A spacecraft two-dimensional pointing mechanism simulator

Abstract

This invention provides a spacecraft two-dimensional pointing mechanism simulator, comprising: a bracket; a drive assembly fixedly mounted on the bracket; a support housing fixedly mounted on the side of the bracket away from the drive assembly, the support housing and the side of the bracket forming a cavity; an angle disk rotatably mounted in the cavity, the first surface of the angle disk having angle scales; an angle pointer mounted on the rotation axis of the drive assembly, the angle pointer including a pointer body and an arc-shaped scale; and a polarity pointer assembly mounted on the angle disk, the polarity pointer assembly including a polarity pointer body configured to rotate along its own axis to adjust the positive and negative polarity display states; the simulator is configured to: initialize the simulator by adjusting the rotation position of the angle disk and the polarity pointer body; and control the drive assembly to rotate for testing, determine the polarity by the position of the angle pointer relative to the polarity pointer body, and read the current angle value by the cooperation of the angle pointer and the arc-shaped scale.

Description

Technical Field

[0001] This invention belongs to the field of aerospace electromechanical technology, and in particular relates to a simulator for a two-dimensional pointing mechanism of a spacecraft. Background Technology

[0002] With the rapid development of modern aerospace technology, space exploration activities are becoming more frequent and the missions more complex. The flexibility of the payloads and data transmission systems carried by spacecraft is also increasing, requiring different space pointing or target tracking pointing tasks according to mission requirements. This has led to a wide variety of spacecraft servo systems (including two-dimensional pointing mechanisms and their controllers).

[0003] During the development phase of servo systems, two-dimensional pointing mechanisms are often used as loads to debug controllers. Furthermore, during spacecraft electrical performance testing, two-dimensional pointing mechanisms are also needed as loads to simplify testing methods.

[0004] Different servo systems have varying mission requirements, functionalities, signal interfaces, rotation angle ranges, and load physical characteristics, resulting in significant differences and poor versatility in their two-dimensional pointing mechanisms and controllers. Using different two-dimensional pointing mechanisms or actual space products for controller debugging and testing based on these differences not only increases the development cycle and cost of the servo system but also leads to unnecessary resource waste. Therefore, mechanism simulators are generally used to equivalently replace real mechanisms, meeting the needs of controller debugging and testing, as well as spacecraft testing.

[0005] Due to inherent mechanical deviations, assembly errors, and differences in the initial zero-point angle definition of the mechanism's angle sensor, angular deviations exist between the mechanical zero point of different mechanisms and the electrical zero point of the angle sensor. These deviations are typically corrected via software. Furthermore, due to variations in installation conditions on spacecraft, the rotational polarity definitions of different mechanisms may differ, which is also defined via software within the controller. While existing technologies include mechanism simulators, they lack functions such as rotational polarity display and adjustment, and high-precision angle reading and adjustment. Moreover, the presence of limit blocks or the inability of cables to withstand unlimited torsion limits their ability to achieve a full rotation, thus failing to fully meet testing requirements and significantly reducing their practicality. Summary of the Invention

[0006] In view of this, the present invention provides a two-dimensional pointing mechanism simulator for spacecraft, which has the functions of rotation polarity display and polarity adjustment, as well as initial angle adjustment and high-precision angle reading.

[0007] To achieve the above objectives, the technical solution of the present invention is as follows: A spacecraft two-dimensional pointing mechanism simulator, comprising: The bracket has two bracket mounting holes. The drive assembly is fixedly installed inside the mounting holes of the bracket; A support housing is fixedly installed on the side of the bracket away from the drive assembly, and the support housing and the side of the bracket form a cavity; An angle disk is rotatably mounted in the cavity, and the first surface of the angle disk has angle markings. An angle pointer is mounted on the rotation shaft of the drive assembly. The angle pointer includes a pointer body and an arc-shaped scale. A polarity pointer assembly is mounted on the angle dial. The polarity pointer assembly includes a polarity pointer body, which is configured to rotate n×180° along its own axis to adjust the positive and negative polarity display status. The simulator is configured as follows: by adjusting the rotation position of the angle disk and the polarity pointer body, the 0 mark value of the angle disk is aligned with the 0 mark line of the angle pointer to initialize the simulator; and the controller controls the rotation test of the drive component, the polarity is determined by the position of the angle pointer relative to the polarity pointer body, and the current angle value is read by the cooperation of the angle pointer and the arc-shaped scale.

[0008] Preferably, the polarity pointer body includes a positive mark and a negative mark for indicating positive and negative polarity, and the positive mark and the negative mark are symmetrically arranged on both sides of the polarity pointer body.

[0009] Preferably, the second surface of the angle dial has a first flange, and the polarity pointer assembly further includes a polarity pointer rod and an elastic element. One end of the polar pointer rod is connected to the polar pointer body, and the polar pointer rod is provided with a protrusion structure. The first flange is provided with a groove that matches the shape and size of the protrusion structure. The elastic element is sleeved on the polarity pointer rod, and the elastic element is used to press the protrusion structure into the groove of the angle plate to limit the non-adjustable rotation of the polarity pointer body; The second surface is the surface opposite to the first surface.

[0010] Preferably, it further includes a hand-tightening screw, which is installed in a threaded hole in the side wall of the support housing; the hand-tightening screw is used to press against the angle plate in the tightened state to constrain the rotation of the angle plate within the support housing.

[0011] Preferably, the side surface of the angle disc is roughened.

[0012] Preferably, the center of the angle pointer, the center of the angle disk, and the center of the polarity pointer body coincide.

[0013] Preferably, the side wall of the support housing is provided with a notch for adjusting the angle dial and the polarity pointer.

[0014] Preferably, it further includes an end cap, which is fixedly connected to the support housing and is used to close the cavity of the support housing.

[0015] Preferably, the end cap is made of a transparent material.

[0016] Preferably, it further includes a conductive slip ring, which is mounted on the end cap; The rotor lead of the conductive slip ring is connected to the rotor lead of the drive assembly, and the stator lead of the conductive slip ring passes through the bracket and is connected to the electrical connector of the simulator.

[0017] Because the present invention adopts the above technical solution, it has the following advantages and positive effects compared with the prior art: This invention features a polarity pointer mounted on an angle dial, capable of rotating n×180° along its own axis. Operators can directly determine the polarity of the current rotation direction by observing the physical position of the pointer (e.g., positive / negative markings). When the rotation polarity defined by the controller is opposite to the actual polarity of the mechanical structure, physical correction can be achieved by rotating the polarity pointer without software modification. This avoids test failures caused by incorrect polarity definitions and significantly improves the simulator's adaptability and accuracy in testing with different controllers.

[0018] This invention, by incorporating a rotatable and adjustable angle dial and polarity pointer assembly, allows operators to manually rotate the angle dial and polarity pointer assembly before testing to precisely align the 0° mark of the dial with the 0° mark of the angle pointer. This mechanical zeroing method achieves initial angle adjustment, while the angle scale on the angle dial, combined with the use of an arc-shaped scale, enables precise reading of the current angle value. This solves the problem of large reading errors caused by the lack of mechanical zeroing functionality in existing simulators, meeting the high-precision angle calibration requirements in spacecraft testing.

[0019] This invention enables the rotating shaft of the drive component to drive the angle pointer to rotate at any angle, even continuously in one direction. This solves the problem in the prior art that "the cable cannot withstand infinite torsion, resulting in a lack of full-circle rotation capability," allowing the simulator to more realistically simulate the full range of motion of the spacecraft's two-dimensional pointing mechanism during on-orbit operation, greatly improving the comprehensiveness of the test and the practicality of the simulator.

[0020] This invention integrates the polarity pointer assembly, angle disk, and angle pointer onto the same support housing, and utilizes the rotation of the angle disk and the polarity pointer assembly to achieve rapid adjustment of polarity and zero position. This design eliminates the need for complex disassembly tools, allowing for quick simulator initialization setup on-site, significantly reducing test preparation time. Compared to existing solutions whose versatility is limited to electrical interface conversion, this invention goes a step further in terms of physical layer versatility for mechanical interfaces and signal logic, possessing greater practical value. Attached Figure Description

[0021] Figure 1 This is a schematic diagram of a spacecraft two-dimensional pointing mechanism simulator according to an embodiment of the present invention. Figure 1 ; Figure 2 This is a schematic diagram of a spacecraft two-dimensional pointing mechanism simulator according to an embodiment of the present invention. Figure 2 ; Figure 3 This is a schematic diagram of a spacecraft two-dimensional pointing mechanism simulator according to an embodiment of the present invention. Figure 3 ; Figure 4 This is a schematic diagram of the structure of the second surface of the angle disk and the polarity pointer assembly in the spacecraft two-dimensional pointing mechanism simulator according to an embodiment of the present invention; Figure 5 This is a schematic diagram of the polarity pointer component in a spacecraft two-dimensional pointing mechanism simulator according to an embodiment of the present invention; Figure 6 This is a vertical cross-sectional view of a spacecraft two-dimensional pointing mechanism simulator according to an embodiment of the present invention; Figure 7 for Figure 6 Enlarged view of section A; Figure 8 This is a schematic diagram of the angle pointer in a spacecraft two-dimensional pointing mechanism simulator according to an embodiment of the present invention; Figure 9 This is a schematic diagram of the supporting shell in a spacecraft two-dimensional pointing mechanism simulator according to an embodiment of the present invention; Figure 10 This is a schematic diagram of the position of a pointer at a certain angle in a spacecraft two-dimensional pointing mechanism simulator according to an embodiment of the present invention.

[0022] Reference numerals: 1-Bracket; 2-Drive assembly; 3-Hand screw; 4-Angle dial; 41-First surface; 42-Second surface; 43-First flange; 5-Angle pointer; 51-Pointer body; 52-Arc-shaped scale; 6-Conductive slip ring; 7-Support housing; 71-Notch; 72-Side wall threaded hole; 73-Second flange; 8-End cap; 81-Third flange; 9-Polar pointer assembly; 91-Polar pointer body; 92-Polar pointer rod; 93-Elastic element; 94-Adjusting screw; 95-Protrusion structure; 10-Electrical connector; 11-Wire hole. Detailed Implementation

[0023] The following detailed description, in conjunction with the accompanying drawings and specific embodiments, provides a more detailed account of a two-dimensional pointing mechanism simulator for spacecraft proposed in this invention. The advantages and features of this invention will become clearer from the following description.

[0024] See Figure 1-10 As shown, a spacecraft two-dimensional pointing mechanism simulator is provided. The simulator simulates two independent axis systems of a two-dimensional mechanism and serves as the object for controller debugging and testing, and spacecraft test control. The simulator includes: a bracket 1, a drive assembly 2, a support shell 7, an angle disk 4, an angle pointer 5, and a polarity pointer assembly 9. The bracket 1 is used to support the entire simulator. The bracket 1 has two bracket 1 mounting holes. The two drive components 2 are fixedly installed in the two bracket 1 mounting holes respectively. The installation and fixing of the two drive components 2 are consistent and distributed on the left and right sides of the bracket 1. The mounting holes on the left and right sides of the bracket 1 are labeled with the axis names X-axis and Y-axis respectively.

[0025] The support housing 7 is fixedly installed on the side of the bracket 1 away from the drive assembly 2. The support housing 7 and the side of the bracket 1 form a cavity to accommodate components such as the angle disk 4. The angle disk 4 is rotatably installed in the cavity of the support housing 7. The first surface 41 of the angle disk 4 has angle scales and corresponding angle scale characters. The angle pointer 5 is installed on the rotation shaft of the drive assembly 2. The angle pointer 5 includes a pointer body 51 and an arc-shaped scale 52. The angle can be roughly read by the direction of the pointer body 51 on the angle disk 4. The angle can be read precisely by aligning the arc-shaped scale 52 with the scale of the angle disk 4. The polarity pointer assembly 9 is installed on the angle disk 4. The polarity pointer assembly 9 includes a polarity pointer body 91. The polarity pointer body 91 is configured to rotate n×180° along its own axis to adjust the positive and negative polarity display state. For example, when the polarity pointer body 91 rotates 180°, the position of its polarity mark will be interchanged, thereby switching the polarity mark at the physical level. The simulator is configured as follows: by adjusting the rotation position of the angle disk 4 and the polarity pointer body 91, the 0 mark value of the angle disk 4 is aligned with the 0 mark line of the angle pointer 5 to initialize the simulator; and the controller controls the rotation test of the drive component 2, the polarity is determined by the position of the angle pointer 5 relative to the polarity pointer body 91, and the precise value of the current angle is read by the cooperation of the angle pointer 5 and the arc-shaped scale 52.

[0026] This embodiment, by incorporating a rotatable and adjustable angle disk 4 and a polarity pointer assembly 9, allows operators to manually rotate the angle disk 4 and polarity pointer assembly 9 before testing to precisely align their 0° scale line with the 0° scale line of the angle pointer 5. This mechanical zeroing method achieves initial angle adjustment, while the angle scale on the angle disk 4, combined with the use of the arc-shaped scale 52, enables precise reading of the current angle value. This solves the problem of large reading errors caused by the lack of mechanical zeroing functionality in existing simulators, meeting the high-precision angle calibration requirements in spacecraft testing.

[0027] This embodiment enables the rotation shaft of the drive component 2 to drive the angle pointer 5 to rotate at any angle, or even rotate continuously in one direction. This solves the problem that "the cable cannot withstand infinite torsion, resulting in a lack of full-circle rotation capability," allowing the simulator to more realistically simulate the full range of motion of the spacecraft's two-dimensional pointing mechanism during on-orbit operation, greatly improving the comprehensiveness of the test and the practicality of the simulator.

[0028] This embodiment integrates the polarity pointer assembly 9, angle disk 4, and angle pointer 5 onto the same support housing 7, and utilizes the rotation of the angle disk 4 and the polarity pointer assembly 9 to achieve rapid adjustment of polarity and zero position. This design eliminates the need for complex disassembly tools, allowing for quick simulator initialization setup on-site, significantly reducing test preparation time. Compared to existing solutions whose versatility is limited to electrical interface conversion, this invention further enhances the versatility of the mechanical interface and signal logic physical layer, possessing greater practical value.

[0029] like Figure 4-7 As shown, in order to display the polarity more intuitively, the polarity pointer body 91 includes a positive mark and a negative mark for indicating positive and negative polarity, and the positive mark and the negative mark are symmetrically arranged on both sides of the polarity pointer body 91.

[0030] like Figure 4-7 As shown, in order to achieve reliable locking and convenient adjustment of the polarity pointer body 91, the polarity pointer assembly 9 also includes a polarity pointer rod 92 and an elastic element 93. The second surface 42 of the angle disk 4 has a first flange 43, and the second surface 42 is the surface opposite to the first surface 41. One end of the polar pointer rod 92 is connected to the polar pointer body 91, and the other end of the polar pointer rod 92 has an adjusting screw 94. The adjusting screw 94 has an internal hexagonal groove. The polar pointer rod 92 is provided with a protrusion structure 95, and the first flange 43 is provided with a groove that matches the shape and size of the protrusion structure 95. The elastic element 93 is sleeved on the polarity pointer rod 92. The elastic element 93 is used to press the protrusion structure 95 into the groove of the angle plate 4 to limit the non-adjustable rotation of the polarity pointer body 91. If the polarity pointer body 91 needs to rotate relative to the angle plate 4, that is, when the polarity needs to be adjusted, the operator uses an external tool, such as an Allen wrench, to press and rotate the adjusting screw 94, causing the protrusion structure 95 to disengage from the groove. After the polarity pointer body 91 rotates 180°, the external tool acting on the adjusting screw 94 will, due to the elasticity of the elastic element 93, cause the protrusion structure 95 to re-engage into the corresponding groove, completing the polarity switch.

[0031] like Figure 6-7 As shown, to ensure reliable locking and rotation of the angle disk 4, the simulator also includes a hand screw 3, which is installed in the threaded hole 72 on the side wall of the support housing 7. The hand screw 3 is used to tighten the angle disk 4, thereby constraining its rotation within the support housing 7. When the hand screw 3 is tightened, its end presses against the side of the angle disk 4, using friction to constrain the rotation of the angle disk 4 within the support housing 7. When the hand screw 3 is loosened, the angle disk 4 can rotate freely, facilitating zero-position alignment.

[0032] Preferably, the inner wall of the support housing 7 is provided with a second flange 73 to restrict the rotation of the angle disk 4.

[0033] Furthermore, the simulator also includes an end cap 8, which is fixedly connected to the support housing 7. The end cap 8 is used to seal the cavity of the support housing 7 and protect the internal components. The inner wall of the end cap 8 is provided with a third flange 81. When the angle disk 4 is locked, the third flange 81 is in contact with the first surface 41 of the angle disk 4, and the second flange 73 is in contact with the second surface 42 of the angle disk 4. When the manual screw is tightened on the angle disk 4, the angle disk 4 is constrained between the second flange 73 of the support housing 7 and the third flange 81 of the end cap 8. In specific applications, there is an axial gap of about 0.02mm between the angle disk 4 and the second flange 73 and the third flange 81. The outer diameter of the angle disk 4 is the same as the inner diameter of the support housing 7, so that the angle disk 4 can be rotated and adjusted between the support housing 7 and the end cap 8.

[0034] To facilitate operator observation of the internal state without disassembling the end cap 8, the end cap 8 is made of a transparent material, such as acrylic or transparent polycarbonate. Operators can directly observe the position of the angle pointer 5 relative to the polarity pointer body 91 and the scale of the angle dial 4 through the end cap 8 without removing or assembling the end cap 8.

[0035] To facilitate the operator's direct rotation of the angle disk 4 with their fingers, the side surface (i.e., cylindrical surface) of the angle disk 4 is roughened, for example by knurling or sandblasting, to increase the friction between the fingers and the angle disk 4.

[0036] To ensure accurate angle reading, the center of the angle pointer 5, the center of the angle disk 4, and the center of the polarity pointer body 91 are aligned. All three are aligned with the rotation center of the drive assembly 2's rotating shaft, eliminating eccentricity errors.

[0037] To facilitate adjustment by the operator, the side wall of the support housing 7 is provided with a notch 71 for adjusting the angle dial 4 and the polarity pointer. The notch 71 penetrates the side wall of the support housing 7 and communicates with the internal cavity, allowing the operator's fingers or tools to be inserted to contact and adjust the angle dial 4 and the polarity pointer assembly 9 (such as by operating the adjusting screw 94).

[0038] In order to achieve unlimited full-circle rotation of the drive component 2, the simulator also includes a conductive slip ring 6, which is mounted on the end cap 8; The rotor wire of the conductive slip ring 6 is connected to the rotor wire of the drive assembly 2. When the rotor of the drive assembly 2 rotates, the rotor of the conductive slip ring 6 rotates accordingly, ensuring that the rotor wire does not get tangled.

[0039] The stator lead of the conductive slip ring 6 passes through the bracket 1 and connects to the electrical connector 10 of the simulator. The bracket 1 has a wire hole 11, through which the stator lead of the conductive slip ring 6 passes and connects to the electrical connector 10 of the simulator. Through the conductive slip ring 6, the rotor of the drive assembly 2 can achieve continuous rotation at any angle, or even infinite rotation in one direction, without the problem of cable breakage, greatly expanding the testing range of the simulator.

[0040] The initialization settings and workflow of the simulator in this embodiment are as follows: Initialization settings: a. Polarity Adjustment: First, rotate the drive assembly 2 to its defined 0° position using the controller. Observe whether the rotation direction matches the polarity (positive or negative) indicated by the current polarity pointer body 91. If not, loosen the hand screw 3 and move the angle dial 4 at the notch 71 of the support housing 7 to expose the polarity pointer assembly 9 at the notch 71. Press and rotate the polarity adjustment screw 94 with a tool to rotate the polarity pointer body 91 180°. Then remove the tool applied to the adjustment screw 94. Due to the elasticity of the elastic element 93, the protrusion structure 95 on the polarity pointer rod 92 re-engages in the groove and locks in place, thus switching the polarity display state.

[0041] b. Zero Alignment: Continue to move the angle dial 4 until the 0° mark of the angle dial 4 is aligned with the tip of the pointer body 51 or the 0° mark of the arc-shaped scale 52. Then tighten the hand screw 3 to lock the angle dial 4.

[0042] Testing and reading: The controller controls the drive component 22 to rotate, and the angle pointer 55 rotates accordingly.

[0043] a. Polarity determination: The polarity is determined based on the position of the angle pointer 5 relative to the polarity pointer body 91. For example, when the angle pointer 5 stops in the direction indicated by the positive mark on the polarity pointer body 91, the current angle is positive; otherwise, it is negative.

[0044] b. Angle reading: First, read the integer degree based on the position of the pointer body 51 of the angle pointer 5 on the angle dial 4; then, observe whether the lines of the arc-shaped scale 52 (e.g., a 50-degree scale) on the angle pointer 5 are aligned with the lines on the angle dial 4, and read the fine degree. The final angle value is the integer part plus the fine part.

[0045] by Figure 10 As shown, the angle dial 4 has a scale every 1°, and the angle pointer 5 has a 50-degree scale 52. That is, the 49° range on the angle dial 4 is divided into 50 equal parts on the 52. Every time the angle pointer 5 rotates 0.02°, a line on the 52 aligns with a line on the angle dial 4. Figure 10 The angle pointer 5 is on the positive arrow side of the polarity pointer, indicating the current angle is positive; the pointer body 51 points between the 24° and 25° scales; furthermore, the 28th division of the arc-shaped scale 52 is aligned with the scale of the angle dial 4, thus obtaining the current angle as 24 + 0.02 × 28 = 24.56°. Using the solution of this invention, the existing angle reading accuracy of 1° can be improved to 0.1° (10-degree arc-shaped scale 52), 0.05° (20-degree arc-shaped scale 52), 0.02° (50-degree arc-shaped scale 52), etc.

[0046] In summary, the embodiments of the present invention, through the 180° adjustable structure of the polarity pointer body 91, the zero-position adjustment function of the angle disk 4, the high-precision reading function of the arc scale 52, and the infinite rotation capability of the conductive slip ring 6, effectively overcome the defects of the prior art in which the simulator cannot display polarity, cannot adjust the zero position, cannot read with high precision, and cannot rotate a full circle. It has extremely high practical value and versatility.

[0047] The embodiments of the present invention have been described in detail above with reference to the accompanying drawings, but the present invention is not limited to the above embodiments. Even if various changes are made to the present invention, if these changes fall within the scope of the claims of the present invention and their equivalents, they shall still fall within the protection scope of the present invention.

Claims

1. A simulator for a two-dimensional pointing mechanism of a spacecraft, characterized in that, include: The bracket has two bracket mounting holes. The drive assembly is fixedly installed inside the mounting holes of the bracket; A support housing is fixedly installed on the side of the bracket away from the drive assembly, and the support housing and the side of the bracket form a cavity; An angle disk is rotatably mounted in the cavity, and the first surface of the angle disk has angle markings. An angle pointer is mounted on the rotation shaft of the drive assembly. The angle pointer includes a pointer body and an arc-shaped scale. A polarity pointer assembly is mounted on the angle dial. The polarity pointer assembly includes a polarity pointer body, which is configured to rotate n×180° along its own axis to adjust the positive and negative polarity display status. The simulator is configured to initialize by adjusting the rotation position of the angle disk and the polarity pointer body; The controller controls the rotation test of the drive component, determines the polarity by the position of the angle pointer relative to the polarity pointer body, and reads the current angle value by cooperating with the arc-shaped scale.

2. The spacecraft two-dimensional pointing mechanism simulator according to claim 1, characterized in that, The polarity pointer body includes a positive mark and a negative mark for indicating positive and negative polarity, and the positive mark and the negative mark are symmetrically arranged on both sides of the polarity pointer body.

3. The spacecraft two-dimensional pointing mechanism simulator according to claim 1 or 2, characterized in that, The second surface of the angle dial has a first flange, and the polarity pointer assembly further includes a polarity pointer rod and an elastic element. One end of the polar pointer rod is connected to the polar pointer body, and the polar pointer rod is provided with a protrusion structure. The first flange is provided with a groove that matches the shape and size of the protrusion structure. The elastic element is sleeved on the polarity pointer rod, and the elastic element is used to press the protrusion structure into the groove of the angle plate to limit the non-adjustable rotation of the polarity pointer body; The second surface is the surface opposite to the first surface.

4. The spacecraft two-dimensional pointing mechanism simulator according to claim 1, characterized in that, It also includes a hand-tightening screw, which is installed in a threaded hole in the side wall of the support housing; the hand-tightening screw is used to press against the angle plate in the tightened state to constrain the rotation of the angle plate within the support housing.

5. The spacecraft two-dimensional pointing mechanism simulator according to claim 1 or 4, characterized in that, The sides of the angle disc are roughened.

6. The spacecraft two-dimensional pointing mechanism simulator according to claim 1, characterized in that, The center of the angle pointer, the center of the angle dial, and the center of the polarity pointer body coincide.

7. The spacecraft two-dimensional pointing mechanism simulator according to claim 1, characterized in that, The side wall of the support housing is provided with a notch for adjusting the angle dial and the polarity pointer.

8. The spacecraft two-dimensional pointing mechanism simulator according to claim 1, characterized in that, It also includes an end cap, which is fixedly connected to the support housing and is used to close the cavity of the support housing.

9. The spacecraft two-dimensional pointing mechanism simulator according to claim 8, characterized in that, The end cap is made of a transparent material.

10. The spacecraft two-dimensional pointing mechanism simulator according to claim 8, characterized in that, It also includes a conductive slip ring, which is mounted on the end cap; The rotor lead of the conductive slip ring is connected to the rotor lead of the drive assembly, and the stator lead of the conductive slip ring passes through the bracket and is connected to the electrical connector of the simulator.

Images