Author(s)

RuoHao Zhang

Affiliation(s)

Rocket Force University of Engineering, Xi’an 710000, Shaanxi, China.

Corresponding Author

RuoHao Zhang

ABSTRACT

Addressing the trajectory deviation problem of long-range ballistic missiles (5000-8000 km range) caused by multiple factors such as aerodynamic disturbance, thrust fluctuation, and gravity field variation during flight, this paper proposes an adaptive PID trajectory correction control method based on a self-tuning parameter strategy. The paper adopts a composite guidance scheme combining inertial and satellite guidance, establishes a three-degree-of-freedom missile flight dynamics model, and designs an improved PID controller incorporating fuzzy parameter tuning, and differential filtering. In simulation experiments on a parabolic-gliding composite trajectory with long-range ballistic missile characteristics, the adaptive PID controller outperforms the traditional PID controller under different flight phases and disturbance conditions, reducing steady-state error by 42.3% and shortening adjustment time by 31.7%. The proposed adaptive PID controller achieves high-precision trajectory tracking during long-range flight, providing theoretical support and simulation validation for control systems in long-range ballistic missile applications.

KEYWORDS

Long-range ballistic missiles; Trajectory deviation correction; Adaptive PID; Composite guidance; Three-degree-of-freedom model; Simulation verification

CITE THIS PAPER

RuoHao Zhang. Performance optimization of trajectory deviation correction in long-range ballistic missiles: an adaptive PID control approach. World Journal of Engineering Research. 2026, 4(2): 1-6. DOI: https://doi.org/10.61784/wjer3082.

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