从总体设计角度透视高超声速飞行器边界层转捩问题

李志文; 袁海涛; 黄斌; 张增辉; 于新源

doi:10.7638/kqdlxxb-2020.0061

从总体设计角度透视高超声速飞行器边界层转捩问题

doi: 10.7638/kqdlxxb-2020.0061

北京机电工程总体设计部，北京　100854

详细信息

作者简介:
李志文^*（1978-），男，湖南永顺人，研究员，研究方向：飞行器总体设计. E-mail：66473583@qq.com

中图分类号: O357.4⁺1
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- 被引次数: 0
出版历程
- 收稿日期: 2020-04-03
- 修回日期: 2020-07-01
- 录用日期: 2020-08-21
- 网络出版日期: 2020-11-10
- 刊出日期: 2021-08-25

The hypersonic boundary-layer transition: a perspective from the view of system design

The System Design Institute of Mechanical-Electrical Engineering, Beijing　100854, China

摘要

摘要: 边界层转捩对飞行器总体性能影响很大，按照弹道式再入、再入机动、高超声速滑翔、高超声速巡航四类飞行器进行分类，与边界层转捩相关的典型问题可归结为气动力、气动热及掺混效率三类，相应带来飞行稳定性与配平能力、落点散布、防热风险、飞行器减重、推进系统优化等问题。针对边界层转捩控制问题，从总体设计方面可采取弹道设计、翼载荷控制、外形设计、材料选择等措施，推迟或诱发转捩，以达到减阻、减热、掺混等设计目标。总体设计单位应重视开展静音风洞试验，充分利用飞行任务资源积累转捩研究基础数据，努力提高理论分析与预示能力，牵引开发高效、高精度的转捩分析工具。
- 边界层转捩 /
- 高超声速飞行器 /
- 总体设计
Abstract: The boundary-layer transition (BLT) has a great impact on the performance of hypersonic vehicles. Typical BLT problems are reviewed concerning hypersonic vehicles with four different types of trajectories known as ballistic reentry, maneuverable reentry, hypersonic glide, and hypersonic cruise. Relating issues are discussed including dynamic stability, trim, impact point dispersion, thermal protection, vehicle weight reduction, and propulsion system optimization, etc., all of which can be attributed to aerodynamic force, aeroheating, and mixing efficiency that BLT impacts directly. Potential methods are suggested to control BLT for system design including adjustments of trajectory, wing load, and aerodynamic configuration, and selection of proper materials, etc., for drag reduction, aeroheating alleviation, and mixing efficiency enhancement. It is beneficial for system-design institutes to utilize quiet wind-tunnel and flight tests to acquire more experience and knowledge about BLT. Efforts should be made to enhance the capability of developing efficient and precise theoretical analyses and prediction tools.
- boundary-layer transition /
- hypersonic vehicle /
- system engineering

HTML全文

图 1 边界层转捩的发展过程

Figure 1. The development of boundary-layer transition

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图 2 转捩的路径（根据参考文献[30]略作修改）

Figure 2. The transition path（Slightly modified based on Ref.[30] ）

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图 3 惯性弹头在边界层转捩期间角运动情况^[32]

Figure 3. The motion of a flight vehicle during the boundary-layer transition^[32]

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图 4 高超声速钝体流动特点^[43]

Figure 4. A sketch of the flow around a hypersonic blunt body^[43]

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图 5 X-37B外形^[45]

Figure 5. The X-37B configuration^[45]

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图 6 BFR飞船外形^[46]

Figure 6. The BFR ship configuration^[46]

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图 7 IXV飞行弹道攻角时间历程^[52]

Figure 7. The time history of the angle-of-attack of the IXV^[52]

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图 8 HTV-1外形^[40]

Figure 8. The HTV-1 configuration^[40]

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图 9 航天飞机再入飞行走廊及参考飞行剖面^[59]

Figure 9. The operational entry corridor and reference drag profile^[59]

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图 10 X-43前体迎风面锯齿设计^[65]

Figure 10. The boundary-layer trips of X-43^[65]

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图 11 X-51风洞试验研究的三种前体迎风面锯齿^[66]

Figure 11. Three types of boundary-layer trips for X-51A wind-tunnel tests^[66]

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