Attitude adjusting device for satellite gyro product polarity test

Abstract

This invention provides an attitude adjustment device for polarity testing of satellite gyroscope products, including a top plate, an attitude adjustment component, a mounting base plate, and a mounting adjustment assembly. The mounting adjustment assembly is installed on top of the top plate, and the mounting base plate is connected to the top plate via the attitude adjustment assembly. The mounting adjustment assembly is used to connect to an external satellite gyroscope mounting plate or an external flywheel mounting plate, and can be adjusted according to different interfaces of different mounting plates. This invention features a simple structure, convenient adjustment, strong adaptability, and good processing performance. The mounting adjustment assembly can be adjusted according to the mounting interfaces of different gyroscope mounting plates, meeting the usage requirements of various mounting interfaces. This invention uses four evenly distributed springs to form the attitude adjustment assembly, which has a simple and compact configuration. Furthermore, while ensuring stable and safe product installation, the operator only needs to apply force to one spring mounting surface to achieve attitude changes, without requiring an additional power source.

Description

Technical Field

[0001] This invention relates to the field of attitude adjustment, specifically to an attitude adjustment device for polarity testing of satellite gyroscope products, and more particularly, to a novel attitude adjustment device designed for the polarity testing process of satellite gyroscope products. Background Technology

[0002] Gyroscopes are attitude-sensing devices for satellites and key components for satellite attitude and orbit control. Polarity verification testing is a crucial test item in the satellite testing process. Traditional methods for gyroscope polarity verification require a turntable. The satellite is positioned at a preset angle (≤3°), and the gyroscope angle is obtained via ground-based testing equipment. The polarity is then determined by comparing the telemetry angle with the turntable angle. The advantage of this traditional method is the quantification of test results; however, its disadvantages include a complex testing process, high equipment cost, long testing time, and the need for specialized, structurally complex turntable equipment.

[0003] The Chinese invention patent "A Polarity Testing Device for a Satellite Attitude Control System" (patent number CN202010261298.7A) uses a simulation device installed on a robotic arm to simulate corresponding signals and change the attitude state of the satellite's attitude control system to determine the polarity state of the satellite's attitude. This invention is a quantitative test at the satellite system level, and the testing system is complex.

[0004] The Chinese invention patent "A method for measuring the attitude and height of a dynamic platform" (patent number CN103090863A) uses two orthogonally mounted, vertically downward scanning two-dimensional laser scanners to obtain road surface scan lines, and uses the road surface data to calculate the attitude and height of the platform. The system is complex and large, and is not suitable for testing precision products.

[0005] In the Chinese invention patent "Antenna Attitude Monitoring System with Electrical Adjustment Function" (patent number CN103116364A), the mechanical angle of the antenna is measured by an attitude sensor installed on the antenna and uploaded to the network management center. The antenna angle can then be remotely adjusted as needed. This invention requires a dedicated sensor to measure the attitude and a remotely controlled motor to adjust the antenna, making the system complex.

[0006] The Chinese invention patent "Attitude Control Rocket Engine Polarity Detection Device" (patent number CN114235416A) uses a rotatable fan-shaped device with LED indicators installed in the middle of the exhaust port to indicate whether the rocket engine is working. This invention is mainly used as a polarity device to monitor whether a rocket engine is working, and is not suitable for polarity testing of gyroscope products.

[0007] The Chinese invention patent "A Novel Attitude-Adjustable Load-Bearing Platform" (patent number CN205394469U) employs a four-link RPR (revolute joint-prismatic joint-revolute joint) mechanism to achieve movement in two coordinate directions and rotation in one coordinate direction. This invention has a complex mechanism, the kinematic joints require lubrication, posing a risk of contamination, and is unsuitable for applications requiring the environmental conditions necessary for aerospace optical products. Summary of the Invention

[0008] In view of the deficiencies in the prior art, the purpose of this invention is to provide an attitude adjustment device for polarity testing of satellite gyroscope products.

[0009] An attitude adjustment device for polarity testing of satellite gyroscope products according to the present invention includes a top plate, an attitude adjustment component, a mounting base plate, and a mounting adjustment component;

[0010] The mounting adjustment assembly is installed on the top of the top plate, and the mounting base plate is connected to the top plate through the attitude adjustment assembly;

[0011] The mounting and adjustment assembly is used to connect to an external satellite gyroscope mounting plate or an external flywheel mounting plate, and the mounting and adjustment assembly can be adjusted according to the different interfaces of different mounting plates.

[0012] Preferably, the mounting and adjusting assembly includes a first fastener, a second fastener, and an adjusting plate; one end of the adjusting plate is rotatably mounted on the top plate via the first fastener; the adjusting plate is provided with a slot along the length direction of the adjusting plate, and the second fastener can slide along the slot;

[0013] The ends of the first and second fasteners are connected to the external satellite gyroscope mounting plate or the external flywheel mounting plate.

[0014] Preferably, both the first fastener and the second fastener are screws or bolts.

[0015] Preferably, the adjusting plate and the mounting base plate are both made of aluminum alloy material and the surface is anodized in real time.

[0016] Preferably, the attitude adjustment component consists of multiple elastic elements evenly distributed circumferentially along the top plate.

[0017] Preferably, the elastic element is a spring, one end of which is connected to the top plate and the other end of which is connected to the mounting base plate.

[0018] Preferably, it also includes anti-slip pads, which are evenly distributed on the bottom of the mounting base plate.

[0019] Preferably, the bottom surface of the mounting base is covered with anti-scratch rubber pads.

[0020] Preferably, the number of springs is four.

[0021] Preferably, the mounting base plate is fixed to the external satellite mounting plate by fasteners.

[0022] Compared with the prior art, the present invention has the following beneficial effects:

[0023] 1. This invention features simple structure, convenient adjustment, strong adaptability, and good processing performance. The installation and adjustment components can be adjusted according to the installation interface of different gyroscope mounting plates to meet the usage requirements of various installation interfaces.

[0024] 2. This invention uses four evenly distributed springs to form the attitude adjustment component, resulting in a simple and ingenious design. Furthermore, by utilizing these four evenly distributed springs, while ensuring stable and safe product installation, the operator only needs to apply force to the mounting surface of one spring to achieve attitude changes, without requiring an additional power source. Attached Figure Description

[0025] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings:

[0026] Figure 1 This is a schematic diagram of the structure of the present invention;

[0027] Figure 2 This is a top view of the structure of the present invention;

[0028] Figure 3 This is a bottom-view structural diagram of the present invention;

[0029] The diagram shows:

[0030] Detailed Implementation

[0031] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0032] This invention provides an attitude adjustment device for polarity testing of satellite gyroscope products, such as... Figure 1-3As shown, the device includes a top plate 2, an attitude adjustment component, a mounting base plate 3, and a mounting adjustment component 4. The mounting adjustment component 4 is mounted on top of the top plate 2, and the mounting base plate 3 is connected to the top plate 2 via the attitude adjustment component. The mounting adjustment component 4 is used to connect to an external satellite gyroscope mounting plate or an external flywheel mounting plate, and the mounting adjustment component 4 can be adjusted according to different interfaces of different mounting plates. The mounting base plate 3 is fixed to the external satellite mounting plate with fasteners. The satellite gyroscope 1 under test is mounted to the attitude adjustment device for polarity testing of the satellite gyroscope product via the external satellite gyroscope mounting plate.

[0033] like Figure 2 As shown, the mounting and adjusting assembly 4 includes a first fastener 41, a second fastener 42, and an adjusting plate 43; one end of the adjusting plate 43 is rotatably mounted on the top plate 2 via the first fastener 41; that is, the first fastener 41 serves as a rotation axis, and the adjusting plate 43 is provided with a slot 431 along the length direction of the adjusting plate 43, and the second fastener 42 can slide along the slot 431; in a preferred embodiment, the slot 431 is located at the other end of the adjusting plate 43.

[0034] The ends of the first fastener 41 and the second fastener 42 are connected to the external satellite gyroscope mounting plate or the external flywheel mounting plate; both the first fastener 41 and the second fastener 42 are screws or bolts; in a preferred embodiment, both the first fastener 41 and the second fastener 42 are double-ended bolts, one end of which is threaded to the top plate 2, and the other end of which is connected to the gyroscope mounting plate or the external flywheel mounting plate. In another preferred embodiment, both the first fastener 41 and the second fastener 42 are ordinary screws or bolts, one end of which passes through the gyroscope mounting plate and the adjusting plate 43 and is mounted on the top plate 2. Specifically, the adjustment plate 43 is connected to the gyroscope mounting plate via two M5 screws. One M5 screw (first fastener 41) serves as the rotation center of the adjustment plate 43, while the other bolt (second fastener 42) can move within the slot 431. The mounting adjustment assembly 4 can be adjusted according to different gyroscope mounting interfaces. The first fastener 41 and the second fastener 42 can be adjusted between 100 and 500 mm, covering current gyroscope product interfaces and also applicable to products such as flywheels. In another preferred embodiment, both the first fastener 41 and the second fastener 42 are T-shaped screws, and the slot 431 is a T-shaped slide. The adjustment plate 43 rotates via the first fastener 41, and the second fastener 42 can move freely within the T-shaped slide to adapt to the satellite gyroscope mounting dimensions.

[0035] The adjustment plate 43 and the mounting base plate 3 are both made of aluminum alloy and have been anodized in real time.

[0036] like Figure 1-3As shown, the attitude adjustment assembly consists of multiple elastic elements 5 evenly distributed circumferentially along the top plate 2. In a preferred embodiment, the elastic element is a spring, with one end connected to the top plate 2 and the other end connected to the mounting base plate 3. Specifically, there are four springs, and the four adjusting springs are connected to the base plate using M4 bolts.

[0037] In a preferred embodiment, the attitude adjustment device for polarity testing of the satellite gyroscope product further includes anti-slip pads, which are evenly distributed on the bottom of the mounting base plate 3. In a preferred embodiment, as... Figure 3 The mounting base plate 3 shown is fixed to the satellite mounting plate by fasteners, such as connecting screws 31. In order to avoid damage to the thermal control paint and coating of the satellite mounting plate by the metal mounting base plate 3, the present invention adopts a method of pasting a 3mm thick anti-scratch rubber pad on the bottom surface of the mounting base plate 3 to ensure the safety of operation during the test process. In addition, the attitude adjustment device is connected to the satellite area ground through a dedicated grounding wire to ensure the safety of the product power-on test process.

[0038] In use, this device is mounted on the satellite mounting plate, and the external gyroscope is mounted on the adjustment assembly 4 via the external satellite gyroscope mounting plate. During the polarity test, by applying a certain concentrated force at the position corresponding to the spring on the top plate 2, the product will deflect at a certain angle when the adaptive adjustment plate 43 is installed. This deflection angle can be directly reflected in the gyroscope's data. By comparing it with the actual deflection direction, the correctness of the polarity can be determined.

[0039] The specific usage process of this invention will be described below.

[0040] Step 1: Adjust the interface size of the installation adjustment component 4 according to the installation interface size of the satellite gyroscope mounting plate to ensure that the interface size can effectively fix the satellite gyroscope mounting plate; and install the satellite gyroscope mounting plate.

[0041] Step 2: Secure the mounting base plate 3 by using four M5 screws (connecting screws 31) to fix the mounting base plate 3 onto the satellite mounting plate.

[0042] Step 3: Before installing the satellite gyroscope 1 to be tested, check the status of the top plate 2, springs, etc. After confirming that the status is correct, fix the gyroscope product to the satellite gyroscope mounting plate with the two locking screws that come with it, connect the grounding wire of the gyroscope product, and measure and confirm that the grounding resistance is ≤1 ohm.

[0043] Step 4: Connect other connectors to the gyroscope product and confirm the connector connection status;

[0044] Step 5: Power on the product and collect and confirm the initial angle of the gyroscope;

[0045] Step 6: Apply a certain torque to the top plate 2, collect and confirm the gyroscope angle, and determine the correctness of the gyroscope product installation polarity by comparing the consistency with the actual deflection angle.

[0046] This invention features a simple structure, convenient adjustment, strong adaptability, and good processing performance. The installation and adjustment component 4 can be adjusted according to the installation interface of different mounting plates, meeting the usage requirements of products with various installation interfaces. It can be further extended to the polarity testing needs of products such as flywheels. This invention uses four evenly distributed springs to form the attitude adjustment component, with a simple and compact configuration. Furthermore, through the stiffness design of the four evenly distributed springs, while ensuring stable and safe product installation, the operator only needs to apply force to one spring mounting surface to achieve attitude changes, without the need for an additional power source.

[0047] This invention features a simple structure, convenient adjustment, low cost, strong adaptability, and good processing performance. The adaptive adjustment plate can be adjusted according to different product installation interfaces, meeting the usage requirements of products with various installation interfaces and avoiding the use of large turntables in traditional testing processes.

[0048] Compared to CN202010261298.7A, this invention is a functional testing fixture with a compact structure, capable of quickly testing the polarity of gyroscope products using only a spring. Compared to CN103090863A, this invention achieves angular excitation for gyroscope polarity testing through simple platform deflection, with a simple structure and convenient operation. Compared to CN103116364A, this invention is a passive mechanism; by appropriately matching the spring stiffness, the platform angle can be tilted to achieve the angle excitation required for gyroscope polarity testing. Compared to CN205394469U, this invention achieves platform angle deflection through a spring, requiring no lubrication or rotating mechanism, with a simple structure and convenient operation.

[0049] In the description of this application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.

[0050] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. An attitude adjustment device for polarity testing of satellite gyroscope products, characterized in that, Includes a top plate (2), an attitude adjustment assembly, a mounting base plate (3), and a mounting adjustment assembly (4); The mounting adjustment assembly (4) is mounted on the top of the top plate (2), and the mounting base plate (3) is connected to the top plate (2) through the attitude adjustment assembly; The mounting adjustment component (4) is used to connect with an external satellite gyroscope mounting plate or an external flywheel mounting plate, and the mounting adjustment component (4) can be adjusted according to different interfaces of different mounting plates; The mounting adjustment assembly (4) includes a first fastener (41), a second fastener (42), and an adjustment plate (43); one end of the adjustment plate (43) is rotatably mounted on the top plate (2) via the first fastener (41); the adjustment plate (43) is provided with a slot (431) along the length direction of the adjustment plate (43), and the second fastener (42) can slide along the slot (431); The ends of the first fastener (41) and the second fastener (42) are connected to the external satellite gyroscope mounting plate or the external flywheel mounting plate. The attitude adjustment component consists of multiple elastic elements (5) evenly distributed circumferentially along the top plate (2).

2. The attitude adjustment device for polarity testing of satellite gyroscope products according to claim 1, characterized in that, Both the first fastener (41) and the second fastener (42) are screws or bolts.

3. The attitude adjustment device for polarity testing of satellite gyroscope products according to claim 1, characterized in that, The adjustment plate (43) and the mounting base plate (3) are both made of aluminum alloy and have been anodized in real time.

4. The attitude adjustment device for polarity testing of satellite gyroscope products according to claim 1, characterized in that, The elastic element (5) is a spring, one end of which is connected to the top plate (2), and the other end of which is connected to the mounting base plate (3).

5. The attitude adjustment device for polarity testing of satellite gyroscope products according to claim 1, characterized in that, It also includes anti-slip pads, which are evenly distributed on the bottom of the mounting base plate (3).

6. The attitude adjustment device for polarity testing of satellite gyroscope products according to claim 1, characterized in that, The bottom of the mounting plate (3) is covered with anti-scratch rubber pads.

7. The attitude adjustment device for polarity testing of satellite gyroscope products according to claim 4, characterized in that, The number of springs is 4.

8. The attitude adjustment device for polarity testing of satellite gyroscope products according to claim 4, characterized in that, The mounting base plate (3) is fixed to the external satellite mounting plate by fasteners.

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