航天返回与遥感
航天返迴與遙感
항천반회여요감
SPACECRAFT RECOVERY & REMOTE SENSING
2014年
1期
29-36
,共8页
火星探测器%降落伞拉直过程%绳帆%动力学建模与仿真%质量阻尼弹簧模型
火星探測器%降落傘拉直過程%繩帆%動力學建模與倣真%質量阻尼彈簧模型
화성탐측기%강락산랍직과정%승범%동역학건모여방진%질량조니탄황모형
Mars probe%parachute deployment%line sail%dynamic modeling and simulating%mass damper spring model
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。
文章在簡要介紹火星探測器的物傘繫統組成以及火星探測器降落傘拉直過程的基礎上,根據拉直過程中各物體的運動屬性,建立瞭火星探測器降落傘拉直過程的三維動力學模型。模型將傘包視為變質量六自由度剛體,進入器視為六自由度剛體,傘繩/傘衣採用質量阻尼彈簧模型,即將傘衣、傘繩、連接繩以及弔帶離散成若榦繩段,每箇繩段處理為質量集中在耑點的三自由度質點,各質點之間以阻尼彈簧相連。利用所提齣的動力學模型對“海盜號”第一次氣毬髮射試驗進行瞭倣真,併與Moog R.D.的倣真計算結果和試驗數據進行瞭對比,驗證瞭該文數學模型的正確性與有效性。
문장재간요개소화성탐측기적물산계통조성이급화성탐측기강락산랍직과정적기출상,근거랍직과정중각물체적운동속성,건립료화성탐측기강락산랍직과정적삼유동역학모형。모형장산포시위변질량륙자유도강체,진입기시위륙자유도강체,산승/산의채용질량조니탄황모형,즉장산의、산승、련접승이급조대리산성약간승단,매개승단처리위질량집중재단점적삼자유도질점,각질점지간이조니탄황상련。이용소제출적동역학모형대“해도호”제일차기구발사시험진행료방진,병여Moog R.D.적방진계산결과화시험수거진행료대비,험증료해문수학모형적정학성여유효성。
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.