JPH0271111A - Method for detecting passing position of supersonic flight body - Google Patents
Method for detecting passing position of supersonic flight bodyInfo
- Publication number
- JPH0271111A JPH0271111A JP22375288A JP22375288A JPH0271111A JP H0271111 A JPH0271111 A JP H0271111A JP 22375288 A JP22375288 A JP 22375288A JP 22375288 A JP22375288 A JP 22375288A JP H0271111 A JPH0271111 A JP H0271111A
- Authority
- JP
- Japan
- Prior art keywords
- shock wave
- detection means
- passing position
- flight body
- detecting
- 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.)
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Links
- 238000000034 method Methods 0.000 title claims description 8
- 230000035939 shock Effects 0.000 claims abstract description 42
- 238000001514 detection method Methods 0.000 claims abstract description 29
- 239000002184 metal Substances 0.000 claims description 6
- 230000003287 optical effect Effects 0.000 claims description 4
- 238000010586 diagram Methods 0.000 description 7
- 230000000694 effects Effects 0.000 description 2
- 238000011156 evaluation Methods 0.000 description 2
- 230000005484 gravity Effects 0.000 description 2
- 238000012544 monitoring process Methods 0.000 description 2
- 230000001133 acceleration Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 238000012937 correction Methods 0.000 description 1
- 229910003460 diamond Inorganic materials 0.000 description 1
- 239000010432 diamond Substances 0.000 description 1
- 230000001902 propagating effect Effects 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
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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で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方法
に関するものである。[Detailed Description of the Invention] [Field of Industrial Application] The present invention relates to a method for detecting the passing position of an aircraft such as a bullet fired by a gun used at a shooting range. be.
［従来の技術］
射撃場に於ける射撃練習では射撃結果を射撃手に知らせ
ることは、射撃技術を向上させる上で重要なことである
。[Prior Art] In shooting practice at a shooting range, it is important to inform the shooter of the shooting results in order to improve shooting skills.
従来、射撃結果の評価については、射撃後的に残った弾
痕を双眼鏡で観察する等していた。Conventionally, shooting results have been evaluated by observing the bullet holes left after the shot with binoculars.
又は、標的を設置する監的濠に人員を配置して弾着の評
価を行い、電話等により評価の内容を射手側連絡してい
た。Alternatively, personnel were placed in the monitoring moat where the target was set up to evaluate the bullet impact, and the content of the evaluation was communicated to the shooter by telephone or other means.
［発明か解決しようとする課題］
然し、的に残った弾痕を双眼鏡で観察する場合、−売筋
の結果を知り得す、総合的な評価となってしまうし、後
者の方法では観察作業が煩雑であると共に時間的な遅れ
がある為、射撃中に修正して技術の向上を図るというこ
とはできなかった。[Problem to be solved by the invention] However, when observing bullet holes left behind by a target with binoculars, it becomes a comprehensive evaluation that allows you to know the best-selling results, and the latter method requires a lot of observation work. Due to the complexity and time delay, it was not possible to make corrections during shooting to improve technique.
本発明は斯かる実情を鑑み、超音速飛行体が飛行する際
に生じる衝撃波を利用し、飛行体の通過位置を電気的に
検知可能とし、検知した電気的信号を演算表示装置等に
入力し、射撃手に射撃結果を直ちに知らせ得るようにし
ようとするものである。In view of these circumstances, the present invention makes it possible to electrically detect the passing position of a supersonic aircraft by using shock waves generated when a supersonic aircraft flies, and inputs the detected electrical signal to a calculation display device, etc. The aim is to make it possible for the shooter to immediately be informed of the results of the shooting.
［課題を解決するための手段］
本発明は、平行に配した２つの線状の衝撃波検知手段を
少なくとも２組交差させる状態で配置し、各組の２つの
検知手段が飛行体のｔｒ撃波をそれぞれ検知した時間差
を求め、各組の検知手段の配置中心に対する飛行体通過
位置の偏差を算出する様にしたことを特徴とし、又衝撃
波検知手段として光ビームを利用し、該光ビームか衝撃
波わを通過する時の屈折による光路ずれを検知する様に
した、或いは衝撃波検知手段として金属製バーの一端に
振動検出器を設けた感知バーを用い、衝撃波がバーに衝
突した際のバーの振動を検知する様にしたものである。[Means for Solving the Problems] The present invention provides at least two sets of parallel linear shock wave detection means arranged in an intersecting manner, and each set of two detection means detects the tr shock wave of an aircraft. The method is characterized in that the time difference between the respective detection times is calculated, and the deviation of the flying object passing position with respect to the center of arrangement of each set of detection means is calculated.Also, a light beam is used as the shock wave detection means, and the shock wave is A sensor bar with a vibration detector installed at one end of a metal bar is used to detect the vibration of the bar when the shock wave collides with the bar. It is designed to detect.
［作 用］
各組の２つの検知手段か時間差をもって衝撃波を検知す
ることにより、飛行体の速度と飛行体か発する衝撃波の
円錐形状に基づいて各組の検知手段の中心からの偏りが
求められ、２組以上の検知手段が交差して設けられてい
ることから平面状の位置が決定される。[Operation] By detecting shock waves with a time difference between the two detection means in each set, the deviation from the center of each set of detection means can be determined based on the speed of the aircraft and the cone shape of the shock wave emitted by the aircraft. , the planar position is determined because two or more sets of detection means are provided in an intersecting manner.
又、検知手段として光ビームを利用すれば衝撃波は高密
度の空気の層であり、衝撃波が光ビームを横切る時には
屈折が生じ、而して光ビームによる衝撃波か検知される
。或いは検知手段として感知バーを用いれば衝撃波が高
エネルギーの空気層であり、金属バーに衝突した際には
振動を与える。而して、金属バーを伝播する振動を振動
検知器でとらえれは衝撃波の到達した時を検知できる。Furthermore, if a light beam is used as a detection means, the shock wave is a layer of high-density air, and when the shock wave crosses the light beam, refraction occurs, and thus the shock wave caused by the light beam is detected. Alternatively, if a sensing bar is used as the detection means, the shock wave is a high-energy air layer, and when it collides with the metal bar, it vibrates. If the vibrations propagating through the metal bar are captured by a vibration detector, it is possible to detect when the shock waves arrive.
［実施 例コ 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] An embodiment of the present invention will be described below with reference to the drawings.
第１図に示す様に弾丸等の飛行体１が超音速で飛行する
と、飛行体１を頂点とする円錐状の衝撃波２か形成され
る。従って、この衝撃波２を検知することで飛行体１の
通過位置を特定することができる。As shown in FIG. 1, when a flying object 1 such as a bullet flies at supersonic speed, a conical shock wave 2 is formed with the flying object 1 at its apex. Therefore, by detecting this shock wave 2, the passing position of the flying object 1 can be specified.
線状の衝撃波検知手段３．４を紙面に対し垂直に設け、
両手段３．４によって座標面を形成し、該両手段３と４
との距離を２ａとする。A linear shock wave detection means 3.4 is provided perpendicular to the paper surface,
A coordinate plane is formed by both means 3.4, and said means 3 and 4
Let the distance between the two points be 2a.
今、円錐の頂角を２γとし飛行体１の速度を■、飛行体
１か座標面を通過し、検出手段３が衝撃波２を検知した
時間を１＋、検出手段３が衝撃波２を検知した時間をｔ
２とすると、該飛行体１の中心０からの閤りｙは以下の
式で求められる。Now, the apex angle of the cone is 2γ, the speed of the flying object 1 is ■, the time when the flying object 1 passes through the coordinate plane and the detection means 3 detects the shock wave 2 is 1+, the time when the detection means 3 detects the shock wave 2 t
2, the offset y from the center 0 of the aircraft 1 is determined by the following formula.
Ｍはマツハ数で音速を■８とすると 一− ■Ｓ である。M is Matsuha's number and the speed of sound is ■8. One- ■S It is.
従って、第２図に示す如く４本の衝撃波検知手段３．４
．５．６を井桁状に組合わせて、座標面を形成し、２組
の検知手段で２方向の閤りを求めれば、該座標面での通
過位置を特定できる。Therefore, as shown in FIG. 2, there are four shock wave detection means 3.4.
．． 5.6 are combined in a grid pattern to form a coordinate plane, and by determining the offset in two directions using two sets of detection means, the passing position on the coordinate plane can be specified.
Ｘ方向の偏りＸは偏りｙと同様に で求められる。The bias in the X direction is the same as the bias y. is required.
次に、座標面に対して飛行体１がφＹの角度をもって入
射した場合について説明する。Next, a case will be described in which the flying object 1 enters the coordinate plane at an angle of φY.
（ａ−ｙ） ｃｏｓ ＜ｒ−φＹ ） ＝Ｖｔｌ Ｓ
ｌ ｒ１７’（ａ ｙ）ｃｏｓ Ｃｒ十φＹ ）＝Ｖ
ｔ２ Ｓ ｉ ｎ７従って、ｙ方向の偏りは、
同様にＸ方向の偏りは、
式（７）より
で求めることができる。(a-y) cos <r-φY) = Vtl S
l r17'(a y)cos Cr+φY)=V
t2 S i n7 Therefore, the deviation in the y direction is similarly determined as the deviation in the x direction from equation (7).
飛行体の速度Ｖ、入射角φ８．φ７については、４本の
衝撃波検知手段で形成される座標面を飛行体の飛行方向
に２組設け、２つの座標面を通過した時の時間差、通過
位置を求めることで算出することができる。The speed of the flying object is V, the angle of incidence is φ8. φ7 can be calculated by providing two sets of coordinate planes formed by four shock wave detection means in the flight direction of the aircraft and determining the time difference and passing position when passing through the two coordinate planes.
或いは、弾丸等初速が与えられて飛行するものは、重力
の作用を受けて落下してゆくので目標点を通過する際に
は水平に対する角度、落角φ（第４図参照）を有する。Alternatively, an object such as a bullet that flies with a given initial velocity falls under the action of gravity, so when it passes the target point it has an angle with respect to the horizontal, a falling angle φ (see FIG. 4).
弾丸の如き飛行体は一般に速度に比例する抵抗力を受け
るとされており、この落角φは下記運動方程式より導か
れる弾道方程式より求められる。It is generally said that a flying object such as a bullet is subjected to a resistance force proportional to its speed, and the falling angle φ is determined from the trajectory equation derived from the equation of motion below.
：飛行体の質量
：空気の粘性抵抗係数
：飛行時間
飛行体の初速度
：飛行体の速度
Ｖ＝Ｖ、ｅ−” −（８）
又、飛行距離をＤ、飛行高さをＨ１打出角をθ。、初速
Ｖｏ、重力の加速度をｇとすると、弾道方程式は下記の
通りとなる。: Mass of the flying object: Coefficient of viscous drag of air: Flight time Initial speed of the flying object: Speed of the flying object V = V, e-" - (8) Also, the flight distance is D, the flight height is H1, and the launch angle is θ., the initial velocity Vo, and the acceleration of gravity as g, the trajectory equation is as follows.
従って、飛距離りでの落角φはｄＨ／ｄＤでとなる。又
、その時の飛行体の速度は、Ｖ ＝ Ｖｏ ＣＯ８θ。Therefore, the fall angle φ at flight distance is dH/dD. Also, the speed of the flying object at that time is V = Vo CO8θ.
−ＫＤ ・（１２＞従って、射撃練習の様に
的迄の距離、飛行体の初速が分かるものについては予め
計算などで求めておけば、速度■、角度φを求める手段
は設けなくてもよい。-KD ・(12> Therefore, in cases where the distance to the target and the initial velocity of the flying object are known, such as shooting practice, if you calculate it in advance, there is no need to provide a means to calculate the speed ■ and angle φ. .
次に、衝撃波の検知手段について説明する。Next, the shock wave detection means will be explained.
第１の例として光ビームを利用するものが挙げられ、こ
れを第５図に於いて説明する。A first example uses a light beam, which will be explained with reference to FIG.
前記した様に飛行体１か超音速で飛行する際には、飛行
体１を頂点とする円錐状の衝撃波２が形成されるが、該
衝撃波２は高密度の空気の層であり、光ビーム７が衝撃
波２を横切ると屈折により光路かｄだけずれを生ずる。As mentioned above, when the flying object 1 flies at supersonic speed, a conical shock wave 2 is formed with the flying object 1 at the apex, but the shock wave 2 is a layer of high-density air and is a light beam. 7 crosses the shock wave 2, the optical path shifts by d due to refraction.
従って、投光器８の光軸上に受光器９を配しておけば、
衝撃波２か光ビーム７を横切っているうちは、受光器９
は光ビーム７を検知しないので、衝撃波２が光ビーム７
へ到達した瞬間が分かる。Therefore, if the receiver 9 is placed on the optical axis of the emitter 8,
While the shock wave 2 is crossing the light beam 7, the receiver 9
does not detect light beam 7, so shock wave 2 detects light beam 7
You will know the moment you reach it.
尚、この光ビームを利用したものでは投光器８、受光器
９を飛行体の通過範囲より遠く離して配置できるので、
飛行体により損傷を受けることがない。In addition, in the case of using this light beam, the projector 8 and the receiver 9 can be placed far away from the passing range of the aircraft, so
Cannot be damaged by flying objects.
又、第２の例として感知バ一方式について説明する。Also, as a second example, a one-sensing bar type will be explained.
これは第６図に示す如く金属製のバー１０の一端に振動
検知器１１を取付けたものである。As shown in FIG. 6, this has a vibration detector 11 attached to one end of a metal bar 10.
衝撃波２がバー１０に衝突した際に、バー１０に振動を
与えるか、この振動は、バー１０中を伝播して振動検知
器１１に到達する。従って、振動検知器１１の出力状態
を監視することにより、衝撃波２がバー１０に到達した
ことを検知できる。When the shock wave 2 collides with the bar 10, the bar 10 is vibrated, or the vibration propagates through the bar 10 and reaches the vibration detector 11. Therefore, by monitoring the output state of the vibration detector 11, it is possible to detect that the shock wave 2 has reached the bar 10.
而して、受光器９或いは振動検知器１１からの信号を式
（２）（３）或いは（５）（６）に従って処理すれば、
飛行体１の通過位置を電気的な信号として取出すことが
可能となる。Then, if the signal from the light receiver 9 or the vibration detector 11 is processed according to equations (2), (3), or (5) and (6),
It becomes possible to extract the passing position of the aircraft 1 as an electrical signal.
尚、上記実施例では２組の検出手段を矩形に組合わせた
が菱形状に組合わせても良く、或いは３組以上の検出手
段を格子状に組合わせてもよいことは勿論である。In the above embodiment, two sets of detection means are combined in a rectangular shape, but it goes without saying that they may be combined in a diamond shape, or three or more sets of detection means may be combined in a lattice shape.
又、その他に受光器９、振動検知機１１より得られるｔ
＋、ｔ２・・・を基にΔ１＋、Δｔ２を算出する電子式
演算装置、Δｔｌ、Δｔ２を基に座標の中心よりの偏差
ｘ、ｙを算出する電子式演算装置、φＸ、φマを算出し
て偏差ｘ、ｙを補正する電子式演算装置、演算結果を射
手側へ伝送する電子式伝送装置、結果を表示する電子式
表示装置等の諸装置を設けてもよいことは勿論である。In addition, t obtained from the light receiver 9 and the vibration detector 11
+, t2..., an electronic arithmetic device that calculates Δ1+, Δt2, an electronic arithmetic device that calculates deviations x, y from the center of coordinates based on Δtl, Δt2, and an electronic arithmetic device that calculates φX, φma. Of course, it is also possible to provide various devices such as an electronic arithmetic device that corrects the deviations x and y, an electronic transmission device that transmits the arithmetic results to the shooter, and an electronic display device that displays the results.
［発明の効果］
以上述べた如く本発明によれは、超音速で飛行する飛行
体の衝撃波を利用して、飛行体の通過位置を検出する様
にしなので、射撃の完了を待って結果を評価する等の必
要かなく、通過直後に直ちに結果を知り得ると言う優れ
た効果を発揮する。[Effects of the Invention] As described above, according to the present invention, the passing position of the flying object is detected by using the shock wave of the flying object flying at supersonic speed, so the result can be evaluated after waiting for the completion of shooting. It has the excellent effect of being able to know the results immediately after passing the test without having to do anything.
第１図は本発明の原理説明図、第２図は飛行体の平面で
の位置を特定する場合の２組の検知手段の配置を示す図
、第３図は飛行体かある角度をもっていた場合の説明図
、第４図は弾道の軌跡を示す図、第５図は光ビ：ムによ
り衝撃波を検知する場合の説明図、第６図は感知バーの
説明図である。
１は飛行体、２は衝撃波、３，４，５．６は検知手段、
７は光ビーム、８は投光器、９は受光器、１０は金属バ
ー、１１は振動検知器を示す。
第
図Fig. 1 is a diagram explaining the principle of the present invention, Fig. 2 is a diagram showing the arrangement of two sets of detection means when specifying the position of an aircraft on a plane, and Fig. 3 is a diagram showing the arrangement of two sets of detection means when the aircraft is at a certain angle. 4 is a diagram showing the locus of the trajectory, FIG. 5 is an explanatory diagram when shock waves are detected by an optical beam, and FIG. 6 is an explanatory diagram of the sensing bar. 1 is a flying object, 2 is a shock wave, 3, 4, 5.6 is a detection means,
7 is a light beam, 8 is a light projector, 9 is a light receiver, 10 is a metal bar, and 11 is a vibration detector. Diagram
Claims (1)
とも２組交差させる状態で配置し、各組の２つの検知手
段が飛行体の衝撃波をそれぞれ検知した時間差を求め、
各組の検知手段の配置中心に対する飛行体通過位置の偏
差を算出する様にしたことを特徴とする超音速飛行体の
通過位置検知方法。 ２）衝撃波検知手段として光ビームを利用し、該光ビー
ムが衝撃波を通過する時の屈折による光路ずれを検知す
る様にした請求項第１項記載の超音速飛行体の通過位置
検知方法。３）衝撃波検知手段として金属製バーの一端
に振動検出器を設けた感知バーを用い、衝撃波がバーに
衝突した際のバーの振動を検知する様にした請求項第１
項記載の超音速飛行体の通過位置検知方法。[Claims] 1) At least two sets of parallel linear shock wave detection means are arranged in a state of intersecting each other, and the time difference between when the two detection means of each set respectively detect the shock waves of the aircraft is determined. ,
A method for detecting a passing position of a supersonic flying object, characterized in that the deviation of the passing position of the flying object with respect to the center of arrangement of each set of detection means is calculated. 2) The method for detecting the passing position of a supersonic flying vehicle according to claim 1, wherein a light beam is used as the shock wave detection means, and an optical path shift due to refraction when the light beam passes through the shock wave is detected. 3) Claim 1, wherein a sensing bar having a vibration detector provided at one end of a metal bar is used as the shock wave detection means to detect the vibration of the bar when the shock wave collides with the bar.
A method for detecting the passing position of a supersonic flying vehicle as described in .
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP22375288A JPH0271111A (en) | 1988-09-07 | 1988-09-07 | Method for detecting passing position of supersonic flight body |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP22375288A JPH0271111A (en) | 1988-09-07 | 1988-09-07 | Method for detecting passing position of supersonic flight body |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH0271111A true JPH0271111A (en) | 1990-03-09 |
Family
ID=16803152
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP22375288A Pending JPH0271111A (en) | 1988-09-07 | 1988-09-07 | Method for detecting passing position of supersonic flight body |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH0271111A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108871595A (en) * | 2018-07-27 | 2018-11-23 | 中国工程物理研究院激光聚变研究中心 | Super time resolution shock velocity calculation method |
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|---|---|---|---|---|
| US2925582A (en) * | 1956-02-22 | 1960-02-16 | Oflice Nat D Etudes Et De Rech | Acoustical firing indicator |
| US3778059A (en) * | 1970-03-13 | 1973-12-11 | Singer Co | Automatic gunnery shock wave scoring apparatus using metallic conductors as shock wave sensors |
| JPS55112999A (en) * | 1979-01-08 | 1980-09-01 | Australasian Training Aids Pty | Device for practicing shooting |
-
1988
- 1988-09-07 JP JP22375288A patent/JPH0271111A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2925582A (en) * | 1956-02-22 | 1960-02-16 | Oflice Nat D Etudes Et De Rech | Acoustical firing indicator |
| US3778059A (en) * | 1970-03-13 | 1973-12-11 | Singer Co | Automatic gunnery shock wave scoring apparatus using metallic conductors as shock wave sensors |
| JPS55112999A (en) * | 1979-01-08 | 1980-09-01 | Australasian Training Aids Pty | Device for practicing shooting |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108871595A (en) * | 2018-07-27 | 2018-11-23 | 中国工程物理研究院激光聚变研究中心 | Super time resolution shock velocity calculation method |
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