Aerospace dynamometer capable of realizing multiple modes
By integrating vibration testing components in aerospace dynamometers, the problem that existing aerospace dynamometers cannot detect vibration of aerospace motors is solved, and the detection of vibration of aerospace motors is realized, reducing detection costs.
Patent Information
- Application Number
- CN202421534199.1
- Authority / Receiving Office
- CN · China
- Patent Type
- Utility models(China)
- Current Assignee / Owner
- Filing Date
- 2024-07-01
- Publication Date
- 2025-03-21
- Estimated Expiration
- 2034-07-01
AI Technical Summary
Existing aerospace dynamometers cannot detect the vibration of aerospace motors, resulting in the need to use a vibration tester when it is necessary to detect the vibration amplitude of the aerospace motors, resulting in higher detection costs.
A multi-mode aerospace dynamometer is designed to detect vibration generated by aerospace motors by setting up vibration testing components in the dynamometer, including protective rubber, springs, placement tables and vibration testers.
The detection function of vibration of aerospace motors has been realized, which makes up for the problem that dynamometers can only detect simple torque and speed but cannot detect vibration in the prior art, reducing the detection cost.
Smart Images
Figure CN222652416U_ABST
Abstract
Description
Technical Field
[0001] The utility model relates to the technical field of dynamometers, in particular to an aerospace dynamometer capable of realizing multiple modes. Background Art
[0002] A dynamometer is a tool used to measure the performance and power of a mechanical or electronic device. They are commonly used to test various devices such as engines, electric motors, hydraulic systems, etc. Dynamometers calculate power by measuring the force or torque generated by the device under load and combining it with the speed of the device. These devices usually include sensors, rotors, control systems, and data acquisition systems. Dynamometers can help engineers and researchers evaluate the performance, efficiency, and reliability of equipment in order to improve and optimize it. They have a wide range of applications in the automotive industry, aerospace, energy production, and other fields.
[0003] Dynamometers are also used in the aerospace field. Generally, the aerospace motor that needs to be tested is connected to the dynamometer through its output terminal. When the aerospace motor is started, the dynamometer is driven to rotate, thereby realizing the detection of the aerospace motor power and torque speed. However, since the aerospace dynamometer of the existing technology cannot detect the vibration of the aerospace motor, when the vibration amplitude of the aerospace motor needs to be detected, a vibration tester needs to be used for monitoring, which leads to high detection costs. Utility Model Content
[0004] The utility model provides an aerospace dynamometer which can realize multiple modes and has the advantages of vibration testing, so as to solve the problem that the aerospace dynamometer in the prior art cannot detect the vibration of the aerospace motor, resulting in the need to use a vibration tester for monitoring when the vibration amplitude of the aerospace motor needs to be detected, thereby resulting in a high detection cost.
[0005] In order to achieve the purpose of vibration testing, the utility model provides the following technical solutions: a multi-mode aerospace dynamometer, comprising a setting plate and a dynamometer, the dynamometer being mounted on the top surface of the setting plate, a transmission shaft being mounted on one side surface of the dynamometer, a connecting socket being mounted on one end of the transmission shaft, a support plate being mounted on the top surface of the setting plate, a test bench being mounted on the top surface of the setting plate, a vibration test assembly being mounted on the top surface of the test bench, and a fixing assembly being mounted on the top surface of the test bench.
[0006] As a preferred technical solution of the utility model, one end of the transmission shaft is fixedly connected to the output end of the dynamometer, the transmission shaft is fixedly connected to the connecting socket, and the outer surface of the transmission shaft is movably and rotatably connected to the inner wall of the support plate.
[0007] As a preferred technical solution of the utility model, the fixing assembly includes a docking hole, a bearing is installed on the inner wall of the docking hole, a connector is installed on the inner wall of the bearing, a limiting block is installed on the outer surface of the bearing, and the docking hole is opened on one side surface of the test bench.
[0008] As a preferred technical solution of the utility model, the outer surface of the connector is movably and rotatably connected to the inner wall of the bearing, there are two limit blocks, and the two limit blocks are equidistantly distributed on the outer surface of the bearing, the outer surfaces of the bearing and the limit blocks are in movably contact with the inner wall of the docking hole, and the connector is movably connected to the connecting socket.
[0009] As a preferred technical solution of the utility model, the vibration test assembly includes a protective rubber, a spring is installed on the top surface of the test table, a placing table is installed on the top surface of the spring, an adjustment hole is opened on the top surface of the placing table, a fixing bolt is installed on the inner wall of the adjustment hole, a fixing hole is opened on the top surface of the test table, the protective rubber is installed on the top surface of the test table, a vibration tester is installed on the outer surface of the placing table, and a fixing plate is fixedly connected to the upper side of the placing table.
[0010] As a preferred technical solution of the utility model, there are four springs, which are evenly distributed on the top surface of the test bench in a circular array, and the top surface of each spring is fixedly connected to the bottom surface of the placement table.
[0011] As a preferred technical solution of the utility model, the top surface of the protective rubber is fixedly connected to the bottom surface of the placement table, the outer surface of the fixing bolt is movably and rotatably connected to the inner wall of the adjustment hole, and the outer surface of the fixing bolt is movably and rotatably connected to the inner wall of the fixing hole.
[0012] Compared with the prior art, the utility model provides a multi-mode aerospace dynamometer, which has the following beneficial effects:
[0013] The multi-mode aerospace dynamometer can transmit the vibration generated by the aerospace motor to the spring installed on the bottom surface of the aerospace motor through the placement table, and a vibration sensor is installed on the surface of one side of the placement table. At this time, the vibration sensor will monitor the vibration of the spring and the placement table, so as to realize the function of vibration testing, thereby compensating for the problem that the aerospace dynamometer of the prior art can only perform simple torque and speed detection on the aerospace motor, and needs to be used in conjunction with other equipment when vibration detection of the aerospace motor is required, resulting in a relatively single function. BRIEF DESCRIPTION OF THE DRAWINGS
[0014] Figure 1 This is a schematic diagram of the external structure of the utility model;
[0015] Figure 2 This is a schematic diagram of the external structure of the utility model from another angle;
[0016] Figure 3 This is a schematic diagram of the internal structure of the utility model;
[0017] Figure 4 This is a schematic diagram of the structure of the vibration test assembly of the utility model;
[0018] Figure 5 This is a schematic diagram of the structure of the fixed component of the utility model;
[0019] Figure 6 The utility model provides Figure 3 A schematic diagram of the enlarged structure of part A.
[0020] In the figure: 1. Setting plate; 2. Dynamometer; 3. Transmission shaft; 4. Connecting socket; 5. Support plate; 6. Test bench; 7. Docking hole; 8. Bearing; 9. Connector; 10. Limit block; 11. Protective rubber; 12. Spring; 13. Placement table; 14. Adjustment hole; 15. Fixing bolt; 16. Fixing hole; 17. Vibration tester; 18. Fixing plate. DETAILED DESCRIPTION
[0021] The following will be combined with the drawings in the embodiments of the utility model to clearly and completely describe the technical solutions in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, not all of the embodiments. Based on the embodiments in the utility model, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the utility model. Embodiment 1
[0022] See also Figure 1-Figure 3 The utility model discloses a multi-mode aerospace dynamometer, comprising a setting plate 1 and a dynamometer 2, the dynamometer 2 being mounted on the top surface of the setting plate 1, a transmission shaft 3 being mounted on one side surface of the dynamometer 2, a connecting socket 4 being mounted on one end of the transmission shaft 3, a supporting plate 5 being mounted on the top surface of the setting plate 1, a test bench 6 being mounted on the top surface of the setting plate 1, a vibration test assembly being mounted on the top surface of the test bench 6, and a fixing assembly being mounted on the top surface of the test bench 6.
[0023] One end of the transmission shaft 3 is fixedly connected to the output end of the dynamometer 2 , the transmission shaft 3 is fixedly connected to the connecting socket 4 , and the outer surface of the transmission shaft 3 is movably and rotatably connected to the inner wall of the support plate 5 .
[0024] The fixing assembly includes a docking hole 7, a bearing 8 is installed on the inner wall of the docking hole 7, a connector 9 is installed on the inner wall of the bearing 8, a limit block 10 is installed on the outer surface of the bearing 8, and the docking hole 7 is opened on one side surface of the test bench 6.
[0025] The outer surface of the connector 9 is movably connected to the inner wall of the bearing 8. There are two limit blocks 10, which are equidistantly distributed on the outer surface of the bearing 8. The outer surfaces of the bearing 8 and the limit blocks 10 are in movably contact with the inner wall of the docking hole 7, and the connector 9 is movably connected to the connecting socket 4. Embodiment 2
[0026] Based on the above Example 1, please refer to Figure 4-Figure 6 The vibration test assembly includes a protective rubber 11, a spring 12 is installed on the top surface of the test table 6, a placing table 13 is installed on the top surface of the spring 12, an adjustment hole 14 is opened on the top surface of the placing table 13, a fixing bolt 15 is installed on the inner wall of the adjusting hole 14, a fixing hole 16 is opened on the top surface of the test table 6, the protective rubber 11 is installed on the top surface of the test table 6, a vibration tester 17 is installed on the outer surface of the placing table 13, and a fixing plate 18 is fixedly connected to the upper side of the placing table 13.
[0027] There are four springs 12 , which are evenly distributed on the top surface of the test bench 6 in a circular array, and the top surface of each spring 12 is fixedly connected to the bottom surface of the placement table 13 .
[0028] The top surface of the protective rubber 11 is fixedly connected to the bottom surface of the placement table 13 , the outer surface of the fixing bolt 15 is movably and rotatably connected to the inner wall of the adjustment hole 14 , and the outer surface of the fixing bolt 15 is movably and rotatably connected to the inner wall of the fixing hole 16 .
[0029] The working principle and use process of the utility model are as follows: when the aerospace dynamometer 2 is needed, the aerospace motor to be tested is placed on the top surface of the placement table 13. After the placement is completed, the output end of the aerospace motor is inserted into the inner wall of the connector 9, and the aerospace motor is pushed. Because the output end of the aerospace motor is inserted into the inner wall of the connector 9 at this time, when the aerospace motor moves, the connector 9 pushes the bearing 8 to move on the inner wall of the docking hole 7, and the bearing 8 and the connector 9 will move toward one side surface of the connecting socket 4. When the connector 9 and the connecting socket 4 are in contact with each other, the connector 9 will be inserted into the inner wall of the connecting socket 4. When the plug-in is completed, the fixing plate 18 is placed on the placement table 13. The top surface is fixed on the top surface of the placement table 13, and the inner wall of the fixing plate 18 is in contact with the outer surface of the aerospace motor. After placement, the fixing plate 18 is fixed to the top surface of the placement table 13 by bolts, so that the fixing plate 18 fixes the aerospace motor on the placement table 13. After fixation, the aerospace motor is connected to the circuit to make the aerospace motor run. When the aerospace motor runs, the connector 9 on its outer surface is driven to rotate through its output end. At this time, the connector 9 is plugged into the inner wall of the connecting socket 4, and one end of the connecting socket 4 is connected to one end of the transmission shaft 3. Therefore, the aerospace motor started at this time will drive the transmission shaft 3 installed at the output end of the dynamometer 2 to rotate through the connector 9, so that the power and speed of the aerospace motor are detected by the dynamometer 2.
[0030] When the aerospace motor needs to be tested for vibration, the fixing bolt 15 installed on the inner wall of the adjustment hole 14 is rotated. When the fixing bolt 15 rotates, it rotates on the inner wall of the adjustment hole 14, and because the fixing bolt 15 is rotated and plugged into the inner wall of the fixing hole 16 at this time, when the fixing bolt 15 rotates, it rotates out from the inner wall of the fixing hole 16. When the fixing bolt 15 rotates out, the fixing bolt 15 between the placement table 13 and the test table 6 is restricted so that the two are no longer in indirect contact, so that the placement table 13 without restriction will be installed on its bottom surface. The spring 12 is lifted up, so that the placement table 13 is supported by the spring 12. At this time, the aerospace motor to be tested is placed on the top surface of the placement table 13, and it is connected to the circuit to make the aerospace motor start to operate. When the aerospace motor on the top surface of the placement table 13 is started to operate, it will vibrate. At this time, the vibration generated by the aerospace motor will be transmitted to the spring 12 installed on its bottom surface through the placement table 13, and a vibration sensor is installed on one side surface of the placement table 13. At this time, the vibration sensor will monitor the vibration of the spring 12 and the placement table 13, thereby realizing the function of vibration testing.
Claims
1. An aerospace dynamometer capable of realizing multiple modes, comprising a setting plate (1) and a dynamometer (2), wherein the dynamometer (2) is mounted on the top surface of the setting plate (1), and characterized in that: A transmission shaft (3) is mounted on one side surface of the dynamometer (2), a connection socket (4) is mounted on one end of the transmission shaft (3), a support plate (5) is mounted on the top surface of the setting plate (1), a test bench (6) is mounted on the top surface of the setting plate (1), a vibration test assembly is mounted on the top surface of the test bench (6), and a fixing assembly is mounted on the top surface of the test bench (6); The vibration test assembly comprises a protective rubber (11), a spring (12) is installed on the top surface of the test bench (6), a placement table (13) is installed on the top surface of the spring (12), an adjustment hole (14) is provided on the top surface of the placement table (13), a fixing bolt (15) is installed on the inner wall of the adjustment hole (14), a fixing hole (16) is provided on the top surface of the test bench (6), the protective rubber (11) is installed on the top surface of the test bench (6), a vibration tester (17) is installed on the outer surface of the placement table (13), and a fixing plate (18) is fixedly connected to the upper side of the placement table (13).
2. The multi-mode aerospace dynamometer according to claim 1, characterized in that: One end of the transmission shaft (3) is fixedly connected to the output end of the dynamometer (2), the transmission shaft (3) is fixedly connected to the connection socket (4), and the outer surface of the transmission shaft (3) is movably and rotatably connected to the inner wall of the support plate (5).
3. The multi-mode aerospace dynamometer according to claim 1, characterized in that: The fixing assembly comprises a docking hole (7), a bearing (8) is installed on the inner wall of the docking hole (7), a connector (9) is installed on the inner wall of the bearing (8), a limit block (10) is installed on the outer surface of the bearing (8), and the docking hole (7) is opened on a side surface of the test bench (6).
4. The multi-mode aerospace dynamometer according to claim 3, characterized in that: The outer surface of the connector (9) is movably connected to the inner wall of the bearing (8), the number of the limit blocks (10) is two, and the two limit blocks (10) are equidistantly distributed on the outer surface of the bearing (8), the outer surfaces of the bearing (8) and the limit blocks (10) are in movably contact with the inner wall of the docking hole (7), and the connector (9) is movably connected to the connecting socket (4).
5. The multi-mode aerospace dynamometer according to claim 1, characterized in that: There are four springs (12), which are distributed equidistantly on the top surface of the test bench (6) in a circular array, and the top surface of each spring (12) is fixedly connected to the bottom surface of the placement table (13).
6. The multi-mode aerospace dynamometer according to claim 1, characterized in that: The top surface of the protective rubber (11) is fixedly connected to the bottom surface of the placement table (13), the outer surface of the fixing bolt (15) is movably and rotatably connected to the inner wall of the adjustment hole (14), and the outer surface of the fixing bolt (15) is movably and rotatably connected to the inner wall of the fixing hole (16).