CDEQ V10.5: Five-Cylinder Star-Configured Clockwise Cyclic Intermittent Detonation Engine -StarEngine-XQ (STARXQ-AERO) Engineering Realization Based on CDEQ V10.0 Control Framework and Countability Theory 

Traditional rotating detonation engines (RDEs) suffer from an intrinsic timescale mismatch between microsecond-scale detonation dynamics and millisecond-scale control responses. Moreover, classical control theory relies on continuous, non-countable mathematical assumptions that conflict with discrete, countable engineering systems, hindering stable industrial deployment. This paper presents the 星擎 StarEngine-XQ (STARXQ-AERO), a five-cylinder star-configured clockwise cyclic intermittent detonation engine. It adopts five uniformly distributed annular combustion chambers, ignited sequentially with a 72° phase shift. Integrating the CDEQ V10.0 framework, it transfers the robust logic of mature air-cooled radial engines and diesel engines into detonation propulsion via topological isomorphism. The system abandons complex real-time feedback and uses a five-element thermodynamic state axiom (P, T, V, S, U) to form a closed system. It unifies variables through Q14 fixed-point countability, ensures cyclic stability via the PCTT-CW theorem (Penta-Cyclic-Clockwise-Topological-Theorem), achieves convergent centripetal energy with CENHE-LEX (Central-Holding-Nonary-Constraint-Execution-Theorem), and validates engineering stability using the GCVT-10 (Global-Convergence-Validation-Theorem) ten-step criterion. Paired with a central gas collector and dual 20° V-nozzle (total 40°), STARXQ-AERO completes the full chain: detonation → energy convergence → directional thrust. Inheriting the high reliability of WWII radial engines, StarEngine-XQ evolves mechanical radial architecture into a crankshaft-free, moving-part-free, purely fluid-driven next-generation detonation powerplant. Theoretical and practical analysis confirms that STARXQ-AERO eliminates mechanical friction and sealing failure at the structural level, drastically reduces thermal load via 1/5 duty-cycle intermittent operation, and resolves RDE control bottlenecks without microsecond real-time tracking. This research provides a novel, low-cost, engineering-ready path for next-generation propulsion, merging the robust reliability of mechanical engineering with the high efficiency of detonation dynamics.