CN118004448A - High-precision pointing device for spacecraft - Google Patents
High-precision pointing device for spacecraft Download PDFInfo
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- CN118004448A CN118004448A CN202410244765.3A CN202410244765A CN118004448A CN 118004448 A CN118004448 A CN 118004448A CN 202410244765 A CN202410244765 A CN 202410244765A CN 118004448 A CN118004448 A CN 118004448A
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- 238000009434 installation Methods 0.000 claims abstract description 11
- 230000005540 biological transmission Effects 0.000 claims description 6
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- 230000001133 acceleration Effects 0.000 claims description 5
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- 238000006073 displacement reaction Methods 0.000 claims description 4
- 230000007774 longterm Effects 0.000 abstract description 3
- 238000012423 maintenance Methods 0.000 abstract description 2
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- 238000012986 modification Methods 0.000 description 2
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- 208000003443 Unconsciousness Diseases 0.000 description 1
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- ZZUFCTLCJUWOSV-UHFFFAOYSA-N furosemide Chemical group C1=C(Cl)C(S(=O)(=O)N)=CC(C(O)=O)=C1NCC1=CC=CO1 ZZUFCTLCJUWOSV-UHFFFAOYSA-N 0.000 description 1
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Abstract
The invention discloses a high-precision pointing device for a spacecraft, which comprises a base, wherein a fixed plate is arranged at the center of the base, and a driving mechanism is arranged on the fixed plate, the driving mechanism comprises a driving motor, a screw rod and a disc which are fixedly arranged at the center of the fixed plate, and the upper end of a convex column is connected with the bottom center of a micro-motion platform through a first spherical hinge; the micro-motion platform comprises a screw rod, a first connecting rod and a second connecting rod, wherein the screw rod is arranged on the screw rod, the first connecting rod is hinged to the edge of the screw rod, the second connecting rod is hinged to the upper end of the first connecting rod, and the upper end of the second connecting rod is connected with the bottom of the micro-motion platform through a second spherical hinge. The invention has simple and compact structure, convenient use and convenient installation and maintenance; the pointing precision is high, the stability is good, and the high-precision pointing requirement of the spacecraft in a complex environment can be met; long service life and high reliability, and can ensure the long-term stable operation of the spacecraft.
Description
Technical Field
The invention belongs to the technical field of pointing devices, and particularly relates to a high-precision pointing device for a spacecraft.
Background
The occurrence of spacecraft expands the range of human activities from the earth atmosphere to a wide and unconscious space, thereby causing the leap of human understanding nature and improving the natural ability and having great influence on social economy and social life.
With the continuous development of the aerospace technology, the function and performance requirements of the spacecraft are higher and higher, the high-precision pointing device is used as an important component of the spacecraft, and the performance of the high-precision pointing device directly influences the overall performance of the spacecraft. Through retrieval, the Chinese patent application number is: CN201810352979.7 discloses an electric propulsion and deployment and thrust direction adjusting mechanism, which relates to the field of spacecraft propulsion and adjustment; the device comprises an installation bottom plate, an elastic unfolding joint, a first unfolding arm, a locking mechanism, a single-degree-of-freedom rotary joint, a second unfolding arm, a double-degree-of-freedom rotary joint and a thruster installation plate; one axial end of the first unfolding arm is fixedly connected with the upper surface of the mounting bottom plate through an elastic unfolding joint; the locking mechanism is fixedly arranged on the lower surface of the first unfolding arm; the single-degree-of-freedom rotary joint is fixedly arranged at the other axial end of the first unfolding arm; one axial end of the second unfolding arm is connected with the first unfolding arm through a single-degree-of-freedom rotary joint; the double-freedom-degree rotary joint is fixedly arranged at the other axial end of the second unfolding arm; the lower bottom surface of the thruster mounting plate is fixedly connected with the double-freedom-degree rotary joint; the invention improves the backup capability of the electric thruster and reduces the consumption of the propellant under the condition of fault ignition; the invention can also improve the efficiency of the electric thruster for maintaining the north-south position.
The above scheme still has defects: at present, the existing high-precision pointing device generally has the problems of complex structure, poor stability, difficult maintenance and the like, and the requirements of high precision and high stability of modern spacecrafts are difficult to meet.
Disclosure of Invention
The invention aims to provide a high-precision pointing device for a spacecraft, which has a simple and compact structure, is convenient to use and is convenient to install and maintain; the pointing precision is high, the stability is good, and the high-precision pointing requirement of the spacecraft in a complex environment can be met; long service life and high reliability, and can ensure long-term stable operation of the spacecraft so as to solve the problems in the prior art in the background art.
In order to achieve the above purpose, the invention adopts the following technical scheme:
The high-precision pointing device for the spacecraft comprises a base, wherein a fixing plate is arranged at the center of the base, a micro-motion platform for realizing high-precision pointing of the spacecraft is arranged right above the base, and a control box is arranged at the bottom center of the micro-motion platform;
The device also comprises a driving mechanism arranged on the fixed plate, the driving mechanism comprises a driving motor, a screw rod and a disc which are fixedly arranged at the central position of the fixed plate, one end of an output shaft of the driving motor is fixedly connected with the screw rod through a coupling, the upper end of the screw rod is rotationally connected to the bottom center position of the disc, a convex column is arranged at the top center position of the disc, and the upper end of the convex column is connected with the bottom center of the micro-motion platform through a first spherical hinge;
the micro-motion platform comprises a screw rod, a first connecting rod and a second connecting rod, wherein the screw rod is arranged on the screw rod, the first connecting rod is hinged to the edge of the screw rod, the second connecting rod is hinged to the upper end of the first connecting rod, four groups of the first connecting rod and the second connecting rod are arranged on the screw rod in a surrounding mode, and the upper end of the second connecting rod is connected with the bottom of the micro-motion platform through a second spherical hinge.
Preferably, a control circuit board, a controller and a sensor module are sequentially arranged in the control box, the sensor module comprises a gyroscope for measuring the rotation angle of the spacecraft around a certain axis, a magnetometer for measuring the linear acceleration of the spacecraft on a certain axis, speed and displacement information can be obtained through integral operation, and the accelerometer is further used for correcting and compensating the posture of the spacecraft and is used for measuring the magnetic field intensity and direction of the place where the spacecraft is located.
Preferably, the support of the first spherical hinge is arranged at the bottom of the control box, and the sphere of the first spherical hinge is arranged at the upper end of the convex column.
Preferably, the support of the second spherical hinge is arranged at the upper end of the second connecting rod, and the sphere of the second spherical hinge is arranged at the bottom of the micro-motion platform in a surrounding manner.
Preferably, the slide is discoid setting, and the equidistance is encircleed on the slide and is set up four group's breach, the lower extreme of first connecting rod articulates in the inside of breach, the other end of first connecting rod is connected in the lower extreme of second connecting rod through articulated mode.
Preferably, a connecting rod for fixing the disc is welded at the bottom of the disc, the lower end of the connecting rod is welded on the surface of the fixing plate, and the connecting rod is obliquely arranged.
Preferably, the bottom of base still is provided with the installation component, the installation component includes slide bar and mounting panel, the mounting panel is the zigzag setting, the slide bar welds in the bottom of base.
Preferably, the slide bar is pegged graft in the mounting panel in the slip, the lower extreme of slide bar runs through the mounting panel and is connected with the stopper, is located and cup joints two sets of rubber rings between mounting panel and the base on the slide bar, has cup jointed compression spring between two sets of rubber rings on the slide bar.
The invention has the technical effects and advantages that: compared with the prior art, the high-precision pointing device for the spacecraft has the following advantages:
According to the invention, the driving mechanism comprising the driving motor, the screw rod and the disc is arranged on the base, the transmission mechanism comprising the sliding seat, the first connecting rod and the second connecting rod is arranged, the first connecting rod is hinged with the sliding seat on the screw rod, the second connecting rod is hinged with the first connecting rod, the second upper end is connected with the bottom of the micro-motion platform through the second spherical hinge, the convex column on the disc is connected with the center of the bottom of the micro-motion platform through the first spherical hinge, and the bottom of the micro-motion platform is also provided with the control box; the pointing precision is high, the stability is good, and the high-precision pointing requirement of the spacecraft in a complex environment can be met; long service life and high reliability, and can ensure the long-term stable operation of the spacecraft.
Drawings
FIG. 1 is a schematic diagram of the structure of the present invention;
FIG. 2 is a schematic structural view of a fixing plate according to the present invention;
FIG. 3 is a schematic view of the micro-motion stage according to the present invention;
FIG. 4 is a schematic view of a sliding seat according to the present invention;
FIG. 5 is a schematic view of a first connecting rod according to the present invention;
fig. 6 is a schematic structural view of the base of the present invention.
In the figure: 1. a base; 2. a fixing plate; 3. a driving motor; 4. a screw rod; 5. a slide; 6. a first link; 7. a second link; 8. a disc; 9. a micro-motion platform; 10. a first spherical hinge; 11. a second spherical hinge; 12. a convex column; 13. a precision bearing; 14. a control box; 15. a notch; 16. a mounting plate; 17. a slide bar; 18. a compression spring; 19. a connecting rod; 20. and (5) mounting holes.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. The specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
The invention provides a high-precision pointing device for a spacecraft, which is shown in fig. 1:
The device comprises a base 1, wherein a fixed plate 2 is arranged at the central position of the base 1, a micro-motion platform 9 for realizing high-precision pointing of a spacecraft is arranged right above the base 1, and a control box 14 is arranged at the central position of the bottom of the micro-motion platform 9;
The control box 14 is internally and sequentially provided with a control circuit board, a controller and a sensor module, wherein the sensor module comprises a gyroscope for measuring the rotation angle of the spacecraft around a certain axis, a magnetometer for measuring the linear acceleration of the spacecraft on a certain axis, and speed and displacement information can be obtained through integral operation, so that the accelerometer is used for correcting and compensating the posture of the spacecraft, and the magnetometer is used for measuring the magnetic field intensity and direction of the place where the spacecraft is located.
The high-precision sensor in the control box 14 is used for monitoring the position, the speed, the acceleration and other parameters of the micro-motion platform 9 in real time and feeding back the parameters to the controller, and the controller calculates a control instruction according to the feedback parameters and the target pointing instruction to drive the motor 3 to correspondingly adjust so as to ensure that the turntable can realize high-precision pointing motion.
Wherein, the sensor module includes:
a gyroscope: the device is used for measuring the rotation angle of the spacecraft around a certain axis, and is a key component for realizing high-precision attitude control.
An accelerometer: the method is used for measuring the linear acceleration of the spacecraft on a certain axis, and the speed and displacement information can be obtained through integral operation, so that the method is used for correcting and compensating the posture of the spacecraft.
Magnetometer: for measuring the magnetic field strength and direction of the spacecraft locus, magnetometers are indispensable sensors for magnetically sensitive loads such as magnetic recorders and the like.
The invention provides a high-precision pointing device for a spacecraft, which is shown in figures 1-3:
The device comprises a fixed plate 2, and is characterized by further comprising a driving mechanism arranged on the fixed plate 2, wherein the driving mechanism comprises a driving motor 3, a screw rod 4 and a disc 8 which are fixedly arranged at the central position of the fixed plate 2, one end of an output shaft of the driving motor 3 is fixedly connected with the screw rod 4 through a coupler, the upper end of the screw rod 4 is rotationally connected with the central position of the bottom of the disc 8, a convex column 12 is arranged at the central position of the top of the disc 8, and the upper end of the convex column 12 is connected with the central position of the bottom of a micro-motion platform 9 through a first spherical hinge 10;
Specifically, the base 1 is fixed when in use, ensuring the stability and vibration resistance of the base 1. Then, the screw rod 4 is connected with the disc 8 through a precision bearing 13, and preliminary debugging and calibration are carried out, so that the micro-motion platform 9 can realize high-precision motion; the center of the bottom of the disc 8 is provided with a precision bearing 13, and the upper end of the screw rod 4 is inserted and fixed on the inner ring of the precision bearing 13.
The invention provides a high-precision pointing device for a spacecraft, which is shown in figures 1-5:
The micro-motion platform 9 is characterized by further comprising a transmission mechanism for adjusting the micro-motion platform 9, wherein the transmission mechanism comprises a sliding seat 5 arranged on a screw rod 4, a first connecting rod 6 hinged to the edge of the sliding seat 5 and a second connecting rod 7 hinged to the upper end of the first connecting rod 6, four groups of the first connecting rod 6 and the second connecting rod 7 are all arranged on the sliding seat 5 in a surrounding mode, and the upper end of the second connecting rod 7 is connected with the bottom of the micro-motion platform 9 through a second spherical hinge 11.
The slide 5 is the setting of disc 8 form, and the equidistance is gone up and is encircleed and is set up four breach 15, and the lower extreme of first connecting rod 6 articulates in the inside of breach 15, and the other end of first connecting rod 6 is connected in the lower extreme of second connecting rod 7 through articulated mode.
The support of the first spherical hinge 10 is mounted at the bottom of the control box 14, and the sphere of the first spherical hinge 10 is arranged at the upper end of the convex column 12. The support of the second spherical hinge 11 is arranged at the upper end of the second connecting rod 7, and the sphere of the second spherical hinge 11 is arranged at the bottom of the micro-motion platform 9 in a surrounding manner.
Specifically, the drive mechanism is integrated with the control box 14 (high precision sensor and controller) to form a complete drive control system. The control system is responsible for receiving and analyzing the instruction, and drives the micro-motion to conduct high-precision pointing motion.
The invention provides a high-precision pointing device for a spacecraft, which is shown in figures 1-2:
the bottom welding of disc 8 has the connecting rod 19 that is used for fixed disc 8, and the lower extreme welding of connecting rod 19 is in the surface of fixed plate 2, and connecting rod 19 is the slope form setting.
By welding the inclined connecting rod 19 on the base 1, the connecting rod 19 not only can fix the disc 8, but also can have good stability and strength.
The invention provides a high-precision pointing device for a spacecraft, as shown in fig.1 and 6:
The bottom of base 1 still is provided with the installation component, and the installation component includes slide bar 17 and mounting panel 16, and mounting panel 16 is the zigzag setting, and slide bar 17 welds in the bottom of base 1. The slide bar 17 is in sliding connection with the mounting plate 16, the lower end of the slide bar 17 penetrates through the mounting plate 16 and is connected with a limiting block, two groups of rubber rings are sleeved between the mounting plate 16 and the base 1 on the slide bar 17, and a compression spring 18 is sleeved between the two groups of rubber rings on the slide bar 17.
Through setting up the installation component including slide bar 17 and mounting panel 16 in base 1 bottom, the slide bar 17 of base 1 bottom is slided and is pegged graft in mounting panel 16, has cup jointed compression spring 18 and rubber circle on the slide bar 17, has seted up mounting hole 20 on the mounting panel 16, in the use of equipment, installation component not only can fix and install base 1, in addition at micro-motion platform 9, during the mechanism work such as driving motor 3, can play good cushioning effect for base 1 has stability more, has further improved the precision of equipment.
The invention provides a high-precision pointing device for a spacecraft, which solves the problems of low precision, poor stability, large volume and the like in the prior art. The device has the advantages of compact structure, high pointing precision, good stability, high response speed, low power consumption and the like, and is suitable for spacecrafts such as space telescopes, communication satellites and the like which need to precisely control pointing. The implementation of the invention can help to improve the performance and the reliability of the spacecraft and promote the further development of the aerospace technology
Taking a space telescope as an example, the high-precision pointing device for the spacecraft can be applied to a pointing system of the space telescope. The control module receives ground instructions and control signals, and the driving motor drives the transmission mechanism and the high-precision pointing mechanism to precisely point and track. Meanwhile, the sensor monitors the state and position information of the device in real time, and feeds the state and position information back to the control module for closed-loop control, so that the pointing accuracy and stability are ensured.
Finally, it should be noted that: the foregoing description is only illustrative of the preferred embodiments of the present invention, and although the present invention has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that modifications may be made to the embodiments described, or equivalents may be substituted for elements thereof, and any modifications, equivalents, improvements or changes may be made without departing from the spirit and principles of the present invention.
Claims (8)
1. A high-precision pointing device for a spacecraft is characterized in that: the device comprises a base (1), wherein a fixed plate (2) is arranged at the central position of the base (1), a micro-motion platform (9) for realizing high-precision pointing of a spacecraft is arranged right above the base (1), and a control box (14) is arranged at the central position of the bottom of the micro-motion platform (9);
the device is characterized by further comprising a driving mechanism arranged on the fixed plate (2), wherein the driving mechanism comprises a driving motor (3), a screw rod (4) and a disc (8) which are fixedly arranged at the central position of the fixed plate (2), one end of an output shaft of the driving motor (3) is fixedly connected with the screw rod (4) through a coupler, the upper end of the screw rod (4) is rotationally connected to the central position of the bottom of the disc (8), a convex column (12) is arranged at the central position of the top of the disc (8), and the upper end of the convex column (12) is connected with the central position of the bottom of the micro platform (9) through a first spherical hinge (10);
The micro-motion platform comprises a screw rod (4), and is characterized by further comprising a transmission mechanism for adjusting the micro-motion platform (9), wherein the transmission mechanism comprises a sliding seat (5) arranged on the screw rod (4), a first connecting rod (6) hinged to the edge of the sliding seat (5) and a second connecting rod (7) hinged to the upper end of the first connecting rod (6), four groups of the first connecting rod (6) and the second connecting rod (7) are all arranged on the sliding seat (5) in a surrounding mode, and the upper end of the second connecting rod (7) is connected with the bottom of the micro-motion platform (9) through a second spherical hinge (11).
2. The high-precision pointing device for spacecraft of claim 1, wherein: the control box (14) is internally provided with a control circuit board, a controller and a sensor module in sequence, wherein the sensor module comprises a gyroscope for measuring the rotation angle of the spacecraft around a certain axis, a linear acceleration of the spacecraft on a certain axis, speed and displacement information can be obtained through integral operation, and then an accelerometer for correcting and compensating the posture of the spacecraft and a magnetometer for measuring the magnetic field intensity and direction of the place where the spacecraft is located.
3. The high-precision pointing device for spacecraft of claim 1, wherein: the support of the first spherical hinge (10) is arranged at the bottom of the control box (14), and the sphere of the first spherical hinge (10) is arranged at the upper end of the convex column (12).
4. The high-precision pointing device for spacecraft of claim 1, wherein: the support of the second spherical hinge (11) is arranged at the upper end of the second connecting rod (7), and the sphere of the second spherical hinge (11) is arranged at the bottom of the micro-motion platform (9) in a surrounding mode.
5. The high-precision pointing device for spacecraft of claim 1, wherein: the sliding seat (5) is arranged in a disc (8) shape, four groups of notches (15) are formed in the sliding seat (5) in an equidistant mode in a surrounding mode, the lower end of the first connecting rod (6) is hinged to the inside of the notch (15), and the other end of the first connecting rod (6) is connected to the lower end of the second connecting rod (7) in a hinged mode.
6. The high-precision pointing device for spacecraft of claim 1, wherein: the bottom welding of disc (8) has connecting rod (19) that are used for fixed disc (8), the lower extreme welding of connecting rod (19) is in the surface of fixed plate (2), connecting rod (19) are the slope form setting.
7. The high-precision pointing device for spacecraft of claim 1, wherein: the bottom of base (1) still is provided with the installation component, the installation component includes slide bar (17) and mounting panel (16), mounting panel (16) are the zigzag setting, slide bar (17) welding is in the bottom of base (1).
8. The high-precision pointing device for a spacecraft of claim 7, wherein: the sliding rod (17) is connected with the mounting plate (16) in a sliding mode, the lower end of the sliding rod (17) penetrates through the mounting plate (16) and is connected with a limiting block, two groups of rubber rings are sleeved between the mounting plate (16) and the base (1) on the sliding rod (17), and a compression spring (18) is sleeved between the two groups of rubber rings on the sliding rod (17).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410244765.3A CN118004448A (en) | 2024-03-04 | 2024-03-04 | High-precision pointing device for spacecraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202410244765.3A CN118004448A (en) | 2024-03-04 | 2024-03-04 | High-precision pointing device for spacecraft |
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| Publication Number | Publication Date |
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| CN118004448A true CN118004448A (en) | 2024-05-10 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202410244765.3A Pending CN118004448A (en) | 2024-03-04 | 2024-03-04 | High-precision pointing device for spacecraft |
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| CN (1) | CN118004448A (en) |
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- 2024-03-04 CN CN202410244765.3A patent/CN118004448A/en active Pending
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