Advances and comparison of mechanisms in controlled chemical micro-propulsion technologies based on solid energetic materials

Controlled chemical micro-propulsion technologies based on solid energetic materials achieve switchable combustion and adjustable thrust through energy coupling between external physical fields and solid energetic material propellants, serving as one of the core supporting technologies for high-precision power systems in micro-nano satellites. This paper systematically reviews the research progress on the mechanisms of three types of controlled micro-propulsion technologies: laser-chemical, electrochemical, and microwave-chemical. By establishing a unified analytical framework grounded in the principle of 'external energy supplementation to exceed critical combustion thresholds,' this review conducts a comparative analysis of these technologies. The results indicate that differences in energy conversion pathways (photo-thermal, electro-thermal/electrolysis, dielectric loss/plasma) and ignition mechanisms (surface hot spots, interfacial electrolysis, volumetric heating) define distinct operational domains, each with its own inherent engineering bottlenecks. Laser-chemical propulsion offers high thrust precision and rapid photothermal response, yet its practical deployment is persistently hindered by optical window contamination and non-uniform surface regression caused by Gaussian beam profiles. Electrochemical propulsion enables multi-pulse operations and real-time thrust modulation via voltage-driven interfacial electrolysis; however, its scalability is fundamentally constrained by a low critical controllable pressure threshold and electrode-contact impedance. Microwave-chemical propulsion provides a unique combination of non-contact energy delivery and volumetric dielectric heating, which eliminates the constraints of optical contamination and electrode impedance, but remains limited by the difficulties of miniaturizing high-power microwave sources and maintaining dynamic impedance matching. This comparative framework enables a direct mapping of each technology's performance boundaries to specific mission profiles (e.g., attitude control, orbital correction, and swarm coordination), offering a decision-making basis for propulsion system selection in micro-nano satellites.