KR100299748B1 - Deployment test apparatus of solar array - Google Patents

Deployment test apparatus of solar array Download PDF

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Publication number
KR100299748B1
KR100299748B1 KR1019990030878A KR19990030878A KR100299748B1 KR 100299748 B1 KR100299748 B1 KR 100299748B1 KR 1019990030878 A KR1019990030878 A KR 1019990030878A KR 19990030878 A KR19990030878 A KR 19990030878A KR 100299748 B1 KR100299748 B1 KR 100299748B1
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South Korea
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solar panel
satellite
rotating cylinder
test apparatus
fixed
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KR1019990030878A
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Korean (ko)
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KR20010011486A (en
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김성훈
김진철
김정수
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장근호
한국항공우주연구원
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G7/00—Simulating cosmonautic conditions, e.g. for conditioning crews
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02S—GENERATION OF ELECTRIC POWER BY CONVERSION OF INFRARED RADIATION, VISIBLE LIGHT OR ULTRAVIOLET LIGHT, e.g. USING PHOTOVOLTAIC [PV] MODULES
    • H02S50/00—Monitoring or testing of PV systems, e.g. load balancing or fault identification
    • H02S50/10—Testing of PV devices, e.g. of PV modules or single PV cells
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/42—Arrangements or adaptations of power supply systems
    • B64G1/44—Arrangements or adaptations of power supply systems using radiation, e.g. deployable solar arrays
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
    • Y02E10/00—Energy generation through renewable energy sources
    • Y02E10/50—Photovoltaic [PV] energy

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  • Engineering & Computer Science (AREA)
  • Remote Sensing (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Sustainable Development (AREA)
  • Photovoltaic Devices (AREA)

Abstract

본 발명은 인공위성에 장착되는 태양전지판의 전개상태를 지상에서 시험할 수 있도록 하는 인공위성 태양전지판 전개시험장치에 관한 것이다.The present invention relates to a satellite solar panel development test apparatus that allows the development of the solar panel mounted on the satellite can be tested on the ground.

이러한 본 발명은 바닥에 고정된 고정축에 회전자재로 외삽되는 회전실린더와, 회전실린더 일측에 부착되는 태양전지판과, 태양전지판의 대향된 방향에서 회전실린더에 설치되는 카운터매스(Counter mass)와, 태양전지판 상부에 결합된 번지케이블과, 번지케이블이 수평이동되게 상부에 고정되는 가이드빔을 구비시킴으로써 이루어진다.The present invention is a rotating cylinder which is extrapolated to the rotating shaft on the fixed shaft fixed to the floor, a solar panel attached to one side of the rotating cylinder, a counter mass (counter mass) installed in the rotating cylinder in the opposite direction of the solar panel, The bungee cable coupled to the upper portion of the solar panel, and the bungee cable is made by having a guide beam fixed to the upper portion to move horizontally.

Description

태양전지판 전개 시험장치{Deployment test apparatus of solar array}Deployment test apparatus of solar array

본 발명은 인공위성에 장착되는 태양전지판의 전개상태를 지상에서 시험할 수 있도록 하는 인공위성 태양전지판 전개시험장치에 관한 것이다.The present invention relates to a satellite solar panel development test apparatus that allows the development of the solar panel mounted on the satellite can be tested on the ground.

인공위성은 발사체에 실려 우주로 발사될 때 그 부피를 줄이기 위하여 도 1 에 도시된 바와 같이 인공위성(1)의 본체(2)에 부착된 태양전지판(3)을 접어서 발사체 속에 탑재되어 발사된 후 인공위성(1)이 본 궤도에 올라가면 태양에너지를 이용하여 전기를 생성하고자 접혀져 있던 태양전지판(3)을 펼쳐주게 된다.In order to reduce the volume when the satellite is launched into space by a projectile, the satellite is folded and mounted on the projectile and mounted on the main body 2 of the satellite 1 as shown in FIG. When 1) climbs to this orbit, it unfolds the folded solar panel 3 to generate electricity using solar energy.

인공위성(1)의 태양전지판(3)의 궤도에서 잘 펼쳐지지 않으면 위성이 요구하는 전력을 생산하지 못하게 되고 이 경우 인공위성(1)은 그 목적하는 대로 사용되지 못하고 실패하게 되는 것이다.If it is not well unfolded in the orbit of the solar panel 3 of the satellite 1, the satellite will not produce the required power, and in this case, the satellite 1 will not be used as intended and will fail.

따라서 몸체(2)에서 태양전지판(3)이 잘 펼쳐지는 가를 지상에서 시험을 해 보아야 하나 지상에서 우주와 같은 무중력 상태를 구현하기 어려워 시험에 어려움이 따르는 것이었다.Therefore, it should be tested on the ground whether the solar panel 3 is well unfolded in the body 2, but it was difficult to implement a weightless state such as space on the ground, which made the test difficult.

태양전지판(3)전개를 시험하기 위해서는 태양전지판(3)을 고정장치에 고정시킨 후 태양전지판(3)에 번지케이블을 묶어준 후 번지케이블의 일단은 가이드빔을 타고 이동될 수 있도록 하여 태양전지판(3)이 무중력상태에 놓인 것과 같이 조건을 만들어 준 후 태양전지판(3)의 전개상태를 관찰하였다.In order to test the development of the solar panel (3), fix the solar panel (3) to the fixing device, tie the bungee cable to the solar panel (3), and then allow one end of the bungee cable to be moved by the guide beam. After (3) was placed in the zero gravity state, the conditions were developed and the developed state of the solar panel (3) was observed.

그러나 본 출원인이 실시하고 있는 다목적 실용위성은 태양전지판이 회전하면서 펼쳐지게 되어 있어 기존과 같은 전개 시험장치를 이용할 경우 번지 케이블이 2차원적으로 움직이게 하여야 하는 어려움이 따르게 된다.However, the multi-purpose practical satellite that is being applied by the present applicant is unfolded while the solar panel is rotated, and thus, when using the conventional deployment test apparatus, the bungee cable has a difficulty of moving two-dimensionally.

본 발명은 인공위성의 태양전지판 전개 시험장치에 있어서, 태양전지판이 부착되는 고정장치를 회전되도록 하여 태양전지판의 전개시험시 번지케이블이 일차원적으로 이동되면서 전개가 이루어지도록 한 것이다.In the present invention, a solar panel development test apparatus for satellites is rotated so that a fixing device to which a solar panel is attached can be developed while the bungee cable is moved one-dimensionally during the development test of the solar panel.

즉 본 발명은 다목적 실용위성의 태양전지판이 회전되면서 전개되므로 태양전지판 전개시 태양전지판 대신 고정장치가 회전되게 하여 태양전지판은 1차원적으로 전개되게 하므로써 번지케이블 및 가이드빔 설계가 용이하도록 한 것이다.That is, the present invention is developed by rotating the solar panel of the multi-purpose practical satellite so that the fixing device is rotated instead of the solar panel when the solar panel is deployed so that the solar panel is developed in one dimension, so that the design of the bungee cable and the guide beam is easy.

이러한 본 발명은 바닥에 고정된 고정축에 회전자재로 외삽되는 회전실린더와, 회전실린더 일측에 부착되는 태양전지판과, 태양전지판의 대향된 방향에서 회전실린더에 설치되는 카운터매스(Counter mass)와, 태양전지판 상부에 결합된 번지케이블과, 번지케이블이 수평이동되게 상부에 고정되는 가이드빔을 구비시킴으로써 이루어진다.The present invention is a rotating cylinder which is extrapolated to the rotating shaft on the fixed shaft fixed to the floor, a solar panel attached to one side of the rotating cylinder, a counter mass (counter mass) installed in the rotating cylinder in the opposite direction of the solar panel, The bungee cable coupled to the upper portion of the solar panel, and the bungee cable is made by having a guide beam fixed to the upper portion to move horizontally.

도 1 은 태양전지판이 접혀진 상태의 인공위성 본체도1 is a satellite body diagram of the solar panel folded state

도 2 는 태양전지판을 펼친 상태의 인공위성 본체도Figure 2 is a satellite body view of the solar panel unfolded state

도 3 은 본 발명 시험장치에 태양전지판을 장착한 정면도Figure 3 is a front view of the solar panel mounted on the test apparatus of the present invention

도 4 는 본 발명 시험장치에 태양전지판을 장착한 평면도4 is a plan view of the solar panel mounted on the test apparatus of the present invention

도 5 는 본 발명 시험장치에서 태양전지판이 전개된 후의 평면도5 is a plan view after the solar panel is deployed in the test apparatus of the present invention

도 6 은 본 발명 시험장치에서 태양전지판이 전개된 후의 정면도6 is a front view after the solar panel is deployed in the test apparatus of the present invention;

[도면의 주요부분에 대한 부호의 설명][Explanation of symbols on the main parts of the drawings]

1 : 인공위성 2 : 본체 3 : 태양전지판1: satellite 2: body 3: solar panel

10 : 고정장치 11 : 고정축 12 : 회전실린더10: fixed device 11: fixed shaft 12: a rotating cylinder

13 : 카운터매스 14 : 루트힌지 15 : 요오크13: counter mass 14: root hinge 15: yoke

16 : 전개분리장치 17 : 번지케이블 18 : 가이드빔16: deployment separator 17: bungee cable 18: guide beam

본 발명의 고정장치(10)는 바닥에 고정된 고정축(11)과, 상기 고정축(11)에 회전자재로 외삽되어 설치되는 회전실린더(12)와, 상기 회전실린더(12)의 일측에 설치된 카운터매스(13)로 구성되며 인공위성의 본체역할을 수행하게 된다.The fixing device 10 of the present invention has a fixed shaft 11 fixed to the bottom, a rotating cylinder 12 is installed to be extrapolated to the fixed shaft 11 by a rotating material, and on one side of the rotating cylinder 12 It is composed of a counter mass 13 is installed and serves as the main body of the satellite.

카운터매스(13)와 반대방향의 회전실린더(12)에는 루트힌지(14)를 이용하여 태양전지판(3)과 요오크(15)로 결합시킨다.The rotating cylinder 12 in the opposite direction to the counter mass 13 is coupled to the solar panel 3 and the yoke 15 using a root hinge 14.

전개분리장치(16)에 의해 전개가 시작되는 태양전지판(3)에는 중력을 없애기 위해 번지케이블(17)을 고정시키고 상기 번지케이블(17)의 타측은 가이드빔(18)이 수평이동 가능한 상태로 결합시킨다.The bungee cable 17 is fixed to the solar panel 3 that is started to be deployed by the deployment separator 16 so as to eliminate gravity, and the other side of the bungee cable 17 is in a state in which the guide beam 18 is horizontally movable. Combine.

이러한 본 발명에서 태양전지판(3)의 전개는 실제 위성에서 사용하는 전개분리장치(16)를 이용하여 고정장치(10)에서 태양전지판(3)을 분리하게 되고 상기 태양전지판(3)은 루트힌지(15)와 패널간 힌지가 갖고 있는 스트레인 에너지가 펼쳐지려는 방향으로 작용하여 태양전지판(3)이 전개된다.In the present invention, the deployment of the solar panel 3 is to separate the solar panel 3 from the fixing device 10 using the deployment separator 16 used in the actual satellite and the solar panel 3 is a root hinge The solar panel 3 is developed by acting in a direction in which the strain energy of the hinge between the panel 15 and 15 is unfolded.

본 발명은 다목적 실용위성과 같이 태양전지판(3)이 회전을 하면서 펼쳐지는시스템을 구현하기 위해 고정장치(10)의 고정축(11)과 회전실린더(12)사이에 축방향으로 베어링을 장착하여 회전이 가능하게 하고 카운터매스(13)를 태양전지판(3)의 반대방향에서 장착하여 인공위성 본체의 관성효과를 구현한다.The present invention is to mount a bearing in the axial direction between the fixed shaft 11 and the rotating cylinder 12 of the fixing device 10 to implement a system in which the solar panel 3 is rotated as a multi-purpose practical satellite Rotation is possible and the countermass 13 is mounted in the opposite direction of the solar panel 3 to realize the inertial effect of the satellite body.

이렇게 함으로써 실제 우주에서는 태양전지판(3)이 회전하면서 펼쳐지는 2차원 운동을 하게 되지만, 본 발명에서는 태양전지판(3)이 회전하는 현상을 회전실런더(12)가 관성효과를 이용하여 회전하게 되므로 태양전지판(3)은 번지케이블(17)에 매달려 가이드빔(18)을 따라 1차원운동만 하게되어 시험장치가 간결해지는 한편 시험의 신뢰도를 높일 수 있다.By doing so, in the real universe, the solar panel 3 is rotated, and the two-dimensional motion is unfolded. However, in the present invention, the phenomenon of the rotation of the solar panel 3 is rotated using the inertial effect. The solar panel 3 hangs on the bungee cable 17 to perform only one-dimensional movement along the guide beam 18, thereby simplifying the test apparatus and increasing the reliability of the test.

따라서 태양전지판(3)은 한방향으로만 펼쳐지게 되고 이에 따라 가이드빔(18)상에서 움직이는 번지케이블(17)도 한방향으로만 움직이게 되어 가이드빔(18)과 수직방향으로의 마찰효과를 최소화할 수 있다.Therefore, the solar panel 3 is unfolded in only one direction and thus the bungee cable 17 moving on the guide beam 18 also moves only in one direction, thereby minimizing the friction effect in the vertical direction with the guide beam 18.

본 발명의 번지케이블(17)은 태양전지판(3)이 펼쳐지는 동안과 펼쳐진 후까지도 중력의 영향이 0이 되도록 보정하는 역할을 하게 된다.The bungee cable 17 of the present invention serves to correct the influence of gravity to zero even when the solar panel 3 is unfolded and even after unfolded.

따라서 태양전지판(3)에 작용하는 중력을 보정하기 위해 태양전지판(3)들이 수평을 잘 이루도록 번지케이블(17)을 조정하여 장착하여야 하고, 태양전지판(3)이 펼쳐지는 운동방향으로 장착된 가이드빔(18)에서의 마찰력에 대한 영향을 최소화하기 위해 가이드빔(18)과 번지케이블(17)사이에는 롤러를 장착하고 충분한 윤활조건을 구현하여 태양전지판(3)전개방향으로의 운동에 영향을 미치지 않도록 한다.Therefore, in order to correct gravity acting on the solar panel 3, the bungee cable 17 should be adjusted and mounted so that the solar panels 3 are well horizontal, and the guide mounted in the movement direction in which the solar panel 3 is unfolded. In order to minimize the influence on the frictional force in the beam 18, rollers are mounted between the guide beam 18 and the bungee cable 17, and sufficient lubrication conditions are implemented to influence the movement in the solar panel 3 deployment direction. Don't get crazy.

또한 번지케이블(17)은 가능한 한 길이를 길게하여 태양전지판 운동방향 외의 다른 방향 운동성분이 태양전지판 전개에 영향을 미치지 않도록 한다.In addition, the bungee cable 17 is made as long as possible so that the movement component in the direction other than the solar panel movement direction does not affect the solar panel development.

그리고 태양전지판(3)의 전개상황은 천장에 비디오 카메라를 장착하여 태양전지판이 전개되는 동안 녹화하고, 바닥면은 가로/세로의 선을 표시하여 시간별로 태양전지판이 펼쳐지는 상황을 모니터링하게 한다.And the development of the solar panel (3) is equipped with a video camera on the ceiling to record during the development of the solar panel, the bottom surface displays the horizontal / vertical line to monitor the solar panel unfolding by time.

본 발명은 태양전지판이 회전하면서 펼쳐지는 인공위성의 태양전지판 전개상태를 시험하는 것으로 위성본체 역할을 하는 고정장치의 회전실린더가 회전되게 하여 태양전지판은 1차원적인 운동을 하면서 펼쳐지도록 하므로써 간단한 시험장치로 시험의 신뢰도를 높일 수 있는 것이다.The present invention is to test the development state of the solar panel of the satellite unfolded while rotating the solar panel by rotating the rotating cylinder of the fixed device that serves as the satellite body by the solar panel to be unfolded during one-dimensional movement as a simple test device The reliability of the test can be increased.

Claims (2)

인공위성 태양전지판 전개 시험장치에 있어서,In the satellite solar panel development test apparatus, 바닥에 고정된 고정축(11)에 회전자재로 외삽되는 회전실린더(12)와,A rotating cylinder 12 which is extrapolated to the fixed shaft 11 fixed to the bottom by a rotating material, 회전실린더(12)일측에 부착되는 태양전지판(3)과,Solar panel 3 attached to one side of the rotating cylinder 12, 상기 태양전지판(3)의 반대위치에서 회전실린더(12)에 설치되는 카운터매스(13)와,A counter mass 13 installed on the rotating cylinder 12 at an opposite position of the solar panel 3, 상기 태양전지판(3)의 상부에 결합된 번지케이블(17)과,Bungee cable 17 coupled to the upper portion of the solar panel 3, 상기 번지케이블(17)이 수평이동되게 상부에 고정되는 가이드빔(18)으로 구성된 것을 특징으로 하는 태양전지판 전개 시험장치.The bungee cable 17 is a solar panel development test device, characterized in that consisting of a guide beam (18) fixed to the upper portion to move horizontally. 제 1 항에서, 고정축(11)과 회전실린더(12)사이에는 축방향으로 베어링을 장착하여 된 것을 특징으로 하는 태양전지판 전개 시험장치.The apparatus of claim 1, wherein a bearing is mounted in the axial direction between the fixed shaft (11) and the rotary cylinder (12).
KR1019990030878A 1999-07-28 1999-07-28 Deployment test apparatus of solar array KR100299748B1 (en)

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KR100400977B1 (en) * 2000-12-21 2003-10-10 한국항공우주연구원 Deployment Test Apparatus of Solar Array under the Cold Environment
KR100472878B1 (en) * 2002-06-04 2005-03-10 한국항공우주연구원 a
KR100832874B1 (en) 2007-06-11 2008-05-28 한국항공우주연구원 Deployment test apparatus of solar array
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KR100315551B1 (en) * 1999-12-07 2001-12-12 장근호 Root hinge assembly and folding test jig
KR100986002B1 (en) * 2008-08-07 2010-10-06 한국항공우주연구원 NEA Unit for Satellite Solar Array Deployment Test AND NEA Simulator Having the same
KR101112000B1 (en) * 2009-06-15 2012-03-15 한국항공우주연구원 Ground-mounting structure for solar cell plate
KR102495624B1 (en) * 2022-08-04 2023-02-06 한화시스템 주식회사 Apparatus and method for testing satellite

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR100400977B1 (en) * 2000-12-21 2003-10-10 한국항공우주연구원 Deployment Test Apparatus of Solar Array under the Cold Environment
KR100472878B1 (en) * 2002-06-04 2005-03-10 한국항공우주연구원 a
KR100832874B1 (en) 2007-06-11 2008-05-28 한국항공우주연구원 Deployment test apparatus of solar array
CN106275525A (en) * 2016-08-12 2017-01-04 浙江工商大学 A kind of sun wing plate air supporting supports ground simulation hanging expanding unit

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