CAJ | 학술논문

火星着陆器在进入减速着陆过程中降落伞是必需的气动力减速装置，然而火星大气的特殊性使得火星降落伞开伞工作时具有超声速、低密度、低动压的特点，因而火星降落伞的构型、参数选择非常关键。文章在对火星盘缝带伞进行理论分析和国际应用研究的基础上，选取四种典型结构参数的盘缝带伞型，即常规透气量和低透气量的探路者型和海盗型伞型，在中国国内首次进行了亚－跨声速风洞试验，对这四种伞型在亚－跨声速下的阻力特性和稳定性开展研究。风洞试验采用横梁式测力天平测量阻力，同时用影像设备观察伞的摆动角度。研究结果表明，盘缝带伞的跨声速段阻力系数与理论值基本相符，能够满足火星环境下的减速需要；盘缝带伞随阻力系数增加稳定性降低，设计中必须兼顾考虑。
화성착륙기재진입감속착륙과정중강락산시필수적기동력감속장치，연이화성대기적특수성사득화성강락산개산공작시구유초성속、저밀도、저동압적특점，인이화성강락산적구형、삼수선택비상관건。문장재대화성반봉대산진행이론분석화국제응용연구적기출상，선취사충전형결구삼수적반봉대산형，즉상규투기량화저투기량적탐로자형화해도형산형，재중국국내수차진행료아－과성속풍동시험，대저사충산형재아－과성속하적조력특성화은정성개전연구。풍동시험채용횡량식측력천평측량조력，동시용영상설비관찰산적파동각도。연구결과표명，반봉대산적과성속단조력계수여이론치기본상부，능구만족화성배경하적감속수요；반봉대산수조력계수증가은정성강저，설계중필수겸고고필。
In the Mars entry decelerate landing program , the parachute is a key instrument of the aerodynamic decelerator system . Because of the particularity of the Mars atmosphere , the parachute used for the Mars misson deploys under the supersonic , low density , low dynamic pressure conditions . So the construction and sizing of the Mars parachute is much important . The Mars parachute technology was investigated and analyzed by four types of parachute ,considering the disk‐band area ratio and porosity of the canopy material . To determine the drag and static stability of the various types of disk‐gap‐band parachute model , the Mars parachute transonic characteristics test in China was firstly conducted . The front truss and wind tunnel balance was used to measure the axis force on the parachute model ,and the photography was used to observe the angle of attack of the parachute . The test results show that , the transonic drag coefficient of the disk‐gap‐band parachute accords with the theoretical one and can satisfy the Mars mission requirements . It is also observed that the reduction of stability of the disk‐gap‐band parachute is accompanied by the increasing of the drag performance .