A collapsible and expandable secondary mirror support structure

Abstract

The present invention relates to the field of space optical technology, and particularly to a foldable and deployable secondary mirror support structure, which includes a first-stage folding and locking mechanism, a first-stage support beam, a second-stage folding and locking mechanism, a second-stage support beam, and a secondary mirror mounting seat; the secondary mirror mounting seat is fixedly connected to the second-stage support beam, and the second-stage support beam realizes relative rotational movement around the end of the first-stage support beam through the second-stage folding and locking mechanism; the first-stage support beam is connected to the frame through the first-stage folding and locking mechanism, and the first-stage support beam can perform one-dimensional rotational movement relative to the frame; the first-stage folding and locking mechanism and the second-stage folding and locking mechanism rotate synchronously and in opposite directions. The secondary mirror support structure of the present invention can be used for the foldable and deployable space telescope, and has a secondary mirror assembly with a large folding ratio, so that the secondary mirror assembly occupies less space in the folded state, better meeting the strict restrictions of the rocket launch envelope size on the volume of the space telescope system.

Description

Technical Field

[0001] The present invention relates to the field of space optical technology, and particularly to a deployable secondary mirror support structure. Background Art

[0002] Space telescopes play a crucial role in astronomical observations. One of the main methods to improve the resolution of telescope systems is to increase the aperture and focal length. For ultra-large space telescopes, the limitation of the launch vehicle envelope volume severely restricts the increase of the telescope aperture. To address this issue, domestic and foreign scholars have proposed the on-orbit deployment + / technical solution, that is, the telescope is launched in a folded state and sent into a predetermined orbit, and each module of the telescope is deployed on orbit and finally reaches the working state after on-orbit debugging. The on-orbit deployable space telescope has become one of the methods to solve the launch problem of ultra-large aperture space optical telescopes and is an important development direction for ultra-large space telescopes. And the on-orbit deployable space telescope generally involves the deployment of the secondary mirror support structure. Therefore, the deployable secondary mirror support structure has relatively important engineering practical significance.

[0003] The deployable secondary mirror support structure generally uses a deployment mechanism to control the folding and deployment of the secondary mirror support structure. It is in a folded state during launch and unfolds after entering the orbit, and reaches the performance requirements of the telescope's on-orbit operation after on-orbit debugging. In addition, some micro-nano remote sensing satellites also widely use the deployable secondary mirror support structure, which greatly improves the space utilization rate inside the launch vehicle fairing. Currently, the deployable and foldable secondary mirror support structure mainly adopts a deployable tripod-type four-bar linkage driven by a stepper motor. This secondary mirror deployment method has the characteristics of simplicity and reliability. However, this type of structure only changes the placement method of the secondary mirror support truss and cannot provide a large folding ratio, so it cannot be applied to some space telescope systems with strict requirements for volume envelope dimensions. Summary of the Invention

[0004] To solve the above problems, the present invention provides a deployable and foldable secondary mirror support structure, which has a large folding ratio, occupies less space in the folded state, and can better meet the strict restrictions of the rocket launch envelope size on the volume of the space telescope system.

[0005] The present invention provides a deployable and foldable secondary mirror support structure, which includes a primary folding and locking mechanism, a primary support beam, a secondary folding and locking mechanism, a secondary support beam, and a secondary mirror mounting seat;

[0006] The secondary mirror mount is fixedly connected to the secondary support beam, and the secondary support beam realizes relative rotational movement around the end of the primary support beam through a secondary folding and locking mechanism; the primary support beam is connected to the frame through the primary folding and locking mechanism, and the primary support beam can perform one-dimensional rotational movement relative to the frame; the primary folding and locking mechanism and the secondary folding and locking mechanism rotate synchronously and in opposite directions.

[0007] Preferably, the primary folding and locking mechanism includes a first driving motor, a first fixed-end base, a first rotating shaft, a first reducer, a first rotating-end base, a first nut, a first screw, a first travel switch, and a first locking motor;

[0008] The first driving motor is installed on the first fixed-end base, the output shaft of the first driving motor is connected to the input shaft of the first reducer, and the output shaft of the first reducer is connected to the first rotating shaft; the first rotating-end base is connected to the first rotating shaft, and the first nut is fixed on the first rotating-end base; the first locking motor is arranged on the first fixed-end base, the first screw is connected to the first locking motor, and the first travel switch is arranged on the first fixed-end base.

[0009] Preferably, the secondary folding and locking mechanism includes a second driving motor, a second fixed-end base, a second rotating shaft, a second reducer, a second rotating-end base, a second nut, a second screw, a second travel switch, and a second locking motor;

[0010] The second driving motor is installed on the second fixed-end base, the output shaft of the second driving motor is connected to the second reducer, and the output shaft of the second reducer is connected to the second rotating shaft; the second rotating-end base is connected to the second rotating shaft, and the second nut is fixed on the second rotating-end base; the second locking motor is arranged on the second fixed-end base, the second screw is connected to the second locking motor, and the second travel switch is arranged on the second fixed-end base.

[0011] Preferably, the primary support beam includes a first joint, a first carbon fiber beam, and a second joint, and the first joint and the second joint are respectively located at both ends of the first carbon fiber beam; the first joint is used to provide a connection interface with the first rotating-end base, and the second joint is used to provide a connection interface with the second fixed-end base

[0012] Preferably, both the first joint and the second joint are fixedly connected to the first carbon fiber beam by an adhesive bonding method.

[0013] Preferably, the secondary support beam includes a third joint, a second carbon fiber beam, and an adapter; the third joint and the adapter are respectively located at two ends of the second carbon fiber beam; the third joint is used to provide a connection interface with the second rotating end base, and the adapter is used to provide a connection interface with the secondary mirror mounting seat.

[0014] Preferably, both the third joint and the adapter are fixedly connected to the second carbon fiber beam by an adhesive method.

[0015] Preferably, the secondary mirror mounting seat is fixedly connected to the primary support beam and is used to provide a mounting interface for the secondary mirror assembly.

[0016] The secondary mirror support structure of the present invention can be used for the foldable deployment of a space telescope and has a secondary mirror assembly with a large fold-out ratio, so that the secondary mirror assembly occupies less space in the folded state, better meeting the strict restrictions of the rocket launch envelope size on the volume of the space telescope system. Description of the Drawings

[0017] Figure 1 is a schematic structural diagram of the unfolded state of the foldable and deployable secondary mirror support structure in the specific embodiment of the present invention;

[0018] Figure 2 is a schematic structural diagram of the folded state of the foldable and deployable secondary mirror support structure in the specific embodiment of the present invention;

[0019] Figure 3 is a schematic structural diagram of the primary folding and locking mechanism in the specific embodiment of the present invention;

[0020] Figure 4 is a sectional view of the primary support beam structure in the specific embodiment of the present invention;

[0021] Figure 5 is a sectional view of the secondary support beam structure in the specific embodiment of the present invention;

[0022] Figure 6 is a schematic structural diagram of the secondary mirror mounting seat in the specific embodiment of the present invention.

[0023] Reference Signs:

[0024] 1. Primary folding and locking mechanism, 11. First driving motor, 12. First fixed end base, 13. First rotating shaft, 14. First reducer, 15. First rotating end base, 16. First nut, 17. First screw rod, 18. First travel switch, 19. First locking motor, 2. Primary support beam, 21. First joint, 22. First carbon fiber beam, 23. Second joint, 3. Secondary folding and locking mechanism, 4. Secondary support beam, 41. Third joint, 42. Second carbon fiber beam, 43. Adapter, 5. Secondary mirror mounting seat. Detailed implementation mode

[0025] In order to make the objectives, technical solutions and advantages of the present invention more clear and understandable, the present invention will be further described in detail below in conjunction with the accompanying drawings and specific embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and do not constitute a limitation to the present invention.

[0026] It should be understood that although terms such as first, second, and third may be used in the detailed implementation mode of the present invention, these should not be limited to these terms. These terms are only used to distinguish. For example, without departing from the scope of the detailed implementation mode of the present invention, the first may also be referred to as the second, and similarly, the second may also be referred to as the first.

[0027] As Figure 1 and Figure 2 shown, they are respectively the structural schematic diagram of the unfolded state and the folded state of the foldable and deployable secondary mirror support structure in the detailed implementation mode of the present invention. It can be seen from the figure that the foldable and deployable secondary mirror support structure provided in the detailed implementation mode of the present invention includes a first-stage folding and locking mechanism 1, a first-stage support beam 2, a second-stage folding and locking mechanism 3, a second-stage support beam 4, and a secondary mirror mounting seat 5; the secondary mirror mounting seat 5 is fixedly connected to the second-stage support beam 4, and the second-stage support beam 4 realizes relative rotational movement around the end of the first-stage support beam 2 through the second-stage folding and locking mechanism 3; the first-stage support beam 2 is connected to the frame through the first-stage folding and locking mechanism 1, and the first-stage support beam 2 can perform one-dimensional rotational movement relative to the frame; the first-stage folding and locking mechanism 1 and the second-stage folding and locking mechanism 3 rotate synchronously and in opposite directions; specifically, the frame is an external connection structure outside the secondary mirror support structure, and the frame may specifically refer to the main load-bearing structure of the telescope main payload.

[0028] In a specific implementation mode, as Figure 3As shown in the figure, it is a schematic structural diagram of the first-stage folding and locking mechanism in the specific embodiment of the present invention. It can be seen from the figure that the first-stage folding and locking mechanism 1 includes a first driving motor 11, a first fixed-end base 12, a first rotating shaft 13, a first reducer 14, a first rotating-end base 15, a first nut 16, a first screw rod 17, a first travel switch 18, and a first locking motor 19; the first driving motor 11 is installed on the first fixed-end base 12, the output shaft of the first driving motor 11 is connected to the input shaft of the first reducer 14, and the output shaft of the first reducer 14 is connected to the first rotating shaft 13; the first rotating-end base 15 is connected to the first rotating shaft 13, and the first nut 16 is fixed on the first rotating-end base 15; the first locking motor 19 is arranged on the first fixed-end base 12, the first screw rod 16 is connected to the first locking motor 19, and the first travel switch 18 is arranged on the first fixed-end base 12.

[0029] In a specific embodiment, the second-stage folding and locking mechanism 3 has basically the same structure as the first-stage folding and locking structure 1 (not shown in specific drawings), and specifically includes a second driving motor, a second fixed-end base, a second rotating shaft, a second reducer, a second rotating-end base, a second nut, a second screw rod, a second travel switch, and a second locking motor; the second driving motor is installed on the second fixed-end base, the output shaft of the second driving motor is connected to the second reducer, and the output shaft of the second reducer is connected to the second rotating shaft; the second rotating-end base is connected to the second rotating shaft, and the second nut is fixed on the second rotating-end base; the second locking motor is arranged on the second fixed-end base, the second screw rod is connected to the second locking motor, and the second travel switch is arranged on the second fixed-end base; specifically, the installation interface of the second fixed-end base is different from that of the first fixed-end base 12.

[0030] In a specific embodiment, as Figure 4 shown, it is a sectional view of the first-stage support beam structure in the specific embodiment of the present invention. It can be seen from the figure that the first-stage support beam 2 includes a first joint 21, a first carbon fiber beam 22, and a second joint 23. The first joint 21 and the second joint 23 are respectively located at both ends of the carbon fiber beam 22; the first joint 21 is used to provide a connection interface with the first rotating-end base 12, and the second joint 23 is used to provide a connection interface with the second fixed-end base; preferably, both the first joint 21 and the second joint 23 are fixedly connected to the first carbon fiber beam 22 by an adhesive bonding method.

[0031] In a specific embodiment, as Figure 5As shown in the figure, it is a sectional view of the secondary support beam structure in the specific embodiment of the present invention. It can be seen from the figure that the secondary support beam 4 includes a third joint 41, a second carbon fiber beam 42, and an adapter 43; the third joint 41 and the adapter 43 are respectively located at both ends of the second carbon fiber beam 42; the third joint 41 is used to provide a connection interface with the second rotating end base, and the adapter 43 is used to provide a connection interface with the secondary mirror mounting seat 5. Preferably, both the third joint 41 and the adapter 43 are fixedly connected to the second carbon fiber beam 42 by bonding.

[0032] In a specific embodiment, as Figure 6 shown in the figure, it is a schematic structural diagram of the secondary mirror mounting seat 5 in the specific embodiment of the present invention; the secondary mirror mounting seat 5 is fixedly connected to the primary support beam 2 and is used to provide a mounting interface for the secondary mirror assembly, facilitating the installation between the secondary mirror assembly and the foldable and deployable secondary mirror support structure of the present invention.

[0033] The working principle of the foldable and deployable secondary mirror support structure provided by the present invention is as follows: When the satellite is launched, the first fixed end base 12 and the first rotating end base 15 form an angle of 190 degrees, and the second fixed end base and the second rotating end base also form an angle of 190 degrees, making the entire secondary mirror support structure in a folded state; after the satellite is in orbit, the first driving motor 11 and the second driving motor on the first fold-locking mechanism 1 and the second fold-locking mechanism 3 are respectively decelerated by the first reducer 14 and the second reducer, and drive the first rotating end base 15 to rotate through the first rotating shaft 13, and drive the second rotating end base through the second rotating shaft, and then drive the primary support beam 2 and the secondary support beam 4 connected thereto to rotate respectively. During the rotation process, by controlling the rotation speeds of the driving motor 11 and the second driving motor, the first fold-locking mechanism 1 and the second fold-locking mechanism 3 are made to move synchronously and in opposite directions, so as to ensure that the axis direction of the secondary support beam 4 remains unchanged. When the first fixed end base 12 and the first rotating end base 15 rotate to the 0-degree position, the first rotating end base 15 contacts the first travel switch 18, making the first travel switch 18 in an excited state, the first driving motor 11 stops moving, and the first locking motor 19 starts and drives the first screw 17 to rotate. The first screw 17 screws into the first nut 16 and starts to pull the first nut 16, and the first nut 16 drives the first rotating end base 15; the first rotating end base 15 contacts the first fixed end base 12 and generates pressure, and when the first locking motor 19 reaches the maximum output torque value, it stops working. The working principle of the second fold-locking mechanism 3 is similar to that of the first fold-locking mechanism 1. The first fold-locking mechanism 1 and the second fold-locking mechanism 3 are locked, thus realizing the deployment and locking of the entire mechanism.

[0034] The secondary mirror support structure of the present invention can be used for the foldable deployment of a space telescope and has a secondary mirror assembly with a large folding ratio, enabling the secondary mirror assembly to occupy less space in the folded state and better meeting the strict restrictions of the rocket launch envelope size on the volume of the space telescope system.

[0035] Although the embodiments of the present invention have been shown and described above, it can be understood that the above embodiments are exemplary and should not be construed as limiting the present invention. Those of ordinary skill in the art can make changes, modifications, substitutions, and variations to the above embodiments within the scope of the present invention.

[0036] The above specific embodiments of the present invention do not constitute a limitation on the protection scope of the present invention. Any other corresponding changes and deformations made according to the technical concept of the present invention should be included within the protection scope of the claims of the present invention.

Claims

1. A collapsible and expandable secondary mirror support structure, characterized in that, The secondary mirror support structure includes a first-stage folding and locking mechanism, a first-stage support beam, a second-stage folding and locking mechanism, a second-stage support beam, and a secondary mirror mounting seat; The secondary mirror mounting seat is fixedly connected to the second-stage support beam, and the second-stage support beam realizes relative rotational movement around the end of the first-stage support beam through the second-stage folding and locking mechanism; the first-stage support beam is connected to the frame through the first-stage folding and locking mechanism, and the first-stage support beam can perform one-dimensional rotational movement relative to the frame; the first-stage folding and locking mechanism and the second-stage folding and locking mechanism rotate synchronously and in opposite directions; The first-stage folding and locking mechanism includes a first driving motor, a first fixed-end base, a first rotating shaft, a first reducer, a first rotating-end base, a first nut, a first screw, a first travel switch, and a first locking motor; the first driving motor is installed on the first fixed-end base, the output shaft of the first driving motor is connected to the input shaft of the first reducer, and the output shaft of the first reducer is connected to the first rotating shaft; the first rotating-end base is connected to the first rotating shaft, and the first nut is fixed on the first rotating-end base; the first locking motor is arranged on the first fixed-end base, the first screw is connected to the first locking motor, and the first travel switch is arranged on the first fixed-end base.

2. The secondary mirror support structure according to claim 1, characterized in that, The second-stage folding and locking mechanism includes a second driving motor, a second fixed-end base, a second rotating shaft, a second reducer, a second rotating-end base, a second nut, a second screw, a second travel switch, and a second locking motor; The second driving motor is installed on the second fixed-end base, the output shaft of the second driving motor is connected to the second reducer, and the output shaft of the second reducer is connected to the second rotating shaft; the second rotating-end base is connected to the second rotating shaft, and the second nut is fixed on the second rotating-end base; the second locking motor is arranged on the second fixed-end base, the second screw is connected to the second locking motor, and the second travel switch is arranged on the second fixed-end base.

3. The secondary mirror support structure according to claim 2, characterized in that, The first-stage support beam includes a first joint, a first carbon fiber beam, and a second joint, and the first joint and the second joint are respectively located at both ends of the first carbon fiber beam; the first joint is used to provide a connection interface with the first rotating-end base, and the second joint is used to provide a connection interface with the second fixed-end base.

4. The secondary mirror support structure according to claim 3, characterized in that, Both the first joint and the second joint are fixedly connected to the first carbon fiber beam by an adhesive bonding method.

5. The secondary mirror support structure according to claim 3, characterized in that, The second-stage support beam includes a third joint, a second carbon fiber beam, and an adapter; the third joint and the adapter are respectively located at both ends of the second carbon fiber beam; the third joint is used to provide a connection interface with the second rotating-end base, and the adapter is used to provide a connection interface with the secondary mirror mounting seat.

6. The secondary mirror support structure according to claim 5, characterized in that, Both the third joint and the adapter are fixedly connected to the second carbon fiber beam by an adhesive bonding method.

7. The secondary mirror support structure according to claim 1, characterized in that, The secondary mirror mounting seat is fixedly connected to the first-stage support beam and is used to provide a mounting interface for the secondary mirror assembly.

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