削面/配平翼飞行器的气动计算及分析

带削面／配平翼的钝双锥外形是高超声速飞行器实现机动飞行的有效途径。该外形具有配平升力大、升阻比大、空间大等特点，可以利用迎风翼面及背风翼面进行配平控制，而且侧向控制翼不仅可以控制侧向配平及稳定，还可以利用不同的扩张角改变飞行器的配平阻力和配平升阻比。研究了此类飞行器的迎风／背风配平控制效率问题，以及飞行器的侧向稳定性问题，并提出了实现滚转控制的技术方案。

Aerodynamic Prediction and Analysis for a Reentry Vehicle with Slice-Ailerons

The first author was also first author of Refs.1, 2, 3, 4, published respectively in 1994, 1996, 2003, and 2003. Refs.1, 2, and 3 dealt with three possible types of reentry vehicle and Ref.4 reviewed the aerodynamic characteristics of European CTV reentry vehicle. In this paper, our aim is to explore the possibility of meeting the maneuvering requirements of hypersonic reentry vehicle with a biconic vehicle with slice-ailerons, which is a promising concept because of its high trimming lift, high trimming lift-to-drag ratio and big inner volume. An engineering model developed from Embedded Newtonian Flow Theory has been presented to estimate the aerodynamic characteristics of the biconic vehicle with slice-ailerons; the comparison of the results with those of N-S equation numerical simulation shows that the accuracy of the presented method is sufficient for the conceptual design and that the correctness and effectiveness of the method are validated. The vehicle can achieve its required trimming by windward control and/or leeward aileron deflection. Windward control has a higher control efficiency; decreasing the windward aileron deflection angle may increase the corresponding trimming angle of attack, which is of much benefit to structural design, joint hinge design and local thermal protection design. Side ailerons can be used to stabilize the vehicle in transverse direction, while bigger deflection angle of side aileron may cause neutral stability, and even instability. Regardless of the selection of windward control or leeward control, side ailerons may make scarcely any difference to the center of pressure, consequently the vehicle may obtain its trimming lift-to-drag ratio and trimming lift to realize different maneuvering abilities through different aileron expansion angles, while the corresponding trimming angle of attack will not be influenced. The present design is neutrally stable in rolling direction. In order to improve the rolling control ability, the windward aileron can be divided into two symmetric parts and when the two parts have the same deflection angle, the vehicle will be trimmed only in pitching plane. If and only if two parts have different angles, i.e. if and only if a differential control model is adopted, the vehicle can not only obtain its trimming in pitching plane, but also generate rolling moment, accordingly can control its rolling movement effectively. The present work indicates that the biconic vehicle with slice-ailerons is one of the feasible choices for hypersonic maneuver, and should be investigated further in the future.