressures only with electrical power and a third exemplary category of formulations that can be ignited and extinguished at low pressures only with electrical power. The new process of MIC formulation provides energetic liquid oxidizers in place of traditional solvents, thus eliminating the need for solvent extraction. The energetic liquid oxidizer serves as a medium in which to suspend and grow the 3D nanostructure formed by the cross linked polymer (PVA). As a consequence, the 3D nanostructure entraps the liquid oxidizer, preventing it from evaporating and thereby eliminating the need for solvent extraction, preserves the 3D nanostructure shape.

Abstract: The present invention is an electrically controlled propellant comprising a binder, an oxidizer, and a cross-linking agent. The boric acid (the cross-linking agent) has been found to function as a cross-linking agent for the high molecular binder used to make the propellant, thereby improving the composition's ability to withstand combustion without melting. The present invention also may include 5-aminotetrazole (5-ATZ) as a stability-enhancing additive. The binder of the present invention may include polyvinylalcohol (PVA) and/or the co-polymer of polyvinylalcohol/polyvinylamine nitrate (PVA/PVAN).

Abstract: A composition capable of producing either solid propellant grains, liquid or gel monopropellants, all of which are electrically ignitable and capable of sustained controllable combustion at ambient pressure. Additional compositions capable of sustained controllable combustion at elevated pressures are described. Applications for the compositions disclosed herein are provided, and include among other applications use in small micro thrusters, large core-burning solid propellant gains, shaped explosives charges for military application, and pumpable liquids and gel monopropellants or explosives for military, commercial mining or gas and oil recovery. In alternative embodiments the above compositions may also incorporate an energetic nitrate polymer, bum rate modifiers, and/or metal fuel(s). The HIPEP formulation makes it possible to ignite and sustain combustion at ambient and vacuum conditions (a) without continuous electrical power and (b) while providing faster bum rates.