首页> 外文会议>4th European Symposium on Aerothermodynamics for Space Vehicles, Oct 15-18, 2001, Capua, Italy >Thermal and Aerodynamic Experimental Testing for Full Scale Models of 465 Descent Modules with Inflatable Braking Device
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Thermal and Aerodynamic Experimental Testing for Full Scale Models of 465 Descent Modules with Inflatable Braking Device

机译:带有充气制动装置的465下降模块全尺寸模型的热力和空气动力学实验测试

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Research on high temperature flexible materials has recently demonstrated their applicability to inflatable reentry capsules in the frame of Inflatable Reentry Device Technology (IRDT) program, developed for ESA by Babakin Space Center and Astrium. As the front shield of such vehicles is of the Inflatable Braking Device (IBD) fixed to a payload. Such a construction allows improving entry spacecraft size and mass characteristics. The IBD of such a Descent Module (DM) is in a packed position during transportation and deployed just before the planet atmospheric entry. The deployed IBD can have any predetermined aerodynamic configuration. DM in form of 90°?-angle cone is described here. A Thermal Protective System (TPS) for IBD of such DM is selected on the base of calculating-experimental method. This flexible TPS consists of the heat absorbing and thermal insulating packets. The serviceability of such TPS integrated in full-scale mock-up of IBD DM (2.32m diameter) has been tested on ground-based facility. It has been determined the methodology of stand regimes selection, simulating in-flight warm-up, mass ablation and aerodynamic load. A full scale of IBD DM's mock-up testing has demonstrated TPS applicability to protect DM against heat loading during orbital reentry in the Earth atmosphere. In the subsonic wind tunnel there have been obtained the aerodynamic coefficients of DM with IBD second cascade at pre-landing phase. The second additional IBD (AIBD) inflation allows increasing its cone base area up to the size providing a selected DM landing speed. AIBD deployment dynamics has also been studied in the same wind tunnel. On the base of these results the minimal value of the AIBD pressurization, allowing preserving shape stability in the aerodynamic flow, has been determined.
机译:高温柔性材料的研究最近证明了其适用于Babakin航天中心和Astrium为ESA开发的可充气折返装置技术(IRDT)计划框架中的可充气折返胶囊。由于这类车辆的前罩是固定在有效载荷上的充气制动装置(IBD)。这种构造允许改善进入航天器的尺寸和质量特性。这种下降模块(DM)的IBD在运输过程中处于包装状态,并在行星大气进入之前部署。部署的IBD可以具有任何预定的空气动力学配置。这里以90°角锥的形式描述DM。在计算实验方法的基础上,选择了此类DM的IBD热防护系统(TPS)。这种灵活的TPS由吸热和隔热包组成。已在地面设施上测试了集成在IBD DM(直径为2.32m)的完整模型中的此类TPS的可服务性。已经确定了机架状态选择,模拟飞行中的热身,质量消融和空气动力负荷的方法。 IBD DM的完整模型测试已证明TPS适用于保护DM使其免于在地球大气中的轨道重入期间受到热负荷。在亚音速风洞中,已经获得了在着陆阶段具有IBD第二级联的DM的空气动力学系数。第二个额外的IBD(AIBD)充气允许将其圆锥形底部面积增加到提供选定DM着陆速度的尺寸。在同一条风洞中还研究了AIBD的部署动力学。根据这些结果,确定了AIBD加压的最小值,该最小值允许在空气动力流中保持形状稳定性。

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