基于DIC的无人机发射系统可靠性应急评估
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V216.8

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DIC-Based UAV Launch System Emergency Reliability Evaluation
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    摘要:

    火箭助推零长发射作为高速无人机的主流起飞方式,其多刚体连接结构的动态稳定性是决定能否发射成功的关键。针对发动机异常振动可能导致的火箭-机体连接位姿偏移问题,提出了一种基于数字图像相关技术的现场应急评估方法。通过构建适配野外环境的简易光学测量系统,实现了火箭助推系统位移场的实时捕捉与分析。针对非实验室条件下的散斑缺失问题,利用无人机复合材料表面自然纹理与火箭筒体加工痕迹作为替代散斑源,结合灰度自适应算法提升匹配精度。测试结果表明,发动机转速升至96 000 r/min时,火箭-机体水平位移差为0.3像素(对应物理位移0.12 mm),垂直位移差为0.5像素(对应物理位移0.20 mm),远低于安全阈值(±2 mm)。后续多次现场发射验证中,系统位姿偏移量标准差保持在0.15 mm以内,发射成功率达100%。

    Abstract:

    In view of the fact that rocket-assisted zero-length launch (ZLL), as the mainstream takeoff method for high-speed UAVs, relies on the dynamic stability of its multi-rigid-body connected structure, which is critical to the success of the launch, a field emergency assessment method based on digital image correlation (DIC) technology has thus been proposed to address the rocket-body connection pose deviation brought about by abnormal engine vibrations. By constructing a simplified optical measurement system adapted for the field environment, a real-time capture, as well as an analysis of the displacement field of the rocket booster system, can be achieved. To address the lack of speckle patterns under non-laboratory conditions, natural textures on the surface of UAV composite materials and processing marks on the rocket body are utilized as alternative speckle sources, combined with grayscale adaptive algorithms so as to improve matching accuracy. Test results show that when the engine speed rises to 96,000 revolutions per minute (r/min), the horizontal displacement difference between the rocket body is 0.3 pixels (corresponding to a physical displacement of 0.12 mm), and the vertical displacement difference is 0.5 pixels (0.20 mm), which is far below the safety threshold (±2mm). In subsequent multiple field launch verifications, the standard deviation of the system pose offset remains within 0.15 mm, with the launch success rate reaching 100%.

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蒋 寒,罗晨辰.基于DIC的无人机发射系统可靠性应急评估[J].湖南工业大学学报,2026,40(3):49-54.

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  • 在线发布日期: 2026-03-27
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