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Addition of a safety control function to the micro-igniter (MI) and improvement of its output energy are key steps required to realize attitude control, state maintenance, and orbit adjustment of micro-aerospace vehicles using a micro-thruster. To solve the system misaction caused by traditional MI due to false triggering, a microelectromechanical system (MEMS) safety device based on Lorentz force is proposed, which can operate reliably under the driving condition of 0.5 T/0.5 A, and increase the safety control function for the MI. In addition, with the aim of addressing the problem that energy attenuation and unreliable ignition of the micro-thrusters are caused by the gap between the MI and the fuel, this paper proposes a hybrid integration process for an energy amplification element (Al/Ni energetic film) and an MI (Ni-Cr) to form a Ni-Cr@Al/Ni energetic MI (EMI). By optimizing the modulation ratio (3:2) and modulation period (75 nm) of the energetic film, the preparation of the integrated EMI is completed. Electrical explosion performance analyses of the micro-igniter are performed. Under 50 V/33 μF capacitor discharge excitation, TheAl / Ni energetic film can increase the output energy of MI by 17.54 mJ. Through the non-contact (2 mm) ignition capability test, the EMI can reliably ignite 30 mg B/KNO 3. Compared with the traditional MI, EMI has the advantages of high output energy per unit space and has a function of non-contact ignition. The EMI has strong application prospects in the aerospace vehicle launch and attitude adjustment field. [Display omitted] • A MEMS safety device based on Lorentz force is proposed. • The safety device can effectively isolate the energy output of the micro-igniter. • The Al/Ni energetic film can increase the output energy of micro--igniter by 17.54 mJ. • Through the non-contact (2 mm) ignition capability test, the energetic-micro-igniter can reliably ignite 30 mg B/KNO 3. [ABSTRACT FROM AUTHOR]