Abstract: Systems, methods, and devices for transmitting and controlling ignition output of a controller having a power source, a programmable interface, a wireless transmission module, and an ignition output unit are disclosed.

Abstract: A rocket motor propellant including a low molecular weight hydroxyl-terminated polybutadiene (HTPB) polymer and, a high molecular weight isocyanate. In some implementations, a rocket motor propellant hereof is plasticizer free.

Abstract: A thrust ring for a rocket motor for one or more of limited re-use or single use, including a rocket motor housing, the motor housing adapted to contain propellant; an aft closure with a nozzle, the aft closure connected or connectable to the housing; a forward closure connected or connectable to the housing; wherein one or both of the aft closure and the forward closure are connectable to the housing in manner adapted for one or both of limited re-use or single use.

Abstract: Delay tools, systems and methods for achieving a selection of alternative delay times, a tool of which including a body, a drill bit operable relative to the body and a knob operably connected to the drill bit, and operably disposed relative to the body for engagement of the body with a rocket motor bulkhead and the drill both relative to a delay to provide for achieving a selection of alternative delay times.

Abstract: Delay tools, systems and methods for achieving a selection of alternative delay times, a tool of which including a body, a drill bit operable relative to the body and a knob operably connected to the drill bit, and operably disposed relative to the body for engagement of the body with a rocket motor bulkhead and the drill both relative to a delay to provide for achieving a selection of alternative delay times.

Abstract: Delay tools, systems and methods for achieving a selection of alternative delay times, a tool of which including a body, a drill bit operable relative to the body and a knob operably connected to the drill bit, and operably disposed relative to the body for engagement of the body with a rocket motor bulkhead and the drill both relative to a delay to provide for achieving a selection of alternative delay times.

Abstract: A thrust ring for a rocket motor for one or more of limited re-use or single use, including a rocket motor housing, the motor housing adapted to contain propellant; an aft closure with a nozzle, the aft closure connected or connectable to the housing; a forward closure connected or connectable to the housing; wherein one or both of the aft closure and the forward closure are connectable to the housing in manner adapted for one or both of limited re-use or single use.

Abstract: Delay tools, systems and methods for achieving a selection of alternative delay times, a tool of which including a body, a drill bit operable relative to the body and a knob operably connected to the drill bit, and operably disposed relative to the body for engagement of the body with a rocket motor bulkhead and the drill both relative to a delay to provide for achieving a selection of alternative delay times.

Abstract: A rocket motor propellant including a low molecular weight hydroxyl-terminated polybutadiene (HTPB) polymer and, a high molecular weight isocyanate. In some implementations, a rocket motor propellant hereof is plasticizer free.

Abstract: Delay tools, systems and methods for achieving a selection of alternative delay times, a tool of which including a body, a drill bit operable relative to the body and a knob operably connected to the drill bit, and operably disposed relative to the body for engagement of the body with a rocket motor bulkhead and the drill both relative to a delay to provide for achieving a selection of alternative delay times.

Abstract: Delay tools, systems and methods for achieving a selection of alternative delay times, a tool of which including a body, a drill bit operable relative to the body and a knob operably connected to the drill bit, and operably disposed relative to the body for engagement of the body with a rocket motor bulkhead and the drill both relative to a delay to provide for achieving a selection of alternative delay times.

Abstract: An ejection delay system, apparatus and/or method including an electronic ejection delay system having an ignition device; a power source connected to the ignition device; and, a flight parameter sensor switch electrically connected to the power source to initiate the provision of power from the power source to the ignition device; the electronic ejection delay system being disposed in some implementations in a housing system including a housing; a forward closure for closing the top end of the housing; and, an aft closure for closing the aft end of the housing. Also disclosed is a method for ejecting a rocket recovery system in flight; including sensing a parameter associated with flight; and, initiating deployment of a recovery system.

Abstract: An ejection delay system, apparatus and/or method including an electronic ejection delay system having an ignition device; a power source connected to the ignition device; and, a flight parameter sensor switch electrically connected to the power source to initiate the provision of power from the power source to the ignition device; the electronic ejection delay system being disposed in some implementations in a housing system including a housing; a forward closure for closing the top end of the housing; and, an aft closure for closing the aft end of the housing. Also disclosed is a method for ejecting a rocket recovery system in flight; including sensing a parameter associated with flight; and, initiating deployment of a recovery system.

Abstract: A rocket motor for one or more of limited re-use or single use, including a rocket motor housing, the motor housing adapted to contain propellant; an aft closure with a nozzle, the aft closure connected or connectable to the housing; a forward closure connected or connectable to the housing; wherein one or both of the aft closure and the forward closure are connectable to the housing in manner adapted for one or both of limited re-use or single use.

Abstract: A pyrotechnic valve, igniter and combustion preheater for hybrid rocket motors is described. Particularly, the present invention comprises a ported connection means in which is mounted a solid charge of pyrotechnic material which provides a barrier to and obstructs the flow ports of the connection means to maintain the physical separation of the fluid propellant from the solid propellant. In operation, the solid charge is ignited and burns which burning consumes the charge and thereby removes the barrier to fluid propellant flow. The preferred pyrotechnic charge also ignites the solid propellant and thereby initiates combustion. The ported connection means may also include a preheater chamber in which is disposed a hollow or slotted cylinder of solid fuel which when burned, reacts with and heats the fluid oxidizer as it flows to the main combustion chamber to increase the ignitability and combustion efficiency of the solid fuel grain disposed therewithin.

Abstract: A modular reusable rocket motor combined with reusable, disposable, and expendable assemblies to provide customized operational characteristics for a rocket launched therewith.

Abstract: A novel and unique rocket ignition system comprising a novel igniter having copper foil laminated plastic substrate having a electro-conductive pyrotechnic coating disposed on one end thereof and ignitable by means of a special power-supplied igniter clip having offset positive and negative terminals for engaging the igniter and transmitting an electrical current therethrough to initiate combustion of the pyrotechnic coating which in turn ignites a rocket propellant disposed in close proximity thereto. Special means are provided to selectively position and secure the rocket ignition system to a rocket motor.

Abstract: Parachute ejection and recovery system for rockets which protects and permits recovery of the entire rocket after launch including means for cooling ejection gases, means for directing the cooler ejection gases for using in ejection, the nose cone and parachute therefrom during flight, and means for controlling descent of the rocket body, its nose cone and a parachute associated therewith.

Abstract: A finlock mechanism for recreational rockets having a pair of finlock ring members disposed in spaced relationship to each other in circumscription about the motor tube in the rocket, each ring member having a plurality of finlock receptors disposed on the perimeter thereof in equispaced relationship to each other for receiving a finlock root extending through the rocket housing in snaplock engagement therewithin.