史蒂文斯响度在超声速民机低声爆设计中的应用

王宇航; 徐悦

doi:10.7638/kqdlxxb-2018.0285

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史蒂文斯响度在超声速民机低声爆设计中的应用

专栏——声爆研究 | 更新时间：2026-05-28

- 史蒂文斯响度在超声速民机低声爆设计中的应用
- Application of Stevens' loudness in low-boom design of supersonic civil aircraft
- 空气动力学学报 2019年37卷第4期页码：683-689
- 作者机构：
  
  中国航空研究院前沿技术研究部,北京,100012
- 作者简介：
  
  王宇航(1991-), 男, 山东德州人, 工程师, 研究方向:飞行器总体设计.E-mail:yunmengjingtian@163.com
- 基金信息：
- DOI：10.7638/kqdlxxb-2018.0285
  中图分类号： V211.3
- 纸质出版：2019
- 稿件说明：
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王宇航, 徐悦. 史蒂文斯响度在超声速民机低声爆设计中的应用[J]. 空气动力学学报, 2019, 37(4): 683-689.

WANG Yuhang, XU Yue. Application of Stevens' loudness in low-boom design of supersonic civil aircraft[J]. 2019, 37(4): 683-689.
王宇航, 徐悦. 史蒂文斯响度在超声速民机低声爆设计中的应用[J]. 空气动力学学报, 2019, 37(4): 683-689. DOI： 10.7638/kqdlxxb-2018.0285.

WANG Yuhang, XU Yue. Application of Stevens' loudness in low-boom design of supersonic civil aircraft[J]. 2019, 37(4): 683-689. DOI： 10.7638/kqdlxxb-2018.0285.

摘要

低声爆设计是超声速民机设计中的关键技术之一，其核心问题在于选择合适的声爆衡量参量作为优化目标。将史蒂文斯响度计算方法集成至现有的超声速民机低声爆优化设计平台，并以Seeb-ALR锥体模型为例，分别选取声爆史蒂文斯总响度级与近场最大过压值为优化目标，以锥体轮廓线为优化对象进行低声爆设计。相比Seeb-ALR原始模型，锥体轮廓线优化后的总响度级优化与近场最大过压值优化使最大过压值分别降低了18.4%和40.6%，地面声爆响度级分别降低了2.2PLdB和1.4PLdB。优化结果表明该超声速民机低声爆设计平台实现了史蒂文斯响度方法的应用，可以通过响度级反映对地面人员的影响，并将其应用于低声爆设计。选择不同的声爆评价参量作为优化目标，优化后的模型轮廓线和远近场过压分布形态均存在较大差异，与近场过压最大值优化相比，基于声爆响度级的优化策略能更有效地降低地面声爆。

Abstract

The low-boom design is one of the key technologies for the design of a supersonic civil aircraft. For a low-boom design

one of the key problems is how to choose the appropriate objective

which is associated with the evaluation of low-boom performance. To apply the sonic boom loudness level to low-boom design

this paper introduces the Stevens' loudness method into the existing low-boom optimization design platform for supersonic civil aircraft and uses the Seeb-ALR model as an example. The Stevens' loudness level of the ground boom and the over-pressure value of the near field are selected as the optimization targets

and the cone contour is used as the optimization objective for the low-boom design. The results show that

compared with the original model

the loudness level/near field over-pressure value optimization reduces the maximum over-pressure value by 18.4% and 40.6%

and the ground boom loudness level by 2.2PLdB and 1.4PLdB

respectively. The optimization results verify the applicability of the Stevens' loudness level in the low-sonic design of supersonic civil aircraft

accurately reflecting the impact of boom on ground personnel

which can be used in the low-boom design. Selecting different boom evaluation parameters as the optimization targets

there are large differences between the obtained model optimization contours and the near/far field over-pressure distribution patterns. Compared with the near field over-pressure value optimization

the optimization of boom loudness level can reduce the ground boom loudness more effectively by changing the distribution of over-pressure.

关键词

Keywords

references

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