A launch apparatus comprising a second stage and a first stage wherein said second stage comprises a second stage space frame; wherein said first stage comprises a first stage space frame; wherein said second stage space frame is approximately pyramid shaped; and wherein said first stage space frame is shaped like a truncated pyramid; and wherein the overall shape of the combined second stage space frame and first stage space frame is pyramidal.

A hybrid propulsion unit, for a space vehicle or rocket, includes an external body defining a combustion chamber configured to receive a block of solid propellant, a pressurized reservoir configured to receive a liquid propellant, and a nozzle to eject the combustion gases produced by the reaction of the propellants. The pressurized reservoir being placed inside the external body, surrounded by the block of solid propellant. The propulsion unit further includes a plurality of liquid-propellant injectors disposed axially between parts of the solid propellant to improve the efficacy of the combustion. A space vehicle, of the launch vehicle type, equipped with such hybrid propulsion unit.

A rocket motor comprising a non-permeable outer shell, an intra-wall channel between the non-permeable outer shell and an annular section, and a center chamber formed at least in part by a first propellant is disclosed. The first propellant is made up of a multi-grained fuel grain, and the center chamber is further formed by an annular section. The intra-wall channel is configured to permit combustion gases to flux between the non-permeable outer shell and the annular section. The annular section configured to permit combustion gases to flux through pores embedded within the annular section.

A method for making a unitary fuel grain for use in a rocket motor or gas generator comprising forming a fuel grain coating substantially free of gas-permeable voids, forming a succession of additional coats of oxidizer depleted grain material substantially free of gas-permeable voids. The fuel grain is then deposited into a print bed along a predetermined distance in a direction primarily parallel to a rocket motor central axis, the fuel grain coating forming a rocket motor fuel grain having a pre-ignition segment and a post-ignition segment, wherein the passivated fuel grain coating of fuel grain material is continuously self-adhered during fuel grain material deposition, and wherein the fuel grain material comprises oxidizer depleted fuel grain material; and wherein the passivated fuel grain coating of fuel grain material forms a substantially circular pattern upon deposition, said substantially circular pattern having an outer shell with an undulating pattern.

A hybrid propulsion system includes a housing, at least two electrodes, a solid-grain fuel material, a combustion chamber, an oxidizer port, and a nozzle. The housing has a first end and a second end and defines a cavity. The electrodes extend into the cavity. The fuel material is free of an oxidizer and is positioned in the cavity. The fuel material has a combustion surface and is exposed to the electrodes. The combustion chamber is defined between the combustion surface and the second end. The oxidizer port provides a flow of oxidizer to the combustion chamber. The nozzle is positioned at the second end. Combustion of the fuel material in the combustion chamber may be dominated by radiative heat transfer.

A fuel grain for a rocket, the fuel grain having a plurality of layers of fuel grain material, each layer comprising a plurality of concentric circular structures of different diameter fused together to form a central opening therein, wherein the fuel grain material comprises an ignitable substance. The plurality of layers are stacked and joined securely to form a cylindrical fuel grain with the central opening of each one of the plurality of layers aligned to form a combustion unit extending axially through the fuel grain and bounded by a combustion surface, and wherein the fuel grain is configured to permit mixing of heterogenous materials to enhance thrust performance.