Large amplitude oscillations of cruciform tailed missiles. Part 1: Catastrophic yaw fundamental analysis

Morote, Jesús; García‐Ybarra, P.L.; Castillo, José L.

doi:10.1016/j.ast.2012.01.002

Cited by 17 publications

(8 citation statements)

References 9 publications

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“…The independent term C mα0 of the complex yaw moment, which contributes to the real part, determines the static stability and the pitch frequency. The imaginary part of C mα R , referred to as the out-of-plane or side moment, plays an important role in the roll lock-in and catastrophic yaw phenomena [11,13]. The rest of the aerodynamic coefficients in Eq.…”

Section: Approximate Equationsmentioning

confidence: 99%

See 1 more Smart Citation

Nonlinear model of the free-flight motion of finned bodies

Liaño

Castillo

García‐Ybarra

2014

Aerospace Science and Technology

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Section: Approximate Equationsmentioning

confidence: 99%

“…An equivalent equation for the linear theory (γ = M = 1, N = 0) was established in [15]. Also, different derivations have been performed previously using a cubic yaw moment [13,16,19,23]. However, no model of the yaw moment (linear, cubic or else) is specified in Eq.…”

Section: Approximate Equationsmentioning

confidence: 99%

Nonlinear model of the free-flight motion of finned bodies

Liaño

Castillo

García‐Ybarra

2014

Aerospace Science and Technology

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“…9 The phenomena of spin-yaw lock-in and catastrophic yaw were then widely studied under different conditions by various researchers. [10][11][12][13][14][15][16] Moreover, the stabilities of spinning missiles with specific configurations also attracted much attention, which included the wrap-around fins, 17,18 the payloads containing liquid 19,20 or with moving mass, 21,22 and dual-spin projectiles. 23 In recent years, more and more guidance and control techniques were utilized in artillery rockets and projectiles to improve their impact accuracy, and it brought some additional factors involving the stability of the coning motion.…”

Section: Introductionmentioning

confidence: 99%

Limit Circular Motion of Spinning Projectiles Induced by Backlash of Actuators

Zhou

Yang

Zhao

2014

AIAA Atmospheric Flight Mechanics Conference

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Divergent coning motions and limit circular motions of spinning projectiles with large amplitude are harmful and have been widely discussed by many researchers. In this paper, a new factor is exposed and its mechanism is elucidated, which is the backlash of actuators that may lead to a limit circular motion of spinning projectiles in free flight phase. The backlash is generated from additional gear drives outside the closed-loop actuators and its nonlinearity is depicted by describing function method. Both the sufficient condition for the existence of a stable limit circular motion and the equation to calculate the amplitude are obtained and then validated by numerical simulations. Meanwhile, the effects of some key parameters on the motion in both free flight and control phase are discussed as well. It is noted that the harmful impact of the backlash in the free flight phase is much greater than that in the control phase. Nomenclatureaxis moment of inertia, kg·m 2 I y = transverse moment of inertia, kg·m 2 K = amplitude of the limit circular motion, deg l = reference length, m m = mass of the airframe, kg p, q, r = roll, pitch, and yaw rates in the non-rolling frame, rad/s Q = 2 1 2 V  , dynamic pressure, N/m 2 S = reference area, m 2 t = time, s u, v, w = velocity components in the non-rolling frame, m/s V = velocity vector of the airframe, m/s  ,  = angles of attack and sideslip in the non-rolling frame, rad   ,   = angles of attack and sideslip in the body-fixed frame, rad  = i    , complex angle of attack in the non-rolling frame, rad   = i      , complex angle of attack in the body-fixed frame, rad  = air density, kg/m 3

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“…Actually, the analysis of dynamic stability for spinning body is always active and attracts many researchers’ attention. 1–9 Theoretical analysis on the stability conditions of spinning missiles has been widely conducted, especially on the angular motion of axisymmetric spinning missiles. The dynamics equations under the nonrolling body frame were established, and the stability criteria based on the linear theory were obtained by Murphy.…”

Section: Introductionmentioning

confidence: 99%

Effects of aeroelasticity on coning motion of a spinning missile

Shi

Zhao

2016

Proceedings of the Institution of Mechanical Engineers, Part G:

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The coning motion is a basic angular behavior of spinning missiles. Research on the stability of coning motion is always active. In this paper, the integrated nonlinear governing equations of rigid-elastic angular motion for a spinning missile with high fineness ratio are derived firstly following the Lagrangian approach. Secondly, a set of linear equation is obtained under some assumptions considering the first order vibration mode in the form of complex summation for theoretical analysis. Finally, the sufficient and necessary conditions of coning motion dynamic stability for spinning missile with and without an acceleration autopilot are analytically derived and verified by numerical simulations based on the linear equation. It is concluded that the aeroelasticity can shrink the stable region of the design parameters, even lead to a divergent coning motion.

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Large amplitude oscillations of cruciform tailed missiles. Part 1: Catastrophic yaw fundamental analysis

Cited by 17 publications

References 9 publications

Nonlinear model of the free-flight motion of finned bodies

Nonlinear model of the free-flight motion of finned bodies

Limit Circular Motion of Spinning Projectiles Induced by Backlash of Actuators

Effects of aeroelasticity on coning motion of a spinning missile

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