CAJ | 학술논문

为研究烧蚀对返回舱配平特性的影响，采用数值模拟方法计算分析了类联盟号返回舱在不同马赫数下的配平特性，同时研究了因烧蚀防热层厚度变化所引起的气动外形改变后的气动特性，尤其是配平特性的变化情况。结果表明：在高超声速段（Ma＞8），类联盟号返回舱的配平攻角绝对值和配平升阻比随着马赫数的增大而减小；因烧蚀防热层厚度变化所引起的气动外形变化后，配平攻角绝对值会增大，配平升阻比也相应增加；研究结果与国外文献中对 CEV 外形的研究结论相符合，类联盟号外形与 CEV 外形在配平特性上具有相同的变化规律，烧蚀对其配平特性的影响规律也相同。
위연구소식대반회창배평특성적영향，채용수치모의방법계산분석료류련맹호반회창재불동마혁수하적배평특성，동시연구료인소식방열층후도변화소인기적기동외형개변후적기동특성，우기시배평특성적변화정황。결과표명：재고초성속단（Ma＞8），류련맹호반회창적배평공각절대치화배평승조비수착마혁수적증대이감소；인소식방열층후도변화소인기적기동외형변화후，배평공각절대치회증대，배평승조비야상응증가；연구결과여국외문헌중대 CEV 외형적연구결론상부합，류련맹호외형여 CEV 외형재배평특성상구유상동적변화규률，소식대기배평특성적영향규률야상동。
In order to investigate the effect of ablation on the re-entry capsule,numerical simulation is used to analyze the trim characteristic of Soyuz re-entry capsule.The aerodynamic characteristic and the trim characteristic are researched as the aerodynamic configuration is changed due to the recession of thermal protection thickness.The result indicates that absolute value of the trim angle of attack and trim lift-drag ratio of Soyuz re-entry capsule are decreased with mach number increasing in hypersonic flow(Ma >8),and the effect of recession is to increase absolute value of the trim angle of attack and trim lift-drag ratio.The results compare well with the conclusion of CEV in overseas reference.The Soyuz and CEV have same changes in the law about trim characteristic,and recessed configuration of them also have similar changes in trends.The research offers reference for the aerodynamic configuration design and improve of the Soyuz re-entry capsule.