Study of Model Uncertainties Influence on the Impact Point Dispersion for a Gasodynamicaly Controlled Projectile

Jacewicz, Mariusz; Lichota, Piotr; Miedziński, Dariusz; Głębocki, R.

doi:10.3390/s22093257

Cited by 5 publications

(3 citation statements)

References 33 publications

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“…Monte Carlo simulation is a method that widely used for predicting the dispersion of a rocket's impact point (Junior et al 2022). Monte Carlo simulation is a method for determining how the simulation output is affected by the uncertainty of the input parameters (Jacewicz et al 2022). This method is ideal for investigating the effect of a combination of various parameters on rocket's performance (Noga, Michalow, and Ptasinski 2021) Monte Carlo simulation is carried out by taking sample of each uncertain input parameter, then simulating a physical model to determine the desired output.…”

Section: Monte Carlo Simulationmentioning

confidence: 99%

Impact Point Dispersion Prediction for 300 mm R-Han 300 Artillery Rocket

Riyadl,

Robertus Heru TriHarjanto,

Pujo Widodo

2023

Indonesian Journal of Aerospace

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The effectiveness of artillery rocket in battlefield is the determined by its impact point dispersion, which may occur due to manufacturing and measurement inaccuracy, initial launch perturbations and atmospheric conditions. Therefore, the objective of this study is to establish model that could predict the impact point dispersion of R-Han 300 rocket using Monte Carlo method. Generic rocket of 6 Degree-of-Freedom model was implemented to investigate the impact point. Initially two simulations with 1000 iterations were carried out, first to study the effect of value uncertainty of every parameter on the impact point dispersion at launch elevation angle 50 degrees, second to study the impact point dispersion caused by value uncertainty of all the parameters at launch elevation angles ranging from 30 to 70 degrees. The second simulation is then repeated with 10000 iterations. This study showed that the dispersion increases as the launch elevation angle increases, except around the optimal launch elevation angle that give the farthest range. Monte Carlo simulation with 10000 iterations showed a better normal distributed data then the simulation with 1000 iterations, but the maximum difference in value of CEP resulted from both simulations is very small, which is 3.16%.

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Section: Monte Carlo Simulationmentioning

confidence: 99%

Impact Point Dispersion Prediction for 300 mm R-Han 300 Artillery Rocket

Riyadl,

Robertus Heru TriHarjanto,

Pujo Widodo

2023

Indonesian Journal of Aerospace

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“…Next, the Monte-Carlo simulation was evaluated to investigate further the model reliability. The uncertainties in quadrotor mass properties, initial conditions, and wind parameters were considered [68]. The disturbances were modeled individually as a Gaussian [69].…”

Section: Monte-carlo Simulationmentioning

confidence: 99%

Validation of the energy consumption model for a quadrotor using Monte-Carlo simulation

Głębocki,

Żugaj,

Jacewicz

2022

Archive of Mechanical Engineering

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Unmanned, battery-powered quadrotors have a limited onboard energy resources. However, flight duration might be increased by reasonable energy expenditure. A reliable mathematical model of the drone is required to plan the optimum energy management during the mission. In this paper, the theoretical energy consumption model was proposed. A small, low-cost DJI MAVIC 2 Pro quadrotor was used as a test platform. Model parameters were obtained experimentally in laboratory conditions. Next, the model was implemented in MATLAB/Simulink and then validated using the data collected during real flight trials in outdoor conditions. Finally, the Monte-Carlo simulation was used to evaluate the model reliability in the presence of modeling uncertainties. It was obtained that the parameter uncertainties could affect the amount of total consumed energy by less than 8% of the nominal value. The presented model of energy consumption might be practically used to predict energy expenditure, battery state of charge, and voltage in a typical mission of a drone.

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“…For example, Liu and Wang [28] investigated the use of TVC to realize the rapid turn in the vertical launch missile system. Studies such as [29] focused on the use of lateral thrusters to reduce the impact point dispersion. Meanwhile, Glebocki and Jacewicz [30] investigated the use of gasodynamic control together with a modified guidance scheme for rocket artillery projectiles.…”

Section: Introductionmentioning

confidence: 99%

Path-Following Control for Thrust-Vectored Hypersonic Aircraft

et al. 2023

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Thrust vector control (TVC) might be used to control aircraft at large altitudes and in post-stall conditions when aerodynamic control surfaces are ineffective. This study demonstrated that the implementation of the TVC on high-speed aircraft is a reasonable solution and might be an alternative when compared to the complicated reaction control system or large aerodynamic control surfaces. The numerical flight dynamics model of the X-15 experimental aircraft was developed and implemented in MATLAB/Simulink and then used to investigate the proposed solution. The obtained results indicate that the aircraft, equipped with full 3D thrust vectoring and two independent horizontal stabilizers to control the roll angle, was able to achieve flight along the path that was defined by a set of waypoints. This paper also highlights the potential benefits and challenges of using TVC as a control method for aircraft. The results of this study contribute to the growing body of research on aircraft control and simulation. Future work can explore the use of TVC for other aircraft with unique configurations and low maneuverability features.

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Study of Model Uncertainties Influence on the Impact Point Dispersion for a Gasodynamicaly Controlled Projectile

Cited by 5 publications

References 33 publications

Impact Point Dispersion Prediction for 300 mm R-Han 300 Artillery Rocket

Impact Point Dispersion Prediction for 300 mm R-Han 300 Artillery Rocket

Validation of the energy consumption model for a quadrotor using Monte-Carlo simulation

Path-Following Control for Thrust-Vectored Hypersonic Aircraft

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