Comparing Aerial-Deployment-Mechanism Designs for Mars Airplane
Comparing Aerial-Deployment-Mechanism Designs for Mars Airplane
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DOI：
10.2322/tjsass.59.323
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发表时间：
2016
影响因子：
1.1
通讯作者：
Koji Fujita;H. Nagai
中科院分区：
文献类型：
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作者：
Koji Fujita;H. Nagai
使用飞机探索火星将带来新的科学发现。飞机可以飞行数百至数千公里并获取高分辨率数据，这是漫游车和卫星无法实现的。此类飞机需要紧凑的部署机构并产生足够的升力以在稀薄的火星大气中飞行。然而，现有的概念设计方法没有考虑部署机制。本文提供了用于火星探索的飞机的概念设计方法，其中包括对与空中部署机制相关的规格的基本估计。这种概念设计方法涉及两种类型的展开机制：折叠式和充气式。比较了具有不同展开机制的飞机的规格。设计结果定量表明，对于短翼展设计，充气式机翼更轻，对于长翼展设计，折叠式机翼更轻。在长翼展条件下，由于翼梁半径小和弯矩大，所需的充气压力增加，充气机翼的质量增加。最后，根据构造方法，提出了可展开机翼火星飞机的可行规格。
Employing airplanes for Mars exploration will lead to novel scientific discoveries. Airplanes can fly over several hundreds to thousands of kilometers and obtain high-resolution data, which is impossible for rovers and satellites to achieve. Such airplanes would require deployment mechanisms to be compact and produce enough lift force to fly in the thin Martian atmosphere. However, existing conceptual design methods do not consider deployment mechanisms. This paper provides the conceptual design method of an airplane intended for Mars exploration that includes a basic estimation of the specifications related to the aerial deployment mechanisms. This conceptual design method deals with two types of deployment mechanisms: a folding type and an inflatable type. The specifications of the airplanes with different deployment mechanisms are compared. The design results quantitatively show that an inflatable type wing is lighter for short wingspan design and a folding type wing is lighter for long wingspan design. The mass of the inflatable wing increases in long wingspan conditions since the required inflation pressure increases owing to the small spar radius and large bending moment. Finally, feasible specifications of the Mars airplane with deployable wings are proposed as a result of the constructed method.