MEMS-based satellite micropropulsion via catalyzed hydrogen peroxide decomposition

TLDR

MEMS technologies enable next‑generation nanosatellites (10–100 kg) to meet stringent propulsion demands for low thrust, impulse, size, mass, power, and cost. The paper outlines the development of a prototype monopropellant MEMS thruster that uses catalyzed hydrogen peroxide decomposition to meet micropropulsion needs. The thruster generates ~500 µN thrust and 140–180 s specific impulse by channeling hydrogen‑peroxide decomposition products through a microscale converging/diverging supersonic nozzle, while addressing fabrication, material, combustion, and hydrodynamic challenges. The project has achieved prototype milestones, identified remaining challenges, and outlined future prospects for MEMS‑based hydrogen‑peroxide propulsion.

Abstract

Microelectromechanical systems (MEMS) techniques offer great potential in satisfying the mission requirements for the next generation of miniaturized spacecraft being designed by NASA and Department of Defense agencies. More commonly referred to as `nanosats', these spacecraft feature masses in the range of 10-100 kg and therefore have unique propulsion requirements. The propulsion systems must be capable of providing extremely low levels of thrust and impulse while also satisfying stringent demands on size, mass, power consumption and cost. We begin with an overview of micropropulsion requirements and some current MEMS-based strategies being developed to meet these needs. The remainder of the paper focuses on the progress being made at NASA Goddard Space Flight Center toward the development of a prototype monopropellant MEMS thruster which uses the catalyzed chemical decomposition of high-concentration hydrogen peroxide as a propulsion mechanism. The products of decomposition are delivered to a microscale converging/diverging supersonic nozzle, which produces the thrust vector; the targeted thrust level is approximately 500 µN with a specific impulse of 140-180 s. Macroscale hydrogen peroxide thrusters have been used for satellite propulsion for decades; however, the implementation of traditional thruster designs on the MEMS scale has uncovered new challenges in fabrication, materials compatibility, and combustion and hydrodynamic modeling. A summary of the achievements of the project to date is given, as is a discussion of remaining challenges and future prospects.