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Solar Panel Deployment Mechanism for a Solar Sailing Nanosatellite

机译:太阳能平板纳米卫星的太阳能电池板部署机制

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Solar cells are used in satellites to satisfy the power demand. In case of solar sailing missions, the sunlight falls only on a limited portion of the satellite due to the presence of the large solar sail and hence the solar cells attached to the satellite walls may not satisfy the power requirements. To increase the number of solar cells facing the sun, deployable solar panels with solar cells fixed on them are needed. These panels are kept in a stowed state using a nylon wire before launch owing to the constrained volume availability in the launch vehicle. This paper is about the design and testing of a reliable, minimum power-consuming solar panel deployment mechanism for COEPSAT-2 which is a nanosatellite being developed by the students of College of Engineering, Pune (COEP). The satellite aims to demonstrate orbit manoeuvring using a solar sail of area 40 meter-square while characterizing the charged particle density in space. The satellite has four solar panels with nine solar cells on each panel. The mechanism uses an outside stop type hinge, loaded with a 180-degree torsion spring of stiffness 1.5 N-mm/degree. One leaf of the hinge is fixed on the satellite while the other movable leaf holds the solar panel. The working of the mechanism consists of three stages viz. release, deployment, and locking. When the nylon nichrome mechanism is actuated the panel gets deployed by the torsion spring. The locking is done after deployment using a cam follower mechanism in which the follower fixed on the free end of a flat spring moves into a slot made on the cam integral with the movable leaf. Due to the geometry of the mechanism, there is a definite relationship between the upward movement of the follower block and rotation of the panel. Constraints on the length, allowable deflection of the free end of the flat spring and the need of sufficient locking force demanded material for flat spring with high Young's modulus and high tensile strength which led to the selectio
机译:太阳能电池用于卫星以满足电力需求。在太阳帆船任务的情况下,由于大太阳帆的存在,阳光仅在卫星的有限部分上落在卫星上,因此附着在卫星壁上的太阳能电池可能不满足功率要求。为了增加面向太阳的太阳能电池数量,需要使用固定在它们上的太阳能电池的可展开太阳能电池板。由于发射车辆中的约束容积可用性,在推出之前,这些面板在推出之前使用尼龙线保持在收起状态。本文是关于CoEPSAT-2可靠,最小的消耗太阳能电池板展署机制的设计和测试,这是由工程学院浦那(COEP)开发的纳米卫星。卫星旨在使用面积40米方形的太阳帆展示轨道操纵,同时表征空间中的带电粒子密度。卫星在每个面板上有四个具有九个太阳能电池的太阳能电池板。该机构使用外部止动型铰链,装有180度扭转弹簧的刚度1.5 n-mm /度。铰链的一片叶片固定在卫星上,而另一个可移动的叶子握住太阳能电池板。该机制的工作包括三个阶段viz。发布,部署和锁定。当缠绕尼龙镍络机构时,面板被扭转弹簧展开。使用凸轮从动机构在部署之后进行锁定,其中固定在扁平弹簧的自由端上的跟随器移动到与可移动叶片的凸轮上形成的槽中。由于该机构的几何形状,从动罩块的向上运动和面板的旋转之间存在明确的关系。在平坦弹簧的自由端的长度,允许偏转的约束,需要足够的锁定力的扁平弹簧材料,具有高的杨氏模量和高抗拉强度,导致了选择

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