The invention is for a startup system for nuclear fusion engines in space. The combustion of hydrogen and oxygen produces heat that is used by a heat engine to produce electricity. This can be supplemented by electricity from other operating engines. The exhaust from the combustion is condensed and electrolyzed to produce hydrogen and oxygen once the engine is in operation. This provides a constant source of energy for future startups. The engine is started up at partial power in electricity generation mode and this power replaces the power from the combustion as it grows. The combustor uses the same heat engine as the nuclear engine uses for power generation.

A space propulsion module for fitting to spacecraft is provided. The space propulsion module includes a solid propellant chemical thruster including a main body, and at least one electric thruster. The at least one electric thruster is mounted on main body of the solid propellant chemical thruster.

A method of making a fuel grain for use in a rocket motor, the method comprising blending a first energetic nanoscale metallic compound and a second compound suitable to form a feedstock material for use in an additive manufacturing apparatus, the additive manufacturing apparatus operatively connected to a computing system, that provides additive manufacturing printing instructions to the additive manufacturing apparatus, permitting construction of an autonomously designed and optimized rocket fuel grain section; wherein the stochastic deposition simulation-assisted fuel grain geometries further comprise a plurality of agglutinated layers of solidified fuel grain compound, each layer of the plurality of layers comprising a plurality of blended and radially displaced beads of different radii, said radial displacement optionally optimized via competitive simulation programs, and wherein the system continuously mixes constituent materials in an inline/static mixer, with viscosity controlled via particle size variations, and material is deposited in a controlled atmosphere or vacuum.

The present invention generally concerns decomposing a ternary metal hydride to isolate nanoparticles to use in a fuel grain. More specifically, the present invention harnesses increased energy densities from two distinct nanoparticles isolated by a precise decomposition of LiAlH.sub.4. The singular material is air stable and is a nanocomposite of Li.sub.3AlH.sub.6 nanoparticles, elemental Al nanoparticles, an amount of Ti metal, and a nanoscale organic layer. We call this nanocomposite nMx, which protects and preserves the high energy densities of the core metals isolated from the controlled reaction, making the nanoparticles safe to handle in air. The narrow distribution of nanoparticles has no byproducts or phase transitions that decrease energy output. The unique burning characteristics of nMx enhance the combustion of solid propellant formulations compatible with solid or hybrid rocket motors, where fuel grains are cast, pressed, or 3D printed with nMx powder, a polymeric binder, or optional additives.

The present invention generally concerns decomposing a ternary metal hydride to isolate nanoparticles to use in a fuel grain. More specifically, the present invention harnesses increased energy densities from two distinct nanoparticles isolated by a precise decomposition of LiAlH.sub.4. The singular material is air stable and is a nanocomposite of Li.sub.3AlH.sub.6 nanoparticles, elemental Al nanoparticles, an amount of Ti metal, and a nanoscale organic layer. We call this nanocomposite nMx, which protects and preserves the high energy densities of the core metals isolated from the controlled reaction, making the nanoparticles safe to handle in air. The narrow distribution of nanoparticles has no byproducts or phase transitions that decrease energy output. The unique burning characteristics of nMx enhance the combustion of solid propellant formulations compatible with solid or hybrid rocket motors, where fuel grains are cast, pressed, or 3D printed with nMx powder, a polymeric binder, or optional additives.

A Duplex Turbine Guide Vane (DTGV) assembly for a turbojet engine includes DTGVs arranged on a non-rotating guide vane ring configured to be positioned coaxially in apposition with a rotatable turbine wheel comprising turbine blades. Each of the DTGVs has an internal channel configured for receiving a gas and delivering the gas toward the turbine blades.

A Duplex Turbine Guide Vane (DTGV) assembly for a turbojet engine includes DTGVs arranged on a non-rotating guide vane ring configured to be positioned coaxially in apposition with a rotatable turbine wheel comprising turbine blades. Each of the DTGVs has an internal channel configured for receiving a gas and delivering the gas toward the turbine blades.

A method of making a multi-grained fuel grain for a rocket is disclosed, the method comprising the steps of using at least one nozzle to extrude a first propellant in an additive manufacturing process, the first propellant comprising a multi-grained fuel grain, the multi-grained fuel grain forming the at least one void, the at least one void facilitating variation in internal ballistics, forming sensors, said sensors permitting continuous monitoring and continuous modification such that a user controls the ballistics profile of a rocket motor, forming an electrically-controlled second propellant in contact with and operatively coupled to the sensors; and wherein the additive manufacturing process uses at least at least one nozzle to extrude raw materials.

Disclosed are a nanoenergetic material composite-based solid propellant, a method of preparing the same, and a projectile using the same. The propellant includes: potassium nitrate-sucrose (KNSU) composite powder; and nanoenergetic material (nEM) composite powder in a solid powder form mixed with the KNSU composite powder to prepare a KNSU/nEM propellant. The method includes: preparing KNSU composite powder; preparing nEM composite powder; and preparing a KNSU/nEM propellant by mixing the KNSU composite powder and the nEM composite powder in a solid powder form. The projectile includes: a clay block; a clay nozzle responsible for releasing the pressure generated by explosion of a propellant; and a propellant lamination area disposed between the clay block and the clay nozzle. Upon ignition of the KNSU/nEM propellant, the nEM composite powder increases the combustion rate and combustion temperature of a potassium nitrate-sucrose (KNSU) propellant.

Disclosed are a nanoenergetic material composite-based solid propellant, a method of preparing the same, and a projectile using the same. The propellant includes: potassium nitrate-sucrose (KNSU) composite powder; and nanoenergetic material (nEM) composite powder in a solid powder form mixed with the KNSU composite powder to prepare a KNSU/nEM propellant. The method includes: preparing KNSU composite powder; preparing nEM composite powder; and preparing a KNSU/nEM propellant by mixing the KNSU composite powder and the nEM composite powder in a solid powder form. The projectile includes: a clay block; a clay nozzle responsible for releasing the pressure generated by explosion of a propellant; and a propellant lamination area disposed between the clay block and the clay nozzle. Upon ignition of the KNSU/nEM propellant, the nEM composite powder increases the combustion rate and combustion temperature of a potassium nitrate-sucrose (KNSU) propellant.