Methods of diverting fluid flow, controlling fluid loss, and/or providing zonal isolation in subterranean formations are provided. In some embodiments, the methods comprise: providing a particulate material that comprises an electrically controlled propellant; placing the particulate material in at least a first portion of the subterranean formation; introducing a treatment fluid into the subterranean formation; and allowing the particulate material to at least partially divert the flow of the treatment fluid away from the first portion of the formation.

Methods of diverting fluid flow, controlling fluid loss, and/or providing zonal isolation in subterranean formations are provided. In some embodiments, the methods comprise: providing a particulate material that comprises an electrically controlled propellant; placing the particulate material in at least a first portion of the subterranean formation; introducing a treatment fluid into the subterranean formation; and allowing the particulate material to at least partially divert the flow of the treatment fluid away from the first portion of the formation.

Systems and methods using electrically controlled propellant to operate equipment in subterranean formations are provided. In some embodiments, the methods comprise: providing a tool assembly that comprises a tool body and an electrically controlled propellant; and placing the tool assembly in at least a portion of a subterranean formation. Electrical current may be applied to at least a portion of the electrically controlled propellant to ignite the portion of the propellant to operate a portion of the tool assembly.

Systems and methods using electrically controlled propellant to operate equipment in subterranean formations are provided. In some embodiments, the methods comprise: providing a tool assembly that comprises a tool body and an electrically controlled propellant; and placing the tool assembly in at least a portion of a subterranean formation. Electrical current may be applied to at least a portion of the electrically controlled propellant to ignite the portion of the propellant to operate a portion of the tool assembly.

A solid propellant rocket motor may comprise a core-burning propellant grain extending along a longitudinal axis of the solid propellant rocket motor between an exhaust end of the solid propellant rocket motor and a forward end of the solid propellant rocket motor, a first burn inhibitor layer surrounding the core-burning propellant grain, an end-burning propellant grain surrounding the first burn inhibitor layer, a second burn inhibitor layer surrounding the end-burning propellant grain, and an aperture at least partially defined by the first burn inhibitor layer. The end-burning propellant grain is ignited by the core-burning propellant grain via the aperture.

A solid propellant rocket motor may comprise a core-burning propellant grain extending along a longitudinal axis of the solid propellant rocket motor between an exhaust end of the solid propellant rocket motor and a forward end of the solid propellant rocket motor, a first burn inhibitor layer surrounding the core-burning propellant grain, an end-burning propellant grain surrounding the first burn inhibitor layer, a second burn inhibitor layer surrounding the end-burning propellant grain, and an aperture at least partially defined by the first burn inhibitor layer. The end-burning propellant grain is ignited by the core-burning propellant grain via the aperture.

The present invention relates to an emulsion composition for an explosive and to a method of preparing the same, wherein the emulsion composition includes, based on the total weight thereof, 85 to 95 wt % of an oxidizing agent aqueous solution, 0.3 to 5 wt % of an emulsifier, and 3 to 10 wt % of oil, the emulsifier including a PIBSA (polyisobutylene succinic anhydride) amine salt having an acid value of 30 or less and an amine value of 45 to 65, under a precondition that the oxidizing agent aqueous solution includes at least one of industrial ammonium nitrate, agricultural ammonium nitrate and low-specific-gravity ammonium nitrate for an ammonium nitrate fuel oil explosive, which is used without additional filtration or removal of impurities.

The present invention relates to an emulsion composition for an explosive and to a method of preparing the same, wherein the emulsion composition includes, based on the total weight thereof, 85 to 95 wt % of an oxidizing agent aqueous solution, 0.3 to 5 wt % of an emulsifier, and 3 to 10 wt % of oil, the emulsifier including a PIBSA (polyisobutylene succinic anhydride) amine salt having an acid value of 30 or less and an amine value of 45 to 65, under a precondition that the oxidizing agent aqueous solution includes at least one of industrial ammonium nitrate, agricultural ammonium nitrate and low-specific-gravity ammonium nitrate for an ammonium nitrate fuel oil explosive, which is used without additional filtration or removal of impurities.

A solid propellant rocket motor may comprise a core-burning propellant grain extending along a longitudinal axis of the solid propellant rocket motor between an exhaust end of the solid propellant rocket motor and a forward end of the solid propellant rocket motor, a first burn inhibitor layer surrounding the core-burning propellant grain, an end-burning propellant grain surrounding the first burn inhibitor layer, a second burn inhibitor layer surrounding the end-burning propellant grain, and an aperture at least partially defined by the first burn inhibitor layer. The end-burning propellant grain is ignited by the core-burning propellant grain via the aperture.

A solid propellant rocket motor may comprise a core-burning propellant grain extending along a longitudinal axis of the solid propellant rocket motor between an exhaust end of the solid propellant rocket motor and a forward end of the solid propellant rocket motor, a first burn inhibitor layer surrounding the core-burning propellant grain, an end-burning propellant grain surrounding the first burn inhibitor layer, a second burn inhibitor layer surrounding the end-burning propellant grain, and an aperture at least partially defined by the first burn inhibitor layer. The end-burning propellant grain is ignited by the core-burning propellant grain via the aperture.