Aerospace Technic and Technology

The complex problem of the simultaneous optimization of the control programs and design parameters of the controlled single-stage rocket with cruise solid propellant rocket engine is formulated. The problem is formulated as an problem of optimal control theory with limitations in the form of equalities and differential constraints. The structure of the optimized parameters of the solid propellant rocket engine includes design parameters of the controlled solid propellant rocket and parameters characterizing the programs of the motion control of the controlled solid propellant rocket and parameters characterizing the motion at the active section of the trajectory. The elements of the mathematical model of the controlled solid propellant rocket are presented what can be used to enable the problem of optimal control theory to be reduced to the nonlinear mathematical programming problem with limitations in the form of equalities and differential constraints. The modified by the author method of gradient optimization is offered for solving the above problem what can be used to determine the optimal motion control programs in the given class of functions and rational values of optimized parameters of the controlled solid propellant rocket at the initial phase of rocket design.

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