Coning motion instability of spinning missiles induced by the delay of strap-down seeker

Hu, Xiao; Yang, Shuxing

doi:10.1016/j.cja.2020.06.025

Cited by 4 publications

(2 citation statements)

References 16 publications

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“…The problem of rotationally guided missiles has been addressed in several stages and forms in the literature. Some of these works refer to two-channel rotation missiles [5][6][7], and others to singlechannel missiles with time-modulated control [8][9][10][11]. Among the two-channel rockets, there is a Disclaimer/Publisher's Note: The statements, opinions, and data contained in all publications are solely those of the individual author(s) and contributor(s) and not of MDPI and/or the editor(s).…”

Section: Introductionmentioning

confidence: 99%

“…Regarding two-channel rotational missiles, several recent works have proposed the following: the design of an autopilot with a single feedback loop [13], double [14] or triple feedback loop [15]. At the same time, other papers aim to assess the stability of precession motion (conical) [5][6][7] under erroneous signal conditions introduced by the target tracking system [14,16]. Another category of papers aims to define sensors with which to determine the attitude, especially the roll angle of the rocket necessary to form the command signal [17,18].…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Stability of Single Channel Homing Slow-Rolling Missile

Chelaru,

Constantinescu,

Pană

et al. 2024

Preprint

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Starting from the model of a slow-rolling missile with six degrees of freedom (6 DOF) in the body frame, a 6 DOF model in the Resal frame is obtained, which is used to linearize the coupled commanded motion. Based on the linearized model, we obtain the structural scheme of the commanded object and define the quality parameters. The obtained parameters have a complex representation (with real and imaginary parts) due to the coupling between longitudinal channels. Then, the kinematic guidance equations, the seeker equations and the actuator specific to the slow-rolling single-channel missile are defined using a switching function. The guidance kinematic equations, the seeker equations and the actuator model are linearized in the Resal frame, and the structural diagram of the homing missile is constructed. Starting from this, the characteristic polynomial having complex coefficients is determined and then analyzed with the Frank-Wall stability criterion. Based on the analysis, a stability range is determined for the navigation constant and a minimum and possibly a maximum limit for the time to hit the target is obtained. The stability range defined for the navigation constant on the linear model is finally validated on the nonlinear model in the body frame.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Stability of Single Channel Homing Slow-Rolling Missile

Chelaru,

Constantinescu,

Pană

et al. 2024

Preprint

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Coning motion stability and decoupling methods analysis of spinning missiles with angle‐of‐attack feedback autopilot

Wang

et al. 2022

Asian Journal of Control

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The angle-of-attack (AOA) three-loop feedback autopilot is an improved three-loop autopilot that has been widely employed in missile control systems. For spinning missiles, however, unstable coning motion can be induced by the cross-couple effect. For spinning missiles with an AOA feedback autopilot, this paper analyzes the coning motion stability with the consideration of the augmentation loop and the position of the accelerometer and compares the performance of three decoupling methods. First, a novel double-channel actuator AOA three-loop autopilot is established, and the sufficient and necessary condition of coning motion stability is proposed analytically on account of the complex system equations. The stability condition shows that the stable region of the design parameters for the autopilot shrinks as a result of the spinning condition. Moreover, methods associated with actuator dynamics, control coupling, static stability, and the decoupling method of setting the lead angle to the control system are presented to improve the stability of spinning missiles. Numerical simulations are implemented to demonstrate the accuracy of the proposed methods, whose results illustrate that the stability conditions can guide AOA autopilot design for the flight stabilization of spinning missiles.

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Dynamic Estimation and Compensation of Time Delay for Missiles with Strapdown Seeker

Wang

et al. 2022

Journal of Guidance, Control, and Dynamics

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Coning motion instability of spinning missiles induced by the delay of strap-down seeker

Cited by 4 publications

References 16 publications

Stability of Single Channel Homing Slow-Rolling Missile

Stability of Single Channel Homing Slow-Rolling Missile

Coning motion stability and decoupling methods analysis of spinning missiles with angle‐of‐attack feedback autopilot

Dynamic Estimation and Compensation of Time Delay for Missiles with Strapdown Seeker

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