宇航学报

宇航学报 ›› 2021, Vol. 42 ›› Issue (10): 1207-1216.doi: 10.3873/j.issn.1000-1328.2021.10.002

• 飞行器设计与力学 • 上一篇    下一篇

一种共轴双旋翼式火星飞行器设计及其试验验证

朱凯杰，唐徳威，沈文清，吕艺轩，赵鹏越，邓慧超，全齐全，孟林智，王彤，邓宗全   


  1. 1. 哈尔滨工业大学机器人技术与系统国家重点实验室，哈尔滨 150001；2. 北京航空航天大学机械工程及自动化学院，北京 100191；3. 北京空间飞行器总体设计部，北京 100094

  • 收稿日期:2020-11-10 修回日期:2021-02-05 出版日期:2021-10-15 发布日期:2021-10-15
  • 基金资助:
    国家自然科学基金(51935005)；国家自然科学基金(51975139)

Design and Experimental Verification of a Coaxial Mars Rotorcraft

ZHU Kai jie, TANG De wei, SHEN Wen qing, LV Yi xuan, ZHAO Peng yue, DENG Hui chao, QUAN Qi quan, MENG Lin zhi, WANG Tong, DENG Zong quan   

  1. 1. State Key Laboratory of Robotics and System, Harbin Institute of Technology, Harbin 150001, China; 2. School of Mechanical Engineering and Automation, Beihang University, Beijing 100191, China; 3. Beijing Institute of Spacecraft System Engineering, Beijing 100094, China

  • Received:2020-11-10 Revised:2021-02-05 Online:2021-10-15 Published:2021-10-15

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1007

摘要： 针对火星飞行器探测需求，提出了一种共轴双旋翼式火星飞行器，基于计算流体力学方法优选了桨叶翼型、平面形状和扭转角等结构参数，基于叶素动量理论建立了旋翼气动力学模型，利用数值模拟方法选择了旋翼转速、旋翼间距和桨叶安装角等飞行参数，设计了原理样机“火星飞鸟-I”的结构与控制系统。构建了火星大气环境模拟器和重力补偿与运动约束装置，开展了模拟火星环境下旋翼式飞行器地面飞行试验，验证了共轴双旋翼式火星飞行器的推进性能，展望了旋翼式火星飞行器技术的发展方向。研究成果对我国开展的火星探测工程具有重要借鉴价值。


关键词: 火星旋翼飞行器, 共轴双旋翼, 悬停特性, 火星大气环境模拟, 试验验证

Abstract: For a Mars aircraft exploration mission, a coaxial Mars rotorcraft is proposed. The structural parameters, such as the blade airfoil, planform, and twist angle, are optimized based on the computational fluid dynamics methods. The aerodynamic model of the rotor is established based on the blade element theory and momentum theory. The flight parameters such as rotor speed, rotor spacing, and blade installation angle are selected based on the numerical simulation methods, which prompt the design of the structure and control system of the prototype “MarsBird I”. A Martian atmosphere simulator and a combined device for gravity compensation and motion constraint are constructed to carry out the ground flight test of the Mars rotorcraft under a simulated Mars environment, which verifies the propulsion performance of the coaxial Mars rotorcraft. Besides, we prospect the research directions of the Mars rotorcraft technology. The research results provide an important reference for China’s Mars exploration project.

Key words: Mars rotorcraft, Coaxial rotor, Hover characteristics, Mars atmosphere simulation, Experimental verification

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