Aerodynamic parameter identification of segmented missiles based on MPSP algorithm

DOI:	10.11809/bqzbgcxb2023.05.017
Keywords:	missile; aerodynamic parameter identification; terminal constraint; guidance law; Model Predictive Static Programming (MPSP)
Abstract:	This paper proposes an innovative identification method for missile aerodynamic parameter identification. Inspired by the Model Predictive Static Programming (MPSP) algorithm which is commonly used in the design of guidance laws with terminal constraints, it is applied to the field of missile aerodynamic identification. A missile mass center dynamics model in the longitudinal plane is used as the identification model, and the missile velocity, position and other flight external ballistic data are used as the model state quantities. The lift coefficient and drag coefficient are innovatively regarded as the “control quantities” in the guidance law. “Guidance” is carried out within the identification step based on the MPSP algorithm so that the predicted terminal state quantity satisfies the “terminal constraint” of the actual external ballistic state quantity to obtain the “control command” (namely, the parameter to be identified). Taking a guided projectile of 155 mm as the background, Matlab is used to compile an identification algorithm program to identify the lift drag coefficient of the given trajectory data. The simulation results show that when there is an error of 30% in the initial aerodynamic parameters, the identification algorithm can approximately converge to the true value within 170 ms on average, and the identification error is within 2%.
Issue:	Vol. 44 No. 5 (2023)
Published:	2023-05-28
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