#Helium electric propulsion verification

Tests with pure argon and an argon/helium mix allow for a comparison of Langmuir probe measurements to the emission spectroscopy results and verification that the helium gas seeding does not significantly affect the thruster performance. Thruster tests conducted with pure helium were used to compare the collisional radiative model to existing models. a helium seed gas to determine the plasma parameters for any propellant. A helium collisional radiative model was developed to estimate electron temperature and density from helium emission line ratios measured experimentally. Helicon thrusters differ from conventional electric propulsion systems in that. This research explores the validity of a non-invasive diagnostic technique using emission spectroscopy with a helium seed gas to determine the plasma parameters for any propellant. These probes can also have measurement errors in the presence of radio frequency, electric, or magnetic fields, making analysis of thruster performance difficult. Conventional invasive plasma diagnostics do not work reliably with water vapor plasma because it is corrosive and contains multiple species of positively and negatively charged particles, which probes that measure only plasma current are unable to distinguish. Water vapor is a possible propellant option because it is cheap, easy to store, and available in space for refueling, making it an attractive choice for deep space missions. Because of this design, propellants that would be corrosive in conventional thrusters can be used in the helicon thruster.

Helicon thrusters differ from conventional electric propulsion systems in that the conductive components that power the thruster do not contact the plasma propellant. A preliminary assessment of the cycle showed that a pressure ratio of 4, turbine entry temperature (TET) of 800 вЊ and mass flow of 50 kg/s could be used to achieve a lightweight helium closed-cycle gas turbine design for UAV mission considering component design constraints.A helicon thruster was developed to research the use of emission spectroscopy diagnostics. Some of the advantages mentioned include high payload, low noise and high altitude mission ability while the major drawbacks include a heat sink, nuclear hazard radiation and the shield weight. The study also investigates the feasibility of using helium closed-cycle gas turbines for UAV propulsion, highlighting the merits and demerits of helium closed-cycle gas turbines. This study analyses the various propulsion systems used in unmanned aerial vehicles (UAVs), paying particular focus on the closed-cycle propulsion systems. On the other hand, a comparison of the stagnation temperatures as a function of.

Aneutronic fusion means fusion that does not produce any neutrons. Helium apparently shows an efficiency advantage over hydrogen and ammonia. LPPFusion uses hydrogenboron-11 (pB11) as an aneutronic fuel for a device called Dense Plasma Focus.This unique combination comprises LPPFusionвЂ™s approach to fusion called Focus Fusion. The engine can even vary the amount of thrust generated. Electric fields heat and accelerate the plasma while the magnetic fields direct the plasma in the proper direction as it is ejected from the engine, creating thrust for the spacecraft. An electric power source is used to ionize fuel into plasma. When selecting a design for an unmanned aerial vehicle, the choice of the propulsion system is vital in terms of mission requirements, sustainability, usability, noise, controllability, reliability and technology readiness level (TRL). Aneutronic fusion can be produced using various aneutronic fuels and various fusion devices or generators. VASIMR is a plasma-based propulsion system.