CN216694875U - Assembled aviation power supply's flatness detection device - Google Patents
Assembled aviation power supply's flatness detection device Download PDFInfo
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- CN216694875U CN216694875U CN202220356410.XU CN202220356410U CN216694875U CN 216694875 U CN216694875 U CN 216694875U CN 202220356410 U CN202220356410 U CN 202220356410U CN 216694875 U CN216694875 U CN 216694875U
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Abstract
The utility model relates to the technical field of detection equipment, in particular to a flatness detection device of an assembled aviation power supply, wherein a transmission device is arranged on a table top of a workbench, a detection mechanism is hung above the center of the transmission device, a display is arranged on the edge of the table top of the workbench, and a control mechanism is arranged below the workbench; the transmission device comprises a threaded screw rod and an object stage which are driven by a servo motor; the detection mechanism comprises a line scanning type laser sensor and two point laser ranging sensors; the control mechanism comprises a control box, an industrial personal computer provided with a motion control card and a servo driver. The utility model has the beneficial effects that: the flatness detection device provided by the utility model has a simple structure, utilizes the high-precision non-contact laser displacement sensor, and the sensor is static in position, thereby effectively reducing errors in the detection process, greatly improving the accuracy of the detection process and meeting the requirement of high-precision detection of the flatness of the power supply of the spacecraft.
Description
Technical Field
The utility model relates to the technical field of detection equipment, in particular to a flatness detection device of an assembled aviation power supply.
Background
The aviation power supply as a secondary power source of the aircraft is an important functional system of the aircraft, which is always regarded by aircraft designers and use departments. At present, in the field of aircraft power supply equipment, along with the improvement of aircraft performance, the requirements on the power supply equipment are more and more strict, and a power supply system is required to be small in size, light in weight, high in efficiency and long in service life. The planar deformation degree directly influences the quality of products, and in order to guarantee its heat dispersion, aviation power supply requires for a high level to the installation face flatness, and installation face flatness needs to be less than or equal to 0.02 mm. Therefore, the flatness detection is an important link in the high-quality plane processing process.
However, the prior art still has the problem that mechanical errors can be generated by the motion of the guide rail in the detection process, so that the flatness detection precision is influenced.
Therefore, the flatness detection device of the assembled aviation power supply is designed to solve the problems.
Disclosure of Invention
The utility model provides a flatness detection device of an assembled aviation power supply, aiming at making up for the defects in the prior art.
The utility model provides an assembled aviation power flatness detecting device, includes the workstation, its characterized in that:
a transmission device is mounted on the table top of the workbench, a detection mechanism is suspended above the center of the transmission device, a display is mounted on the edge of the table top of the workbench, and a control mechanism is mounted below the workbench;
the transmission device comprises a threaded screw rod and an object stage which are driven by a servo motor;
the detection mechanism comprises a line scanning type laser sensor and two point laser ranging sensors;
the control mechanism comprises a control box, an industrial personal computer provided with a motion control card and a servo driver.
Furthermore, in order to better realize the utility model, the transmission device is electrically connected with the control mechanism, a threaded screw of the transmission device is flatly placed on the workbench, the threaded screw is movably connected with an objective table from left to right, a clamp is arranged on the objective table, and an aviation power supply is placed on the objective table through the clamp.
Further, in order to better realize the utility model, the detection mechanism is fixed at the center above the workbench, the line scanning type laser sensor and the two point laser ranging sensors are fixedly arranged below the suspended plate, and the plate is parallel to the transmission device and keeps static.
Furthermore, in order to better realize the utility model, the display is electrically connected with the control mechanism and displays the data transmitted by the industrial personal computer.
Further, in order to better realize the utility model, the industrial personal computer receives and processes data sent by the line scanning type laser sensor and the point laser ranging sensor, and judges whether the flatness of the mounting surface of the aviation power supply on the objective table is qualified.
The utility model has the beneficial effects that:
the flatness detection device provided by the utility model has a simple structure, utilizes the high-precision non-contact laser displacement sensor, and the sensor is static in position, thereby effectively reducing errors in the detection process, greatly improving the accuracy of the detection process and meeting the requirement of high-precision detection of the flatness of the power supply of the spacecraft.
Drawings
FIG. 1 is a schematic perspective view of the present invention;
FIG. 2 is a partial schematic view of the transmission and detection mechanism of the present invention;
FIG. 3 is a schematic side view of the present invention.
In the figure, the position of the first and second end faces,
1. the device comprises a workbench, 2, a transmission device, 3, a detection mechanism, 4, a display, 5, a control mechanism, 6, a servo motor, 7, a threaded screw, 8, an objective table, 9, a line scanning type laser sensor, 10, a point laser ranging sensor, 11, a control box, 12, an industrial personal computer, 13, a servo driver, 14 and a fixture.
Detailed Description
The technical solution in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. It is to be understood that the described embodiments are merely a few embodiments of the utility model, and not all embodiments. The components of embodiments of the present invention generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations.
Thus, the following detailed description of the embodiments of the present invention, presented in the figures, is not intended to limit the scope of the utility model, as claimed, but is merely representative of selected embodiments of the utility model. All other embodiments, which can be derived by a person skilled in the art from the embodiments of the present invention without making any creative effort, shall fall within the protection scope of the present invention.
It should be noted that: like reference numbers and letters refer to like items in the following figures, and thus, once an item is defined in one figure, it need not be further defined and explained in subsequent figures.
In the description of the present invention, it should be noted that the terms "middle", "upper", "lower", "horizontal", "inner", "outer", and the like indicate orientations or positional relationships based on orientations or positional relationships shown in the drawings or orientations or positional relationships conventionally laid out when products of the present invention are used, and are only used for convenience in describing the present invention and simplifying the description, but 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," "second," and the like are used merely to distinguish one description from another, and are not to be construed as indicating or implying relative importance.
Furthermore, the terms "horizontal", "vertical" and the like do not imply that the components are required to be absolutely horizontal or pendant, but rather may be slightly inclined. For example, "horizontal" merely means that the direction is more horizontal than "vertical" and does not mean that the structure must be perfectly horizontal, but may be slightly inclined.
In the description of the present invention, it should be noted that the terms "disposed," "connected," and "connected" are to be construed broadly and may be, for example, fixedly connected, detachably connected, or integrally connected unless otherwise explicitly stated or limited. Either mechanically or electrically. They may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
Some embodiments of the utility model are described in detail below with reference to the accompanying drawings. The embodiments described below and the features of the embodiments can be combined with each other without conflict.
Fig. 1-3 show an assembled aviation power flatness detecting device of the present invention, which can be used to detect the flatness of an aviation power installation surface, and includes a workbench 1, a transmission device 2, a detecting mechanism 3, a display 4 and a control mechanism 5. The transmission device is arranged on the working table and consists of a servo motor 6, a threaded screw 7 and an object stage 8, and the threaded screw 7 is driven by the servo motor to further drive the object stage 8 to move left and right. The detection mechanism 3 is fixed above the workbench in parallel and consists of a line scanning type laser sensor 9 and two point laser distance sensors 10 which are arranged in a straight line. The control mechanism 5 is arranged below the working table and specifically comprises a control box 11, an industrial personal computer 12 with a motion control card and a servo driver 13. In the detection process, a power supply to be detected is placed upwards, a clamping device 14 is arranged to clamp the power supply, and the power supply is dragged by an objective table 8 to move stably from left to right. And the line scanning type laser sensor scans the flatness data of the surface to be detected of the power supply. The two point laser ranging sensors measure vertical displacement runout of two edge sides of the objective table.
In this embodiment, the sensor is a line scanning laser sensor and a point laser ranging sensor. And the line scanning type laser sensor scans the flatness data of the surface to be detected of the power supply. The two point laser ranging sensors measure vertical displacement runout of two edge sides of the objective table. The length of the surface to be measured of the workpiece is about 300mm, the linear guide rail carries out laser ranging once when running for 30mm, and the flatness error is evaluated by a least square method. Assume a total of 20 points measured on the stage, designated as P1, P2.. P20, respectively. The first point measured on the stage was taken as the reference point and was designated as point P1. Converting the plane by taking the horizontal plane passing through the starting point A as a reference by using a formula
Conversion of the base level height value Zij. Then, the regression value Z of the evaluation criterion is calculated according to a plane equationij'. 20 points (X) can be measuredi,Yi,Z'ij) Has a flatness error of fij＝Zij-Z'ij. The sum of the absolute values of the maximum positive and negative errors of each measuring point on the measured object carrying table relative to the evaluation benchmark is taken as the plane error of the whole object carrying table and is recorded as f1＝fmax-fmin. The same principle can be used for obtaining the integral plane error f of the power supply to-be-detected surface2，f＝|f2-f1And | is the flatness error. The data collected by the sensors are sent to the control mechanism, and the industrial personal computer receives and processes the data sent by the sensors, performs the operation, judges whether the flatness of the workpiece mounting surface is qualified or not and displays the flatness by the display.
Finally, the above embodiments are only used for illustrating the technical solutions of the present invention and not for limiting, and other modifications or equivalent substitutions made by the technical solutions of the present invention by those of ordinary skill in the art should be covered within the scope of the claims of the present invention as long as they do not depart from the spirit and scope of the technical solutions of the present invention.
Claims (5)
1. The utility model provides an assembled aviation power supply's flatness detection device, includes workstation (1), its characterized in that:
a transmission device (2) is mounted on the table top of the workbench (1), a detection mechanism (3) is suspended above the center of the transmission device (2), a display (4) is mounted on the edge of the table top of the workbench (1), and a control mechanism (5) is mounted below the workbench (1);
the transmission device (2) comprises a threaded screw (7) and an object stage (8) which are driven by a servo motor (6);
the detection mechanism (3) comprises a line scanning type laser sensor (9) and two point laser ranging sensors (10);
the control mechanism (5) comprises a control box (11), an industrial personal computer (12) provided with a motion control card and a servo driver (13).
2. The flatness detecting apparatus of an assembled aviation power supply according to claim 1, wherein:
drive arrangement (2) electricity connection control mechanism (5), threaded screw (7) of drive arrangement (2) are kept flat on workstation (1), and swing joint has objective table (8) about threaded screw (7), installs fixture (14) on objective table (8), places aviation power through fixture (14) on objective table (8).
3. The flatness detecting apparatus of an assembled aviation power supply according to claim 1, wherein:
the detection mechanism (3) is fixed at the center above the workbench (1), the line scanning type laser sensor (9) and the two point laser ranging sensors (10) are fixedly arranged below the suspended plate, and the plate is parallel to the transmission device (2) and keeps static.
4. The flatness detecting apparatus of an assembled aviation power supply according to claim 1, wherein:
the display (4) is electrically connected with the control mechanism (5) and displays data transmitted by the industrial personal computer (12).
5. The flatness detecting apparatus of an assembled aviation power supply according to claim 1, wherein:
the industrial personal computer (12) receives and processes data sent by the line scanning type laser sensor (9) and the point laser ranging sensor (10), and judges whether the flatness of the mounting surface of the aviation power supply on the objective table (8) is qualified.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202220356410.XU CN216694875U (en) | 2022-02-22 | 2022-02-22 | Assembled aviation power supply's flatness detection device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202220356410.XU CN216694875U (en) | 2022-02-22 | 2022-02-22 | Assembled aviation power supply's flatness detection device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN216694875U true CN216694875U (en) | 2022-06-07 |
Family
ID=81828378
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202220356410.XU Active CN216694875U (en) | 2022-02-22 | 2022-02-22 | Assembled aviation power supply's flatness detection device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN216694875U (en) |
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2022
- 2022-02-22 CN CN202220356410.XU patent/CN216694875U/en active Active
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