摘要
针对新概念组合式无人机对快速可靠分离技术的需求,本文提出了一种力矩驱动的低冲击柔顺分离机构,开展了力学特性研究、仿真计算分析与分离试验验证。基于正弦加速度函数曲线的柔顺特性,构建机构分离力学模型,采用动量N-S方程和Coulomb摩擦定律,获得了全工况下气动载荷分布规律。采用有限元方法对分离机构开展力学特性分析,根据尺寸参数优化方法对分离机构进行优化设计,有效降低分离机构主要承力部件的集中应力。通过分离动力学仿真计算,初步验证了所构建分离机构模型的柔顺特性,开展了分离机构物理样机在多种分离环境下的解锁分离试验。仿真分析与地面试验结果表明,设计的分离机构具有良好的低冲击柔顺分离特性,本文可为航空航天工程中的可靠分离技术提供设计方法与分析途径。
To meet the demand for fast and reliable separation technology in aerospace engineering,a low-impact compliant separation mechanism driven by torque is proposed.The mechanical characteristics,simulation,and calculation analysis were conducted,and the separation experiment was validated.Based on the compliance characteristics of the sinusoidal acceleration function curve,a mechanical model of the separation mechanism was constructed.The momentum Navier-Stokes equations and Coulomb’s friction law were employed to determine the aerodynamic load distribution under all operating conditions.The mechanical characteristics of the separation mechanism were analyzed using the finite element method,and a dimensional parameter optimization technique was applied to optimize the separation mechanism,effectively reducing stress concentration on its main bearing parts.Through dynamic simulation of separations,preliminary verification of flexibility characteristics in the model of this separation mechanism was achieved.Physical prototype testing demonstrated successful unlocking and separation in various environments.Simulation results along with ground experiments indicate that the proposed separation mechanism exhibits excellent low-impact properties as well as compliant behavior,thus providing a design methodology and analytical approach for reliable aerospace engineering separation technology.
作者
张青松
贾山
陈金宝
龚子轩
蒋希健
ZHANG Qingsong;JIA Shan;CHEN Jinbao;GONG Zixuan;JIANG Xijian(College of Astronautics,Nanjing University of Aeronautics and Astronautics,Nanjing 211106,China;Laboratory of Aerospace Entry,Descent and Landing Technology,Nanjing 211106,China;Key Laboratory of Aerospace Science and Technology for Entry Deceleration and Landing,Nanjing 211106,China;College of Physics,Nanjing University of Aeronautics and Astronautics,Nanjing 211106,China)
出处
《振动工程学报》
北大核心
2025年第12期3030-3038,共9页
Journal of Vibration Engineering
基金
国家科技专项计划资助项目(2021-JCJQ-JJ-0233,23-TQ01-04-ZT-01-017,D050202)
国家自然科学基金资助项目(52075242)
中央高校基本科研业务费资助项目(NT2022026)。
关键词
分离机构
柔顺分离技术
分离动力学
气动特性
separation mechanism
compliant separation technology
separation dynamics
aerodynamic characteristics
