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.

IPC Classes  ?

• D03D 23/00 - General weaving methods not special to the production of any particular woven fabric or the use of any particular loomWeaves not provided for in any other single group
• D03D 43/00 - Looms with change-boxes
• C06B 45/00 - Compositions or products which are defined by structure or arrangement of component or product
• C06B 25/34 - Compositions containing a nitrated organic compound the compound being a nitrated acyclic, alicyclic or heterocyclic amine

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.

IPC Classes  ?

• F02K 9/95 - Rocket-engine plants, i.e. plants carrying both fuel and oxidant thereforControl thereof characterised by starting or ignition means or arrangements
• F42C 19/08 - PrimersDetonators
• F23R 7/00 - Intermittent or explosive combustion chambers

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.

IPC Classes  ?

• C06B 47/00 - Compositions in which the components are separately stored until the moment of burning or explosion, e.g. "Sprengel"-type explosivesSuspensions of solid component in a normally non-explosive liquid phase, including a thickened aqueous phase
• C06D 5/00 - Generation of pressure gas, e.g. for blasting cartridges, starting cartridges, rockets

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.

IPC Classes  ?

• F23N 5/00 - Systems for controlling combustion

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.

IPC Classes  ?

• C06B 45/00 - Compositions or products which are defined by structure or arrangement of component or product