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접이식 직렬날개형 공중투하 무인비행체의 공력 모델링 및 시뮬레이션

An Aerodynamic Modeling and Simulation of a Folding Tandem Wing Type Aerial Launching UAV

  • 투고 : 2018.07.11
  • 심사 : 2018.10.29
  • 발행 : 2018.12.30

초록

공중투하형 무인비행체는 비행성능의 극대화 및 모기체 탑재시의 소요공간 최소화를 위하여 접이식 직렬날개를 주로 사용한다. 이러한 접이식 직렬날개는 전방날개의 후류에 의한 후방날개 간섭문제, 날개 전개시 전후방 날개에 걸리는 피봇 모멘트의 불균형 등 일반적인 형태의 고정익 비행체와 다른 독특한 공기역학적 문제를 가지고 있다. 이에 본 논문에서는 유한체적법 기반의 전산유체역학을 통하여 여러 경우에 대하여 모델링 및 시뮬레이션을 수행하였으며 접이식 직렬날개 방식 비행체의 여러 공기역학적 현상에 대해 분석하였다. 그 결과 받음각 변화에 따른 전방날개에 의한 후류영향을 최소화하기 위하여 전방 날개를 후방날개보다 수직방향으로 높게 설치할 필요가 있었다. 또한 공력에 의한 피봇모멘트를 고려시 전방날개에 비하여 후방날개가 훨씬 빠른 속도로 펼쳐질 수 있으므로 날개 펼침 기구 개발 시 이에 대한 고려가 필요함을 확인하였다.

The aerial launching UAV(Unmanned Aerial Vehicle) mainly uses a set of folding tandem wings to maximize flight performance and minimize the space required for mounting in a mothership. This folding tandem wing has a unique aerodynamic problem that is different from the general type of fixed wing aircraft, such as the rear wing interference problem caused by the wing of the front wing wake and vortex, and the imbalance of the pivot moment applied to the front and rear wings when the wing is deployed. In this paper, we have modeled and simulated various cases through computational fluid dynamics based on the finite volume method and analyzed various aerodynamic phenomena of the tandem wing type aircraft. We find that the front wing shall be installed higher than the rear for minimizing the wake influence and the rear wing can be deployed faster than the front because of the pivot moment due to aerodynamic forces. Also, considering the pivot moment due to aerodynamic force, the rear wing can be deployed much faster than the front wing. Therefore, it is necessary to consider it when developing the wing deploy mechanism.

키워드

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Fig. 1. Tandem wing type aerial launching UAVs, above : Coyote UAV, below : 9M61 UAV

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Fig. 2. Mesh models for simulation (7.6million elements).(above) ISO view of total elements (below)detail view of UAV skin elements

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Fig. 3. Configuration of aerial launching UAV for analysis(vertical fins and propellers are not displayed)

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Fig 4. Configuration comparison FWD High and FWD Low

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Fig. 5. Angle of attack vs pitching moment coefficient

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Fig. 6. Angle of attack vs lift drag ratio

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Fig. 9. Influence of fuselage boundary layer(above : FWD High, below : FWD Low)

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Fig. 10. Wing deploy angle and pivot moment

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Fig. 11. Wing deploy angle vs pivot moment(angle of attack : 0deg)

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Fig. 7. (above) Streamlines of FWD High Configuration (AOA=8deg), (Below) Wing tip vortex of forward wing (AOA=8deg)

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Fig. 8. (above) Streamlines of FWD Low Configuration (AOA=8deg), (Below) Wing tip vortex of forward wing (AOA=8deg)

Table 1. Dimension parameters of aerial launching UAV

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Table 2. Rear wing aerodynamic forces of various configuration

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참고문헌

  1. B. J. Brinkworth (2016) "On the aerodynamics of the Miles Libellula tandem-wing aircraft concept, 1941-1947", Jounal of Aeronautical History
  2. Tony S. Tao and R. John Hansman (2016) "Development of an In-Flight Deployable Micro-UAV", 54th AIAA Aerospace Sciences Meeting Paper No. 2016/02
  3. Nurhayyan H. Rosid, Irsyad Lukman E., Ahmad Fadlillah M., and M. Agoees Moelyadi. (2018) "Aerodyamic Characteristics of Tube-Launched Tandem Wing Unmanned Aerial Vehicle", 5th International Seminar of Aerospace Science and Technology
  4. H. Stone, K.C. Wong (1997) "Preliminary Design of a Tandem-Wing Tail Sitter UAV Using Multi-Disciplinary Desing Optimisation", International Aerospace Congress, Sydney, February 1997, p707-720
  5. B. Rajesh Kumar, C. Reginald, R. Sivasankaran, S. Vignesh, B. Ragavan, Vasudevan G. & Dharmahinder Singh Chand (2017) "Real time Characteristics of Tandem Wing UAV" Global Journal of Researches in Engineering Vol 17 Issue 1
  6. Liang Gao, Changle Li, Hongzhe Jin, Yanhe Zhu, Jie Zhao and Hegao Cai (2017) "Aerodynamic characteristics of a novel catapult launched morphing tandem-wing unmanned aerial vehicle", Adavanes in Mechanical Engineering Vol 9(2) 1-15
  7. Daniel Raymer (2012) "Aircraft Design : A Conceptual Apporach, 5th Edition", AIAA Education Series