Satellite attitude control serves as the fundamental guarantee for in-orbit stable operation and mission execution of spacecraft. Precise Earth imaging for remote sensing satellites, directional beam alignment for communication satellites, and attitude stabilization & orbital maneuver for deep-space detectors all rely on high-precision, fast-response attitude control systems. Micro-propulsion systems represent the core actuators for modern high-precision satellite attitude control, including cold gas micro-thrusters, electrothermal thrusters, Hall micro-thrusters, ion micro-thrusters, and vacuum arc thrusters. Compared with traditional momentum wheels and magnetic torquers, micro-propulsion features no momentum saturation, zero magnetic interference, high thrust accuracy and rapid response, becoming standard actuators for high-resolution remote sensing satellites, low-orbit communication constellations and deep-space probes. High-voltage drive power supplies are critical core components of micro-propulsion systems, delivering high-precision, fast-response high voltage for thrust chambers, ionization chambers, accelerating electrodes and solenoid valves. Their dynamic response speed, output stability, thrust control accuracy and in-orbit reliability directly determine the response speed, precision and stability of satellite attitude control. Modern high-precision attitude control requires thrust response ≤1 ms and thrust accuracy better than ±1%, demanding power supply dynamic response ≤500 μs and voltage overshoot/drop ≤0.5% under sudden load changes. Multi-channel independent output is also required to support multi-thruster layouts for multi-axis attitude control. Conventional satellite power supplies suffer slow dynamic response, severe voltage fluctuation during load transients and low control accuracy, failing to meet fast-response demands. The design strictly complies with aerospace standards including GJB 3758-99, GJB 1027A-2005 and GJB 2494A-2013, while satisfying satellite requirements for miniaturization, lightweight design, high reliability and low power consumption. This methodology establishes a full-process universal technical framework covering fast-response topology design, dynamic optimization, high-precision thrust closed-loop control, in-orbit reliability engineering and satellite compatibility, applicable to high-voltage drive demands of all micro-propulsion systems, and providing standardized design criteria for domestic high-precision satellite attitude control upgrades. Adopting the main architecture of dual closed-loop feedforward control + phase-shifted full-bridge ZVZCS topology + modular multi-channel independent design, combined with fully digital high-speed control and minimized low-parasitic power loops, it eliminates traditional bottlenecks of slow response and large transient fluctuation, achieving microsecond-level dynamic response and high-precision output fully compliant with stringent attitude control requirements. Five core design principles are defined: 1.Phase-shifted full-bridge ZVZCS main topology realizes ZVS for primary switches and ZCS for secondary rectifiers across full load range, ensuring low switching loss, high efficiency and ultra-wide control bandwidth for rapid response to step load changes. Supporting 28 V/100 V satellite bus input and 200 V–2000 V wide high-voltage output, it adapts to diverse micro-thruster driving demands; optimized resonant clamping maintains soft switching from 10% to 100% load for long-term reliability. 2.Modular multi-channel independent architecture supports 6–12 thrusters for 3-axis 6-degree-of-freedom attitude control. Each channel integrates independent power conversion, driving, closed-loop regulation and protection with full electrical & physical isolation; single-module faults cause no system-wide impact, enhancing redundancy and survivability. Ultra-compact lightweight design achieves power density ≥200 W/in³ and weight ≤0.8 kg/kW to meet satellite volume & mass constraints. 3.High-speed dual closed-loop feedforward control adopts current inner loop + voltage outer loop + load feedforward + input feedforward composite digital regulation. Current loop bandwidth ≥50 kHz tracks rapid current variation; voltage outer loop with lead-lag correction ensures stable high-precision output; real-time load & bus feedforward adjusts phase angle within 1 μs to suppress transient voltage deviation and eliminate control delay. 4.Minimized low-parasitic power loop utilizes laminated busbars to restrict loop inductance within 5 nH, reducing electromagnetic inertia and accelerating current dynamics. Symmetric component layout shortens current paths; combined low-ESR thin-film & ceramic output capacitors lower output impedance and enhance voltage holding capability during load transients. 5.Satellite platform compatibility integrates full EMI filtering and surge suppression on the input side to avoid interference with sensitive payloads; supporting CAN, RS485 and 1553B interfaces for seamless communication with on-board computers and attitude control systems; full fault isolation ensures no bus contamination under abnormal conditions. Fast dynamic response optimization is achieved across four dimensions: Fully digital FPGA-based control reduces algorithm delay below 1 μs with sampling/update frequency above 1 MHz, enabling parallel multi-channel synchronous regulation. Deadbeat predictive current control realizes ultra-fast current tracking ≤10 μs; adaptive PID with feedforward drastically suppresses transient overshoot/drop by over 80%. Anti-windup limiting and multi-rate filtering further minimize control latency. Low-parasitic power loop optimization adopts SiC MOSFETs for fast switching; symmetric full-bridge layout ensures uniform dynamic performance; synchronous rectification reduces output impedance; hierarchical capacitor configuration delivers instant energy during load steps. High-speed isolated gate driving with peak current ≥4 A accelerates switching; compact driving layout minimizes loop inductance; adaptive gate resistance balances response speed and EMI; 100 ns ultra-fast fault locking protects power devices. Output impedance reduction via optimized filtering parameters and active damping enhances transient stability; low-inductance matched cables eliminate transmission delay between power supply and thrusters. High-precision attitude adaptation and in-orbit reliability design ensure long-term stable operation: Thrust-voltage-current closed-loop modeling achieves thrust accuracy better than ±1% and response ≤1 ms; synchronous multi-channel control guarantees torque synchronization ≤10 μs for precise 3-axis stabilization; in-orbit calibration corrects aging & environmental drift throughout the service life. Full redundancy design includes hot standby parallel channels, dual redundant buses, triple modular redundant control circuits and dual hardware/software protection for seamless fault switching within 100 μs. Space radiation hardening adopts aerospace-grade radiation-tolerant devices (total dose ≥50 krad(Si), SEU LET ≥60 MeV·cm²/mg), EDAC error correction, alloy shielding, full conduction thermal design for −40 ℃~+85 ℃ operation, and vacuum potting for high-voltage insulation against corona discharge. Comprehensive in-orbit telemetry monitors voltage, current, temperature and fault status in real time via satellite buses; full-protection mechanisms including overvoltage, overcurrent, short circuit, overtemperature and arc fault respond within 1 μs for fast fault isolation and automatic transient recovery. In summary, this integrated methodology resolves core weaknesses of conventional power supplies, achieving dynamic response ≤500 μs, transient voltage fluctuation ≤0.5% and thrust accuracy better than ±1%. Widely applicable to micro-propulsion attitude control for remote sensing satellites, communication constellations and deep-space probes, it provides critical domestic technical support for high-performance satellite attitude control systems.