Spaceflight single-shaft small mechanism measurement circle grating shaft system device

Abstract

The utility model discloses a kind of aerospace single-shaft small mechanism measurement circle grating shafting devices, device includes mounting bracket, bearing mounting seat is fixed on it;Driving shaft, in bearing mounting seat, the outside of driving shaft is connected with bearing mounting seat through contact bearing;Circle grating mounting shaft, with driving shaft fixed connection, and located in mounting bracket, the end of circle grating mounting shaft is connected with circle grating;Reading head, symmetrically set on mounting bracket, and located in the opposite side of circle grating;Adapter shaft, set in the one end of driving shaft away from mounting bracket;Control device, set in the outside of bearing mounting seat, with reading head electric connection.After the device is connected with solar panel driving mechanism, the driving force of solar panel driving mechanism is used to drive the device synchronous rotation, in the process of rotation, the reading head located in the opposite side of circle grating can accurately read speed stability value and angle precision value in time, to improve the efficiency and accuracy of measurement.

Description

Technical Field

[0001] This utility model belongs to the field of aerospace single-axis small mechanism measurement technology, specifically relating to an aerospace single-axis small mechanism measurement circular grating axis system device. Background Technology

[0002] In the aerospace field, solar panel drive mechanisms and antenna rotation mechanisms have strict requirements for the smoothness of the rotation process and the accuracy when rotating to a specific angle. However, the current acceptance measurement methods for these two types of indicators are not only complicated, but also unreliable, which brings many challenges to the smooth progress of aerospace engineering.

[0003] In existing technologies, to measure the speed stability of a single-axis rotating mechanism, a fiber optic gyroscope is typically installed at one end of the mechanism, and the evaluation is based on the gyroscope parameters. However, this method involves many variables that significantly affect the reliability of the test results. Firstly, the fiber optic gyroscope itself may have internal problems, such as component aging or performance instability, which can interfere with the accurate measurement of speed stability. Secondly, the proper installation of the fiber optic gyroscope is also crucial; deviations in the installation position or inaccurate installation angles can lead to distorted measurement data, failing to accurately reflect the speed stability of the single-axis rotating mechanism.

[0004] For measuring the angular accuracy of aerospace single-axis rotating mechanisms, existing technology involves installing a docking fixture at one end of the shaft to fix a 23-sided prism. During measurement, a light tube is aligned with the 23-sided prism, and then the prism is rotated at the same intervals set by the drive software in the single-axis rotating mechanism until it reaches 360°. The accuracy of the angular rotation value given by the motor drive software is judged by comparing the mean square value of all the angles that need to be adjusted when the light tube is readjusted at each same interval. However, this testing method has significant drawbacks. In the initial preparation stage, different types of single-axis rotating mechanisms require re-fabrication of the corresponding fixtures for mounting the 23-sided prism according to their own interfaces. Moreover, the installation requirements for the 23-sided prism are extremely high, requiring professional calibration personnel to use an adjustment tower to ensure that the measured mechanism remains coaxial with the 23-sided prism. This places extremely high demands on the technical level and operational experience of the professionals. In addition, the initial operation of the positive light tube is extremely complicated and requires specific personnel with rich experience in optical assembly and calibration. This not only wastes a lot of parts processing costs, but also consumes a lot of time and manpower, seriously affecting measurement efficiency and the progress of aerospace engineering.

[0005] In summary, existing measurement methods for the speed stability and angular accuracy of single-axis rotation mechanisms in aerospace have many drawbacks and cannot meet the requirements of the aerospace field for measurement accuracy and efficiency. Therefore, developing a more reliable and efficient measurement method is of great practical significance. Utility Model Content

[0006] The purpose of this invention is to provide a device for measuring the circular grating axis system of aerospace single-axis small mechanisms, in order to solve the technical defects in the existing measuring devices and methods for measuring the speed stability and angular accuracy of aerospace single-axis rotating mechanisms, which cannot meet the requirements of the aerospace field for measurement accuracy and efficiency.

[0007] To achieve the above objectives, the present invention adopts the following technical solution:

[0008] A single-axis small-mechanism measurement circular grating axis system device for aerospace applications, comprising:

[0009] Mounting bracket, on which bearing mounting seats are fixed;

[0010] An active rotating shaft is disposed in the bearing mounting base, and the outer side of the active rotating shaft is connected to the bearing mounting base through a contact bearing;

[0011] A circular grating mounting shaft is fixedly connected to an active rotating shaft and is located in the mounting frame. A circular grating is connected to the end of the circular grating mounting shaft.

[0012] The reading heads are symmetrically arranged on the mounting bracket and located on opposite sides of the circular grating;

[0013] The adapter shaft is located at the end of the drive shaft furthest from the mounting bracket.

[0014] The control device is located on the outside of the bearing mounting seat and is electrically connected to the reading head.

[0015] Furthermore, the bearing mounting base has a hollow internal structure;

[0016] The contact bearings are symmetrically arranged in the hollow structure, and the active rotating shaft is installed between the two contact bearings.

[0017] Furthermore, the bearing mounting base has a ring-shaped structure.

[0018] Furthermore, the adapter shaft has a horizontal end and a vertical end, and the horizontal end and the vertical end are an integral structure;

[0019] The horizontal end is located in the bearing mounting base and is bolted to the drive shaft, while the end of the vertical end extends to the outside of the bearing mounting base.

[0020] Furthermore, both the horizontal and vertical ends of the adapter shaft coincide with the axial direction of the active rotating shaft.

[0021] Furthermore, the mounting bracket has an L-shaped structure, with a mounting hole on its longer end, and the circular grating mounting shaft is located in the mounting hole.

[0022] Furthermore, the end of the adapter shaft is provided with a coupling, which is used to connect the solar panel drive mechanism.

[0023] Furthermore, the controller is equipped with a display panel, which is used to display the speed stability data and rotation angle accuracy data of the solar panel drive mechanism.

[0024] Furthermore, the bearing mounting base has detachable legs at opposite ends on its outer side, and the legs are fixedly connected to the top of the mounting bracket.

[0025] Furthermore, the support leg is connected to the mounting bracket by screws.

[0026] Compared with the prior art, the present invention has the following beneficial effects:

[0027] After the adapter shaft in the device is connected to the solar panel drive mechanism or the antenna rotation mechanism, the device is driven to rotate synchronously by the driving force of the solar panel drive mechanism or the antenna rotation mechanism. During the rotation, the reading heads located on opposite sides of the circular grating can read the speed stability value and angle accuracy value in a timely and accurate manner, thereby improving the efficiency and accuracy of the measurement. Attached Figure Description

[0028] To more clearly illustrate the technical solutions of the embodiments of this utility model, the drawings used in the embodiments will be briefly introduced below. It should be understood that the following drawings only show some embodiments of this utility model and should not be regarded as a limitation on the scope. For those skilled in the art, other related drawings can be obtained based on these drawings without creative effort.

[0029] Figure 1 A three-dimensional schematic diagram of a single-axis small mechanism measuring circular grating axis system device for aerospace applications provided by this utility model;

[0030] Figure 2 A cross-sectional schematic diagram of a single-axis small mechanism measuring circular grating axis system device for aerospace applications provided by this utility model;

[0031] Figure 3 A schematic diagram of the operation of a single-axis small mechanism measuring circular grating axis system device for aerospace applications provided by this utility model;

[0032] The components include: 1. Mounting bracket; 2. Bearing mounting seat; 3. Drive shaft; 4. Adapter shaft; 5. Circular grating; 6. Reading head; 7. Contact bearing; 8. Circular grating mounting shaft; 9. Coupling; 10. Solar panel drive mechanism. Detailed Implementation

[0033] To make the objectives, technical solutions, and advantages of the embodiments of this utility model clearer, the technical solutions of the embodiments of this utility model will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of this utility model, and not all embodiments. The components of the embodiments of this utility model described and shown in the accompanying drawings can generally be arranged and designed in various different configurations.

[0034] Therefore, the following detailed description of the embodiments of the present invention provided in the accompanying drawings is not intended to limit the scope of the claimed invention, but merely to illustrate selected embodiments of the invention. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without inventive effort are within the scope of protection of the present invention.

[0035] It should be noted that similar labels and letters in the following figures indicate similar items. Therefore, once an item is defined in one figure, it does not need to be further defined and explained in subsequent figures.

[0036] In the description of the embodiments of this utility model, it should be noted that if terms such as "upper," "lower," "horizontal," or "inner" indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, or the orientation or positional relationship commonly used when the utility model product is in use, they are only for the convenience of describing the utility model 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, and therefore should not be construed as a limitation on the utility model. Furthermore, terms such as "first" and "second" are only used to distinguish descriptions and should not be construed as indicating or implying relative importance.

[0037] Furthermore, the use of the term "horizontal" does not imply that the component must be absolutely horizontal, but rather that it can be slightly tilted. For example, "horizontal" simply means that its direction is more horizontal than "vertical," and does not mean that the structure must be completely horizontal, but can be slightly tilted.

[0038] In the description of the embodiments of this utility model, it should also be noted that, unless otherwise explicitly specified and limited, the terms "set," "install," "connect," and "link" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model according to the specific circumstances.

[0039] In the aerospace field, solar panel drive mechanisms and antenna rotation mechanisms, when driving the solar panels and antennas to rotate, have stringent requirements for the smoothness of the rotation process and the accuracy at specific angles. These mechanisms need to operate stably for extended periods in the space environment; any minute speed fluctuations or angular deviations can lead to malfunctions in the spacecraft. However, current acceptance measurement methods for these two types of indicators are not only complex in operation but also difficult to guarantee the reliability of the measurement results, posing a serious challenge to the smooth progress of aerospace engineering.

[0040] Existing measurement technologies face two major bottlenecks. Firstly, in velocity stability measurement, fiber optic gyroscopes are commonly used. This method carries a significant risk of systematic errors. On one hand, the performance stability of the gyroscope itself is difficult to guarantee; on the other hand, even minor deviations during installation can distort the measurement data. More importantly, the gyroscope measurement results require complex algorithmic processing to obtain velocity stability parameters, introducing additional error factors. Secondly, in angular accuracy measurement, current technology relies on a 23-sided prism combined with a light tube. This approach is extremely cumbersome. Each change in the rotating mechanism requires the redesign and manufacture of a dedicated prism mounting fixture, and the installation process demands precise calibration by specialized optical technicians. Furthermore, significant time is spent aligning the light tube before measurement. The entire measurement process is time-consuming and labor-intensive, severely impacting the schedule of aerospace engineering projects. Moreover, this measurement method is highly sensitive to environmental vibrations and temperature changes, frequently resulting in unstable measurement results in practical engineering applications.

[0041] To address the technical deficiencies mentioned in the background section, this embodiment provides a single-axis small-mechanism measurement circular grating axis system device for aerospace applications. The invention will now be described in further detail with reference to the accompanying drawings:

[0042] like Figures 1-3As shown, a bearing mounting seat 2 is fixed on the mounting frame 1, and the active rotating shaft 3 is located in the bearing mounting seat 2. The outer side of the active rotating shaft 3 is connected to the bearing mounting seat 2 through a contact bearing 7. The circular grating mounting shaft 8 is fixedly connected to the active rotating shaft 3 and is located in the mounting frame 1. A circular grating 5 is connected to the end of the circular grating mounting shaft 8. The reading head 6 is symmetrically arranged on the mounting frame 1 and located on opposite sides of the circular grating 5. The adapter shaft 4 is located at the end of the active rotating shaft 3 away from the mounting frame 1. The control device is located on the outside of the bearing mounting seat 2 and is electrically connected to the reading head 6.

[0043] The mounting bracket 1 is used to support the bearing mounting seat 2. Specifically, it can be implemented using a metal frame. Its rigid design can reduce vibration interference during the measurement process. The circular grating mounting shaft 8 refers to the shaft that fixes the circular grating 5. It is coaxially connected with the active rotating shaft 3 to ensure the consistency of the angle measurement reference. The reading head 6 is a sensor for detecting the circular grating signal. It eliminates eccentricity error through differential signal.

[0044] Specifically, the active shaft 3 rotates within the bearing mounting seat 2 via the contact bearing 7, driving the circular grating mounting shaft 8 to rotate synchronously. Symmetrically arranged reading heads 6 continuously collect the grating 5's engraving signals, converting angle changes into electrical signals that are transmitted to the control device. The adapter shaft 4 transmits the torque of the solar panel drive mechanism 10 to the active shaft 3, forming a complete kinematic chain. The control device analyzes the time-series data of the reading head 6 signals to calculate the rotational speed stability index and evaluates the rotational angle repeatability accuracy by statistically analyzing the angle encoding values ​​of the circular grating 5.

[0045] Compared with existing technologies, this device directly uses the circular grating 5 to measure the motion parameters of the rotating shaft, eliminating the errors caused by the installation deviation of the fiber optic gyroscope. The symmetrical layout of the reading head 6 effectively suppresses the measurement noise caused by the eccentricity of the circular grating 5. Compared with single-point detection, it improves the reliability of the data. The adapter shaft 4 replaces the prism tooling, eliminating the need for customized processing and precision calibration, significantly shortening the test preparation cycle. This enables the synchronous measurement of the speed stability and angular accuracy of the solar panel drive mechanism 10, avoiding systematic errors caused by the cooperation of multiple devices, and providing an efficient and reliable testing method for aerospace institutions' acceptance testing.

[0046] Furthermore, the bearing mounting base 2 has a hollow structure inside, with the contact bearings 7 symmetrically arranged in the hollow structure, and the drive shaft 3 is installed between the two contact bearings 7.

[0047] The hollow structure refers to the through-cavity formed inside the bearing mounting base 2, which can be implemented using an annular or cylindrical structure. Its internal space accommodates the contact bearings 7, the drive shaft 3, and the adapter shaft 4. Specifically, the hollow bearing mounting base 2 provides installation space for the contact bearings 7 through its internal cavity. Two contact bearings 7 are fixed at opposite ends of the cavity, and the drive shaft 3 passes through the inner rings of the two contact bearings 7, forming a tight fit. When the adapter shaft 4 rotates, the symmetrically arranged contact bearings 7 synchronously bear the radial force, effectively suppressing the radial runout of the drive shaft 3 during high-speed operation. This ensures that the drive shaft 3 remains in a stable mechanical equilibrium state during rotation, eliminating measurement errors caused by insufficient support stiffness. This effectively improves the stability of the drive shaft 3's operation and ensures the accuracy of the circular grating 5's measurement data.

[0048] In practice, the bearing mounting base 2 has a ring-shaped structure, which allows the radial force borne by the active rotating shaft 3 during rotation to be uniformly transmitted to the contact bearing 7, effectively suppressing the sway of the active rotating shaft 3 and providing a more stable reference support for the measurement of the circular grating 5, thereby improving the reliability of the measurement of the rotational accuracy of the solar panel drive mechanism 10.

[0049] In this solution, the adapter shaft 4 has a horizontal end and a vertical end. The horizontal end and the vertical end are an integral structure. The horizontal end is located in the bearing mounting seat 2 and is connected to the drive shaft 3 by bolts. The end of the vertical end extends to the outside of the bearing mounting seat 2. Through the integrally formed adapter shaft 4 structure, it can directly adapt to different external mechanism interfaces, eliminate the angular deviation caused by multi-stage transmission, and simplify the assembly process by bolt connection.

[0050] Specifically, the horizontal and vertical ends of the adapter shaft 4 are both axially aligned with the active shaft 3, so that the adapter shaft 4 does not require additional adjustment during installation. It can be secured with bolts to ensure the coaxiality of the vertical end with the active shaft 3, reducing assembly difficulty and time cost.

[0051] Furthermore, the mounting bracket 1 has an L-shaped structure with a mounting hole on its longer end. The circular grating mounting shaft 8 is located in the mounting hole. When the active rotating shaft 3 drives the circular grating mounting shaft 8 to rotate, the mounting hole mechanically limits the radial movement of the circular grating mounting shaft 8.

[0052] Furthermore, a coupling 9 is provided at the end of the adapter shaft 4. The coupling 9 is used to connect the solar panel drive mechanism 10. The coupling 9 is directly connected to the output shaft of the solar panel drive mechanism 10 through a standardized interface. When the solar panel drive mechanism 10 rotates, the coupling 9 synchronously transmits power to the adapter shaft 4. At the same time, the circular grating 5 on the circular grating mounting shaft 8 collects rotation angle data in real time through the reading head 6. The control device directly analyzes the stability of the rotation speed and the accuracy of the angle based on the data.

[0053] Furthermore, the controller is equipped with a display panel, which displays the speed stability data and rotation angle accuracy data of the solar panel drive mechanism 10. When the solar panel drive mechanism 10 drives the active shaft 3 to rotate via the adapter shaft 4, the circular grating mounting shaft 8 rotates synchronously. The reading heads 6 on both sides collect the displacement signal of the circular grating 5 in real time and transmit it to the controller. After the controller converts the displacement signal into speed stability data and rotation angle accuracy data, it directly outputs the data visually through the display panel, making it convenient for operators to view in real time.

[0054] In this design, the two opposite ends of the outer side of the bearing mounting base 2 are detachably connected with support legs, which are fixedly connected to the top of the mounting bracket 1; specifically, the support legs are connected to the mounting bracket 1 by screws.

[0055] In addition, such as Figure 2 As shown, the clamping amount of the contact bearing 7 consists of the outer ring clamping amount and the inner ring clamping amount. The outer ring clamping amount is calculated from the hole depth L1 at the bearing housing mounting seat 2, the total thickness L2 of the outer ring of the pair of angular contact bearings 7, and the outer pressure ring L3 of the contact bearing 7, and its value = L2 + L3 - L1. The inner ring clamping amount is calculated from the shaft platform height H1 at the main rotating shaft 3, the total thickness H2 of the inner ring of the pair of angular contact bearings 7, and the clamping boss H3 of the circular grating mounting shaft 8, and its value = H2 + H3 - H1. The clamping amount is adjusted by modifying the height L3 of the clamping boss of the outer pressure ring of the contact bearing 7 and the clamping of the circular grating mounting shaft 8. The height H3 of the boss changes; therefore, in the design, the dimensions L3 of the outer pressure ring of the contact bearing 7 and the height H3 of the pressure boss of the main rotating shaft 3 determine the accuracy of the installation of the circular grating shaft system. Through simulation analysis, a range of dimensions L3 and H3 are obtained. Then, two parts with different dimensions L3 and H3 within the range of dimensions obtained from the simulation analysis are actually machined. The shaft system wobble and shaft system rotation accuracy are verified by actual testing with a level and optical tube, thus obtaining a definite dimension L3 and H3, which ensures the accuracy of the installation of the circular grating shaft system itself.

[0056] Finally, it should be noted that the above embodiments are only used to illustrate the technical solution of this utility model and not to limit its protection scope. Although the utility model has been described in detail with reference to the above embodiments, those skilled in the art should understand that after reading this utility model, they can still make various changes, modifications or equivalent substitutions to the specific implementation of the utility model, but these changes, modifications or equivalent substitutions are all within the protection scope of the pending claims of the utility model.

Claims

1. A single-axis small-mechanism measuring circular grating axis system device for aerospace applications, characterized in that, include: Mounting bracket, on which bearing mounting seats are fixed; An active rotating shaft is disposed in the bearing mounting base, and the outer side of the active rotating shaft is connected to the bearing mounting base through a contact bearing; A circular grating mounting shaft is fixedly connected to an active rotating shaft and is located in the mounting frame. A circular grating is connected to the end of the circular grating mounting shaft. The reading heads are symmetrically arranged on the mounting bracket and located on opposite sides of the circular grating; The adapter shaft is located at the end of the drive shaft furthest from the mounting bracket. The control device is located on the outside of the bearing mounting seat and is electrically connected to the reading head.

2. The aerospace single-axis small mechanism measuring circular grating axis device according to claim 1, characterized in that, The bearing mounting base has a hollow internal structure; The contact bearings are symmetrically arranged in the hollow structure, and the active rotating shaft is installed between the two contact bearings.

3. The aerospace single-axis small mechanism measuring circular grating axis device according to claim 2, characterized in that, The bearing mounting base has a ring-shaped structure.

4. The aerospace single-axis small mechanism measuring circular grating axis device according to claim 1, characterized in that, The adapter shaft has a horizontal end and a vertical end, and the horizontal end and the vertical end are an integral structure. The horizontal end is located in the bearing mounting base and is bolted to the drive shaft, while the end of the vertical end extends to the outside of the bearing mounting base.

5. The aerospace single-axis small mechanism measuring circular grating axis device according to claim 4, characterized in that, Both the horizontal and vertical ends of the adapter shaft coincide with the axial direction of the drive shaft.

6. The aerospace single-axis small mechanism measuring circular grating axis device according to claim 1, characterized in that, The mounting bracket has an L-shaped structure, with a mounting hole on its longer end, and the circular grating mounting shaft is located in the mounting hole.

7. The aerospace single-axis small mechanism measuring circular grating axis device according to claim 1, characterized in that, The adapter shaft is provided with a coupling at its end, which is used to connect the solar panel drive mechanism.

8. The aerospace single-axis small mechanism measuring circular grating axis device according to claim 1, characterized in that, The control device is equipped with a display panel, which is used to display the speed stability data and rotation angle accuracy data of the solar panel drive mechanism.

9. The aerospace single-axis small mechanism measuring circular grating axis device according to claim 1, characterized in that, The bearing mounting base has detachable legs at opposite ends on its outer side, and the legs are fixedly connected to the top of the mounting frame.

10. The aerospace single-axis small mechanism measuring circular grating axis system device according to claim 9, characterized in that, The legs are connected to the mounting bracket by screws.

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