摘要
文章在简要介绍火星探测器的物伞系统组成以及火星探测器降落伞拉直过程的基础上,根据拉直过程中各物体的运动属性,建立了火星探测器降落伞拉直过程的三维动力学模型。模型将伞包视为变质量六自由度刚体,进入器视为六自由度刚体,伞绳/伞衣采用质量阻尼弹簧模型,即将伞衣、伞绳、连接绳以及吊带离散成若干绳段,每个绳段处理为质量集中在端点的三自由度质点,各质点之间以阻尼弹簧相连。利用所提出的动力学模型对"海盗号"第一次气球发射试验进行了仿真,并与Moog R.D.的仿真计算结果和试验数据进行了对比,验证了该文数学模型的正确性与有效性。
By briefly introducing the parachute-payload system compositions and parachute deployment of Mars probe, and on the basis of the movement characteristics of parachute-payload system during deploy-ment process, a three-dimensional dynamical model is developed to study the deployment process of Mars probe. The parachute bag is considered as a variable mass 6-DOF rigid. The probe is treated as a 6-DOF rigid. The parachute system uses the mass-spring-damper model, viz., the canopy, suspension lines, risers and bridles are discreted into some 3-DOF segments with their centralized mass on the end points. Each segment is mod-eled as a mass damper spring. The dynamic model is utilized to simulate the balloon launched decelerator test of Viking AV-1, and the simulated results are compared with Moog R.D.’s results and test data, which validates correctness and validity of the model.
出处
《航天返回与遥感》
2014年第1期29-36,共8页
Spacecraft Recovery & Remote Sensing
