CN213515967U - Mass and mass center measuring device - Google Patents
Mass and mass center measuring device Download PDFInfo
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- CN213515967U CN213515967U CN202022609656.7U CN202022609656U CN213515967U CN 213515967 U CN213515967 U CN 213515967U CN 202022609656 U CN202022609656 U CN 202022609656U CN 213515967 U CN213515967 U CN 213515967U
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Abstract
The utility model discloses a quality barycenter measuring device relates to the aeronautical technical field, and its technical scheme main points are: the device comprises a front support frame, a rear support plate, a first measuring mechanism, a second measuring mechanism, a third measuring mechanism, a front lifting support plate, a left main lifting support plate, a right main lifting support plate, a front lifting guide rail, a main lifting guide rail and a distance measuring and positioning mechanism; the front lifting guide rail is arranged on the front supporting frame; the first measuring mechanism is arranged on the front lifting guide rail and is in sliding connection with the front lifting guide rail; the front lifting supporting plate is arranged at the top end of the first measuring mechanism; the rear supporting plate is connected with the top ends of the second measuring mechanism and the third measuring mechanism; the main lifting guide rail is fixedly arranged on the top surface of the rear supporting plate; the left main lifting support plate and the right main lifting support plate are arranged on the main lifting guide rail, and the left main lifting support plate and the right main lifting support plate are connected with the main lifting guide rail in a sliding mode. The device simple structure, reliable, measuring range is wide, and measurement accuracy is high, and convenient dismantlement installation, and can measure the quality of being surveyed the aircraft simultaneously, the barycenter of X direction and the barycenter of Y direction.
Description
Technical Field
The utility model relates to an aeronautical technical field, more specifically say, it relates to a quality barycenter measuring device.
Background
The quality characteristic parameters comprise parameters such as mass, mass center, rotational inertia and the like, and are important parameters in the overall design, orbit control and attitude control of the aircraft. With the continuous and deep design work of the aircraft, the rationality of the design of the quality characteristics and the accuracy of the calculation and measurement of the quality characteristics are key factors influencing the overall design of the aircraft. Therefore, based on the reasons, the design of a set of high-precision mass and mass center measuring device has profound significance for improving the flight performance of the aircraft and improving the control precision.
At present, a mass and mass center measuring device in the prior art is inconvenient to disassemble and complex in structure, can only be used in a fixed place, cannot meet the test requirement of outfield maneuvering, and is narrow in measuring range. Therefore, the utility model aims at designing a quality barycenter measuring device to solve above-mentioned problem.
SUMMERY OF THE UTILITY MODEL
The utility model aims at providing a quality barycenter measuring device, the device simple structure, reliable, measuring range is wide, and measurement accuracy is high, and convenient dismantlement and installation, and the barycenter that can simultaneous measurement surveyed aircraft's quality, X direction and the barycenter of Y direction.
The above technical purpose of the present invention can be achieved by the following technical solutions: a mass center of mass measuring device comprises a front support frame, a rear support plate, a measuring mechanism I, a measuring mechanism II, a measuring mechanism III, a front lifting support plate, a left main lifting support plate, a right main lifting support plate, a front lifting guide rail, a main lifting guide rail and a distance measuring and positioning mechanism;
the front lifting guide rail is fixedly arranged on the top surface of the front support frame; the first measuring mechanism is arranged on the front lifting guide rail and is in sliding connection with the front lifting guide rail; the front lifting supporting plate is fixedly arranged at the top end of the first measuring mechanism;
the rear supporting plate is fixedly connected with the top ends of the second measuring mechanism and the third measuring mechanism; the main lifting guide rail is fixedly arranged on the top surface of the rear supporting plate; the left main lifting support plate and the right main lifting support plate are arranged on the main lifting guide rail and are in sliding connection with the main lifting guide rail;
two ends of one end part of the front support frame are respectively connected with the bottom ends of the second measuring mechanism and the third measuring mechanism; and the distance measuring and positioning mechanism is fixedly arranged at the end part of the front support frame far away from the rear support plate.
By adopting the technical scheme, when in use, the tested aircraft is lifted on the measuring device, and the three undercarriage wheels of the tested aircraft can be conveniently supported through the front lifting support plate, the left main lifting support plate and the right main lifting support plate, so that the tested aircraft is fixed on the measuring device, and the operation of measuring the tested aircraft is convenient; the front support frame is convenient for mounting and supporting the first measuring mechanism; the rear supporting plate is convenient for mounting the second measuring mechanism and the third measuring mechanism and supporting the main lifting guide rail; the measuring mechanism can slide on the top surface of the front support frame through the front lifting guide rail, so that the position of the first measuring mechanism can be conveniently adjusted; the left main lifting support plate and the right main lifting support plate can slide on the top surface of the rear support plate through the main lifting guide rail, so that the positions of the left main lifting support plate and the right main lifting support plate can be conveniently adjusted; the pressure applied to the first measuring mechanism, the second measuring mechanism and the third measuring mechanism by the three undercarriage wheels of the measured aircraft is conveniently measured by the first measuring mechanism, the second measuring mechanism and the third measuring mechanism, so that the mass of the measured aircraft is conveniently calculated according to the data measured by the first measuring mechanism, the second measuring mechanism and the third measuring mechanism; the distance of the measuring mechanism I on the front supporting frame can be conveniently measured through the distance measuring and positioning mechanism; and the mass of the tested aircraft, the mass center in the X direction and the mass center in the Y direction can be conveniently calculated by combining the data measured by the first measuring mechanism, the second measuring mechanism, the third measuring mechanism and the ranging and positioning mechanism.
The utility model discloses further set up to: and the centers of the second measuring mechanism and the third measuring mechanism and the rear supporting plate are symmetrical points and are arranged at the bottom ends of the rear supporting plates in a bilateral symmetry manner.
By adopting the technical scheme, the second measuring mechanism and the third measuring mechanism are symmetrically arranged, so that the mass center of the tested aircraft can be conveniently calculated according to the data measured by the second measuring mechanism and the third measuring mechanism.
The utility model discloses further set up to: the front support frame is an assembled truss type support frame.
Through adopting above-mentioned technical scheme, adopt equipment truss-like support frame, this measuring device's of being convenient for dismantlement and installation.
The utility model discloses further set up to: the first measuring mechanism, the second measuring mechanism and the third measuring mechanism are all composed of a shell, a weighing sensor, a leveling mechanism and a lifting structure.
By adopting the technical scheme, the weighing sensor is convenient for measuring the mass; the leveling mechanisms on the first measuring mechanism, the second measuring mechanism and the third measuring mechanism are used for conveniently adjusting a front lifting support plate, a left main lifting support plate and a right main lifting support plate on the top surfaces of the first measuring mechanism, the second measuring mechanism and the third measuring mechanism respectively to keep the leveling devices; through the lifting structure on the first measuring mechanism, the second measuring mechanism and the third measuring mechanism, when weighing, the lifting structure descends, so that the front supporting plate, the left main supporting plate and the right main supporting plate fall onto respective weighing sensors respectively for weighing, and when not weighing, the lifting structure ascends to support the front supporting plate, the left main supporting plate and the right main supporting plate so as to protect the weighing sensors.
The utility model discloses further set up to: the number of the weighing sensors is 4, the leveling mechanisms are positioned at the bottom end inside the shell, the bottom end of the lifting structure is connected with the top end of the leveling mechanism, and the top end of the lifting structure penetrates through the top surface of the shell and extends out of the shell; the lifting structure consists of an electric cylinder and a lifting rod fixedly connected with the telescopic end of the electric cylinder.
By adopting the technical scheme, the top end of the lifting structure penetrates through the top surface of the shell and extends out of the shell to be connected with the bottom ends of the front lifting support plate, the left main lifting support plate or the right main lifting support plate, so that the effect of supporting the front lifting support plate, the left main lifting support plate and the right main lifting support plate is realized through the lifting function of the lifting structure, and the protection of the weighing sensor is realized; the leveling mechanism is adjusted to conveniently adjust the horizontal state of the lifting structure, so that the horizontal state of the top end of the lifting structure is conveniently adjusted to realize a horizontal measurement state; through electronic jar, be convenient for drive lifter goes up and down, realizes elevation structure's raising and lowering functions.
To sum up, the utility model discloses following beneficial effect has: the three undercarriage wheels of the tested aircraft can be conveniently supported through the front lifting support plate, the left main lifting support plate and the right main lifting support plate, so that the tested aircraft is fixed on the measuring device, and the operation of measuring the tested aircraft is convenient; the front support frame is convenient for mounting and supporting the first measuring mechanism; the rear supporting plate is convenient for mounting the second measuring mechanism and the third measuring mechanism and supporting the main lifting guide rail; the measuring mechanism can slide on the top surface of the front support frame through the front lifting guide rail, so that the position of the first measuring mechanism can be conveniently adjusted; the left main lifting support plate and the right main lifting support plate can slide on the top surface of the rear support plate through the main lifting guide rail, so that the positions of the left main lifting support plate and the right main lifting support plate can be conveniently adjusted; the pressure applied to the first measuring mechanism, the second measuring mechanism and the third measuring mechanism by the three undercarriage wheels of the measured aircraft is conveniently measured by the first measuring mechanism, the second measuring mechanism and the third measuring mechanism, so that the mass of the measured aircraft is conveniently calculated according to the data measured by the first measuring mechanism, the second measuring mechanism and the third measuring mechanism; the distance of the measuring mechanism I on the front supporting frame can be conveniently measured through the distance measuring and positioning mechanism; and the mass of the tested aircraft, the mass center in the X direction and the mass center in the Y direction can be conveniently calculated by combining the data measured by the first measuring mechanism, the second measuring mechanism, the third measuring mechanism and the ranging and positioning mechanism.
Drawings
Fig. 1 is a schematic structural diagram in an embodiment of the present invention;
fig. 2 is a schematic diagram of an internal structure of a first measuring mechanism in an embodiment of the present invention.
In the figure: 1. a front support frame; 2. a rear support plate; 3. a first measuring mechanism; 4. a second measuring mechanism; 5. a third measuring mechanism; 6. a front lifting supporting plate; 7. a left main lifting plate; 8. a right main lifting plate; 9. a front-lift guide rail; 10. a main lifting guide rail; 11. a distance measuring and positioning mechanism; 12. a weighing sensor; 13. a leveling mechanism; 14. a lifting structure; 15. a housing; 16. an electric cylinder; 17. a lifting rod.
Detailed Description
The present invention will be described in further detail with reference to the accompanying fig. 1-2.
Example (b): a mass center of mass measuring device is shown in figures 1 and 2 and comprises a front supporting frame 1, a rear supporting frame 2, a measuring mechanism I3, a measuring mechanism II 4, a measuring mechanism III 5, a front lifting supporting plate 6, a left main lifting supporting plate 7, a right main lifting supporting plate 8, a front lifting guide rail 9, a main lifting guide rail 10 and a distance measuring and positioning mechanism 11.
The front guide rail 9 is fixedly arranged on the top surface of the front support frame 1. The first measuring mechanism 3 is installed on the front lifting guide rail 9, and the first measuring mechanism 3 is connected with the front lifting guide rail 9 in a sliding mode. The front lifting supporting plate 6 is fixedly arranged at the top end of the measuring mechanism I3.
And the rear supporting plate 2 is fixedly connected with the top ends of the second measuring mechanism 4 and the third measuring mechanism 5. The main lifting guide 10 is fixedly installed on the top surface of the rear support plate 2. The left main lifting support plate 7 and the right main lifting support plate 8 are arranged on a main lifting guide rail 10, and the left main lifting support plate 7 and the right main lifting support plate 8 are in sliding connection with the main lifting guide rail 10.
Two ends of one end part of the front support frame 1 are respectively connected with the bottom ends of the second measuring mechanism 4 and the third measuring mechanism 5. The distance measuring and positioning mechanism 11 is fixedly arranged at the end part of the front support frame 1 far away from the rear support plate 2.
In this embodiment, preceding layer board 6, the main layer board 7 of rising of left side and the main layer board 8 of rising of right side can adjust according to the interval of different unmanned aerial vehicle undercarriage, make this measuring device can be applicable to multiple model unmanned aerial vehicle's measurement demand. When the measuring device is used for measuring the mass and the mass center of the measured aircraft, the measured aircraft is firstly hung on the measuring device, and three undercarriage wheels of the measured aircraft are convenient to hold up through the front lifting support plate 6, the left main lifting support plate 7 and the right main lifting support plate 8, so that the measured aircraft is fixed on the measuring device, and the measured aircraft is convenient to measure. Through front support frame 1, be convenient for the installation of measuring mechanism 3 and support measuring mechanism 3. Through back backup pad 2, be convenient for the installation of second 4 and third 5 of measuring mechanism, and be convenient for support main guide rail 10. Through the front guide rail 9, the measuring mechanism can slide on the top surface of the front support frame 1, and the position of the measuring mechanism 3 can be conveniently adjusted. Through the leading guide rail 10, make left leading layer board 7 and the right leading layer board 8 of playing slide at back support plate 2 top surface to be convenient for adjust the left leading layer board 7 of playing and the right leading layer board 8 position of playing. Through the first measuring mechanism 3, the second measuring mechanism 4 and the third measuring mechanism 5, the pressure applied to the first measuring mechanism 3, the second measuring mechanism 4 and the third measuring mechanism 5 by the three undercarriage wheels of the measured aircraft is measured conveniently, and therefore the mass of the measured aircraft is calculated conveniently according to the data measured by the first measuring mechanism 3, the second measuring mechanism 4 and the third measuring mechanism 5. Through range finding positioning mechanism 11, be convenient for measure the distance of measuring mechanism 3 on preceding support frame 1. And the mass of the tested aircraft, the mass center in the X direction and the mass center in the Y direction can be conveniently calculated by combining the data measured by the first measuring mechanism 3, the second measuring mechanism 4, the third measuring mechanism 5 and the ranging and positioning mechanism 11.
The second measuring mechanism 4 and the third measuring mechanism 5 are arranged at the bottom end of the rear supporting plate 2 in a bilateral symmetry mode with the center of the rear supporting plate 2 as a symmetry point.
In this embodiment, the second measuring mechanism 4 and the third measuring mechanism 5 are symmetrically arranged, so that the centroid of the tested aircraft can be conveniently calculated according to the data measured by the second measuring mechanism 4 and the third measuring mechanism 5.
The front support frame 1 is an assembled truss type support frame.
In this embodiment, the assembled truss-type support frame is adopted, so that the measurement device is convenient to disassemble and assemble and is convenient to carry.
The first measuring mechanism 3, the second measuring mechanism 4 and the third measuring mechanism 5 are all composed of a shell 15, a weighing sensor 12, a leveling mechanism 13 and a lifting structure 14.
In the present embodiment, the measurement of mass is facilitated by load cell 12. The leveling mechanisms 13 on the first measuring mechanism 3, the second measuring mechanism 4 and the third measuring mechanism 5 are used for conveniently adjusting the front lifting support plate 6, the left main lifting support plate 7 and the right main lifting support plate 8 on the top surfaces of the first measuring mechanism 3, the second measuring mechanism 4 and the third measuring mechanism 5 respectively to keep horizontal devices. Through the lifting structure 14 on the first measuring mechanism 3, the second measuring mechanism 4 and the third measuring mechanism 5, during weighing, the lifting structure 14 descends to enable the front lifting support plate 6, the left main lifting support plate 7 and the right main lifting support plate 8 to fall onto respective weighing sensors 12 respectively for weighing, and when the weighing is not carried out, the lifting structure 14 ascends to support the front lifting support plate 6, the left main lifting support plate 7 and the right main lifting support plate 8 so as to protect the weighing sensors 12.
The weighing sensors 12 are mounted on the top surface of the shell 15, the number of the leveling mechanisms 13 is 4, the leveling mechanisms 13 are located at the bottom end inside the shell 15, the bottom end of the lifting structure 14 is connected with the top end of the leveling mechanism 13, and the top end of the lifting structure 14 penetrates through the top surface of the shell 15 and extends out of the shell 15. The lifting structure 14 is composed of an electric cylinder 16 and a lifting rod 17 fixedly connected to the telescopic end of the electric cylinder 16.
In this embodiment, 4 leveling mechanisms 13 are respectively connected to the bottom end of the lifting rod 17 by threads, and the leveling function is realized by twisting the rotary leveling mechanisms 13. The top end of the lifting structure 14 penetrates through the top surface of the shell 15 and extends out of the shell 15, and is connected with the bottom end of the front supporting plate 6, the left main supporting plate 7 or the right main supporting plate 8, so that the lifting function of the lifting structure 14 can support the effect of the front supporting plate 6, the left main supporting plate 7 and the right main supporting plate 8, and the protection of the sensor 12 is realized. The leveling mechanism 13 is adjusted to conveniently adjust the horizontal state of the lifting structure 14, so that the horizontal state of the top end of the lifting structure 14 is conveniently adjusted to realize a horizontal measurement state. The electric cylinder 16 is convenient for driving the lifting rod 17 to lift, and the lifting function of the lifting structure 14 is realized.
The working process is as follows: when the measuring device is used for measuring the quality and the mass center of an aircraft to be measured, firstly, a calibration part is installed, the first measuring mechanism 3, the second measuring mechanism 4, the third measuring mechanism 5 and the distance measuring and positioning mechanism 11 are calibrated through the calibration part, after calibration is finished, the aircraft to be measured is hoisted to the measuring device, three undercarriage wheels of the aircraft to be measured accurately fall on the front lifting supporting plate 6, the left main lifting supporting plate 7 and the right main lifting supporting plate 8 by adjusting the positions of the front lifting supporting plate 6, the left main lifting supporting plate 7 and the right main lifting supporting plate 8, then the front lifting supporting plate 6, the left main lifting supporting plate 7 and the right main lifting supporting plate 8 are fixed, the measuring posture of the aircraft to be measured is adjusted by adjusting the lifting state of the measuring mechanism, the aircraft to be measured is taken down firstly after adjustment is finished, the measuring data of the first measuring mechanism 3, the second measuring mechanism 4 and the third measuring mechanism 5 are set to zero, after zero setting is completed, the aircraft is installed, and then the mass, the mass center in the X direction and the mass center in the Y direction of the tested aircraft are calculated by reading the measurement data of the first measurement mechanism 3, the second measurement mechanism 4, the third measurement mechanism 5 and the ranging and positioning mechanism 11. The measuring device has the advantages of simple and reliable structure, wide measuring range, high measuring precision, convenient disassembly and assembly, and capability of simultaneously measuring the mass of the tested aircraft, the mass center in the X direction and the mass center in the Y direction.
The present embodiment is only for explaining the present invention, and it is not limited to the present invention, and those skilled in the art can make modifications to the present embodiment without inventive contribution as required after reading the present specification, but all of them are protected by patent laws within the scope of the claims of the present invention.
Claims (5)
1. The utility model provides a quality barycenter measuring device which characterized by: the device comprises a front support frame (1), a rear support plate (2), a first measuring mechanism (3), a second measuring mechanism (4), a third measuring mechanism (5), a front lifting support plate (6), a left main lifting support plate (7), a right main lifting support plate (8), a front lifting guide rail (9), a main lifting guide rail (10) and a distance measuring and positioning mechanism (11);
the front lifting guide rail (9) is fixedly arranged on the top surface of the front support frame (1); the first measuring mechanism (3) is arranged on the front lifting guide rail (9), and the first measuring mechanism (3) is connected with the front lifting guide rail (9) in a sliding manner; the front lifting supporting plate (6) is fixedly arranged at the top end of the measuring mechanism I (3);
the rear supporting plate (2) is fixedly connected with the top ends of the second measuring mechanism (4) and the third measuring mechanism (5); the main lifting guide rail (10) is fixedly arranged on the top surface of the rear supporting plate (2); the left main lifting support plate (7) and the right main lifting support plate (8) are arranged on a main lifting guide rail (10), and the left main lifting support plate (7) and the right main lifting support plate (8) are in sliding connection with the main lifting guide rail (10);
two ends of one end part of the front support frame (1) are respectively connected with the bottom ends of the second measuring mechanism (4) and the third measuring mechanism (5); the distance measuring and positioning mechanism (11) is fixedly arranged at the end part of the front support frame (1) far away from the rear support plate (2).
2. The mass centroid measuring device of claim 1, wherein: and the second measuring mechanism (4) and the third measuring mechanism (5) are arranged at the bottom end of the rear supporting plate (2) in a bilateral symmetry mode by taking the center of the rear supporting plate (2) as a symmetry point.
3. The mass centroid measuring device of claim 1, wherein: the front support frame (1) is an assembled truss type support frame.
4. The mass centroid measuring device of claim 1, wherein: the first measuring mechanism (3), the second measuring mechanism (4) and the third measuring mechanism (5) are all composed of a shell (15), a weighing sensor (12), a leveling mechanism (13) and a lifting structure (14).
5. The mass centroid measuring device of claim 4, wherein: the weighing sensors (12) are mounted on the top surface of the shell (15), the number of the leveling mechanisms (13) is 4, the leveling mechanisms (13) are located at the bottom end inside the shell (15), the bottom end of the lifting structure (14) is connected with the top end of the leveling mechanisms (13), and the top end of the lifting structure penetrates through the top surface of the shell (15) and extends out of the shell (15); the lifting structure (14) is composed of an electric cylinder (16) and a lifting rod (17) fixedly connected with the telescopic end of the electric cylinder (16).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022609656.7U CN213515967U (en) | 2020-11-12 | 2020-11-12 | Mass and mass center measuring device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022609656.7U CN213515967U (en) | 2020-11-12 | 2020-11-12 | Mass and mass center measuring device |
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| Publication Number | Publication Date |
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| CN213515967U true CN213515967U (en) | 2021-06-22 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202022609656.7U Expired - Fee Related CN213515967U (en) | 2020-11-12 | 2020-11-12 | Mass and mass center measuring device |
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| CN (1) | CN213515967U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR102490822B1 (en) * | 2022-03-28 | 2023-01-20 | 국방과학연구소 | Aircraft weight and center of gravity measurement system |
-
2020
- 2020-11-12 CN CN202022609656.7U patent/CN213515967U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR102490822B1 (en) * | 2022-03-28 | 2023-01-20 | 국방과학연구소 | Aircraft weight and center of gravity measurement system |
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