JPH0271112A - Correction method in method for detecting passing position of flight body by sensing bar system - Google Patents
Correction method in method for detecting passing position of flight body by sensing bar systemInfo
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- JPH0271112A JPH0271112A JP22375388A JP22375388A JPH0271112A JP H0271112 A JPH0271112 A JP H0271112A JP 22375388 A JP22375388 A JP 22375388A JP 22375388 A JP22375388 A JP 22375388A JP H0271112 A JPH0271112 A JP H0271112A
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- sensing bar
- sensing
- shock wave
- passing position
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- 238000000034 method Methods 0.000 title claims abstract description 16
- 238000012937 correction Methods 0.000 title claims description 6
- 230000035939 shock Effects 0.000 claims abstract description 28
- 238000001514 detection method Methods 0.000 claims abstract description 14
- 238000005259 measurement Methods 0.000 claims abstract description 3
- 101150069512 RHO1 gene Proteins 0.000 abstract 1
- 101150012845 RHO2 gene Proteins 0.000 abstract 1
- 238000010586 diagram Methods 0.000 description 2
- 230000005484 gravity Effects 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 230000001133 acceleration Effects 0.000 description 1
- 238000007796 conventional method Methods 0.000 description 1
- 238000002474 experimental 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
超音速飛行体の通過位置を感知バーにより検出する飛行
体の通過位置検知方法に於ける補正方法に関するもので
ある。[Detailed Description of the Invention] [Industrial Application Field] The present invention relates to a system for detecting the passing position of a supersonic flying object, such as a bullet fired by a gun used at a shooting range, using a sensing bar. The present invention relates to a correction method in a detection method.
［従来の技術］
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ー
方法がある。[Prior Art] 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５図、第６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, referring to FIGS. 5 and 6, 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の両端に振動検知器２．３
を取付は感知バーユニットを構成する。1 is a metal sensing bar arranged in a direction perpendicular to the traveling direction of the flying object P, and vibration detectors 2.3 are installed at both ends of the sensing bar 1.
The mounting comprises the sensing bar unit.
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Ｐ、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 P is X, then the distance from the arrival point Px to the vibration detector 2 and from the arrival point Px to the vibration detector 3 are There is a difference of 2x from the distance, and Δt = 2x/V to both detectors 2 and 3.
. (V.
は金属ロッド中の音速）の時間差をもって振動か到達す
る。この時間差Δｔは振動検知器２，３か振動を感知し
たときの時間すれを検出することによりもとめられ、結
局中心からの距、Ｊｔｘ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 rod). This time difference Δt is determined by detecting the time lapse when the vibration detectors 2 and 3 sense vibrations, and the distance from the center, Jtx, is determined by the following equation.
Ｘ−Ｖ ｍ ・Δｔ／２ ・・・（１）而して、感知
バー１．５を第７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 m ・Δt/2 ... (1) Therefore, if the sensing bars 1.5 are arranged orthogonally in an L-shape and in the same plane as shown in FIG. The point can be specified by 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Δｔ７とすると、Ｐえ、ＰＹ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,
Assuming that the time difference in sensing the vibration at the sensing bar 1 is Δtx, and the time difference at the sensing bar 5 is Δt7, P and PY are obtained as follows.
ｐｘ−＝ｖ、 ・Δし、／２
Ｐ ｙ ＝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ー方式では以下に述べる問
題がある。px-=v, ·ΔtY/2 P y =V, ·ΔtY/2 [Problems to be Solved by the Invention] However, the conventional sensing bar method described above has the following problems.
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８図参照）を有する。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 of fall φ (see Fig. 8) with respect to the horizontal.
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。This fall angle φ is obtained from the trajectory equation derived from the equation of motion below.
ｍ：飛行体の質量 に：空気の粘性抵抗係数 ｔ：時間 ■＝飛行体の速度 式（２）より Ｖ＝Ｖｏ ｅ −” ・・・（３） 又、飛行距離をＤ、飛行高さをＨ１打出角をθ。m: mass of the flying object ：Viscous drag coefficient of air t: time ■=Speed of the aircraft From formula (2) V=Vo e-”...(3) Also, the flight distance is D, the flight height is H1, and the launch angle is 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。If the initial velocity is vo and the acceleration of gravity is g, then 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＝Ｖｏｃｏｓθ、 −Ｋ
Ｄ −（７）ところが、弾丸等により発生
する衝撃波は弾丸を頂点とする円錐形状をしていること
から、２本の直交する感知バーが形成する座標面に対し
て飛行体が前記した落角φをもって入射すると以下に述
べる様に誤差を生じてしまう。Therefore, the fall angle φ at flight distance is dH/dD. Also, the speed of the flying object at that time is V=Vocosθ, −K
D-(7) However, since the shock wave generated by a bullet etc. has a conical shape with the bullet as the apex, the falling angle of the flying object with respect to the coordinate plane formed by the two orthogonal sensing bars is If the beam is incident with φ, an error will occur as described below.
周知の如く円錐をその中心線に対し傾斜した面で切断し
た切断面の外形線は楕円である。従って、２本の感知バ
ーに対して衝撃波は第９図のようにあたかも楕円状に伝
播し衝突する。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９図で示した様にＥの検知誤差を生じてしまう。As is well known, the outline of a cut surface obtained by cutting a cone with a plane inclined with respect to its center line is an ellipse. Therefore, the shock wave propagates in an elliptical shape and collides with the two sensing bars as shown in FIG. However, because the shock waves collide in an elliptical shape, the point of impact does not indicate the coordinates of the passing position of the flying object P. In other words, if the flying object passes obliquely to the coordinate plane, This results in a detection error of E.
本発明は、上記実状に鑑み飛行体通過姿勢により検知精
度が影響受けることなく、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 makes it possible to detect a flight passing position without the detection accuracy being affected by the flying object's passing attitude.
［課題を解決するための手段］
本発明は、超音速飛行体から発生する衝撃波が到達した
時に振動を伝達する感知バーとその両端に設けた振動検
知器により、衝撃波の感知バーでの到達位置を検知する
様にした感知バーユニットを同一平面内に２組配設し、
両感知バーにより座標面を形成し、該座標面内を通過し
た飛行体の衝撃波を２組の感知バーユニットで検知して
通過位置を特定する様に感知バー方式による飛行体の通
過位置検知方法に於いて、飛打体の座標面入射時の入射
角、飛行速度を実験等所要の手段で求め、該入射角、飛
行速度と両感知バーユニットの検知結果を基に衝撃波か
座標面で形成する２の楕円の形状を求め、各楕円形状に
基づき求められる真の飛行体通過位置によって前記検知
結果を補正することを特徴とするものである。[Means for Solving the Problems] The present invention uses a sensing bar that transmits vibrations when a shock wave generated from a supersonic flying vehicle arrives, and vibration detectors provided at both ends of the sensing bar, to determine the position at which the shock wave reaches the sensing bar. Two sets of sensing bar units are arranged in the same plane to detect
A method for detecting the passing position of an aircraft using a sensing bar method, in which a coordinate plane is formed by both sensing bars, and the shock wave of the aircraft passing within the coordinate plane is detected by two sets of sensing bar units to identify the passing position. In this case, the incident angle and flight speed of the projectile when it enters the coordinate plane are determined by experiments or other necessary means, and based on the incident angle, flight speed, and the detection results of both sensing bar units, a shock wave or a coordinate plane is formed. The present invention is characterized in that the shape of the second ellipse is determined, and the detection result is corrected based on the true flying object passing position determined based on each ellipse shape.
［作 用コ
超音速の飛行体が座標面に対して傾斜して入射すると２
つの感知バーに対して衝撃波は楕円形状で伝播して衝突
する。従って、感知バーで感知する衝撃波の到達位置は
誤差を含んだものとなる。ところか、この楕円の形状は
衝撃波が円錐形状であって、而もこの円錐の頂角はマツ
ハ数できまることから、予め或いは何らかの手段で入射
角を求めておけば、感知バーユニットの感知結果より楕
円形状を特定できる。楕円形状が特定できれば楕円の中
心の位置等より補正すべき誤差を求めることができる。[Action] When a supersonic flying object enters the coordinate plane at an angle, 2
The shock wave propagates in an elliptical shape and collides with the two sensing bars. Therefore, the arrival position of the shock wave sensed by the sensing bar includes an error. However, the shape of this ellipse means that the shock wave is conical, and the apex angle of this cone is determined by Matsuha's number, so if the angle of incidence is determined in advance or by some means, the sensing result of the sensing bar unit can be It is possible to identify more elliptical shapes. If the ellipse shape can be specified, the error to be corrected can be found from the position of the center of the ellipse.
［実 施 例］ 以下図面を参照しつつ本発明の一実施例を説明する。[Example] An embodiment of the present invention will be described below with reference to the drawings.
先ず、前記した誤差Ｅについて第１図に於いて詳述する
。First, the error E mentioned above will be explained in detail with reference to FIG.
第１図は垂直方向にのみ角度φをもって入射した場合を
示し、図中衝撃波４の円錐の頂角の１／２をγとしであ
る。FIG. 1 shows the case where the shock wave is incident only in the vertical direction at an angle φ, and in the figure, γ is 1/2 of the apex angle of the cone of the shock wave 4.
この時の衝撃波の伝播形状は、辻線ｉとｉ′と座標面と
の交点ｂ１とｂ２を結ぶ直線ｂ＋ ｂ２を長軸とし、ｂ
、ｂ２／２の点Ｏ′を含む円ｊの座標面との交点ａ１と
ａ２を結ぶ直線ＥＬ、ａ２を短軸とする楕円となる。而
して、感知バー５が中心Ｏ′の点よりａの距離のところ
にあったとすると感知バー５は８１点の位置で感知する
。ところか、弾丸Ｐの実際の通過位置はＯであるので０
０’ ＝Ｅの誤差か生じてしまう。The propagation shape of the shock wave at this time has a straight line b + b2 connecting the intersections b1 and b2 of the intersection lines i and i' with the coordinate plane as the long axis, and b
, b2/2 with the coordinate plane of the circle j including the point O', the straight line EL connecting the intersection points a1 and a2 forms an ellipse with a2 as the minor axis. Thus, if the sensing bar 5 is located at a distance a from the center point O', the sensing bar 5 senses at a position of 81 points. However, the actual passing position of bullet P is O, so it is 0.
An error of 0' = E will occur.
第１図に於いて０ｂ１＝ρ、 、ｏｂ２＝ρ２、頂点か
ら０迄の距離ρ、０を含む円の半径をＲとし、図形より
Ｅを求めると下記の如くになる。In FIG. 1, 0b1=ρ, ob2=ρ2, the distance from the vertex to 0 is ρ, and the radius of the circle including 0 is R, and E is determined from the figure as follows.
Ｅ＝（ρ２−ρ１）／２ ・・・（８）ここで、
更にＲは式（１２）でｙ＝Ｅの時のＸ座標で従って、
ここでａついては感知バー１によって求められ、結局式
（９）と式（１３）により誤差Ｅは、又、γはマツハ角
と呼ばれマツハ数をＭとすると、の関係がある。E=(ρ2-ρ1)/2...(8) Here, furthermore, R is the X coordinate when y=E in equation (12). Here, a is determined by the sensing bar 1, and finally, the equation According to (9) and equation (13), the error E has the following relationship, where γ is called the Matsuh angle and M is the Matsuh number.
更に衝撃波４が座標面で作る楕円の方程式は・・（１４
）
で求められる。Furthermore, the equation of the ellipse created by shock wave 4 on the coordinate plane is...(14
).
而して、入射角φは前記式（６）で求められ、γは前記
式（１０）で求められることから誤差Ｅが求められ、感
知バー５で感知した結果を補正することができる。Since the incident angle φ is obtained from the above equation (6) and γ is obtained from the above equation (10), the error E can be obtained and the result sensed by the sensing bar 5 can be corrected.
次に、第２図に示す如く、座標面に対しφ、即ち水平方
向にφＸ、垂直方向にφＹ、傾斜して入射したとした場
合についての補正について説明する。Next, as shown in FIG. 2, correction will be described in the case where the light is incident at an angle of φ with respect to the coordinate plane, that is, φX in the horizontal direction and φY in the vertical direction.
この時、衝撃波が座標面で作る楕円は、水平方向にφだ
け傾斜して入射した場合に作られる楕円を第３図に示す
様に、
β（−ｔａｎ”φＹ／φｘ２φＸ２＋φ ２）たけ回転
させたものである。At this time, the ellipse created by the shock wave on the coordinate plane is the ellipse created when the shock wave is incident at an angle of φ in the horizontal direction, as shown in Figure 3, which is rotated by β(-tan"φY/φx2φX2+φ2). It is something.
従って、楕円の方程式は、
と前記式（１２）より、
式（１６）と水平接線との接点を求めるとここでｅは離
心率で、
又、式（１６）と垂直線との接点を求めると、式（１７
）に於けるＸｌは感知バー１の検知結果で、ｙｌは感知
バー１の設置位置よりわかり、又式（１８）に於けるｘ
２は感知バー５の設置位置から、ｙ２は感知バー５の感
知結果でわかるところから、ａ、ｅ（即ちｂ）を求める
ことかでき、座標面での２つの楕円形状、楕円の中心を
決定することかできる。Therefore, the equation of the ellipse is: From the above equation (12), find the point of contact between equation (16) and the horizontal tangent line, where e is the eccentricity, and find the point of contact between equation (16) and the vertical line. and formula (17
), Xl is the detection result of sensing bar 1, yl can be found from the installation position of sensing bar 1, and x in equation (18)
2 is from the installation position of the sensing bar 5, and y2 is from the sensing result of the sensing bar 5. From this, a and e (i.e. b) can be found, and the two elliptical shapes and the center of the ellipse on the coordinate plane are determined. I can do something.
更に、楕円の中心と円錐の中心との［？［は式（１２）
で求めた誤差に外ならず、βだけ回転する前の楕円より
２つの楕円のＥＩ、Ｅ２をそれぞれ求めることかでき、
従ってＸ方向についてはＥ、ＣＯ５β、Ｘ方向について
は
Ｅ２ｓｉｎβの補正量が求められ、又感知バー１か感知
した位置とＸ方向の楕円中心迄の距離ΔＸ、感知バー５
か感知した位置とＸ方向の楕円中心迄の距離Δｙについ
てはそれぞれ楕円の中心が求められることから直ちに求
め得ることか出来る。Furthermore, [?] between the center of the ellipse and the center of the cone. [is formula (12)
It is possible to find the EI and E2 of the two ellipses from the ellipse before rotating by β without exceeding the error found in
Therefore, the correction amount of E, CO5β in the X direction and E2sin β in the
The distance Δy between the sensed position and the center of the ellipse in the X direction can be immediately determined since the center of each ellipse is determined.
而して、感知バー１については（Δχ十Ｅｔｃｏｓβ）
が補正すべき量Ｅｘとなり、感知バー５については（Δ
３’十Ｅ２ Ｓ ｉ ｎβ）が補正すべき量Ｅｖとなる
（第４図参照）。Therefore, for sensing bar 1, (Δχ + Etcos β)
is the amount Ex to be corrected, and for the sensing bar 5, (Δ
3'+E2 S i nβ) is the amount Ev to be corrected (see FIG. 4).
尚、補正すべき誤差Ｅｘ 、Ｅｖは入射角を１方向にの
み傾斜したφ８及びφＹとした楕円についてそれぞれ式
（１４）で求めたと同様な手法で求めることもできる。It should be noted that the errors Ex and Ev to be corrected can also be determined using the same method as that for the ellipses with angles of incidence φ8 and φY tilted in only one direction, respectively, using equation (14).
又、２本の感知バーで構成されるもう１つの座標面を所
定の距離離して設ければ、２つの座標面の検知結果より
飛行体の速度、座標面への入射角を求めることができる
。In addition, if another coordinate plane consisting of two sensing bars is installed a predetermined distance apart, the speed of the aircraft and the angle of incidence on the coordinate plane can be determined from the detection results of the two coordinate planes. .
更に、２本の感知バーは必ずしも直交する必要はなく、
２本の感知バーを所定の角度で配置した場合でも２本の
感知バーを接線とし、該接線と衝撃波の楕円との接点を
求め楕円の形状を決定すれば、上記したと同様な手法で
補正すべき誤差は求められる。Furthermore, the two sensing bars do not necessarily have to be orthogonal;
Even if the two sensing bars are arranged at a predetermined angle, if the two sensing bars are set as tangents and the contact point between the tangent and the shock wave ellipse is determined to determine the shape of the ellipse, correction can be made using the same method as described above. The error should be determined.
［発明の効果］
以上述べた如く本発明によれば、座標面に対する飛行体
の入射角と、飛行速度を計算、実測等所要の手段で求め
るようにすれば、感知バー方式により求められた検知結
果を補正することかでき、飛行体の通過位置検知精度を
大幅に向上させることができる。[Effects of the Invention] As described above, according to the present invention, if the angle of incidence of the aircraft with respect to the coordinate plane and the flight speed are determined by necessary means such as calculation or actual measurement, the detection determined by the sensing bar method can be achieved. The results can be corrected, and the accuracy of detecting the passing position of an aircraft can be greatly improved.
第１図は座標面に対して角度をもって入射した場合に生
じる誤差の説明図、第２図は座標面に対する入射角の説
明図、第３図は楕円をＸ軸に関してβだけ回転させた場
合の説明図、第４図は楕円形状に対する誤差の関係を示
す説明図、第５図、第６図感知パ一方式による通過位置
検知の原理を示す説明図、第７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８
図は弾道の軌跡を示す図、第９図は感知バー方式で生じ
る誤差についての説明図である。
１．５は感知バー、２．３．６．７は振動検知器、４は
衝撃波を示す。Figure 1 is an illustration of the error that occurs when the incidence is at an angle to the coordinate plane, Figure 2 is an illustration of the angle of incidence to the coordinate plane, and Figure 3 is an illustration of the error that occurs when the ellipse is rotated by β about the X axis. Explanatory drawings, Fig. 4 is an explanatory drawing showing the relationship of error to the elliptical shape, Figs. 5 and 6 are explanatory drawings showing the principle of passing position detection by one type of sensor, and Fig. 7 is an explanatory drawing showing the principle of passing position detection using two orthogonal sensing lines. Explanatory diagram showing that the position of the sound source can be identified with the bar, No. 8
The figure shows the locus of the trajectory, and FIG. 9 is an explanatory diagram of errors caused by the sensing bar method. 1.5 is a sensing bar, 2.3.6.7 is a vibration detector, and 4 is a shock wave.
Claims (1)
動を伝達する感知バーとその両端に設けた振動検知器に
より、衝撃波の感知バーでの到達位置を検知する様にし
た感知バーユニットを同一平面内に２組配設し、両感知
バーにより座標面を形成し、該座標面内を通過した飛行
体の衝撃波を２組の感知バーユニットで検知して通過位
置を特定する様に感知バー方式による飛行体の通過位置
検知方法に於いて、飛行体の座標面入射時の入射角、飛
行速度を実測等所要の手段で求め、該入射角、飛行速度
と両感知バーユニットの検知結果を基に衝撃波が座標面
で形成する２の楕円の形状を求め、各楕円形状に基づき
求められる真の飛行体通過位置によつて前記検知結果を
補正することを特徴とする感知バー方式による飛行体の
通過位置検知方法に於ける補正方法。1) The same sensing bar unit uses a sensing bar that transmits vibrations when a shock wave generated from a supersonic aircraft arrives, and vibration detectors installed at both ends to detect the position where the shock wave reaches the sensing bar. Two sets of sensing bars are arranged in a plane, and both sensing bars form a coordinate plane, and the two sets of sensing bar units detect the shock waves of an aircraft passing within the coordinate plane to identify the passing position. In the method of detecting the passing position of a flying object using this method, the angle of incidence and flight speed of the flying object when it enters the coordinate plane are determined by actual measurement or other necessary means, and the angle of incidence, flight speed, and the detection results of both sensing bar units are calculated. A flying object based on a sensing bar method, characterized in that the shape of the second ellipse formed by the shock wave on the coordinate plane is determined based on the shape of the second ellipse, and the detection result is corrected by the true passing position of the flying object determined based on each elliptical shape. A correction method in the passing position detection method.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP22375388A JPH0271112A (en) | 1988-09-07 | 1988-09-07 | Correction method in method for detecting passing position of flight body by sensing bar system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP22375388A JPH0271112A (en) | 1988-09-07 | 1988-09-07 | Correction method in method for detecting passing position of flight body by sensing bar system |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH0271112A true JPH0271112A (en) | 1990-03-09 |
Family
ID=16803168
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP22375388A Pending JPH0271112A (en) | 1988-09-07 | 1988-09-07 | Correction method in method for detecting passing position of flight body by sensing bar system |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH0271112A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US11525453B2 (en) | 2017-03-08 | 2022-12-13 | Robert Bosch Gmbh | Bearing arrangement for a drive shaft of a turbo-machine, and a turbo-machine including such a bearing arrangement |
-
1988
- 1988-09-07 JP JP22375388A patent/JPH0271112A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US11525453B2 (en) | 2017-03-08 | 2022-12-13 | Robert Bosch Gmbh | Bearing arrangement for a drive shaft of a turbo-machine, and a turbo-machine including such a bearing arrangement |
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