JPH0766049B2 - Aircraft optical system device - Google Patents
Aircraft optical system deviceInfo
- Publication number
- JPH0766049B2 JPH0766049B2 JP61230623A JP23062386A JPH0766049B2 JP H0766049 B2 JPH0766049 B2 JP H0766049B2 JP 61230623 A JP61230623 A JP 61230623A JP 23062386 A JP23062386 A JP 23062386A JP H0766049 B2 JPH0766049 B2 JP H0766049B2
- Authority
- JP
- Japan
- Prior art keywords
- light
- filter
- optical axis
- mirror
- wavelength band
- 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.)
- Expired - Lifetime
Links
Landscapes
- Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
- Optical Radar Systems And Details Thereof (AREA)
- Gyroscopes (AREA)
Description
【発明の詳細な説明】 ［発明の目的］ （産業上の利用分野） この発明は、反射型光学系を用い、かつ二つの波長帯で
目標を検知する誘導飛翔体用シーカとして用いられる飛
翔体用光学系装置に関する。DETAILED DESCRIPTION OF THE INVENTION Object of the Invention (Industrial field of application) The present invention relates to a flying object that uses a reflective optical system and is used as a seeker for a guided flying object that detects a target in two wavelength bands. Optical system device.
（従来の技術） 周知のように誘導飛翔体用シーカとして用いられる光学
系装置は、例えば可視域と赤外域の二つの波長帯におい
て目標を検知すると、目標と背景、あるいは目標と擬似
目標（フレア、火炎等）の弁別が容易になるという利点
がある。一般に、反射型光学系を用いたシーカでこれを
実現する場合には、第３図に示した形式の光学系装置が
容易に考えられる。ここでは可視、赤外ともに検知素子
としてはCCDを用いるものとする。(Prior Art) As is well known, an optical system device used as a seeker for a guided vehicle detects a target in two wavelength bands, for example, a visible range and an infrared range, or a target and a background, or a target and a pseudo target (flare). , Flame, etc.) can be easily distinguished. Generally, when this is realized by a seeker using a reflection type optical system, an optical system device of the type shown in FIG. 3 can be easily considered. Here, a CCD is used as a detection element for both visible light and infrared light.
第３図において、ジャイロ部１は２自由度を持つように
２個のジンバル2,3で支持されており、フリージャイロ
方式又はレートジャイロ方式により空間安定化されてい
る。これには光学系の１次鏡４、２次鏡４′、ダイクロ
イック・ミラー５、可視光検知素子６、赤外光検知素子
７が取り付けられている。８は検知素子６および７の出
力から目標位置情報を検出し、飛翔体の目標追尾（ホー
ミング）を行わせるための操舵制御出力およびシーカの
目標追尾を行わせるためのシーカ駆動出力を発生する信
号処理回路である。9,10は上記シーカ駆動出力に応じて
光学系の光軸と一致しているジャイロ軸11が目標方向に
向くように、互に直角な方向の駆動力を発生しジャイロ
部１を駆動する第１、第２のトルカであってジャイロ部
に結合されている。In FIG. 3, the gyro unit 1 is supported by two gimbals 2 and 3 so as to have two degrees of freedom, and is spatially stabilized by a free gyro system or a rate gyro system. An optical primary mirror 4, a secondary mirror 4 ', a dichroic mirror 5, a visible light detecting element 6, and an infrared light detecting element 7 are attached to this. Reference numeral 8 is a signal that detects target position information from the outputs of the detection elements 6 and 7 and generates a steering control output for performing target tracking (homing) of the flying object and a seeker drive output for performing target tracking of the seeker. It is a processing circuit. Reference numerals 9 and 10 are for driving the gyro unit 1 by generating driving forces in directions orthogonal to each other so that the gyro axis 11 which coincides with the optical axis of the optical system faces the target direction in accordance with the seeker drive output. The first and second torquers are connected to the gyro part.
このようなシーカの光学系装置においては次の如き欠点
がある。The Seeker optical system device has the following drawbacks.
（１）ジャイロの空間安定化を容易にするためには、ジ
ャイロ部ではジャイロ軸と一致する光軸に対称に、ジャ
イロ部を構成する部品が配置されていることが望ましい
が、可視光検知素子６はこの原則にかなっていない。実
際には、第３図においてジャイロ軸の対象位置Ａにダミ
ーのウェートを配置する必要がある。(1) In order to facilitate the spatial stabilization of the gyro, it is desirable that the components constituting the gyro are arranged symmetrically with respect to the optical axis that coincides with the gyro in the gyro. 6 does not follow this principle. Actually, it is necessary to arrange a dummy weight at the target position A of the gyro axis in FIG.
（２）ダイクロイック・ミラー５の機能は入射光を可視
域と赤外域の光に分割することにあり、一般には平板で
作られる。しかし第３図の如きシーカでは、平板ミラー
が収束光の中に斜めにおかれることになり、光学系の収
差を劣下させることになる。これを避けるためにはダイ
クロイック・ミラー５は第３図に示した如く、ミラー・
ブロックとして構成する必要があり、重量の増大、コス
トの増大等不利となる。(2) The function of the dichroic mirror 5 is to split incident light into light in the visible range and infrared range, and is generally made of a flat plate. However, in the seeker as shown in FIG. 3, the flat plate mirror is obliquely placed in the convergent light, which deteriorates the aberration of the optical system. In order to avoid this, the dichroic mirror 5 is a mirror mirror as shown in FIG.
Since it has to be configured as a block, there are disadvantages such as an increase in weight and an increase in cost.
（発明が解決しようとする問題点） この発明は、従来装置ではダミーのウェートを配置する
必要があり、またダイクロイック・ミラーをミラー・ブ
ロックとして構成する必要があるため、重量の増大、コ
ストの増大等を招いていた点を改善し、ジャイロとして
の部品配置が容易であり、軽量かつ低コスト化の可能
な、誘導飛翔体用シーカとして好適する飛翔体用光学系
装置を提供することを目的とする。(Problems to be Solved by the Invention) In the present invention, since it is necessary to dispose a dummy weight in the conventional device, and it is necessary to configure the dichroic mirror as a mirror block, the weight is increased and the cost is increased. It is an object of the present invention to provide a flying object optical system device that is suitable as a guided flying object seeker, in which the arrangement of parts as a gyro is easy, the weight is low, and the cost can be reduced. To do.
［発明の構成］ （問題点を解決するための手段） この発明に係る飛翔体用光学系装置は、光軸上に配置さ
れ、第１の波長帯の光を透過し第１の波長帯とは異なる
第２の波長帯の光を反射するフィルタを備え、前記光軸
について対称な形状をなし、前記フィルタに入射光を導
いて前記フィルタの透過光と反射光を前記光軸上に前記
フィルタと共に集光させる光学系と、それぞれ前記フィ
ルタの透過光、反射光の焦点に配置され、前記フィルタ
で透過された第１の波長帯の光を検出する第１の光検出
器及び前記フィルタで反射された第２の波長帯の光を検
出する第２の光検出器とを具備して構成される。[Configuration of the Invention] (Means for Solving the Problems) An optical system device for a flying vehicle according to the present invention is arranged on the optical axis, transmits light in the first wavelength band, and transmits light in the first wavelength band. Includes a filter that reflects light of a different second wavelength band, has a shape symmetrical with respect to the optical axis, guides incident light to the filter, and allows transmitted light and reflected light of the filter to be on the optical axis. And an optical system for condensing the light, a first photodetector that is disposed at the focal points of the transmitted light and the reflected light of the filter, and that detects the light of the first wavelength band transmitted by the filter and the light reflected by the filter. And a second photodetector for detecting light in the second wavelength band.
（作用） 上記構成による飛翔体用光学系装置は、光軸上に第１の
波長帯の光を透過し第２の波長帯の光を反射するフィル
タを配置し、前記光軸について対称な形状をなす光学系
により、フィルタに入射光を導いてフィルタの透過光と
反射光を光軸上に集光させ、それぞれの焦点に配置した
第１、第２の光検出器により各波長帯の光を検出するよ
うにしたものである。(Operation) In the flying vehicle optical system device having the above configuration, a filter that transmits light in the first wavelength band and reflects light in the second wavelength band is arranged on the optical axis, and has a shape symmetrical with respect to the optical axis. The optical system that forms an optical system guides the incident light to the filter to collect the transmitted light and the reflected light of the filter on the optical axis, and the first and second photodetectors arranged at the respective focal points detect the light of each wavelength band. Is detected.
（実施例） 以下、この発明の一実施例を第１図及び第２図を参照し
て説明する。但し、第１図において第３図と同一部分に
は同一符号を付してその説明を省略する。(Embodiment) An embodiment of the present invention will be described below with reference to FIGS. 1 and 2. However, in FIG. 1, the same parts as those in FIG.
第１図は誘導飛翔体用シーカにこの発明に係る光学系装
置を適用した場合の構成を示すもので、第３図の２次鏡
４′の中央附近は本来反射鏡として使用されない部分で
あり、この部分に光検知素子の一つを配置することがで
きる。これを行ったのが第１図のシーカであり、第３図
のダイクロイック・ミラー５のかわりに、片面に所要波
長域を反射する反射膜を備えたフィルタ25が用いられて
いる。FIG. 1 shows a configuration in which the optical system device according to the present invention is applied to a guided vehicle seeker, and the vicinity of the center of the secondary mirror 4'in FIG. 3 is a portion which is not originally used as a reflecting mirror. , One of the light detecting elements can be arranged in this portion. This is done by the seeker shown in FIG. 1, and instead of the dichroic mirror 5 shown in FIG. 3, a filter 25 having a reflecting film for reflecting a required wavelength region on one surface is used.
すなわち、第１図において、波長が異なる第１、第２の
光は１次鏡24で反射され２次鏡24′に入射される。２次
鏡24′は中空部を有し、外周部反射面で第１、第２の光
を反射する。フィルタ25は２次鏡24′で反射された第
１、第２の光を受け、それぞれ光軸上の反対方向に一方
の光は反射し他方の光は透過する。フィルタ25で反射さ
れた光は２次鏡24′の中空部を通って検出器26で検出さ
れ、フィルタ25を透過した光は検出器27で検出される。
検出器26,27は１次鏡24、２次鏡24′フィルタ25と同一
光軸31上に配置されている。That is, in FIG. 1, the first and second lights having different wavelengths are reflected by the primary mirror 24 and enter the secondary mirror 24 '. The secondary mirror 24 'has a hollow portion and reflects the first and second lights on the outer peripheral reflection surface. The filter 25 receives the first and second light reflected by the secondary mirror 24 ', and one light is reflected and the other light is transmitted in opposite directions on the optical axis. The light reflected by the filter 25 passes through the hollow portion of the secondary mirror 24 'and is detected by the detector 26, and the light transmitted by the filter 25 is detected by the detector 27.
The detectors 26 and 27 are arranged on the same optical axis 31 as the primary mirror 24 and the secondary mirror 24 'filter 25.
尚、第１図では25は平板フィルタで示されているが、レ
ンズ作用を持ったフィルタとすることも可能である。ま
た光検知素子26は２次鏡24′の後方に配置してあるが、
小形であれば２次鏡24′と同一面又は２次鏡24′より前
方に配置することも可能である。Although 25 is shown as a flat plate filter in FIG. 1, it is also possible to use a filter having a lens function. Also, the light detecting element 26 is arranged behind the secondary mirror 24 ',
If it is small, it can be placed on the same plane as the secondary mirror 24 'or in front of the secondary mirror 24'.
また、第２図に示す如く、２次鏡と反射フィルタの両機
能を具備したフィルタ35を用いることも可能である。Further, as shown in FIG. 2, it is possible to use a filter 35 having both functions of a secondary mirror and a reflection filter.
第２図において、波長が異なる第１、第２の光は１次鏡
34で反射される。フィルタ35は１次鏡34で反射された第
１、第２の光を受け、一方の光は前面で反射し他方の光
は透過する。これら光はそれぞれ同一光軸41上の検出器
36,37で検出される。フィルタ35はレンズ作用をもって
おり、透過した光の焦点距離を長くしている。一方の光
が可視光、他方の光が赤外光の場合、フィルタ25,35に
は、赤外光を透過して可視光を反射させる膜がコーティ
ングされている。In FIG. 2, the first and second lights having different wavelengths are primary mirrors.
Reflected at 34. The filter 35 receives the first and second lights reflected by the primary mirror 34, one light is reflected on the front surface, and the other light is transmitted. Each of these lights is a detector on the same optical axis 41.
Detected at 36,37. The filter 35 has a lens function and lengthens the focal length of the transmitted light. When one light is visible light and the other light is infrared light, the filters 25 and 35 are coated with a film that transmits infrared light and reflects visible light.
したがって、上記構成による飛翔体光学系装置を用いた
場合、同一光軸上でかつフィルタの両側に各検知器を配
置できるので、誘導飛翔体においてシーカ部の軽量小型
化がはかれ、バランスもよい。Therefore, when the flying object optical system device having the above-mentioned configuration is used, the detectors can be arranged on the same optical axis and on both sides of the filter, so that the seeker portion of the guided flying object can be reduced in weight and size, and the balance is good. .
［発明の効果］ 以上述べたようにこの発明によれば、二つの波長帯と二
つの光検知素子を用い、かつ、反射型光学系で構成する
誘導飛翔体用シーカに用いた場合、ジャイロバランス上
部品配置が容易で、軽量かつ低価格であり、光学性能の
優れたシーカを実現できる飛翔体用光学系装置を提供す
ることができる。[Effects of the Invention] As described above, according to the present invention, when two wavelength bands and two photodetectors are used and a seeker for a guided vehicle constructed with a reflection type optical system is used, a gyro balance is obtained. It is possible to provide an optical system device for a flying object, which is easy to dispose upper parts, is lightweight and inexpensive, and can realize a seeker having excellent optical performance.
第１図はこの発明に係る飛翔体用光学系装置の一実施例
を示す構成図、第２図はこの発明に係る他の実施例を示
す構成図、第３図は従来の光学系装置を用いた誘導飛翔
体用シーカの構成を示す構成図である。 1,21……ジャイロ部、2,3,22,23……ジンバル、4,24,34
……１次鏡、４′,24′……２次鏡、５……ダイクロイ
ック・ミラー、6,7,26,27,36,37……可視光または赤外
光検知素子、８……信号処理回路、9,10……トルカ、1
1,31,41……ジャイロ軸、25,35……フィルタ。FIG. 1 is a block diagram showing an embodiment of an optical system device for a flying object according to the present invention, FIG. 2 is a block diagram showing another embodiment according to the present invention, and FIG. 3 is a conventional optical system device. It is a block diagram which shows the structure of the seeker for guided vehicles which was used. 1,21 …… Gyro part, 2,3,22,23 …… Gimbal, 4,24,34
…… Primary mirror, 4 ′, 24 ′ …… Secondary mirror, 5 …… Dichroic mirror, 6,7,26,27,36,37 …… Visible or infrared light detector, 8 …… Signal Processing circuit, 9,10 ... ToruCa, 1
1,31,41 …… Gyro axis, 25,35 …… Filter.
Claims (3)
過し第１の波長帯とは異なる第２の波長帯の光を反射す
るフィルタを備え、前記光軸について対称な形状をな
し、前記フィルタに入射光を導いて前記フィルタの透過
光と反射光を前記光軸上に前記フィルタと共に集光させ
る光学系と、それぞれ前記フィルタの透過光、反射光の
焦点に配置され、前記フィルタで透過された第１の波長
帯の光を検出する第１の光検出器及び前記フィルタで反
射された第２の波長帯の光を検出する第２の光検出器と
を具備する飛翔体用光学系装置。1. A filter arranged on the optical axis for transmitting light of a first wavelength band and reflecting light of a second wavelength band different from the first wavelength band, and symmetric with respect to the optical axis. An optical system having a shape, which guides incident light to the filter and collects transmitted light and reflected light of the filter together with the filter on the optical axis, and is disposed at the focal points of the transmitted light and the reflected light of the filter, respectively. A first photodetector for detecting light in the first wavelength band transmitted by the filter, and a second photodetector for detecting light in the second wavelength band reflected by the filter. Aircraft optical system device.
形成され入射光を前記光軸上の一点に集光する一次鏡
と、前記一次鏡の中空部と略同径で、前記光軸中心部に
中空部が形成され前記一次鏡とその焦点との間に配置さ
れ前記一次鏡の反射光を再反射して前記一次鏡の中空部
後方の光軸上に集光させる二次鏡とを備え、 前記フィルタに前記二次鏡の反射光が導かれ、このフィ
ルタによって透過された第１の波長帯の光が前記一次鏡
の中空部後方に配置される第１の光検出器の受光面に集
光され、反射される第２の波長帯の光が前記二次鏡の中
空部後方に配置される第２の光検出器の受光面に集光さ
れるようにしたことを特徴とする特許請求の範囲第１項
記載の飛翔体用光学系装置。2. The optical system includes a primary mirror having a hollow portion formed at the center of the optical axis for converging incident light at one point on the optical axis, and having a diameter substantially the same as that of the hollow portion of the primary mirror. A hollow portion is formed at the center of the optical axis and is disposed between the primary mirror and its focal point to re-reflect the reflected light of the primary mirror and focus it on the optical axis behind the hollow portion of the primary mirror. A second mirror, the reflected light of the secondary mirror is guided to the filter, and the light of the first wavelength band transmitted by the filter is disposed behind the hollow portion of the primary mirror. The light of the second wavelength band that is condensed and reflected on the light receiving surface of the detector is condensed on the light receiving surface of the second photodetector arranged behind the hollow portion of the secondary mirror. The optical system device for a flying object according to claim 1.
形成され、入射光を前記光軸上の一点に集光する反射鏡
を備え、 前記フィルタは、前記反射鏡の中空部と略同径で、前記
反射鏡とその焦点との間に配置され、前記反射鏡からの
光を入射して第１の波長帯の光を透過し前記光軸上に集
光する機能と、前記反射鏡からの光を入射して第２の波
長帯の光を反射し前記反射鏡の中空部後方の光軸上に集
光させる機能とを有することを特徴とする特許請求の範
囲第１項記載の飛翔体用光学系装置。3. The optical system includes a reflecting mirror having a hollow portion formed at the center of the optical axis and condensing incident light at one point on the optical axis, and the filter has a hollow portion of the reflecting mirror. A function of collecting light from the reflecting mirror, transmitting light of a first wavelength band, and condensing the light on the optical axis, the light having substantially the same diameter as that of the reflecting mirror and the focal point thereof. The light having a function of causing the light from the reflecting mirror to enter, reflecting the light in the second wavelength band, and condensing the light on the optical axis behind the hollow portion of the reflecting mirror. An optical system device for a flying object according to the item.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP61230623A JPH0766049B2 (en) | 1986-09-29 | 1986-09-29 | Aircraft optical system device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP61230623A JPH0766049B2 (en) | 1986-09-29 | 1986-09-29 | Aircraft optical system device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| JPS6383683A JPS6383683A (en) | 1988-04-14 |
| JPH0766049B2 true JPH0766049B2 (en) | 1995-07-19 |
Family
ID=16910675
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP61230623A Expired - Lifetime JPH0766049B2 (en) | 1986-09-29 | 1986-09-29 | Aircraft optical system device |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH0766049B2 (en) |
Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH06294856A (en) * | 1993-04-06 | 1994-10-21 | Nec Corp | Image guiding device for homing guiding |
| JPH0792249A (en) * | 1993-09-21 | 1995-04-07 | Tech Res & Dev Inst Of Japan Def Agency | Image pickup apparatus |
| DE102008045439A1 (en) | 2007-10-05 | 2009-04-16 | Samsung Electro - Mechanics Co., Ltd., Suwon-shi | Laser measuring device |
| KR100951243B1 (en) * | 2007-10-05 | 2010-04-05 | 삼성전기주식회사 | Light detection and ranging apparatus |
| JP5984437B2 (en) * | 2012-03-08 | 2016-09-06 | 三菱重工業株式会社 | Image guiding apparatus and image guiding method |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS4888963A (en) * | 1972-02-23 | 1973-11-21 |
-
1986
- 1986-09-29 JP JP61230623A patent/JPH0766049B2/en not_active Expired - Lifetime
Also Published As
| Publication number | Publication date |
|---|---|
| JPS6383683A (en) | 1988-04-14 |
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