Journal of Aerospace System Engineering (항공우주시스템공학회지)

The Society for Aerospace System Engineering (항공우주시스템공학회)
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A Study on the Vibration Characteristics of Attitude Maneuvering of Satellite

위성의 자세기동에 따른 진동특성에 관한 연구

  • Pyeon, Bong-Do (School of Aerospace and Mechanical Engineering, Graduate School at Korea Aerospace University) ;
  • Bae, Jae-Sung (Dept. of Aerospace and Mechanical Engineering, Korea Aerospace University) ;
  • Kim, Jong-Hyuk (School of Aerospace and Mechanical Engineering, Graduate School at Korea Aerospace University) ;
  • Park, Jung-Sun (Dept. of Aerospace and Mechanical Engineering, Korea Aerospace University)
  • 편봉도 (한국항공대학교 항공우주 및 기계공학과 대학원) ;
  • 배재성 (한국항공대학교 항공우주 및 기계공학부) ;
  • 김종혁 (한국항공대학교 항공우주 및 기계공학과 대학원) ;
  • 박정선 (한국항공대학교 항공우주 및 기계공학부)
  • Received : 2018.12.15
  • Accepted : 2019.03.31
  • Published : 2019.06.30
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Abstract

The design requirements of modern satellites vary depending on the purpose of operation. Like conventional medium and large-scale satellites, small satellites which operate on low orbit may also serve military purposes. As a result, there is increased demand for high-resolution photos and videos and multi-target observation becomes important. The most important design parameter for multi-target observation is the satellites' maneuverability. For increased maneuverability, the miniaturization is required to increase the stiffness of the satellite as this decreases the mass moment of inertia of the satellite. In the case of a solar panel having relatively low stiffness compared to the satellites' body, vibrations are generated when the attitude maneuver is performed, which greatly influences the image acquisition. For verification of such vibrational characteristics, the satellites is modeled as a reduced model, and experimental zig for simulating attitude maneuver is introduced. A rigidity simulator for simulating the stiffness of the satellite is also proposed. Additionally, the objective of the experimental method is to simulate the maneuvering angle of the satellite based on the winding length of the wire using a step motor, and to experimentally verify the vibration characteristics of the satellite body and the solar panel generated during the maneuvering test.

현대의 위성들의 설계요구조건은 운용되는 목적에 따라 다양해진다. 기존 중/대형 위성과는 달리 저궤도에서 운용되는 소형위성의 경우 군사적인 목적을 나타내기도 한다. 그렇기 때문에 고해상도의 사진 및 영상 수요가 증가하며 다표적 관측이 중요하게 된다. 이에 다표적 관측을 하기 위해서 위성의 기동성은 중요한 설계변수이다. 기동성이 증가하기 위해서 소형화가 되면 전체 질량관성모멘트가 감소하기 때문에 위성의 강성을 높여야한다. 본체에 비해서 강성이 낮은 태양전지판의 경우 진동이 발생하기 때문에 영상획득에 큰 영향을 미친다. 이러한 진동특성을 확인하기 위하여 본 연구에서는 위성을 축소모델로 제작하여 자세기동을 모사하기 위한 실험 치구를 도입하였고, 위성의 강성을 모사하기 위한 모사장치를 제시하였다. 또한 실험방식은 스텝모터를 이용하여 와이어의 감는 길이에 따라 위성의 기동각을 모사하였으며, 기동실험 시 발생되는 위성의 본체 및 태양전지판에 대하여 진동특성을 실험적으로 검증하고자 한다.

Keywords

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Fig. 1 Configuration of high agility a satellite

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Fig. 2 Deformation according to the force of a beam

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Fig. 3 Conceptual design of hinge-torsional spring

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Fig. 4 Conceptual design of the attitude maneuvering tester

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Fig. 5 The First Mode of FE Model

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Fig. 6 The Second Mode of FE Model

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Fig. 7 The Third Mode of FE model

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Fig. 8 Schematic Diagram of the Experimental Setup

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Fig. 9 Input Maneuvering Profile

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Fig. 10 Experiment Setup for Vibration Test of the Satellite Structure Model

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Fig. 11 Frequency Response Function of the Satellite’s Body

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Fig. 12 Frequency Response Function of the Body and Panel 1

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Fig. 13 Frequency Response Function of the Body, Panel 1 and Panel 3

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Fig. 14 Time-Acceleration Response of each panel

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Fig. 15 Frequency Response Function of the solar panels

Table 1. Specification of scale down satellite model

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Table 2. Requirements of attitude maneuvering

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Table. 4 Comparison of FEM Analysis and Experimental Results

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Table. 5 Experimental Results with Symmetrical panel

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