斜向弹性支撑飞船座椅缓冲性能  

Buffer Characteristics of Titled Elastic Supporting Seat in Manned Spacecraft

作　　者：谢燕[1] 廖一寰[1] 雷勇军[1] 李道奎[1] 

机构地区：[1]国防科学技术大学航天与材料工程学院,湖南长沙410073

出　　处：《航空学报》2009年第6期1023-1027,共5页Acta Aeronautica et Astronautica Sinica

基　　金：中国博士后科学基金(20060390892)

摘　　要：当出现具有较大水平速度的斜冲击着陆工况时,飞船座椅头盆向冲击过载可能危及航天员生命安全。在现有的胸背向着陆冲击过载缓冲机构的基础上,引入座椅斜向弹性支撑模型,建立了斜向弹性支撑座椅缓冲系统的动力学模型。对具有较大水平速度的斜冲击着陆工况的仿真结果表明,相比于现有的铰接支撑缓冲系统,适当参数组合下的斜向弹性支撑座椅缓冲系统能有效降低航天员头盆向冲击过载且不增加胸背向冲击过载;综合支撑角度、刚度和阻尼各个参数影响规律,可以得到优化的座椅设计方案。When a manned spacecraft lands with high horizontal velocity, the resulting excessive head-pelvis acceleration is harmful to the astronaut＇s safety. The existing buffer seat makes use of a passive buffer mechanism system to alleviate the chest-back landing-impact loads; however, the focus of this article is to reduce the dangerous head-pelvis acceleration. A dynamic model of the titled elastic supporting buffer seat in reentry manned spacecraft is designed. The buffer characteristics of the seat alleviating the chest-back and head-pelvis impact loads are analyzed by the model for the reentry spacecraft at high multi-direction impact velocities. The results of mathematic simulation indicate that the improved titled elastic supporting buffer seat is better than the existing gemel joint supporting buffer seat, because the proposed seat attenuates the impact of head-pelvis acceleration effectively without increasing chest-back impact acceleration. The rules of support angle, stiffness, and damper described in this article can provide good reference for the optimal design of the buffer seat.

关 键 词：载人飞船 斜冲击 斜向弹性支撑座椅 胸背向载荷 头盆向载荷 着陆 

分 类 号：V414.4[航空宇航科学与技术—航空宇航推进理论与工程]