CN218330429U - Aircraft control surface weight gravity center measuring device - Google Patents
Aircraft control surface weight gravity center measuring device Download PDFInfo
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- CN218330429U CN218330429U CN202222687751.8U CN202222687751U CN218330429U CN 218330429 U CN218330429 U CN 218330429U CN 202222687751 U CN202222687751 U CN 202222687751U CN 218330429 U CN218330429 U CN 218330429U
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Abstract
The application provides an aircraft control surface weight focus survey device includes: the three adjustable supporting devices are arranged in a form of three fixed points of a right triangle to support the control surface; each weighing sensor is arranged at the top of the adjustable supporting device and is positioned between the control surface and the adjustable supporting device, and the measurement of the gravity at the supporting point of the adjustable supporting device is realized through the weighing sensors; the first track is positioned on a right-angle side formed by one of the two adjustable supporting devices, the third track is positioned on the other right-angle side formed by the two adjustable supporting devices, and the second track is parallel to the first track; and the data processing device is connected with the three weighing sensors and calculates the weight and the gravity center of the control surface according to the measured values of the three weighing sensors. The device can be used for conveniently measuring and calibrating the weight and the gravity center of the control surface of the airplane.
Description
Technical Field
The application belongs to the technical field of aircraft structure measurement, and particularly relates to a device for measuring weight and gravity center of an aircraft control surface.
Background
Generally, after the aircraft control surface structure is assembled, the weight and the gravity center need to be measured so as to calculate the rotational inertia of the control surface and record the factory state. The general airplane control surface gravity center measurement adopts a suspension method, namely, an end point of a control surface is randomly selected and is suspended by a rope, after the control surface is static, a vertical line is drawn on the control surface along the direction of a suspension line through a suspension point, then a point is found outside the vertical line for suspension, and the intersection point of the two vertical lines is the gravity center of the control surface.
The hanging method is simple to operate, but because the control surface of the airplane is a curved surface and has a large size, the operation is inconvenient during manual line drawing, and large errors are easy to cause; in addition, the control surface is not stable enough when being hoisted by one point, so that the control surface is easy to scratch, and potential safety hazards exist.
Disclosure of Invention
It is an object of the present application to provide an aircraft control surface weight centroid determining apparatus that solves or mitigates at least one of the problems of the background art.
The technical scheme of the application is as follows: an aircraft control surface weight centroid determining apparatus, said apparatus comprising:
the three adjustable supporting devices are arranged in a form of three fixed points of a right-angled triangle to support the control surface;
each weighing sensor is arranged at the top of the adjustable supporting device and is positioned between the control surface and the adjustable supporting device, and the measurement of the gravity at the supporting point of the adjustable supporting device is realized through the weighing sensors;
the first track is positioned on a right-angle side formed by two adjustable supporting devices, the third track is positioned on the other right-angle side formed by the two adjustable supporting devices, and the second track is parallel to the first track;
and the data processing device is connected with the three weighing sensors and calculates the weight and the gravity center of the control surface according to the measured values of the three weighing sensors.
Further, the adjustable supporting device is a jack.
Further, the positions of the three adjustable supporting devices in the right triangle layout can enable the gravity center of the control surface to be located in the right triangle.
Further, the laser positioner of the first track points to the second track, and the laser positioner of the second track points to the control surface.
Further, the distance between the laser positioner of the first track and the right-angle fixed point is an abscissa value of the gravity center of the control surface, and the ordinate values of the laser positioner of the first track and the laser positioner of the second track from the gravity center of the control surface.
The utility model provides an aircraft control surface weight focus survey device has increased the control surface and has laid stability and check weighing accuracy through the right angled triangle mode through adopting three point support cooperation weighing sensor to measure control surface weight jointly, arranges with the right angle summit as the initial point, and control surface focus calculation process is simple, can comparatively accurate obtain the focus coordinate of control surface fast through the computational formula. The measuring device is simple to operate, convenient to maintain and overhaul, low in cost and safe to operate, and calibration errors caused by manual measurement and scribing in a suspension method are effectively reduced.
Drawings
In order to more clearly illustrate the technical solutions provided in the present application, the drawings will be briefly described below. It is to be understood that the drawings described below are merely exemplary of some embodiments of the application.
Fig. 1 is a schematic view of an aircraft control surface weight center of gravity measuring device according to the present application.
Fig. 2 is a schematic diagram of the positions of the adjustable supporting device and the load cell in the present application.
Detailed Description
In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application.
In order to solve the problems of inconvenient operation, large error, poor safety and the like caused by methods such as a suspension method and the like adopted during the measurement of the weight center of gravity of the control surface of the airplane, the application provides the device for measuring the weight center of gravity of the control surface of the airplane, which can carry out precise measurement and is simple and easy to implement.
As shown in fig. 1, the present application provides an aircraft weight center of gravity measuring device comprising: three adjustable support means 1, three load cells 2 and a first rail 31 with laser locators, a second rail 32 with laser locators, a third rail 33 without laser locators and a data processing device (not shown).
The three adjustable supporting devices 1 are arranged in the form of three fixed points of a right triangle to support the control surface 4, so that the stability of the control surface is ensured. The gravity center position of the control surface 4 can be positioned in the triangle as much as possible by the layout form of the right triangle, so that the measurement accuracy is improved, and the measurement of a gravity center position coordinate system is facilitated.
In an embodiment of the present application, the adjustable supporting device 1 may be implemented by using a jack, which can improve a large supporting force while achieving height adjustment.
As shown in fig. 2, a weighing sensor 2 is arranged at the top of each adjustable supporting device 1, the weighing sensor 2 is located between the control surface 4 and the adjustable supporting device 1, and the weighing sensor 2 is used for measuring the gravity at the supporting point of the adjustable supporting device 1, so as to accurately calculate the total weight of the control surface 4.
The first track 31 is located at one of the legs, the third track 33 is located at the other leg, and the second track 32 is arranged parallel to the first track 31.
The data processing device is connected with the three weighing sensors 2, and the gravity center coordinates of the control surface are calculated according to the measuring results of the weighing sensors 2.
During measurement, a control surface 4 is lifted and placed on three adjustable supporting devices 1 with weighing sensors 2 at the tops, the three adjustable supporting devices 1 are placed in a right-angled triangle layout mode, the height of each adjustable supporting device 1 is adjusted to enable the control surface 4 to be kept in a horizontal state, the three weighing sensors 2 convert received loads into resistors, the control surface loads received at three points are calculated according to the resistors, the control surface loads at the three points are multiplied by gravity acceleration to obtain the weight sizes G1, G2 and G3 at the three points, and finally the total weight G = G1+ G2+ G3 of the control surface can be obtained.
After the three adjustable supporting devices 1 are arranged according to a right triangle, the distances between the three supporting points are respectively measured by using a tape measure and are respectively recorded as L1, L2 and L3, wherein the L1 and the L2 are right-angle sides. The first track 31 and the third track 33 are respectively arranged on the two right-angle sides L1 and L2, the second track 32 is placed to be close to the third track 33, and meanwhile, a right-angle ruler is used for ensuring that the second track 32 is parallel to the first track 31 so as to accurately calibrate the gravity center position. Establishing a rectangular coordinate system with three adjustable supporting devices 1 as triangular vertexes, taking a second supporting point as an origin (rectangular vertex), and calculating a formula according to the gravity center: lx = L2 × G3/(G1 + G2+ G3), ly = L1 × G1/(G1 + G2+ G3), and the data processing module calculates the control surface barycentric coordinates (Lx, ly).
According to the calculated barycentric coordinates (Lx, ly) of the control surface, the laser locators on the first track 31 and the second track 32 are respectively moved, the distance from the laser locator on the first track 31 to a right-angle fixed point is Lx, the laser locator on the first track 31 points to the second track 32, the distance from the second track 32 to the first track 31 is Ly, the laser locator on the second track 32 is moved to the position pointed by the laser locator on the first track 31, the laser locator on the second track 32 emits laser in the direction of the control surface, the point where the laser locator strikes the control surface is the barycenter of the control surface, and therefore calibration of the barycenter of the control surface is completed.
The utility model provides an aircraft control surface weight focus survey device has increased the control surface and has laid stability and check weighing accuracy through the right angled triangle mode through adopting three point support cooperation weighing sensor to measure control surface weight jointly, arranges with the right angle summit as the initial point, and control surface focus calculation process is simple, can comparatively accurate obtain the focus coordinate of control surface fast through the computational formula. The measuring device is simple to operate, convenient to maintain and overhaul, low in cost and safe to operate, and calibration errors caused by manual measurement and scribing in a suspension method are effectively reduced.
The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.
Claims (5)
1. An aircraft control surface weight centroid measurement apparatus, said apparatus comprising:
the three adjustable supporting devices (1) are arranged according to the form of three fixed points of a right triangle to support the control surface (4);
the device comprises three weighing sensors (2), wherein each weighing sensor (2) is arranged at the top of an adjustable supporting device (1) and is positioned between a control surface (4) and the adjustable supporting device (1), and the gravity of the supporting point of the adjustable supporting device (1) is measured through the weighing sensors (2);
a first track (31) and a second track (32) with laser locators and a third track (33) without laser locators, wherein the first track (31) is positioned on one right-angle side formed by the two adjustable supporting devices (1), the third track (33) is positioned on the other right-angle side formed by the two adjustable supporting devices (1), and the second track (32) is parallel to the first track (31);
and the data processing device is connected with the three weighing sensors (2), and the weight and the gravity center of the control surface (4) are calculated according to the measured values of the three weighing sensors (2).
2. Aircraft control surface weight centre of gravity determination device according to claim 1, characterized in that the adjustable support means (1) is a jack.
3. Aircraft control surface weight centre of gravity determination device according to claim 1, characterized in that the three adjustable support means (1) in the right triangle layout are positioned such that the control surface centre of gravity is located within the right triangle.
4. Aircraft control surface weight centre of gravity determination device according to claim 1, characterized in that the laser locator of the first rail (31) is directed to the second rail (32) and the laser locator of the second rail (32) is directed to the control surface (4).
5. The device for determining the center of gravity of the control surface of an aircraft according to claim 4, wherein the distance between the laser locator of the first track (31) and the orthogonal fixed point is an abscissa value of the center of gravity of the control surface, and the distance between the laser locator of the first track (31) and the laser locator of the second track (32) is an ordinate value of the center of gravity of the control surface.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222687751.8U CN218330429U (en) | 2022-10-12 | 2022-10-12 | Aircraft control surface weight gravity center measuring device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202222687751.8U CN218330429U (en) | 2022-10-12 | 2022-10-12 | Aircraft control surface weight gravity center measuring device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN218330429U true CN218330429U (en) | 2023-01-17 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202222687751.8U Active CN218330429U (en) | 2022-10-12 | 2022-10-12 | Aircraft control surface weight gravity center measuring device |
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| Country | Link |
|---|---|
| CN (1) | CN218330429U (en) |
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2022
- 2022-10-12 CN CN202222687751.8U patent/CN218330429U/en active Active
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