![]() ![]() ![]() The developed numerical simulation might be used in design process of new sensors intended for projectile navigation. The novelty in this paper is the comparison of the IMU errors’ influence on the accuracy of the two control algorithms utilizing lateral pulse jet control. The paper finishes with a short summary of the conclusions shown in Section 4. Section 3 presents the simulational study and its results, followed by the discussion and interpretation. In Section 2.2 the simulational model created in MATLAB/Simulink R2020b is presented. At last, the used control algorithms are shown. The external loads comprised of aerodynamics, gravity, propulsion, and correction thrusters are presented, and this is followed by the description of inertial parameters, atmosphere, and Inertial Measurement Unit modelling approach. The dynamic equations of motion, followed by additional kinematic equations are shown in that section. The prepared article is organised as follows: in Section 2 the mathematical model of the rocket is presented in the Section 2.1 with used assumptions and coordinate systems. The analysis was performed using the Monte Carlo approach. Two types of control algorithms were tested, Multi-Condition Control Algorithm (MCCA) and modified Proportional Navigation Guidance (mPNG). The uncertainties in the aerodynamic parameters, thrust curve, and initial conditions, as well as the uncertainties caused by the Inertial Measurement Unit model and its errors are analyzed. In this paper, the analysis of the impact point dispersion caused by model uncertainties is presented. Monte Carlo analysis of the impact point dispersion due to the missile parameters and atmospheric conditions’ uncertainties was performed in and the impact point dispersion reduction due to high spin motion was analyzed in. The analysis of the robustness of the control algorithm with respect to uncertainty regarding the launch environment and rocket conditions was presented in. IMU errors and noise impact on the guidance were also investigated in. The influence of missile initial conditions’ uncertainties and IMU errors on the impact point dispersion using lateral thrusters for control were investigated in and the influence of uncertainties in rocket parameters on the performance of a cold launch were analyzed in. In the effects of launch condition variability, atmospheric factors, and IMU errors on the guidance accuracy were investigated. In the impact point dispersion due to manufacturing errors using Monte Carlo method was studied. Launch conditions’ uncertainties were studied in. In the impact point dispersion of a lateral pulse jet controlled rocket following a reference trajectory and its robustness to the effects of the measurement noise were studied. ![]() To maximize the accuracy of the projectile, various types of control methods, algorithms, and target detection methods are utilized, such as H ∞ guidance law, proportional navigation guidance and its modifications, various optimal control methods or model predictive approach. Key factors influencing the flight of the object, and the hardest to obtain accurately for modelling, are the aerodynamic characteristics, thrust curve, and initial conditions. Due to the imperfections of modelling of the flight of such objects, unknowns, simplifications, and uncertainties in model parameters, it is important to take into account the various possibilities of scenarios and determine and quantify the dispersion of possible landing points. Determining and lowering the impact point dispersion of an artillery projectile is an important factor when determining its usefulness and effectiveness. ![]()
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