Aviation motor controller vibration test clamp

Abstract

The invention discloses an aviation motor controller vibration test clamp which comprises a base plate serving as a base connected with a vibration table, two sets of supporting plates are vertically arranged on the left side and the right side of the top end of the base plate, wire passing holes are formed in the side walls of the supporting plates of each set, and triangular rib plates are connected to the outer side walls of the supporting plates of each set through first fasteners. The top surfaces of the two groups of supporting plates are transversely connected with a mounting plate through second fasteners; the plates are assembled in a threaded connection and argon arc welding mode, the integrity is good, the rigidity is high, the connection reliability of the plates of the clamp is improved, it is ensured that the rigidity and vibration quantity value transmission of the clamp meet the test requirements, the center of gravity of the clamp can be controlled to be the lowest, effective transmission of force vibration magnitude is ensured, and the test efficiency is improved. The device can simulate the vibration environment of the motor controller in a real onboard installation environment to verify the reliability of the motor controller, and is suitable for inverted installation of the aviation motor controller.

Description

Technical Field

[0001] This invention relates to the field of vibration testing fixtures for motor controllers in the aviation industry, specifically to a vibration testing fixture for an aviation motor controller. Background Technology

[0002] A motor controller is an integrated circuit that actively controls a motor to operate according to a set direction, speed, angle, and response time.

[0003] As a key device on the aircraft, the reliability of the motor controller in vibration environment is crucial to flight safety. Currently, traditional fixture designs suffer from insufficient rigidity, transmission distortion, lack of center of gravity control, and poor connection reliability, making it difficult to meet the stringent requirements of aviation-grade testing. Summary of the Invention

[0004] The purpose of this invention is to provide a vibration test fixture for an aircraft motor controller, so as to solve the problems of insufficient stiffness, transmission distortion, lack of center of gravity control, and poor connection reliability in the traditional fixture design mentioned in the background art.

[0005] To achieve the above objectives, the present invention provides the following technical solution: a vibration test fixture for an aircraft motor controller, comprising a base plate serving as the foundation for connection to a vibration table, two sets of support plates vertically arranged on the top of the base plate, each set of support plates having wire holes on its sidewalls, each set of support plates having a triangular rib plate connected to its outer sidewalls via a first fastener, and the bottom of the triangular rib plate being fixed to the base plate, the top surfaces of the two sets of support plates being laterally connected to a mounting plate via a second fastener, and the motor controller being connected to the mounting plate via a third fastener.

[0006] Furthermore, both the substrate and the top of the vibration table are provided with several sets of mounting holes, and the substrate is fastened to the vibration table by bolts passing through the mounting holes.

[0007] Furthermore, the side view of the support plate is an isosceles trapezoidal structure, and the vertical height of the support plate does not exceed the vertical height of the triangular rib plate.

[0008] Furthermore, the lateral length of the mounting plate does not exceed the lateral length of the top panel of the support plate.

[0009] Furthermore, both the mounting plate and the base plate have a rectangular shape when viewed from above, and the mounting plate is made of aluminum.

[0010] Furthermore, the gaps at the joints between the mounting plate and the support plate, and between the support plate and the substrate, can all be welded using argon arc welding.

[0011] The beneficial effects of this invention are: This invention features high rigidity, good center of gravity control, reliable connection, and convenient testing. The assembly process involves threading the base plate, support plate, triangular rib plate, and mounting plate together, followed by argon arc welding. This results in good overall integrity and high rigidity, providing better vibration resistance and relaxation. It also enhances the reliability of connections between the fixture plates, ensuring that the fixture's rigidity and vibration transmission meet test requirements. Furthermore, the fit between the support plate and the wiring holes allows the fixture to maintain a minimum center of gravity while accommodating motor controller installation and test wiring, reducing the amplification of vibration test magnitudes and ensuring effective transmission of force vibration magnitudes. Simultaneously, it can simulate the vibration environment experienced by the motor controller in a real-world on-board installation environment to verify its reliability. This invention is suitable for inverted installation of aircraft motor controllers, facilitating the widespread use of this aircraft motor controller vibration test fixture. Attached Figure Description

[0012] Figure 1 This is a schematic diagram showing the usage state of the vibration test fixture for the aircraft motor controller of the present invention; Figure 2 This is a three-dimensional structural view of the vibration test fixture for the aircraft motor controller of the present invention.

[0013] In the diagram: 1. Substrate; 101. Mounting hole; 2. Support plate; 3. Triangular rib; 4. Mounting plate; 5. Wiring hole; 6. Vibration table. Detailed Implementation

[0014] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0015] Please see Figure 1-2 This invention provides a technical solution: a vibration test fixture for an aircraft motor controller, comprising a base plate 1 serving as the foundation for connection to a vibration table 6. Two sets of support plates 2 are vertically arranged on the top left and right sides of the base plate 1. Each set of support plates 2 has wire-passing holes 5 on its side walls. The wire-passing holes 5 have a circular side shape. Each set of support plates 2 has a triangular rib plate 3 connected to its outer side wall by a first fastener. The bottom of the triangular rib plate 3 is fixed to the base plate 1. The top surfaces of the two sets of support plates 2 are laterally connected to a mounting plate 4 by a second fastener. The side view of the support plate 2 is an isosceles trapezoidal structure. The vertical height of the support plate 2 does not exceed the vertical height of the triangular rib plate 3. The motor controller is connected to the mounting plate 4 by a third fastener.

[0016] The lateral length of the mounting plate 4 does not exceed the lateral length of the top panel of the support plate 2. Both the mounting plate 4 and the base plate 1 have a rectangular shape when viewed from above. The mounting plate 4 is made of, but is not limited to, aluminum plate, and the thickness of the aluminum plate can be 30mm. The top of the base plate 1 and the vibration table 6 are provided with several sets of mounting holes 101. The base plate 1 is fastened to the vibration table 6 by bolts through the mounting holes 101. The mounting holes 101 are arranged in an array on the base plate 1 and the vibration table 6. The array of mounting holes 101 can be adapted to different types of vibration tables 6 to achieve rapid installation of the vibration fixture. The gaps between the mounting plate 4 and the support plate 2, and between the support plate 2 and the base plate 1, can all be welded by argon arc welding. The first fastener, the second fastener, and the third fastener are all made of, but are not limited to, bolts, screws, or screws. The bottom surface of the support plate 2 is rough to increase the friction of the bottom of the support plate 2, so that the support plate 2 is more stably installed on the base plate 1.

[0017] Before use, this vibration test fixture for an aircraft motor controller is based on a base plate 1. Support plates 2 are vertically mounted on the base plate 1 using threaded connections, forming a polyhedral frame structure. Three triangular ribs 3 on each side are threadedly fastened to the base plate 1 and support plates 2 for reinforcement. Finally, mounting plates 4 are threadedly connected to the two support plates 2. The plates can then be welded for further reinforcement. During use, the vibration fixture is first placed in the center of the vibration table 6, with the base plate 1 aligned with the mounting holes 101 on the vibration table 6. Bolts are then used to fasten the fixture through the mounting holes 101. The motor controller is then fastened to the mounting plate 4 with screws, and the wiring harness for the required vibration sensors is arranged using the wire holes 5. Before the test, the vibration response near the mounting screws of the motor controller is monitored. Subsequent tests are conducted only after the vibration response meets the standard requirements. After the test, the fixture is disassembled and any dirt removed.

[0018] It should be noted that the two vertical support plates 2 serve as the support structure for the mounting plate 4. While meeting the installation height requirements of the motor controller, the height of the support plates 2 is controlled to an optimal state to lower the overall center of gravity of the fixture, reducing the amplification of the vibration test magnitude. The circular wire-passing holes 5 on the support plates 2 facilitate the installation of vibration test sensors. The triangular ribs 3 on both sides reinforce the vertically erected support plates 2, enhancing their overall rigidity and significantly improving the torsional and bending resistance of the overall frame, ensuring efficient transmission and minimal amplification of the vibration magnitude. The mounting plate 4 is... The motor controller is provided with mounting plate 4, which can be equipped with threaded holes of different specifications and spacing to accommodate the inverted installation requirements of motor controllers of similar size. Mounting plate 4 can be made of 30mm thick aluminum plate, which has strong strength and rigidity, and forms a polyhedral frame structure with other parts to further reduce the deflection of the fixture during vibration. The plates are first connected with M8 screws, and then argon arc welding is used at the joints of the plates to improve the integrity of the fixture and ensure the effectiveness of vibration magnitude transmission. Compared with integral molding, this processing method has a lower cost.

[0019] This vibration test fixture for an aircraft motor controller features a multi-faceted frame design. The plates are assembled using a combination of threaded connections and argon arc welding, resulting in good overall integrity and high rigidity in all axes. This ensures that the rigidity of the fixture and the transmission of vibration values ​​meet the test requirements. The first-order frequency of the fixture exceeds 2000Hz, which is outside the 10Hz to 2000Hz frequency range of random vibration of the aircraft motor controller, effectively avoiding resonance points with the controller. To facilitate the arrangement of the sensor wiring harness during the test, two through holes 5 are provided on the vertical support plate 2 to facilitate the arrangement of the sensor wiring harness during horizontal vibration. The front and rear directions adopt an open design, which facilitates both product installation and the arrangement of sensor wiring harnesses in the front and rear directions.

[0020] Among them, the vibration test fixture for the aircraft motor controller uses M8 screws to connect the plates of the fixture first, and then argon arc welding is used to weld the gaps between the overlapping surfaces of the plates. Compared with the traditional screw connection, it has a better anti-vibration and anti-loosening effect, improves the connection reliability between the plates of the fixture, and, while meeting the requirements of motor controller installation and test wiring, controls the center of gravity to the lowest level, improves the dynamic stability and first-order frequency of the fixture, and ensures the effective transmission of force vibration magnitude.

[0021] The technical features of the above embodiments can be combined in any way. For the sake of brevity, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0022] The above embodiments only illustrate preferred embodiments of the present invention, and their descriptions are relatively specific and detailed, but they should not be construed as limiting the scope of the invention patent. It should be understood that, for those skilled in the art, several modifications and improvements can be made without departing from the concept of the present invention, and these all fall within the protection scope of the present invention. In the present invention, unless otherwise explicitly specified and limited, the terms "installation," "connection," "joining," "fixing," etc., should be interpreted broadly. For example, it can refer to a fixed connection, a detachable connection, or an integral part; it can refer to a mechanical connection; it can refer to a direct connection or an indirect connection through an intermediate medium; it can refer to the internal communication of two components or the interaction between two components. Among these, there are various ways of detachable installation, such as by using a combination of plug-in and snap-fit, or by using bolt connections, etc.

[0023] Although embodiments of the invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. A vibration test fixture for an aircraft motor controller, characterized in that: The system includes a base plate that serves as the foundation for connecting to the vibration table. Two sets of support plates are vertically arranged on the top of the base plate. Each set of support plates has wire holes on its sidewalls. Each set of support plates has a triangular rib connected to its outer sidewall by a first fastener. The bottom of the triangular rib is fixed to the base plate. The top surfaces of the two sets of support plates are horizontally connected to a mounting plate by a second fastener. A motor controller is connected to the mounting plate by a third fastener.

2. The vibration test fixture for an aircraft motor controller according to claim 1, characterized in that: Both the substrate and the top of the vibration table are provided with several sets of mounting holes. The substrate is fastened to the vibration table by bolts through the mounting holes.

3. The vibration test fixture for an aircraft motor controller according to claim 1, characterized in that: The support plate has an isosceles trapezoidal shape when viewed from the side, and its vertical height does not exceed the vertical height of the triangular rib plate.

4. The vibration test fixture for an aircraft motor controller according to claim 1, characterized in that: The lateral length of the mounting plate does not exceed the lateral length of the top panel of the support plate.

5. The vibration test fixture for an aircraft motor controller according to claim 1, characterized in that: Both the mounting plate and the base plate have a rectangular shape when viewed from above, and the mounting plate is made of aluminum.

6. The vibration test fixture for an aircraft motor controller according to claim 1, characterized in that: The gaps at the joints between the mounting plate and the support plate, and between the support plate and the base plate, can all be welded using argon arc welding.

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