An intelligent in-orbit micro-vibration suppression system for satellites

Abstract

Intelligent In-orbit Micro-vibration Suppression System for Satellites. It belongs to the technical field of spacecraft systems, specifically involving the technical field of vibration suppression for remote sensing satellites. It solves the problem that the existing variable-parameter satellite vibration isolators cannot be actually controlled and applied. The system includes a variable-parameter satellite vibration isolator, a central control unit, and a power distribution and thermal control unit; the central control unit: includes a rotational speed acquisition module, a parameter calculation module, and a temperature control module; the power distribution and thermal control unit: includes a first power distribution and thermal control unit and a second power distribution and thermal control unit; the second power distribution and thermal control unit receives the temperature control command from the temperature control module and supplies power to the heating wire in the variable-parameter satellite vibration isolator according to the temperature control command. The system of the present invention can be applied in the fields of remote sensing satellite assembly and manufacturing, remote sensing satellite vibration suppression, and remote sensing satellite imaging system design.

Description

Technical Field

[0001] The present invention belongs to the technical field of spacecraft systems, and specifically relates to the technical field of vibration suppression for remote sensing satellites. Background Art

[0002] When a remote sensing satellite is operating in orbit, it is affected by rotating mechanisms such as on-board momentum wheels, control moment gyros, solar panel drive assemblies, and antenna turrets. When these devices work, they generate small-amplitude and wide-frequency disturbing vibrations, which damage the "ultra-temperature and ultra-quiet" environment of the satellite in orbit, and then cause the camera optical axis to shake, resulting in a decline in the imaging quality of the satellite.

[0003] Remote sensing satellites generally use vibration isolators, such as silicone rubber vibration isolators, wire rope vibration isolators, wire spring vibration isolators, etc. to suppress micro-vibrations. This is a passive suppression scheme that does not require additional electrical energy and control signals. The advantages are simple structure and high reliability, while the disadvantages are low vibration isolation efficiency, being designed only for one or several excitation force conditions, usually having only a fixed vibration isolation frequency (for a second-order system), a fixed damping ratio, lack of pertinence, and poor performance.

[0004] Another common suppression method is to install active vibration isolation devices with different driving methods and their control circuits on the satellite. The driving mechanisms are such as Stewart mechanisms, electromagnetic mechanisms, etc. The execution process of the active vibration isolation device is a process of solving the platform attitude by knowing the lengths and positions of six telescopic rods. The solving process is complex and prone to singular solutions. In addition, as the driving process is continuously executed, the cumulative error of the system will increase, and there is a risk of reduction in the calculation accuracy of the system.

[0005] In view of the above defects, the Chinese invention patent application "A Variable-Parameter Satellite Vibration Isolator and Vibration Isolation Method" (application number 202310080576.2) with a filing date of February 8th proposes a variable-parameter satellite vibration isolator, which is formed by co-curing and processing a filled polymer and a metal structure. The mechanical properties of the polymer are extremely sensitive to temperature, and different temperatures correspond to different elastic moduli and damping ratios; a heating wire is installed near the polymer of the vibration isolator. When the heating wire works, the temperature of the polymer of the vibration isolator rises; when the heating wire is idle, the temperature of the polymer of the vibration isolator drops; a thermistor can collect the surface temperature of the polymer. By installing a heating and temperature-measuring circuit on the surface of the polymer of the vibration isolator, the vibration isolation performance of the vibration isolator can be controlled according to the design parameters. However, this Chinese invention patent application only explains the vibration isolation principle and usage method of the variable-parameter satellite vibration isolator, and does not provide an explanation on how to specifically and practically apply the variable-parameter satellite vibration isolator in the real on-orbit satellite operating environment. Summary of the Invention

[0006] To solve the problem that the existing variable-parameter satellite vibration isolator cannot be actually controlled and applied, the present invention provides a satellite on-orbit micro-vibration intelligent suppression system.

[0007] The system includes a central machine control unit, a power distribution and thermal control unit, and a variable-parameter satellite vibration isolator. The central machine control unit: includes a rotational speed acquisition module, a parameter calculation module, and a temperature control module. The rotational speed acquisition module is used to acquire the current rotational speed information of the flywheel group and input the rotational speed information into the parameter calculation module. The parameter calculation module is used to determine the control target temperature value of the variable-parameter satellite vibration isolator according to the rotational speed information and input the control target temperature value into the temperature control module. The temperature control module is used to send a temperature acquisition instruction to the power distribution and thermal control unit; it is also used to generate a temperature control instruction according to the control target temperature value and input the temperature control instruction into the power distribution and thermal control unit. The power distribution and thermal control unit includes a second power distribution and thermal control unit; the second power distribution and thermal control unit is used to acquire the current temperature of the variable-parameter satellite vibration isolator according to the temperature acquisition instruction and is also used to adjust the temperature of the variable-parameter satellite vibration isolator according to the temperature control instruction; the variable-parameter satellite vibration isolator: includes a filled polymer, a resistance wire, and a thermistor, the resistance wire heats the filled polymer, and the thermistor acquires the temperature value of the filled polymer; when the variable-parameter satellite vibration isolator works, the vibration isolation performance is changed by changing the temperature of the filled polymer.

[0008] Further, for the system according to claim 1, it is characterized in that the current rotational speed information of the flywheel group includes the current rotational speed value of the flywheel group + ω x r·min -1 and the rotational speed change value of the flywheel group Δω x r·min -1 .

[0009] Further, the method for determining the control target temperature value of the variable-parameter satellite vibration isolator is as follows: the parameter calculation module calculates the rotational speed value of the flywheel group at the time of satellite imaging (ω x+ Δω x ·ΔT) r·min -1 according to the current rotational speed value of the flywheel group, the rotational speed change value of the flywheel group, and the planned imaging time ΔT, and checks the flywheel group rotational speed - frequency - vibration amplitude value data table and the polymer temperature - damping ratio - elastic modulus data table according to the rotational speed value of the flywheel group at the time of satellite imaging to determine the control target temperature value T i of the variable-parameter satellite vibration isolator, so that F(Ω i , f)·*T r ≤F0(Ω i , f), where F(Ω i , f) is the vibration amplitude value at the rotational speed of Ω i , and T rFor the transfer efficiency of the variable-parameter satellite vibration isolator, F0(Ω i , f) is the limit value of the disturbing amplitude at the rotational speed of Ω i .

[0010] Furthermore, to obtain the rotational speed-frequency-disturbing amplitude data table of the flywheel group, the method adopted is as follows:

[0011] Conduct a ground test, measure the relationship data F(Ω, f) of the rotational speed Ω, frequency f, and disturbing amplitude F of the flywheel group through a force measuring platform, make a rotational speed-frequency-disturbing amplitude data table of the flywheel group, and write the data table into the parameter calculation module.

[0012] Furthermore, to obtain the polymer temperature-damping ratio-elastic modulus data table, the method adopted is as follows:

[0013] Conduct a ground test, obtain the relationship data T(E, ζ) between the polymer temperature T, polymer damping ratio ζ, and polymer elastic modulus E in the variable-parameter satellite vibration isolator through dynamic thermomechanical analysis of materials, make a polymer temperature-damping ratio-elastic modulus data table, and write the data table into the parameter calculation module.

[0014] Furthermore, where λ represents the frequency ratio, λ = f / f n , f n is the natural frequency of the variable-parameter satellite vibration isolator.

[0015] Furthermore, the method for collecting the current temperature of the variable-parameter satellite vibration isolator according to the temperature acquisition instruction is as follows:

[0016] Power the thermistor in the variable-parameter satellite vibration isolator according to the temperature acquisition instruction, and the thermistor collects the temperature of the variable-parameter satellite vibration isolator.

[0017] Furthermore, the method for adjusting the temperature of the variable-parameter satellite vibration isolator according to the temperature control instruction is as follows:

[0018] Power the heating wire in the variable-parameter satellite vibration isolator according to the temperature control instruction, and the heating wire heats the filled polymer.

[0019] Furthermore, the power distribution thermal control unit further includes a first power distribution thermal control unit, and the first power distribution thermal control unit powers the flywheel group of the satellite.

[0020] The beneficial effects of the system of the present invention are as follows:

[0021] (1) Provide a complete control system for the variable-parameter satellite vibration isolator to perform vibration isolation operations in the real in-orbit space of remote sensing satellites, including a central control unit and a power distribution and thermal control unit. Among them, the central control unit calculates the required temperature of the vibration isolator, and the power distribution and thermal control unit controls the temperature of the vibration isolator. The parameter calculation and parameter control of the variable-parameter satellite vibration isolator are separately executed. Each unit in the system has a clear division of labor, and when a fault occurs, the maintenance operation is more convenient. By corresponding different functions to different units and having each unit cooperate, the control accuracy and control efficiency of the variable-parameter satellite vibration isolator are improved.

[0022] (2) A feedback mechanism is set in the central control unit and the power distribution and thermal control unit, specifically manifested as: the second power distribution and thermal control unit outputs voltage to the resistance wire of the variable-parameter satellite vibration isolator according to the control target temperature value. The temperature of the resistance wire rises, heating the filled polymer to reach the target temperature. The resistance wire has a simple structure, high heating efficiency, and saves resources; at the same time, the second power distribution and thermal control unit real-time measures the temperature of the variable-parameter satellite vibration isolator through a thermistor and feeds back the temperature to the temperature control module, and the temperature control module decides whether to continue to supply power to the resistance wire to ensure that after a specified time, the variable-parameter satellite vibration isolator reaches the required temperature and does not exceed the required temperature. The control performed by the system of the present invention is all automatically carried out by the system, which is easy to use.

[0023] The system of the present invention can be applied in the fields of remote sensing satellite assembly and manufacturing, remote sensing satellite vibration suppression, and remote sensing satellite imaging system design. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 It is a schematic diagram of the in-orbit micro-vibration intelligent suppression system for remote sensing satellites;

[0025] Figure 2 It is an installation schematic diagram of each part of the in-orbit micro-vibration intelligent suppression system for remote sensing satellites. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0026] The technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are some, but not all, of the embodiments of the present invention. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present invention without creative efforts shall fall within the protection scope of the present invention.

[0027] Example 1.

[0028] As Figure 1 shown is a schematic diagram of the in-orbit micro-vibration intelligent suppression system provided by this embodiment. The system includes a variable-parameter satellite vibration isolator, a central control unit, and a power distribution and thermal control unit.

[0029] The variable-parameter satellite vibration isolator adopts the variable-parameter satellite vibration isolator proposed in the Chinese invention patent application "A Variable-parameter Satellite Vibration Isolator and Vibration Isolation Method" with the application date of February 8th (application number 202310080576.2).

[0030] The central machine control unit: includes a rotational speed acquisition module, a parameter calculation module, and a temperature control module; the rotational speed acquisition module acquires the current rotational speed information of the flywheel group and inputs it into the parameter calculation module, the parameter calculation module determines the control target temperature value of the variable-parameter satellite vibration isolator according to the rotational speed information, writes the control target temperature value into the temperature control module, the temperature control module sends a temperature control instruction to the power distribution thermal control unit, and the power distribution thermal control unit conducts temperature control on the variable-parameter satellite vibration isolator. The temperature control module sends a temperature acquisition instruction to the power distribution thermal control unit, and the power distribution thermal control unit acquires the temperature of the variable-parameter satellite vibration isolator and inputs the acquired temperature value into the temperature control module.

[0031] Other types of modules can also be added to the central machine control unit according to specific needs, such as Figure 1 As shown, a rotational speed control module is also added to control the rotational speed of the flywheel group by receiving attitude control instructions.

[0032] The variable-parameter satellite vibration isolator: includes a filled polymer, a heating wire, and a thermistor. The heating wire heats the polymer material, and the thermistor acquires the temperature value of the filled polymer; when the variable-parameter satellite vibration isolator works, the vibration isolation performance is changed by changing the temperature of the filled polymer.

[0033] The power distribution thermal control unit: includes a first power distribution thermal control unit and a second power distribution thermal control unit; the first power distribution thermal control unit supplies power to the flywheel group of the satellite, the second power distribution thermal control unit receives the temperature control instruction of the temperature control module, supplies power to the heating wire in the variable-parameter satellite vibration isolator according to the temperature control instruction, and the heating wire conducts a heating operation on the variable-parameter satellite vibration isolator. The second power distribution thermal control unit receives the temperature acquisition instruction of the temperature control module, supplies power to the thermistor in the variable-parameter satellite vibration isolator according to the temperature acquisition instruction, and the thermistor acquires the temperature of the variable-parameter satellite vibration isolator.

[0034] Embodiment 2.

[0035] This embodiment further limits Embodiment 1. The current rotational speed information of the flywheel group acquired by the rotational speed acquisition module includes the current rotational speed value + ω x r·min -1 of the flywheel group and the rotational speed change value Δω x r·min -1 . Among them, when the flywheel group accelerates, the rotational speed change value Δω of the flywheel groupx r·min -1 Take a positive value for the change value Δω of the flywheel group speed when the flywheel group decelerates. x r·min -1 Take a negative value.

[0036] Embodiment 3.

[0037] This embodiment further limits Embodiment 2. The parameter calculation module calculates the rotational speed value (ω x+ Δω x ·ΔT) r·min of the flywheel group during satellite imaging based on the current rotational speed value of the flywheel group, the change value of the flywheel group speed, and the planned imaging time ΔT. -1 For example, the current rotational speed of flywheel X is ω x r·min -1 and it is decreasing at a speed of Δω x r·min -1 . Then, after ΔT time, the rotational speed of the flywheel becomes (ω x -Δω x ·ΔT) r·min -1 , and the rotational speed remains slightly changed during the imaging time, considering the rotational speed of the flywheel remains unchanged during this process.

[0038] Look up the flywheel group speed - frequency - vibration amplitude value data table and the polymer temperature - damping ratio - elastic modulus data table according to the rotational speed value of the flywheel group during satellite imaging to determine the control target temperature value T i of the variable - parameter satellite isolator, such that F(Ω i , f)·*T r ≤F0(Ω i , f), where F(Ω i , f) is the vibration amplitude value at the rotational speed of Ω i , T r is the transfer efficiency of the variable - parameter satellite isolator, and F0(Ω i , f) is the limit value of the vibration amplitude value at the rotational speed of Ω i .

[0039] Embodiment 4.

[0040] This embodiment further limits Embodiment 3. The flywheel group speed - frequency - vibration amplitude value data table is obtained during the ground test stage. The obtaining method of the flywheel group speed - frequency - amplitude data table is as follows: Conduct a ground test, measure the relationship data F(Ω, f) of the flywheel group speed Ω, the flywheel group frequency f, and the flywheel group vibration amplitude value F through a force - measuring platform, make a flywheel group speed - frequency - amplitude data table, and write the data table into the parameter calculation module.

[0041] Embodiment 5.

[0042] This embodiment further limits Embodiment 3. The polymer temperature-damping ratio-elastic modulus data table is obtained during the ground test stage. The obtaining method of the polymer temperature-damping ratio-elastic modulus data table is as follows: Conduct a ground test, and through dynamic thermomechanical analysis of materials, obtain the relationship data T(E,ζ) between the polymer temperature T, the polymer damping ratio ζ, and the polymer elastic modulus E in the variable-parameter satellite vibration isolator, and make a polymer temperature-damping ratio-elastic modulus data table, and write the data table into the parameter calculation module.

[0043] Embodiment 6.

[0044] This embodiment further limits Embodiment 3. Where λ represents the frequency ratio, λ = f / f n , f n is the natural frequency of the variable-parameter satellite vibration isolator. Look up the polymer temperature-damping ratio-elastic modulus data table to determine the polymer damping ratio ζ such that F(Ω i , f)·*T r ≤F0(Ω i , f), so as to determine the control target temperature value Ti of the polymer.

[0045] Embodiment 7.

[0046] This embodiment further limits Embodiment 3. The second power distribution thermal control unit outputs voltage to the heating wire of the variable-parameter satellite vibration isolator according to the control target temperature value T i , and the temperature of the heating wire rises to heat the polymer to reach the target temperature. At the same time, the second power distribution thermal control unit real-time measures the temperature of the variable-parameter satellite vibration isolator through a thermistor and feeds back the temperature to the temperature control module. The temperature control module decides whether to continue to supply power to the heating wire to ensure that after ΔT time, the variable-parameter satellite vibration isolator reaches the required temperature.

[0047] Embodiment 8.

[0048] This embodiment further limits Embodiment 1. For example Figure 2The following is a schematic diagram of the installation of each part of the intelligent micro-vibration suppression system for a remote sensing satellite in orbit. The optical system 1 for satellite imaging is installed on the satellite platform 3. The central computer control unit 4 is installed on the satellite platform 3. The power distribution and thermal control unit 2 is installed on the satellite platform 3. The variable parameter satellite isolator 6 is installed between the satellite platform 3 and the reaction wheel 5. Under normal circumstances, the reaction wheel provides 4 flange holes with a diameter of 20 mm to 50 mm and a height of 5 mm to 10 mm for the variable parameter satellite isolator. One end of the variable parameter satellite isolator is connected to the satellite platform 3, and the other end is connected to the reaction wheel end cover and screws through the flange holes. During installation, first connect and fix the optical system 1 to the satellite platform 3, then install the central computer control unit 4 and the power distribution and thermal control unit 2 on the satellite platform 3, and finally install the variable parameter satellite isolator 6 and the reaction wheel. All mechanical connections are installed using titanium alloy screws and the aerospace standard torque is used during installation.

Claims

1. An intelligent suppression system for on-orbit micro-vibrations of a satellite, characterized in that, The system includes a central machine control unit, a power distribution thermal control unit, and a variable parameter satellite vibration isolator; The central machine control unit: includes a rotational speed acquisition module, a parameter calculation module, and a temperature control module; The rotational speed acquisition module is used to acquire the current rotational speed information of the flywheel group and input the rotational speed information into the parameter calculation module; The parameter calculation module is used to determine the control target temperature value of the variable parameter satellite vibration isolator according to the rotational speed information and input the control target temperature value into the temperature control module; The temperature control module is used to send a temperature acquisition instruction to the power distribution thermal control unit; it is also used to generate a temperature control instruction according to the control target temperature value and input the temperature control instruction into the power distribution thermal control unit; The power distribution thermal control unit includes a second power distribution thermal control unit; The second power distribution thermal control unit is used to acquire the current temperature of the variable parameter satellite vibration isolator according to the temperature acquisition instruction and is also used to adjust the temperature of the variable parameter satellite vibration isolator according to the temperature control instruction; The variable parameter satellite vibration isolator: includes a filled polymer, a resistance wire, and a thermistor. The resistance wire heats the filled polymer, and the thermistor acquires the temperature value of the filled polymer; when the variable parameter satellite vibration isolator works, the vibration isolation performance is changed by changing the temperature of the filled polymer.

2. The system according to claim 1, wherein The current rotational speed information of the flywheel group includes the current rotational speed value +ω of the flywheel group x r·min -1 and the rotational speed change value Δω of the flywheel group x r·min -1 .

3. The system according to claim 2, wherein The method for determining the control target temperature value of the variable parameter satellite vibration isolator is as follows: The parameter calculation module calculates the rotational speed value (ω) of the flywheel group during satellite imaging based on the current rotational speed value of the flywheel group, the change value of the flywheel group's rotational speed, and the planned imaging time ΔT x+ Δω x ·ΔT) r·min -1 , and determines the control target temperature value T of the variable-parameter satellite isolator by looking up the flywheel group rotational speed - frequency - amplitude data table and the polymer temperature - damping ratio - elastic modulus data table according to the rotational speed value of the flywheel group during satellite imaging i , such that F(Ω i , f)·*T r ≤F0(Ω i , f), where F(Ω i , f) is the amplitude at the rotational speed of Ω i , T r is the transmission efficiency of the variable-parameter satellite isolator, and F0(Ω i , f) is the amplitude limit value at the rotational speed of Ω i .

4. The system according to claim 3, wherein The method for acquiring the rotational speed-frequency-amplitude data table of the flywheel group is as follows: Conduct a ground test. By measuring with a force measuring platform, obtain the relationship data F(Ω, f) between the rotational speed Ω of the flywheel group, the frequency f of the flywheel group, and the vibration amplitude value F of the flywheel group, make a rotational speed-frequency-amplitude data table of the flywheel group, and write the data table into the parameter calculation module.

5. The system according to claim 3, characterized in that, The method for acquiring the polymer temperature-damping ratio-elastic modulus data table is as follows: Conduct a ground test. Through dynamic thermomechanical analysis of materials, obtain the relationship data T(E, ζ) between the polymer temperature T, the polymer damping ratio ζ, and the polymer elastic modulus E in the variable parameter satellite vibration isolator, make a polymer temperature-damping ratio-elastic modulus data table, and write the data table into the parameter calculation module.

6. The system according to claim 3, wherein where λ represents the frequency ratio, λ = f / f n , f n is the natural frequency of the variable-parameter satellite vibration isolator.

7. The system according to claim 1, characterized in that The method for acquiring the current temperature of the variable parameter satellite vibration isolator according to the temperature acquisition instruction is as follows: Power the thermistor in the variable parameter satellite vibration isolator according to the temperature acquisition instruction, and the thermistor acquires the temperature of the variable parameter satellite vibration isolator.

8. The system according to claim 1, wherein The method for adjusting the temperature of the variable parameter satellite vibration isolator according to the temperature control instruction is as follows: Power the resistance wire in the variable parameter satellite vibration isolator according to the temperature control instruction, and the resistance wire heats the filled polymer.

9. The system according to claim 1, characterized in that, The power distribution thermal control unit further includes a first power distribution thermal control unit, and the first power distribution thermal control unit powers the flywheel group of the satellite.

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