Impact point prediction guidance based on iterative process for dual-spin projectile with fixed canards

Zhang, Xin; Yao, Xiaoxian; Zheng, Qiushi

doi:10.1016/j.cja.2019.06.002

Cited by 13 publications

(7 citation statements)

References 23 publications

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“…The aerodynamic force coefficients appearing in Equation ( 4) are measured in the Velocity frame while the moment coefficients appearing in Equation ( 5) are measured in the body frame, and they need to be transformed into the BFP frame using the transformation matrix (Equation (1) previously used in the dynamic model. The aerodynamic coefficients of a 122 mm rocket without a canard fuze are similar to the data presented in references [12,28,[32][33][34][35] which are based on CFD simulations and Missile DATCOM.…”

Section: -Degree Of Freedom (Dof) Dynamic Modelsupporting

confidence: 79%

“…The Impact Point Prediction (IPP) method is used as a feedback loop to generate guidance commands to correct trajectory during the error correction phase of rocket flight [12,28,37,38]. The IPP routine is evaluated during the error correction phase after every 0.1 s, making it is a suitable compromise between guidance computation burden and required miss-distance precision.…”

Section: Impact Point Predictionmentioning

confidence: 99%

“…Based on the IPP method, various guidance and control strategies have been studied. An iterative impact point prediction method has been formulated by [28] for fixed canard angle fuze, but this iterative method is not computationally efficient and puts an unnecessary high burden on the guidance computer. Whereas in this research, the impact point is rapidly predicted during discrete intervals of the rocket's flight using Modified Projectile Linear Theory [29], and control action is based on the swerve response of the projectile, thus eliminating the need for the iterative process.…”

Section: Introductionmentioning

confidence: 99%

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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 Modelsupporting

confidence: 79%

Section: Impact Point Predictionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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

Raza

Wang

2022

Aerospace

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“…Obviously, real-time estimation of the damage effect function relies on a variety of types of data detection by the guidance-integrated fuze system [ 17 , 18 , 19 , 20 ]. It is worth noting that the priority of distance and the direction for damage-effect optimization varies during different stages of the pursuit.…”

Section: Introductionmentioning

confidence: 99%

Optimal-Damage-Effectiveness Cooperative-Control Strategy for the Pursuit–Evasion Problem with Multiple Guided Missiles

Dai

et al. 2022

Sensors

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In this paper, an optimal-damage-effectiveness cooperative-control strategy based on a damage-efficiency model and a virtual-force method is proposed to solve the pursuit–evasion problem with multiple guided missiles. Firstly, different from the overly ideal assumption in the traditional pursuit–evasion problem, an optimization problem that maximizes the damage efficiency is established and solved, making the optimal-damage-effectiveness strategy more meaningful for practical applications. Secondly, a modified virtual-force method is proposed to obtain this optimal-damage-effectiveness control strategy, which solves the numerical solution challenges brought by the high-complexity damage function. Thirdly, adaptive gain is designed in this strategy based on guidance-integrated fuze technology to achieve robust maximum damage efficiency in unpredictable interception conditions. Finally, the effectiveness and robustness of the proposed strategy are verified by numerical simulations.

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“…A few publications specifically pertain to the guidance of DSPs. Iterative impact point prediction has been used to create a GL for a DSP with control force imparted by fixed canards 20 . A modified form of projectile linear theory is used to predict where the projectile will land and make the necessary corrections to the control system.…”

Section: Introductionmentioning

confidence: 99%

A novel quasi-dynamic guidance law for a dynamic dual-spin projectile with non-conventional, asymmetric roll constraints

Norris

Economou

Hameed

2022

Proceedings of the Institution of Mechanical Engineers, Part G:

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A novel quasi-dynamic guidance law (QDGL) is presented for a dual-spin projectile (DSP) with unconventional constraints on roll direction. A 7 degree-of-freedom (DOF) dynamic model is established and the projectile operational mechanism is presented with a description of how it is used to enact control. The QDGL is presented and a parametric study is conducted to show how the QDGL parameters affect the system response. A procedure of using batches of Monte Carlo simulations is described, to numerically compare the system response with different QDGL configurations. A genetic algorithm is then used to optimise both the innate system parameters and PID controller gains. The disturbance rejection capabilities of the optimal QDGL are then evaluated along with the performance against different target profiles. It was found that the GA optimised QDGL is able to provide satisfactory control capabilities against static and dynamic targets.

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Impact point prediction guidance based on iterative process for dual-spin projectile with fixed canards

Cited by 13 publications

References 23 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

Optimal-Damage-Effectiveness Cooperative-Control Strategy for the Pursuit–Evasion Problem with Multiple Guided Missiles

A novel quasi-dynamic guidance law for a dynamic dual-spin projectile with non-conventional, asymmetric roll constraints

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