CN216209247U - Vane type sensor for measuring pneumatic data - Google Patents
Vane type sensor for measuring pneumatic data Download PDFInfo
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- CN216209247U CN216209247U CN202121348452.0U CN202121348452U CN216209247U CN 216209247 U CN216209247 U CN 216209247U CN 202121348452 U CN202121348452 U CN 202121348452U CN 216209247 U CN216209247 U CN 216209247U
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- total pressure
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- 230000003068 static effect Effects 0.000 claims abstract description 25
- 230000000712 assembly Effects 0.000 claims abstract description 4
- 238000000429 assembly Methods 0.000 claims abstract description 4
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 claims description 4
- 239000000463 material Substances 0.000 claims description 4
- 239000000741 silica gel Substances 0.000 claims description 4
- 229910002027 silica gel Inorganic materials 0.000 claims description 4
- 239000002131 composite material Substances 0.000 claims description 3
- 239000011152 fibreglass Substances 0.000 claims description 3
- 229910001220 stainless steel Inorganic materials 0.000 claims description 3
- 239000010935 stainless steel Substances 0.000 claims description 3
- 238000005259 measurement Methods 0.000 abstract description 8
- 238000012360 testing method Methods 0.000 abstract description 4
- 238000009434 installation Methods 0.000 description 5
- 230000009286 beneficial effect Effects 0.000 description 2
- 230000007547 defect Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical compound C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000010998 test method Methods 0.000 description 1
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Abstract
The utility model discloses a vane type sensor for measuring pneumatic data, and particularly relates to the technical field of sensors. A vane type sensor for measuring pneumatic data comprises an airspeed tube assembly and two vane assemblies; the axis of the first total pressure pipe head is superposed with the axis of the front pipe, the second total pressure pipe head and the first total pressure pipe head form an included angle of 40 degrees, and the third total pressure pipe head and the second total pressure pipe head form an included angle of 40 degrees; the first total pressure pipe head, the second total pressure pipe head and the third total pressure pipe head are connected with total pressure guide pipes, and the static pressure guide pipes penetrate through the rear pipe; the angle sensor sets up in the horizontal side of head tube, and angle sensor sets up in the oblique below of head tube and upwards, and angle sensor connects in the wind vane pivot, and the wind vane pole is worn to penetrate at the wind vane pivot. By adopting the technical scheme of the utility model, the problem that the traditional vane type sensor has a small measurement range and cannot meet the requirement of large attack angle measurement of more than 30 degrees is solved, and the vane type sensor can be used for a large attack angle model flight test.
Description
Technical Field
The utility model relates to the technical field of sensors, in particular to a vane type sensor for measuring pneumatic data.
Background
The model flight test is a simulated flight test method for researching the aerodynamic problem by flying an aircraft model in the atmosphere, and is one of three aerodynamic research means. The aerodynamic characteristic and the operational stability characteristic of the large attack angle are obtained by developing a model large attack angle flight test, so that the dangerous boundary flight control law can be effectively verified, and technical support is provided for developing a fighter with the stall-passing maneuvering flight capability. The development of a vane type sensor capable of accurately measuring the pneumatic data of a model airplane in a large attack angle flight state is the key for implementing a large attack angle flight test. The pneumatic data to be measured mainly include: airspeed, angle of attack, sideslip angle. The traditional vane type sensor has a small measurement range and cannot meet the requirement of large attack angle measurement of more than 30 degrees.
SUMMERY OF THE UTILITY MODEL
The utility model aims to provide a vane type sensor for measuring pneumatic data, and solves the problems that the traditional vane type sensor is small in measuring range and cannot meet the requirement of large attack angle measurement of more than 30 degrees.
In order to achieve the purpose, the technical scheme of the utility model is as follows: a vane type sensor for measuring pneumatic data comprises an airspeed tube assembly and two vane assemblies;
the airspeed tube assembly comprises a front tube, a rear tube, a first total pressure tube head, a second total pressure tube head, a third total pressure tube head, a total pressure guide tube and a static pressure guide tube, wherein the front tube and the rear tube are fixedly connected, the axis of the first total pressure tube head is overlapped with that of the front tube, the second total pressure tube head and the first total pressure tube head form an included angle of 40 degrees, and the third total pressure tube head and the second total pressure tube head form an included angle of 40 degrees; the first total pressure pipe head, the second total pressure pipe head and the third total pressure pipe head are connected with total pressure guide pipes, and the other end of each total pressure guide pipe penetrates out of the rear pipe; the static pressure guide pipe penetrates through the rear pipe;
each set of the wind vane assembly comprises an angle sensor, a wind vane rotating shaft, a wind vane rod and a wind vane blade, wherein any one angle sensor is arranged on the horizontal side surface of the front pipe, the other angle sensor is arranged in the direction which is obliquely downward and forms an included angle of 45 degrees with the axis of the front pipe, a lead of the angle sensor penetrates through the rear pipe, the other end of the angle sensor is detachably connected to one end of the wind vane rotating shaft, and the wind vane rod penetrates through the other end of the wind vane rotating shaft; the vane is arranged at one end of the vane rod.
Further, the angle sensor adopts a photoelectric absolute angle encoder.
Furthermore, four static pressure holes are symmetrically formed in the pipe wall of the rear pipe, the included angle between the axes of the two static pressure holes on the upper side is 38 degrees, and the included angle between the axes of the two static pressure holes on the upper side is 43 degrees.
Through the arrangement, the included angle can be used for increasing the accuracy of measuring the static pressure.
Furthermore, the vane rod is made of stainless steel materials, and the vane blades are made of glass fiber reinforced plastic composite materials.
Through the setting, adopt different density vanes and wind indicator pole can realize moment balance, compare all vanes and wind indicator pole that adopt same kind of material and want smallly.
Furthermore, the windward end surface of the wind vane rod is in a hemispherical shape.
Furthermore, the total pressure guide pipe and the static pressure guide pipe are both silica gel hoses.
Through the setting, adopt the silica gel hose can be crooked wantonly, easily avoid intraductal obstacle, arrange the convenience.
Compared with the prior art, the beneficial effect of this scheme:
the measuring range of the scheme reaches 100 degrees, and the measuring capability far exceeds the traditional measuring range; by adopting the photoelectric absolute angle encoder as the angle sensor, the defect that the traditional Hall angle sensor is easily interfered by a magnetic field is overcome, and the measurement range and the measurement precision are improved; by adopting the self-balancing vane, the counterweight is saved, and the influence of airframe airflow is reduced.
Drawings
FIG. 1 is a schematic diagram of a vane-type sensor for measuring pneumatic data in accordance with the present invention;
FIG. 2 is a cross-sectional view of a space velocity tube member in accordance with the present invention;
FIG. 3 is a cross-sectional view A-A of FIG. 2;
FIG. 4 is a schematic structural view of the weathervane assembly of the present invention;
FIG. 5 is a schematic structural diagram of the mounting position of the total pressure pipe head in the present invention;
FIG. 6 is a front view of the mounting location of the weathervane assembly of the present invention;
FIG. 7 is a left side view of the mounting location of the weathervane assembly of the present invention.
Detailed Description
The present invention will be described in further detail below by way of specific embodiments:
reference numerals in the drawings of the specification include: the air speed tube assembly 10, the weathervane assembly 20, the front tube 11, the rear tube 12, the first total pressure tube head 13, the second total pressure tube head 14, the third total pressure tube head 15, the total pressure guide tube 16, the static pressure guide tube 17, the angle sensor 21, the weathervane rotating shaft 22, the weathervane rod 23 and the weathervane blade 24.
Examples
As shown in figure 1: a weathervane sensor for measuring pneumatic data comprising an airspeed tube assembly 10 and two sets of weathervane assemblies 20;
as shown in fig. 2, 3 and 5, the pitot tube assembly 10 includes a front tube 11, a rear tube 12, a first total pressure tube head 13, a second total pressure tube head 14, a third total pressure tube head 15, a total pressure guide tube 16 and a static pressure guide tube 17, the front tube 11 and the rear tube 12 are fixedly connected, four static pressure holes are symmetrically formed in the tube wall of the rear tube 12 from top to bottom, an included angle between the hole axes of the two static pressure holes located on the upper side is 38 °, an included angle between the hole axes of the two static pressure holes located on the upper side is 43 °, one end of the static pressure guide tube 17 is installed on the static pressure hole, and the other end of the static pressure guide tube 17 penetrates through the right end of the rear tube 12. The first total pressure pipe head 13, the second total pressure pipe head 14 and the third total pressure pipe head 15 are all installed in the front pipe 11, the installation position of the first total pressure pipe head 13 is overlapped with the axis of the front pipe 11, the installation position of the second total pressure pipe head 14 and the installation position of the first total pressure pipe head 13 form an included angle of 40 degrees, and the installation position of the third total pressure pipe head 15 and the installation position of the second total pressure pipe head 14 form an included angle of 40 degrees; the tail ends of the first total pressure pipe head 13, the second total pressure pipe head 14 and the third total pressure pipe head 15 are connected with total pressure guide pipes 16, and the right end of each total pressure guide pipe 16 penetrates out of the right end of the rear pipe 12. Each total pressure conduit 16 and each static pressure conduit 17 adopt silica gel hoses.
As shown in fig. 4, 6 and 7, each set of vane assembly 20 includes an angle sensor 21, a vane rotating shaft 22, a vane rod 23 and a vane blade 24, each angle sensor 21 employs a photoelectric absolute angle encoder, and the photoelectric absolute angle encoder measures each scribed line of a photoelectric encoding disk in the rotating process to obtain a unique code, and further calculates the rotating angle, thereby overcoming the defect that the conventional hall angle sensor is easily interfered by a magnetic field, and being beneficial to improving the measuring range and the measuring precision. Any angle sensor 21 is installed on the horizontal side of head tube 11, another angle sensor 21 is installed on the oblique below of head tube 11 upwards and is 45 contained angles with the axis of head tube 11, angle sensor 21's wire passes back pipe 12, the top of weathercock pivot 22 is opened there is the cross bore, the bottom is opened there is the perpendicular hole, angle sensor 21's pivot penetrates the perpendicular hole of weathercock pivot 22, and wear to be equipped with the screw jointly on angle sensor 21's pivot and the weathercock pivot 22, weathercock pole 23 passes and penetrates in the cross bore of weathercock pivot 22 and is fixed with weathercock pole 23 cementing, the weathercock pole 23 windward end face adopts the hemisphere shape, reduce air resistance and disturb. The vane blade 24 is provided at one end of the vane rod 23. When the vane assembly 20 works, the vane 24, the vane rod 23, the vane rotating shaft 22 and the rotating shaft of the angle sensor 21 are fixedly connected into a whole. The vane 24 of the wind vane is made of glass fiber reinforced plastic composite material with low density, the vane rod 23 is made of stainless steel material with high density, self-balancing effect is achieved by adopting the vane 24 and the vane rod 23 with different densities, and the pneumatic center of the wind vane is adjusted to the position of a cross hole, so that radial moment applied to the wind vane is small, and the wind vane is suitable for measuring an attack angle and a sideslip angle in a low-speed state.
In the working process of the scheme, the vane sensor is arranged right ahead of the airplane, and the airspeed tube assembly 10 is parallel to the axial direction of the airplane body and points forwards; the wind vane assembly 20 which is positioned at the front and faces to the side surface measures attack angle data, and the wind vane assembly 20 which is positioned at the rear and faces to the oblique lower side measures sideslip angle data; the vane sensor is far away from the surface of the airplane body, is slightly influenced by the airflow on the surface of the airplane, and can accurately output the measurement data of the attack angle and the sideslip angle.
When the center line of the vane 24 is parallel to the airflow direction, no attack angle or sideslip angle is generated, the aerodynamic force does not generate moment, and the vane 24 does not rotate. When the model airplane flies at a certain attack angle or sideslip angle, the vane 24 of the vane rotates to eliminate the attack angle of the vane until the central line of the vane 24 of the vane is consistent with the direction of the airflow because the vane 24 of the vane generates moment by aerodynamic force, and at the moment, the included angle between the vane 24 of the vane and the axis of the airplane body is equal to the attack angle or the sideslip angle of the model airplane. The vane 24 of the vane deflects to drive the vane rotating shaft 22 to rotate, the rotating angle of the vane rotating shaft 22 is directly read by the angle sensor 21, and then the angle sensor is used for resolving and outputting attack angle or sideslip angle data outwards.
The total pressure guide pipe 16 and the static pressure guide pipe 17 led out from the airspeed pipe assembly 10 are respectively connected with an air pressure sensor, the total pressure and the static pressure of a flow field are read, and then the flight speed can be obtained by using a Bernoulli equation; reading the data of an air pressure sensor connected with the first main pressure pipe head 13 when the attack angle is within the range of +/-20 degrees; reading the data of an air pressure sensor connected with the second total pressure tube head 14 when the attack angle is within the range of 20-60 degrees; and reading the data of the air pressure sensor connected with the third total pressure pipe head 15 when the attack angle is within the range of 60-100 degrees.
The foregoing are merely examples of the present invention and common general knowledge of known specific structures and/or features of the schemes has not been described herein in any greater detail. It should be noted that, for those skilled in the art, without departing from the structure of the present invention, several changes and modifications can be made, which should also be regarded as the protection scope of the present invention, and these will not affect the effect of the implementation of the present invention and the practicability of the patent. The scope of the claims of the present application shall be determined by the contents of the claims, and the description of the embodiments and the like in the specification shall be used to explain the contents of the claims.
Claims (6)
1. A weathervane sensor for measuring pneumatic data, comprising: comprises an airspeed head assembly (10) and two sets of vane assemblies (20);
the airspeed tube assembly (10) comprises a front tube (11), a rear tube (12), a first total pressure tube head (13), a second total pressure tube head (14), a third total pressure tube head (15), a total pressure guide tube (16) and a static pressure guide tube (17), wherein the front tube (11) and the rear tube (12) are fixedly connected, the first total pressure tube head (13) is overlapped with the axis of the front tube (11), the second total pressure tube head (14) and the first total pressure tube head (13) form an included angle of 40 degrees, and the third total pressure tube head (15) and the second total pressure tube head (14) form an included angle of 40 degrees; the first total pressure pipe head (13), the second total pressure pipe head (14) and the third total pressure pipe head (15) are connected with total pressure guide pipes (16), and the other end of each total pressure guide pipe (16) penetrates through the rear pipe (12); the static pressure guide pipe (17) penetrates through the rear pipe (12);
each set of the vane assembly (20) comprises an angle sensor (21), a vane rotating shaft (22), a vane rod (23) and a vane blade (24), any one of the angle sensors (21) is arranged on the horizontal side surface of the front pipe (11), the other angle sensor is arranged on the inclined lower direction forming an included angle of 45 degrees with the axis of the front pipe (11), a lead of the angle sensor (21) penetrates through the rear pipe (12), the other end of the angle sensor (21) is detachably connected to one end of the vane rotating shaft (22), and the vane rod (23) penetrates through the other end of the vane rotating shaft (22); the vane (24) is arranged at one end of the vane rod (23).
2. A weathervane sensor for measuring pneumatic data according to claim 1, wherein: the angle sensor (21) adopts a photoelectric absolute angle encoder.
3. A weathervane sensor for measuring pneumatic data according to claim 1, wherein: four static pressure holes are symmetrically formed in the pipe wall of the rear pipe (12), the included angle between the axes of the two static pressure holes on the upper side is 38 degrees, and the included angle between the axes of the two static pressure holes on the upper side is 43 degrees.
4. A weathervane sensor for measuring pneumatic data according to claim 1, wherein: the vane rod (23) is made of stainless steel materials, and the vane blades (24) are made of glass fiber reinforced plastic composite materials.
5. A weathervane sensor for measuring pneumatic data according to claim 1, wherein: the windward end surface of the wind indicator rod (23) is in a hemispherical shape.
6. A weathervane sensor for measuring pneumatic data according to claim 1, wherein: the total pressure conduit (16) and the static pressure conduit (17) both adopt silica gel hoses.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121348452.0U CN216209247U (en) | 2021-06-17 | 2021-06-17 | Vane type sensor for measuring pneumatic data |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121348452.0U CN216209247U (en) | 2021-06-17 | 2021-06-17 | Vane type sensor for measuring pneumatic data |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN216209247U true CN216209247U (en) | 2022-04-05 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202121348452.0U Withdrawn - After Issue CN216209247U (en) | 2021-06-17 | 2021-06-17 | Vane type sensor for measuring pneumatic data |
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| Country | Link |
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| CN (1) | CN216209247U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113419078A (en) * | 2021-06-17 | 2021-09-21 | 中国空气动力研究与发展中心空天技术研究所 | Vane type sensor for measuring pneumatic data |
-
2021
- 2021-06-17 CN CN202121348452.0U patent/CN216209247U/en not_active Withdrawn - After Issue
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113419078A (en) * | 2021-06-17 | 2021-09-21 | 中国空气动力研究与发展中心空天技术研究所 | Vane type sensor for measuring pneumatic data |
| CN113419078B (en) * | 2021-06-17 | 2024-05-14 | 中国空气动力研究与发展中心空天技术研究所 | Wind vane type sensor for measuring pneumatic data |
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| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20220405 Effective date of abandoning: 20240514 |
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| AV01 | Patent right actively abandoned |
Granted publication date: 20220405 Effective date of abandoning: 20240514 |
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| AV01 | Patent right actively abandoned | ||
| AV01 | Patent right actively abandoned |