推进-气动耦合的分布式动力翼增升特性

杨敬亭; 王科雷; 周洲; 曾佳

doi:10.7638/kqdlxxb-2025.0065

欢迎来到能源电力期刊网！

English Version 期刊登录

您当前的位置：

首页 >

文章列表页 >

推进-气动耦合的分布式动力翼增升特性

研究专栏——无人机飞发气动综合设计 | 更新时间：2026-05-28

- 推进-气动耦合的分布式动力翼增升特性
- Lift enhancement characteristics of distributed propulsion wing with propulsion-aerodynamic coupling
- 空气动力学学报 2025年43卷第11期页码：97-109
- 作者机构：
  
  1. 西北工业大学航空学院,西安,710072
  2. 飞行器基础布局全国重点实验室,西安,710072
  3. 中国航空工业集团成都飞机设计研究所,成都,610091
- 作者简介：
  
  杨敬亭（2001—），男，四川成都人，硕士研究生，研究方向：飞行器设计. E-mail：yangjingting@mail.nwpu.edu.cn
  王科雷*，副研究员，研究方向：飞行器设计. E-mail：craig-wang@nwpu.edu.cn
- 基金信息：
  
  航空科学基金（2024Z006053001）
- DOI：10.7638/kqdlxxb-2025.0065
  中图分类号： V211.3;V279
- 纸质出版：2025
- 稿件说明：
移动端阅览
杨敬亭, 王科雷, 周洲, 等. 推进-气动耦合的分布式动力翼增升特性[J]. 空气动力学学报, 2025, 43(11): 97−109.

YANG Jingting, WANG Kelei, ZHOU Zhou, et al. Lift enhancement characteristics of distributed propulsion wing with propulsion-aerodynamic coupling[J]. 2025, 43(11): 97-109.
杨敬亭, 王科雷, 周洲, 等. 推进-气动耦合的分布式动力翼增升特性[J]. 空气动力学学报, 2025, 43(11): 97−109. DOI： 10.7638/kqdlxxb-2025.0065

YANG Jingting, WANG Kelei, ZHOU Zhou, et al. Lift enhancement characteristics of distributed propulsion wing with propulsion-aerodynamic coupling[J]. 2025, 43(11): 97-109. DOI： 10.7638/kqdlxxb-2025.0065.

摘要

为提升短距起降无人机的高升力需求与巡航效率，本文提出了一种融合分布式推进与动力增升技术的分布式动力翼增升布局。基于某分布式电推进短距起降无人机技术背景，通过短距起降、巡航多工况数值模拟，分析了该布局的气动-推进耦合特性及流场结构演化，揭示了动力单元数量对升阻特性的影响规律。研究结果表明：在短距起降状态下，可以利用气动-推进耦合作用产生最优的增升减阻效果，在获得高升力系数2.68的同时，升阻比可达14.11，且随着动力单元数量由6增长至18，总升力水平可提升60%以上，而总阻力水平在12动力单元下达到最低，此时构型为增升减阻效果最优的动力分布配置；在巡航状态下，通过增大动力单元数量可有效改善整体升阻特性，当增大至18后，升阻比达到最大。本文研究可为新一代高性能、高机动短距起降飞行器设计提供理论支撑。

Abstract

To reconcile the high-lift demands of short takeoff and landing (STOL) with the requirement for efficient cruise in unmanned aerial vehicles (UAVs)

this paper presents a novel distributed propulsion wing lift enhancement configuration (DPWLEC) that capitalizes on aerodynamic-propulsive coupling. Based on the technical background of a specific distributed electric propulsion (DEP) STOL UAV

numerical simulations for multiple flight conditions

including STOL and cruise

are conducted. The study analyzes the aerodynamic-propulsion coupling characteristics and the evolution of the flow field structure for this configuration

revealing the influence of the propulsor number on the lift and drag characteristics. The research results indicate that during the STOL phase

the aerodynamic-propulsion coupling effect can be utilized to achieve optimal lift enhancement and drag reduction. A high lift coefficient of 2.68 is obtained simultaneously with a lift-to-drag ratio of 14.11. As the propulsor number increases from 6 to 18

the total lift increases by more than 60%. The total drag reaches its minimum value with a configuration of 12 propulsors

which represents the optimal DEP distribution for achieving the best combined lift-enhancement and drag-reduction effect. On the other hand

during the cruise phase

increasing the propulsor number effectively improves the overall lift-to-drag characteristics. After the propulsor number is increased to 18

the lift-to-drag ratio reaches up to a maximum value. These findings can provide theoretical support for the design of a new-generation of high-efficiency

high-maneuverability STOL aircraft.

关键词

Keywords

references

KIM H D, BROWN G V, FELDER J L. Distributed turboelectric propulsion for hybrid wing body aircraft[C]//2008 International Powered Lift Conference Royal Aeronautical Society. , 2008.

HUANG J. Survey on design technology of distributed electric propulsion aircraft[J]. Acta Aeronautica et Astronautica Sinica, 2021, 42(3): 624037 (in Chinese). doi: 10.7527/S1000-6893.2020.24037

DEERE K A, VIKEN J K, VIKEN S, et al. Computational analysis of a wing designed for the X-57 distributed electric propulsion aircraft[C]// 35th AIAA Applied Aerodynamics Conference, Denver, Colorado. Reston, Virginia: AIAA, 2017: 3923. doi: 10.2514/6.2017-3923

LIAO Z Q. Research on the development of hybrid electric propulsion system[J]. Aerospace Power, 2018(2): 45−50 (in Chinese).

LAN H Q. Regional/Trunk Aircraft with Hybrid Electric Propulsion System[J]. Aerospace Power, 2021(06): 41−44 (in Chinese).

ZHANG Y, ZHOU Z, GUO J H. Effects of distributed electric propulsion jet on aerodynamic performance of rear wing[J]. Acta Aeronautica et Astronautica Sinica, 2021, 42(9): 224977 (in Chinese). doi: 10.7527/S1000-6893.2020.24977

GUO J H. Research on aerodynamic design of vertical take-off and landing aircraft coupled distributed ducted fan[D]. Northwestern Polytechnical University, 2022 (in Chinese).

CHEN Y L. Experimental study on the distributed electric propulsion aircraft[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2019 (in Chinese).

STOLL A M, BEVIRT J, MOORE M D, et al. Drag reduction through distributed electric propulsion[C]// 14th AIAA Aviation Technology, Integration, and Operations Conference, Atlanta, GA. Reston, Virginia: AIAA, 2014: 2851. doi: 10.2514/6.2014-2851

NASA. Boundary layer ingestion propulsion: Conceptual design and analysis of distributed propulsion systems[R]. Washington, D. C. : NASA, 2020.

SMITH T, JONES R. Aerodynamic benefits of distributed electric propulsion[J]. Journal of Propulsion and Power, 2018, 34(3): 502−515.

PERRY A T, ANSELL P J, KERHO M F. Aero-propulsive and propulsor cross-coupling effects on a distributed propulsion system[J]. Journal of Aircraft, 2018, 55(6): 2414−2426. doi: 10.2514/1.C034861

WICK A T, HOOKER J R, ZEUNE C H. Integrated aerodynamic benefits of distributed propulsion[C]// 53rd AIAA Aerospace Sciences Meeting, Kissimmee, Florida. Reston, Virginia: AIAA, 2015: 1500. doi: 10.2514/6.2015-1500

CHENG Z Y, YANG Y X, LU J C, et al. Effects of power layout on aerodynamic performance of distributed electric propulsion aircraft[J]. Acta Aerodynamica Sinica, 2024, 42(5): 81−96 (in Chinese). doi: 10.7638/kqdlxxb-2023.0070

LI Z Y, YANG X D, SUN K, et al. Aerodynamic configuration of distributed ducted fan with complex strong interference effect and performance influence[J]. Acta Aeronautica et Astronautica Sinica, 2025, 46(3): 218−237 (in Chinese). doi: 10.7527/S1000-6893.2024.30805

WANG K L, ZHOU Z, GUOJIA H, et al. Propulsive/aerodynamic coupled characteristics of distributed-propulsion-wing during forward flight[J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(2): 132−150 (in Chinese). doi: 10.7527/S1000-6893.2023.28643

HADLEY G. Meet DARPA's X-65: A jet without external control surfaces[J]. Air Force Magazine, 2023, 106(6-7): 2.

MENTER F R. Two-equation eddy-viscosity turbulence models for engineering applications[J]. AIAA Journal, 1994, 32(8): 1598−1605. doi: 10.2514/3.12149

RAJAGOPALAN R G, FANUCCI J B. Finite difference model for vertical axis wind turbines[J]. Journal of Propulsion and Power, 1985, 1(6): 432−436. doi: 10.2514/3.22824

GUOJIA H, ZHOU Z, LI X, et al. An unsteady momentum source method and its application in simulation of hovering rotor[J]. Journal of Northwestern Polytechnical University, 2020, 38(3): 571−579 (in Chinese). doi: 10.1051/jnwpu/20203830571

XU D, XU X P, XIA J Y, et al. Aerodynamic-propulsion coupling characteristics of distributed electric propulsion system[J]. Journal of Aerospace Power, 2024, 39(9): 20220681 (in Chinese). doi: 10.13224/j.cnki.jasp.20220681

ZHANG T, BARAKOS G N. High-fidelity CFD validation and assessment of ducted propellers for aircraft propulsion[J]. Journal of the American Helicopter Society, 2021, 66(1): 1−28. doi: 10.4050/jahs.66.012008

CHEN G Q, BAI P, ZHAN H L, et al. Numerical simulation study on propeller slipstream effect on unmanned air vehicle with propeller engine[J]. Acta Aerodynamica Sinica, 2015, 33(4): 554−562 (in Chinese). doi: 10.7638/kqdlxxb-2014.0013

浏览量

下载量

CSCD

文章被引用时，请邮件提醒。

提交

工具集

关联资源

大展弦比飞行器突风响应数值计算

基于LBM方法的LAGOON起落架噪声预测与降噪方法研究

热防护材料动态烧蚀形貌结构光视觉测量技术

离心通风机降噪研究进展

个体间距对多扑翼气动噪声的影响特性