飞船返回舱着陆冲击缓冲座椅系统改进设计研究
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摘要
载人飞船返回舱安全着陆技术是载人航天的关键技术之一。返回舱内航天员缓冲座椅系统,为减小着陆冲击载荷、保障航天员安全着陆发挥关键作用。现有缓冲座椅主要能有效缓冲航天员胸背向冲击载荷,而对头盆向的缓冲能力较弱。在较大的水平着陆冲击下,通过座椅传递过来的多向冲击过载,存在超过航天员头盆向耐受极限的可能性。为同时提高座椅对航天员胸背向与头盆向冲击过载的缓冲性能,论文通过理论分析和实验研究,系统地研究了缓冲座椅的改进设计、缓冲性能分析、座椅参数优化、冲击缓冲实验等问题。论文主要研究内容包括:
1)分析了返回舱着陆工况及现有前支座铰接支撑座椅的缓冲性能。
根据返回舱着陆过程特点和座椅竖直缓冲杆工作原理,建立并验证了现有铰接支撑座椅系统的动力学模型;分析了不同着陆速度、输入冲击波形、测点位置和缓冲杆力学特性下座椅系统的响应特点;发现当存在水平着陆冲击时,现有缓冲座椅可能出现缓冲行程空间不够、头盆向冲击过载超过航天员耐受极限的问题;通过对现有缓冲座椅结构特点的分析,提出了缓冲座椅的改进途径。
2)研究了前支座弹性支撑改进座椅的缓冲性能及参数影响和优化设计。
基于座椅前支座设置弹性支撑缓冲器的前提,分别提出了水平向支撑、竖直向支撑、双向支撑和斜向支撑四种改进方案;建立了改进座椅的动力学模型,分析了改进座椅的缓冲性能以及缓冲器的刚度、阻尼和支撑角度对缓冲性能的影响规律;应用多目标优化方法对四种缓冲座椅的缓冲器参数进行了优化设计;研究发现:前支座水平向弹性支撑座椅可有效降低头盆向冲击过载,且工程约束要求低,是四种弹性支撑方案中的最佳方案。
3)研究了前支座采用不同水平向缓冲器座椅的缓冲性能,确定座椅改进方案。
水平向非线性缓冲器支撑座椅方案中依次比较了非线性弹簧阻尼、磁流变阻尼器和胀环式缓冲杆三类支撑,其中水平向胀环式缓冲杆支撑座椅具有良好的缓冲效果,使减幅后的头盆向峰值接近于无水平冲击着陆工况下铰接支撑座椅的响应值,同时具有响应时间短、能够参考现有铰接支撑座椅的竖直缓冲杆安装设计的优点,被确定为最合适的改进方案。
4)提出了胀环与锥套结构的设计方法,并开展结构参数与扩径力的实验测量。
提出了胀环和锥套结构构型中的设计参数,推导了胀环扩径力的理论计算公式,分析了结构参数对扩径缓冲力的影响规律;利用实验测量的方法获取了胀环力学性能参数和胀环与锥套之间摩擦系数这两个关键的设计参数;开展的胀环拟静态扩径实验研究,验证了理论计算分析的正确性。
5)发展了缓冲杆的工程设计与优化设计方法,开展缓冲杆冲击缓冲实验研究。
计及胀环式缓冲杆在典型、极限着陆工况下的全部工作特性,提出了缓冲杆的“初始—中间—末了”的三部分设计方法;引入了缓冲力与缓冲行程调节系数,扩展了等长胀环与不等长胀环缓冲杆的设计范围;针对竖直缓冲杆与水平缓冲杆,分别讨论了工程设计方法和多目标优化设计方法;最后完成的胀环式缓冲杆动态冲击实验,基本验证了其缓冲性能的高效性与工程设计方法的有效性。
The landing technology of reentry capsule of manned spacecraft is a key technology for manned space flight. The buffer seats in reentry capsule are essential to reduce the impact overload on the astronauts to ensure their safety. Buffer seats at present have strong compatibility to attenuate the chest-back impact acceleration,but weak to the head-pelvis one. The multi-directional impact loads imposed on the crewman maybe exceed the head-pelvis acceleration limit. To improve attenuation compatibility of the chest-back and the head-pelvis acceleration, this dissertation presents a systematic survey on the improved design schemes, attenuation capability, parameters optimization of buffer seats and the shock attenuation experiments of the cushion pole. The main research contents and results in this dissertation are summarized as follows.
1) The landing conditions of reentry capsule and the attenuation compatibility of the present seat with the front gemel support are analyzed.
A dynamic model of the present buffer seat is established based on the characteristics of the reentry capsule landing and work mechanism of the vertical cushion pole. The response and characteristics of the landing conditions, shapes of shock, various positions of buffer seats, and mechanics of the cushion pole are studied respectively. The analysis of the horizontal impact factors reveal hidden trouble due to short buffer distance and increscent head-pelvis acceleration. The promising measures are presented consequently according to the structural features of the present seat.
2) The attenuation compatibility, the influence of the parameters and optimal design of the improved seats with the front elastic supports are studied.
Four promising schemes are provided by supplementing elastic supports on the front end of the buffer seat, consisting of the horizontal support, the vertiacl support, the double support and the titled support. The dynamic models of the improved buffer seats are established. The influence of stiffness, damper and surport angle for all improvement schemes is studied. A multi-objective optimization algorithm is applied for obtaining parameters ranges of the design problems. One design scheme which applying a horizontal elastic support on the front end of the seat is choosed finally, because of its effective reduction of the head-pelvis impact load and small engineering constraints.
3) The attenuation compatibility of seats with various horizontal buffers support on the front end is studied, and the optimum improved scheme is determined finally.
The preferred design scheme that uses a horizontal nonlinear buffer support is analyzed in detail. This chapter is concerned with the comparison of three nonlinear support design schemes, including nonlinear spring and damper surpport, magneto-rheological fluid damper support, and expandable ring cushion pole support. The horizontal expandable ring cushion pole support is superior to the other two schemes because of its outstanding head-pelvis energy disppation capability, its short response time and convenient installation resulting from many references to the present buffer seat.
4)The design methods of the expandable ring and the conic knot are proposed, and the experiments to measure the structural parameters and force are conducted.
The design parameters of the expandable rings and the conic knot are proposed. The fomula to calculate the expanding force of the expandable rings are raised. The influence of the design parameters to the expanding force are discussed by numeric simulation. Two design parameters are obtained from the expanding ring material mechanical capability tests and the friction coefficient measure tests between expanding rings and a conic knot. The following successful static expanding ring tests show that the design fomula and the theory analysis are reliable.
5) The engineering design and the multi-objective optimization of the expandable ring cushion pole are developed, and the shock attenuation experiments of the the cushion pole are conducted.
Three segments design route of the expandable ring cushion pole is put forward, with normal and extreme landing speed considered. By the introduction of adjusting coefficients for the force and the stroke, the design extension is extended for the cushion pole that is made of same or various length rings. The preselecting engineering design and the comprehensive multi-objective optimum design are applied to the vertical cushion pole and the horizontal cushion pole. The high buffer capability of the expandable ring cushion pole and the validity of the engineering design are proved by the dynamic tests of the pole.
1)分析了返回舱着陆工况及现有前支座铰接支撑座椅的缓冲性能。
根据返回舱着陆过程特点和座椅竖直缓冲杆工作原理,建立并验证了现有铰接支撑座椅系统的动力学模型;分析了不同着陆速度、输入冲击波形、测点位置和缓冲杆力学特性下座椅系统的响应特点;发现当存在水平着陆冲击时,现有缓冲座椅可能出现缓冲行程空间不够、头盆向冲击过载超过航天员耐受极限的问题;通过对现有缓冲座椅结构特点的分析,提出了缓冲座椅的改进途径。
2)研究了前支座弹性支撑改进座椅的缓冲性能及参数影响和优化设计。
基于座椅前支座设置弹性支撑缓冲器的前提,分别提出了水平向支撑、竖直向支撑、双向支撑和斜向支撑四种改进方案;建立了改进座椅的动力学模型,分析了改进座椅的缓冲性能以及缓冲器的刚度、阻尼和支撑角度对缓冲性能的影响规律;应用多目标优化方法对四种缓冲座椅的缓冲器参数进行了优化设计;研究发现:前支座水平向弹性支撑座椅可有效降低头盆向冲击过载,且工程约束要求低,是四种弹性支撑方案中的最佳方案。
3)研究了前支座采用不同水平向缓冲器座椅的缓冲性能,确定座椅改进方案。
水平向非线性缓冲器支撑座椅方案中依次比较了非线性弹簧阻尼、磁流变阻尼器和胀环式缓冲杆三类支撑,其中水平向胀环式缓冲杆支撑座椅具有良好的缓冲效果,使减幅后的头盆向峰值接近于无水平冲击着陆工况下铰接支撑座椅的响应值,同时具有响应时间短、能够参考现有铰接支撑座椅的竖直缓冲杆安装设计的优点,被确定为最合适的改进方案。
4)提出了胀环与锥套结构的设计方法,并开展结构参数与扩径力的实验测量。
提出了胀环和锥套结构构型中的设计参数,推导了胀环扩径力的理论计算公式,分析了结构参数对扩径缓冲力的影响规律;利用实验测量的方法获取了胀环力学性能参数和胀环与锥套之间摩擦系数这两个关键的设计参数;开展的胀环拟静态扩径实验研究,验证了理论计算分析的正确性。
5)发展了缓冲杆的工程设计与优化设计方法,开展缓冲杆冲击缓冲实验研究。
计及胀环式缓冲杆在典型、极限着陆工况下的全部工作特性,提出了缓冲杆的“初始—中间—末了”的三部分设计方法;引入了缓冲力与缓冲行程调节系数,扩展了等长胀环与不等长胀环缓冲杆的设计范围;针对竖直缓冲杆与水平缓冲杆,分别讨论了工程设计方法和多目标优化设计方法;最后完成的胀环式缓冲杆动态冲击实验,基本验证了其缓冲性能的高效性与工程设计方法的有效性。
The landing technology of reentry capsule of manned spacecraft is a key technology for manned space flight. The buffer seats in reentry capsule are essential to reduce the impact overload on the astronauts to ensure their safety. Buffer seats at present have strong compatibility to attenuate the chest-back impact acceleration,but weak to the head-pelvis one. The multi-directional impact loads imposed on the crewman maybe exceed the head-pelvis acceleration limit. To improve attenuation compatibility of the chest-back and the head-pelvis acceleration, this dissertation presents a systematic survey on the improved design schemes, attenuation capability, parameters optimization of buffer seats and the shock attenuation experiments of the cushion pole. The main research contents and results in this dissertation are summarized as follows.
1) The landing conditions of reentry capsule and the attenuation compatibility of the present seat with the front gemel support are analyzed.
A dynamic model of the present buffer seat is established based on the characteristics of the reentry capsule landing and work mechanism of the vertical cushion pole. The response and characteristics of the landing conditions, shapes of shock, various positions of buffer seats, and mechanics of the cushion pole are studied respectively. The analysis of the horizontal impact factors reveal hidden trouble due to short buffer distance and increscent head-pelvis acceleration. The promising measures are presented consequently according to the structural features of the present seat.
2) The attenuation compatibility, the influence of the parameters and optimal design of the improved seats with the front elastic supports are studied.
Four promising schemes are provided by supplementing elastic supports on the front end of the buffer seat, consisting of the horizontal support, the vertiacl support, the double support and the titled support. The dynamic models of the improved buffer seats are established. The influence of stiffness, damper and surport angle for all improvement schemes is studied. A multi-objective optimization algorithm is applied for obtaining parameters ranges of the design problems. One design scheme which applying a horizontal elastic support on the front end of the seat is choosed finally, because of its effective reduction of the head-pelvis impact load and small engineering constraints.
3) The attenuation compatibility of seats with various horizontal buffers support on the front end is studied, and the optimum improved scheme is determined finally.
The preferred design scheme that uses a horizontal nonlinear buffer support is analyzed in detail. This chapter is concerned with the comparison of three nonlinear support design schemes, including nonlinear spring and damper surpport, magneto-rheological fluid damper support, and expandable ring cushion pole support. The horizontal expandable ring cushion pole support is superior to the other two schemes because of its outstanding head-pelvis energy disppation capability, its short response time and convenient installation resulting from many references to the present buffer seat.
4)The design methods of the expandable ring and the conic knot are proposed, and the experiments to measure the structural parameters and force are conducted.
The design parameters of the expandable rings and the conic knot are proposed. The fomula to calculate the expanding force of the expandable rings are raised. The influence of the design parameters to the expanding force are discussed by numeric simulation. Two design parameters are obtained from the expanding ring material mechanical capability tests and the friction coefficient measure tests between expanding rings and a conic knot. The following successful static expanding ring tests show that the design fomula and the theory analysis are reliable.
5) The engineering design and the multi-objective optimization of the expandable ring cushion pole are developed, and the shock attenuation experiments of the the cushion pole are conducted.
Three segments design route of the expandable ring cushion pole is put forward, with normal and extreme landing speed considered. By the introduction of adjusting coefficients for the force and the stroke, the design extension is extended for the cushion pole that is made of same or various length rings. The preselecting engineering design and the comprehensive multi-objective optimum design are applied to the vertical cushion pole and the horizontal cushion pole. The high buffer capability of the expandable ring cushion pole and the validity of the engineering design are proved by the dynamic tests of the pole.
引文
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