Flight stability of a dual-spin projectile with canards

Zhu, Dalin; Tang, Shijie; Guo, Jie; Chen, Rui

doi:10.1177/0954410014539293

Cited by 26 publications

(21 citation statements)

References 16 publications

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“…The mass center and around mass center motions of projectile flight effected by canard control force are descripted by the mathematical model of 6-DOF rigid motions, which are established in four reference frames, respectively, inertial reference frame (IRF: --), velocity reference frame (VRF: 2 -2 -2 ), no-roll reference frame (NRRF: --), and canard reference frame (CRF: --). These reference frames and their relationships are shown in Figures 3,4,and 5. In the CRF, axle coincides with projectile body axle in the NRRF, axle coincides with the direction of canard 1, and axle coincides with the direction of canard 4 in Figure 2. The axles and rotate around axle .…”

Section: Flight Motionsmentioning

confidence: 96%

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Swerving Orientation of Spin-Stabilized Projectile for Fixed-Cant Canard Control Input

Shen

2015

Mathematical Problems in Engineering

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Due to the large launch overload and high spin rate of spin-stabilized projectile, no attitude sensor is adopted in square crossing fixed-cant canard concept, which causes the lack of existing projectile linear theory for the close form solution of swerving motion. This work focuses on swerving orientation prediction with the restricted conditions. By importing the mathematical models of canard force and moment into the projectile angular motion equations, trim angle induced by canard control force is extracted as the analytical solution of angle of attack increment (AOAI). On this basis, analytical orientations of trajectory angular rate increment and swerving increment are obtained via the frozen coefficient method. A series of simulations under different conditions were implemented to validate the expressions in this effort. Results state that increment orientation of swerving motion can be predicted with available trajectory parameters. The analytical orientations indicate trim value of numerical orientations. Deviations between analytical and numerical orientations relate to initial launch angles and control start time, both lower initial launch angle, and the start time which is closer to the end of flight decreases the deviation convergence time.

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Section: Flight Motionsmentioning

confidence: 96%

“…Dual-spin projectile concept is commonly adopted in the direct methods [3][4][5]. Projectile swerving dynamics are solved by yaw/pitch channels decoupling controller [6].…”

Section: Introductionmentioning

confidence: 99%

Swerving Orientation of Spin-Stabilized Projectile for Fixed-Cant Canard Control Input

Shen

2015

Mathematical Problems in Engineering

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“…In fact, the small circle motion is the real coning motion that is used as pure coning environment in many researches. 9,10,14 Since x b generates a continuous surface in space during a period of time, a continuous curve of x b can be acquired in Oy c z c . A new frame O x y z is defined for the real coning motion, O x coincides with velocity and vertical to O y z that is parallel to Oy c z c in unit distance ".…”

Section: Geometry-solving Algorithm Of Real Coning Motionmentioning

confidence: 99%

Measuring and solving real coning motion of spinning carriers

Zhang

2016

Proceedings of the Institution of Mechanical Engineers, Part G:

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Coning motion of spinning carriers is a complex rotating motion with various forms that include single circular motion, double circular motion and multiple circular motion. Due to the fact that it is difficult to describe the real coning motion of double circular motion and multiple circular motion by the common method of attack angle and sideslip angle (A-S), a cone frame and cone angles are defined to describe coning motion. Through analysis of measuring the relationship between coning motion and inertial devices such as gyroscopes and accelerometers, an inertial measuring method is proposed to build the measuring equation and resolving equation. A geometry-solving algorithm of real coning motion is derived in detail, and radiuses of large circle and real cone circle are obtained as well. A flight simulation of a spinning carrier with coning motion is designed and used to verify the measuring method and the geometry-solving algorithm. The result shows that: (1) the inertial measuring method has the same validity as A-S method to describe coning motion, but is superior to A-S method for the reason of providing the rotation information of carriers; (2) due to coupling relationship, the rotating angle is equal to the subtraction of roll angle and precession angle; (3) the real precession angle and the real nutation angle are calculated by the geometry-solving algorithm, and the real coning motion is obtained finally.

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“…Murphy [21] derived the stability boundaries for the maximum trim angles induced by control force. D Zhu [22] extended Murphy's work through Hurwitz stability criterion and derived an analytic solutions of stability boundaries.…”

Section: Introductionmentioning

confidence: 97%

Research on Instability Boundaries of Control Force for Trajectory Correction Projectiles

Fan

2019

Mathematical Problems in Engineering

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The balance of stability and maneuverability is the foundation of the trajectory correction projectile. For the terminal correction projectile without an attitude feedback loop, a larger control force is expected which may cause an instability. This paper proposes a novel method to derive instability boundaries for the control force magnitude. No additional coordinate system is needed in this method. By introducing the concept of angular compensation matrix, the exterior ballistic linearized equations considering control force are established. The necessary prerequisite for a stable flight under control is given by the Routh stability criterion. The instability boundaries for the control force magnitude are derived. The results of example flights are 13.5% more accurate compared with that in relevant research. Numerical simulations demonstrate that if the control force magnitude lies in the unstable scope derived in this paper, the projectile loses its stability. Furthermore, the effects of the projectile pitch, velocity, and roll rate on flight stability during correction are investigated using the proposed instability boundaries.

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Flight stability of a dual-spin projectile with canards

Cited by 26 publications

References 16 publications

Swerving Orientation of Spin-Stabilized Projectile for Fixed-Cant Canard Control Input

Swerving Orientation of Spin-Stabilized Projectile for Fixed-Cant Canard Control Input

Measuring and solving real coning motion of spinning carriers

Research on Instability Boundaries of Control Force for Trajectory Correction Projectiles

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