JPH0433198Y2 - - Google Patents
Info
- Publication number
- JPH0433198Y2 JPH0433198Y2 JP15727486U JP15727486U JPH0433198Y2 JP H0433198 Y2 JPH0433198 Y2 JP H0433198Y2 JP 15727486 U JP15727486 U JP 15727486U JP 15727486 U JP15727486 U JP 15727486U JP H0433198 Y2 JPH0433198 Y2 JP H0433198Y2
- Authority
- JP
- Japan
- Prior art keywords
- static pressure
- aircraft
- thin plate
- pressure hole
- guide
- 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
Links
- 230000003068 static effect Effects 0.000 claims description 35
- 230000001105 regulatory effect Effects 0.000 claims description 2
- 230000033228 biological regulation Effects 0.000 description 7
- 238000000034 method Methods 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 3
- 238000009530 blood pressure measurement Methods 0.000 description 2
- 230000007423 decrease Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
Landscapes
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
- Medicinal Preparation (AREA)
Description
【考案の詳細な説明】
〔産業上の利用分野〕
本考案は航空機の速度系の位置誤差を補償する
航空機の速度系静圧調節装置に関する。[Detailed Description of the Invention] [Industrial Application Field] The present invention relates to an aircraft speed system static pressure regulating device for compensating for position errors in the speed system of an aircraft.
航空機の速度系は通常、第6図A,Bに示すよ
うに、総圧を計測する総圧管07と静圧を計測す
る静圧孔08とからなり、これらが結合されて航
空機速度計06に速度が指示される。この場合、
総圧は機体形状の影響をうけることが少く、位置
誤差は小さいが、静圧は機体形状の影響をうけや
すく位置誤差が大きい。開発機の場合、位置誤差
の規定を満足する静圧孔を決定することが非常に
難しい。
The speed system of an aircraft usually consists of a total pressure pipe 07 for measuring total pressure and a static pressure hole 08 for measuring static pressure, as shown in FIGS. 6A and 6B, and these are connected to form an aircraft speedometer 06. Speed is indicated. in this case,
Total pressure is less affected by the shape of the aircraft and its positional error is small, but static pressure is easily affected by the shape of the aircraft and has a large positional error. In the case of the developed machine, it is extremely difficult to determine a static pressure hole that satisfies the position error regulations.
従来は第4図に示すように、航空機01の機体
表面に多数の静圧子02をあけておいて、位置誤
差の規定を満足する静圧孔を飛行試験を行つて選
択していた。また別の方法として、第5図A,B
に示すように静圧孔02の近傍に突起物03をも
うけて、位置誤差の規定を満足する突起物03の
位置および高さ等を飛行試験でトライアンドエラ
ー方式により決定していた。 Conventionally, as shown in FIG. 4, a large number of static pressure holes 02 are drilled on the surface of an aircraft 01, and static pressure holes that satisfy the positional error regulations are selected by performing a flight test. As another method, Fig. 5 A and B
As shown in FIG. 2, a protrusion 03 is provided near the static pressure hole 02, and the position, height, etc. of the protrusion 03 that satisfies the positional error regulations are determined by a trial and error method in a flight test.
前記の如く、航空機の速度系は通常、総圧管に
よる総圧計測と、静圧孔による静圧計測とにより
行われるが、静圧が機体形状や位置によつて大き
く影響され、位置誤差が生じる。この位置誤差を
規定範囲内におさえるため、開発機の初期に大変
な時間と労力を要し、苦労することが多いという
問題点があつた。
As mentioned above, the speed system of an aircraft is usually measured by total pressure measurement using a total pressure pipe and static pressure measurement using a static pressure hole, but static pressure is greatly affected by the shape and position of the aircraft, resulting in position errors. . In order to keep this positional error within a specified range, there was a problem in that it required a lot of time and effort in the early stages of developing the machine, and it was often difficult.
本考案は、以上の問題点を解消させ、規定を満
足させるための静圧を容易に得ることができる航
空機の速度系静圧調節装置を提供することを目的
とする。 SUMMARY OF THE INVENTION An object of the present invention is to provide an aircraft speed system static pressure adjustment device that can solve the above problems and easily obtain static pressure that satisfies regulations.
本考案による航空機の速度系静圧調節装置は、
航空機の機体表面に穿設された静圧孔と、この静
圧孔の近傍に設けられてガイドに沿つて動かされ
る薄板と、前記航空機に配設され前記薄板の前記
静圧孔に対する位置および高さを前記ガイドに沿
つて変化させるコントローラとを具備してなるこ
とを特徴とし、コントローラによりガイド(溝状
のもの)に沿つて静圧孔に対する位置および高さ
を航空機機上で変化できる薄板を用いて、1回の
飛行試験で位置誤差の規定を満足する静圧孔を決
定できるようにしている。
The aircraft speed system static pressure adjustment device according to the present invention has the following features:
A static pressure hole drilled in the surface of the aircraft body, a thin plate provided near the static pressure hole and moved along a guide, and a position and height of the thin plate provided on the aircraft with respect to the static pressure hole. and a controller that changes the height along the guide, and a thin plate whose position and height relative to the static pressure hole can be changed on the aircraft along the guide (groove-shaped) by the controller. Using this method, a static pressure hole that satisfies the position error regulations can be determined in a single flight test.
例えば第3図に示すように、空気中に物体を突
出させると、その前方では静圧が大きくなり、後
方では静圧が小さくなる。本考案によればこの原
理を応用し、静圧孔に対する薄板の位置および高
さをコントローラにより変化させることにより、
航空機の静圧孔のあらゆる方向に容易にかなりの
大きさの静圧を変化させることができる。
For example, as shown in FIG. 3, when an object is projected into the air, the static pressure increases in front of it and decreases behind it. According to the present invention, by applying this principle and changing the position and height of the thin plate with respect to the static pressure hole using a controller,
The static pressure can easily be changed by a significant amount in all directions in the static pressure hole of the aircraft.
第1図および第2図は、それぞれ本考案の一実
施例の構成を示す部分断面図および平面図であ
り、1は航空機の機体表面6に穿設された静圧
孔、2は静圧孔1の近傍に設けられて溝状のガイ
ド3に沿つて動かされる静圧調節用の薄板、4は
航空機に配設され薄板2の静圧孔1に対する位置
および高さをガイド3に沿つて変化させるコント
ローラ、5はコントローラ4により制御されて薄
板2を静圧孔1に対して上下方向(突出方向)に
移動させたり、および円周方向に回動(相対位置
の移動)させたりする駆動機構を示す。
1 and 2 are a partial sectional view and a plan view, respectively, showing the configuration of an embodiment of the present invention, in which 1 is a static pressure hole drilled in the fuselage surface 6 of an aircraft, and 2 is a static pressure hole. A thin plate 4 for adjusting static pressure is provided near 1 and moved along a groove-shaped guide 3; 4 is disposed on the aircraft and changes the position and height of the thin plate 2 relative to the static pressure hole 1 along the guide 3 5 is a drive mechanism that is controlled by the controller 4 to move the thin plate 2 in the vertical direction (protrusion direction) with respect to the static pressure hole 1 and rotate it in the circumferential direction (move the relative position). shows.
上記本考案の一実施例の作用について説明す
る。 The operation of the embodiment of the present invention described above will be explained.
コントローラ4により駆動機構5を制御して薄
板2を任意の位置および突出高さに設定して航空
機の飛行試験を行なう。このとき位置誤差の規定
を満足していなかつたら、コントローラ4により
再び駆動機構5を制御して、薄板2を他の位置お
よび突出高さに設定して引続いて飛行試験を行な
う。このようにして機上でコントローラ4を操作
することにより、位置誤差の規定を満足する薄板
2の突出高さおよび位置を1回の飛行試験で決定
できる。 The drive mechanism 5 is controlled by the controller 4 to set the thin plate 2 at an arbitrary position and protrusion height, and a flight test of the aircraft is performed. At this time, if the positional error regulation is not satisfied, the controller 4 controls the drive mechanism 5 again to set the thin plate 2 at another position and protrusion height, and then perform a flight test. By operating the controller 4 onboard the aircraft in this way, the protrusion height and position of the thin plate 2 that satisfy the positional error regulations can be determined in one flight test.
以上のように、従来技術によれば、航空機の機
体改修工事の増大、飛行試験回数の増加およびフ
ロータイムの増大等の問題点があつたが、本考案
によればこれらの問題点を解消し、航空機の速度
系静圧の大きさを容易に調節でき、開発機の飛行
試験を効率良く実施できる等の優れた効果があ
る。
As described above, the conventional technology had problems such as an increase in aircraft body modification work, an increase in the number of flight tests, and an increase in flow time, but the present invention solves these problems. This method has excellent effects such as being able to easily adjust the magnitude of the aircraft's speed-related static pressure and efficiently conducting flight tests of the developed aircraft.
第1図は本考案の一実施例の構成を示す部分断
面図、第2図は本考案の一実施例の構成を示す部
分平面図、第3図は本考案の原理を示す図、第4
図〜第6図A,Bは従来例を説明するための図で
ある。
1……静圧孔、2……薄板、3……ガイド、4
……コントローラ、5……駆動機構。
Fig. 1 is a partial sectional view showing the structure of an embodiment of the present invention, Fig. 2 is a partial plan view showing the structure of an embodiment of the invention, Fig. 3 is a diagram showing the principle of the invention, and Fig. 4 is a diagram showing the principle of the invention.
6A and 6B are diagrams for explaining a conventional example. 1... Static pressure hole, 2... Thin plate, 3... Guide, 4
... Controller, 5 ... Drive mechanism.
Claims (1)
静圧孔の近傍に設けられてガイドに沿つて動かさ
れる薄板と、前記航空機に配設され前記薄板の前
記静圧孔に対する位置および高さを前記ガイドに
沿つて変化させるコントローラとを具備してなる
ことを特徴とする航空機の速度系静圧調節装置。 A static pressure hole drilled in the surface of the aircraft body, a thin plate provided near the static pressure hole and moved along a guide, and a position and height of the thin plate provided on the aircraft with respect to the static pressure hole. An aircraft speed system static pressure regulating device, comprising: a controller for changing the static pressure along the guide.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP15727486U JPH0433198Y2 (en) | 1986-10-14 | 1986-10-14 |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
JP15727486U JPH0433198Y2 (en) | 1986-10-14 | 1986-10-14 |
Publications (2)
Publication Number | Publication Date |
---|---|
JPS6363300U JPS6363300U (en) | 1988-04-26 |
JPH0433198Y2 true JPH0433198Y2 (en) | 1992-08-10 |
Family
ID=31079666
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
JP15727486U Expired JPH0433198Y2 (en) | 1986-10-14 | 1986-10-14 |
Country Status (1)
Country | Link |
---|---|
JP (1) | JPH0433198Y2 (en) |
Families Citing this family (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2891368B1 (en) * | 2005-09-27 | 2007-11-30 | Airbus France Sas | SYSTEM FOR MONITORING ANEMOBAROMLINOMETRIC PARAMETERS FOR AIRCRAFT |
-
1986
- 1986-10-14 JP JP15727486U patent/JPH0433198Y2/ja not_active Expired
Also Published As
Publication number | Publication date |
---|---|
JPS6363300U (en) | 1988-04-26 |
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