JPH05149961A - Measurement device of mach number and the like - Google Patents
Measurement device of mach number and the likeInfo
- Publication number
- JPH05149961A JPH05149961A JP33931691A JP33931691A JPH05149961A JP H05149961 A JPH05149961 A JP H05149961A JP 33931691 A JP33931691 A JP 33931691A JP 33931691 A JP33931691 A JP 33931691A JP H05149961 A JPH05149961 A JP H05149961A
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- Prior art keywords
- angle
- shock wave
- pressure
- mach number
- cone
- Prior art date
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- Indicating Or Recording The Presence, Absence, Or Direction Of Movement (AREA)
Abstract
Description
【０００１】[0001]
【産業上の利用分野】本発明は航空機の速度及び機体姿
勢の計測、風洞の高速気流試験装置の気流特性計測等の
気流マッハ数および気流偏角の計測装置に関するもので
ある。BACKGROUND OF THE INVENTION 1. Field of the Invention The present invention relates to a device for measuring airflow Mach number and airflow declination, such as measurement of aircraft speed and body attitude, and measurement of airflow characteristics of a high-speed airflow test device in a wind tunnel.
【０００２】[0002]
【従来の技術】従来の航空機・ミサイル等の超音速飛行
体のマッハ数の計測は図４に示す通り、胴体先端に突き
出したピトー総静圧管０１により圧力を計測し、マッハ
数を計算している。０２は総圧孔、０３は静圧孔、０４
は衝撃波である。この場合、マッハ数の計算式が複雑で
あると同時に、迎角に対する補正も非常に複雑であり、
実質上不可能である。2. Description of the Related Art As shown in FIG. 4, the measurement of the Mach number of a conventional supersonic vehicle such as an aircraft or a missile is performed by measuring the pressure with a Pitot total static pressure pipe 01 protruding from the tip of the fuselage and calculating the Mach number. There is. 02 is a total pressure hole, 03 is a static pressure hole, 04
Is a shock wave. In this case, the calculation formula of the Mach number is complicated, and at the same time, the correction for the angle of attack is also very complicated.
Practically impossible.
【０００３】[0003]
【発明が解決しようとする課題】航空機・ミサイル等の
従来の飛行マッハ数の計測は次の課題を有する。 (1) 総圧及び静圧からマッハ数を計算する式が複雑であ
る。 (2) 迎角に対する補正が複雑である。The conventional measurement of the flight Mach number of an aircraft or missile has the following problems. (1) The formula for calculating Mach number from total pressure and static pressure is complicated. (2) The correction for the angle of attack is complicated.
【０００４】上記２項について下記に説明する。 (1) について、従来のマッハ数計測・計算はレイリーの
公式を使用している。これによると、気流のマッハ数Ｍ
は、一様流静圧Ｐ1 とピトー管計測総圧Ｐｔ2 から Ｐｔ2 ／Ｐ1 ＝（６Ｍ2 ／５）7/2 （６／７Ｍ2 −１）5/2 で表わされ、これをＭについて解いてマッハ数が求めら
れる。一様流静圧Ｐ1 もピトー管計測静圧Ｐ2 から Ｐ2 ／Ｐ1 ＝（７Ｍ2 −１）／６ で計算しなくてはならない。上記の表式は数学で言う陰
関数となっているため、簡単には解けず、遂次近似法等
の複雑な手順を踏まなければならず、この計算を行なう
計算機に対して大きな負担となる。The above item 2 will be described below. Regarding (1), the conventional Mach number measurement / calculation uses Rayleigh's formula. According to this, Mach number M of the air flow
Is expressed in Pt 2 / P 1 = (6M 2/5) 7/2 (6 / 7M 2 -1) 5/2 from uniform flow static pressure P 1 and the Pitot tube measured total pressure Pt 2, which Is solved for M to obtain the Mach number. The uniform flow static pressure P 1 must also be calculated from the Pitot tube measured static pressure P 2 as P 2 / P 1 = (7M 2 −1) / 6. Since the above expression is an implicit function in mathematics, it cannot be easily solved and complicated procedures such as the successive approximation method must be taken, which imposes a heavy burden on the computer that performs this calculation. ..
【０００５】(2) について、ピトー総静圧管による迎角
の計測は、単体検定データに基づいて行なう。しかしピ
トー総静圧管は小さな迎角において、迎角変化に対する
特性変化が鈍感で、計測精度が極めて低い。したがっ
て、一般にはピトー総静圧管は迎角計測には使用されて
いない。With respect to (2), the angle of attack is measured by the Pitot total static pressure tube based on simple substance verification data. However, the Pitot total static pressure pipe is insensitive to changes in the angle of attack at small angles of attack, and its measurement accuracy is extremely low. Therefore, generally, the Pitot total static pressure tube is not used for the angle of attack measurement.
【０００６】[0006]
【課題を解決するための手段】本発明は前記従来の課題
を解決したもので、円錐またはくさびによる衝撃波を利
用し、その角度を計測することにより気流のマッハ数を
同定し、また前記の衝撃波形状の非対称性を計測するこ
とにより気流の偏角を同定するマッハ数等計測装置であ
る。DISCLOSURE OF THE INVENTION The present invention has solved the above-mentioned conventional problems and utilizes a shock wave due to a cone or a wedge, and identifies the Mach number of the air flow by measuring its angle. It is a measuring device such as a Mach number that identifies the deviation angle of the air flow by measuring the asymmetry of the shape.
【０００７】即ち、 (1) 胴体先端に、円錐またはくさびを設置し、衝撃波を
発生させ、その衝撃波形状を計測する棒状の装置を展開
し、それに圧力孔を設ける。 (2) 前記の圧力孔位置の総圧分布を計測し、円錐または
くさびによる衝撃波の角度から気流のマッハ数を同定す
る。 (3) 発生した衝撃波形状の非対称性を、前記圧力計測に
より把握し、気流偏角を同定する。That is, (1) A cone or a wedge is installed at the tip of the body, a shock wave is generated, a rod-shaped device for measuring the shape of the shock wave is developed, and a pressure hole is provided therein. (2) The total pressure distribution at the pressure hole position is measured, and the Mach number of the air flow is identified from the angle of the shock wave generated by the cone or the wedge. (3) The asymmetry of the generated shock wave shape is grasped by the pressure measurement, and the airflow declination is identified.
【０００８】[0008]
【作用】超音速気流中に物体が置かれた場合（または物
体が超音速で飛行する場合）には、衝撃波と呼ばれる強
い圧縮波が形成される。この衝撃波により気流の静圧は
大幅に上昇し、また総圧は低下する。この衝撃波前後の
圧力の変化を計測して気流のマッハ数および気流の偏角
（または機体姿勢）を同定しようとするのが本発明の主
趣である。When an object is placed in the supersonic airflow (or when the object flies at supersonic speed), a strong compression wave called a shock wave is formed. Due to this shock wave, the static pressure of the air flow increases significantly and the total pressure decreases. The main purpose of the present invention is to measure the change in pressure before and after the shock wave to identify the Mach number of the air flow and the declination (or body attitude) of the air flow.
【０００９】前記の衝撃波は円錐またはくさび状物体先
端から発生する場合には、斜め衝撃波と呼ばれ、この衝
撃波形状（角度）は気流マッハ数に大きく依存する。
（鈍頭物体のときは垂直衝撃波と斜め衝撃波の組合せに
なり、複雑な形状となる。）この衝撃波の角度を計測す
ることにより、気流マッハ数を逆算することができる。When the shock wave is generated from the tip of a cone or a wedge-shaped object, it is called an oblique shock wave, and the shape (angle) of this shock wave largely depends on the Mach number of the air flow.
(In the case of a blunt object, the vertical shock wave and the diagonal shock wave are combined to form a complicated shape.) By measuring the angle of this shock wave, the airflow Mach number can be calculated backward.
【００１０】この角度計測は以下のように行なう。すな
わち、円錐またはくさびの下流に棒状のものを気流と直
角方向に伸ばす。この棒状のものに圧力孔を多数分布さ
せ、圧力を計測する。そして円錐またはくさびから発生
する衝撃波がこの棒状の物体に当るようにする。This angle measurement is performed as follows. That is, a rod-shaped object is extended downstream of the cone or wedge in a direction perpendicular to the airflow. A large number of pressure holes are distributed in this rod-shaped object to measure the pressure. Then, the shock wave generated from the cone or the wedge hits the rod-shaped object.
【００１１】すると、棒状物体の圧力が衝撃波の当る部
分において大きく変化する。棒と円錐（またはくさび）
の相対位置と圧力孔の位置は設計において十分に把握で
きているので、棒状物体上の圧力の変化位置を知ること
により、衝撃波の形状を知ることができる。この衝撃波
形状は気流マッハ数の関数なので、容易に気流マッハ数
を知ることができる。Then, the pressure of the rod-shaped object changes greatly at the portion where the shock wave hits. Rod and cone (or wedge)
Since the relative position of and the position of the pressure hole are sufficiently grasped in the design, the shape of the shock wave can be known by knowing the change position of the pressure on the rod-shaped object. Since this shock wave shape is a function of the airflow Mach number, the airflow Mach number can be easily known.
【００１２】円錐またはくさびを対称形状に製作してお
けば、形成される衝撃波も、気流に偏向がない場合に
は、対称となる。気流に偏向がある場合には、衝撃波形
状も非対称になる。気流に垂直な棒状物体を対称に左右
（または上下）に展開することによりこの非対称な衝撃
波の形状を把握でき、逆に気流の偏角（または機体姿
勢）を同定することができる。If the cone or the wedge is manufactured in a symmetrical shape, the formed shock wave will also be symmetrical if the air flow is not deflected. When the air flow is deflected, the shock wave shape is also asymmetric. By symmetrically deploying a rod-shaped object perpendicular to the air flow to the left and right (or up and down), the shape of this asymmetrical shock wave can be grasped, and conversely, the declination of the air flow (or airframe attitude) can be identified.
【００１３】[0013]
【実施例】本発明の一実施例を図１ないし図３を参照し
ながら説明する。航空機またはミサイルの胴体先端に円
錐１（またはくさび）と圧力孔２を有する棒状機構３を
設置する。DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS An embodiment of the present invention will be described with reference to FIGS. A rod-shaped mechanism 3 having a cone 1 (or wedge) and a pressure hole 2 is installed at the tip of the fuselage of an aircraft or a missile.
【００１４】棒状機構３は、 (1) 空力荷重によって変形しないこと。 (2) 外部の空気流に対して乱れが少ないような細小形状
であること。 (3) 圧力孔が穿けられ、圧力孔から圧力変換器までの配
管が可能なこと。が条件となっている。The rod-shaped mechanism 3 should not be deformed by (1) aerodynamic load. (2) It has a small shape so that there is little turbulence with respect to the external air flow. (3) A pressure hole should be drilled and piping from the pressure hole to the pressure transducer should be possible. Is a condition.
【００１５】また、「棒状」と表現しているが、気流に
対して乱れが小さい「板状」（気流ベクトルが板面とほ
ぼ平行になるようにする）でもよい。棒状機構３の設置
位置（気流に平行な方向の棒の長さ）に対する制限もな
い。Further, although expressed as "rod-shaped", it may be "plate-shaped" (so that the air flow vector is substantially parallel to the plate surface) with little disturbance to the air flow. There is no limitation on the installation position of the rod-shaped mechanism 3 (the length of the rod in the direction parallel to the air flow).
【００１６】垂直な棒を後方に置くと、衝撃波角度の計
測精度は向上する。（圧力孔２の大きさが有限であるた
め、隣り合った圧力孔２間の距離の最小値が限られる。
下流に行く程、この最小値に原因する衝撃波角度の計算
誤差が小さくなる。）その反面、本機構の形状が大きく
なり、コンパクト性が犠牲になる。If the vertical rod is placed rearward, the accuracy of shock wave angle measurement is improved. (Since the size of the pressure holes 2 is finite, the minimum value of the distance between the adjacent pressure holes 2 is limited.
As it goes downstream, the calculation error of the shock wave angle due to this minimum value becomes smaller. ) On the other hand, the size of this mechanism becomes large and the compactness is sacrificed.
【００１７】次に棒状機構３の圧力孔２により総圧分布
を計測し、総圧の低下より衝撃波４の角度５を求める。Next, the total pressure distribution is measured by the pressure hole 2 of the rod-shaped mechanism 3, and the angle 5 of the shock wave 4 is obtained from the decrease in the total pressure.
【００１８】衝撃波４の角度５は幾何学的に計算する。
図１(a) において、円錐１から発生する衝撃波４の外側
と内側で総圧が変化する。外側および内側ではそれぞれ
一定の値となる。The angle 5 of the shock wave 4 is calculated geometrically.
In Fig. 1 (a), the total pressure changes outside and inside the shock wave 4 generated from the cone 1. The outside and inside have constant values.
【００１９】即ち、図２に示すように、ある所で急激に
圧力が変化し、ステップ状の変化となる。そして計測値
よりステップ状に変化する場所Ｙ1 を探し、式 ｔａｎθ＝（Ｙ1 −Ｙ0 ）／Ｌ から衝撃波角度θを求める。That is, as shown in FIG. 2, the pressure changes abruptly at a certain place and changes stepwise. Then, a place Y 1 that changes stepwise from the measured value is searched for, and the shock wave angle θ is obtained from the equation tan θ = (Y 1 −Y 0 ) / L.
【００２０】衝撃波角度θの計算精度は、圧力孔２の分
布の度合い（図２でΔＹ）に依存する。風洞試験模型の
例では加工上 ΔＹ＝１．０mm は十分に可能なので、Ｌ＝２００mm，θ＝３０°（気流
マッハ数３．０、円錐半頂角約２０度のとき）とする
と、 ｛ｔａｎ３０°＝１１５．４７／２００ ｔａｎθｅ＝１１５．４７＋１．０／２００） ∴θｅ＝３０．２° となり、角度計測誤差は０．２度となる。前述のよう
に、Ｌを大きくしたり、ΔＹを小さくすれば（両者共に
容易である）この誤差は小さくすることができる。The accuracy of calculation of the shock wave angle θ depends on the degree of distribution of the pressure holes 2 (ΔY in FIG. 2). In the example of the wind tunnel test model, ΔY = 1.0 mm is sufficiently possible in processing, so if L = 200 mm and θ = 30 ° (when the airflow Mach number is 3.0 and the cone half apex angle is about 20 degrees), {tan30 ° = 115.47 / 200 tan θe = 115.47 + 1.0 / 200) ∴θe = 30.2 °, and the angle measurement error is 0.2 degrees. As described above, this error can be reduced by increasing L or decreasing ΔY (both are easy).
【００２１】衝撃波４の角度５とマッハ数の関係から気
流マッハ数Ｍを同定する。The airflow Mach number M is identified from the relationship between the angle 5 of the shock wave 4 and the Mach number.
【００２２】即ち、図１(a) において衝撃波の角度５
（θとおく）と円錐１の半頂角（δとおく）とマッハ数
Ｍの関係は次式で与えられる。 ｓｉｎ6 θ＋ｂｓｉｎ4 θ＋ｃｓｉｎ2 θ＝０ ここに、 ｂ＝−Ｍ2 ＋２／Ｍ2 −１．４ ｓｉｎ2 δ ｃ＝（２Ｍ2 ＋１）／Ｍ4 ＋［２．４2 ／４＋０．４／Ｍ2 ］ｓｉｎ2 δ ｄ＝−ｃｏｏ2 δ／Ｍ である。従って、円錐１の形状と衝撃波の角度５（θ）
が解れば、上式をマッハ数Ｍについて解けばマッハ数が
解る。That is, in FIG. 1 (a), the shock wave angle 5
The relationship between (must be θ), half-vertical angle of cone 1 (must be δ) and Mach number M is given by the following equation. sin 6 θ + bsin 4 θ + c sin 2 θ = 0 where b = −M 2 + 2 / M 2 −1.4 sin 2 δ c = (2M 2 +1) / M 4 + [2.4 2 /4+0.4/M 2 ] sin 2 δd = −coo 2 δ / M. Therefore, the shape of the cone 1 and the shock wave angle 5 (θ)
If the above is solved, the Mach number can be found by solving the above formula for the Mach number M.
【００２３】図１(b) にて衝撃波４の上側の角度６と下
側の角度７との差より迎角８を同時に同定することがで
きる。In FIG. 1B, the angle of attack 8 can be identified at the same time from the difference between the upper angle 6 and the lower angle 7 of the shock wave 4.
【００２４】円錐１により衝撃波４が形成される。円錐
が迎角αを持つときには、衝撃波の角度θ1 とθ2 が異
なる。逆に、α＝０°のときは、θ1 ＝θ2 である。そ
こで、θ1 とθ2 との差θ1 −θ2 を調べれば、迎角α
がわかる。A shock wave 4 is formed by the cone 1. When the cone has an attack angle α, the shock wave angles θ 1 and θ 2 are different. On the contrary, when α = 0 °, θ 1 = θ 2 . Therefore, by examining the difference θ 1 −θ 2 between θ 1 and θ 2 , the angle of attack α
I understand.
【００２５】θ1 −θ2 とαの関係は前もって検定して
グラフを作成すると図３のようになる。このグラフを利
用すれば、上記の方法でθ1 とθ2 を出し、この差から
α対θ1 −θ2 のグラフによって迎角αが計算できる。The relation between θ 1 -θ 2 and α is shown in FIG. 3 when a graph is prepared by previously testing. If this graph is used, θ 1 and θ 2 are obtained by the above method, and the angle of attack α can be calculated from the difference by a graph of α vs. θ 1 −θ 2 .
【００２６】データ処理に関する圧力変換器と計算機は
図示していない。Pressure transducers and calculators for data processing are not shown.
【００２７】[0027]
【発明の効果】本発明は前記装置であるので、 (1) マッハ数の計算が簡単になる。 (2) 迎角も同時に計測することができる。等の効果を有
する。EFFECTS OF THE INVENTION Since the present invention is the above apparatus, (1) the calculation of the Mach number is simplified. (2) The angle of attack can also be measured at the same time. And so on.
【図１】本発明の一実施例に係る説明図で、(a) は迎角
が０、(b)は迎角がαの場合である。FIG. 1 is an explanatory diagram according to an embodiment of the present invention, in which (a) shows an attack angle of 0 and (b) shows an attack angle of α.
【図２】総圧が階段状に変化する状態図である。FIG. 2 is a state diagram in which the total pressure changes stepwise.
【図３】迎角αと衝撃波θ1 −θ2 の関係を示すグラフ
である。FIG. 3 is a graph showing a relationship between an attack angle α and a shock wave θ 1 −θ 2 .
【図４】従来のマッハ数計測装置の断面図である。FIG. 4 is a sectional view of a conventional Mach number measuring device.
１ 円錐またはくさび ２ 圧力孔 ３ 棒状機構 ４ 衝撃波 ５ 角度 ６ 上側角度 ７ 下側角度 ８ 迎角（気流偏角） 1 cone or wedge 2 pressure hole 3 rod-like mechanism 4 shock wave 5 angle 6 upper angle 7 lower angle 8 angle of attack (air flow declination)
Claims (1)
し、その角度を計測することにより気流のマッハ数を同
定し、また、前記の衝撃波形状の非対称性を計測するこ
とにより気流の偏角を同定することを特徴とするマッハ
数等計測装置。1. A shock wave from a cone or a wedge is used, and the angle is measured to identify the Mach number of the air flow, and the asymmetry of the shock wave shape is measured to identify the declination of the air flow. Mach number measuring device characterized by the above.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP33931691A JPH05149961A (en) | 1991-11-29 | 1991-11-29 | Measurement device of mach number and the like |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP33931691A JPH05149961A (en) | 1991-11-29 | 1991-11-29 | Measurement device of mach number and the like |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| JPH05149961A true JPH05149961A (en) | 1993-06-15 |
Family
ID=18326306
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| JP33931691A Withdrawn JPH05149961A (en) | 1991-11-29 | 1991-11-29 | Measurement device of mach number and the like |
Country Status (1)
| Country | Link |
|---|---|
| JP (1) | JPH05149961A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112417776A (en) * | 2020-11-10 | 2021-02-26 | 西北工业大学 | Method and device for solving geometric construction of oblique shock wave parameters |
| CN114235325A (en) * | 2021-11-19 | 2022-03-25 | 中国航天空气动力技术研究院 | Shock plate control system and method for wind tunnel continuous variable Mach number test |
-
1991
- 1991-11-29 JP JP33931691A patent/JPH05149961A/en not_active Withdrawn
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112417776A (en) * | 2020-11-10 | 2021-02-26 | 西北工业大学 | Method and device for solving geometric construction of oblique shock wave parameters |
| CN114235325A (en) * | 2021-11-19 | 2022-03-25 | 中国航天空气动力技术研究院 | Shock plate control system and method for wind tunnel continuous variable Mach number test |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| A300 | Withdrawal of application because of no request for examination |
Free format text: JAPANESE INTERMEDIATE CODE: A300 Effective date: 19990204 |