Efficiency Analysis of Canards-Based Course Correction Fuze for a 155-mm Spin-Stabilized Projectile

Gagnon, Éric; Vachon, Alexandre

doi:10.1061/(asce)as.1943-5525.0000634

Cited by 10 publications

(6 citation statements)

References 21 publications

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“…Assuming that the initial conditions of and 0 are 0 ¼ 0 þ 0 i and 0 0 ¼ 0 0 þ i 0 0 , respectively, the solution to this differential equation (shown as equations (18) to (24)) can be calculated as…”

Section: Analytical Solutionmentioning

confidence: 99%

“…To calculate the acceleration response, the equation of vector Â Ã T should be established. Considering ¼ þ i, equation (18) can be rewritten as…”

Section: Appendixmentioning

confidence: 99%

“…7 compared the CCF to simpler drag and spin brake concepts, while several more advanced concepts using various combinations of fixed and movable canards were compared in Gagnon and Vachon. 18 Fresconi 19 derived a guidance and control strategy based on flight dynamics that enables precision and trajectory shaping with reduced sensor and actuator requirements for a fin-stabilized projectile. Theodoulis et al.…”

Section: Introductionmentioning

confidence: 99%

“…With regard to guidance and control, Gagnon et al 7 compared the CCF to simpler drag and spin brake concepts, while several more advanced concepts using various combinations of fixed and movable canards were compared in Gagnon and Vachon. 18 Fresconi 19 derived a guidance and control strategy based on flight dynamics that enables precision and trajectory shaping with reduced sensor and actuator requirements for a fin-stabilized projectile. Theodoulis et al 20 designed autopilots using a mixed sensitivity approach with H 1 -based methods, while Se`ve et al 21 used a loop-shaping approach for every necessary flight condition.…”

Section: Introductionmentioning

confidence: 99%

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Normal acceleration response to canard control with wind for spin-stabilized projectiles

Wang

2020

Proceedings of the Institution of Mechanical Engineers, Part G:

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In this investigation, the normal acceleration response to the control inputs of spin-stabilized projectiles considering the atmospheric wind with the coupled effects of canard control, gravity, and aerodynamic forces, being an important reference for the guidance design of low-cost guided projectiles with less measurement information (only translational motion), is deduced and analyzed. Based on the approximate formulas predicting the angle of attack under canard control and considering the atmospheric wind obtained by a linear model of the pitch and yaw motion, estimated expressions for the normal acceleration response to canard control are deduced and analyzed. To analyze the cross-coupling between pitch and yaw and simplify the design of guidance and control, the acceleration response is divided into controllable and uncontrollable parts. The phase shift between the controllable acceleration response and the direction of the control input is defined to represent the coupling effect between the pitch and the yaw; this is found to be strongly dependent on the projectiles' state parameters rather than the control parameters. The results indicate that the acceleration and phase are dramatically altered under different control directions. This condition adversely affects guidance and control because uncontrollable directions arise when the deflection angle is smaller than the critical angle.

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Section: Analytical Solutionmentioning

confidence: 99%

“…To calculate the acceleration response, the equation of vector Â Ã T should be established. Considering ¼ þ i, equation (18) can be rewritten as…”

Section: Appendixmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Normal acceleration response to canard control with wind for spin-stabilized projectiles

Wang

2020

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…There exists a lot of disturbances [2] which can create a significant dispersion of the impact points, e.g., muzzle velocity variations, tip-off effect or side wind. One of the current development tendencies aimed at improving the delivery accuracy is the use various correction systems, like body-fixed aero fins, roll decoupled canards, lateral thrusters, spin brakes, foldable plates or internal movable masses to reduce the collateral damage [3,4]. In this way, the total number of fired shells could be decreased significantly.…”

Section: Introductionmentioning

confidence: 99%

Archive of Mechanical Engineering

Szklarski

Głębocki

Jacewicz

2020

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Impact point prediction guidance parametric study for 155 mm rocket assisted artillery projectile with lateral thrustersThe modified configuration of the 155 mm rocket assisted projectile equipped with lateral thrusters was proposed. Six degree of freedom mathematical model was used to investigate the quality of the considered projectile. Impact point prediction guidance scheme intended for low control authority projectile was developed to minimize the dispersion radius. Simple point mass model was applied to calculate the impact point coordinates during the flight. Main motor time delay impact on range characteristics was investigated. Miss distance errors and Circular Error Probable for various lateral thruster total impulse were obtained. Monte-Carlo simulations proved that the impact point dispersion could be reduced significantly when the circular array of 15 solid propellant lateral thrusters was used. Single motor operation time was set to be 0.025 s. Finally, the warhead radii of destruction were analyzed.

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