ANALYSIS OF THE INFLUENCE OF THE CONFIGURATION OF MAIN ENGINES ON THE EFFICIENCY OF THE GUIDANCE SYSTEM OF A SPACE LAUNCH VEHICLE

The paper investigates the influence of the configuration of the control surfaces of a space launch vehicle (SLV), in the most critical section of the flight phase of the first stage, on the efficiency of the guidance system. As the control surfaces are considered the main vectored engines with variable thrust vector. At present considerable efforts have been made in the Russian Federation to develop reusable space launch vehicles, which will reduce production costs, as well as the reuse of the first stage will reduce the landing operations area, which will have a positive effect on the ecology of the surrounding area. When developing a perspective reusable space launch vehicle, an analysis of the influence of the number of engines and the variant of their configurations on the stability and controllability will allow predicting the advisability of choosing the layout of these engines, at the stage of preliminary design. The analysis was effected in the pitch and yaw channels, using the perturbation equation of motion of the SLV. The conducted computation of the dependence of the controlled and disturbing moment on the flight time, as well as the loading of the control elements allowed to exclude unacceptable layouts and to choose the most perspective and effective variants of the location of the SLV main engines. In the early stages of development of reusable SLV, this result will be a necessary tool for solving problems of controllability at the predesign stage, and evaluation of the degree of unification of the 1st and 2nd stage recovery block main engines.

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