In the context of extending the operational lifetime of EP systems, HETs and GITs face significant challenges, primarily due to critical components such as ion-acceleration grids and hollow cathode neutralizers. The degradation of these components during prolonged operation can significantly limit the lifespan of the thrusters. As mission profiles demand higher performance and longer operational durations, addressing these limitations will be crucial for the future development of reliable and durable propulsion systems. Innovations in materials and design, as well as alternative approaches to neutralization and ion acceleration will be essential in overcoming these challenges. To address the limitations of existing EP systems--such as reliance on hollow cathode neutralizers, high-voltage acceleration grids, and a restricted selection of propellants--a novel concept is proposed to enhance the performance of LEO/VLEO modern spacecraft. This innovative approach aims to improve efficiency, simplify design, and broaden propellant compatibility, leading to more effective and adaptable propulsion solutions for space applications. Various types of electrodeless plasma thrusters (PTs) have emerged as potential disruptors to current technologies, including the Helicon Double Layer Thruster (HDLT) [7; 8], the Variable Specific Impulse Magnetoplasma Rocket (VASIMR) [9], the High Power Helicon (HPT) thruster [10; 11], the Helicon Hall Thruster (HHT) [12; 13], and the Electron Cyclotron Resonance Thruster (ECRT) [14]. These designs collectively represent a significant shift towards robust and high-performance propulsion systems that are suitable for a wide range of space missions. Table 1 highlights the advanced research on RF-powered propulsion technology conducted by different research groups worldwide. Fully electrodeless Electric Thrusters (ETs) have emerged as disruptive propulsion systems, characterized by several advanced features, including high plasma densities, low electron temperatures, extended operational lifetimes, flexible propellant options, scalable power outputs, and a compact, simple design [27]. Helicon Plasma Thrusters (HPTs) based on Magnetically Enhanced Inductively Coupled Plasma (MEICP) reactors show consid \begin{table}
\begin{tabular}{c c c c c c c c c} \hline \hline
**Authors** & **Group** & **Year** & \(\mathbf{P_{RF}(W)}\) & \(\mathbf{F(mN)}\) & \(\mathbf{I_{sp}(s)}\) & \(\mathbf{\frac{F}{p_{RF}}\left(\frac{mN}{RW}\right)}\) & \(\mathbf{\eta\%}\) & **Prop** \\ \hline [PERSON] et al. [16] & Tohoko & 2011 & 900 & 3 & 510 & 3.3 & 0.8 & [PERSON] et al. [17] & Surrey & 2011 & 650 & 2.8 & 286 & 4.3 & 0.6 & [PERSON] et al. [18] & Tohoko & 2011 & 800 & 6 & 816 & 7.5 & 3 & [PERSON] et al. [19] & Canberra & 2012 & 800 & 5 & 680 & 6.3 & 2.1 & [PERSON] et al. [20] & Tohoko & 2013 & 1000 & 11 & 1559 & 11 & 8.4 & [PERSON] et al. [21] & Atlanta & 2013 & 600 & 6 & 136 & 10 & 0.7 & [PERSON] et al. [22] & Surrey & 2013 & 400 & 1.1 & 187 & 2.8 & 0.3 & [PERSON] et al. [23] & Tokyo & 2017 & 1000 & 6 & 510 & 6 & 1.5 & [PERSON] et al. [24] & Phase Four & 2017 & 100 & 5 & 146 & 50 & 3.6 & [PERSON] et al. [25] & Padova & 2017 & 150 & 1.4 & 714 & 9.3 & 3.3 & [PERSON] et al. [26] & Phase Four & 2018 & 440 & 6.2 & 1350 & 14.1 & 9.3 & Xe \\ \hline \hline \end{tabular}
\end{table} 
Table 1: Performance metrics of different HPTs with RF powers below 1000 W [15]. erable potential in meeting the growing demand for efficient and sustainable propulsion solutions in the space sector. This technology can provide continuous, precise propulsion metrics over prolonged periods, making it ideal for applications such as station keeping, orbit raising, constellation flights, and deep-space exploration. Market segmentation [28; 29] reveals a diverse range of customer groups, including satellite manufacturers, space agencies, and private space exploration companies, each with unique requirements.