Development of a test flight mission for simulation of aircraft motion on the active section of the trajectory

The work is devoted to the development of a test flight mission for a launch vehicle. The relevance of the topic is due to the fact that the synthesis of a control system in modern times is usually based on digital and / or semi-natural simulation of the movement of an aircraft. The task is to synthesize the parameters of the corrective devices of the control system. In this case, it is necessary to know the input task of the control system, that is, to have a flight task. The very task of obtaining a flight mission is very difficult, since it is necessary to take into account both the characteristics of the rocket and engines considered in their models, and external influencing factors: the impact of the Earth and the atmosphere. Control and overload limitations must also be taken into account. As a result, the laws of motion of the aircraft are complex, depending on the type of maneuver and the selected section of the trajectory. The paper considers only the active part of the motion trajectory. The applied coordinate systems, the equations of motion of the center of mass are considered, taking into account the influence of the Earth and the aerodynamics of the apparatus. The control of movement by changing the thrust of engines is considered. All the necessary formulas for calculating the trajectory, the necessary assumptions are given. For the entire program trajectory, the coefficients of the model of the perturbed motion of the launch vehicle were calculated. The computer simulation of the above methodology for calculating the test flight task was carried out, the graphs obtained from the results of the simulation are shown, allowing us to conclude that the main restrictions on the program trajectory are met. Based on this, we can assume that the received flight task can be used at the stage of preliminary development of the control system for a reusable single-stage launch vehicle.