On-orbit maintainable micro-vibration isolation device

Abstract

The invention relates to the technical field of micro-vibration of spacecrafts, in particular to an on-orbit maintainable micro-vibration isolation device which comprises a butt joint ring, a plurality of vibration isolators, a plurality of first-stage connecting assemblies and a second-stage connecting assembly. When on-orbit maintenance is needed, the micro-vibration isolation device and the micro-vibration source equipment can be detached from each other, and the micro-vibration isolation device and the spacecraft cabin can also be detached from each other, so that the on-orbit maintainable micro-vibration isolation device and the micro-vibration source equipment can be detached, maintained, replaced and used conveniently, and the on-orbit replaceable maintenance requirement is met. When the on-orbit maintainable micro-vibration isolation device is detached from the spacecraft cabin, each first-stage connecting assembly can be disconnected from the spacecraft cabin, and the second-stage connecting assemblies are kept connected with the spacecraft cabin, so that the on-orbit maintainable micro-vibration isolation device is prevented from freely drifting in a weightless environment. And then, the secondary connecting assembly is disconnected from the spacecraft cabin, so that the astronaut can conveniently implement subsequent maintenance work.

Description

Technical Field

[0001] The invention relates to the technical field of spacecraft micro-vibration, and in particular to an on-orbit maintainable micro-vibration isolation device. Background Art

[0002] Space telescopes have high requirements for observation resolution and stability. When the control moment gyroscope and other equipment on the space telescope work normally, micro-vibrations will be generated, causing micro-vibrations in the spacecraft cabin, which in turn cause micro-vibrations in the large, highly sensitive space camera on board the spacecraft cabin, which will greatly reduce the observation accuracy of the space telescope and make it unable to work normally. Therefore, it is necessary to control the micro-vibrations generated by equipment such as the control moment gyroscope. Usually, a micro-vibration isolation device is installed between the spacecraft cabin and equipment such as the control moment gyroscope that generates micro-vibrations. The installation work is completed at one time on the ground. After the space telescope enters orbit, the vibration isolation device and the control moment gyroscope and other equipment / spacecraft cabin that generates micro-vibrations cannot be disassembled. Since the space telescope as a whole requires a long on-orbit life, as the working years of the space telescope increase, the performance of the control moment gyroscope or the vibration isolation device degrades, and it is difficult to continue to ensure the vibration isolation effect. Therefore, the demand for on-orbit maintainability is proposed.

[0003] Therefore, how to meet the demand for on-orbit maintainability has become a technical problem that needs to be urgently solved by technical personnel in this field. Summary of the invention

[0004] The invention provides an on-orbit maintainable micro-vibration isolation device, which is used to solve the problem of how to meet the demand for on-orbit maintainability.

[0005] The present invention provides an on-orbit maintainable micro-vibration isolation device, comprising:

[0006] Docking ring;

[0007] There are multiple vibration isolators, which are fixedly installed on one side of the docking ring along the circumference of the docking ring; the side of each vibration isolator away from the docking ring is suitable for detachable connection with the micro-vibration source device;

[0008] A plurality of first connection assemblies are installed on a side surface of the docking ring along the circumference of the docking ring; each first connection assembly is suitable for detachably connecting with the spacecraft cabin;

[0009] The secondary connection assembly is one and is installed on one side of the docking ring and is suitable for detachable connection with the spacecraft cabin.

[0010] In some embodiments, each primary connection component includes:

[0011] There are multiple first screws, which are arranged in pairs;

[0012] There are multiple first constraint cylinders, which are arranged outside the first screws in one-to-one correspondence with the multiple first screws; the diameter of the top opening of each first constraint cylinder is smaller than the diameter of the nut of the first screw.

[0013] In some embodiments, the secondary connection component includes:

[0014] A protective cap is fixedly mounted on one side of the docking ring;

[0015] A retaining ring, installed in the protective cap;

[0016] The clamping column has one end suitable for fixed connection with the spacecraft cabin body, and the other end is formed with a clamping joint capable of inserting or disengaging a clamping spring.

[0017] In some embodiments, the secondary connection component further comprises:

[0018] The resistance adjustment piece is installed on the protective cap and is used to adjust the resistance of the clamping spring to the clamping joint.

[0019] In some embodiments, the resistance adjustment assembly includes:

[0020] A second screw is installed on the protective cap and fixedly connected to a side of the clamping spring away from the clamping column;

[0021] The second restraining tube is covered outside the second screw; the diameter of the top opening of each second restraining tube is smaller than the diameter of the nut of the second screw.

[0022] In some embodiments, each vibration isolator comprises:

[0023] The housing has a bottom end detachably connected to the top surface of the docking ring;

[0024] The upper rubber spring ring is installed in the housing;

[0025] A lower rubber spring ring is installed in the housing;

[0026] The sleeve has a bottom end inserted into the housing; a limit plate is formed at the bottom end of the sleeve; the top surface of the limit plate abuts against the bottom surface of the upper rubber spring ring, and the bottom surface abuts against the top surface of the lower rubber spring ring;

[0027] A metal spring is inserted into the sleeve;

[0028] The adapter has one end detachably connected to the top end of the sleeve and the other end suitable for detachably connecting to the micro-vibration source device.

[0029] In some of the embodiments, a first weight-reducing hole is provided on the adapter;

[0030] A second weight-reducing hole is provided on the docking ring.

[0031] In some of the embodiments, reinforcing ribs are provided on the docking ring.

[0032] In some of the embodiments, the micro-vibration source device is a control moment gyroscope.

[0033] The beneficial effects of the present invention are as follows: The on-orbit repairable micro-vibration isolation device of the present invention is provided with a docking ring, a plurality of vibration isolators, a plurality of primary connection components and a secondary connection component, and the side of each vibration isolator away from the docking ring is suitable for detachable connection with the micro-vibration source device. Each first connection component is suitable for detachable connection with the spacecraft cabin. The secondary connection component is suitable for detachable connection with the spacecraft cabin. When on-orbit maintenance is required, the on-orbit repairable micro-vibration isolation device and the micro-vibration source device can be detached from each other, and the on-orbit repairable micro-vibration isolation device and the spacecraft cabin can also be detached from each other, so that the on-orbit repairable micro-vibration isolation device and the micro-vibration source device can be disassembled, repaired and replaced for use, meeting the demand for on-orbit replaceable maintenance. When the on-orbit repairable micro-vibration isolation device is detached from the spacecraft cabin, each primary connection component can be disconnected from the spacecraft cabin first, while the secondary connection component remains connected to the spacecraft cabin, so as to prevent the on-orbit repairable micro-vibration isolation device from drifting at will in a weightless environment. Next, the secondary connection assembly is disconnected from the spacecraft cabin to facilitate the astronauts to carry out subsequent maintenance work. BRIEF DESCRIPTION OF THE DRAWINGS

[0034] Figure 1 It is a schematic structural diagram of some specific embodiments of an on-orbit maintainable micro-vibration isolation device of the present invention;

[0035] Figure 2 yes Figure 1 A schematic diagram of the internal structure of a primary connection assembly in an on-orbit repairable micro-vibration isolation device is shown;

[0036] Figure 3 yes Figure 1 A schematic diagram of the internal structure of the secondary connection assembly in the on-orbit repairable micro-vibration isolation device shown;

[0037] Figure 4 It is a schematic diagram of the structure when the micro-vibration source device is connected to the spacecraft cabin;

[0038] Figure 5 It is a schematic diagram of the structure when the micro-vibration source device is partially disconnected from the spacecraft cabin;

[0039] Figure 6 It is a schematic diagram of the structure when the micro-vibration source equipment is completely disconnected from the spacecraft cabin.

[0040] In the accompanying drawings, 110, docking ring; 111, second weight-reducing hole; 112, reinforcing rib; 120, vibration isolator; 121, outer shell; 124, adapter; 1241, first weight-reducing hole; 130, primary connection assembly; 131, first screw; 132, first restraint cylinder; 140, secondary connection assembly; 141, protective cap; 142, retaining spring; 143, clamping column; 144, resistance adjustment member; 1441, second screw; 1442, second restraint cylinder; 200, micro-vibration source equipment; 300, spacecraft cabin. DETAILED DESCRIPTION

[0041] The technical solution of the present invention will be clearly and completely described below in conjunction with the embodiments. Obviously, the described embodiments are part of the embodiments of the present invention, rather than all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0042] As described in the background technology, when the control moment gyroscope and other equipment on the space telescope works normally, micro-vibration will be generated, causing micro-vibration of the spacecraft cabin, and then causing micro-vibration of the large and highly sensitive space camera carried on the spacecraft cabin, which will lead to a significant reduction in the observation accuracy of the space telescope and make it unable to work normally. Therefore, it is necessary to control the micro-vibration generated by the control moment gyroscope and other equipment. Usually, a micro-vibration isolation device is installed between the spacecraft cabin and the control moment gyroscope and other equipment that generates micro-vibration. The installation work is completed at one time on the ground. After the space telescope is put into orbit, the vibration isolation device and the control moment gyroscope and other equipment / spacecraft cabin that generates micro-vibration cannot be disassembled. Since the space telescope as a whole requires a long on-orbit life, as the working years of the space telescope increase, the control moment gyroscope or the vibration isolation device will degrade in performance, and it is difficult to continue to ensure the vibration isolation effect. Therefore, the demand for on-orbit maintainability is proposed.

[0043] To solve the above problems, refer to Figure 1 , Figure 2 , Figure 3 , Figure 4 , Figure 5 and Figure 6The present invention provides an on-orbit maintainable micro-vibration isolation device, comprising a docking ring 110, a plurality of vibration isolators 120, a plurality of primary connection assemblies 130 and a secondary connection assembly 140. The plurality of vibration isolators 120 are fixedly mounted on a side surface of the docking ring 110 along the circumference of the docking ring 110. The side surface of each vibration isolator 120 away from the docking ring 110 is suitable for detachable connection with a micro-vibration source device 200. It should be pointed out that the micro-vibration source device 200 is a device that generates micro-vibrations when a control moment gyroscope or the like is working. The plurality of primary connection assemblies 130 are mounted on a side surface of the docking ring 110 along the circumference of the docking ring 110. Each first connection assembly is suitable for detachable connection with a spacecraft cabin 300. The secondary connection assembly 140 is mounted on one side of the docking ring 110, and is suitable for detachable connection with the spacecraft cabin 300. When in-orbit maintenance is required, the in-orbit maintainable micro-vibration isolation device and the micro-vibration source device 200 can be detached from each other, and the in-orbit maintainable micro-vibration isolation device and the spacecraft cabin 300 can also be detached from each other, so that the in-orbit maintainable micro-vibration isolation device and the micro-vibration source device 200 can be disassembled for maintenance and replacement, meeting the demand for in-orbit replaceable maintenance. When the in-orbit maintainable micro-vibration isolation device is detached from the spacecraft cabin 300, each primary connection component 130 can be disconnected from the spacecraft cabin 300, while the secondary connection component 140 remains connected to the spacecraft cabin 300, so as to prevent the in-orbit maintainable micro-vibration isolation device from drifting randomly in a weightless environment. Then, the secondary connection component 140 is disconnected from the spacecraft cabin 300 to facilitate the astronauts to carry out subsequent maintenance work.

[0044] Specifically, in the example, Figure 1 and Figure 2 As shown, each primary connection assembly 130 includes a plurality of first screws 131 and a plurality of first constraint cylinders 132. The plurality of first screws 131 are arranged in parallel in pairs. The plurality of first constraint cylinders 132 are covered outside the first screws 131 in a one-to-one correspondence with the plurality of first screws 131. Each first constraint cylinder 132 is fixedly mounted on a side surface of the docking ring 110. It should be noted that a threaded hole compatible with the first screw 131 is provided on the spacecraft cabin 300. Each first screw 131 can be rotated with the aid of a tool so that each first screw 131 is connected or disconnected with the spacecraft cabin 300, thereby connecting or disconnecting each primary connection assembly 130 with the spacecraft cabin 300. When each first screw 131 is disconnected from the spacecraft cabin 300, since the diameter of the top opening of each first restraint tube 132 is smaller than the diameter of the nut of the first screw 131, it can effectively prevent the first screw 131 from detaching from the first restraint tube 132, thereby preventing the first screw 131 from being stranded in space and becoming space junk, and making the first screw 131 recyclable.

[0045] Specifically, in the example, Figure 1 and Figure 3 As shown, the secondary connection assembly 140 includes a protective cap 141, a retaining spring 142, a clamping post 143 and a resistance adjustment member 144. The protective cap 141 is fixedly mounted on one side of the docking ring 110. The retaining spring 142 is installed in the protective cap 141. One end of the clamping post 143 is suitable for fixed connection with the spacecraft cabin 300, and the other end is formed with a clamping joint that can be inserted into or detached from the retaining spring 142. The resistance adjustment member 144 is installed on the protective cap 141 and is used to adjust the resistance of the retaining spring 142 to the clamping joint. Before the secondary connection assembly 140 is disconnected from the spacecraft cabin 300, the resistance of the retaining spring 142 to the clamping joint can be adjusted by the resistance adjustment member 144 to reduce the resistance of the retaining spring 142 to the clamping joint. When the secondary connection assembly 140 is disconnected from the spacecraft cabin 300, the protective cap 141 moves with the docking ring 110 in a direction away from the spacecraft cabin 300, and the retaining spring 142 moves with the protective cap 141 in a direction away from the spacecraft cabin 300, so that the clamping joint is separated from the retaining spring 142. When the secondary connection assembly 140 is connected to the spacecraft cabin 300, the protective cap 141 moves with the docking ring 110 toward the spacecraft cabin 300, and the retaining spring 142 moves with the protective cap 141 toward the spacecraft cabin 300, so that the clamping joint is inserted into the retaining spring 142. The form of matching the retaining joint and the retaining spring 142 makes it very convenient to connect or disconnect the secondary connection assembly 140 with the spacecraft cabin 300. The resistance adjustment assembly includes a second screw 1441 and a second constraint cylinder 1442. The second screw 1441 is rotatably mounted on the protective cap 141, and one end close to the retaining spring 142 is fixedly connected to the side of the retaining spring 142 away from the clamping column 143 through two clamping nuts. The second constraint cylinder 1442 is covered outside the second screw 1441 and fixedly mounted on the protective cap 141. The second screw 1441 can be rotated with the help of a tool to adjust the resistance of the retaining spring 142 to the clamping joint. The caliber of the top opening of each second constraint cylinder 1442 is smaller than the diameter of the nut of the second screw 1441, which can effectively prevent the second screw 1441 from detaching from the second constraint cylinder 1442, thereby preventing the second screw 1441 from being stranded in space and becoming space junk, and making the second screw 1441 recyclable.

[0046] Specifically, in the example, Figure 1 and Figure 4As shown, each vibration isolator includes a shell 121, an upper rubber spring ring, a lower rubber spring ring, a sleeve, a metal spring and an adapter 124. The bottom end of the shell 121 is detachably connected to the top surface of the docking ring 110. The upper rubber spring ring is installed in the shell 121. The lower rubber spring ring is installed in the shell 121. The bottom end of the sleeve is inserted in the shell. A limiting plate is formed at the bottom end of the sleeve, and the top surface of the limiting plate abuts against the bottom surface of the upper rubber spring ring, and the bottom surface abuts against the top surface of the lower rubber spring ring. The metal spring is inserted into the sleeve. One end of the adapter 121 is detachably connected to the top end of the sleeve, and the other end is suitable for detachably connecting to the micro-vibration source device. The end of the adapter 124 that is not connected to the sleeve can swing to facilitate the connection of the adapter 124 to the micro-vibration source device 200. The vibration isolator 120 plays a vibration isolation role, preventing the micro-vibration generated by the micro-vibration source device 200 from being transmitted to the spacecraft cabin 300, thereby preventing the large and highly sensitive space camera from generating micro-vibration, thereby ensuring the observation accuracy of the space telescope.

[0047] Preferably, the adapter 124 of each vibration isolator 120 is in the shape of an elongated strip, with a first threaded hole provided at one end, through which the rubber spring 122 and the adapter 124 can be fixedly connected by a third screw, and a second threaded hole provided at the other end, through which the micro-vibration source device 200 and the adapter 124 can be fixedly connected by a fourth screw, and 3-5 first weight-reducing holes 1241 are provided in the middle to reduce the weight of the adapter 124. 3-5 second weight-reducing holes 111 are provided on the docking ring 110 along the circumference of the docking ring 110 to reduce the weight of the docking ring 110. Multiple layers of reinforcing ribs 112 are provided on the docking ring 110, and the multiple layers of reinforcing ribs 112 are respectively inner layer reinforcing ribs, middle layer reinforcing ribs and outer layer reinforcing ribs to improve the rigidity and strength of the docking ring 110.

[0048] Preferably, the docking ring 110 is annular, with an outer diameter of 720 mm, an inner diameter of 460 mm, and a thickness of 10 mm. The distance between each two adjacent vibration isolators 120 is 274 mm. The height of each layer of reinforcement ribs is 30 mm and the thickness is 10 mm.

[0049] In the description of the present invention, it is to be understood that the terms “center”, “longitudinal”, “lateral”, “length”, “width”, “thickness”, “up”, “down”, “front”, “back”, “left”, “right”, “vertical”, “horizontal”, “top”, “bottom”, “inside”, “outside”, “clockwise”, “counterclockwise”, “axial”, “radial”, “circumferential”, etc., indicating orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the present invention.

[0050] In addition, the terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, the features defined as "first" and "second" may explicitly or implicitly include at least one of the features. In the description of the present invention, the meaning of "plurality" is at least two, such as two, three, etc., unless otherwise clearly and specifically defined.

[0051] In the present invention, unless otherwise clearly specified and limited, the terms "installed", "connected", "connected", "fixed" and the like should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral one; it can be a mechanical connection, an electrical connection, or communication with each other; it can be a direct connection, or an indirect connection through an intermediate medium, it can be the internal connection of two elements or the interaction relationship between two elements, unless otherwise clearly defined. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood according to specific circumstances.

[0052] In the present invention, the terms "one embodiment", "some embodiments", "examples", "specific examples", or "some examples" etc. mean that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representations of the above terms do not necessarily refer to the same embodiment or example. Moreover, the described specific features, structures, materials or characteristics may be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art may combine and combine the different embodiments or examples described in this specification and the features of the different embodiments or examples, without contradiction.

[0053] Although the embodiments of the present invention have been shown and described above, it is to be understood that the above embodiments are exemplary and are not to be construed as limitations of the present invention. A person skilled in the art may change, modify, replace and vary the above embodiments within the scope of the present invention.

Claims

1. An on-orbit maintainable micro-vibration isolation device, characterized in that: include: Docking ring; There are multiple vibration isolators, which are fixedly installed on one side of the docking ring along the circumference of the docking ring; the side of each vibration isolator away from the docking ring is suitable for detachable connection with the micro-vibration source device; A plurality of first-stage connection assemblies are installed on a side surface of the docking ring along the circumference of the docking ring; each of the first-stage connection assemblies is suitable for detachably connecting with the spacecraft cabin; The secondary connection assembly is one and is installed on one side of the docking ring and is suitable for detachable connection with the spacecraft cabin.

2. The on-orbit maintainable micro-vibration isolation device according to claim 1, characterized in that: Each of the primary connection components comprises: There are multiple first screws, which are arranged in pairs; There are multiple first constraint cylinders, which are covered outside the first screws in a one-to-one correspondence with the multiple first screws; the diameter of the top opening of each first constraint cylinder is smaller than the diameter of the nut of the first screw.

3. The on-track maintainable micro-vibration isolation device according to claim 2, characterized in that: The secondary connection component comprises: A protective cap, fixedly mounted on one side of the docking ring; A retaining ring installed in the protective cap; A clamping column has one end adapted to be fixedly connected to the spacecraft cabin, and the other end is formed with a clamping joint capable of being inserted into or detached from the clamping spring.

4. The on-orbit maintainable micro-vibration isolation device according to claim 3, characterized in that: The secondary connection component also includes: A resistance adjusting member is installed on the protective cap and is used to adjust the resistance of the clamping spring to the clamping joint.

5. The on-track maintainable micro-vibration isolation device according to claim 4, characterized in that: The resistance adjustment component comprises: A second screw is installed on the protective cap and fixedly connected to a side of the clamping spring away from the clamping column; The second constraint tube is covered outside the second screw; the diameter of the top opening of each second constraint tube is smaller than the diameter of the nut of the second screw.

6. The on-track maintainable micro-vibration isolation device according to any one of claims 1 to 5, characterized in that: Each of the vibration isolators comprises: A housing, the bottom end of which is detachably connected to the top surface of the docking ring; An upper rubber spring ring is installed in the housing; A lower rubber spring ring is installed in the housing; A sleeve, the bottom end of which is inserted into the shell; a limit plate is formed at the bottom end of the sleeve; the top surface of the limit plate abuts against the bottom surface of the upper rubber spring ring, and the bottom surface abuts against the top surface of the lower rubber spring ring; A metal spring is inserted into the sleeve; The adapter has one end detachably connected to the top end of the sleeve and the other end suitable for detachably connecting to the micro-vibration source device.

7. The on-orbit maintainable micro-vibration isolation device according to claim 6, characterized in that: The adapter is provided with a first weight-reducing hole; The docking ring is provided with a second weight-reducing hole.

8. The on-track maintainable micro-vibration isolation device according to any one of claims 1 to 5, characterized in that: The butt joint ring is provided with reinforcing ribs.

9. The on-track maintainable micro-vibration isolation device according to any one of claims 1 to 5, characterized in that: The micro-vibration source device is a control moment gyroscope.

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