高马赫数临近空间无人机主要总体参数设计方法

doi:10.7527/S1000-6893.2016.0255

Abstract

Abstract:

An improved method is proposed for preliminary sizing in conceptual design of a near-space high supersonic unmanned aerial vehicle (HSUAV). This improved method is aimed to enhance reliability of the preliminary sizing. An iterative sizing process is developed, in which the aerodynamic and propulsion models with higher applicability and accuracy are integrated into traditional methods of constraint analysis and mission analysis. The aerodynamic model is established using the parametric method. The aerothermodynamic model of the propulsion system is achieved by treating each stream as the one-dimensional flow of a perfect gas. With the method proposed, the preliminary sizing process in the conceptual design of the near-space high supersonic unmanned aerial vehicles is accomplished. The results show that sizing parameters are converged after several iterations, and there exist significant differences between the result obtained from the traditional method and that from the improved method. The preliminary sizing results obtained from the method proposed in the paper are more reliable due to higher fidelity of the aerodynamic and propulsion models.

Key words: unmanned aerial vehicle, conceptual design, near space, high supersonic speed, constraint analysis, mission analysis

CLC Number:

V221

YOU Lianxing, YU Xiongqing. Preliminary sizing method for near-space high supersonic unmanned aerial vehicles[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2017, 38(4): 220514-220514.

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Preliminary sizing method for near-space high supersonic unmanned aerial vehicles

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