CN113340264B - Method and device for debugging installation angle of aircraft attack angle sensor - Google Patents
Method and device for debugging installation angle of aircraft attack angle sensor Download PDFInfo
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- CN113340264B CN113340264B CN202010135742.0A CN202010135742A CN113340264B CN 113340264 B CN113340264 B CN 113340264B CN 202010135742 A CN202010135742 A CN 202010135742A CN 113340264 B CN113340264 B CN 113340264B
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
- G01C1/00—Measuring angles
Abstract
A method and a device for debugging the installation angle of an aircraft attack angle sensor are disclosed, wherein an angle vernier scale is arranged on a flange plate of an installation support, and a corresponding angle vernier is arranged on an adjusting plate; the adjusting plate is connected with the flange plate through a first adjustable structure; the angle of attack sensor and the adjusting disk are relatively fixed through a positioning pin, so that an angle cursor on the adjusting disk and the angle of attack sensor form a whole; the angle of attack sensor and the adjusting plate are connected with the flange plate of the mounting bracket through the second adjustable structure, the mounting angle adjustment quantity of the angle of attack sensor is calculated through trial flight data, the mounting angle of the adjusting plate is adjusted through the first adjustable structure between the flange plate and the adjusting plate until the mounting angle adjustment quantity of the angle of attack sensor is calculated through the trial flight data and is within an allowable range, and the position of the angle cursor on the adjusting plate relative to the angle cursor scale on the flange plate corresponds to the final mounting angle of the angle of attack sensor, so that the mounting angle of the angle of attack sensor is adjusted.
Description
Technical Field
The invention relates to the field of aviation manufacturing, in particular to a method for debugging the installation angle of an aircraft attack angle sensor capable of adjusting the angle with high precision.
Background
The airborne stall warning system measures the attack angle of the airplane in real time through an attack angle sensor arranged on the airplane and carries out stall warning according to the attack angle. The accuracy of the angle of attack sensor affects the false alarm rate of the stall warning system. The accuracy of the angle of attack sensor is mainly composed of the measurement accuracy and the installation accuracy of the sensor itself. In order to reduce the false alarm rate of the stall warning system, a high-precision attack angle sensor can be used to ensure the measurement precision, and meanwhile, the installation precision of the attack angle sensor needs to be improved.
When the airplane is manufactured, the first installation angle of the attack angle sensor on the airplane is obtained through theoretical calculation, and the first installation angle needs to be corrected according to the measured real local airflow direction of the airplane during test flight, so that the installation angle of the attack angle sensor needs to be adjusted.
In the prior art, the high-precision attack angle sensor extends out of the interior of an aircraft skin and needs to be fixed on a nose in an installation mode from inside to outside, so that the high-precision attack angle sensor is installed in the aircraft manufacturing process and is positioned by taking a fixture as a reference, and after the aircraft is assembled, if the installation angle of the high-precision attack angle sensor needs to be adjusted, the high-precision attack angle sensor cannot be accurately positioned, so that the installation angle debugging of the aircraft attack angle sensor is very difficult.
Disclosure of Invention
The application aims to provide a low-cost, simple, convenient and quick installation angle debugging method and installation device capable of adjusting an aircraft attack angle sensor with high precision aiming at the defects in the prior art and the requirements of aircraft development and production.
The utility model provides a method for debugging the installation angle of an aircraft angle of attack sensor, contains installing support, adjusting disk and angle of attack sensor, and the installing support is the recess support of taking the ring flange, and the recess support is connected with the aircraft organism, and the ring flange is connected with adjusting disk and angle of attack sensor, and the probe of angle of attack sensor passes through the central through-hole of adjusting disk and installing support and stretches out outside the aircraft organism, and its characterized in that contains following content: 1) Angle vernier scales are arranged on a flange plate of the mounting bracket, and a corresponding angle vernier is arranged on the adjusting plate; 2) The adjusting plate is connected with the flange plate through a first adjustable structure; 3) The angle of attack sensor and the adjusting disk are relatively fixed through a positioning pin, so that an angle cursor on the adjusting disk and the angle of attack sensor form a whole; 4) The angle of attack sensor and the adjusting plate are connected with the flange plate of the mounting bracket through a second adjustable structure, 5) the angle of attack sensor is mounted on the airplane body through the mounting bracket and the adjusting plate, and the position of an angle cursor on the adjusting plate relative to the angle cursor scale on the flange plate is recorded and corresponds to the mounting angle of the angle of attack sensor; 6) The method comprises the following steps of (1) carrying out test flight on an airplane provided with an attack angle sensor, and calculating the installation angle adjustment quantity of the attack angle sensor through test flight data; 7) Separating the attack angle sensor and the adjusting disc from a flange plate of the mounting bracket, and adjusting the mounting angle of the adjusting disc through a first adjustable structure between the flange plate and the adjusting disc according to the mounting angle adjustment amount of the attack angle sensor; 8) And (5) repeating the step 5), the step 6) and the step 7) until the adjustment quantity of the mounting angle of the attack angle sensor is calculated to be within the allowable range through the test flight data, and the position of the angle cursor on the adjusting disc relative to the angle cursor scale on the flange plate corresponds to the final mounting angle of the attack angle sensor, so that the adjustment of the mounting angle of the attack angle sensor is realized.
The flange plate is provided with angle vernier scales which are arranged at the position close to the outer edge of the flange plate and are arranged in a fan shape; the adjusting disc is provided with a fan-shaped notch at the position corresponding to the angle vernier scale of the flange disc, and the edge of the fan-shaped notch is provided with an angle vernier matched with the angle vernier scale of the flange disc for use.
The first adjustable structure is formed by matching a long circular hole and a fastening piece, and the long circular hole is a connecting hole which is formed in the adjusting plate and used for being connected with the flange plate, or is a connecting hole which is formed in the flange plate and used for being connected with the adjusting plate.
The second adjustable structure is formed by matching a long circular hole and a fastening piece, wherein the long circular hole is a connecting hole which is formed in the adjusting plate and used for being connected with the attack angle sensor, or a connecting hole which is formed in the flange plate and used for being connected with the attack angle sensor, and the long circular hole which is formed in the flange plate and used for passing through a locating pin of the attack angle sensor.
The application still provides an installation device of aircraft angle of attack sensor, contains installing support and adjusting disk, and the installing support is the recess support of taking the ring flange, and the recess support is connected with the aircraft organism, and the ring flange is connected with adjusting disk and angle of attack sensor, and outside the probe of angle of attack sensor stretches out the aircraft organism through the central through-hole of adjusting disk and installing support, its characterized in that: the flange plate of the mounting bracket is provided with angle vernier scales, and the adjusting plate is provided with a corresponding angle vernier.
The flange plate is provided with angle vernier scales which are arranged at the position close to the outer edge of the flange plate and are arranged in a fan shape; the adjusting disc is provided with a fan-shaped notch at the position corresponding to the angle vernier scale of the flange plate, and the edge of the fan-shaped notch is provided with an angle vernier matched with the angle vernier scale of the flange plate for use.
The angle of attack sensor is characterized in that a flange plate of the mounting support is provided with a connecting round hole for connecting an adjusting plate, a fixing round hole for connecting the angle of attack sensor, a long round hole for passing through a positioning pin of the angle of attack sensor and angle vernier scales, the adjusting plate is provided with a connecting long round hole corresponding to the connecting round hole for connecting the adjusting plate with the flange plate, a positioning round hole corresponding to the fixing pin of the angle of attack sensor, a fixing long round hole corresponding to the fixing round hole for connecting the angle of attack sensor with the flange plate and an angle vernier corresponding to the angle vernier scales of the flange plate.
The beneficial effect of this application lies in: 1) Through the angle vernier scale and the angle vernier on the installation device of the aircraft attack angle sensor, the accuracy of the installation and adjustment angle of the aircraft attack angle sensor can be guaranteed to reach 0.1 degree or even higher, and the accurate installation of the aircraft attack angle sensor is met. 2) After the airplane is assembled, the airplane reference is not required to be searched to adjust the installation angle of the attack angle sensor, so that the installation angle of the attack angle sensor can be adjusted without reference; 3) The mounting angle of the attack angle sensor can be adjusted by using a general guarantee tool without using a special stable position tool or a special mounting tool; 4) Simple and easy to operate, and can be adjusted without professional training.
The present application is described in further detail below with reference to the accompanying drawings of embodiments.
Drawings
Fig. 1 is a schematic view of the installation angle debugging principle of an aircraft angle of attack sensor.
Fig. 2 is a schematic view of the connection of the mounting bracket to the airframe of the aircraft.
Fig. 3 is a schematic view of the flange surface of the mounting bracket.
Fig. 4 is a schematic view of the structure of the adjustment disk.
Fig. 5 is an illustration of the adjustment relationship of the adjustment disk superimposed on the mounting bracket flange.
The numbering in the figures illustrates: the device comprises an aircraft body 1, a mounting bracket 2, an adjusting disc 3, an attack angle sensor 4, a probe 5, a central through hole 6, a flange plate 7, an angle vernier scale 8, a connecting circular hole 9, a connecting circular hole 10, a fixing circular hole 11, a connecting circular hole 12, a positioning circular hole 13, a fixing circular hole 14, a fan-shaped notch 15 and an angle vernier 16.
Detailed Description
Referring to the attached drawings, the installation device of the aircraft attack angle sensor provided by the application comprises an installation support 2 and an adjusting plate 3, wherein the installation support 2 is a groove support with a flange 7, the groove support is connected with an aircraft body 1, the flange 7 is connected with the adjusting plate 3 and an attack angle sensor 4, a probe 5 of the attack angle sensor 4 extends out of the aircraft body 1 through a central through hole 6 of the adjusting plate and the installation support, angle vernier scales 8 are arranged on the flange 7 of the installation support 2, and a corresponding angle vernier 16 is arranged on the adjusting plate 3.
The flange plate 7 is provided with angle vernier scales 8, and the angle vernier scales 8 are arranged at the position close to the outer edge of the flange plate 7 and are arranged in a fan shape; the adjusting disc 3 is provided with a fan-shaped notch 15 at the position corresponding to the angle vernier scale 8 of the flange, and the edge of the fan-shaped notch 15 is provided with an angle vernier 16 matched with the angle vernier scale 8 of the flange for use.
Be equipped with the connection round hole 9 of connecting adjustment disk 3 on the ring flange 7 of installing support 2, connect the fixed round hole 11 of angle of attack sensor 4, through slotted hole 10 and angle vernier scale 8 of passing through of angle of attack sensor 4 locating pin, be equipped with on the adjustment disk 3 and connect the connection slotted hole 12 that the connection round hole 9 of adjustment disk was connected with ring flange 7, the location round hole 13 that corresponds with angle of attack sensor fixed pin to and the fixed long round hole 14 that the fixed round hole 11 of angle of attack sensor corresponds and the angle vernier 16 that corresponds with ring flange angle vernier scale 8 are connected to the ring flange.
When the angle of the aircraft attack angle sensor is debugged, the adjusting disc 3 is connected with the flange 7 of the mounting bracket 2 through a first adjustable structure; 3) The attack angle sensor 4 and the adjusting disc 3 are relatively fixed through a positioning pin, so that an angle cursor 16 on the adjusting disc 3 and the attack angle sensor 4 are integrated; 4) The angle of attack sensor 4 and the adjusting disk 3 are connected with a flange 7 of the mounting bracket through a second adjustable structure, 5) the angle of attack sensor 4 is mounted on the aircraft body 1 through the mounting bracket 2 and the adjusting disk 3, and the position of an angle vernier 16 on the adjusting disk 3 relative to an angle vernier scale 8 on the flange 7 is recorded, wherein the position corresponds to the mounting angle of the angle of attack sensor 4; 6) The airplane provided with the attack angle sensor 4 is subjected to test flight, and the installation angle adjustment amount of the attack angle sensor is calculated through test flight data; 7) When the angle of attack sensor is adjusted, the angle of attack sensor 4 and the adjusting disk 3 are separated from the flange 7 of the mounting bracket, and the mounting angle of the adjusting disk 3 is adjusted through a first adjustable structure between the flange 7 and the adjusting disk 3 according to the mounting angle adjustment quantity of the angle of attack sensor; and then, carrying out trial flight, calculating the mounting angle adjustment quantity of the angle of attack sensor through trial flight data until the mounting angle adjustment quantity of the angle of attack sensor calculated through the trial flight data is within an allowable range, and adjusting the mounting angle of the angle of attack sensor by enabling the position of the angle cursor 16 on the adjusting disc 3 relative to the angle cursor scale 8 on the flange 7 to correspond to the final mounting angle of the angle of attack sensor 4.
In implementation, the adjusting disk 3 is connected with the flange 7 of the mounting bracket 2 through a first adjustable structure, the first adjustable structure is formed by matching an arc-shaped long circular hole and a fastening piece, so that the adjusting disk can rotate for a certain angle relative to the flange of the mounting bracket 2, and the arc-shaped long circular hole is a connecting hole which is arranged on the adjusting disk and used for being connected with the flange or a connecting hole which is arranged on the flange and used for being connected with the adjusting disk.
The angle of attack sensor 4 and adjusting disk 3 are connected with the flange 7 of the mounting bracket through a second adjustable structure, the second adjustable structure is formed by matching an arc-shaped long round hole and a fastener, so that the angle of attack sensor 4 can rotate for a certain angle relative to the flange 7 of the mounting bracket, and the arc-shaped long round hole is a connecting hole which is arranged on the adjusting disk and used for being connected with the angle of attack sensor, or a connecting hole which is arranged on the flange and used for being connected with the angle of attack sensor, and an arc-shaped long round hole which is arranged on the flange and passes through a positioning pin of the angle of attack sensor.
The angle vernier scale 8 on the flange plate of the mounting bracket of the attack angle sensor is matched with the angle vernier 16 on the mounting adjusting plate 3 of the attack angle sensor to realize the function of a vernier angle ruler and indicate the mounting angle of the attack angle sensor.
The angle adjusting method based on the angle of attack sensor installation device can adjust the angle of attack sensor installation with high precision, does not need to use a special installation tool, and is simple to operate, convenient and easy to operate.
Claims (8)
1. The utility model provides a method for debugging the installation angle of an aircraft angle of attack sensor, contains installing support, adjusting disk and angle of attack sensor, and the installing support is the recess support of taking the ring flange, and the recess support is connected with the aircraft organism, and the ring flange is connected with adjusting disk and angle of attack sensor, and the probe of angle of attack sensor passes through the central through-hole of adjusting disk and installing support and stretches out outside the aircraft organism, and its characterized in that contains following content: 1) Angle vernier scales are arranged on a flange plate of the mounting bracket, and a corresponding angle vernier is arranged on the adjusting plate; 2) The adjusting plate is connected with the flange plate through a first adjustable structure; 3) The angle of attack sensor and the adjusting disk are relatively fixed through a positioning pin, so that an angle cursor on the adjusting disk and the angle of attack sensor form a whole; 4) The angle of attack sensor and the adjusting plate are connected with a flange plate of the mounting bracket through a second adjustable structure, 5) the angle of attack sensor is mounted on the airplane body through the mounting bracket and the adjusting plate, and the position of an angle vernier on the adjusting plate relative to the position of an angle vernier scale on the flange plate is recorded, wherein the position corresponds to the mounting angle of the angle of attack sensor; 6) The method comprises the following steps of (1) carrying out test flight on an airplane provided with an attack angle sensor, and calculating the installation angle adjustment quantity of the attack angle sensor through test flight data; 7) Separating the attack angle sensor and the adjusting disc from the flange plate of the mounting bracket, and adjusting the mounting angle of the adjusting disc through a first adjustable structure between the flange plate and the adjusting disc according to the mounting angle adjustment amount of the attack angle sensor; 8) And repeating the step 5), the step 6) and the step 7) until the adjustment quantity of the mounting angle of the angle of attack sensor is calculated to be within the allowable range through the test flight data, wherein the position of the angle vernier on the adjusting disc relative to the angle vernier scale on the flange plate corresponds to the final mounting angle of the angle of attack sensor, and the adjustment of the mounting angle of the angle of attack sensor is realized.
2. The method for debugging the installation angle of the aircraft attack angle sensor according to claim 1, wherein the flange is provided with angle vernier scales which are arranged at the near outer edge of the flange and arranged in a fan shape; the adjusting disc is provided with a fan-shaped notch at the position corresponding to the angle vernier scale of the flange disc, and the edge of the fan-shaped notch is provided with an angle vernier matched with the angle vernier scale of the flange disc for use.
3. The aircraft angle of attack sensor installation angle debugging method of claim 1, wherein the first adjustable structure is formed by matching an arc-shaped oblong hole and a fastener, and the arc-shaped oblong hole is a connecting hole arranged on the adjusting disk and used for connecting with the flange plate or a connecting hole arranged on the flange plate and used for connecting with the adjusting disk.
4. The aircraft angle of attack sensor installation angle debugging method of claim 1, wherein the second adjustable structure is formed by matching an arc-shaped oblong hole and a fastener, and the arc-shaped oblong hole is a connecting hole arranged on the adjusting disc and used for connecting with the angle of attack sensor, or a connecting hole arranged on the flange disc and used for connecting with the angle of attack sensor, and the arc-shaped oblong hole arranged on the flange disc and used for passing through an angle of attack sensor positioning pin.
5. The aircraft attack angle sensor installation angle debugging method of claim 1, 2, 3 or 4, characterized in that the flange plate of the installation support is provided with a connecting circular hole for connecting the adjusting plate, a fixing circular hole for connecting the attack angle sensor, a through circular hole for passing through the locating pin of the attack angle sensor and an angle cursor scale, the adjusting plate is provided with a connecting circular hole corresponding to the connecting circular hole of the flange plate connecting the adjusting plate, a locating circular hole corresponding to the locating pin of the attack angle sensor, a fixing circular hole corresponding to the fixing circular hole of the flange plate connecting the attack angle sensor and an angle cursor corresponding to the angle cursor scale of the flange plate.
6. The utility model provides an aircraft angle of attack sensor's installation device, contains installing support and adjusting disk, and the installing support is the recess support of taking the ring flange, and the recess support is connected with the aircraft organism, and the ring flange is connected with adjusting disk and angle of attack sensor, and the probe of angle of attack sensor stretches out outside the aircraft organism through the central through-hole of adjusting disk and installing support, its characterized in that: the flange plate of the mounting bracket is provided with angle vernier scales, and the adjusting plate is provided with a corresponding angle vernier.
7. The mounting device for an aircraft angle of attack sensor as claimed in claim 6, wherein the flange is provided with angle vernier scales which are arranged at the near outer edge of the flange and are arranged in a fan shape; the adjusting disc is provided with a fan-shaped notch at the position corresponding to the angle vernier scale of the flange disc, and the edge of the fan-shaped notch is provided with an angle vernier matched with the angle vernier scale of the flange disc for use.
8. The mounting device for the aircraft angle of attack sensor according to claim 6 or 7, wherein the flange plate of the mounting bracket is provided with a connecting circular hole for connecting the adjusting plate, a fixing circular hole for connecting the angle of attack sensor, a through circular hole for passing through the positioning pin of the angle of attack sensor and an angle cursor scale, and the adjusting plate is provided with a connecting circular hole corresponding to the connecting circular hole of the flange plate connecting the adjusting plate, a positioning circular hole corresponding to the fixing pin of the angle of attack sensor, a fixing circular hole corresponding to the fixing circular hole of the flange plate connecting the angle of attack sensor and an angle cursor corresponding to the angle cursor scale of the flange plate.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010135742.0A CN113340264B (en) | 2020-03-02 | 2020-03-02 | Method and device for debugging installation angle of aircraft attack angle sensor |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010135742.0A CN113340264B (en) | 2020-03-02 | 2020-03-02 | Method and device for debugging installation angle of aircraft attack angle sensor |
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| Publication Number | Publication Date |
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| CN113340264A CN113340264A (en) | 2021-09-03 |
| CN113340264B true CN113340264B (en) | 2023-03-14 |
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| CN202010135742.0A Active CN113340264B (en) | 2020-03-02 | 2020-03-02 | Method and device for debugging installation angle of aircraft attack angle sensor |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2001165694A (en) * | 1999-12-10 | 2001-06-22 | Nec Corp | Attitude angle sensor calibrating device for artificial satellite |
| CN103837071A (en) * | 2014-03-20 | 2014-06-04 | 沈阳飞机工业（集团）有限公司 | Rod displacement sensor angular measurement clamp |
| CN104986355A (en) * | 2015-07-14 | 2015-10-21 | 中航飞机股份有限公司西安飞机分公司 | Giving method and giving device of aircraft incidence angle |
| CN207197491U (en) * | 2017-09-20 | 2018-04-06 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of control stick angle measurement unit |
| CN208000102U (en) * | 2018-01-24 | 2018-10-23 | 中国人民解放军第五七二一工厂 | A kind of aircraft horizontal tail degree of bias signal mechanism detection angles measuring device |
-
2020
- 2020-03-02 CN CN202010135742.0A patent/CN113340264B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2001165694A (en) * | 1999-12-10 | 2001-06-22 | Nec Corp | Attitude angle sensor calibrating device for artificial satellite |
| CN103837071A (en) * | 2014-03-20 | 2014-06-04 | 沈阳飞机工业（集团）有限公司 | Rod displacement sensor angular measurement clamp |
| CN104986355A (en) * | 2015-07-14 | 2015-10-21 | 中航飞机股份有限公司西安飞机分公司 | Giving method and giving device of aircraft incidence angle |
| CN207197491U (en) * | 2017-09-20 | 2018-04-06 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of control stick angle measurement unit |
| CN208000102U (en) * | 2018-01-24 | 2018-10-23 | 中国人民解放军第五七二一工厂 | A kind of aircraft horizontal tail degree of bias signal mechanism detection angles measuring device |
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| CN113340264A (en) | 2021-09-03 |
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