Missile and spacecraft coning instabilities

Platus, D. H.

doi:10.2514/3.21303

Cited by 26 publications

(9 citation statements)

References 30 publications

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“…[25][26][27] In fact, its mechanism can be ascribed to a kind of side moment or out-of-plane moment which is a destabilizing factor for spinning missiles. 28 Recently, Yang and Zhou further figured out that actuators under hinge moment would also introduce out-of-plane moment and the angular motion would be unstable if the stiffness of the actuators was insufficient. 29 A new factor is depicted in this paper, which is the backlash of actuators that may result in a limit circular motion of spinning projectiles in free flight phase.…”

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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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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“…The coning motion instability of spinning missiles is widely studied throughout the 20th century. 1,2 Recently, a new destabilizing factor, which is the hinge moment, was found by Zhou and Yang. 3 It was demonstrated that the hinge moment acting on the actuator would induce an out-of-plane moment, which resulted in the instability of a 122 mm guided artillery rocket after burnout.…”

Section: Introductionmentioning

confidence: 99%

Retuning the actuator proportional–integral–derivative controller of spinning missiles

Zhou

Yang

Zhao

2016

Proceedings of the Institution of Mechanical Engineers, Part G:

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The hinge moment acting on the actuator will cause an out-of-plane moment, which is a destabilizing factor to the angular motion of spinning missiles. A new tuning criterion for the actuator controller is proposed to decrease the out-of-plane moment. It is noted that the integral element does not decrease the out-of-plane moment. A carefully designed proportional–derivative controller with some compromises can ensure the stability of the missile and provide good performance for the actuator.

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“…In general, the presence of nonlinear aerodynamic moments together with a trim condition can cause a wide range of possible coning or limit cycle motions. Murphy 3 and Platus 4,5 provide good overviews of some of these possible flight instabilities.…”

Section: Introductionmentioning

confidence: 99%

Tracking of spiraling reentry vehicles with varying frequency using a new target dynamic model

Ohlmeyer

Menon

2013

Proceedings of the Institution of Mechanical Engineers, Part G:

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As ballistic targets reenter the earth’s atmosphere, they undergo rapid deceleration and may perform spiraling motion that can make accurate tracking very difficult. A variety of filter structures have been proposed for this problem, including variants of the Kalman filter. The present work employs a new target dynamic model combined with an unscented Kalman filter to yield an effective tracking solution. The new target model includes, in addition to position and velocity states, a modified drag coefficient, the target spiral frequency, and two harmonic states describing the periodic rotation of the target body around its velocity vector. The spiral frequency was allowed to have a general variation with time. The unscented Kalman filter with new target model produced very satisfactory tracking for targets with varying frequency. The sensitivity to angle measurement accuracy using a reduced set of measurements was evaluated and a threshold value was determined. Finally, tracking performance was confirmed by Monte Carlo analysis.

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Missile and spacecraft coning instabilities

Cited by 26 publications

References 30 publications

Limit Circular Motion of Spinning Projectiles Induced by Backlash of Actuators

Limit Circular Motion of Spinning Projectiles Induced by Backlash of Actuators

Retuning the actuator proportional–integral–derivative controller of spinning missiles

Tracking of spiraling reentry vehicles with varying frequency using a new target dynamic model

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