CN117719698A - Two-stage active vibration isolation directional satellite platform configuration based on magnetic levitation actuator and Stewart voice coil motor - Google Patents
Two-stage active vibration isolation directional satellite platform configuration based on magnetic levitation actuator and Stewart voice coil motor Download PDFInfo
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- CN117719698A CN117719698A CN202311771383.8A CN202311771383A CN117719698A CN 117719698 A CN117719698 A CN 117719698A CN 202311771383 A CN202311771383 A CN 202311771383A CN 117719698 A CN117719698 A CN 117719698A
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Abstract
The invention provides a two-stage active vibration isolation directional satellite platform configuration based on a magnetic suspension actuator and a Stewart voice coil motor, which relates to the field of satellite vibration isolation configuration design. The invention can provide quiet working environment for the front end part and the rear end part of the split load at the same time, and realize decoupling control of the two parts of loads; the satellite has simple configuration, and can be used in high-low orbit satellites, in particular in the fields of large optical satellites with high micro-vibration requirements, large satellite scale, complex load and the like.
Description
Technical Field
The invention relates to the field of satellite vibration isolation configuration design, in particular to a two-stage active vibration isolation directional satellite platform configuration based on a magnetic levitation actuator and a Stewart voice coil motor.
Background
Along with the increasing complexity of the scale and the functions of the spacecraft, large flexible accessories and rotating mechanisms such as a solar sailboard, an antenna, a light shield, a control moment gyro and the like need to be configured, so that the high-precision imaging, the rapid attitude maneuver and the stability of the satellite are affected. And along with the appearance of split type load with complex functions, the traditional primary active vibration isolation can not realize that the front end and the rear end of the load all need to be realized with vibration isolation and alignment control simultaneously, so that a new satellite configuration for respectively realizing vibration isolation on the front end and the rear end of the load needs to be designed.
The patent of self-flying and the like designs a passive vibration isolation device consisting of a vibration absorption elastic unit, a damping layer and the like in a micro-vibration isolation and vibration absorption combined vibration reduction device (CN 201410588759.6) for a satellite flywheel and a micro-vibration parallel vibration isolation device (CN 201410572359.6) for a satellite control moment gyro group, so as to reduce micro-vibration response of vibration sources such as the flywheel, the CMG and the like. The passive vibration isolation system is a typical single-machine passive vibration isolation system, and can not meet the index requirement of high-precision optical and other loads on micro-vibration.
Zhou Liubin et al in the patent "an electromagnetic active-passive composite vibration isolator" (CN 201510396715.8) designed an active-passive composite vibration isolator in which a passive vibration isolator and a non-contact active electromagnetic actuator are connected in series, so as to effectively isolate vibration in different frequency bands. However, the device is only used for vibration isolation, and cannot realize the function of directional control.
Zheng Gangtie et al in patent "satellite payload multiple degree of freedom isolator and system" (CN 201110058327.0) designed a passive isolator for isolating platform vibrations, and designed an isolation system using the isolator to realize attenuation of platform vibrations to load transfer. The passive vibration isolation structure is simple, but the vibration isolation efficiency is lower than that of the active vibration isolation.
Shang Liang et al in patent "ultra-high precision attitude of spacecraft multistage compound control" (CN 201810588771.5) describe a satellite platform, an active and active pointing ultra-static platform and a fast reflector three-stage vibration isolation platform, and load ultra-static environment is realized through vibration source, load and fast reflector three-stage vibration compensation. But this approach does not allow for a vibration isolation design that separates the loads.
Zhang Wei et al describe a non-contact two-cabin satellite configuration based on a magnetic suspension actuator in a patent of a double super satellite eight-rod six-degree-of-freedom satellite platform and a decoupling control method thereof (CN 201810588771.5), and the non-contact two-cabin satellite configuration is applied to a platform and a load two-body satellite only by micro-vibration of a non-contact isolation platform in space.
At present, research on the active vibration isolation direction of the front end and the rear end of the load is not seen. The invention designs a satellite configuration with two-stage active vibration isolation pointing based on a non-contact magnetic levitation actuator and a Stewart voice coil motor technology.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a two-stage active vibration isolation directional satellite platform configuration based on a magnetic levitation actuator and a Stewart voice coil motor.
The invention provides a two-stage active vibration isolation directional satellite platform configuration based on a magnetic suspension actuator and a Stewart voice coil motor, which comprises a satellite platform, a rear-end active vibration isolation, a load rear end, a middle cabin section, a front-end active vibration isolation and a load front end, wherein the load front end is connected with the middle cabin section of the satellite through the front-end active vibration isolation, the load rear end is connected with the satellite platform through the rear-end active vibration isolation, the load rear end and the load front end realize vibration isolation on the satellite platform through the rear-end active vibration isolation and the front-end active vibration isolation respectively, and the alignment of the load rear end and the load front end is realized by adjusting the direction and the position of the load rear end;
six Stewart voice coil motors are adopted for rear-end active vibration isolation, and eight magnetic levitation actuators are adopted for front-end active vibration isolation; or eight magnetic levitation actuators are adopted for rear-end active vibration isolation, and six Stewart voice coil motors are adopted for front-end active vibration isolation.
Preferably, the front end of the load is in non-contact connection with the satellite platform through front end active vibration isolation, and the front end active vibration isolation keeps the relative position and the relative posture of the front end of the load and the satellite platform, so that collision between the load and the satellite platform is avoided.
Preferably, the rear load end is in non-contact connection with the satellite platform through rear end active vibration isolation, and a control instruction is calculated by feeding back the relative position and relative posture information of the rear load end relative to the front load end, so that the rear load end is aligned to the front load end, and the load requirement is met.
Preferably, the relative position and the relative posture of the load rear end and the load front end are accurately tested through a high-precision measuring device, and the high-precision measuring device realizes closed-loop control of the relative posture.
Preferably, the control of the relative position and relative attitude of the rear end of the load with respect to the front end of the load is achieved by closed loop control.
Preferably, the rear end active vibration isolation, the load rear end, the front end active vibration isolation and the load front end are respectively connected in the satellite service cabin, the middle cabin section is fixedly connected in the satellite service cabin, and the middle cabin section provides structural support for the front end active vibration isolation.
Preferably, the load rear end and the load front end realize information interaction through inter-cabin cables or wireless communication and laser communication.
Preferably, the load rear end and the load front end are powered by an inter-bay cable.
Preferably, a moving part, a flexible part and a storage tank are arranged on the satellite platform, and the satellite platform realizes whole-satellite energy supply, satellite-ground information interaction and orbit and attitude control of the service cabin.
Compared with the prior art, the invention has the following beneficial effects:
the invention can provide quiet working environment for the front end part and the rear end part of the split load at the same time, and realize decoupling control of the two parts of loads; the satellite has simple configuration, and can be used in high-low orbit satellites, in particular in the fields of large optical satellites with high micro-vibration requirements, large satellite scale, complex load and the like.
Drawings
Other features, objects and advantages of the present invention will become more apparent upon reading of the detailed description of non-limiting embodiments, given with reference to the accompanying drawings in which:
FIG. 1 is a schematic structural diagram of embodiment 1 of the present invention;
fig. 2 is a schematic structural diagram of embodiment 2 of the present invention.
Reference numerals in the drawings: the system comprises a satellite platform 1, a rear-end active vibration isolation 2, a load rear end 3, an intermediate cabin section 4, a front-end active vibration isolation 5 and a load front end 6.
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the present invention, but are not intended to limit the invention in any way. It should be noted that variations and modifications could be made by those skilled in the art without departing from the inventive concept. These are all within the scope of the present invention.
Example 1
According to the two-stage active vibration isolation directional satellite platform configuration based on the magnetic levitation actuator and the Stewart voice coil motor, as shown in fig. 1, the two-stage active vibration isolation directional satellite platform configuration comprises a satellite platform 1, a rear-end active vibration isolation 2, a load rear end 3, an intermediate cabin section 4, a front-end active vibration isolation 5 and a load front end 6, wherein six Stewart voice coil motors are adopted for the rear-end active vibration isolation 2, and eight magnetic levitation actuators are adopted for the front-end active vibration isolation 5.
The front load end 6 is connected with the middle cabin section 4 of the satellite through the front end active vibration isolation 5, and the rear load end 3 is connected with the satellite platform 1 through the rear end active vibration isolation 2. Vibration isolation of the load front end 6 and the satellite platform 1 is realized through the distribution of the non-contact front end active vibration isolation 5, and a control instruction is calculated through feeding back the relative position and relative posture information of the load front end 6 relative to the satellite platform 1, so that the distance between the load front end 6 and the satellite platform 1 is ensured to be kept in a certain range, and collision between the load and the satellite platform 1 is avoided. Vibration isolation of the load rear end 3 and the satellite platform 1 is realized through the layout rear end active vibration isolation 2, a control instruction is calculated through feedback of relative position and relative posture information of the load rear end 3 relative to the load front end 6, and alignment of the load rear end 3 to the load front end 6 is realized through adjustment of the pointing direction and the position of the load rear end 3, so that the load requirement is met. In order to realize closed-loop control of the relative pose, a high-precision measuring device needs to be configured to accurately test the relative position and the relative pose of the load rear end 3 and the load front end 6, and the relative position and the relative pose are used as measurement information of the relative pose control. The relative position and relative attitude of the load rear end 3 with respect to the load front end 6 are maintained at the desired control by closed loop control.
The load rear end 3 and the load front end 6 realize information interaction through inter-cabin cables or wireless communication and laser communication, and the load rear end 3 and the load front end 6 realize power supply through the inter-cabin cables. The load rear end 3 and the load front end 6 are respectively the rear end and the front end of a separated load, the relative positions and the relative postures of the two parts are required to be kept in a certain range, and the two parts are matched in a cooperative manner to meet the working requirements of the load. The rear-end active vibration isolation 2, the load rear end 3, the front-end active vibration isolation 5 and the load front end 6 are respectively connected in the satellite service cabin, the middle cabin section 4 is fixedly connected in the satellite service cabin, and the middle cabin section 4 provides structural support for the front-end active vibration isolation 5.
The satellite platform 1 is provided with a motion part such as a control moment gyro, a flexible part such as a solar wing and a large antenna, a storage tank and the like, and mainly realizes functions such as whole-satellite energy, information, attitude control and the like, and a thruster and the storage tank are arranged to realize orbit adjustment and orbit position of a satellite; the two-wing solar sailboard, the driving mechanism, the storage battery pack and the PCDU are installed to realize energy supply; mounting a measurement and control antenna, a data transmission antenna and a driving mechanism to realize the transmission of ground information; six control moment gyroscopes are installed to realize attitude maneuver and stable control of the whole star.
Example 2
This example 2 was completed on the basis of example 1, as shown in fig. 2, and is specifically as follows:
eight magnetic levitation actuators are adopted in the rear-end active vibration isolation 2, and six Stewart voice coil motors are adopted in the front-end active vibration isolation 5.
In the description of the present application, it should be understood that the terms "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," and the like indicate orientations or positional relationships based on the orientations or positional relationships illustrated in the drawings, merely to facilitate description of the present application and simplify the description, and do not indicate or imply that the devices or elements being referred to must have a specific orientation, be configured and operated in a specific orientation, and are not to be construed as limiting the present application.
The foregoing describes specific embodiments of the present invention. It is to be understood that the invention is not limited to the particular embodiments described above, and that various changes or modifications may be made by those skilled in the art within the scope of the appended claims without affecting the spirit of the invention. The embodiments of the present application and features in the embodiments may be combined with each other arbitrarily without conflict.
Claims (9)
1. The two-stage active vibration isolation directional satellite platform configuration based on a magnetic levitation actuator and a Stewart voice coil motor is characterized by comprising a satellite platform (1), a rear-end active vibration isolation (2), a load rear end (3), a middle cabin section (4), a front-end active vibration isolation (5) and a load front end (6), wherein the load front end (6) is connected with the middle cabin section (4) of a satellite through the front-end active vibration isolation (5), the load rear end (3) is connected with the satellite platform (1) through the rear-end active vibration isolation (2), and the load rear end (3) and the load front end (6) realize vibration isolation of the satellite platform (1) through the rear-end active vibration isolation (2) and the front-end active vibration isolation (5) respectively, and realize alignment of the load rear end (3) and the load front end (6) through adjustment of the direction and the position of the load rear end (3).
Six Stewart voice coil motors are adopted for the rear-end active vibration isolation (2), and eight magnetic levitation actuators are adopted for the front-end active vibration isolation (5); or, eight magnetic levitation actuators are adopted for the rear-end active vibration isolation (2), and six Stewart voice coil motors are adopted for the front-end active vibration isolation (5).
2. The two-stage active vibration isolation pointing satellite platform configuration based on a magnetic levitation actuator and a Stewart voice coil motor according to claim 1, wherein the load front end (6) is in non-contact connection with the satellite platform (1) through the front end active vibration isolation (5), and the front end active vibration isolation (5) maintains the relative position and the relative posture of the load front end (6) and the satellite platform (1) so as to avoid collision of the load and the satellite platform (1).
3. The two-stage active vibration isolation directional satellite platform configuration based on the magnetic levitation actuator and the Stewart voice coil motor according to claim 1, wherein the load rear end (3) is in non-contact connection with the satellite platform (1) through the rear end active vibration isolation (2), and control instructions are calculated by feeding back relative position and relative posture information of the load rear end (3) relative to the load front end (6), so that the load rear end (3) is aligned to the load front end (6), and load requirements are met.
4. The two-stage active vibration isolation directional satellite platform configuration based on a magnetic levitation actuator and a Stewart voice coil motor according to claim 3, wherein the relative position and relative attitude of the load rear end (3) and the load front end (6) are accurately tested by a high-precision measuring device, and the high-precision measuring device realizes closed-loop control of the relative pose.
5. The two-stage active vibration isolation directional satellite platform configuration based on a magnetic levitation actuator and a Stewart voice coil motor according to claim 4, wherein the relative position and relative attitude of the load rear end (3) with respect to the load front end (6) is maintained at a desired control by closed loop control.
6. The two-stage active vibration isolation pointing satellite platform configuration based on a magnetic levitation actuator and a Stewart voice coil motor according to claim 1, wherein the rear end active vibration isolation (2), the load rear end (3), the front end active vibration isolation (5) and the load front end (6) are respectively connected in a satellite service cabin, the middle cabin section (4) is fixedly connected in the satellite service cabin, and the middle cabin section (4) provides structural support for the front end active vibration isolation (5).
7. The two-stage active vibration isolation directional satellite platform configuration based on the magnetic levitation actuator and the Stewart voice coil motor according to claim 1, wherein the load rear end (3) and the load front end (6) realize information interaction through inter-cabin cables or wireless communication and laser communication.
8. The two-stage active vibration isolation directional satellite platform configuration based on a magnetic levitation actuator and a Stewart voice coil motor according to claim 1, wherein the load back end (3) and the load front end (6) are powered by an inter-cabin cable.
9. The two-stage active vibration isolation pointing satellite platform configuration based on the magnetic levitation actuator and the Stewart voice coil motor, according to claim 1, is characterized in that a moving part, a flexible part and a storage tank are installed on the satellite platform (1), and the satellite platform (1) realizes whole-satellite energy supply, satellite-ground information interaction and orbit and attitude control of a service cabin.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311771383.8A CN117719698A (en) | 2023-12-20 | 2023-12-20 | Two-stage active vibration isolation directional satellite platform configuration based on magnetic levitation actuator and Stewart voice coil motor |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311771383.8A CN117719698A (en) | 2023-12-20 | 2023-12-20 | Two-stage active vibration isolation directional satellite platform configuration based on magnetic levitation actuator and Stewart voice coil motor |
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| CN117719698A true CN117719698A (en) | 2024-03-19 |
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| CN202311771383.8A Pending CN117719698A (en) | 2023-12-20 | 2023-12-20 | Two-stage active vibration isolation directional satellite platform configuration based on magnetic levitation actuator and Stewart voice coil motor |
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