CAJ | 학술논문

对非规则板舱组合体天宫飞行器300～200 km低轨道飞行过程空气动力特性一体化计算建模，提出考虑复杂构型物面遮盖效应面元解析法与经修正的Boettcher／Legge非对称桥函数，发展基于三角形面元逼近复杂外形通用处理方法，建立适于天宫飞行器复杂物形处理与面元气动力系数计算规则；将DSMC方法与求解Boltzmann 模型方程气体运动论统一算法应用于天宫飞行器简化外形，进行气动力当地化关联参数计算修正，建立针对大型复杂结构天宫飞行器低轨道飞行控制过程空气动力特性一体化快速算法与程序软件。对大尺度圆柱体外形与天宫飞行器300～200 km不同高度变轨飞行过程不同迎角与侧滑角及帆板平面与本体主轴不同夹角复杂构型气动力特性计算分析验证，表明天宫飞行器在200 km以上低轨道飞行控制过程中所受空气动力系数随飞行高度发生显著变化（8％～50％），证实长期在轨运行的大型航天器若采用统一固定的气动力系数，误差累积巨大，需要采取防护措施，低轨道飞控大气阻力仍是制约航天器定轨预报精度最关键因素。
대비규칙판창조합체천궁비행기300～200 km저궤도비행과정공기동력특성일체화계산건모，제출고필복잡구형물면차개효응면원해석법여경수정적Boettcher／Legge비대칭교함수，발전기우삼각형면원핍근복잡외형통용처리방법，건립괄우천궁비행기복잡물형처리여면원기동력계수계산규칙；장DSMC방법여구해Boltzmann 모형방정기체운동론통일산법응용우천궁비행기간화외형，진행기동력당지화관련삼수계산수정，건립침대대형복잡결구천궁비행기저궤도비행공제과정공기동력특성일체화쾌속산법여정서연건。대대척도원주체외형여천궁비행기300～200 km불동고도변궤비행과정불동영각여측활각급범판평면여본체주축불동협각복잡구형기동력특성계산분석험증，표명천궁비행기재200 km이상저궤도비행공제과정중소수공기동력계수수비행고도발생현저변화（8％～50％），증실장기재궤운행적대형항천기약채용통일고정적기동력계수，오차루적거대，수요채취방호조시，저궤도비공대기조력잉시제약항천기정궤예보정도최관건인소。
The surface analytical method , considering surface shielding effect of the complex struc-ture and the modified Boettcher/Legge nonsymmetric bridge correction function , was proposed to computationally model aerodynamic characteristics of the large-scale Tiangong spacecraft of irregular plate-capsule assembly .The complex configuration processing and computing rules of surface ele-ment aerodynamic coefficients were set up by developing a general triangle element approximation for complex shapes .A unified fast algorithm and computing software for aerodynamic characteristics of large-scale complex spacecraft structures were developed , by computing correction of local correla-tion parameters during Tiangong spacecraft ’ s low-earth orbit flight control , in which the DSMC method and the gas-kinetic unified algorithm solving the Boltzmann model equation were applied .It is indicated that , by computing the aerodynamics of the Tiangong spacecraft in 300~200 km alti-tude-orbit flight process , with various flying heights , various angles of attack and various angles be-tween the panel and the principal axis , the aerodynamic coefficients varied remarkably , with a range of 8%~50%, with the altitude change , and the atmospheric drag in low-earth orbit flight control was the key factor of the spacecraft orbit prediction accuracy .It is validated that, if the fixed and constant unity aerodynamic coefficient is used for long-term orbit flight of a large spacecraft , the er-ror accumulation will be huge , and protective measures are needed .