Wind Tunnel Tests and Open-Loop Trajectory Simulations for a 155 mm Canards Guided Spin Stabilized Projectile

Wernert, Philippe; Leopold, Friedrich; Bidino, Denis; Juncker, Joseph; Lehmann, Lutz; Bär, K.; Reindler, A.

doi:10.2514/6.2008-6881

Cited by 19 publications

(8 citation statements)

References 2 publications

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“…The trajectory model of the dual-spin rocket is based on a 7-DOF nonlinear dynamic model expressed in the Body Fixed Plane (BFP) frame as a set of 14 nonlinear differential equations [30]. The dynamic model consists of quaternion rate equations with normalization to determine the Euler Angles of the rocket orientation, so that singularities can be avoided that may occur when the pitch angle of the rocket reaches −90 • during the terminal correction phase.…”

Section: -Degree Of Freedom (Dof) Dynamic Modelmentioning

confidence: 99%

Range and Accuracy Improvement of Artillery Rocket Using Fixed Canards Trajectory Correction Fuze

Raza

Wang

2022

Aerospace

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This paper presents a two-phase guidance and control algorithm to extend the range and improve the impact point accuracy of a 122-mm rocket using a fixed canards trajectory correction fuze. The guidance algorithm consists of a unique glide and correction phase of the rocket trajectory that is activated after the flight’s apex. The glide phase operates in an open-loop configuration where guidance commands are generated to increase the range of the rocket. In contrast, the correction phase operates in a closed-loop configuration where the Impact Point Prediction method based on Modified Projectile Linear Theory is used as a feedback channel to correct the range and drift errors. The proposed fixed canards trajectory correction fuze has a simple and reliable single channel roll-orientation control configuration. The rocket trajectory model consists of a 7-DOF non-linear dynamic model of a dual-spin rocket configuration with a fixed canards correction fuze mounted at the nose. A Monte Carlo simulation of the rocket’s inertial and launch point perturbations show that the fixed canards fuze with the proposed guidance algorithm can double the range of the rocket without changing the rocket motor thrust-time curve. At the same time, the rocket’s accuracy can also be improved beyond the results of an unguided rocket.

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Section: -Degree Of Freedom (Dof) Dynamic Modelmentioning

confidence: 99%

Range and Accuracy Improvement of Artillery Rocket Using Fixed Canards Trajectory Correction Fuze

Raza

Wang

2022

Aerospace

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“…To facilitate theoretical analysis, the general method is to apply the linearization theory of projectile. This theory has been regarded as an effective tool to analyse the flight stability of projectiles and applied [8][9][10][11][12][13]. Therefore, in order to linearize these two equations, the following assumptions are introduced firstly:…”

Section: Angular Motion Equations Of the Dual-spin Projectilementioning

confidence: 99%

“…Liu et al [7] deduced the analytical expressions without attitude information, which can predict the increment orientation for trajectory angular rate and swerving motion induced by canard control force. Wernert et al [8] carried out the wind tunnel test of a canards guided 155 mm artillery and got the result of open-loop trajectory simulations.…”

Section: Introductionmentioning

confidence: 99%

Flight Stability of Canard-Guided Dual-Spin Projectiles with Angular Rate Loops

Zheng

Zhou

2020

International Journal of Aerospace Engineering

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Generally, as a precision-guided weapon, the missile has many disadvantage such as high price, difficult maintenance, and low yield. Modern war requires more and more new guided ammunition with high precision, low cost, and low collateral damage. Therefore, as a simple guided conventional ammunition technology, the dual-spin projectile has attracted the attention of ammunition experts recently. This paper proposes a dual-spin projectile scheme based on the rotation control method. Firstly, the concept of the dual-spin projectile is introduced. Secondly, the mathematical model of the dual-spin projectile is established, and the angular motion equation is finally obtained by using some linearized assumptions. Finally, the sufficient and necessary conditions of coning motion stability for dual-spin projectile with angular rate loops are analytically derived and further verified by numerical simulations. It is noticed that the upper bound of the control gain is affected by the delay angle of the control system and the spinning rate of the projectile.

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“…Costello M [17] extended the gyro stability factor and dynamic stability factor to dual-spin projectile by linearization. In the area of flight stability with control, Wernert [18,19] found that the control force induced by canards exerted an influence on steady angle of attack compared with conventional projectile without control. Cooper G and Fresconi F [20] regarded the projectile with activating canards asymmetric and investigated its flight stability under control.…”

Section: Introductionmentioning

confidence: 99%

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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Wind Tunnel Tests and Open-Loop Trajectory Simulations for a 155 mm Canards Guided Spin Stabilized Projectile

Cited by 19 publications

References 2 publications

Range and Accuracy Improvement of Artillery Rocket Using Fixed Canards Trajectory Correction Fuze

Range and Accuracy Improvement of Artillery Rocket Using Fixed Canards Trajectory Correction Fuze

Flight Stability of Canard-Guided Dual-Spin Projectiles with Angular Rate Loops

Research on Instability Boundaries of Control Force for Trajectory Correction Projectiles

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