12. Methodological Support for Initial Phase Optimization of Projecting Design, Trajectory Parameters and Rocket Object Motion Control Programs
12. Methodological Support for Initial Phase Optimization of Projecting Design, Trajectory Parameters and Rocket Object Motion Control Programs 
Aksyonenko A. V., Baranov E. Y., Gursky A. I., Klochkov A. S., Morozov A. S., Alpatov A. P., Sen’kin V. S., SyutkinaDoronina S. V.
Yangel Yuzhnoye State Design Office, Dnipro, Ukraine Institute of Technical Mechanics (National Academy of Sciences of Ukraine, State Space Agency of Ukraine), Dnipro, Ukraine 
Kosm. teh. Raket. vooruž. 2018, (2); 101116 
https://doi.org/10.33136/stma2018.02.101 
Language: Russian 
Annotation:
The main scientific and methodological propositions for designing singlestage guided missiles with main solid rocket motors that are intended for delivering payload to the given spatial point with required and specified kinematic motion parameters are defined. The aim of the article is to develop methodology for the early design phase to improve the basic characteristics of guided missiles, including formalization of complex problem to optimize design parameters, trajectory parameters and motion control programs for guided missiles capable of flying along the ballistic, aeroballistic or combined trajectories. The task is defined as a problem of the optimal control theory with limitations in form of equality, inequality and differential constraints. An approach to program forming is proposed for motion control in the form of polynomial that brings the problem of the optimal control theory to a simpler problem of nonlinear mathematical programming. When trajectory parameters were calculated the missile was regarded as material point of variable mass and the combined equations for centerofmass motion of the guided missile with projections on axes of the terrestrial reference system were used. The structure of the mathematical model was given along with the calculation sequence of criterion functional that was used for optimization of design parameters, control programs and basic characteristics of the guided missile. The mathematical model of the guided missile provides adequate accuracy for design study to determine: overall dimensions and mass characteristics of the guided missile in general and its structural components and subsystems; power, thrust and consumption characteristics of the main engine; aerodynamic and ballistic characteristics of the guided missile. The developed methodology was tested by solving design problems. Applications of the developed program were studied to present the research results in a userfriendly form.

Key words: complex problem of the optimal control theory, problem of nonlinear mathematical programming, main solid rocket motor, limitations for motion parameters and basic characteristics of the object 
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