Satellite-borne diffuse reflection sunlight calibration movable device

Abstract

The satellite-borne diffuse reflection sunlight calibration movable device provided by the invention not only can avoid the rotating risk of a moving part in a launching stage, but also can realize the light path on-off control under the condition that the calibration plate is fixed, meanwhile, the structure is simplified, the mass is reduced, and the long-life and high-reliability in-orbit calibration requirements of a satellite-borne optical instrument are met. Aiming at the situation that an observation window needs to be opened when a satellite-borne optical instrument carries out sunlight calibration observation on orbit, the invention designs a satellite-borne sunlight calibration observation window baffle moving part with a launching locking function, and the baffle is used for opening the observation window when the satellite-borne optical instrument needs to be calibrated; when the optical instrument completes sunlight calibration, the sunlight observation window is shielded. According to the movable part, the movable part is locked through the electromagnet which is powered on and locked, rotation of the movable part is avoided when a rocket is launched, and the electromagnet does not need to work again when in orbit. The invention provides full-period protection of transportation and on-orbit phases.

Description

Technical Field

[0001] This invention belongs to the field of optomechanical structure design, specifically relating to a spaceborne diffuse reflection solar calibration device. Background Technology

[0002] In existing on-orbit solar calibration technologies for spaceborne optical instruments, rotating calibration plates are commonly used to switch optical paths. For example, a spaceborne diffuse transmission edge calibration mechanism (CN114252152A) uses a stepper motor to drive an adapter plate, causing the primary / backup calibration plates to rotate in and out of a protective slot, thereby controlling whether sunlight shines on the calibration plate surface. This scheme adopts a structure where the rotation axis is parallel to the calibration plate surface, and a protective slot is designed to prevent the calibration plates from being directly exposed to sunlight when not calibrated. A counterweight copper block is also included to balance the center of gravity of the rotating components, and microswitches are used for limit switches.

[0003] However, the above technical solutions still have the following shortcomings: First, as a moving component, the calibration plate needs to form a cantilevered rotating body with the adapter plate, counterweight, etc., resulting in a large moment of inertia, which places high demands on the load-bearing capacity of the drive motor. Moreover, long-term rotation in orbit is prone to mechanical wear, affecting positioning accuracy and reliability. Second, the calibration plate is always exposed during rotation. Even with the protective groove design, it may still be exposed to stray light or temperature difference impact at the moment of switching, accelerating the performance degradation of the calibration plate. Third, the solution does not consider active locking during the launch phase and only relies on the motor to maintain torque, which poses a risk of rotation under rocket vibration environment. Fourth, the bearing system adopts a conventional support method and is not designed to adapt to axial thermal deformation caused by extreme temperature differences in space, which can easily lead to jamming or stress concentration. Fifth, the overall structure is relatively complex, and there is still room for improvement in integration and lightweighting. Summary of the Invention

[0004] To address the aforementioned technical problems, this invention provides a spaceborne solar calibration device with smaller rotational inertia, higher reliability, and stronger thermal adaptability. This invention offers a spaceborne diffuse reflection solar calibration device that avoids the risk of rotation of moving parts during launch, while enabling optical path control under fixed calibration plate conditions. It also simplifies the structure, reduces weight, and meets the long-life, high-reliability on-orbit calibration requirements of spaceborne optical instruments. Specifically, this invention addresses the need to open the observation window when spaceborne optical instruments perform on-orbit solar calibration observations. It designs a spaceborne solar calibration observation window baffle movable component with launch locking. When the spaceborne optical instrument needs calibration, the baffle opens the observation window; when the optical instrument completes solar calibration, it blocks the solar observation window. This movable component uses an energized locking electromagnet to lock the moving parts of the component, preventing rotation during rocket launch. The electromagnet does not need to operate while in orbit. This invention realizes a shutter-type solar calibration switch mechanism that transfers the moving parts from the calibration plate to the baffle, eliminating the need for precise movement of the calibration plate and reducing the requirements for accuracy and stability. It adopts the combined action of electromagnet launching and locking and baffle blocking to provide full-cycle protection during transportation and on-orbit phases. At the same time, a shaft structure is designed to address the extreme temperature differences in space.

[0005] To achieve the above objectives, the present invention adopts the following technical solution:

[0006] A spaceborne diffuse reflection solar calibration device includes:

[0007] The base support module includes a calibration chamber housing and a rotating shaft seat, a motor seat, and an electromagnet seat mounted on the calibration chamber housing;

[0008] The core calibration module includes a solar diffuser plate that is fixedly installed on the calibration chamber.

[0009] The drive transmission module includes a stepper motor with a planetary gear reducer mounted on a motor mount and an adapter connector connected to the output end of the stepper motor.

[0010] The shading execution module includes a solar calibration observation window baffle that is fixedly connected to the adapter connector. The solar calibration observation window baffle is configured to rotate relative to the solar diffuse reflector to open or block the calibration observation window.

[0011] The fixed-end shaft system support module includes a fixed-end bearing seat installed at one end of the rotating shaft system seat, a fixed-end angular contact ball bearing pair disposed in the fixed-end bearing seat, and a fixed-end shaft that mates with the fixed-end angular contact ball bearing pair. The fixed-end shaft is connected to the adapter connector.

[0012] The floating end shaft system support module includes a floating end bearing seat installed at the other end of the rotating shaft system seat, a pair of floating end angular contact ball bearings disposed in the floating end bearing seat, and a floating end shaft that mates with the pair of floating end angular contact ball bearings. The floating end shaft is connected to the adapter connector.

[0013] The locking and positioning module includes an electromagnet chuck installed on the baffle of the solar calibration observation window, an electromagnet base installed on the calibration chamber housing and corresponding to the position of the electromagnet chuck, a micro switch stop rod installed on the moving end shaft, and a micro switch that cooperates with the micro switch stop rod.

[0014] Furthermore, the outer ring of the fixed-end angular contact ball bearing pair is axially fixed to the fixed-end bearing seat through the bearing outer ring fixing pressure ring, and the inner ring of the fixed-end angular contact ball bearing pair is pre-tightened and positioned to the shaft shoulder of the fixed-end shaft through the inner ring fixing thread pressure ring.

[0015] Furthermore, the outer ring of the floating end angular contact ball bearing pair is not completely fixed axially relative to the floating end bearing housing to reserve axial floating clearance, and the inner ring of the floating end angular contact ball bearing pair is pre-tightened and positioned by the floating end inner ring fixing thread pressure ring and the shoulder of the floating end shaft.

[0016] Furthermore, the electromagnet base is configured to be energized during the rocket launch phase to attract the electromagnet chuck, thereby locking the solar calibration observation window baffle onto the calibration chamber housing.

[0017] Furthermore, the micro switch lever is configured to rotate synchronously with the movable end shaft and touch the micro switch, so as to position and limit the opening / closing position of the solar calibration observation window baffle.

[0018] Furthermore, the adapter connector is fixedly connected to the fixed end shaft and the moving end shaft by screws, and the solar calibration observation window baffle is fixedly connected to the adapter connector.

[0019] Furthermore, the stepper motor with planetary gear reducer is fixedly connected to the motor mount by screws, and the motor mount is fixedly connected to the calibration chamber housing by screws.

[0020] Furthermore, the fixed end bearing housing and the floating end bearing housing are respectively fixedly installed at both ends of the rotating shaft system housing by screws.

[0021] Furthermore, the base support module provides the assembly foundation for the entire device, the solar diffuse reflector of the calibration core module adopts a non-moving fixed installation method, and the solar calibration observation window baffle of the shading execution module is the only active moving component.

[0022] Furthermore, the solar calibration observation window baffle is provided with a weight reduction groove structure.

[0023] Beneficial effects:

[0024] 1. Significantly reduced moment of inertia: This invention replaces the calibration plate with a calibration observation window baffle. The calibration plate is always fixedly installed in the calibration chamber. The mass of the rotating part is reduced by about 60%, and the moment of inertia is significantly reduced. A smaller drive motor can be selected, reducing power consumption and mechanical wear.

[0025] 2. Active locking of the launch section: This invention innovatively adopts an energized locking electromagnet, which uses electromagnetic force to attract and lock the baffle during the rocket launch phase, completely eliminating the risk of rotation caused by vibration and impact; when the electromagnet is de-energized during operation in orbit, the position is fixed by relying on the torque maintained by the motor's own reducer, which has high reliability.

[0026] 3. Excellent thermal adaptability: The shaft system design of this invention adopts a segmented support structure combining a fixed-end angular contact ball bearing pair and a floating-end angular contact ball bearing pair. The fixed end achieves axial pre-tightening and positioning, while the floating end is reserved with axial floating space. This can effectively adapt to thermal expansion and contraction caused by temperature differences of more than ±100℃, avoid bearing jamming, and ensure rotational accuracy.

[0027] 4. Compact and lightweight structure: The present invention uses a stepper motor with an integrated planetary gear reducer, which shortens the axial dimension; the baffle adopts a weight-reducing groove design, which improves the specific stiffness, making the overall structure more compact and lighter.

[0028] 5. More stable calibration plate performance: Since the calibration plate is fixedly installed in this invention, there is no need to rotate it, which completely avoids problems such as mechanical stress, uneven lighting and friction contamination, and the calibration accuracy and lifespan are fundamentally guaranteed.

[0029] 6. Precise positioning: The micro switch lever of this invention is directly mounted on the movable end shaft and rotates synchronously with the baffle. High-precision positioning is achieved by touching the micro switch, which meets the alignment requirements of the calibration optical path. Attached Figure Description

[0030] Figure 1 This is an assembly diagram of a spaceborne diffuse reflection solar calibration device according to the present invention;

[0031] Figure 2 This is a schematic diagram illustrating the working principle of a spaceborne diffuse reflection solar calibration device according to the present invention; the left figure shows the open state, and the right figure shows the closed state.

[0032] Figure 3 This is a position axis diagram of a spaceborne diffuse reflection solar calibration device according to the present invention.

[0033] The attached figures are labeled as follows: 1-Calibration chamber housing; 2-Solar diffuse reflector; 3-Stepper motor with planetary gear reducer; 4-Motor base; 5-Rotating shaft base; 6-Adapter connector; 7-Solar calibration observation window baffle; 8-Electromagnet chuck; 9-Electromagnet base; 10-Micro switch stop lever; 11-Micro switch; 12-Fixed end angular contact ball bearing pair; 13-Fixed end bearing seat; 14-Inner ring fixing thread pressure ring; 15-Bearing outer ring fixing pressure ring; 16-Fixed end shaft; 17-Roaming end angular contact ball bearing pair; 18-Roaming end bearing seat; 19-Roaming end inner ring fixing thread pressure ring; 20-Roaming end shaft. Detailed Implementation

[0034] To make the objectives, technical solutions, and advantages of this invention clearer, the invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative and not intended to limit the invention. Furthermore, the technical features involved in the various embodiments of this invention described below can be combined with each other as long as they do not conflict with each other.

[0035] like Figure 1 As shown, a spaceborne diffuse reflection solar calibration device of the present invention includes a base support module, a calibration core module, a drive transmission module, a shading execution module, a fixed end shaft support module, a mobile end shaft support module, and a locking and positioning module.

[0036] The base support module consists of a calibration chamber housing 1, a rotating shaft seat 5, a motor seat 4, and an electromagnet seat 9. Serving as the assembly foundation for the entire device, it provides installation interfaces and structural support for the calibration plate, drive system, shaft system, and locking device, forming a modular integrated architecture.

[0037] The calibration core module consists only of the solar diffuse reflector 2. As the core component of the optical calibration function, it adopts a non-moving fixed installation method, which fundamentally avoids the mechanical stress, uneven illumination, and wear and contamination problems caused by traditional rotating mechanisms, ensuring calibration accuracy and lifespan.

[0038] The drive transmission module consists of a stepper motor 3 with a planetary gear reducer and an adapter connector 6. The stepper motor 3 with the planetary gear reducer provides rotational power, and the torque is increased and the size is reduced through the reducer; the adapter connector 6 transmits the torque to the solar calibration observation window baffle 7 to realize the shutter-type opening and closing action, which combines compactness and high reliability.

[0039] The shading execution module includes a solar calibration observation window baffle 7. As the only active moving component, it opens / blocks the calibration window by rotating, thus controlling the light path. Its moment of inertia is reduced by about 60% compared to the traditional calibration plate rotation scheme, significantly reducing the driving burden.

[0040] The fixed-end shaft support module includes a fixed-end angular contact ball bearing pair 12, a fixed-end bearing housing 13, a fixed-end shaft 16, an inner ring fixing threaded pressure ring 14, and a bearing outer ring fixing pressure ring 15. It achieves precise axial positioning and pre-tightening of the shaft system, ensuring rotational accuracy, while also bearing the main axial loads.

[0041] The floating end shaft support module consists of a floating end angular contact ball bearing pair 17, a floating end bearing housing 18, a floating end shaft 20, and a floating end inner ring fixing threaded pressure ring 19. The floating end and the fixed end form a segmented support structure. The outer ring of the bearing is not completely fixed to reserve an axial floating clearance, which can effectively adapt to thermal expansion and contraction caused by temperature differences of ±100℃ or more in the space and prevent jamming.

[0042] The locking and positioning module includes an electromagnet chuck 8, an electromagnet base 9, a micro switch lever 10, and a micro switch 11. During the launch phase, it is energized to engage the solar calibration observation window baffle 7, actively locking it to eliminate the risk of rotation. The micro switch 11, in conjunction with the micro switch lever 10, precisely limits the opening / closing position of the solar calibration observation window baffle 7, meeting the requirements for optical path alignment.

[0043] Specifically, the solar diffuser 2 is mounted on the calibration chamber housing 1, the stepper motor 3 with a planetary gear reducer is mounted on the motor mount 4, the rotating shaft mount 5 has a pair of axial fixed-end angular contact ball bearings 12 mounted near the motor end, and a pair of axial sliding angular contact ball bearings mounted away from the motor end. The adapter 6 is connected and fixed to the movable end shaft 20 and the fixed end shaft 16. The solar calibration observation window baffle 7 is fixed to the adapter 6, thereby allowing rotation to open or block the solar calibration observation window. The electromagnet chuck 8 is mounted on the solar calibration observation window baffle 7, and the electromagnet seat 9 is mounted on the calibration chamber housing 1. When the rocket is launched, the electromagnet seat 9 is energized to hold the electromagnet chuck 8 tightly, ensuring that the moving parts of the moving components do not rotate relative to the calibration chamber housing 1 during launch. The micro switch lever 10 is mounted on the movable end shaft 20, and the micro switch 11 is activated by the micro switch lever 10 to achieve positioning and limiting of the moving parts.

[0044] like Figure 2 As shown (left image shows the open state, right image shows the closed state), when the spaceborne optical instrument needs to perform solar calibration, the solar calibration observation window baffle 7 opens, allowing sunlight to illuminate the solar diffuse reflector 2, and the light diffusely reflected by the solar diffuse reflector 2 can then enter the optical payload observation window. When the spaceborne optical instrument needs to perform nadir observation, the solar calibration observation window baffle 7 opens, allowing light from the Earth and the atmosphere to enter the optical payload observation window.

[0045] like Figure 3As shown, the fixed-end bearing housing 13 and the sliding-end bearing housing 18 are mounted on the rotating shaft system seat 5. A pair of fixed-end angular contact ball bearings 12 are installed inside the fixed-end bearing housing 13. The outer ring of the fixed-end angular contact ball bearing pair is axially fixed by the bearing outer ring fixing ring 15 and the fixed-end bearing housing 13. The inner ring of the fixed-end angular contact ball bearing pair 12 is pre-tightened and positioned by the inner ring fixing threaded ring 14 and the shoulder of the fixed-end shaft 16. A pair of floating-end angular contact ball bearings 17 are installed inside the floating-end bearing housing 18. The outer ring of the floating-end angular contact ball bearing pair 17 is not axially fixed to ensure thermal deformation adaptability and assembly adaptability. The inner ring of the floating-end angular contact ball bearing pair 17 is pre-tightened and positioned by the floating-end inner ring fixing threaded ring 19 and the shoulder of the floating-end shaft 20. The adapter connector 6 is connected and fixed to the solar calibration observation window baffle 7 at both ends of the fixed-end shaft 16 and the floating-end shaft 20 by screws.

[0046] This invention utilizes a stepper motor with a planetary gear reducer to drive the rotating shaft system and the calibration window baffle to rotate. Two microswitches are used to position and limit the rotating parts. The stepper motor is mounted on a motor mount, which is connected to the calibration box by screws. The calibration box cover is connected to the calibration box by screws and has a light-shielding groove designed on it to protect the diffuse transmission calibration plate from sunlight, which would affect the calibration effect.

[0047] In summary, this invention employs two sets of angular contact ball bearings to support the shaft rotation, providing strong vibration resistance. Simultaneously, with one end fixed and the other movable, it exhibits good axial thermal shrinkage adaptability. An energized locking electromagnet is used to lock the moving parts during rocket launch, and the moving parts can be fixed in position by the motor's own locking torque while in orbit. A stepper motor with a planetary gear reducer is used to drive the rotation of the moving parts, significantly reducing the motor's size. The solar panel incorporates a weight-reducing groove design, giving it high specific stiffness.

[0048] This invention addresses the need for solar calibration of spaceborne optical instruments during orbital operation. A stepper motor with an integrated planetary gear reducer drives a shaft system containing a solar calibration observation window baffle to rotate, opening and closing the window. When the window is open, sunlight illuminates a diffuse reflector, which then reflects the light into the optical instrument. An electromagnet locks the moving parts of the instrument, preventing rotation during rocket launch. By designing a combination of fixed-end angular contact ball bearings and sliding-end ball bearings, and separating the two sections, the invention achieves good axial thermal deformation, convenient assembly, and excellent rotational accuracy and support rigidity.

Claims

1. A spaceborne diffuse reflection solar calibration device, characterized in that, include: The base support module includes a calibration chamber housing and a rotating shaft seat, a motor seat, and an electromagnet seat mounted on the calibration chamber housing; The core calibration module includes a solar diffuser plate that is fixedly installed on the calibration chamber. The drive transmission module includes a stepper motor with a planetary gear reducer mounted on a motor mount and an adapter connector connected to the output end of the stepper motor. The shading execution module includes a solar calibration observation window baffle that is fixedly connected to the adapter connector. The solar calibration observation window baffle is configured to rotate relative to the solar diffuse reflector to open or block the calibration observation window. The fixed-end shaft system support module includes a fixed-end bearing seat installed at one end of the rotating shaft system seat, a fixed-end angular contact ball bearing pair disposed in the fixed-end bearing seat, and a fixed-end shaft that mates with the fixed-end angular contact ball bearing pair. The fixed-end shaft is connected to the adapter connector. The floating end shaft system support module includes a floating end bearing seat installed at the other end of the rotating shaft system seat, a pair of floating end angular contact ball bearings disposed in the floating end bearing seat, and a floating end shaft that mates with the pair of floating end angular contact ball bearings. The floating end shaft is connected to the adapter connector. The locking and positioning module includes an electromagnet chuck installed on the baffle of the solar calibration observation window, an electromagnet base installed on the calibration chamber housing and corresponding to the position of the electromagnet chuck, a micro switch stop rod installed on the moving end shaft, and a micro switch that cooperates with the micro switch stop rod.

2. The spaceborne diffuse reflection solar calibration device according to claim 1, characterized in that, The outer ring of the fixed-end angular contact ball bearing pair is axially fixed to the fixed-end bearing seat through the bearing outer ring fixing pressure ring, and the inner ring of the fixed-end angular contact ball bearing pair is pre-tightened and positioned to the shaft shoulder of the fixed-end shaft through the inner ring fixing thread pressure ring.

3. The spaceborne diffuse reflection solar calibration device according to claim 1, characterized in that, The outer ring of the floating end angular contact ball bearing pair is not completely fixed axially relative to the floating end bearing housing to reserve axial floating clearance. The inner ring of the floating end angular contact ball bearing pair is pre-tightened and positioned by the floating end inner ring fixing thread pressure ring and the shoulder of the floating end shaft.

4. The spaceborne diffuse reflection solar calibration device according to claim 1, characterized in that, The electromagnet base is configured to be energized during rocket launch to attract the electromagnet chuck, thereby locking the solar calibration observation window baffle onto the calibration chamber.

5. The spaceborne diffuse reflection solar calibration device according to claim 1, characterized in that, The micro switch lever is configured to rotate synchronously with the movable end shaft and touch the micro switch to limit the opening / closing position of the solar calibration observation window baffle.

6. The spaceborne diffuse reflection solar calibration device according to claim 1, characterized in that, The adapter connector is fixedly connected to the fixed end shaft and the moving end shaft by screws, and the solar calibration observation window baffle is fixedly connected to the adapter connector.

7. The spaceborne diffuse reflection solar calibration device according to claim 1, characterized in that, The stepper motor with planetary gear reducer is fixedly connected to the motor mount by screws, and the motor mount is fixedly connected to the calibration chamber by screws.

8. The spaceborne diffuse reflection solar calibration device according to claim 1, characterized in that, The fixed-end bearing housing and the floating-end bearing housing are respectively fixedly installed at both ends of the rotating shaft system housing by screws.

9. The spaceborne diffuse reflection solar calibration device according to claim 1, characterized in that, The base support module provides the assembly foundation for the entire device. The solar diffuse reflector of the calibration core module is installed in a non-moving fixed manner. The solar calibration observation window baffle of the shading execution module is the only active moving component.

10. The spaceborne diffuse reflection solar calibration device according to any one of claims 1 to 9, characterized in that, The solar calibration observation window baffle is equipped with a weight reduction groove structure.

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