KR20020085020A - a - Google Patents

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Publication number
KR20020085020A
KR20020085020A KR1020010024229A KR20010024229A KR20020085020A KR 20020085020 A KR20020085020 A KR 20020085020A KR 1020010024229 A KR1020010024229 A KR 1020010024229A KR 20010024229 A KR20010024229 A KR 20010024229A KR 20020085020 A KR20020085020 A KR 20020085020A
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KR
South Korea
Prior art keywords
mirror
target mirror
target
bracket
horizontal angle
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KR1020010024229A
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Korean (ko)
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KR100431543B1 (en
Inventor
윤용식
이중엽
이상설
조창래
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한국항공우주연구원
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Priority to KR10-2001-0024229A priority Critical patent/KR100431543B1/en
Publication of KR20020085020A publication Critical patent/KR20020085020A/en
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Publication of KR100431543B1 publication Critical patent/KR100431543B1/en

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    • 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
    • B64G1/222—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles for deploying structures between a stowed and deployed state
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
    • 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
    • B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
    • B64G1/28—Guiding or controlling apparatus, e.g. for attitude control using inertia or gyro effect
    • B64G1/283—Guiding or controlling apparatus, e.g. for attitude control using inertia or gyro effect using reaction wheels
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
    • G01B11/00—Measuring arrangements characterised by the use of optical techniques
    • G01B11/26—Measuring arrangements characterised by the use of optical techniques for measuring angles or tapers; for testing the alignment of axes

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  • Engineering & Computer Science (AREA)
  • Remote Sensing (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Astronomy & Astrophysics (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Length Measuring Devices By Optical Means (AREA)

Abstract

PURPOSE: A method and an apparatus for measuring a target mirror for measuring the reaction wheel alignment of a satellite are provided to precisely control a stand by measuring the error of a target mirror and to measure three-dimensional coordinates by installing a theodolite on the three shafts of the target mirror. CONSTITUTION: A mirror bracket(3) has a fixing stand(2) on which an optical hand mirror(1') is installed vertically. Assembling holes(10) are formed in four portions of an inclined surface(12) on which the mirror bracket and an auxiliary bracket(4) are installed. A reaction wheel(5) is slantingly fixed in connecting holes(6,9) by a fixing bolt(8). The error of a target mirror(1) is measured by checking if the value of the horizontal angle is 180 degrees, zero' or zero" when the theodolite and the target mirror are automatically collimated.

Description

위성체 반작용 휠 얼라인먼트 측정용 타켓미러의 측정방법 및 장치{a}Method and apparatus for measuring target mirror for satellite reaction wheel alignment measurement {a}

본 발명은 우주 궤도에서 위성체의 자세제어를 위해 위성체의 발사전 지상 시험의 일종으로 얼라인먼트를 측정하기 위한 미러 브라켓의 제작과 타켓 미러의 오차를 측정하여 정확한 자세제어를 가능하게 하는 위성체 반작용 휠 얼라인먼트측정용 타켓미러의 측정방법 및 장치에 관한 것이다.The present invention is a kind of ground test before the launch of a satellite in space orbit to produce a mirror bracket for measuring the alignment and to measure the error of the target mirror satellite wheel reaction measurement to enable accurate attitude control It relates to a measuring method and apparatus for a target mirror.

우주 궤도에서 위성체의 자세제어를 위해 위성체의 발사전 지상 시험의 일종으로 얼라인먼트를 측정한다.Alignment is measured as a kind of pre-launch ground test of satellites to control satellites' attitude in space orbit.

얼라인먼트 측정은 측정 기준을 위한 기준 입방 면경(Master Cube)에 대한 각 자세제어용 센서 혹은 탑재 센서에 부착된 타켓 미러(Taget Mirror)의 상대적인 3차원 좌표를 측정하는 것이다.Alignment measurement measures the relative three-dimensional coordinates of a target mirror attached to each attitude control sensor or mounted sensor relative to a reference master cube for measurement criteria.

대부분의 자세제어용 센서 혹은 탑재 센서에서는 얼라인먼트 측정의 정확성을 위하여 제작시 타켓 미러를 보울트 혹은 접착제를 이용하여 장착하지만 반작용 휠(Reaction Wheel)은 장치의 민감성과 미러 설치 위치의 제한성 등으로 얼라인먼트의 측정을 위한 타켓 미러를 설계하고 제작·검증을 거쳐야 한다.Most posture sensors or sensors are equipped with a target mirror using bolts or adhesives for the purpose of alignment measurement accuracy. However, the reaction wheel performs alignment measurement due to the sensitivity of the device and the limitation of the mirror installation position. The target mirror must be designed, manufactured and verified.

본 발명은 위성체의 자세제어용 장치인 반작용 휠의 얼라인먼트를 측정하는 미러 브라켓과 타켓 미러를 제공한다.The present invention provides a mirror bracket and a target mirror for measuring the alignment of the reaction wheel which is a device for attitude control of the satellite.

본 발명은 타켓 미러의 3축에 데오도라이트를 설치하여 얼라인먼트의 측정이나 3차원 좌표 측정이 가능하도록 하는 것이다.The present invention is to install the deodorite on the three axes of the target mirror to enable the measurement of alignment or measurement of three-dimensional coordinates.

본 발명은 광학 면경이 직각으로 설치되는 고정대를 갖는 미러 브라켓과,The present invention provides a mirror bracket having a fixing table that is installed at right angles to the optical mirror;

상기 미러 브라켓과 보조 브라켓이 설치되는 경사면의 4곳에 조립공을 설치하여 연결공에서 고정 보울트로 경사지게 고정되는 반작용 휠을 설치함을 특징으로 하는 것이다.It is characterized in that the reaction hole is installed to be inclined by the fixing bolt in the connection hole by installing the assembly hole in the four places of the inclined surface on which the mirror bracket and the auxiliary bracket is installed.

도 1 은 본 발명의 설치상태 정면도1 is a front view of the installation state of the present invention

도 2 는 본 발명의 설치상태 일부절개 측면도2 is a partially cutaway side view of the installation state of the present invention

도 3 은 본 발명의 측정방법을 나타낸 설치상태 평면도Figure 3 is a plan view of the installation state showing the measuring method of the present invention

[도면의 주요 부분에 대한 부호의 설명][Description of Symbols for Main Parts of Drawing]

1 : 타켓 미러1' : 광학 면경1: target mirror 1 ': optical mirror

2 : 반작용 휠3 : 미러 브라켓2: reaction wheel 3: mirror bracket

4 : 보조 브라켓5 : 반작용 휠4: auxiliary bracket 5: reaction wheel

6, 9 : 연결공7 : 여유공6, 9: connection hole 7: clearance hole

8 : 고정 보울트10 : 조립공8: fixing bolt 10: assembling worker

12 : 경사면13 : 입방 면경12: inclined surface 13: cubic diameter

본 발명은 미러 브라켓(3)을 설치하기 위하여 직접 위성용 반작용 휠에 설치할 수 없으므로, 반작용 휠의 설치 각도와 동일한 각도의 경사면(12)을 갖도록 한다.The present invention can not be installed directly on the reaction wheel for the satellite in order to install the mirror bracket (3), so as to have an inclined surface 12 of the same angle as the installation angle of the reaction wheel.

밑면의 편평도가 0.1㎜이하인 모조 반작용 휠(5)을 구성하며, 경사면(12)의 4곳에 조립공(10)을 형성한다.The flatness of the base constitutes a counter reaction wheel 5 having a thickness of 0.1 mm or less, and the assembly holes 10 are formed in four places of the inclined surface 12.

반작용 휠(5)의 조립공(10)에 일치하는 연결공(9)을 형성한 보조 브라켓(4)을 설치하고, 보조 브라켓(4)의 상측으로 연결공(6)이 형성된 미러 브라켓(3)을 형성하여 연결공(6, 9)에서 고정 보울트(8)로 반작용 휠(5)의 조립공(10)에 연결시킨다.Mirror bracket (3) provided with auxiliary bracket (4) having a connection hole (9) corresponding to the assembly hole (10) of the reaction wheel (5), and having a connection hole (6) formed above the auxiliary bracket (4). Formed to connect to the assembly hole 10 of the reaction wheel (5) with a fixing bolt (8) in the connection hole (6, 9).

이때 반작용 휠(5)과 조립공(10) 및 경사면(12)은 위성용 반작용 휠과 동일한 위치와 크기로 제작한다.At this time, the reaction wheel 5, the assembly hole 10 and the inclined surface 12 is manufactured in the same position and size as the reaction wheel for satellite.

미러 브라켓(3)은 알루미늄 등의 재질로 제작하여 위성용 반작용 휠(5)의 조립공(10)에서 동일한 위치에 조립할 수 있도록 한다.The mirror bracket 3 is made of a material such as aluminum to be assembled at the same position in the assembly hole 10 of the reaction wheel 5 for the satellite.

미러 브라켓(3)의 상단 중앙에는 고정대(2)를 형성하여 직각을 이루도록 하고, 직각이 확인된 상태에서 접착제를 사용하여 파장이 λ/4인 광학 면경(1')을 수직으로 설치하여 타켓 미러(1)의 설치작업을 완료한다.In the center of the upper end of the mirror bracket (3) to form a fixing stand (2) to form a right angle, and the optical mirror (1 ') having a wavelength of λ / 4 is installed vertically using an adhesive in a state where the right angle is confirmed, the target mirror Complete the installation in (1).

미러 브라켓(3)의 고정 보울트(8)가 4곳에 설치되어 있으며, 양측으로 2개씩의 여유공(7)을 설치한다.Fixing bolts 8 of the mirror bracket 3 are provided at four locations, and two clearance holes 7 are provided at both sides.

본 발명은 도 3 과 같이 타켓 미러(2)의 후방과 측면으로 데오도라이트(A, B)를 설치하고 정면으로 또하나의 데오도라이트(C)를 설치한다.The present invention is to install the deodorite (A, B) in the rear and side of the target mirror (2) as shown in Figure 3 and install another deodorite (C) in front.

상기 데오도라이트(A, B, C)에는 타켓 미러(2)를 향하여 입방 면경(13)이 설치되어 있다.The deodorites A, B, and C are provided with a cubic mirror 13 toward the target mirror 2.

이러한 구성으로 이루어진 본 발명은 타켓 미러(1)를 측정하기 위하여 지면이 고르고, 내·외부의 진동이 없는 장소에 석정반 혹은 편평도가 좋은 평판에서 타켓 미러(1)가 설치된 미러 브라켓(3)과 반작용 휠(5)을 결합하여 올려놓는다.The present invention having such a configuration includes a mirror bracket (3) provided with the target mirror (1) in a flat surface or a flat plate in a good flatness and flatness in a place without vibrations inside and outside to measure the target mirror (1) and Combine and place the reaction wheel (5).

반작용 휠(5)의 반대쪽에 직각자로 직각을 확인한 위치에 입방 면경(Cube Mirror)을 설치한다.A cube mirror is installed on the opposite side of the reaction wheel 5 at a position where a right angle is identified at a right angle.

각도를 정밀 측정하는 데오도라이트 2대를 입방 면경(13) 2면의 정면에 설치하여 타켓 미러(1) 정 반대면을 측정하는 데오도라이트를 A라 하고, 이 입방 면경(13)의 수직 방향면을 측정하는 데오도라이트를 B라고 하며, 미러 브라켓(3)에 설치된 타켓 미러(1) 정면에 설치되어 측정하는 데오도라이트를 C라고 한다.The two deodorites for precisely measuring the angle are installed in front of the two surfaces of the cubic mirror 13 and the deodorites for measuring the opposite surface of the target mirror 1 are called A, and the perpendicular of the cubic mirror 13 The deodorite for measuring the directional plane is called B, and the deodorite is installed at the front of the target mirror 1 installed on the mirror bracket 3 and measured.

먼저, 타켓 미러(1) 정 반대면에 있는 입방 면경(13)의 수직각이 0° 0' 0", 수직각이 90° 0' 0" 가 되도록 하고, 이 면의 직각에 있는 입방 면경(13)의 수평각이 90° 0' 0", 수직각이 90° 0' 0" 가 되도록 조정한다.First, the vertical angle of the cubic mirror 13 on the opposite side of the target mirror 1 is 0 ° 0 '0 ", and the vertical angle is 90 ° 0' 0". 13) Adjust the horizontal angle of 90 ° 0 '0 "and the vertical angle of 90 ° 0' 0".

입방 면경의 위치 조정이 완료되면, 데오도라이트(A, B)를 오토-콜리메이션 (Auto-Collimation)한다.When the positioning of the cubic mirror is completed, auto-collimation of the deodorites A and B is performed.

이때 타켓 미러(1) 반대편을 측정한 데오도라이트(A)의 오토-콜리메이션된 수평각 값에 180°를 더한 후 360°를 뺀 값을 데오도라이트(B)에 수평각으로 입력한다.At this time, 180 ° is added to the auto-collimated horizontal angle value of the deodorite (A) measured on the opposite side of the target mirror (1), and the value obtained by subtracting 360 ° is input to the deodorite (B) as the horizontal angle.

다시 데오도라이트(B)와 데오도라이트(C)를 오토-콜리메이션하고, 수평각이입력된 상태에서 측정된 데오도라이트(B)에서 측정되는 수평각 값에 180°를 더한 후 360°를 뺀 값을 데오도라이트(C)에 수평값으로 입력한다.Auto-collimate the theodolites (B) and theodolites (C) again, add 180 ° to the horizontal angle values measured at the deodorites (B) measured with the horizontal angle input, and subtract 360 °. Enter the value as a horizontal value in theodolite (C).

수평각이 입력된 상태에서 데오도라이트(C)와 타켓 미러(1)를 오토-콜리메이션하여 이때 수평각의 값이 180° 0' 0" 가 되는지를 확인한다.Auto-collimate the deodorite (C) and the target mirror (1) while the horizontal angle is input, and check if the horizontal angle is 180 ° 0 '0 ".

만약 180°0' 0" 가 되지 않는 경우에는 미러 제작상의 오차 혹은 반작용 휠(5)의 경사면(12)이 제작상의 오차로 판단하여 이 차이값을 실제 반작용 휠의 측정시 계산하여야 한다.If the angle is not 180 ° 0 '0 ", the mirror manufacturing error or the inclined surface 12 of the reaction wheel 5 is determined as the manufacturing error, and this difference value should be calculated when measuring the actual reaction wheel.

본 발명은 인공위성 자세제어 센서인 반작용 휠의 얼라인먼트 측정뿐만 아니라 방향성이 요구되는 항공기 및 인공위성의 자세제어용 센서의 얼라인먼트 측정이나 3차원 좌표 측정시 동일한 방법으로 장치를 제작하여 사용할 수 있는 효과를 제공한다.The present invention provides the effect that the device can be manufactured and used in the same way when the alignment measurement or three-dimensional coordinate measurement of the attitude control sensor of the aircraft and satellites that require directionality as well as the alignment measurement of the reaction wheel which is a satellite attitude control sensor.

Claims (3)

타켓 미러 정 반대면에 있는 입방 면경의 수직각이 0° 0' 0", 수직각이 90° 0' 0" 가 되도록 하고, 이 면의 직각에 있는 입방 면경의 수평각이 90° 0' 0", 수직각이 90° 0' 0" 가 되도록 조정하는 과정과,The vertical angle of the cubic mirror on the opposite side of the target mirror is 0 ° 0 '0 ", the vertical angle is 90 ° 0' 0", and the horizontal angle of the cubic mirror at right angles is 90 ° 0 '0 ". To adjust the vertical angle to 90 ° 0 '0 ", 입방 면경의 위치 조정이 완료되면, 데오도라이트(A, B)를 오토-콜리메이션 하여 타켓 미러(1) 반대편을 측정한 데오도라이트(A)의 오토-콜리메이션된 수평각 값에 180°를 더한 후 360°를 뺀 값을 데오도라이트(B)에 수평각으로 입력하는 과정과,When the positioning of the cubic mirror is completed, the auto-collimation of the deodorites (A, B) is performed to measure 180 ° to the auto-collimated horizontal angle value of the deodorites (A) measured on the opposite side of the target mirror (1). Add the subtracted 360 ° to the deodorite (B) as a horizontal angle, 다시 데오도라이트(B)와 데오도라이트(C)를 오토-콜리메이션하고, 수평각이 입력된 상태에서 측정된 데오도라이트(B)에서 측정되는 수평각 값에 180°를 더한 후 360°를 뺀 값을 데오도라이트(C)에 수평값으로 입력하는 과정과,Auto-collimate the theodolites (B) and theodolites (C) again, add 180 ° to the horizontal angle measured from the deodorite (B) measured with the horizontal angle input, and subtract 360 °. Inputting a value into a deodorite (C) as a horizontal value, 수평각이 입력된 상태에서 데오도라이트(C)와 타켓 미러를 오토-콜리메이션하여 이때 수평각의 값이 180°0' 0" 가 되는지를 확인하여 오차를 측정함을 특징으로 하는 위성체 반작용 휠 얼라인먼트 측정용 타켓미러의 측정방법.Auto-collimates the deodorite (C) and the target mirror in the state where the horizontal angle is input, and measures the error by checking whether the horizontal angle value becomes 180 ° 0 '0 "at this time. Measurement method of target mirror. 위성체의 자세제어용 장치인 반작용 휠(5)의 얼라인먼트 측정을 위한 미러 브라켓에 있어서,In the mirror bracket for the alignment measurement of the reaction wheel (5) which is a device for attitude control of the satellite body, 광학 면경(1')이 직각으로 설치되는 고정대(2)를 갖는 미러 브라켓(3)과,A mirror bracket (3) having a fixing table (2) on which an optical surface mirror (1 ') is installed at a right angle, 상기 미러 브라켓(3)과 보조 브라켓(4)이 설치되는 경사면(12)의 4곳에 조립공(10)을 설치하여 연결공(6, 9)에서 고정보울트(8)로 경사지게 고정되는 반작용 휠(5)을 구성함을 특징으로 하는 위성체 반작용 휠 얼라인먼트 측정용 타켓미러의 측정장치.Reaction wheel (5) installed inclined from the connecting holes (6, 9) to the high information bolt (8) by installing assembly holes (10) in four places of the inclined surface (12) where the mirror bracket (3) and the auxiliary bracket (4) are installed. Target mirror measuring device for measuring the reaction wheel alignment of the satellite body, characterized in that the configuration. 제2항에 있어서, 타켓 미러(1)의 후방과 측면에 데오도라이트 (A, B)를 설치하고, 타켓 미러(1)의 전방으로 데오도라이트(C)를 설치하여 타켓미러(1)를 측정하도록 함을 특징으로 하는 위성체 반작용 휠 얼라인먼트 측정용 타켓미러의 측정장치.The target mirror (1) according to claim 2, wherein deodorites (A, B) are provided on the rear and side surfaces of the target mirror (1), and deodorites (C) are installed in front of the target mirror (1). Target mirror measuring device for measuring the reaction reaction wheel alignment, characterized in that to measure.
KR10-2001-0024229A 2001-05-04 2001-05-04 a KR100431543B1 (en)

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JPS58111716A (en) * 1981-12-26 1983-07-02 Nippon Kogaku Kk <Nikon> Scale reading device of theodolite
JPS58148927A (en) * 1982-03-01 1983-09-05 Matsushita Electric Ind Co Ltd Earth sensor for artificial satellite attitude control
JP3165987B2 (en) * 1993-12-10 2001-05-14 日本電気エンジニアリング株式会社 Alignment measurement system and its measurement method
US6089508A (en) * 1998-03-02 2000-07-18 Hughes Electronics Corporation Autonomous spacecraft safing with reaction wheels
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