JPH0271106A - Apparatus for detecting passing position of flight body - Google Patents
Apparatus for detecting passing position of flight bodyInfo
- Publication number
- JPH0271106A JPH0271106A JP22375588A JP22375588A JPH0271106A JP H0271106 A JPH0271106 A JP H0271106A JP 22375588 A JP22375588 A JP 22375588A JP 22375588 A JP22375588 A JP 22375588A JP H0271106 A JPH0271106 A JP H0271106A
- Authority
- JP
- Japan
- Prior art keywords
- flight body
- range
- light
- passes
- passing position
- 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.)
- Pending
Links
- 230000003287 optical effect Effects 0.000 claims abstract description 10
- 238000001514 detection method Methods 0.000 abstract description 18
- 230000000694 effects Effects 0.000 abstract description 3
- 230000035939 shock Effects 0.000 description 10
- 239000013307 optical fiber Substances 0.000 description 7
- 238000010586 diagram Methods 0.000 description 5
- 239000002184 metal Substances 0.000 description 2
- 238000007796 conventional method Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 239000012528 membrane Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
Landscapes
- Length Measuring Devices By Optical Means (AREA)
Abstract
Description
【発明の詳細な説明】
[産業上の利用分野]
本発明は、射撃場で使用する銃等から発射された弾丸等
の飛行体の通過位置を検出する飛行体の通過位置検知装
置に関するものである。[Detailed Description of the Invention] [Field of Industrial Application] The present invention relates to a passing position detection device for a flying object, which detects the passing position of a flying object such as a bullet fired from a gun used at a shooting range. be.
[従来の技術1
従来の弾丸等の飛行体の検知方法としては、弾丸等が超
音速で飛行した際に発生する衝撃波を利用する感知バ一
方法がある。[Prior Art 1] As a conventional method for detecting a flying object such as a bullet, there is a sensing bar method that utilizes shock waves generated when a bullet or the like flies at supersonic speed.
先ず第3図、第4図に於いて感知バーを用い衝撃波を感
知することによって飛行体の通過位置を検出する原理を
説明する。First, with reference to FIGS. 3 and 4, the principle of detecting the passing position of an aircraft by sensing shock waves using a sensing bar will be explained.
1は飛行体Pの進行方向と直角な方向に配置した金属製
の感知バーで該感知バー1の両端には振動検知器2,3
が取付けである。1 is a metal sensing bar arranged in a direction perpendicular to the traveling direction of the flying object P, and vibration detectors 2 and 3 are installed at both ends of the sensing bar 1.
is the installation.
飛行体Pの発生する衝撃波4が、感知バー1に到達する
とその到達点に振動を与える。この振動は感知バー1を
伝わって両端に設けられた振動検知器2.3に到達し感
知される。When the shock wave 4 generated by the flying object P reaches the sensing bar 1, it imparts vibration to the reaching point. This vibration is transmitted through the sensing bar 1, reaches vibration detectors 2.3 provided at both ends, and is sensed.
今、衝撃波4の到達点Px、感知バー1の中心0から到
達点Px迄の距離をXとすると、到達点Pxから振動検
知器2迄の距離と到達点Pxから振動検知器3迄の距離
との差は2xあり、両検知器2.3へはΔt=2x/V
、(V。Now, if the distance from the arrival point Px of the shock wave 4 and the center 0 of the sensing bar 1 to the arrival point Px is X, then the distance from the arrival point Px to the vibration detector 2, and the distance from the arrival point Px to the vibration detector 3. There is a difference of 2x, and Δt=2x/V to both detectors 2.3.
, (V.
は金属バー中の音速)の時間差をもって振動が到達する
。この時間差Δtは振動検知器2.3が振動を感知した
ときの時間ずれを検出することによりもとめられ、結局
中心からの距Mxは下記の式で求められる。The vibrations arrive with a time difference of (the speed of sound in the metal bar). This time difference Δt is determined by detecting the time lag when the vibration detector 2.3 senses the vibration, and the distance Mx from the center is determined by the following formula.
x=V、、・Δt/2 ・・・ (1)而して、感知
バー1.5を第5図に示す如くL字状に直交させて同一
面内に配置すれば、飛行体Pの通過点は感知バー1及び
5の中心を通り直交するX軸、Y軸の直交座標で特定で
きる。x=V, .Δt/2... (1) Therefore, if the sensing bars 1.5 are arranged perpendicularly in an L-shape and in the same plane as shown in FIG. The passing point can be specified by the orthogonal coordinates of the X and Y axes that pass through the centers of the sensing bars 1 and 5 and are perpendicular to each other.
即ち、飛行体Pの通過位置のX座標Px、y座標PY、
感知バー1での振動を感知する時間差をΔtx、感知バ
ー5での時間差をΔtyとすると、Px、P−は以下の
如く求められる。That is, the X coordinate Px, the y coordinate PY of the passing position of the aircraft P,
If the time difference in sensing the vibration at the sensing bar 1 is Δtx, and the time difference at the sensing bar 5 is Δty, then Px and P- can be obtained as follows.
px=v、−ΔtX/2
pY=v、・ΔtY/2
[発明が解決しようとする課題]
然し、上記した従来の感知バ一方式では以下にのべる問
題がある。px=v, -ΔtX/2 pY=v, ·ΔtY/2 [Problems to be Solved by the Invention] However, the above-described conventional sensing bar type has the following problems.
衝撃波を感知するということから感知バーの配置は、飛
行体の通過位置の近くとしなければならないが、該飛行
体が予定した範囲をそれた場合、飛行体が感知バーを損
傷することがある。In order to sense shock waves, the sensing bar must be placed close to the position where the flying object passes, but if the flying object deviates from the intended range, the sensing bar may be damaged by the flying object.
更に、衝撃波が円錐状をしていることから2本の直交す
る感知バーが形成する座標面に対し飛行体が垂直に通過
した場合以外では誤差を生じてしまう。周知の如く円錐
をその中心線に傾斜した面で切断した切断面の外形線は
楕円である。Furthermore, since the shock wave has a conical shape, errors will occur unless the aircraft passes perpendicularly to the coordinate plane formed by two orthogonal sensing bars. As is well known, the outline of a cut surface obtained by cutting a cone with a plane inclined to its center line is an ellipse.
従って、2本の感知バーに対して衝撃波は第6図のよう
にあたかも楕円状に伝播し衝突する。Therefore, the shock wave propagates in an elliptical shape and collides with the two sensing bars as shown in FIG.
ところが、衝撃波が楕円状に衝突するがゆえ、その衝突
点は飛行体Pの通過位置の座標を示さない。即ち、飛行
体が座標面に対して斜めに通過した場合、第6図で示し
たようにiの検知誤差を生じてしまう。However, since the shock waves collide in an elliptical shape, the collision point does not indicate the coordinates of the passing position of the aircraft P. That is, if the flying object passes obliquely to the coordinate plane, a detection error of i will occur as shown in FIG.
更に又、感知バ一方式では音速以下の衝撃波を形成しな
い飛行体に対しては検知不能である。Furthermore, the one-sensing bar type cannot detect flying objects that do not generate shock waves below the speed of sound.
本発明は、上記実状に鑑み飛行体に損傷されることなく
、飛行体通過姿勢により検知精度か影響受けることなく
、更に飛行体が音速以下で飛行する場合にも確実に飛行
通過位置の検知を可能とするものである。In view of the above-mentioned circumstances, the present invention has been devised to detect the passing position of the flying object without being damaged by the flying object, without having the detection accuracy affected by the flying object's passing attitude, and even when the flying object is flying below the speed of sound. It makes it possible.
[課題を解決するための手段]
本発明は、膜状の平行光線を投照する2組の発光手段を
その光軸が交差し、且平行光線の2つの膜面が同一を含
む平行となるよう配置し、両売光手段に対応させて2組
の受光手段を設け、該受光手段で飛行体通過時に生じる
陰影の位置を検知し得るよう構成したことを特徴とする
ものである。[Means for Solving the Problems] The present invention provides two sets of light emitting means for projecting film-like parallel light rays, the optical axes of which intersect, and the two film surfaces of the parallel light rays are parallel and include the same surface. The present invention is characterized in that two sets of light-receiving means are provided corresponding to the two-way light means, and the light-receiving means can detect the position of a shadow that occurs when an aircraft passes by.
[作 用]
飛行体が2膜面を通過する時、通過位置に応じた陰影が
生じ、この陰影は受光手段により感知され、受光手段が
感知した陰影の位置を判別することによって飛行体の通
過位置が判別される。[Function] When an aircraft passes through two membrane surfaces, a shadow is created depending on the passing position, this shadow is detected by the light receiving means, and by determining the position of the shadow detected by the light receiving means, the passing of the aircraft is detected. The location is determined.
[実 施 例1 以下図面を参照しつつ本発明の一実施例を説明する。[Implementation Example 1] An embodiment of the present invention will be described below with reference to the drawings.
第1因数いて同一平面内に相互の光軸が直交するように
光源6.7を配設し、該光源6.7の前にそれぞれ集光
レンズ8.9を配設する。更に、集光レンズ8.9の前
に所要長さのスリット10,11を光源6,7と同一面
内となるよう穿設したスリット板12.13を配設し、
集光レンズ8.9からの光を膜状の平行光線14.15
とする。この2つの平行光線14.15が交差する矩形
部分が飛行体Pの通過位置を検知することが可能な検知
範囲16となる。Light sources 6.7 are arranged so that their optical axes are perpendicular to each other in the same plane based on the first factor, and a condenser lens 8.9 is arranged in front of each light source 6.7. Further, in front of the condenser lens 8.9, a slit plate 12.13 having slits 10, 11 of a required length formed in the same plane as the light sources 6, 7 is arranged,
The light from the condensing lens 8.9 is transformed into a film-like parallel beam 14.15
shall be. A rectangular portion where these two parallel light beams 14 and 15 intersect becomes a detection range 16 in which the passing position of the aircraft P can be detected.
前記スリット板12.13に対峙させ、検知範囲16よ
り所要距離能れた位置に集光レンズ17.18を配設し
、更に該集光レンズ17.18の光軸上、後側に受光器
19.20を設ける。A condenser lens 17.18 is disposed at a position facing the slit plate 12.13 and a required distance from the detection range 16, and a light receiver is disposed on the rear side of the condenser lens 17.18 on the optical axis. 19.20 will be established.
該受光器19.20は、その受光面が微細な感光素子の
集合、例えばCODのようなものであって、局部的な光
度変化を感知し得ると共に光度変化した受光面上の位置
を検知し得るものである。The light receivers 19 and 20 have a light-receiving surface that is a collection of minute photosensitive elements, such as a COD, and can sense local changes in light intensity and detect the position on the light-receiving surface where the light intensity has changed. It's something you get.
膜状の平行光線が投照され受光器が該光線を受けている
状態で、飛行体Pが検知範囲16の9点を通過すると、
飛行体Pによる陰影21.22が生じ、この陰影21
、22は受光器19.20で検出されると共に2点の位
置、例えば検知範囲16の2辺を座標軸とし、該座標軸
からの距Mx、yを直ちに検出できる。この検出結果は
飛行体Pが検知範囲を、圭角に通過した場合でも斜めに
通過した場合でも何等変わることかない。When the flying object P passes through nine points in the detection range 16 while the film-like parallel light beam is being projected and the light receiver is receiving the light beam,
Shadows 21 and 22 are caused by the aircraft P, and this shadow 21
, 22 are detected by the light receivers 19 and 20, and the positions of two points, for example, the two sides of the detection range 16, are used as coordinate axes, and the distances Mx and y from the coordinate axes can be immediately detected. This detection result does not change in any way whether the flying object P passes through the detection range at an angle or diagonally.
更に、集光レンズ8,9、スリット板12,13、集光
レンズ17.18等の光学系は、検知範囲の中心に近付
けても離しても検知範囲16の広さ、検知能力について
は影響がないので、飛行体Pが検知範囲を外れる可能性
がある場合は、充分安全な位置まで光学系を遠ざけるこ
とができ、飛行体による損傷を防止し得る。Furthermore, whether the optical system such as the condenser lenses 8, 9, slit plates 12, 13, condenser lenses 17, 18, etc. is brought close to or away from the center of the detection range, the width of the detection range 16 and the detection ability will be affected. Therefore, if there is a possibility that the flying object P is out of the detection range, the optical system can be moved away to a sufficiently safe position, and damage by the flying object can be prevented.
尚、集光レンズ17.18に代えシリンドカルレンズ(
カマボコ状の棒レンズ)を用いれば、スリット板12.
13は省略できる。In addition, a cylindrical lens (
If a semi-cylindrical rod lens is used, the slit plate 12.
13 can be omitted.
第2図は光学系の変更例を示すものであり、23.24
は光ファイバ25.26・・・を束ねた光ファイバ束で
ある。光ファイバ束23は、その基部を円状に束ねてあ
り、光源からの光を充分に受は得るようにし、その先部
は一列に並べ光ファイバ23からスリット光が投照され
るようにしである。Figure 2 shows an example of changing the optical system.
is an optical fiber bundle made up of optical fibers 25, 26, and so on. The optical fiber bundle 23 has its base tied in a circular shape to receive sufficient light from the light source, and its tip is arranged in a line so that slit light is emitted from the optical fibers 23. be.
他方の光ファイバ束24の一端部はやはり一列に並べら
れスリット光を確実に受は得る配置となっており、他端
部は光ファイバ26.26・・・−本一本がばらばらと
なりそれぞれが対応するフォトトランジスタ等の受光素
子27.27・・・へ光を導くようになっている。One end of the other optical fiber bundle 24 is arranged in a line to ensure that the slit light can be received, and the other end of the optical fiber bundle 24 is arranged so that the optical fibers 26, 26...- each one is separated. Light is guided to corresponding light receiving elements 27, 27, etc., such as phototransistors.
該例でも、各受光素子27.27の出力を監視すること
で飛行体Pの通過時の陰影をその位置と共に検知し得る
。In this example as well, by monitoring the output of each light-receiving element 27, 27, it is possible to detect the shadow of the flying object P when it passes along with its position.
尚、2組の光学系は必ずしも直交していなくてもよいこ
とは勿論であり、更に2つの膜状平行光線が飛行体の飛
行方向に多少ずれていても構わないことも言うまでもな
い。It goes without saying that the two sets of optical systems do not necessarily have to be perpendicular to each other, and furthermore, it is also possible for the two film-like parallel rays to be slightly shifted in the flight direction of the aircraft.
[発明の効果]
以上述べた如く本発明によれば下記の優れた効果を発揮
する。[Effects of the Invention] As described above, the present invention exhibits the following excellent effects.
(i)飛行体が如何なる角度で通過しても確実且正確に
通過位置を検出し得る。(i) No matter what angle the flying object passes through, the passing position can be detected reliably and accurately.
(ii)飛行体により設置された各機器が損傷を受ける
ことかない。(ii) Equipment installed by the aircraft will not be damaged.
(i)衝撃波を発生しない音速以下の飛行体の通過位置
の検知も可能である。(i) It is also possible to detect the passing position of a subsonic flying object that does not generate a shock wave.
第1図は本発明の第一の実施例を示す説明図、第2図は
同前他の実施例を示す部分説明図、第3図、第4図は衝
撃波を利用した感知バ一方式の原理説明図、第5図は2
本の直交した感知バーで音源の位置を特定し得ることを
示す説明図、第6図は感知バ一方式で生じる誤差につい
ての説明図である。
6.7は光源、14.15は平行光線、16は検知範囲
、19.20は受光器、21.22は陰影を示す。
第6図Fig. 1 is an explanatory diagram showing a first embodiment of the present invention, Fig. 2 is a partial explanatory diagram showing another embodiment of the same, and Figs. Principle explanatory diagram, Figure 5 is 2
FIG. 6 is an explanatory diagram showing that the position of a sound source can be specified by orthogonal sensing bars of a book, and FIG. 6 is an explanatory diagram of errors caused by the one-sensing bar system. 6.7 is a light source, 14.15 is a parallel ray, 16 is a detection range, 19.20 is a light receiver, and 21.22 is a shadow. Figure 6
Claims (1)
軸が交差し、且平行光線の2つの膜面が同一を含む平行
となるよう配置し、両発光手段に対応させて2組の受光
手段を設け、該受光手段で飛行体通過時に生じる陰影の
位置を検知し得るよう構成したことを特徴とする飛行体
の通過位置検知装置。1) Two sets of light emitting means that emit film-like parallel light rays are arranged so that their optical axes intersect and the two film surfaces of the parallel light rays are parallel to each other, including the same film surface, and are made to correspond to both light emitting means. 1. An apparatus for detecting a passing position of a flying object, characterized in that two sets of light receiving means are provided, and the light receiving means is configured to detect the position of a shadow that occurs when the flying object passes.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP22375588A JPH0271106A (en) | 1988-09-07 | 1988-09-07 | Apparatus for detecting passing position of flight body |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP22375588A JPH0271106A (en) | 1988-09-07 | 1988-09-07 | Apparatus for detecting passing position of flight body |
Publications (1)
Publication Number | Publication Date |
---|---|
JPH0271106A true JPH0271106A (en) | 1990-03-09 |
Family
ID=16803201
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP22375588A Pending JPH0271106A (en) | 1988-09-07 | 1988-09-07 | Apparatus for detecting passing position of flight body |
Country Status (1)
Country | Link |
---|---|
JP (1) | JPH0271106A (en) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2006170671A (en) * | 2004-12-13 | 2006-06-29 | Babcock Hitachi Kk | Device for measuring bullet position |
JP2007162989A (en) * | 2005-12-12 | 2007-06-28 | Babcock Hitachi Kk | Bullet position measuring device |
JP2011089763A (en) * | 2010-12-07 | 2011-05-06 | Babcock Hitachi Kk | Bullet position measuring device |
Citations (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPS5619456A (en) * | 1979-07-27 | 1981-02-24 | Teac Co | Ball speed detector |
-
1988
- 1988-09-07 JP JP22375588A patent/JPH0271106A/en active Pending
Patent Citations (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPS5619456A (en) * | 1979-07-27 | 1981-02-24 | Teac Co | Ball speed detector |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2006170671A (en) * | 2004-12-13 | 2006-06-29 | Babcock Hitachi Kk | Device for measuring bullet position |
JP4699018B2 (en) * | 2004-12-13 | 2011-06-08 | バブコック日立株式会社 | Bullet position measuring device |
JP2007162989A (en) * | 2005-12-12 | 2007-06-28 | Babcock Hitachi Kk | Bullet position measuring device |
JP2011089763A (en) * | 2010-12-07 | 2011-05-06 | Babcock Hitachi Kk | Bullet position measuring device |
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