小型电力系统适用于高要求的有效载荷

A. Tambini, F. Antonini, N. Melega, G. Mariotti, V. Centonze, A. Gabriele
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摘要

继ESEO航天器发射之后,uHETsat将是第二个基于SITAEL S-50/75微卫星平台的IOV/IOD任务。在这种情况下,在轨验证的主题将是SITAEL HT100霍尔效应推力器(HET),这是同类中最小的推力器之一,将首次登上并在一个小型平台上运行。从它的前身开始,该航天器经历了一系列必要的更新和升级,以满足新的任务要求。虽然与ESEO相比,一些AODCS设备已经发生了变化[1],但大部分适应动力系统(PS)的努力都花在了处理推进子系统正常运行所需的动力上。PS的重新设计包括一套新的可展开太阳能阵列(SA),一个修订的电源管理板(PMB)和电源分配单元(PDU),以及一个更大的电池,将允许任务完成其目标:2000次点火和推进子系统1000小时的点火。这次重新设计活动的主要目标是通过对组件选择的仔细审查来提高整体可靠性,同时在制造方面保持单故障容忍度和低成本方法(自动-手动混合)。uHETsat PS目前正在接受飞行,其所有组件都已作为EQM进行了测试,显示了系统支持平台和有效载荷操作的能力。在对uHETsat任务进行简要概述之后,重点将转移到PS架构描述、冗余策略和单点无故障设计方法上。
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uHETsat small Power System for high demanding payloads
Coming right after the launch of the ESEO spacecraft, uHETsat will be the second mission based on the use of SITAEL S-50/75 microsatellite platform for IOV/IOD purposes. In this case the subject of the In Orbit Validation will be SITAEL HT100 Hall Effect Thruster (HET) -one of the smallest of its kind-that for the first time will be embarked and operated onboard a small platform. Starting from its predecessor, the spacecraft has undergone a series of updates and upgrades necessary to comply with the new set of mission requirements. Although some of the AODCS equipment has changed compared to ESEO [1], most of the efforts in the adaptation of the Power System (PS) were spent to handle the power required by the propulsion subsystem for its proper functioning. The PS re-design included a new set of deployable Solar Arrays (SA), a revised Power Management Board (PMB) and Power Distribution Unit (PDU), and a larger battery that will allow the mission to accomplish its goals: 2000 ignitions and 1000 hours of firing for the propulsion subsystem. Main objectives for this re-design activity have been the improvement of the overall reliability through a meticulous review of the components selection, at the same time preserving the single failure tolerance and the low cost approach (hybrid automatic-manual) in terms of manufacturing. The uHETsat PS is currently being accepted for flight and all its components have been tested as EQM showing the capability of the system to support both platform and payload operations. After a brief overview of the uHETsat mission, the focus will be moved to the PS architecture description, redundancies strategy and the single point failure free design approach.
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