Abstract: A Fiber-fed Pulsed Plasma Thruster (FPPT) has an anode, a coaxial insulator, and a fiber propellant feed system. At least two cathodes insulated from each other are configured about the coaxial insulator to define an interior profile shaped into a nozzle region. At least one igniter fitted through each cathode. Wherein when the igniters are triggered, the igniters expel electrons toward the anode to ignite a primary high energy discharge between the anode and the cathodes thereby creating a plasma that vaporizes the fiber propellant. The dissociated fiber propellant combines with the primary high energy discharge to create a partially or fully ionized plasma, that is electromagnetically and electrothermally accelerated to produce predominantly {right arrow over (j)}×{right arrow over (B)}{right arrow over (j)}×{right arrow over (B)} thrust.

Abstract: A Fiber-fed Pulsed Plasma Thruster (FPPT) utilizes a motor to feed PTFE fiber to its discharge region, enabling high PPT propellant throughput and variable exposed fuel area. A highly parallel ceramic capacitor bank lowers system specific mass. Impulse bits (I-bits) from 0.057-0.241 mN-s have been measured on a thrust stand with a specific impulse (Isp) of 900-2400 s, representing an enhancement from state-of-the-art PPT technology. A 1 U (10 cm×10 cm×10 cm, or 1 liter) volume FPPT thruster package will provide 2900-7700 N-s total impulse, enabling 0.6-1.6 km/s delta-V for a 5 kg CubeSat. A 1 U design variation with 590 g propellant enables as much as ˜10,000 N-s and a delta-V of 2 km/s for a 5 kg CubeSat. Increasing the form factor to 2U increases propellant mass to 1.4 kg and delta-V to 10.7 km/s for an 8 kg CubeSat.

Abstract: The monofilament vaporization propulsion system in accordance with an embodiment of the invention includes a mechanical feed, an elongated barrel, a heater block, a tube, and a nozzle. A monofilament solid propellant is wound around a spool and fed into the mechanical feed. The elongated barrel is configured to receive the solid propellant towards a second end. The heater block is positioned near the second end of the barrel and configured to heat the propellant into a liquid propellant as the solid propellant moves towards the second end. The tube receives the liquid propellant and is configured to evaporate the liquid propellant into a gaseous propellant. The gaseous propellant enters a nozzle in communication with the tube. The gaseous propellant being fed into the nozzle entrance expands there-through to create propulsion out an nozzle exit.

Abstract: A Fiber-fed Pulsed Plasma Thruster (FPPT) will enable enhanced low Earth orbit, cis-lunar, and deep space missions for small satellites. FPPT technology utilizes an electric motor to feed PTFE fiber to its discharge region, enabling high PPT propellant throughput and variable exposed fuel area. An innovative, parallel ceramic capacitor bank dramatically lowers system specific mass. FPPT minimizes range safety concerns by the use of non-pressurized, non-toxic, inert propellant and construction materials. Estimates are that a 1U (10 cm×10 cm×10 cm, or 1 liter) volume FPPT thruster package may provide more than 10,000 N-s total impulse and a delta-V of 1.4 km/s delta-V for an 8 kg CubeSat.

Abstract: A Fiber-fed Pulsed Plasma Thruster (FPPT) utilizes a motor to feed PTFE fiber to its discharge region, enabling high PPT propellant throughput and variable exposed fuel area. A highly parallel ceramic capacitor bank lowers system specific mass. Impulse bits (I-bits) from 0.057-0.241 mN-s have been measured on a thrust stand with a specific impulse (Isp) of 900-2400 s, representing an enhancement from state-of-the-art PPT technology. A 1U (10 cm×10 cm×10 cm, or 1 liter) volume FPPT thruster package will provide 2900-7700 N-s total impulse, enabling 0.6-1.6 km/s delta-V for a 5 kg CubeSat. A 1U design variation with 590 g propellant enables as much as ˜10,000 N-s and a delta-V of 2 km/s for a 5 kg CubeSat. Increasing the form factor to 2U increases propellant mass to 1.4 kg and delta-V to 10.7 km/s for an 8 kg CubeSat.

Abstract: A Fiber-fed Pulsed Plasma Thruster (FPPT) will enable enhanced low Earth orbit, cis-lunar, and deep space missions for small satellites. FPPT technology utilizes an electric motor to feed PTFE fiber to its discharge region, enabling high PPT propellant throughput and variable exposed fuel area. An innovative, parallel ceramic capacitor bank dramatically lowers system specific mass. FPPT minimizes range safety concerns by the use of non-pressurized, non-toxic, inert propellant and construction materials. Estimates are that a 1 U (10 cm×10 cm×10 cm, or 1 liter) volume FPPT thruster package may provide more than 10,000 N-s total impulse and a delta-V of 1.4 km/s delta-V for an 8 kg CubeSat.

Abstract: An initial surface is provided. An overlay of colored grout is provided. The colored grout is on the initial surface. In this manner an intermediate surface is created. An acid stain is provided. The acid stain is on the intermediate surface. A two part clear epoxy resin is provided. The epoxy resin is provided on the intermediate surface. In this manner an exterior surface is created.

Abstract: A pulsed plasma thruster provides for an advanced lightweight design with solid propellant and predominately electromagnetic thrust in a coaxial geometry. Electromagnetic forces are generated in a plasma by current flowing from a small central electrode to an electrically conducting diverging nozzle electrode. The thruster employs a series of electric current pulses of limited duration and varying frequency between the pair of electrodes creating a series of electric arcs. The electric arcs pass over a propellant surface located between the electrodes, forming a plasma, which is then exhausted from the device to produce thrust. The thruster maintains a low plasma resistance and cavity pressure, which in turn yields strong electromagnetic body forces, resulting in a high efficiency and consistent pulse-to-pulse performance.

Abstract: An initial surface is provided. An overlay of colored grout is provided. The colored grout is on the initial surface. In this manner an intermediate surface is created. An acid stain is provided. The acid stain is on the intermediate surface. A two part clear epoxy resin is provided. The epoxy resin is provided on the intermediate surface. In this manner an exterior surface is created.