变结构微小空间飞行器释放与运动特性研究
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摘要
变结构微小空间飞行器是一类具有伸展结构,在发射过程中从折叠状态展开至规定工作形态的飞行器,展开成型后空间飞行器将保持固定结构进入自由飞行阶段。本文针对其结构和工作特点,应用理论分析、数值模拟和试验研究相结合的手段,对变结构微小空间飞行器的释放发射、自由飞行过程进行了系统研究,获得了该飞行器运动特点和动力学特性,主要研究内容包括以下几方面：
1.对变结构微小空间飞行器的主要工作系统,包括动力装置、轴向展开机构和径向展开机构等,完成了结构设计,并对各分系统的结构组成和工作原理进行了分析；对变结构微小空间飞行器系统的任务要求和主要计算参数进行了说明：建立了空间飞行器的时序工作流程方案,系统分析了各时序工作任务,得到了变结构微小空间飞行器在整个运行过程中的时序工作特点。
2.设计了固体火箭发动机内弹道性能测试试验和变结构微小空间飞行器地面释放发射试验,对动力装置的工作性能和飞行器的释放发射过程进行了研究。采用高速摄像及多通道瞬态信号记录仪等试验仪器对试验过程进行记录和数据采集,初步探讨了点火药量对火箭发动机内弹道性能的影响,时序工作下的空间飞行器释放发射过程运动特点,获得了系统动力装置和整体释放发射的工作特点与运动发展历程,为数值模拟和工程设计提供了宝贵数据。
3.建立了各分系统的数值研究模型,通过数值模拟分析得到各分系统的运动规律和工作性能。采用内弹道学和固体火箭发动机设计理论建立了动力装置的数值研究模型,并对释放火箭发动机进行了不同点火药量的数值研究,对比试验结果得到固体火箭发动机压力和推力性能随点火药量的变化规律；采用结构动力学方法描述柔性体变形的模态求解模型,结合接触碰撞的连续求解方法,建立了展开机构的动力学模型,通过数值研究得到了轴向展开机构和径向展开机构的运动特性和动力响应。
4.变结构微小空间飞行器在释放发射过程中经历了轴向展开、径向展开两次主要结构变化,期间伴随接触碰撞等行为,系统的运动变化复杂。采用多体系统动力学方法对释放发射阶段的结构变化和系统动力学发展进行了数学描述,建立了变结构微小空间飞行器释放发生过程的数值研究模型,并对理想工况和非理想工况下飞行器绕行一周的轨道运动和姿态变化进行了研究分析,通过数值研究和试验研究得到了系统在释放发射过程中的运动特性和动力学响应,讨论了飞行器在不同初始条件下的姿态变化情况,获得飞行器系统工作姿态在不同工况下的变化规律。
5.针对在长时间的运行过程中,空间飞行器系统能量缓慢损失的问题,引入能量耗散系数,推导建立变结构微小空间飞行器长期自由飞行过程能耗研究模型,探讨分析了在特定假设条件下,空间飞行器系统在线性耗散常系数和非线性抛物线型耗散系数作用下的一些轨道和姿态运动的变化情况,并通过数值仿真预测飞行器系统的稳定工作时长。
本文研究不仅为飞行器结构变化动态研究提供途径,也可作为变结构微小飞行器系统结构工程设计与优化、姿态控制规划提供相应的理论依据。
Variable structure micro-spacecraft(VSMS) has a sort of expansion mechanism, which spread to prescriptive work structure from the state of folded style. The aircraft will keep fixed structure during free flight process. In this dissertation, aiming as characteristics of structure and performance, a novel method using theory analysis, numerical simulation and experiment is applied to investigate systemically the process of releasing-launching and free flight. The operational principle、kinetic characteristics and dynamic property of VSMS was obtained. The major works were done in this thesis as follows.
1. The central work system of VSMS includes power installation、axial expansion mechanism and radial expansion mechanism, et al. The structure design is completed. The structure form and operational principle of each subsystem are analysed. Mission demands and primary technology insex are introduced. Time sequential work flow scheme is set up, each time sequential operation mission is analysed systemically, the time sequential operation characteristics of VSMS are obtained.
2. The interior ballistic test of solid rocket motor and ground releasing-launching test of VSMS are designed, the operating performance on power installation and releasing-launching process are researched. The test process is recorded by high-speed video recorder, and the data is gathered by multichannel instantaneous recorder. The effect of igniting charge mass on interior ballistic performance of solid rocket motor and motion performance under releasing-launching are discussed elementarily. Expanding course of power installation and the system during releasing-launching phase is achieved. The valuable data is offered for numerical simulation and engineering project.
3. The mathematical models for subsystem are established. According to numerical simulation, the subsystem motion laws and performance characteristics are analysed. The model of power installation is educed with interior ballistics and designed theoty of solid rocket motor. The numerical study with different igniting charge mass of releasable solid rocket motor. Veriety laws on pressure and thrust of solid rocket motor is obtained by comparing with test data. The mode model of flexible body is adopted; a dynamic model of expansion mechanism is established with continuous inpact method. The performance characteristics and dynamic response are researched with simulation.
4. VSMS experiences two important structure variety of axial and radial expansion, contact-impact accompanies variable process, and the system motion development is complicated. The system structure transformation and dynamic development is described based on mulrybody systems method during releasing-launching phase. The VSMS model of releasing-launching phase is established, orbital and attitude movement of ideal and nonideal operating condition is studied for running a circle. The motion characteristics and dynamic response are obtained at the stage by numerical and test study, attitude movement under different initial conditions is discussed, and the work attitude laws is summarized.
5. For research the problem about energy tardo loss in the long running period, a VSMS energy dissipation model is enduced using energy dissipation coefficient. Some conditions about orbit and attitude movement with linearity constant coefficient and nonlinear parabola style coefficient is discussed in given hypothesis, and stable work time of VSMS is forecasted.
This research provides an approach to study dynamic structure variety of spacecraft. It also can supply vital reference to the structural engineering design and optimization as well as the programming of attitude control.
1.对变结构微小空间飞行器的主要工作系统,包括动力装置、轴向展开机构和径向展开机构等,完成了结构设计,并对各分系统的结构组成和工作原理进行了分析；对变结构微小空间飞行器系统的任务要求和主要计算参数进行了说明：建立了空间飞行器的时序工作流程方案,系统分析了各时序工作任务,得到了变结构微小空间飞行器在整个运行过程中的时序工作特点。
2.设计了固体火箭发动机内弹道性能测试试验和变结构微小空间飞行器地面释放发射试验,对动力装置的工作性能和飞行器的释放发射过程进行了研究。采用高速摄像及多通道瞬态信号记录仪等试验仪器对试验过程进行记录和数据采集,初步探讨了点火药量对火箭发动机内弹道性能的影响,时序工作下的空间飞行器释放发射过程运动特点,获得了系统动力装置和整体释放发射的工作特点与运动发展历程,为数值模拟和工程设计提供了宝贵数据。
3.建立了各分系统的数值研究模型,通过数值模拟分析得到各分系统的运动规律和工作性能。采用内弹道学和固体火箭发动机设计理论建立了动力装置的数值研究模型,并对释放火箭发动机进行了不同点火药量的数值研究,对比试验结果得到固体火箭发动机压力和推力性能随点火药量的变化规律；采用结构动力学方法描述柔性体变形的模态求解模型,结合接触碰撞的连续求解方法,建立了展开机构的动力学模型,通过数值研究得到了轴向展开机构和径向展开机构的运动特性和动力响应。
4.变结构微小空间飞行器在释放发射过程中经历了轴向展开、径向展开两次主要结构变化,期间伴随接触碰撞等行为,系统的运动变化复杂。采用多体系统动力学方法对释放发射阶段的结构变化和系统动力学发展进行了数学描述,建立了变结构微小空间飞行器释放发生过程的数值研究模型,并对理想工况和非理想工况下飞行器绕行一周的轨道运动和姿态变化进行了研究分析,通过数值研究和试验研究得到了系统在释放发射过程中的运动特性和动力学响应,讨论了飞行器在不同初始条件下的姿态变化情况,获得飞行器系统工作姿态在不同工况下的变化规律。
5.针对在长时间的运行过程中,空间飞行器系统能量缓慢损失的问题,引入能量耗散系数,推导建立变结构微小空间飞行器长期自由飞行过程能耗研究模型,探讨分析了在特定假设条件下,空间飞行器系统在线性耗散常系数和非线性抛物线型耗散系数作用下的一些轨道和姿态运动的变化情况,并通过数值仿真预测飞行器系统的稳定工作时长。
本文研究不仅为飞行器结构变化动态研究提供途径,也可作为变结构微小飞行器系统结构工程设计与优化、姿态控制规划提供相应的理论依据。
Variable structure micro-spacecraft(VSMS) has a sort of expansion mechanism, which spread to prescriptive work structure from the state of folded style. The aircraft will keep fixed structure during free flight process. In this dissertation, aiming as characteristics of structure and performance, a novel method using theory analysis, numerical simulation and experiment is applied to investigate systemically the process of releasing-launching and free flight. The operational principle、kinetic characteristics and dynamic property of VSMS was obtained. The major works were done in this thesis as follows.
1. The central work system of VSMS includes power installation、axial expansion mechanism and radial expansion mechanism, et al. The structure design is completed. The structure form and operational principle of each subsystem are analysed. Mission demands and primary technology insex are introduced. Time sequential work flow scheme is set up, each time sequential operation mission is analysed systemically, the time sequential operation characteristics of VSMS are obtained.
2. The interior ballistic test of solid rocket motor and ground releasing-launching test of VSMS are designed, the operating performance on power installation and releasing-launching process are researched. The test process is recorded by high-speed video recorder, and the data is gathered by multichannel instantaneous recorder. The effect of igniting charge mass on interior ballistic performance of solid rocket motor and motion performance under releasing-launching are discussed elementarily. Expanding course of power installation and the system during releasing-launching phase is achieved. The valuable data is offered for numerical simulation and engineering project.
3. The mathematical models for subsystem are established. According to numerical simulation, the subsystem motion laws and performance characteristics are analysed. The model of power installation is educed with interior ballistics and designed theoty of solid rocket motor. The numerical study with different igniting charge mass of releasable solid rocket motor. Veriety laws on pressure and thrust of solid rocket motor is obtained by comparing with test data. The mode model of flexible body is adopted; a dynamic model of expansion mechanism is established with continuous inpact method. The performance characteristics and dynamic response are researched with simulation.
4. VSMS experiences two important structure variety of axial and radial expansion, contact-impact accompanies variable process, and the system motion development is complicated. The system structure transformation and dynamic development is described based on mulrybody systems method during releasing-launching phase. The VSMS model of releasing-launching phase is established, orbital and attitude movement of ideal and nonideal operating condition is studied for running a circle. The motion characteristics and dynamic response are obtained at the stage by numerical and test study, attitude movement under different initial conditions is discussed, and the work attitude laws is summarized.
5. For research the problem about energy tardo loss in the long running period, a VSMS energy dissipation model is enduced using energy dissipation coefficient. Some conditions about orbit and attitude movement with linearity constant coefficient and nonlinear parabola style coefficient is discussed in given hypothesis, and stable work time of VSMS is forecasted.
This research provides an approach to study dynamic structure variety of spacecraft. It also can supply vital reference to the structural engineering design and optimization as well as the programming of attitude control.
引文
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