Stability Design of Spinning Missile Autopilot Considering Parasitical Loop of Roll-pitch Seeker

doi:10.3969/j.issn.1000-1093.2022.01.001

Abstract

Abstract: For the problem that the parasitical loop of roll-pitch seeker affects the dynamic stability of spinning missile, the disturbance rejection rate model of roll-pitch seeker and the mathematical equation of spinning missile are established, and the cross-coupling effect of control system induced by the rotation motion of missile body is derived and analyzed. The relationship between the autopilot gain coefficients and the expected frequency or damping is formulated. The sufficient and necessary condition for the dynamic stability of spinning missiles is analytically derived by stability analysis. The dynamic stability of spinning missile under various conditions is studied by numerical simulations. The results indicate that the stability of spinning missiles is closely related to the disturbance rejection rate and rolling rate of roll-pitch seeker, and the design indices of autopilot. The stability region of design frequency of spinning missile autopilot is obvisously smaller than that of the non-spinning missile, and the low rolling rate is helpful to reduce the effect of parasitic loop of roll-pitch seeker on the stability of spinning missile.

Key words: spinningmissile, roll-pitchseeker, parasiticalloop, disturbancerejectionrate, stability

CLC Number:

ZHOU Jianping, LI Wei, WEN Qiuqiu, XIA Qunli, JIANG Huan. Stability Design of Spinning Missile Autopilot Considering Parasitical Loop of Roll-pitch Seeker[J]. Acta Armamentarii, 2022, 43(1): 1-10.

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第43卷第1期2022 年1月
兵工学报ACTA ARMAMENTARII
Vol.43No.1Jan.2022

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