In response to the requirements of a lightweight, compact, and highly reliable commercial recoverable satellite recovery system, a recovery controller product based on a MEMS accelerometer for ballistic overload measurement are designed. It incorporates dual-core, four-process “AND-OR” logic for redundant control, and utilizes capacitive discharge semiconductor bridge igniter detonation technology for pyrotechnic device management. The ballistic overload trigger verification tests for the return process are planned. The ignition efficiency simulation analysis of the capacitive energy release system is carried out under different initial voltages, capacitor array capacitance values, and circuit resistance values. The results show that the recovery controller can achieve an overload sensing accuracy of ±0.28 g for the return trajectory under the lightweight and compact constraints, and has real-time and highly reliable control of the parachute opening logic. The optimized parameters for the capacitive discharge circuit of the semiconductor bridge igniter comprise an initial voltage greater than 24 V, a circuit resistance less than 0.3 Ω, and an initial capacitance greater than 22 μF, which can ensure highly reliable ignition control of the igniter. This design can greatly reduce the weight of the product without significantly increasing hardware consumption, and can provide reference for the design of similar electronic systems in aerospace applications.