CN210166407U - Aircraft angle of attack sensor - Google Patents
Aircraft angle of attack sensor Download PDFInfo
- Publication number
- CN210166407U CN210166407U CN201920337603.9U CN201920337603U CN210166407U CN 210166407 U CN210166407 U CN 210166407U CN 201920337603 U CN201920337603 U CN 201920337603U CN 210166407 U CN210166407 U CN 210166407U
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Abstract
The utility model discloses an aircraft angle of attack sensor designs airborne vehicle technical field, including the shell with install at the inside five bleed pipes of shell, these five bleed pipes include first side bleed pipe, second side bleed pipe, central bleed pipe, third side bleed pipe and fourth side bleed pipe, and central bleed pipe is located central position, and all the other four side bleed pipes are located central bleed pipe's both sides, and the heating pipe is still installed to the shell inside. The utility model discloses an aircraft angle of attack sensor can increase angle of attack measuring range through reasonable bleed pipe combination, can avoid bleed intraduct to freeze moreover under the effect of heating pipe, guarantees that angle of attack sensor can normally work.
Description
Technical Field
The utility model relates to an airborne vehicle technical field, in particular to aircraft angle of attack sensor.
Background
The angle of attack sensor is a device for measuring the angle of attack of an airplane and mainly comprises a probe type angle of attack sensor, a differential pressure type sensor and a vane type sensor. The probe type attack angle sensor is usually integrated on a nose airspeed head, and mainly utilizes pressure change to measure the attack angle. The differential pressure type attack angle sensor mainly uses the pressure difference measured by paired holes with an included angle of 90 degrees, and obtains an angle value according to the angular displacement of an element caused by feedback moment generated by the pressure difference. What is more commonly used on civil aircraft is a weathervane angle of attack sensor, its constitution mainly includes: a flow angle sensor and a potentiometer.
The existing probe type attack angle sensor mainly measures total pressure, static pressure, speed and two airflow angles (sideslip angle and pitch angle) based on a five-hole pneumatic probe, and measures the airflow angles based on a three-hole pneumatic probe. The angle measurement range of the two pneumatic probes is small, and the three-hole pneumatic probe is sensitive to the angle (sideslip angle) in the other direction; the two pneumatic probes are mainly used for measuring the internal flow field of the engine, and the icing problem which can occur when the pneumatic probes are used as an attack angle sensor is not considered.
SUMMERY OF THE UTILITY MODEL
The embodiment of the utility model provides a probe-type aircraft angle of attack sensor adopts the design of five hole pneumatic probe, has installed the heating pipe simultaneously, has great angle of attack measuring range, has overcome frozen problem moreover.
The embodiment of the utility model provides an aircraft angle of attack sensor, include the shell and install the inside hollow bleed air pipe of five of shell: the air guide pipe comprises a first side air guide pipe, a second side air guide pipe, a central air guide pipe, a third side air guide pipe and a fourth side air guide pipe;
the first side air-entraining pipe and the fourth side air-entraining pipe are distributed on two sides of the central air-entraining pipe, the second side air-entraining pipe and the third side air-entraining pipe are distributed on two sides of the central air-entraining pipe, the second side air-entraining pipe is positioned between the central air-entraining pipe and the first side air-entraining pipe, and the third side air-entraining pipe is positioned between the central air-entraining pipe and the fourth side air-entraining pipe;
the central air-entraining pipe is a straight pipe, the first side air-entraining pipe, the second side air-entraining pipe, the third side air-entraining pipe and the fourth side air-entraining pipe all comprise a straight pipe section and a bent pipe section, an included angle between the straight pipe section and the bent pipe section in the second side air-entraining pipe is larger than an included angle between the straight pipe section and the bent pipe section in the first side air-entraining pipe, and an included angle between the straight pipe section and the bent pipe section in the third side air-entraining pipe is larger than an included angle between the straight pipe section and the bent pipe section in the fourth side air-entraining pipe;
at least one heating pipe is arranged in the shell.
The embodiment of the utility model provides an aircraft angle of attack sensor has following advantage:
(1) the measurement range of the attack angle is large;
(2) the influence of the sideslip angle on the measurement of the attack angle is small;
(3) meanwhile, atmospheric data such as attack angle, total pressure, static pressure and the like can be measured;
(4) the pipeline is prevented from being blocked by icing at high altitude;
(5) the volume of the airflow pipeline cavity is small, and the reaction is fast;
(6) it can also be used as a side slip angle measurement;
(7) can be used as a redundant design of an airplane atmosphere measuring system.
Drawings
Fig. 1 is a schematic structural view of an aircraft angle of attack sensor provided by an embodiment of the present invention.
The reference numbers illustrate:
100-housing, 110-heating duct, 120-first side bleed air duct, 130-second side bleed air duct, 140-central bleed air duct, 150-third side bleed air duct, 160-fourth side bleed air duct.
Detailed Description
In the following, an embodiment of the present invention will be described in detail with reference to the drawings, but it should be understood that the scope of the present invention is not limited by the embodiment.
Referring to fig. 1, the utility model provides an aircraft angle of attack sensor, include shell 100 and install the inside five bleed air pipes of shell 100, these five bleed air pipes are respectively: a first side bleed air duct 120, a second side bleed air duct 130, a central bleed air duct 140, a third side bleed air duct 150, and a fourth side bleed air duct 160, all of which are air ducts for introducing external air.
In this embodiment, the five bleed air pipes are all distributed in the same plane, and the first side bleed air pipe 120 and the fourth side bleed air pipe 160 have the same shape, and the second side bleed air pipe 130 and the third side bleed air pipe 150 have the same shape. First side bleed air pipe 120 and fourth side bleed air pipe 160 symmetric distribution are in the both sides of central bleed air pipe 140, second side bleed air pipe 130 and third side bleed air pipe 150 symmetric distribution are in the both sides of central bleed air pipe 140, just second side bleed air pipe 130 is located between central bleed air pipe 140 and first side bleed air pipe 120, third side bleed air pipe 150 is located between central bleed air pipe 140 and fourth side bleed air pipe 160.
The central bleed air pipe 140 is a straight pipe, the first side bleed air pipe 120, the second side bleed air pipe 130, the third side bleed air pipe 150 and the fourth side bleed air pipe 160 are bent pipes, the four side bleed air pipes all include straight pipe sections and bent pipe sections, and the straight pipe sections of the four side bleed air pipes are substantially the same in length and substantially corresponding in position. The included angle between straight tube section and bend section is the same in second side bleed air pipe 130 and third side bleed air pipe 150, the included angle between straight tube section and bend section is the same in first side bleed air pipe 120 and fourth side bleed air pipe 160, just the included angle between straight tube section and the bend section is greater than in second side bleed air pipe 130 the included angle between straight tube section and the bend section in first side bleed air pipe 120. In this embodiment, the angle between the straight pipe section and the bent pipe section in the first bypass bleed pipe 120 is 90 degrees.
In order to avoid the icing inside the bleed air duct, at least one heating pipe 110 is further installed inside the housing 100, the heating pipe 110 is installed at a position close to the bleed air duct, and the heating pipe may be an electric heating pipe, and the generated heat can be transferred to the bleed air duct to avoid the icing. In this embodiment, the number of the heating pipes 110 is two, and the two heating pipes are respectively and symmetrically installed on two sides of the plane where the air entraining pipe is located, and the heating pipes 110 are U-shaped pipes, so that the emitted heat can be more uniformly transferred to the air entraining pipe.
The utility model discloses a sensor compares with the probe of internal flow test, has that the size is big, anti-icing, prevent blockking up, hold the chamber small, advantage that the reaction is fast.
For five bleed air ducts, the total pressure, static pressure, angle of attack, etc. atmospheric data may be determined by measuring the absolute pressure inside the central bleed air duct 140, and the relative pressures of the first side bleed air duct 120, the second side bleed air duct 130, the third side bleed air duct 150, and the fourth side bleed air duct 160 to the central bleed air duct 140. The attack angle sensor needs to be calibrated in the wind tunnel before being used, and the attack angle range is not less than +/-120 degrees. A relationship between the five-hole pressure coefficient and the angle of attack (similar to the three-hole probe) is obtained, the five-hole probe is equivalent to three-hole probes with the second side bleed air tube 130, the central bleed air tube 140 and the third side bleed air tube 150 as center holes, and the combination of the first side bleed air tube 120 and the second side bleed air tube 130, the third side bleed air tube 150 and the fourth side bleed air tube 160 can expand the measurement range of the angle of attack.
In actual use, if one of the second side bleed air pipe 130, the central bleed air pipe 140 and the third side bleed air pipe 150 has the maximum pressure, the hole with the maximum pressure is taken as a middle hole, and measurement is performed according to a three-hole needle; if one of the first or fourth side bleed air tubes 120, 160 apertures is at its greatest pressure, a measurement is taken with the second or third side bleed air tube 130, 150 as the three-aperture needle of the intermediate aperture.
The above disclosure is only for a few specific embodiments of the present invention, however, the present invention is not limited to the embodiments, and any changes that can be considered by those skilled in the art shall fall within the protection scope of the present invention.
Claims (5)
1. Aircraft angle of attack sensor, its characterized in that, including the shell and install five hollow bleed air pipes inside the shell: the air guide pipe comprises a first side air guide pipe, a second side air guide pipe, a central air guide pipe, a third side air guide pipe and a fourth side air guide pipe;
the first side air-entraining pipe and the fourth side air-entraining pipe are distributed on two sides of the central air-entraining pipe, the second side air-entraining pipe and the third side air-entraining pipe are distributed on two sides of the central air-entraining pipe, the second side air-entraining pipe is positioned between the central air-entraining pipe and the first side air-entraining pipe, and the third side air-entraining pipe is positioned between the central air-entraining pipe and the fourth side air-entraining pipe;
the central air-entraining pipe is a straight pipe, the first side air-entraining pipe, the second side air-entraining pipe, the third side air-entraining pipe and the fourth side air-entraining pipe all comprise a straight pipe section and a bent pipe section, an included angle between the straight pipe section and the bent pipe section in the second side air-entraining pipe is larger than an included angle between the straight pipe section and the bent pipe section in the first side air-entraining pipe, and an included angle between the straight pipe section and the bent pipe section in the third side air-entraining pipe is larger than an included angle between the straight pipe section and the bent pipe section in the fourth side air-entraining pipe;
at least one heating pipe is arranged in the shell.
2. An aircraft angle of attack sensor according to claim 1, characterised in that the first, second, central, third and fourth side bleed air ducts all lie in the same plane.
3. An aircraft angle of attack sensor according to claim 1, characterised in that the included angles between the straight and curved sections of the second and third side bleed air tubes are the same and the included angles between the straight and curved sections of the first and fourth side bleed air tubes are the same.
4. An aircraft angle of attack sensor according to claim 2, characterised in that the number of heating tubes is two, each symmetrically mounted on either side of the plane in which the five bleed air tubes lie.
5. An aircraft angle of attack sensor according to claim 1, wherein the heating tube is a U-tube.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920337603.9U CN210166407U (en) | 2019-03-15 | 2019-03-15 | Aircraft angle of attack sensor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920337603.9U CN210166407U (en) | 2019-03-15 | 2019-03-15 | Aircraft angle of attack sensor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN210166407U true CN210166407U (en) | 2020-03-20 |
Family
ID=69789558
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201920337603.9U Expired - Fee Related CN210166407U (en) | 2019-03-15 | 2019-03-15 | Aircraft angle of attack sensor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN210166407U (en) |
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2019
- 2019-03-15 CN CN201920337603.9U patent/CN210166407U/en not_active Expired - Fee Related
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20200320 Termination date: 20210315 |
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| CF01 | Termination of patent right due to non-payment of annual fee |