Space particle radiation induces charging and discharging phenomena in spacecraft dielectric materials, leading to electrostatic discharge (ESD) and electromagnetic pulses (EMP), which pose significant risks to spacecraft electronic systems by causing interference and potential damage. Accurate and timely monitoring of these phenomena, combined with a comprehensive understanding of their underlying mechanisms, is critical for developing effective protection strategies against satellite charging effects. Addressing in-orbit monitoring requirements, this study proposes the design of a compact sleeve monopole antenna. Through simulations, the relationships between the antenna’s design parameters and its voltage standing wave ratio (VSWR) are analyzed alongside its critical performance characteristics, including frequency band, gain, radiation pattern, and matching circuit. The proposed antenna demonstrates operation within a frequency range of (28.73–31.25) MHz (VSWR < 2), with a center frequency of 30 MHz and a relative bandwidth of 8.4%. Performance evaluations and simulation-based experiments reveal that the antenna can measure pulse signals with electric field strengths ranging from (−1000 to −80) V/m and (80 to 1000) V/m, centered at 25.47 MHz. It reliably monitors discharge pulses generated by electron irradiation on spacecraft-grade FR4 (Flame-Retardant 4) dielectric materials, providing technical support for the engineering application of discharge research in space environments. 31 1 2025 16 2 180 180 25 2 2025 © 2025 by the authors. Licensee MDPI, Basel, Switzerland. This article is an open access article distributed under the terms and conditions of the Creative Commons Attribution (CC BY) license ( https://creativecommons.org/licenses/by/4.0/ ). Abstract Space particle radiation induces charging and discharging phenomena in spacecraft dielectric materials, leading to electrostatic discharge (ESD) and electromagnetic pulses (EMP), which pose significant risks to spacecraft electronic systems by causing interference and potential damage. Keywords: spacecraft electrostatic discharge, FR4 (Flame-Retardant 4) dielectric materials, monopole antenna, impedance matching, standing wave ratio, real-time monitoring status released display-pdf yes is-olf no is-manuscript no is-preprint no is-journal-matter no is-scanned no is-retracted no Received 2024 Dec 17; Revised 2025 Jan 24; Accepted 2025 Jan 27; Collection date 2025 Feb. 1. Introduction During orbital deployment, spacecraft materials and components are inevitably exposed to various environmental stressors, including space plasmas, intense charged particle radiation, and solar radiation. These factors collectively contribute to radiation damage, which manifests in diverse forms such as total dose effects, single-event effects, and, most critically, charging and discharging phenomena [ 1 , 2 ]. Such effects significantly influence the reliability, lifespan, and overall success of spacecraft missions. Among these, particle radiation-induced charging and discharging within spacecraft dielectric materials pose a severe threat to spacecraft integrity and operational safety [ 1 , 2 , 3 ]. The phenomenon of Spacecraft Charging-Induced Electrostatic Discharge (SESD) encompasses two key processes. These efforts serve as fundamental prerequisites for the comprehensive evaluation and design of effective protection strategies against spacecraft charging and discharging effects. Such advancements are critical for ensuring the reliability, safety, and mission success of spacecraft operating in the harsh space environment. SESD can generate high voltage, strong electric fields, and transient heavy currents, accompanied by intense electromagnetic radiation, resulting in an electrostatic discharge (ESD) electromagnetic pulse. The current array of detection equipment for monitoring electrostatic discharge (ESD) electromagnetic radiation pulses in spacecraft includes monopole, dipole [ 7 , 8 , 9 ], TEM horn [ 10 ], log-periodic [ 11 ], long-wire, planar, flexible antennas, and planar interdigital sensors [ 12 ]. However, these systems face significant limitations in monitoring space discharge pulses, such as frequency band mismatches and excessive antenna sizes. The existing literature primarily describes antenna designs from simulation or simple experimental perspectives [ 14 , 15 , 16 , 17 , 18 , 19 , 20 ]. This lack of research has impeded the development of mature technologies and the systematic accumulation of data for spacecraft ESD monitoring systems. Therefore, this paper, focusing on in-orbit flight applications, discusses the adaptive design and feasibility simulation test verification of monopole antennas for monitoring electrostatic discharge in spacecraft dielectric materials, providing technical The electrical ground of the circuit module is connected to the metal cover, while the metal cover is isolated from the earth ground through a high-resistance insulator. The DC power supply and oscilloscope are connected to the main power through a series isolation transformer to complete the power supply. The above design simulates the isolated suspension of the spacecraft and the electrical ground connection state of the spacecraft’s internal circuits. Figure 12 Schematic diagram of satellite discharge pulse detection simulation experiment. Beam Density (pA/cm 2 ) Time (min) Number of Discharges (Times) 0.16 0~30 1 30~90 2 90~180 4 0.81 0~30 1 30~90 3 90~180 5 4.2 0~30 2 30~90 4 90~180 7 19 0~30 2 30~90 6 90~180 9 32 0~30 3 30~90 7 90~180 11 5. Conclusions Based on the results and discussions presented, the following conclusions are drawn: (1) A sleeve monopole antenna tailored for monitoring the electrostatic discharge (ESD) processes in spacecraft dielectric materials was successfully designed. The antenna operates in the frequency range (28.73~31.25) MHz (VSWR < 2), with a center frequency of 30 MHz and a relative bandwidth of 8.4%.