A Modular Electrical Power System Architecture for Small Spacecraft

被引：33
作者：
Lim, Timothy M. [1 ]
Cramer, Aaron M. [1 ]
Lumpp, James E., Jr. [1 ]
Rawashdeh, Samir A. [2 ]
机构：
[1] Univ Kentucky, Lexington, KY 40506 USA
[2] Univ Michigan Dearborn, Dearborn, MI 48128 USA
来源：
IEEE TRANSACTIONS ON AEROSPACE AND ELECTRONIC SYSTEMS | 2018年 / 54卷 / 04期
关键词：
STABILITY ANALYSIS; NANOSATELLITE; DESIGN;
D O I：
10.1109/TAES.2018.2803598
中图分类号：
V [航空、航天];
学科分类号：
08 ; 0825 ;
摘要：
An electrical power system for low-Earth-orbit satellites, which can be reused for a variety of mission requirements with minimal redesign, is proposed. The goals of the proposed power system are achieved by modularizing the subsystems of a small spacecraft and designing them to allow any number of each module to be connected simullaneously. The modularized subsystems include solar energy generation and energy storage. The overall objectives will be accomplished without compromising efficiency or power system stability. The purpose of this paper is to describe the proposed power system and detail the experimental results. The generalized system can be used as a one-size-fils-all solution that only requires basic power systems knowledge to configure and operate.
引用
收藏
页码：1832 / 1849
页数：18
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