Pulse-frequency modulated guidance laws for a mortar missile with a pulse jet control mechanism

Pavic, Milos; Pavkovic, Bojan; Mandić, Slobodan; Živković, Sanja; Ćuk, Danilo V.

doi:10.1017/s0001924000010526

Cited by 3 publications

(2 citation statements)

References 12 publications

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“…200 samples were used to generate dispersion patterns. Based on the data from (Pavic et al, 2015) and the Gaussian distribution was used to introduce the uncertainty in each model parameter (Table 2). Marsenne-Twister algorithm was used to generate pseudorandom numbers.…”

Section: Simulation Resultsmentioning

confidence: 99%

“…A roll autopilot design methodology for a canard controlled 122 mm artillery rocket using state-dependent Riccati equation method was presented in (Siddiq et al, 2012). A set of control laws based on proportional navigation with a pulse jet control mechanism was investigated in (Pavic et al, 2015). The authors achieved a drastic reduction of the mortar munition dispersion.…”

Section: State Of the Artmentioning

confidence: 99%

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Modified trajectory tracking guidance for artillery rocket

Ożóg¹,

Jacewicz²,

Głębocki³

2020

Journal of Theoretical and Applied Mechanics

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This paper contributes to a modified guidance scheme based on a trajectory tracking method which is dedicated for an artillery rocket with a finite set of single use solid propellant side thrusters. Frequency modulation of pulses was used to achieve effective firing logic. The proposed control law is applicable in the last phase of flight when the rocket reaches the vertex of the trajectory. A correction engine activation sequence was chosen in such a way that possibility of rocket axial unbalance is minimized due to motors firing. Numerical simulation results indicate that significant dispersion reduction was achieved and the number of activated side rocket thrusters is minimized.

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Section: Simulation Resultsmentioning

confidence: 99%

Section: State Of the Artmentioning

confidence: 99%

Modified trajectory tracking guidance for artillery rocket

Ożóg¹,

Jacewicz²,

Głębocki³

2020

Journal of Theoretical and Applied Mechanics

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Parametric Study of Guidance of a 160-mm Projectile Steered with Lateral Thrusters

Głębocki

Jacewicz

2020

Aerospace

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The development of projectile guidance requires consideration of a large number of possible flight scenarios with various system parameters. In this paper, the Monte-Carlo parametric study for a 160 mm artillery rocket equipped with a set of 34 small, solid propellant lateral thrusters located before the center of mass was evaluated to reduce projectile dispersion and collateral damage. The novelty of this paper lies in the functionality of modifying the shape of the trajectory in the terminal phase using lateral thrusters only. A six degree of freedom mathematical model implemented in MATLAB/Simulink was used to investigate the influence of numerous parameters on the resulting accuracy at several launch elevation angles. Augmented impact point prediction guidance was applied in the descending portion of the flight trajectory to achieve the trajectory shaping functionality. The optimum combination of thruster magnitude and algorithm parameters was obtained. The real data from the LN200 inertial measurement unit were used to investigate the influence of noise on the resulting accuracy. It was shown that with the proposed guidance method, the dispersion could be reduced by more than 250 times and the projectile impact angle might be increased when compared to an unguided projectile.

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Wavelet-Based Identification for Spinning Projectile with Gasodynamic Control Aerodynamic Coefficients Determination

Lichota

Jacewicz

Głębocki

et al. 2022

Sensors

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Identification of a spinning projectile controlled with gasodynamic engines is shown in this paper. A missile model with a measurement inertial unit was developed from Newton’s law of motion and its aerodynamic coefficients were identified. This was achieved by applying the maximum likelihood principle in the wavelet domain. To assess the results, this was also performed in the time domain. The outcomes were obtained for two cases: when noise was not present and when it was included in the data. In all cases, the identification was performed in the passive mode, i.e., no special system identification experiments were designed. In the noise-free case, aerodynamic coefficients were estimated with high accuracy. When noise was included in the data, the wavelet-based estimates had a drop in their accuracy, but were still very accurate, whereas for the time domain approach the estimates were considered inaccurate.

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Pulse-frequency modulated guidance laws for a mortar missile with a pulse jet control mechanism

Cited by 3 publications

References 12 publications

Modified trajectory tracking guidance for artillery rocket

Modified trajectory tracking guidance for artillery rocket

Parametric Study of Guidance of a 160-mm Projectile Steered with Lateral Thrusters

Wavelet-Based Identification for Spinning Projectile with Gasodynamic Control Aerodynamic Coefficients Determination

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