JP2003098441A - Space telescope - Google Patents
Space telescopeInfo
- Publication number
- JP2003098441A JP2003098441A JP2001292224A JP2001292224A JP2003098441A JP 2003098441 A JP2003098441 A JP 2003098441A JP 2001292224 A JP2001292224 A JP 2001292224A JP 2001292224 A JP2001292224 A JP 2001292224A JP 2003098441 A JP2003098441 A JP 2003098441A
- Authority
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- Japan
- Prior art keywords
- main reflecting
- space
- mirror surface
- reflecting mirrors
- support structure
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
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- Telescopes (AREA)
- Mounting And Adjusting Of Optical Elements (AREA)
Abstract
Description
【０００１】[0001]
【発明の属する技術分野】この発明は、例えば宇宙空間
に配備され、各種の観測を実行する宇宙望遠鏡に関す
る。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a space telescope that is deployed in outer space and performs various observations.
【０００２】[0002]
【従来の技術】宇宙開発の分野においては、宇宙空間に
宇宙望遠鏡を配備して宇宙空間から地上や、他の惑星等
の観測を実行する観測システムがある。このような宇宙
望遠鏡は、例えば図１２に示すようなハッブル宇宙望遠
鏡を知られている。このハッブル宇宙望遠鏡は、電力源
を形成する太陽電池パドル１、及び図示しない姿勢制御
系や通信系等で構成される宇宙用バス系機器２を備え
て、その姿勢を、宇宙ようバス系機器の姿勢制御系（図
示せず）で制御しながらその望遠鏡本体３で所望の方向
の光を集光する。そして、この望遠鏡本体３で集光した
光は、その観測部４で、例えば受光及び記録されて、そ
の取得した観測データが上記通信系を介して基地局に送
信される。2. Description of the Related Art In the field of space development, there is an observation system that deploys a space telescope in outer space to observe the ground and other planets from outer space. As such a space telescope, for example, a Hubble space telescope as shown in FIG. 12 is known. This Hubble Space Telescope is equipped with a solar cell paddle 1 that forms a power source and a space bus system device 2 including an attitude control system and a communication system (not shown). The telescope main body 3 collects light in a desired direction while controlling it by an attitude control system (not shown). Then, the light condensed by the telescope main body 3 is received and recorded by the observation unit 4, for example, and the acquired observation data is transmitted to the base station via the communication system.
【０００３】しかしながら、上記宇宙望遠鏡では、それ
自体を宇宙空間まで輸送して配備しなければならない構
成上、その宇宙空間までの輸送の制約により、望遠鏡本
体３の光を集光する反射鏡の開口径の大口径化を図るの
が困難であるために、その観測の信頼性や運用の多様化
の要請を満足することが困難であるという問題を有す
る。However, in the above-mentioned space telescope, due to the structure that the space telescope itself has to be transported and deployed to outer space, due to the constraint of transportation to the outer space, the opening of the reflecting mirror for condensing the light of the telescope main body 3. Since it is difficult to increase the diameter, it is difficult to satisfy the requirements of the reliability of observation and diversification of operation.
【０００４】そこで、最近の宇宙開発の分野において
は、開口径の大口径化を図り得るようにした宇宙望遠鏡
の開発が急がれている。Therefore, in the recent field of space development, there is an urgent need to develop a space telescope capable of increasing the aperture diameter.
【０００５】[0005]
【発明が解決しようとする課題】以上述べたように、従
来の宇宙望遠鏡では、開口径の大口径化が困難であると
いう問題を有する。As described above, the conventional space telescope has a problem that it is difficult to increase the aperture diameter.
【０００６】この発明は、上記の事情に鑑みてなされた
もので、宇宙空間までの効率的な輸送を実現したうえ
で、開口径の大口径化を図り得るようにして、信頼性の
高い高精度な観測を実現した宇宙望遠鏡を提供すること
を目的とする。The present invention has been made in view of the above circumstances, and realizes efficient transportation to outer space and, at the same time, makes it possible to increase the diameter of the aperture, thereby achieving high reliability and high reliability. The purpose is to provide a space telescope that realizes accurate observation.
【０００７】[0007]
【課題を解決するための手段】この発明は、支持構造体
の周囲に着脱可能に配設される外形が略六角形形状に形
成された複数の主反射鏡と、これら複数の主反射鏡の鏡
面に対向して配設される複数の副反射鏡と、前記複数の
主反射鏡及び複数の副反射鏡を介して集光した光を観測
する光観測手段と、宇宙航行体を構成するための宇宙バ
ス系とを備えて宇宙望遠鏡を構成した。SUMMARY OF THE INVENTION According to the present invention, a plurality of main reflecting mirrors, each of which has a substantially hexagonal outer shape and which is detachably arranged around a support structure, and a plurality of main reflecting mirrors are provided. A plurality of sub-reflecting mirrors arranged to face the mirror surface, a light observing means for observing the light condensed through the plurality of main reflecting mirrors and the plurality of sub-reflecting mirrors, and for configuring a spacecraft. The space telescope was constructed with the space bus system.
【０００８】上記構成によれば、複数の主反射鏡は、支
持構造体の周囲に略リング形状に配置することができる
ことにより、その収納状態における外形寸法を所望の寸
法に保ってうえで、鏡面としての開口径の大口径化を促
進することが可能となる。従って、信頼性の高い高精度
な観測を行うことが可能となる。According to the above construction, since the plurality of main reflecting mirrors can be arranged in a substantially ring shape around the support structure, the outer dimensions in the housed state can be maintained at desired dimensions and the mirror surface can be maintained. As a result, it is possible to promote the increase of the opening diameter. Therefore, highly reliable and highly accurate observation can be performed.
【０００９】また、この発明は、複数の主反射鏡が着脱
されて所望の鏡面を形成する支持構造体を組立可能ある
いは折り畳み展開可能に構成した。これによれば、宇宙
空間までの輸送の簡略化の促進を図ることが可能とな
る。Further, according to the present invention, a support structure having a plurality of main reflecting mirrors attached and detached to form a desired mirror surface can be assembled or folded and developed. According to this, it becomes possible to promote simplification of transportation to outer space.
【００１０】また、この発明は、支持構造体に電気コネ
クタを有した複数の取っ手を所定の間隔に設けて、作業
ロボットアームが取っ手を把持した状態で、該作業ロボ
ットアームが電気コネクタを介して宇宙バス系と電気的
に接続され、所望の作業が可能に構成した。これによれ
ば、支持構造体の作業ロボットアームを使用した主反射
鏡の着脱作業を含む各種の作業を、安全に行うことが可
能となる。Further, according to the present invention, a plurality of handles having an electric connector are provided on a support structure at predetermined intervals, and the work robot arm holds the handles while the work robot arm interposes the electric connectors. It was electrically connected to the space bus system, and was configured so that desired work could be performed. According to this, it becomes possible to safely perform various works including the work of attaching and detaching the main reflecting mirror using the work robot arm of the support structure.
【００１１】また、この発明は、前記光観測手段を、前
記複数の主反射鏡で集光した光を個別に観測する個別観
測手段と、前記複数の主反射鏡で集光した光を合成して
観測する光束合成観測手段と、前記個別観測手段及び前
記光束合成観測手段のいずれかを選択して個別観測ある
いは光束合成観測を実行する観測選択手段とを備えて構
成した。In the present invention, the light observing means combines the individual observing means for individually observing the light collected by the plurality of main reflecting mirrors with the light collecting by the plurality of main reflecting mirrors. And the observation selection means for selecting either the individual observation means or the luminous flux synthesis observation means to perform individual observation or luminous flux synthesis observation.
【００１２】上記構成によれば、観測選択手段により、
個別観測あるいは光束合成観測を実行することにより、
高精度な観測を実現したうえで、運用の多様化を図るこ
とが可能となる。According to the above arrangement, the observation selection means
By performing individual observation or luminous flux combination observation,
It is possible to diversify the operation after realizing highly accurate observation.
【００１３】また、この発明は、複数の主反射鏡を、外
形が略六角形形状の鏡面支持体と、この鏡面支持体の一
方面に配設される略中央部にバッフル筒が設けられた反
射鏡面とを備え、前記鏡面支持体の鏡面側及び背面側に
第１及び第２の嵌合部を設けると共に、前記反射鏡面の
バッフル筒の両端に第３及び第４の嵌合部を設けて前記
鏡面支持体の第１の嵌合部を、他の主反射鏡の鏡面支持
体の第２の嵌合部と嵌合させ、前記反射鏡面のバッフル
筒の第３の嵌合部を前記他の主反射鏡のバッフル筒の第
４の嵌合部と嵌合させて複数個を積重状に収容可能に構
成した。Further, according to the present invention, a plurality of main reflecting mirrors are provided, a mirror surface support having an outer shape of a substantially hexagonal shape, and a baffle tube provided at a substantially central portion provided on one surface of the mirror surface support. A reflecting mirror surface, first and second fitting portions are provided on a mirror surface side and a back surface side of the mirror surface support, and third and fourth fitting portions are provided on both ends of the baffle cylinder of the reflecting mirror surface. The first fitting portion of the mirror surface support member with the second fitting portion of the mirror surface support member of the other main reflecting mirror, and the third fitting portion of the reflecting mirror surface baffle tube is connected to the first fitting portion. A plurality of the plurality of main reflecting mirrors can be housed in a stack by being fitted with the fourth fitting portion of the baffle cylinder.
【００１４】上記構成によれば、複数の主反射鏡は、そ
の鏡面支持体の第１の嵌合部を、他の主反射鏡の鏡面支
持体の第２の嵌合部と嵌合させ、その反射鏡面のバッフ
ル筒の第３の嵌合部を他の主反射鏡のバッフル筒の第４
の嵌合部と嵌合させて複数個が順に積重状に収容配置さ
れる。従って、開口径の大口径化を実現したうえで、コ
ンパクトな収納が可能となり、宇宙空間への簡便にして
容易な輸送が可能となる。According to the above construction, in the plurality of main reflecting mirrors, the first fitting portion of the mirror surface support body is fitted with the second fitting portion of the mirror surface support body of the other main reflecting mirror, The third fitting portion of the baffle cylinder on the reflecting mirror surface is connected to the fourth fitting of the baffle cylinder of the other main reflecting mirror.
A plurality of them are sequentially accommodated and stacked in a stack by being fitted with the fitting portion of. Therefore, it is possible to realize a large opening diameter and compact storage, and it is possible to easily and easily transport into space.
【００１５】[0015]
【発明の実施の形態】以下、この発明の実施の形態につ
いて、図面を参照して詳細に説明する。BEST MODE FOR CARRYING OUT THE INVENTION Embodiments of the present invention will now be described in detail with reference to the drawings.
【００１６】図１及び図２は、この発明の一実施の形態
に係る宇宙望遠鏡を示すもので、図１は側面を示し、図
２は、鏡面側から見た状態を示す。即ち、支持構造体１
０は、例えば梁部材が、折り畳み展開可能に略六角柱形
状にトラス結合されて形成される。そして、この支持構
造体１０には、その一方端の周囲に略六角形形状の主反
射鏡１１が６台、略円形状に着脱可能に取り付けられ
る。この支持構造体１０の他方端には、副鏡取付部１０
１が上記６台の主反射鏡１１に対応して６箇所設けら
れ、この各副鏡取付部１０１には、副反射鏡１２がそれ
ぞれ主反射鏡に対向するように取り付けられる。1 and 2 show a space telescope according to an embodiment of the present invention. FIG. 1 shows a side surface, and FIG. 2 shows a state viewed from the mirror surface side. That is, the support structure 1
0 is formed, for example, by beam members being trussed in a substantially hexagonal column shape so as to be foldable and expandable. The support structure 10 has six substantially hexagonal main reflecting mirrors 11, which are detachably attached in a substantially circular shape, around one end thereof. At the other end of the support structure 10, the secondary mirror mounting portion 10
1 is provided in 6 places corresponding to the above-mentioned 6 main reflecting mirrors 11, and the sub reflecting mirrors 12 are attached to the respective sub mirror attaching portions 101 so as to face the main reflecting mirrors.
【００１７】上記主反射鏡１１は、例えば図３に示すよ
うに骨組み構造に形成される鏡面支持体１３と、該鏡面
支持体１３上に組み付けられる、例えばガラス等で略放
物面形状に形成される反射鏡面１４で構成される。この
うち鏡面支持体１３は、図４に示すようにその外形が上
記支持構造体１０の一辺に対応するように略六角形形状
に形成され、その一方面には、鏡面支持部１３１が設け
られる。そして、この鏡面支持部１３１上には、上記反
射鏡面１４の背面側が載置されて組み付けられる。The main reflecting mirror 11 is, for example, as shown in FIG. 3, a mirror surface support 13 formed in a frame structure, and is assembled on the mirror surface support 13 and is formed of, for example, glass in a substantially parabolic shape. The reflecting mirror surface 14 is formed. Of these, the mirror surface support 13 is formed in a substantially hexagonal shape so that its outer shape corresponds to one side of the support structure 10 as shown in FIG. 4, and a mirror surface support portion 131 is provided on one surface thereof. . Then, the back side of the reflecting mirror surface 14 is placed and assembled on the mirror surface supporting portion 131.
【００１８】また、鏡面支持体１３には、その周囲の一
辺に構造体結合部１３２が上記支持構造体１０１に対応
して設けられ、この構造体結合部１３２を介して上記支
持構造体１３２に着脱される。さらに、鏡面支持体１３
２には、構造体結合部１３２を挟んで鏡面結合部１３３
がそれぞれ設けられ、この鏡面結合部１３３を介して隣
接される他の主反射鏡１１の鏡面支持体１３に鏡面結合
部１３３と着脱される。Further, the mirror support 13 is provided with a structure connecting portion 132 on one side around the mirror support 13 corresponding to the support structure 101, and is connected to the support structure 132 via the structure connecting portion 132. Detachable. Furthermore, the mirror surface support 13
2 includes a mirror coupling part 133 with the structure coupling part 132 interposed therebetween.
Are provided respectively, and are attached to and detached from the mirror surface coupling portion 133 on the mirror surface support 13 of the other main reflecting mirror 11 which is adjacent via the mirror surface coupling portion 133.
【００１９】さらに、上記鏡面支持体１３には、その鏡
面側の上面側に例えば図５に示すように凹状の第１の嵌
合部１３４が所定の間隔に設けられ、その背面側に凸状
に第２の嵌合部１３５が上記第１の嵌合部１３４に対応
して所定の間隔に設けられる。これら第１及び第２の嵌
合部１３４、１３５には、異なる主反射鏡１１の鏡面支
持体１３の第２及び第１の嵌合部１３５、１３４が嵌合
される。Further, the mirror-like support 13 is provided with concave first fitting portions 134 at predetermined intervals on the mirror-like upper surface thereof, as shown in FIG. Second fitting portions 135 are provided at predetermined intervals corresponding to the first fitting portions 134. The first and second fitting portions 134, 135 are fitted with the second and first fitting portions 135, 134 of the mirror surface support 13 of the different main reflecting mirror 11.
【００２０】また、上記反射鏡面１４には、その略中央
部に遮光用のバッフル筒１５が設けられ、このバッフル
筒１５には、両端に嵌合可能に構成する第３及び第４の
嵌合部１５１、１５２が形成される。この第３及び第４
の嵌合部１５１、１５２は、他の主反射鏡１１の反射鏡
面１４のバッフル筒１５の第４及び第３の嵌合部１５
２、１５１に嵌合される。The reflecting mirror surface 14 is provided with a baffle cylinder 15 for light shielding at a substantially central portion thereof, and the baffle cylinder 15 is provided with third and fourth fittings which can be fitted to both ends. The parts 151 and 152 are formed. This third and fourth
The fitting portions 151, 152 of the second and third fitting portions 15 of the baffle cylinder 15 of the reflecting mirror surface 14 of the other main reflecting mirror 11
2, 151 is fitted.
【００２１】即ち、６台の主反射鏡１１は、その第１及
び第３の嵌合部１３４、１５１に対して、その鏡面側に
積重される他の主反射鏡１１に第２及び第４の嵌合部１
３５、１５２が嵌合され、その第２及び第４の嵌合部１
３５、１５２に対してその背面側に積重される他の主反
射鏡１１の第１及び第３の嵌合部１３４、１５１が嵌合
されて積重配置される。これにより、６台の主反射鏡１
１は、その第１乃至第４の嵌合部１３４、１３５、１５
１、１５２の作用により、略六角柱形状に位置決めされ
た状態で収納されて、宇宙空間への効率的な輸送が可能
となる。That is, the six main reflecting mirrors 11 are provided with the second and second main reflecting mirrors 11 stacked on the mirror surface side of the first and third fitting portions 134 and 151. Fitting part 1 of 4
35 and 152 are fitted together, and the second and fourth fitting portions 1 thereof are
The first and third fitting portions 134 and 151 of the other main reflecting mirror 11, which are stacked on the back surface side of 35 and 152, are fitted and stacked. As a result, the six main reflecting mirrors 1
1 is the first to fourth fitting portions 134, 135, 15
By the action of 1, 152, it is housed in a state of being positioned in a substantially hexagonal prism shape, and efficient transportation to outer space is possible.
【００２２】上記６台の主反射鏡１１には、そのバッフ
ル筒１５の出力側に個別観測装置１６がそれぞれ配設さ
れる。この個別観測装置１６は、例えば図６に示すよう
にバッフル筒１５に対応して配設される個別観測選択用
の切換反射境１６１及び個別観測部１６２でそれぞれ構
成される。この切換反射鏡１６１は、例えば後述する通
信系の通信アンテナ１７を介して入力される切換信号に
より切換制御され、バッフル筒１５に集光された光を選
択的に個別観測部１６２に案内する。この個別観測部１
６２は、入力した光を受光して例えば記録すると共に、
その観測データを、上記通信アンテナ１７を介して地上
局等の基地局に送信する。An individual observation device 16 is provided on the output side of the baffle cylinder 15 of each of the six main reflecting mirrors 11. The individual observation device 16 is composed of a switching reflection boundary 161 for individual observation selection and an individual observation unit 162, which are arranged corresponding to the baffle cylinder 15 as shown in FIG. 6, for example. The switching reflecting mirror 161 is switch-controlled by a switching signal input via a communication antenna 17 of a communication system described later, and selectively guides the light condensed on the baffle tube 15 to the individual observation section 162. This individual observation section 1
62 receives the input light and, for example, records the received light,
The observation data is transmitted to a base station such as a ground station via the communication antenna 17.
【００２３】また、切換反射鏡１６１の後段には、光束
合成光学系１８が設けられ、この光束合成光学系１８の
後段には、観測部１９が配設される。この光束結合光学
系１８には、主反射鏡１１に対応して位相調整器１８１
及び指向制御機構部１８２がそれぞれ設けられ、その出
力側には、上記観測部１９及び偏差・位相差検出センサ
２０が部分反射器２１を介して設けられる。Further, a light beam combining optical system 18 is provided after the switching reflecting mirror 161, and an observing section 19 is provided after the light beam combining optical system 18. The beam combiner optical system 18 includes a phase adjuster 181 corresponding to the main reflecting mirror 11.
, And a pointing control mechanism section 182 are provided respectively, and the observation section 19 and the deviation / phase difference detection sensor 20 are provided on the output side thereof via a partial reflector 21.
【００２４】このうち偏差・位相差検出センサ２０は、
部分反射器２１を介して光束合成された光が入力される
と、その偏差及び位相差を検出して信号処理部２２に出
力する。信号処理部２２は、入力した偏差及び位相差情
報に基づいて主反射鏡１１毎の指向駆動信号及び位相調
整信号を形成して上記指向制御機構部１８２及び位相調
整器１８１に出力する。この指向制御機構部１８２及び
位相調整器１８２は、入力した指向駆動信号及び位相調
整信号に基づいて指向方向を制御すると共に、その位相
を調整制御する。Of these, the deviation / phase difference detection sensor 20 is
When the light combined by the light flux is input through the partial reflector 21, the deviation and the phase difference are detected and output to the signal processing unit 22. The signal processing unit 22 forms a pointing drive signal and a phase adjustment signal for each main reflecting mirror 11 based on the input deviation and phase difference information, and outputs the pointing drive signal and the phase adjustment signal to the pointing control mechanism unit 182 and the phase adjuster 181. The pointing control mechanism unit 182 and the phase adjuster 182 control the pointing direction based on the input pointing drive signal and phase adjustment signal, and adjust and control the phase.
【００２５】また、上記信号処理部２２は、偏差情報を
宇宙航行体を構成する宇宙バス系の姿勢制御部２３に出
力する。この姿勢制御部２３には、図示しない検出セン
サを介して姿勢情報が入力されると共に、指令情報が入
力され、これら姿勢情報及び指令情報と偏差情報とに基
づいて姿勢制御信号を生成して図示しないアクチュエー
タを駆動して全体の姿勢を制御する。Further, the signal processing unit 22 outputs the deviation information to the attitude control unit 23 of the space bus system which constitutes the spacecraft. The posture information is input to the posture control unit 23 via a detection sensor (not shown) and command information is input, and a posture control signal is generated based on the posture information and the command information and the deviation information. Do not drive the actuator to control the overall posture.
【００２６】他方、上記観測部１９は、光束合成された
光を受光して記録すると共に、その観測データを、上記
通信アンテナ１７を介して地上局等の基地局に送信す
る。On the other hand, the observing section 19 receives and records the combined light flux, and transmits the observation data to the base station such as a ground station via the communication antenna 17.
【００２７】上記宇宙バス系としては、その他、例えば
太陽電池パドル等の電源系２４、や上記通信系を構成す
る通信アンテナ１７、熱制御系等が設けられ、その電源
系２４を介して上記個別観測装置１６、偏差・位相差検
出センサ２０、指向制御機構部１８２、位相調整器１８
１、信号処理部２２、上記検出センサ（図示せず）等に
対して電力が供給される。As the space bus system, in addition, a power supply system 24 such as a solar cell paddle, a communication antenna 17 constituting the communication system, a thermal control system, etc. are provided, and the individual power supply system 24 is used to provide the individual power supply system. Observation device 16, deviation / phase difference detection sensor 20, pointing control mechanism section 182, phase adjuster 18
1, power is supplied to the signal processing unit 22, the detection sensor (not shown), and the like.
【００２８】また、上記支持構造体１０には、図７に示
すように作業ロボットアーム把持用の複数の取っ手２５
が所定の間隔に設けられる。これら複数の取っ手２５
は、例えば図８（ａ）（ｂ）（ｃ）に示すように係止孔
２５１及び電気コネクタ２５２が設けられる。この取っ
手２５の電気コネクタ２５２は、上記電源系２４に電気
的に接続される。そして、この取っ手２５は、その係止
孔２５１が作業ロボットアーム２６（図９参照）の指部
により係止されて把持されると、該作業ロボットアーム
２６が電気コネクタ２５２を介して上記電源系２４等と
電気的に接続される。Further, as shown in FIG. 7, the support structure 10 has a plurality of handles 25 for gripping the work robot arm.
Are provided at predetermined intervals. These multiple handles 25
For example, as shown in FIGS. 8A, 8B, and 8C, a locking hole 251 and an electric connector 252 are provided. The electric connector 252 of the handle 25 is electrically connected to the power supply system 24. When the locking hole 251 of the handle 25 is gripped by being locked by the fingers of the work robot arm 26 (see FIG. 9), the work robot arm 26 receives the power supply system via the electric connector 252. 24 and the like are electrically connected.
【００２９】上記作業ロボットアーム２６は、図示しな
いが、例えば両端に電気コネクタを備えた把持部が設け
られ、その一端の把持部で支持構造体１０の一つの取っ
手２５を把持した状態で、その他方の把持部で支持構造
体１０の他の取っ手２５を把持したり、上記主反射鏡１
１の鏡面支持体１３に設けられる取っ手１３６を把持す
ることが可能に構成される。この際、作業ロボットアー
ム２６は、その一端の把持部で支持構造体１０の取っ手
２５を把持した状態で、該取っ手２５の電気コネクタ２
５２を介して上記電源系２４等に電気的に接続されて動
作制御が行われる。これにより、作業ロボットアーム２
６としては、比較的小形のものを用いて主反射鏡１１を
支持構造体１０に着脱することが可能となり、宇宙空間
における安全な組立作業が可能となる。Although not shown, the work robot arm 26 has, for example, gripping portions provided with electrical connectors at both ends, and one gripping portion 25 of the support structure 10 is gripped by the gripping portions at one end of the work robot arm 26. The other grip 25 of the support structure 10 is gripped by one gripping portion, and the main reflecting mirror 1 described above is used.
The handle 136 provided on the first mirror surface support 13 can be held. At this time, the work robot arm 26 holds the handle 25 of the support structure 10 with the grip portion at one end thereof, and then the electric connector 2 of the handle 25 is held.
It is electrically connected to the power supply system 24 and the like via 52 to control the operation. As a result, the work robot arm 2
As 6, the main reflecting mirror 11 can be attached to and detached from the support structure 10 by using a relatively small one, and a safe assembling work in outer space becomes possible.
【００３０】例えば、上記主反射鏡１１の鏡面支持体１
３に設けられる取っ手１３６は、作業ロボットアーム２
６の把持部（図示せず）により把持された状態で、その
構造体結合部１３２及び鏡面結合部１３を結合可能な鏡
面支持体１３の所定に位置に設けられる。For example, the mirror surface support 1 for the main reflecting mirror 11
The handle 136 provided on the work robot arm 2 is
6 is provided at a predetermined position of the mirror surface support body 13 to which the structure body coupling portion 132 and the mirror surface coupling portion 13 can be coupled in a state of being grasped by the grasping portion 6 (not shown).
【００３１】上記構成において、例えば支持構造体１０
には、その略中央部に光束合成光学系１８及び観測部１
９が組み付けられると共に、宇宙バス系を構成する姿勢
制御部２３、電源系２４及び通信アンテナ１７等が配設
され、この状態で宇宙空間に輸送される。ここで、支持
構造体１０は、図示しない展開機構部が駆動されて略六
角柱形状に展開され、その副鏡取付部１０１に対して副
反射鏡１２が取り付けられる。In the above structure, for example, the support structure 10
Of the beam combining optical system 18 and the observing unit
9 is assembled, the attitude control unit 23, the power supply system 24, the communication antenna 17, and the like that form the space bus system are arranged, and the space bus system is transported in this state. Here, the supporting structure 10 is expanded into a substantially hexagonal column shape by driving a not-illustrated expanding mechanism section, and the sub-reflecting mirror 12 is attached to the sub-mirror attaching section 101.
【００３２】一方、主反射鏡１１は、上述したように６
台が、その鏡面支持体１３の第１及び第３の嵌合部１３
４、１５１を、鏡面側に積重される他の主反射鏡１１の
鏡面支持体１３の第２及び第４の嵌合部１３５、１５２
を嵌合させると共に、その第２及び第４の嵌合部１３
５、１５２を背面側に積重される他の主反射鏡１１の鏡
面支持体１３の第１及び第３の嵌合部１３４、１５１に
嵌合させて順に積重状に収納した状態で、宇宙空間に輸
送される。ここで、これら６台の主反射鏡１１は、各第
１乃至第４の嵌合部１３４、１３５、１５１、１５２の
嵌合により、堅牢な状態に保たれて、宇宙空間まで安全
に輸送される。On the other hand, the main reflecting mirror 11 has the 6
The base is the first and third fitting portions 13 of the mirror surface support body 13.
Second and fourth fitting portions 135, 152 of the mirror surface support 13 of the other main reflecting mirror 11 stacked on the mirror surface side.
And the second and fourth fitting portions 13 thereof.
In a state in which 5, 152 are fitted in the first and third fitting portions 134, 151 of the mirror surface support 13 of the other main reflecting mirror 11 to be stacked on the back side, and are housed in a stack in order, Transported to outer space. Here, these six main reflecting mirrors 11 are kept in a robust state by the fitting of the first to fourth fitting portions 134, 135, 151, 152, and are safely transported to outer space. It
【００３３】そして、宇宙空間において、支持構造体１
０の一方端の周囲部には、その取っ手２５を、図９に示
すように作業ロボットアーム２６で把持した状態で、該
作業ロボットアーム２６の先端部側の把持部で、６台の
主反射鏡１１の鏡面支持体１３の取っ手１３６が把持さ
れて、その構造体結合部１３２が取り付けられて、上述
したように略リング状に取り付けられる。この際、６台
の主反射鏡１１は、その鏡面結合部１３３が隣接される
主反射鏡１１の鏡面結合部１３３と結合されて略リング
形状に一体的に組み付けられる。ここで、６台の主反射
鏡１１には、支持構造体１０の副鏡取付部１０１に取り
付けられた副反射鏡１２が対向配置されて支持構造体１
０への組付け配置が完了される（図１０参照、但し、図
１０中では、一箇所のみを図示）。In the outer space, the support structure 1
In the peripheral portion of one end of 0, with the handle 25 being gripped by the work robot arm 26 as shown in FIG. The handle 136 of the mirror surface support 13 of the mirror 11 is gripped, the structure coupling portion 132 thereof is attached, and the attachment is substantially ring-shaped as described above. At this time, the six main reflecting mirrors 11 are integrally assembled in a substantially ring shape by joining the mirror surface coupling portions 133 to the mirror surface coupling portions 133 of the adjacent main reflecting mirrors 11. Here, the sub-reflecting mirrors 12 attached to the sub-mirror attaching portions 101 of the supporting structure 10 are arranged so as to face the six main reflecting mirrors 11 so that the supporting structure 1
The assembling placement to 0 is completed (see FIG. 10, but only one place is shown in FIG. 10).
【００３４】ここで、上述したように６台の主反射鏡１
１は、各指向方向の光を取り込んで各副反射鏡１２を介
して各バッフル筒１５に光を集光する。この各主反射鏡
１１で集光された光は、それぞれ個別観測装置１６に入
力される。Here, as described above, the six main reflecting mirrors 1
Reference numeral 1 captures light in each direction and focuses the light on each baffle cylinder 15 via each sub-reflecting mirror 12. The light collected by each main reflecting mirror 11 is input to the individual observation device 16.
【００３５】個別観測装置１６は、指令情報に基づいて
切換反射鏡１６１を動作制御して選択的に個別観測部１
６２でそれぞれの主反射鏡で集光した光の受光、記録を
実行して、その観測データを上記通信アンテナ１７を介
して基地局に送信する。The individual observation device 16 selectively controls the switching reflecting mirror 161 based on the command information to selectively operate the individual observation unit 1.
At 62, the light collected by each main reflecting mirror is received and recorded, and the observation data is transmitted to the base station via the communication antenna 17.
【００３６】また、個別観測装置１６は、選択的に光束
合成光学系１８に各主反射鏡１１で集光した光を出力す
る。この光束合成光学系１８に導かれ各光は、合成され
て部分反射器２１を介して観測部１９及び偏差・位相差
検出センサ２０にそれぞれ出力される。すると、偏差・
位相差検出センサ２０は、入力した光に基づいて各主反
射鏡１１の偏差及び位相差を算出して信号処理部２２に
出力する。信号処理部２２は、入力した偏差及び位相差
情報に基づいて指向駆動信号及び位相調整信号を生成し
て指向制御機構部１８２及び位相調整器１８１を駆動制
御して、各指向方向及び位相を調整する。Further, the individual observation device 16 selectively outputs the light condensed by each main reflecting mirror 11 to the light flux combining optical system 18. The respective lights guided to the light flux combining optical system 18 are combined and output to the observation unit 19 and the deviation / phase difference detection sensor 20 via the partial reflector 21. Then the deviation
The phase difference detection sensor 20 calculates the deviation and the phase difference of each main reflecting mirror 11 based on the input light and outputs it to the signal processing unit 22. The signal processing unit 22 generates a directional drive signal and a phase adjustment signal based on the input deviation and phase difference information, drives and controls the directional control mechanism unit 182 and the phase adjuster 181, and adjusts each directional direction and phase. To do.
【００３７】また、信号処理部２２は、偏差情報を姿勢
制御部２３に出力する。この姿勢制御部２３には、上述
したように姿勢情報及び指令情報が入力され、これら姿
勢情報及び指令情報と偏差情報とに基づいて姿勢制御信
号を生成して上記アクチュエータ（図示せず）を駆動し
て全体の姿勢を制御する。The signal processing section 22 also outputs deviation information to the attitude control section 23. The posture information and the command information are input to the posture control unit 23 as described above, and a posture control signal is generated based on the posture information and the command information and the deviation information to drive the actuator (not shown). And control the whole posture.
【００３８】このように、上記宇宙望遠鏡は、宇宙航行
体を構成するための宇宙バス系を配備すると共に、その
支持構造体１０の周囲に対して、外形が略六角形形状に
形成される６台の主反射鏡１１を着脱可能に組み付け
て、この６台の主反射鏡１１の鏡面に対向して配設され
る副反射鏡１２を対向配置し、これら主反射鏡１１及び
副反射鏡１２を介して集光した光を観測するように構成
した。As described above, the space telescope is provided with a space bus system for constructing a space navigation body, and its outer shape is formed into a substantially hexagonal shape around the support structure 10. The main reflecting mirrors 11 of the table are detachably assembled, and the sub-reflecting mirrors 12 arranged so as to face the mirror surfaces of the six main reflecting mirrors 11 are arranged to face each other. It was configured to observe the light condensed via the.
【００３９】これによれば、６台の主反射鏡１１は、支
持構造体１０の周囲に略リング形状に配置することがで
きることにより、その収納状態における外形寸法を所望
の寸法に保ってうえで、鏡面としての開口径の大口径化
を促進することが可能となる。従って、信頼性の高い高
精度な観測を行うことが可能となる。According to this, since the six main reflecting mirrors 11 can be arranged in a substantially ring shape around the support structure 10, the outer dimensions in the housed state can be maintained at desired dimensions. Therefore, it becomes possible to promote the enlargement of the aperture diameter as a mirror surface. Therefore, highly reliable and highly accurate observation can be performed.
【００４０】なお、上記実施の形態では、支持構造体１
０として、梁部材を、略六角柱形状のトラス結合して折
り畳み展開可能に構成した場合で説明したが、これに限
ることなく、例えば梁部材等の構成部材を分割組立可能
に組合せ構成した支持構造においても適用可能である。
また、支持構造体１０の一部を展開式にして、その他の
部分を組立式に構成するようにしてもよい。さらに、支
持構造体の形状としては、略六角柱形状に限ることな
く、構成することが可能である。In the above embodiment, the support structure 1
0 has been described as a case where the beam members are configured by truss connection of a substantially hexagonal column shape so that the beam members can be folded and expanded. It can also be applied to the structure.
Further, a part of the support structure 10 may be a development type and the other parts may be an assembly type. Further, the shape of the support structure is not limited to the substantially hexagonal prism shape, and can be configured.
【００４１】また、上記実施の形態では、支持構造体１
０に副鏡取付部１０１を設けて、この副鏡取付部１０１
に副反射鏡１２を取り付け配置するように構成した場合
で説明したが、これに限ることなく、例えば図１１に示
すように主反射鏡１１に支持部材１１１を介して一体的
に取り付けて、主反射鏡１１とともに支持構造体１０に
取り付け配置するように構成することも可能である。Further, in the above embodiment, the support structure 1
0 is provided with a secondary mirror mounting portion 101, and the secondary mirror mounting portion 101
The case where the sub-reflecting mirror 12 is attached to the main reflecting mirror 12 has been described above. However, the present invention is not limited to this. For example, as shown in FIG. It may be configured to be attached to the support structure 10 together with the reflecting mirror 11.
【００４２】さらに、上記実施の形態では、主反射鏡１
１の後段にそれぞれ個別観測装置１６を配設して選択的
に各主反射鏡１１で取り込んだ光を観測し得るように構
成した場合で説明したが、これに限ることなく、個別観
測装置１６を設けることなく、光束合成光学系１８で直
接的に各光を合成して、その合成した光を観測するよう
に構成してもよい。この場合には、個別観測装置１６を
備える構成に比して運用の多様化の点で若干劣ることと
なる。Further, in the above embodiment, the main reflecting mirror 1
The case where the individual observation devices 16 are arranged in the latter stage of the first configuration so that the light captured by each main reflecting mirror 11 can be selectively observed has been described, but the invention is not limited to this. Alternatively, it is possible to directly combine the light beams by the light beam combining optical system 18 and observe the combined light beam without arranging. In this case, it is slightly inferior to the configuration including the individual observation device 16 in terms of diversification of operation.
【００４３】また、上記実施の形態では、支持構造体１
０に対して光束合成光学系１８及び観測部１９が組み付
けられると共に、宇宙バス系を構成する姿勢制御部２
３、電源系２４及び通信アンテナ１７等が組み付け配置
して、宇宙空間に輸送するように構成した場合で説明し
たが、これの限ることなく、例えばこれらを宇宙空間に
おいて支持構造体１０に組み付け配置するように構成す
ることも可能である。Further, in the above embodiment, the support structure 1
The light flux synthesizing optical system 18 and the observing unit 19 are assembled with respect to 0, and the attitude control unit 2 forming the space bus system
3, the power supply system 24, the communication antenna 17 and the like are assembled and arranged to be transported to outer space. However, the present invention is not limited to this, and for example, these are assembled and arranged on the support structure 10 in outer space. It can also be configured to do so.
【００４４】さらに、上記実施の形態では、６台の主反
射鏡１１を支持構造体１０の周囲に略円形状に配置する
ように構成した場合で説明したが、この数に限ることな
く、配置構成することも可能である。Further, in the above-described embodiment, the case where the six main reflecting mirrors 11 are arranged around the support structure 10 in a substantially circular shape has been described, but the number is not limited to this. It is also possible to configure.
【００４５】よって、この発明は、上記実施の形態に限
ることなく、その他、実施段階ではその要旨を逸脱いな
い範囲で種々の変形を実施し得ることが可能である。さ
らに、上記実施形態には、種々の段階の発明が含まれて
おり、開示される複数の構成要件における適宜な組合せ
により種々の発明が抽出され得る。Therefore, the present invention is not limited to the above-described embodiment, and in addition, various modifications can be carried out at the stage of implementation without departing from the scope of the invention. Further, the embodiments include inventions at various stages, and various inventions can be extracted by appropriately combining a plurality of disclosed constituent elements.
【００４６】例えば実施形態に示される全構成要件から
幾つかの構成要件が削除されても、発明が解決しようと
する課題の欄で述べた課題が解決でき、発明の効果で述
べられている効果が得られる場合には、この構成要件が
削除された構成が発明として抽出され得る。For example, even if some constituent elements are deleted from all the constituent elements shown in the embodiment, the problems described in the section of the problem to be solved by the invention can be solved, and the effects described in the effects of the invention can be obtained. When the above is obtained, the configuration in which this constituent element is deleted can be extracted as the invention.
【００４７】[0047]
【発明の効果】以上詳述したように，この発明によれ
ば、宇宙空間までの効率的な輸送を実現したうえで、開
口径の大口径化を図り得るようにして、信頼性の高い高
精度な観測を実現した宇宙望遠鏡を提供することができ
る。As described above in detail, according to the present invention, efficient transportation to outer space can be realized, and at the same time, the aperture diameter can be increased to achieve high reliability and high reliability. It is possible to provide a space telescope that realizes accurate observation.
【図１】この発明の一実施の形態に係る宇宙望遠鏡の側
面から見た状態を示したそ構成図である。FIG. 1 is a configuration diagram showing a state of a space telescope according to an embodiment of the present invention viewed from a side surface.
【図２】図１を鏡面側から見た状態を示した構成図であ
る。FIG. 2 is a configuration diagram showing a state in which FIG. 1 is viewed from a mirror surface side.
【図３】図１の主反射鏡を取り出して示した図である。FIG. 3 is a diagram showing the main reflecting mirror of FIG. 1 taken out.
【図４】図１の主反射鏡の鏡面支持体を取り出した図で
ある。FIG. 4 is a view showing a mirror surface support of the main reflecting mirror shown in FIG.
【図５】図３を断面して示した図である。5 is a cross-sectional view of FIG.
【図６】図１の光学系の構成を示した図である。FIG. 6 is a diagram showing a configuration of the optical system of FIG.
【図７】図１を分解して示した図である。7 is an exploded view of FIG. 1. FIG.
【図８】図１のロボット把持用の取っ手の構成を示した
図である。FIG. 8 is a diagram showing a configuration of a grip for gripping the robot of FIG. 1.
【図９】図１の主反射鏡の組立動作を説明するために示
した図である。FIG. 9 is a diagram shown for explaining an assembling operation of the main reflecting mirror of FIG. 1.
【図１０】支持構造体に組み付けられた主反射鏡及び副
反射鏡の位置関係を示した図である。FIG. 10 is a diagram showing a positional relationship between a main reflecting mirror and a sub-reflecting mirror assembled to a support structure.
【図１１】この発明の他の実施の形態を示した図でる。FIG. 11 is a diagram showing another embodiment of the present invention.
【図１２】従来の宇宙望遠鏡を示した構成図である。FIG. 12 is a configuration diagram showing a conventional space telescope.
１０ … 支持構造体。 １０１ … 副鏡取付部。 １１ … 主反射鏡。 １１１ … 支持部材。 １２ … 副鏡。 １３ … 鏡面支持体。 １３１ … 鏡面支持部。 １３２ … 構造体結合部。 １３３ … 鏡面結合部。 １３４ … 第１の嵌合部。 １３５ … 第２の嵌合部。 １３６ … 取っ手。 １４ … 反射鏡面。 １５ … バッフル筒。 １５１ … 第３の嵌合部。 １５２ … 第４の嵌合部。 １６ … 個別観測装置。 １６１ … 切換反射鏡。 １６２ … 個別観測部。 １７ … 通信アンテナ。 １８ … 光束合成光学系。 １８１ … 位相調整器。 １８２ … 指向制御機構部。 １９ … 観測部。 ２０ … 偏差・位相差検出センサ。 ２１ … 部分反射器。 ２２ … 信号処理部。 ２３ … 姿勢制御部。 ２４ … 電源系。 ２５ … 取っ手。 ２５１ … 係止孔。 ２５２ … 電気コネクタ。 ２６ … 作業ロボットアーム。 10 ... Support structure. 101 ... Secondary mirror mounting portion. 11 ... Main reflector. 111 ... Support member. 12 ... Secondary mirror. 13 ... Mirror surface support. 131 ... Mirror surface support. 132 ... Structure connecting part. 133 ... Mirror surface coupling part. 134 ... 1st fitting part. 135 ... 2nd fitting part. 136 ... Handle. 14 ... Reflective mirror surface. 15 ... Baffle cylinder. 151 ... 3rd fitting part. 152 ... 4th fitting part. 16 ... Individual observation device. 161 ... Switching mirror. 162 ... Individual observation unit. 17 ... Communication antenna. 18 ... Light flux combining optical system. 181 ... Phase adjuster. 182 ... Direction control mechanism section. 19 ... Observation Department. 20 ... Deviation / phase difference detection sensor. 21 ... Partial reflector. 22 ... Signal processing unit. 23 ... Attitude control unit. 24 ... Power supply system. 25 ... Handle. 251 ... Locking hole. 252 ... Electrical connector. 26 ... Working robot arm.
───────────────────────────────────────────────────── フロントページの続き (71)出願人 301072650 エヌイーシー東芝スペースシステム株式会 社 神奈川県横浜市港北区新横浜二丁目６番３ 号 (74)上記１名の代理人 100071272 弁理士 後藤 洋介 （外１名） (72)発明者 西田 信一郎 神奈川県川崎市幸区小向東芝町１番地 株 式会社東芝小向工場内 (72)発明者 戎崎 俊一 埼玉県和光市広沢２番１号 理化学研究所 内 Ｆターム(参考） 2H039 AA02 AB24 AB44 AB57 AC00 2H043 CA01 CB02 CD04 CE00 ─────────────────────────────────────────────────── ─── Continued front page (71) Applicant 301072650 NEC Toshiba Space Systems Stock Association Company 2-6-3 Shin-Yokohama, Kohoku Ward, Yokohama City, Kanagawa Prefecture issue (74) One agent mentioned above 100071272 Attorney Yosuke Goto (1 outside) (72) Inventor Shinichiro Nishida 1st Komukai Toshiba-cho, Sachi-ku, Kawasaki-shi, Kanagawa Ceremony Company Toshiba Komukai Factory (72) Inventor Shunichi Ebisaki 2-1, Hirosawa, Wako-shi, Saitama RIKEN Within F-term (reference) 2H039 AA02 AB24 AB44 AB57 AC00 2H043 CA01 CB02 CD04 CE00
Claims (10)
る外形が略六角形形状に形成された複数の主反射鏡と、 これら複数の主反射鏡の鏡面に対向して配設される複数
の副反射鏡と、 前記複数の主反射鏡及び複数の副反射鏡を介して集光し
た光を観測する光観測手段と、 宇宙航行体を構成するための宇宙バス系とを具備したこ
とを特徴とする宇宙望遠鏡。1. A plurality of main reflecting mirrors which are detachably arranged around a support structure and whose outer shape is formed into a substantially hexagonal shape, and a plurality of main reflecting mirrors which are arranged so as to face the mirror surfaces of the plurality of main reflecting mirrors. A plurality of sub-reflecting mirrors, a light observing means for observing the light condensed through the plurality of main reflecting mirrors and the plurality of sub-reflecting mirrors, and a space bus system for constituting a spacecraft. Space telescope characterized by that.
造部材を略六角柱形状に組立結合したことを特徴とする
請求項１記載の宇宙望遠鏡。2. The space telescope according to claim 1, wherein the support structure is formed by assembling and coupling a plurality of divisible structural members into a substantially hexagonal prism shape.
数の構造部材は、少なくとも一部が折り畳み展開可能に
設けられることを特徴とする請求項２記載の宇宙望遠
鏡。3. The space telescope according to claim 2, wherein at least a part of the plurality of divisible structural members forming the support structure is provided so as to be foldable and expandable.
成され、略六角柱形状に展開されることを特徴とする請
求項１記載の宇宙望遠鏡。4. The space telescope according to claim 1, wherein the support structure is formed to be foldable and expandable, and is expanded into a substantially hexagonal column shape.
開構造と、この展開構造に組立結合される組立構造とで
形成されることを特徴とする請求項４記載の宇宙望遠
鏡。5. The space telescope according to claim 4, wherein the support structure is formed of a deployable structure that can be folded and deployed, and an assembly structure that is assembled and coupled to the deployable structure.
が解放可能に把持するもので、前記作業ロボットアーム
の把持状態で該作業ロボットアームと電気的に接続され
る前記宇宙バス系に接続された電気コネクタを有する複
数の取っ手が設けられることを特徴とする請求項１乃至
５のいずれか記載の宇宙望遠鏡。6. The support structure is releasably gripped by a work robot arm, and is connected to the space bus system electrically connected to the work robot arm in a gripped state of the work robot arm. A space telescope according to any one of the preceding claims, characterized in that a plurality of handles with electrical connectors are provided.
で集光した光を個別に観測する個別観測手段と、前記複
数の主反射鏡で集光した光を合成して観測する光束合成
観測手段と、前記個別観測手段及び前記光束合成観測手
段のいずれかを選択して個別観測あるいは光束合成観測
を実行する観測選択手段とを備えることを特徴とする請
求項１乃至６のいずれか記載の宇宙望遠鏡。7. The light observing means combines the individual observing means for individually observing the light collected by the plurality of main reflecting mirrors and the light flux for observing the light collected by the plurality of main reflecting mirrors. 7. A combination observation means, and an observation selection means for selecting one of the individual observation means and the light flux synthesis observation means to perform individual observation or light flux synthesis observation, according to any one of claims 1 to 6. Space telescope as described.
形状の鏡面支持体と、この鏡面支持体の一方面に配設さ
れる略中央部にバッフル筒が設けられた反射鏡面とを備
え、前記鏡面支持体の鏡面側及び背面側に第１及び第２
の嵌合部を設けると共に、前記反射鏡面のバッフル筒の
両端に第３及び第４の嵌合部を設けて前記鏡面支持体の
第１の嵌合部を、他の主反射鏡の鏡面支持体の第２の嵌
合部と嵌合させ、前記反射鏡面のバッフル筒の第３の嵌
合部を前記他の主反射鏡のバッフル筒の第４の嵌合部と
嵌合させて複数個を積重状に収容可能に構成したことを
特徴とする請求項１乃至７のいずれか記載の宇宙望遠
鏡。8. The plurality of main reflecting mirrors include a mirror surface support whose outer shape is a substantially hexagonal shape, and a reflecting mirror surface provided with a baffle cylinder at a substantially central portion arranged on one surface of the mirror surface support. And a first surface and a second surface on the mirror surface side and the back surface side of the mirror surface support.
And a third and a fourth fitting portion are provided at both ends of the baffle cylinder for the reflecting mirror surface, and the first fitting portion of the mirror surface support is used for supporting the mirror surface of another main reflecting mirror. A plurality of fitting units are fitted to the second fitting unit of the body, and the third fitting unit of the baffle cylinder of the reflecting mirror surface is fitted to the fourth fitting unit of the baffle cylinder of the other main reflecting mirror. The space telescope according to claim 1, wherein the space telescopes are configured so that they can be housed in a stack.
は前記主反射鏡のいずれか一方に、前記主反射鏡の鏡面
に対応して取付配置されることを特徴とする請求項１乃
至８のいずれか記載の宇宙望遠鏡。9. The sub-reflecting mirror is attached to one of the support structure and the main reflecting mirror so as to correspond to a mirror surface of the main reflecting mirror. Space telescope according to any one of.
との通信を実行する通信手段と、 電力を供給するための電力源と、 前記複数の主反射鏡、前記複数の副反射鏡、前記光観測
手段、前記通信手段及び前記電力源を含む前記支持構造
体の姿勢を制御する姿勢制御手段とを備えることを特徴
とする請求項１乃至９のいずれか記載の宇宙望遠鏡。10. The space bus system includes a communication unit that performs communication with at least an external station, a power source for supplying power, the plurality of main reflecting mirrors, the plurality of sub-reflecting mirrors, and the light. The space telescope according to any one of claims 1 to 9, further comprising: an observation means, the communication means, and an attitude control means for controlling an attitude of the support structure including the power source.
Priority Applications (1)
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|---|---|---|---|
| JP2001292224A JP4955166B2 (en) | 2001-09-25 | 2001-09-25 | Space telescope |
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|---|---|---|---|
| JP2001292224A JP4955166B2 (en) | 2001-09-25 | 2001-09-25 | Space telescope |
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| JP4955166B2 JP4955166B2 (en) | 2012-06-20 |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102436052A (en) * | 2011-12-13 | 2012-05-02 | 北京空间机电研究所 | Optical axis levelling and gravity unloading supporting method of large diameter lightweight mirror |
| JP2012103332A (en) * | 2010-11-08 | 2012-05-31 | Nano Optonics Energy Co Ltd | Altazimuth mount type reflecting telescope |
| JP2018529992A (en) * | 2015-09-29 | 2018-10-11 | レイセオン カンパニー | High rigidity structure for large aperture telescope |
| CN113589517A (en) * | 2021-08-11 | 2021-11-02 | 哈尔滨工业大学 | Separable modular sub-mirror structure of large-scale space telescope and on-orbit replacement method |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR101455232B1 (en) | 2013-01-07 | 2014-11-04 | 한국 천문 연구원 | Optical system of signal detection for near-infrared and tera hertz waves band |
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|---|---|
| JP4955166B2 (en) | 2012-06-20 |
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