Optimizing the propulsion of a hypersonic accelerator aircraft of a two-stage aerospace system

Abstract

The paper deals with the propulsion of a hypersonic accelerator aircraft acting as the first stage of a two-stage aerospace system. Optimal and approximately optimal angle of attack programmes are defined on condition that fuel consumption is minimal. The impact of the trajectory inclination finite angle magnitude on the pattern of control programmes and mechanical trajectories is analysed.

About the authors

V. L. Balakin

Samara State Aerospace University

Author for correspondence.
Email: balakin@ssau.ru
Russian Federation

A. A. Bebyakov

Samara State Aerospace University

Email: balakin@ssau.ru
Russian Federation

A. G. Kotchyan

Samara State Aerospace University

Email: balakin@ssau.ru
Russian Federation

References

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