Ascent-stage trajectory of two-stage to-orbit aerospace vehicle and design method

Abstract

The invention discloses an ascent-stage trajectory of a two-stage to-orbit aerospace vehicle and a design method. By dividing primary and secondary ascent stages, an ascent-stage trajectory form is determined; firstly, the position of a separation point is determined; secondly, a secondary trajectory is designed; and thirdly, a primary trajectory is designed. The ascent-stage trajectory of the two-stage to-orbit aerospace vehicle and the design method have the advantages of simple algorithm and efficient calculation and can be widely used for designing ascent-stage trajectories of aerospace vehicles and near space hypersonic airplanes.

Description

technical field [0001] The invention relates to a trajectory and a design method for an ascending section of a two-stage aerospace vehicle entering orbit, and belongs to the technical field of orbiting trajectory design for aerospace vehicles. Background technique [0002] The aerospace vehicle is a new type of space-to-ground transport vehicle powered by an air-breathing combined engine that can shuttle aircraft in dense atmosphere, adjacent space, and space. According to the number of stages of orbiting, it can be divided into two-stage orbiting spacecraft and single Two-stage orbiting aerospace vehicle, while the technical difficulty of two-stage orbiting aerospace vehicle is relatively low, and the first sub-stage adopts air-breathing combined power, and the second sub-stage adopts rocket-powered two-stage orbiting aerospace vehicle (referred to as two-stage Orbiting aerospace vehicles) will form practical capabilities faster. [0003] The ascent segment includes the en...

AI Technical Summary

Problems solved by technology

[0005] Due to the difference in the trajectory form, the trajectory design method for the ascent section of the two-stage launch vehicle cannot be applied to the trajectory design of the ascent section of the two-stage aerospace vehicle

Moreover, the current research on the trajectory design method for the ascent section of the two-stage spacecraft into orbit mainly focuses on the optimization design method of the nominal trajectory in the longitudinal plane, and the design indicators are mostly the best fuel and the shortest time, etc. The positional relationship, the trajectory design of the ascending section cannot meet the space constraint requirements

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