CN215728232U - Attack angle sensor calibrating device - Google Patents
Attack angle sensor calibrating device Download PDFInfo
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- CN215728232U CN215728232U CN202121845491.1U CN202121845491U CN215728232U CN 215728232 U CN215728232 U CN 215728232U CN 202121845491 U CN202121845491 U CN 202121845491U CN 215728232 U CN215728232 U CN 215728232U
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Abstract
The utility model belongs to the technical field of aircraft maintenance, and discloses an attack angle sensor calibration device which comprises a mounting plate, a base, a rotating mechanism, a locking member, a measuring member and a first positioning member, wherein the mounting plate is connected to a fuselage skin; the base is connected with the mounting plate; the rotating mechanism comprises a rotating body and a connecting arm assembly, and the base is rotatably connected with the connecting arm assembly; the locking piece is used for limiting the rotation between the base and the connecting arm assembly; the measuring piece is arranged on the rotating body and used for measuring the angle of the rotating body; the first positioning piece is used for positioning the relative position of the vane and the rotating body. According to the attack angle sensor calibration device provided by the utility model, the angle of rotation of the rotating mechanism measured by the measuring part is a deviation value between the mechanical zero position and the system zero position, and the correction of the installation position of the attack angle sensor is realized by utilizing the deviation value, so that the high-precision calibration of the mechanical zero position of the attack angle sensor is realized.
Description
Technical Field
The utility model relates to the technical field of aircraft maintenance, in particular to an attack angle sensor calibration device.
Background
The angle of attack of an aircraft is the angle between the wing chord and the relative wind speed, and is one of important atmospheric data, and a fire control system, a cruise control system and a stall warning system of the aircraft cannot depart from the angle of attack information of the aircraft. The aircraft body skin is provided with a first positioning hole and a second positioning hole, the vane is provided with a vane positioning hole, the attack angle sensor is installed behind the aircraft body skin, and when the first positioning hole, the second positioning hole and the vane positioning hole are on the same straight line, the position is defined as the system zero position of the attack angle sensor. When the airplane is defined to be in a horizontal state, the zero position of the attack angle sensor in a natural release state is defined as the mechanical zero position of the attack angle sensor. In actual operation, the zero position of the system and the zero position of the machine are deviated, so that the accuracy of the angle of attack sensor for measuring the angle of attack of the airplane is influenced, and the angle of attack sensor needs to be calibrated.
However, at present, a calibration device specially used for an attack angle sensor does not exist, the accuracy of the universal angle gauge is measured and calibrated mainly through measuring tools such as a manual rotation tool, a universal angle gauge and a bubble level gauge, the precision is poor, meanwhile, the reading needs to be estimated, the artificial influence factor is large, the reading is complicated, meanwhile, the zero setting process of the universal angle gauge is complicated, and great inconvenience is caused to the use.
SUMMERY OF THE UTILITY MODEL
The utility model aims to provide a calibration device for an attack angle sensor, which improves the measurement precision of a weathercock angle.
In order to achieve the purpose, the utility model adopts the following technical scheme:
an angle of attack sensor calibration device, comprising:
a mounting plate connected to the fuselage skin;
a base connected to the mounting plate;
the rotating mechanism comprises a rotating body and a connecting arm assembly, and the base is rotatably connected with the connecting arm assembly;
a retaining member for limiting relative rotation between the base and the arm assembly;
a measuring member provided on the rotating body, the measuring member being for measuring an angle of the rotating body;
the first positioning piece is used for positioning the relative position of the vane and the rotating body.
Preferably, the rotating body is of an L-shaped structure and comprises a transverse plate and a vertical plate, and the measuring piece and the connecting arm assembly are arranged on the transverse plate.
Preferably, the connecting arm assembly comprises two oppositely arranged connecting arms, the two connecting arms are connected to the transverse plate, and the base portion is arranged between the two connecting arms and is rotatably connected to the two connecting arms.
Preferably, two all seted up first mounting hole on the linking arm, the base has seted up the second mounting hole correspondingly, the pin passes first mounting hole with the second mounting hole.
Preferably, a bushing assembly is arranged on the inner wall attached to the first mounting hole, the pin penetrates through the bushing assembly, and the locking piece can penetrate through the connecting arm and the bushing assembly and abuts against a pin rod of the pin.
Preferably, the retaining member is a limiting pin, and the limiting pin penetrates through the base and the two connecting arms to limit the relative rotation of the base and the rotating mechanism.
Preferably, the vane is provided with a vane positioning hole, the vertical plate is provided with a through hole, and the first positioning piece penetrates through the through hole and the vane positioning hole.
Preferably, the first positioning element comprises a fixing bush and a pin rod, the fixing bush is arranged in the through hole and attached to the inner wall of the through hole, and the pin rod penetrates through the fixing bush and the vane positioning hole.
Preferably, the measuring piece is connected to the transverse plate, and the measuring piece is a digital display type angle measuring instrument.
Preferably, the fuselage skin is provided with a first positioning hole and a second positioning hole, the mounting plate is correspondingly provided with a third positioning hole and a fourth positioning hole, the second positioning element penetrates through the third positioning hole and the first positioning hole, and the third positioning element penetrates through the fourth positioning hole and the second positioning hole.
The utility model has the beneficial effects that:
according to the attack angle sensor calibration device provided by the utility model, when an airplane is in a horizontal state, the measurement component is firstly zeroed and is installed on the rotating body of the rotating mechanism, the relative position of the vane and the rotating mechanism is determined by utilizing the first positioning component, the locking component is loosened, the rotating mechanism can rotate relative to the base, so that the vane is driven by the rotating mechanism to reach the position of the zero position of the system, the angle of rotation of the rotating mechanism measured by the measurement component is a deviation value between the mechanical zero position and the zero position of the system, and the installation position of the attack angle sensor is corrected by utilizing the deviation value, so that the high-precision calibration of the mechanical zero position of the attack angle sensor is realized.
Drawings
FIG. 1 is a schematic structural view of a weathervane disposed on a fuselage skin provided by an embodiment of an angle of attack sensor calibration apparatus according to the present invention;
fig. 2 is a schematic structural diagram provided by an embodiment of the angle of attack sensor calibration apparatus according to the present invention.
In the figure:
100. a fuselage skin; 101. a first positioning hole; 102. a second positioning hole;
200. a weather vane; 201. a vane positioning hole;
1. mounting a plate; 11. a third positioning hole; 12. a fourth positioning hole; 13. an avoidance groove;
2. a base;
3. a rotation mechanism; 31. rotating the body; 311. a transverse plate; 312. a vertical plate; 32. a connecting arm assembly;
4. a locking member;
5. a first positioning member.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings and examples. It is to be understood that the specific embodiments described herein are merely illustrative of the utility model and are not limiting of the utility model. It should be further noted that, for the convenience of description, only some of the structures related to the present invention are shown in the drawings, not all of the structures.
As shown in fig. 1, a first positioning hole 101 and a second positioning hole 102 are formed in the fuselage skin 100, a vane positioning hole 201 is formed in the vane 200, and after the angle-of-attack sensor is installed on the fuselage skin 100 of the aircraft, when the first positioning hole 101, the second positioning hole 102 and the vane positioning hole 201 are aligned, the position is defined as a system zero position of the angle-of-attack sensor. When the airplane is defined to be in a horizontal state, the zero position of the attack angle sensor in a natural release state is defined as the mechanical zero position of the attack angle sensor. In actual operation, the zero position of the system and the zero position of the machine are deviated, so that the accuracy of the angle of attack sensor for measuring the angle of attack of the airplane is influenced.
In order to calibrate an attack angle sensor, the embodiment provides an attack angle sensor calibration device, which relates to the technical field of aircraft maintenance, and as shown in fig. 2, the attack angle sensor calibration device comprises a mounting plate 1, a base 2, a rotating mechanism 3, a locking member 4, a measuring member and a first positioning member 5, wherein the mounting plate 1 is connected to a fuselage skin 100; the base 2 is connected with the mounting plate 1; the rotating mechanism 3 comprises a rotating body 31 and a connecting arm assembly 32, and the base 2 is rotatably connected to the connecting arm assembly 32; the locking member 4 is used to limit the relative rotation between the base 2 and the connecting arm assembly 32; the measuring piece is arranged on the rotating body 31 and used for measuring the angle of the rotating body 31; the first positioning member 5 is used to position the vane 200 and the rotating body 31 in relative positions.
The angle of attack sensor calibrating device that this embodiment provided, when the aircraft is in the horizontality, with the zero set of measuring part earlier, and install it on rotary body 31 of rotary mechanism 3, utilize first locating piece 5 to realize the relative position's of weathercock 200 and rotary mechanism 3 definite, not hard up retaining member 4, make rotary mechanism 3 rotate for base 2, thereby make rotary mechanism 3 drive weathercock 200 reach the position of system zero-bit, thereby the measuring part measures the angle that rotary mechanism 3 rotated and is the deviation value of mechanical zero-bit and system zero-bit promptly, utilize this deviation value to realize the correction of angle of attack sensor's mounted position, thereby realize the high accuracy calibration of angle of attack sensor mechanical zero-bit.
Specifically, a first positioning hole 101 and a second positioning hole 102 are formed in the fuselage skin 100, a third positioning hole 11 and a fourth positioning hole 12 are correspondingly formed in the mounting plate 1, so that the second positioning element passes through the third positioning hole 11 and the first positioning hole 101, the third positioning element passes through the fourth positioning hole 12 and the second positioning hole 102, and the second positioning element and the third positioning element are matched with the first positioning element 5, so that the observation of a constructor is facilitated. When the first positioning element 5, the second positioning element and the third positioning element are in the same straight line, the angle of attack sensor is said to reach the zero position of the system. It should be noted that the second positioning element is a circular positioning pin, and the third positioning element is a diamond positioning pin. Specifically, the mounting plate 1 is bolted to the fuselage skin 100.
Optionally, an avoiding groove 13 is formed in the mounting plate 1, so as to avoid parts on the fuselage skin 100, and the avoiding groove 13 reduces the weight of the attack angle sensor calibration device, thereby facilitating the calibration work of constructors.
Optionally, the rotating body 31 is an L-shaped structure, the rotating body 31 includes a horizontal plate 311 and a vertical plate 312, and the measuring member and the connecting arm assembly 32 are both disposed on the horizontal plate 311. The connecting arm assembly 32 is disposed on a side of the cross plate 311 adjacent to the base 2 for pivotal connection with the base 2. The measuring member is disposed on a side of the cross plate 311 away from the connecting arm assembly 32 and is secured to the cross plate 311 by bolts. In the embodiment, the connecting arm assembly 32 and the rotating body 31 are integrally formed, so as to reduce the number of parts.
Optionally, a measuring member is connected to the cross plate 311, the measuring member being a digital display type angle measuring instrument. The digital display type angle measuring instrument can realize high-precision measurement of 200 skewness of the wind vane of the attack angle sensor, the angle measurement range is 0-360 degrees, the resolution is 0.01 degrees (0-9.99 degrees)/0.10 degrees (10-90 degrees), the angle measurement precision is +/-0.05 degrees (0-10 degrees)/+/-0.20 degrees (10-90 degrees), and the digital display type angle measuring instrument has the advantage of being convenient to disassemble and assemble. In other embodiments, another measuring member may be selected as long as it can measure the angle of rotation of the rotating body 31 of the rotating mechanism 3.
Alternatively, the connecting arm assembly 32 includes two oppositely disposed connecting arms, both of which are connected to the cross plate 311, and the base 2 is partially disposed between and rotatably connected to the two connecting arms. The base 2 is partially arranged between the two connecting arms, and the two connecting arms have a certain limiting effect on the base 2. The base 2 and the rotating mechanism 3 are rotatably connected through the base 2 and the two connecting arms.
Specifically, all seted up first mounting hole on two linking arms, base 2 corresponds has seted up the second mounting hole, and the pin passes first mounting hole and second mounting hole. Pass first mounting hole and second mounting hole through setting up the pin to realize that base 2 and two linking arms rotate to be connected.
Specifically, the inner wall of the first mounting hole is provided with a bushing assembly, the pin penetrates through the bushing assembly, and the locking piece 4 can penetrate through the connecting arm and the bushing assembly and abut against the pin rod of the pin. The bushing assembly comprises a copper sleeve and a threaded bushing sleeved on the copper sleeve, and the copper sleeve is directly abutted to the outer wall of the pin penetrating through the first mounting hole. Set up the bush subassembly in first mounting hole, thereby prevent that the pin is not hard up in first mounting hole and take place to rock. Pass linking arm, screw bush, copper sheathing from supreme in proper order down with retaining member 4 to the butt is in the pin pole of pin, thereby the rotation of restriction pin, thereby restriction rotary mechanism 3 is for the rotation of base 2. When the locking member 4 is moved away from the pin, the pin can be rotated, i.e. the rotation mechanism 3 is rotated relative to the base 2.
Alternatively, in other embodiments, the locking member 4 is a limiting pin, and the limiting pin passes through the base 2 and the two connecting arms to limit the relative rotation of the base 2 and the rotating mechanism 3. When the limit pin is pulled out, the rotating mechanism 3 can rotate relative to the base 2.
Optionally, the vane 200 is provided with a vane positioning hole 201, the vertical plate 312 is provided with a through hole, and the first positioning member 5 penetrates through the through hole and the vane positioning hole 201. When the calibration work is carried out, the first positioning piece 5 penetrates through the through hole and the vane positioning hole 201 on the vane 200, so that the rotation mechanism 3 and the vane 200 are positioned. When the first positioning element 5, the second positioning element and the third positioning element are in the same line, it means that the zero position of the system of the angle of attack sensor is reached
In this embodiment, the first positioning element 5 includes a fixing bushing and a pin, the fixing bushing is disposed in the through hole and attached to the inner wall of the through hole, and the pin passes through the fixing bushing and the wind positioning hole 201. And a fixed bushing is arranged in the through hole to limit the pin rod from shaking in the through hole, so that the pin rod passes through the fixed bushing and the vane positioning hole 201, the vane 200 and the vertical plate 312 are positioned, and the subsequent calibration work of the attack angle sensor is facilitated.
The embodiment provides the use steps of the angle of attack sensor calibration device:
when the aircraft is in a horizontal state, the mounting plate 1 is fixed on the fuselage skin 100, and then the measuring part is zeroed and mounted on the transverse plate 311 of the rotating body 31;
then, the pin rod of the first positioning piece 5 passes through the through hole and the vane positioning hole 201 on the vane 200;
secondly, the locking member 4 is far away from the pin, and the wind vane 200 is rotated to enable the first positioning member 5, the second positioning member and the third positioning member to be on the same straight line and reach the zero position of the system;
and finally, reading an angle value displayed on the measuring part, wherein the angle value is a deviation value of the system zero position and the mechanical zero position, and adjusting the installation position of the attack angle sensor according to the deviation value.
The embodiment also provides a deflection measuring method of the attack angle sensor, which comprises the following steps:
when the aircraft is in any state, the mounting plate 1 is fixed on the fuselage skin 100, and the measuring piece is arranged on the transverse plate 311 of the rotating body 31;
firstly, enabling the first positioning piece 5, the second positioning piece and the third positioning piece to be on the same straight line, and reaching a system zero position to perform zero setting on the measuring piece;
and then the locking piece 4 is far away from the pin, the rotating mechanism 3 is rotated to drive the vane 200 to rotate, and the angle value displayed by the measuring piece is read, so that the deflection of the attack angle sensor is obtained.
In the description of the present embodiments, unless expressly stated or limited otherwise, the terms "connected," "connected," and "fixed" are to be construed broadly, e.g., as meaning permanently connected, removably connected, or integral to one another; can be mechanically or electrically connected; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
In this embodiment, unless expressly stated or limited otherwise, the first feature "on" or "under" the second feature may comprise direct contact of the first and second features, or may comprise contact of the first and second features not directly but through another feature in between. Also, the first feature being "on," "above" and "over" the second feature includes the first feature being directly on and obliquely above the second feature, or merely indicating that the first feature is at a higher level than the second feature. A first feature being "under," "below," and "beneath" a second feature includes the first feature being directly under and obliquely below the second feature, or simply meaning that the first feature is at a lesser elevation than the second feature.
In the description of the present embodiment, the terms "upper", "lower", "right", and the like are used in the orientation or positional relationship shown in the drawings only for convenience of description and simplicity of operation, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus should not be construed as limiting the present invention. Furthermore, the terms "first" and "second" are used only for descriptive purposes and are not intended to have a special meaning.
It should be understood that the above-described embodiments of the present invention are merely examples for clearly illustrating the present invention, and are not intended to limit the embodiments of the present invention. Numerous obvious variations, adaptations and substitutions will occur to those skilled in the art without departing from the scope of the utility model. And are neither required nor exhaustive of all embodiments. Any modification, equivalent replacement, and improvement made within the spirit and principle of the present invention should be included in the protection scope of the claims of the present invention.
Claims (10)
1. An angle of attack sensor calibration device, comprising:
a mounting plate (1), the mounting plate (1) being connected to a fuselage skin (100);
a base (2), the base (2) being connected to the mounting plate (1);
the rotary mechanism (3), the rotary mechanism (3) comprises a rotary body (31) and a connecting arm assembly (32), and the base (2) is rotatably connected to the connecting arm assembly (32);
a retaining member (4), the retaining member (4) for limiting relative rotation between the base (2) and the arm assembly (32);
a measuring member provided on the rotating body (31) for measuring an angle of the rotating body;
a first locator (5), the first locator (5) being for locating a relative position of a vane (200) and the rotating body.
2. The angle of attack sensor calibration device according to claim 1, characterized in that the rotating body (31) is an L-shaped structure, the rotating body (31) comprising a transverse plate (311) and a vertical plate (312), the measuring member and the connecting arm assembly (32) being both arranged on the transverse plate (311).
3. The angle of attack sensor calibration device according to claim 2, characterized in that the connecting arm assembly (32) comprises two oppositely arranged connecting arms, both of which are connected to the cross plate (311), the base (2) being partly arranged between and rotatably connected to both of the connecting arms.
4. The angle of attack sensor calibration device according to claim 3, wherein a first mounting hole is formed on each of the two connecting arms, a second mounting hole is correspondingly formed on the base (2), and a pin is inserted through the first mounting hole and the second mounting hole.
5. The angle of attack sensor calibration device according to claim 4, characterized in that a bushing assembly is provided against the inner wall of the first mounting hole, the pin passes through the bushing assembly, and the locking member (4) can pass through the connecting arm and the bushing assembly and abut against the pin shaft of the pin.
6. The angle of attack sensor calibration device according to claim 3, characterized in that the locking member (4) is a stop pin that passes through the base (2) and the two connecting arms to limit the relative rotation of the base (2) and the rotation mechanism (3).
7. The angle of attack sensor calibration device according to claim 2, wherein the vane (200) has a vane positioning hole (201) formed therein, the riser (312) has a through hole formed therein, and the first positioning member (5) passes through the through hole and the vane positioning hole (201).
8. The angle of attack sensor calibration device according to claim 7, wherein the first positioning member (5) comprises a fixing bushing disposed within the through hole and abutting against an inner wall of the through hole, and a pin passing through the fixing bushing and the vane positioning hole (201).
9. The angle of attack sensor calibration device according to claim 2, characterized in that the measuring member is connected to the cross plate (311), the measuring member being a digital display angle gauge.
10. The angle of attack sensor calibration device according to claim 1, wherein the fuselage skin (100) is provided with a first positioning hole (101) and a second positioning hole (102), the mounting plate (1) is correspondingly provided with a third positioning hole (11) and a fourth positioning hole (12), the second positioning element passes through the third positioning hole (11) and the first positioning hole (101), and the third positioning element passes through the fourth positioning hole (12) and the second positioning hole (102).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121845491.1U CN215728232U (en) | 2021-08-09 | 2021-08-09 | Attack angle sensor calibrating device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202121845491.1U CN215728232U (en) | 2021-08-09 | 2021-08-09 | Attack angle sensor calibrating device |
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| Publication Number | Publication Date |
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| CN215728232U true CN215728232U (en) | 2022-02-01 |
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| CN202121845491.1U Active CN215728232U (en) | 2021-08-09 | 2021-08-09 | Attack angle sensor calibrating device |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116605416A (en) * | 2023-07-17 | 2023-08-18 | 四川腾盾科技有限公司 | Automatic inclinator calibration equipment and calibration method |
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2021
- 2021-08-09 CN CN202121845491.1U patent/CN215728232U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116605416A (en) * | 2023-07-17 | 2023-08-18 | 四川腾盾科技有限公司 | Automatic inclinator calibration equipment and calibration method |
| CN116605416B (en) * | 2023-07-17 | 2023-10-24 | 四川腾盾科技有限公司 | Automatic inclinator calibration equipment and calibration method |
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