摘要
着陆缓冲气囊发生反弹将造成系统姿态不可控、二次冲击等危害,针对排气型着陆缓冲气囊系统易发生反弹的问题,提出了一种着陆缓冲气囊的无反弹设计方法。首先给出了6种不同形状气囊的缓冲过程变形假设,并基于牛顿第二定律和热力学方程建立了气囊系统的动力学解析模型;然后采用该模型以无反弹为约束条件对着陆缓冲气囊进行优化,实现了气囊的无反弹设计。运用此方法对圆柱形气囊进行无反弹多目标优化,得到了有效载荷最大冲击加速度更小、触地速度更小,且缓冲过程无反弹的气囊模型;优化前后气囊模型的解析计算结果与有限元仿真结果一致性好,表明所建解析模型合理,精度较高,验证了所提方法的有效性。
Rebound of the landing impact attenuating airbag will induce uncontrollable system attitude,secondary shock or other hazards.To solve the rebound problem of the venting type airbag system,a rebound free design method for landing impact attenuating airbag was proposed.The deformation assumptions of six different shapes of airbags during cushioning were given,and an analytical dynamic model of airbag system was established based on the deformation assumptions,thermodynamics equations and Newton’s second low.Then,using this analytical model,the landing airbag was optimized under the constraint of no rebound.The multi-objective optimization design of the cylindrical airbag was carried out by using this design method,and the airbag without bouncing back was obtained.Compared with the non-optimized one,the maximum impact acceleration and the touchdown speed of the optimized cylindrical airbag system were smaller.The calculation results of the analytical model of the cylindrical airbag before and after optimization were preferably consistent with the results of finite element analysis.The results demonstrated that the airbag analytical model was reasonable and accurate.Consequently,the effectiveness of the proposed design method was verified.
作者
周旋
周仕明
李道奎
ZHOU Xuan;ZHOU Shiming;LI Daokui(College of Aerospace Science and Engineering,National University of Defense Technology,Changsha 410073,China)
出处
《载人航天》
CSCD
北大核心
2020年第2期190-199,共10页
Manned Spaceflight
基金
载人航天领域预先研究项目(040202)。
关键词
气囊
着陆缓冲
反弹
优化
缓冲性能
airbag
landing impact attenuation
rebound
optimization
cushioning performance
