CN215155784U - Multi-redundancy satellite intelligent attitude control assembly - Google Patents
Multi-redundancy satellite intelligent attitude control assembly Download PDFInfo
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- CN215155784U CN215155784U CN202120638974.8U CN202120638974U CN215155784U CN 215155784 U CN215155784 U CN 215155784U CN 202120638974 U CN202120638974 U CN 202120638974U CN 215155784 U CN215155784 U CN 215155784U
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Abstract
A multi-redundancy satellite intelligent attitude control assembly comprises a box body (1), a reaction flywheel set (2), a magnetic torquer set (3), a magnetic torquer coil (4), a control panel (5) and a gyroscope (6), wherein a magnetic torquer coil mounting groove (11) and a control panel mounting groove (12) are formed in the box body; the reaction flywheel sets comprise a first reaction flywheel set, a second reaction flywheel set, a third reaction flywheel set and a fourth reaction flywheel set which are respectively arranged at four corners of the box body, each reaction flywheel set comprises an X-axis reaction flywheel (21), a Y-axis reaction flywheel (22) and a Z-axis reaction flywheel (23), and X, Y-axis reaction flywheels are arranged on the side wall of the box body; the magnetic torquer group carries out magnetic unloading on the reaction flywheel, and comprises X-axis magnetic torquers and Y-axis magnetic torquers which are arranged on a bottom plate of the box body and are symmetrically distributed; the magnetic torquer coil is arranged in a magnetic torquer coil mounting groove of the box body and is in the Z-axis direction; the control panel is arranged in the center of the box body and is arranged in the control panel mounting groove; the gyroscopes are three and are all arranged on the bottom plate in the box body.
Description
Technical Field
The utility model relates to an aerospace's technical field especially relates to a many redundant satellite intelligence appearance accuse subassembly.
Background
Attitude control actuators for satellites, earth observation platforms, spacecraft, space telescopes, and other spacecraft are required to be small in size, light in weight, long in service life, low in power consumption, and high in reliability. Currently, a system for attitude control of a spacecraft includes: a reaction flywheel, a magnetic torquer, a nine-axis sensor actuating mechanism and the like; the reaction flywheel and the magnetic torquer are generally in a group of three, and the three axial postures of the spacecraft are respectively controlled. Obviously, when one of the reaction flywheels or the magnetic torquers breaks down, the axial attitude cannot be adjusted, so that the normal operation of the whole spacecraft is affected, and the failure of the spacecraft can be caused in severe cases.
Obviously, in space, a plurality of groups of reaction flywheels are arranged in each direction, and each group of flywheels can completely complete the attitude control of the spacecraft, so that when the reaction flywheels in one direction fail, the other reaction flywheels are started in the other direction, and the attitude control of the spacecraft is completely and reliably completed. The more the number of the reaction flywheel sets is, the better the reliability is, namely the more the redundancy is, the stronger the stability of the spacecraft attitude control system is; however, the problem is not solved by simply adding several sets of reaction flywheels and magnetic torquers. The weight and the volume of parts of a spacecraft launched into the sky are key indexes of the design of the spacecraft, and the manufacturing cost is obviously increased even if 1 g or 1 cubic centimeter is increased, so that the attitude control reliability of the spacecraft can be ensured only by adding a plurality of groups of reaction flywheels and magnetic torquers, the requirements on the weight and the volume are balanced as much as possible, and the spacecraft is an important choice for scientific researchers. In addition, the placement positions of the reaction flywheel and the magnetic torquer are also very important, the vibration suffered by the main body of the intelligent attitude control assembly of the satellite is very large for adjusting and controlling the reaction flywheel and the magnetic torquer of the satellite attitude, and how to reduce the vibration suffered by the reaction flywheel and the magnetic torquer is also important for scientific research personnel.
Disclosure of Invention
For overcoming the defect of the prior art, the to-be-solved technical problem of the utility model is to provide a many redundant satellite intelligence appearance accuse subassembly, it greatly improves the attitude control reliability under the prerequisite of increase assembly weight and volume as far as possible, keeps the global balance of subassembly in the assembly, and the vibration that the reaction flywheel that significantly reduces received guarantees the attitude control accuracy.
The technical scheme of the utility model is that: this kind of many redundant satellites intelligence attitude control assembly, it includes: a box body (1), a reaction flywheel set (2), a magnetic torquer set (3), a magnetic torquer coil (4), a control panel (5) and a gyroscope (6),
the box body is provided with a magnetic torquer coil mounting groove (11) and a control panel mounting groove (12);
the reaction flywheel sets comprise a first reaction flywheel set, a second reaction flywheel set, a third reaction flywheel set and a fourth reaction flywheel set, the four reaction flywheel sets are respectively arranged in four corners of the box body, each reaction flywheel set comprises an X-axis reaction flywheel (21), a Y-axis reaction flywheel (22) and a Z-axis reaction flywheel (23), and the X-axis reaction flywheel and the Y-axis reaction flywheel are arranged on the side wall of the box body;
the magnetic torquer group carries out magnetic unloading on the reaction flywheel, and comprises an X-axis magnetic torquer and a Y-axis magnetic torquer which are arranged on a bottom plate of the box body and are symmetrically distributed;
the magnetic torquer coil is arranged in a magnetic torquer coil mounting groove of the box body and is in the Z-axis direction;
the control panel is arranged in the center of the box body and is arranged in the control panel mounting groove;
the gyroscopes are three and are all arranged on the bottom plate in the box body.
The reaction flywheel set of the utility model comprises a first reaction flywheel set, a second reaction flywheel set, a third reaction flywheel set and a fourth reaction flywheel set, and the four reaction flywheel sets are respectively arranged in four corners of the box body, so that the reliability of attitude control can be greatly improved on the premise of increasing the weight and the volume of the component as little as possible, and the overall balance of the whole component is kept in assembly; the X-axis reaction flywheel and the Y-axis reaction flywheel are arranged on the side wall of the box body, so that vibration of the reaction flywheel can be greatly reduced, and the attitude control accuracy is guaranteed.
Still provide another many redundant satellite intelligence appearance accuse subassembly, it includes: a box body (1), a reaction flywheel set (2), a magnetic torquer coil, a control panel (5) and a gyroscope (6),
the box body is provided with a magnetic torquer coil mounting groove and a control panel mounting groove;
the reaction flywheel sets comprise a first reaction flywheel set, a second reaction flywheel set, a third reaction flywheel set and a fourth reaction flywheel set, the four reaction flywheel sets are respectively arranged in four corners of the box body, each reaction flywheel set comprises an X-axis reaction flywheel, a Y-axis reaction flywheel and a Z-axis reaction flywheel, and the X-axis reaction flywheel and the Y-axis reaction flywheel are arranged on the side wall of the box body;
the magnetic torquer coil carries out magnetic unloading on the reaction flywheel and comprises an X-axis magnetic torquer coil (41), a Y-axis magnetic torquer coil (42) and a Z-axis magnetic torquer coil (43), wherein the X-axis magnetic torquer coil and the Y-axis magnetic torquer coil are arranged on the side wall of the box body, and the Z-axis magnetic torquer coil is arranged in a magnetic torquer coil mounting groove of the box body;
the control panel is arranged in the center of the box body and is arranged in the control panel mounting groove;
the gyroscopes are three and are all arranged on the bottom plate in the box body.
The magnetic torquer of the assembly completely uses magnetic torquer coils, namely an X-axis magnetic torquer coil, a Y-axis magnetic torquer coil and a Z-axis magnetic torquer coil, and because the shapes of the magnetic torquer coils can be changed according to requirements, the installation space of other parts can be increased, and the integral balance of the whole assembly is kept in assembly; the X-axis magnetic torquer coil and the Y-axis magnetic torquer coil are arranged on the side wall of the box body, so that the vibration of the magnetic torquer can be greatly reduced, and the attitude control accuracy is ensured; the reaction flywheel sets comprise a first reaction flywheel set, a second reaction flywheel set, a third reaction flywheel set and a fourth reaction flywheel set, and the four reaction flywheel sets are respectively arranged in four corners of the box body, so that the attitude control reliability can be greatly improved on the premise of increasing the weight and the volume of the assembly as little as possible, and the integral balance of the whole assembly is kept in assembly; the X-axis reaction flywheel and the Y-axis reaction flywheel are arranged on the side wall of the box body, so that vibration of the reaction flywheel can be greatly reduced, and the attitude control accuracy is guaranteed.
Drawings
Fig. 1 shows according to the utility model discloses a split structure schematic diagram of first many redundant satellite intelligence appearance accuse subassembly.
FIG. 2 illustrates a top view of the multi-redundant satellite intelligent attitude control assembly of FIG. 1.
Fig. 3 shows according to the utility model discloses a split structure schematic diagram of second kind of many redundant satellite intelligence appearance accuse subassembly.
FIG. 4 illustrates a top view of the multi-redundant satellite intelligent attitude control assembly of FIG. 3.
Fig. 5 shows according to the utility model discloses a split structure schematic diagram of third kind of many redundant satellite intelligence appearance accuse subassembly.
FIG. 6 illustrates a top view of the multi-redundant satellite intelligent attitude control assembly of FIG. 5.
Fig. 7 shows according to the utility model discloses a fourth kind of many redundant satellite intelligence appearance accuse subassembly's split structure schematic diagram.
FIG. 8 illustrates a top view of the multi-redundant satellite intelligent attitude control assembly of FIG. 7.
Detailed Description
As shown in fig. 1, the multi-redundant satellite intelligent attitude control assembly includes: a box body 1, a reaction flywheel set 2, a magnetic torquer set 3, a magnetic torquer coil 4, a control panel 5 and a gyroscope 6,
the box body is provided with a magnetic torquer coil mounting groove 11 and a control panel mounting groove 12;
the reaction flywheel sets comprise a first reaction flywheel set, a second reaction flywheel set, a third reaction flywheel set and a fourth reaction flywheel set, the four reaction flywheel sets are respectively arranged in four corners of the box body, each reaction flywheel set comprises an X-axis reaction flywheel 21, a Y-axis reaction flywheel 22 and a Z-axis reaction flywheel 23, and the X-axis reaction flywheel and the Y-axis reaction flywheel are arranged on the side wall of the box body;
the magnetic torquer group carries out magnetic unloading on the reaction flywheel, and comprises an X-axis magnetic torquer and a Y-axis magnetic torquer which are arranged on a bottom plate of the box body and are symmetrically distributed;
the magnetic torquer coil is arranged in a magnetic torquer coil mounting groove of the box body and is in the Z-axis direction;
in addition, the magnetic torquer coil is also provided with a magnetic torquer coil cover plate 41 for preventing dust and impurities from entering the magnetic torquer coil, and the magnetic torquer coil is used for fixing the magnetic torquer coil and preventing the magnetic torquer coil from jumping out of a magnetic torquer coil mounting groove during vibration;
the control panel is arranged in the center of the box body and is arranged in the control panel mounting groove;
the gyroscopes are three and are all arranged on the bottom plate in the box body.
The reaction flywheel set of the utility model comprises a first reaction flywheel set, a second reaction flywheel set, a third reaction flywheel set and a fourth reaction flywheel set, and the four reaction flywheel sets are respectively arranged in four corners of the box body, so that the reliability of attitude control can be greatly improved on the premise of increasing the weight and the volume of the component as little as possible, and the overall balance of the whole component is kept in assembly; the X-axis reaction flywheel and the Y-axis reaction flywheel are arranged on the side wall of the box body, so that vibration of the reaction flywheel can be greatly reduced, and the attitude control accuracy is guaranteed.
Preferably, as shown in fig. 1 and 2, all the reaction flywheels are mounted by using a bottom external flange plate, and the Z-axis reaction flywheels are mounted on a bottom plate in the box body.
Preferably, as shown in fig. 3 and 4, the reaction flywheel is installed by using side positioning holes, the electric connector on the reaction flywheel is defined as the front surface, the prism on the back surface of the reaction flywheel is provided with installation positioning holes, and the X-axis reaction flywheel, the Y-axis reaction flywheel and the Z-axis reaction flywheel are all installed on the side wall of the box body. Because the X-axis reaction flywheel, the Y-axis reaction flywheel and the Z-axis reaction flywheel are all arranged on the side wall of the box body, the vibration of the reaction flywheel can be reduced to the maximum extent, the attitude control accuracy is guaranteed, and the space of the box body can be fully utilized.
Preferably, as shown in fig. 1 and 4, the number of the X-axis magnetic torquers and the number of the Y-axis magnetic torquers are 2, and the X-axis magnetic torquers and the Y-axis magnetic torquers are both positioned above the magnetic torquer coils. Thus, the space of the box body can be fully utilized.
The control panel shown in fig. 1 comprises three layers. Alternatively, similar to fig. 2 and 3, the control board includes: the bottom control panel and the top control panel are respectively installed in the control panel installation groove of the bottom and the control panel installation groove of the top, and the two layers are connected through an electric connector.
Preferably, as shown in fig. 1, each gyroscope is provided with a protective cover fixed to a side wall of the case.
Alternatively, as shown in fig. 4, three gyroscopes share a single protective cover, and the protective cover is mounted on the bottom plate of the case.
As shown in fig. 2 and 3, another multi-redundancy satellite intelligent attitude control assembly is further provided, which includes: a box body 1, a reaction flywheel set 2, a magnetic torquer coil, a control panel 5 and a gyroscope 6,
the box body is provided with a magnetic torquer coil mounting groove and a control panel mounting groove;
the reaction flywheel sets comprise a first reaction flywheel set, a second reaction flywheel set, a third reaction flywheel set and a fourth reaction flywheel set, the four reaction flywheel sets are respectively arranged in four corners of the box body, each reaction flywheel set comprises an X-axis reaction flywheel, a Y-axis reaction flywheel and a Z-axis reaction flywheel, and the X-axis reaction flywheel and the Y-axis reaction flywheel are arranged on the side wall of the box body;
the magnetic torquer coil carries out magnetic unloading on the reaction flywheel and comprises an X-axis magnetic torquer coil 41, a Y-axis magnetic torquer coil 42 and a Z-axis magnetic torquer coil 43, wherein the X-axis magnetic torquer coil and the Y-axis magnetic torquer coil are arranged on the side wall of the box body, and the Z-axis magnetic torquer coil is arranged in a magnetic torquer coil mounting groove of the box body;
the control panel is arranged in the center of the box body and is arranged in the control panel mounting groove;
the gyroscopes are three and are all arranged on the bottom plate in the box body.
The magnetic torquer of the assembly completely uses magnetic torquer coils, namely an X-axis magnetic torquer coil, a Y-axis magnetic torquer coil and a Z-axis magnetic torquer coil, and because the shapes of the magnetic torquer coils can be changed according to requirements, the installation space of other parts can be increased, and the integral balance of the whole assembly is kept in assembly; the X-axis magnetic torquer coil and the Y-axis magnetic torquer coil are arranged on the side wall of the box body, so that the vibration of the magnetic torquer can be greatly reduced, and the attitude control accuracy is ensured; the reaction flywheel sets comprise a first reaction flywheel set, a second reaction flywheel set, a third reaction flywheel set and a fourth reaction flywheel set, and the four reaction flywheel sets are respectively arranged in four corners of the box body, so that the attitude control reliability can be greatly improved on the premise of increasing the weight and the volume of the assembly as little as possible, and the integral balance of the whole assembly is kept in assembly; the X-axis reaction flywheel and the Y-axis reaction flywheel are arranged on the side wall of the box body, so that vibration of the reaction flywheel can be greatly reduced, and the attitude control accuracy is guaranteed.
Preferably, the X-axis magnetic torquer coil and the Y-axis magnetic torquer coil are mounted on the side wall of the box body through a bracket, or an X-axis mounting groove and a Y-axis mounting groove are further formed in the outer side of the side wall of the box body and used for mounting the X-axis magnetic torquer coil and the Y-axis magnetic torquer coil.
The above is only the preferred embodiment of the present invention, and is not intended to limit the present invention in any form, and all the technical matters of the present invention are to make any simple modification, equivalent change and modification to the above embodiments, and still belong to the protection scope of the present invention.
Claims (9)
1. A multi-redundant satellite intelligent attitude control assembly, comprising: box (1), reaction flywheel group (2), magnetic torque group (3), magnetic torque ware coil (4), control panel (5), gyroscope (6), its characterized in that:
the box body is provided with a magnetic torquer coil mounting groove (11) and a control panel mounting groove (12); the reaction flywheel sets comprise a first reaction flywheel set, a second reaction flywheel set, a third reaction flywheel set and a fourth reaction flywheel set, the four reaction flywheel sets are respectively arranged in four corners of the box body, and each reaction flywheel set comprises an X-axis reaction flywheel (21) and a Y-axis reaction flywheel (21)
The flywheel device comprises a shaft reaction flywheel (22) and a Z shaft reaction flywheel (23), wherein the X shaft reaction flywheel and the Y shaft reaction flywheel are arranged on the side wall of the box body;
the magnetic torquer group carries out magnetic unloading on the reaction flywheel, and comprises an X-axis magnetic torquer and a Y-axis magnetic torquer which are arranged on a bottom plate of the box body and are symmetrically distributed;
the magnetic torquer coil is arranged in a magnetic torquer coil mounting groove of the box body and is in the Z-axis direction;
the control panel is arranged in the center of the box body and is arranged in the control panel mounting groove;
the gyroscopes are three and are all arranged on the bottom plate in the box body.
2. The multi-redundant satellite intelligent attitude control assembly of claim 1, wherein: all reaction flywheels are installed by adopting an outer flange plate at the bottom, and the Z-axis reaction flywheels are all installed on a bottom plate in the box body.
3. The multi-redundant satellite intelligent attitude control assembly of claim 1, wherein: the reaction flywheel is installed by adopting side positioning holes, the electric connector on the reaction flywheel is defined as the front surface, the prism on the back surface of the reaction flywheel is provided with installation positioning holes, and the X-axis reaction flywheel, the Y-axis reaction flywheel and the Z-axis reaction flywheel are all installed on the side wall of the box body.
4. The multi-redundant satellite intelligent attitude control assembly of claim 1, wherein: the number of the X-axis magnetic torquers and the number of the Y-axis magnetic torquers are both 2, and the X-axis magnetic torquers and the Y-axis magnetic torquers are both positioned above the coils of the magnetic torquers.
5. The multi-redundant satellite intelligent attitude control assembly of claim 1, wherein: the control panel includes: the bottom control panel and the top control panel are respectively installed in the control panel installation groove of the bottom and the control panel installation groove of the top, and the two layers are connected through an electric connector.
6. The multi-redundant satellite intelligent attitude control assembly of claim 1, wherein: each gyroscope is provided with a protective cover, and the protective covers are fixed on the side wall of the box body.
7. The multi-redundant satellite intelligent attitude control assembly of claim 1, wherein: the three gyroscopes share one protective cover, and the protective cover is arranged on a bottom plate of the box body.
8. A multi-redundant satellite intelligent attitude control assembly, comprising: box (1), reaction flywheel group (2), magnetic torquer coil, control panel (5), gyroscope (6), its characterized in that: the box body is provided with a magnetic torquer coil mounting groove and a control panel mounting groove;
the reaction flywheel sets comprise a first reaction flywheel set, a second reaction flywheel set, a third reaction flywheel set and a fourth reaction flywheel set, the four reaction flywheel sets are respectively arranged in four corners of the box body, each reaction flywheel set comprises an X-axis reaction flywheel, a Y-axis reaction flywheel and a Z-axis reaction flywheel, and the X-axis reaction flywheel and the Y-axis reaction flywheel are arranged on the side wall of the box body;
the magnetic torquer coil carries out magnetic unloading on the reaction flywheel and comprises an X-axis magnetic torquer coil (41), a Y-axis magnetic torquer coil (42) and a Z-axis magnetic torquer coil (43), wherein the X-axis magnetic torquer coil and the Y-axis magnetic torquer coil are arranged on the side wall of the box body, and the Z-axis magnetic torquer coil is arranged in a magnetic torquer coil mounting groove of the box body;
the control panel is arranged in the center of the box body and is arranged in the control panel mounting groove;
the gyroscopes are three and are all arranged on the bottom plate in the box body.
9. The multi-redundant satellite intelligent attitude control assembly of claim 8, wherein: the X-axis magnetic torquer coil and the Y-axis magnetic torquer coil are mounted on the side wall of the box body through the support, or an X-axis mounting groove and a Y-axis mounting groove are further formed in the outer side of the side wall of the box body and used for mounting the X-axis magnetic torquer coil and the Y-axis magnetic torquer coil.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202120638974.8U CN215155784U (en) | 2021-03-30 | 2021-03-30 | Multi-redundancy satellite intelligent attitude control assembly |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202120638974.8U CN215155784U (en) | 2021-03-30 | 2021-03-30 | Multi-redundancy satellite intelligent attitude control assembly |
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| CN215155784U true CN215155784U (en) | 2021-12-14 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112937920A (en) * | 2021-03-30 | 2021-06-11 | 湖南揽月机电科技有限公司 | Multi-redundancy satellite intelligent attitude control assembly and working method thereof |
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- 2021-03-30 CN CN202120638974.8U patent/CN215155784U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112937920A (en) * | 2021-03-30 | 2021-06-11 | 湖南揽月机电科技有限公司 | Multi-redundancy satellite intelligent attitude control assembly and working method thereof |
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