Robust Aerial Deployment of Mars Airplane with Tilted Folding-Axis
Robust Aerial Deployment of Mars Airplane with Tilted Folding-Axis
复制标题
具有倾斜折叠轴的火星飞机的稳健空中部署
DOI：
10.2514/6.2016-0023
复制
发表时间：
2016
期刊：
影响因子：
--
通讯作者：
A. Oyama
中科院分区：
文献类型：
--
作者：
Koji Fujita;H. Nagai;A. Oyama
折叠翼是用于火星探测的飞机的一种有效的展开机构。在日本，弹簧加载的铰链被认为是火星飞机的展开执行器。铰链扭矩是控制空中展开行为的基本设计变量之一。展开所需的铰链扭矩与展开机构的质量直接相关。由于火星飞机需要彻底减轻质量，因此有必要降低所需的铰链扭矩，同时保持空中部署的高稳健性。本文对空中展开行为的稳健性进行了研究，重点研究了铰链轴倾斜对展开行为的影响。非倾斜铰链轴设计的铰链轴被定义为平行于中心体坐标的X轴。针对飞机的状态定义了判断部署成功或失败的条件。将该条件下的飞机状态裕度设置为安全性评价函数。使用西格玛水平来评估安全性的稳健性，其中西格玛水平是评估函数的平均和标准差的函数。对于稳健性评价，本研究考虑了四个离散参数：下落速度、周围阵风速度、初始俯仰角和高度。对几种倾斜和非倾斜铰链轴的稳健性进行了计算和比较。结果表明，倾斜铰链轴设计可以比非倾斜铰链轴设计以更小的扭矩展开。然后研究了个别情况下的运动，以揭示铰链轴倾斜的影响。结果表明，倾斜铰链轴设计可以在较宽的条件下使外翼攻角为正。因此，气动力帮助展开。在适当的条件下，机翼在没有展开执行器扭矩的情况下展开。
A folding wing is an effective deployment mechanism for the airplane that is used for Mars exploration. A spring loaded hinge is considered as a deployment actuator for Mars airplane in Japan. A hinge torque is one of the primitive design variables to control the aerial deployment behavior. The required hinge torque for deployment is directly concerned with the deployment mechanism mass. Since the Mars airplane requires thorough mass reduction, it is necessary to reduce the required hinge torque while keeping high robustness for the aerial deployment. This paper investigates the robustness of the aerial deployment behavior especially focused on the effect of the hinge axis tilting. The hinge axis of the nontilted hinge axis design is defined to be parallel to the X-axis of the center body coordinates. The conditions to judge whether the deployment succeeded or failed are defined for the state of the airplane. The margins of the airplane state for the conditions are set to the evaluation functions of the safety. The robustness of the safety is evaluated using the sigma level where the sigma level is a function of the average and standard deviation of the evaluation functions. For the robustness evaluation, this study deals with four dispersive parameters: drop velocity, surrounding gust velocity, initial pitch angle, and height. The robustness of several tilted and non-tilted hinge axis designs are calculated and then compared. The result clearly shows that the tilted hinge axis design can deploy with lower torque than the torque of the non-tilted hinge axis design. The motions of the individual cases are then studied to reveal the effect of the hinge axis tilting. It is clarified that the tilted hinge axis design is able to set the angle of attack of the outer wing positive under the wide range of conditions. Therefore, the aerodynamic force assists the deployment. In the appropriate condition, the wings deploy without torque of the deployment actuator.
影响因子：
2.5
作者：
M. Okamoto;A. Azuma
通讯作者：
M. Okamoto;A. Azuma