四旋翼火星飞行器动力系统驱动方法与试验验证

  • 孙宇宏 ,
  • 邓慧超 ,
  • 郭鲲 ,
  • 谢达 ,
  • 邱昊洋 ,
  • 李一川 ,
  • 唐博 ,
  • 邓宗全
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  • 1. 北京航空航天大学
    2. 北京空间飞行器总体设计部
    3. 中国电科五十八所
    4. 哈尔滨工业大学

收稿日期: 2026-06-01

  修回日期: 2026-09-11

  网络出版日期: 2026-09-20

Driving Method and Experimental Verification of Power System for Mars Quadrotor Aircraft

  • SUN Yu-Hong ,
  • DENG Hui-Chao ,
  • GUO Kun ,
  • XIE Da ,
  • QIU Hao-Yang ,
  • LI Yi-Chuan ,
  • TANG Bo ,
  • DENG Zong-Quan
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Received date: 2026-06-01

  Revised date: 2026-09-11

  Online published: 2026-09-20

摘要

火星大气稀薄的环境特征,以及四旋翼火星飞行器独特的可折叠结构,对飞行器动力系统的响应速度、抗扰性能和转矩脉动抑制能力提出了严苛挑战。针对传统永磁无刷直流电机驱动存在扭矩脉动、有感磁场定向控制(FOC)在火星极端环境下可靠性低等问题,提出一种基于无感FOC技术的动力系统快速响应驱动方法。首先建立飞行器位姿动力学与旋翼主导气动力模型,明确动力系统转速与飞行器姿态调控的映射关系;在传统FOC控制框架下,设计基于扩展卡尔曼滤波器(EKF)的无感观测器,引入火星环境精确转矩模型提升转子位置与转速的估计精度,将自抗扰控制器(ADRC)应用于转速外环,增强系统抗扰特性与动态响应能力;同步设计集成电源管理、功率驱动等功能模块的专用电机驱动硬件,保障算法工程实现。通过火星四旋翼飞行仿真、动力系统响应特性测试及模拟火星大气环境的实机飞行试验验证所提方法的有效性,仿真确定电机峰值扭矩的关键选型依据,动力系统测试表明电机阶跃转速响应无超调且加减速响应性能优异,实机实验中飞行器可平稳完成起飞-悬停-爬升-降落全飞行流程。结果表明,本文所提驱动方法显著改善了动力系统动态响应性能,飞行器在模拟火星大气环境中可维持良好的飞行稳定性。

本文引用格式

孙宇宏 , 邓慧超 , 郭鲲 , 谢达 , 邱昊洋 , 李一川 , 唐博 , 邓宗全 . 四旋翼火星飞行器动力系统驱动方法与试验验证[J]. 航空学报, 0 : 1 -0 . DOI: 10.7527/S1000-6893.2026.34018

Abstract

The rarefied Martian atmosphere and the unique foldable structure of Mars quadrotor aircraft pose severe challenges to the response speed, disturbance rejection and torque ripple suppression capability of the vehicle power system. To address the torque ripple issue of traditional permanent magnet brushless DC motor drives and the low reliability of sensored field-oriented control (FOC) in extreme Martian environments, this paper proposes a fast-response driving method for power systems based on sensorless FOC. Firstly, the pose dynamics model of the aircraft and the domi-nant aerodynamic model of rotors are established to clarify the mapping relationship between motor speed and aircraft attitude regulation. Within the conventional FOC framework, a sensorless observer based on the extended Kalman filter (EKF) is designed. An accurate torque model adapted to the Martian environment is adopted to improve the esti-mation accuracy of rotor position and rotational speed. An active disturbance rejection controller (ADRC) is deployed in the outer speed loop to enhance the system's anti-disturbance performance and dynamic response. Meanwhile, dedicated motor drive hardware integrating power management, power drive and other functional modules is devel-oped to realize the proposed algorithm in engineering practice. The effectiveness of the proposed method is verified via flight simulation of the Mars quadrotor, dynamic characteristic tests of the power system, and real flight experi-ments under simulated Martian atmospheric conditions. The simulation results provide critical references for the selec-tion of motor peak torque. Test results show that the motor achieves step speed response without overshoot and de-livers excellent acceleration and deceleration performance. In real flight tests, the aircraft completes the full flight en-velope including takeoff, hovering, climbing and landing smoothly. The results demonstrate that the proposed driving method greatly improves the dynamic response of the power system, and the aircraft maintains excellent flight stability in the simulated Martian atmospheric environment.

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