The doctoral dissertation has been divided into eight chapters, of which the first chapter is introductory, and the eighth concludes the dissertation. The list of used literature, as well as the lists of figures, tables, and variables used in the text, are especially singled out. The first introductory chapter brings the motivation for research and an overview of previous research. The goal and hypothesis of the work are set, and the methodology of problemsolving is presented. In the end, an overview of the entire doctoral dissertation is given. The research is based on the following hypotheses: by applying the non-deterministic model of the unguided missile flight, it is possible to determine the functional dependence between mass imbalance and thrust asymmetry with increasing area of impact points dispersion, and to give recommendations for projectile production aiming to reduce dispersion area. The aim of this dissertation is to improve a non-deterministic flight model with six degrees of freedom for unguided projectiles, to show the sensitivity of the trajectory to various disturbances. The model will incorporate the mass imbalance and thrust asymmetry for the selected rocket and will assess the impact of these disturbances on the increase of impact points dispersion area. The second chapter presents a parametric CAD model of a projectile manufactured with certain errors. The whole dissertation tries to solve the problem of the influence of production errors on the flight of the projectile and emphasizes the differences between the ideal and nonideal projectile trajectory, where the latter is burdened with production errors. At the beginning of the chapter, a CAD 3D model of the projectile is given, and it is shown why it is divided into two main parts (components): the spacecraft and the propellant. After that, it is shown how the parameterization of production errors in the CAD 3D model was performed. The newly introduced geometric coordinate system (G-KS) is explained. After that, the production errors are described: errors in the connection of the warhead and the engine chamber. The third chapter describes the adjusted 6DOF flight model of the projectile. The basic differential equations of the 6DOF model are given, where the aerodynamic force and torque are especially elaborated. The reason is that it is necessary to adjust the aerodynamics due to the noncollinearity of the warhead and the engine chamber symmetry axes (due to the faulty produced joint between the warhead and the engine chamber). After that, the inertia characteristics of the projectile are presented, separately for each component: the aircraft and the propellant. For the first time, the reason for the introduction of the CAD 3D model is visible, because its output variables (geometrical and inertial characteristics) become the input for the 6DOF model. Finally, the classic and modified 6DOF model (called G6DOF for the sake of distinction, but also because of the coordinate system in which it was developed) are compared. The fourth chapter presents the software solution of the 6DOF flight model. This is important to explain the interrelationships of individual program parts, but also to explain the capabilities of the program itself as it can incorporate not only manufacturing errors but also many other disturbances (e.g., atmospheric conditions, weapons conditions, etc.). The main program is presented, and it is shown how the production errors are introduced. The setting of differential equations and connections with other parts of the program is further clarified. An example of determining the trajectory of an (ideal) missile is also given, and the flight parameters are compared with the data from the corresponding Firing tables. The 122 mm M-21 GRAD rocket is taken as an example. In the fifth chapter, the impact of production errors is analyzed, and these errors are treated as deterministic variables. The methods of classical analysis of the production errors impact are described, followed by the separate analysis for each of the four previously described production errors: erroneously manufactured joint of the warhead and engine chamber, warhead (or its bore), nozzle, and propellant installation. The first three described errors change the geometrical and inertial characteristics of the component "frame", while the last error relates to the component "propellant". The chapter provides a comparison of the effects for all analyzed errors, first at the maximum allowable angles of noncollinearity i  and then at the same angle for all errors. Finally, the impact point deviation (i.e., the inaccuracy of the missile) is analyzed due to the described errors and the rocket effectiveness on the target. The sixth chapter describes the statistical processing of the simulation results. Errors are treated as nondeterministic variables, and the simulation is performed by the Monte Carlo (MC) method. The MC method is commented at the beginning, and the methods of determining the MC simulation parameters are described: defining the sample size, selecting the probability distribution function according to which the input variables will be dispersed (normal probability, Weibull, or Rayleigh). The parameters included in this MC Monte Carlo simulation are given, and the occurrence of just one and then all four production errors at the same time is simulated separately. The chapter describes methods for estimating the normality of the impact points distribution. Further, it compares the simulation results if the input parameters follow the normal, or if they follow the Rayleigh distribution. All results are compared with the area of the dispersion as stated in the corresponding Firing tables. It is analyzed which error explains most of the dispersion listed in the Firing tables. Chapter 7 describes a statistical analysis of the relationship between production quality levels and projectile precision. The terms "level of production quality" and the "index of potential capacity of the process Cp" (which directly determine the limits of the specification, i.e. the limits of the allowed parameter's value) are introduced. Nine combinations of production quality levels are simulated (where each stage of production can be performed in high-, standardor low- quality) and it is shown not only that one production error is dominant, but also how dominant. This error effect cannot be compensated even by reducing other errors to a minimum. A comparison of the trajectory of an ideal projectile and a projectile produced with the maximum permissible errors is given. Chapter eight gives the conclusion of the doctoral dissertation. Scientific contributions of the dissertation are: 1) improvement of the flight model with six degrees of freedom for unguided projectiles, in such a way as to enable the implementation of statistical simulations and analysis of non-deterministic characteristics of projectiles having the unbalanced mass and asymmetric thrust; 2) determining the functional relationships between mass imbalance and thrust asymmetry and increased impact points dispersion area, by using statistical methods; 3) improving the assessment of the allowable limits of non-deterministic projectile design errors, according to the allowable limits of the projectile impact points dispersion area. Finally, possible directions for further research are given.