KR20210082971A - Method and apparatus for performing vibration shake test of satellites - Google Patents

Abstract

A satellite vibration excitation test method and an apparatus thereof are provided. The satellite vibration excitation test apparatus according to an embodiment of the present invention comprises: a sensor data receiving unit for receiving a plurality of force sensor data from the satellite; a plurality of charge signal amplifiers corresponding to each of the plurality of force sensor data; a force moment calculation logic unit for calculating the total force and moment of the satellite using a voltage signal output from the charge signal amplifier; a vibration control unit for controlling vibration using the force moment of the satellite output from the force moment calculation logic unit; and a communication unit for performing network communication with a force moment monitoring device.

Description

Satellite vibration excitation test method and apparatus { METHOD AND APPARATUS FOR PERFORMING VIBRATION SHAKE TEST OF SATELLITES }

The present invention relates to a satellite vibration excitation test method and apparatus. More particularly, it relates to a method and apparatus for measuring changes in a plurality of sensor data of an artificial satellite while performing a vibrophotographic test of the artificial satellite.

The force/moment measuring device for performing the satellite vibration environment test measures the total force and moment acting on the satellite during the vibration test process by applying a number of force sensors to the lower part of the satellite. . Since the force and moment components acting on the satellite are very large during the vibration test process, it is necessary to measure the overall force and moment components by applying multiple force sensors. In the case of artificial satellites, it is generally performed by applying 12 force sensors or 24 force sensors in the case of large satellites with a large weight.

The existing force-moment measurement system unilaterally adds the charge signals output from various force sensors using a charge signal summation unit, and the charge signal for the total force obtained therefrom is converted into a charge signal amplifier (Charge Amplifier). ) to convert the voltage signal to measure the entire force component. Therefore, there is a problem in that it is not possible to check the size and distribution of the force component acting on each force sensor and the change according to the vibration frequency. For reference, the vibration excitation test of the satellite starts at 5 Hz and vibrates while changing the frequency up to the frequency of 100 Hz. Therefore, depending on the frequency at which the satellite shakes, the distribution of the force according to the size and position of the total force is very different.

In addition, since it is not possible to check the force information acting on each force sensor, there is a limitation in that it is difficult to check whether each force sensor is operating normally during the vibration excitation test process and whether it is used within the effective range of the force sensor. exist.

Embodiments of the present invention provide a satellite vibration excitation test method and apparatus for accurately measuring in real time the distribution of force acting on each force sensor of the satellite and the force and moment of the entire satellite.

In the satellite vibration test apparatus according to an embodiment of the present invention, a sensor data receiver for receiving a plurality of force sensor data from a satellite, a plurality of charge signal amplifiers corresponding to each of the plurality of force sensor data, and the charge signal amplifier A force moment calculation logic unit for calculating the total force and moment of the artificial satellite using the output voltage signal, a vibration control unit for controlling vibration using the force moment of the artificial satellite output from the force moment calculation logic unit, and force moment monitoring It may include a communication unit for performing network communication with the device.

In an embodiment, the sensor data receiver may receive sensor data from a plurality of force sensors of the artificial satellite at designated intervals.

In an embodiment, the force moment calculation logic unit may convert the total force and moment of the satellite into time series data according to the specified period.

In an embodiment, the charge signal amplifier may amplify a charge signal included in the plurality of force sensor data and convert it into a voltage signal.

In an embodiment, the force moment calculation logic unit may convert the voltage signal output from the charge signal amplifier into a digital signal, calculate the total force and moment of the artificial satellite, and output the voltage signal.

In an embodiment, the vibration control unit may compare a specified target value with respect to the total force and moment of the artificial satellite, and control the vibration signal applied to the artificial satellite.

In an embodiment, the communication unit may transmit a plurality of force sensor data received from the satellite and the total force and moment of the artificial satellite to the force moment monitoring device in real time.

In an embodiment, the communication unit may transmit the plurality of force sensor data and the total force and moment as time series data to the force moment monitoring device.

A satellite vibration excitation test method according to another embodiment of the present invention comprises the steps of receiving a plurality of force sensor data from a satellite, amplifying each of the charge signals of the plurality of force sensor data to generate a voltage signal, the voltage signal calculating the total force and moment of the artificial satellite by using, controlling vibration by using the calculated force moment of the artificial satellite, and externalizing a plurality of force sensor data received from the satellite and the total force and moment of the artificial satellite It may include the step of sending to a server.

In an embodiment, the receiving of the sensor data may include receiving the sensor data from a plurality of force sensors of the artificial satellite at designated intervals.

In an embodiment, calculating the total force and moment of the artificial satellite may include converting the total force and moment of the artificial satellite into time series data according to the specified period.

In an embodiment, generating the voltage signal may include amplifying a charge signal included in the plurality of force sensor data and converting the voltage signal into a voltage signal.

In one embodiment, calculating the total force and moment of the artificial satellite includes converting the voltage signal output from the charge signal amplifier into a digital signal, calculating the total force and moment of the artificial satellite, and outputting a voltage signal may include

In an embodiment, the controlling of the vibration may include comparing a specified target value with respect to the total force and moment of the artificial satellite, and controlling the vibration signal applied to the artificial satellite.

In an embodiment, the transmitting to the external server may include transmitting a plurality of force sensor data received from the satellite and the total force and moment of the satellite to an external server in real time.

In one embodiment, the transmitting to the external server may include transmitting the plurality of force sensor data and the total force and moment as time series data to the external server.

1 is a view for explaining a satellite vibration excitation test system according to an embodiment of the present invention.
2 is a hardware configuration diagram of a force moment measuring device and a force moment monitoring device according to an embodiment of the present invention.
3 is a block diagram for explaining the hardware configuration and operation of the satellite vibration excitation test apparatus according to an embodiment of the present invention.
4 is a view for explaining a force moment monitoring method according to an embodiment of the present invention.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS [0010] DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS [0010] DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS [0023] Reference is made to the accompanying drawings, which show by way of illustration specific embodiments in which the invention may be practiced. These embodiments are described in sufficient detail to enable those skilled in the art to practice the present invention. It should be understood that the various embodiments of the present invention are different but need not be mutually exclusive. For example, certain shapes, structures, and characteristics described herein may be implemented with changes from one embodiment to another without departing from the spirit and scope of the present invention. In addition, it should be understood that the location or arrangement of individual components within each embodiment may be changed without departing from the spirit and scope of the present invention. Accordingly, the following detailed description is not to be taken in a limiting sense, and the scope of the present invention should be taken as encompassing the scope of the claims and all equivalents thereto. In the drawings, like reference numerals refer to the same or similar elements throughout the various aspects.

Hereinafter, various embodiments of the present invention will be described in detail with reference to the accompanying drawings in order to enable those of ordinary skill in the art to easily practice the present invention.

1 is a view for explaining a satellite vibration excitation test system according to an embodiment of the present invention.

A test system with satellite vibration according to an embodiment may include a satellite 10 , an acceleration sensor 20 , a moment measuring device 100 with a vibration test, and a vibration control device 200 .

The acceleration sensor 20 may detect whether the satellite 10 vibrates. In an embodiment, the acceleration sensor 20 may be connected to the lower end of the satellite 10 . The acceleration sensor 20 is only one of a plurality of sensors for detecting the vibration of the artificial satellite, and the sensor data received by the test apparatus with satellite vibration according to some embodiments of the present invention is not limited to the aforementioned acceleration sensor, but various sensors Note that it can be received from

The force moment measuring apparatus 100 may receive sensor data in real time from the acceleration sensor 20 that senses the vibration of the artificial satellite 10 . The force moment measuring apparatus 100 may measure the force and moment of the entire artificial satellite by using a plurality of received sensor data. The vibration control device 200 may transmit a feedback control signal to the vibration tester 30 using the force and moment data of the entire satellite and the current acceleration sensor data received from the force moment measuring device 100 . In one embodiment, the vibration control device 200 may generate the above-described feedback control signal after performing comparison with a specified target value for the total force and moment of the artificial satellite, and the vibration tester 30 receives the feedback control signal In response, it is possible to control the vibration applied to the satellite.

In an embodiment, in the course of the satellite vibration excitation test, a plurality of force sensor data and the total force and moment data of the satellites may be stored and managed as time series data. Through this, it is possible to perform detailed analysis on the distribution of the force acting on each force sensor and the accuracy of the calculated total force and moment. In addition, according to the satellite vibration excitation test method according to some embodiments of the present invention, it is possible to minimize the delay time between the force signal measured by the sensor and the total force and moment signal of the artificial satellite for real-time feedback control during the vibration excitation test process of the satellite. have.

2 is a hardware configuration diagram of a force moment measuring device and a force moment monitoring device according to an embodiment of the present invention.

In FIG. 2 , the internal configuration of the force moment measuring device 100 and the force moment monitoring device 120 will be described in detail as an example of the satellite vibration excitation test device according to an embodiment of the present invention.

In one embodiment, the force moment measuring device 100 and the force moment monitoring device 120 are input/output interfaces 101, 121, memories 102, 122, processors 103, 123 and communication modules 104, 124. may include

The memories 102 and 122 are computer-readable recording media and may include random access memory (RAM), read only memory (ROM), and permanent mass storage devices such as disk drives. In addition, the memories 102 and 122 may temporarily or permanently store program codes and settings for controlling the force moment measuring device 100 or the force moment monitoring device 120 , a camera image, and sensor data.

The processors 103 and 123 may be configured to process instructions of a computer program by performing basic arithmetic, logic, and input/output operations. Instructions may be provided to the processor 103 , 123 by the memory 102 , 122 or the communication module 104 , 124 . For example, the processors 103 and 123 may be configured to execute received instructions according to program code stored in a recording device such as the memories 102 and 122 . In one embodiment, the processor 103 of the force moment measuring device 100 receives a plurality of force sensor data from the satellite, amplifies each of the charge signals of the plurality of force sensor data to generate a voltage signal, and the voltage signal Calculates the total force and moment of the artificial satellite by using , controls vibration using the calculated force moment of the artificial satellite, and calculates the total force and moment of the artificial satellite and a plurality of force sensor data received from the satellite as a force moment It may be transmitted to the monitoring device 120 .

The communication modules 104 and 124 may provide functions for communicating over the network 40 . In one example, a request generated by the processor 103 of the force moment measuring device 100 according to a program code stored in a recording device such as the memory 102 is a force through the network 40 under the control of the communication module 104 . It may be transmitted to the moment monitoring device (120). Conversely, a control signal, command, content, file, etc. provided under the control of the processor 123 of the force moment monitoring device 120 is transmitted through the network 40 through the communication module 104 to the force moment measuring device 100 ) can be received. For example, a control signal or command of the force moment monitoring device 120 received through the communication module 104 may be transmitted to the processor 123 or the memory 122 , and data or files may be transmitted to the force moment measuring device. 100 may be stored as a storage medium that may further include. Although the communication method is not limited, the network 40 may be a local area wireless network. For example, the network 40 may be a Bluetooth (Bluetooth), BLE (Bluetooth Low Energy), or Wifi communication network. In one embodiment, the communication module 104 of the force moment measuring device 100 may transmit a plurality of force sensor data received from the satellite and the total force and moment of the satellite to the force moment monitoring device in real time, In this case, the plurality of force sensor data and the total force and moment data of the satellite may be in the form of time series data.

In addition, the input/output interfaces 101 and 121 may receive a user input and display output data. The input/output interfaces 101 and 121 according to an exemplary embodiment may receive a numerical value for the degree of vibration from a user, and may display sensor data of the satellite as a graph and output it on a display.

Also, in other embodiments, the force moment measuring device 100 and the force moment monitoring device 120 may include more components than those of FIG. 2 . However, there is no need to clearly show most of the prior art components. For example, the force moment measuring device 100 and the force moment monitoring device 120 may include a battery and a charging device for supplying power to the internal components of the user terminal, at least some of the above-described input and output devices It may be implemented to include or further include other components such as a transceiver, a global positioning system (GPS) module, various sensors, and a database. For example, the force moment measuring apparatus 100 may store 72-channel force sensor time series data with 25 kHz sampling.

3 is a block diagram for explaining the hardware configuration and operation of the satellite vibration excitation test apparatus according to an embodiment of the present invention.

Existing satellite vibration excitation test apparatus uses charge signal summation unit for charge signals output from force sensors to create the sum of charge signals of all force sensors and passes them through a charge amplifier for general analysis. Generate a voltage signal for the total force available. In addition, in the case of the moment signal, additional hardware was required because it should be output as the sum of the force component and the information (distance) about the position of the sensor. Such a conventional satellite vibration test apparatus adds up all the charge signals output from various force sensors, and measures the total force component using the charge signal for the total force obtained therefrom. Therefore, there is a limit in that it is impossible to check the size and distribution of the force component acting on each force sensor and the change according to the vibration frequency.

On the other hand, as shown in Figure 3, the satellite vibration excitation test apparatus according to some embodiments of the present invention can solve the above limitation by having an independent signal calculating device. The satellite vibration test apparatus according to an embodiment may include a sensor data receiving unit for receiving a plurality of sensor data, a charge signal amplifier corresponding to each of the plurality of sensor data, a force moment calculation logic unit, and a vibration control unit, and in some embodiments In an example, it may further include a total force moment measurement unit, a force moment monitoring unit, and a force moment storage unit, and in another embodiment may further include a communication unit.

The sensor data receiver may receive a plurality of force sensor data 201 , 202 , 203 , and 204 . The sensor data receiver according to an embodiment may receive a plurality of force sensor data 201 , 202 , 203 , and 204 every specified period.

The charge signal amplifiers 211 , 212 , 213 , and 214 may correspond to each of the received plurality of sensor data 201 , 202 , 203 , 204 , and may correspond to each of the plurality of force sensor data 201 , 202 , 203 and 204 . The included charge signal can be amplified and changed into a voltage signal.

The force moment calculation logic unit 220 may calculate the total force and moment of the artificial satellite using the voltage signals output from the plurality of charge signal amplifiers 211 , 212 , 213 , and 214 . In an embodiment, the force moment calculation logic unit 220 may convert the voltage signal output from the charge signal amplifier into a digital signal, calculate the total force and moment of the satellite, and output an analog signal. The analog signal may be, for example, a voltage signal. Also, in an embodiment, the force moment calculation logic unit 220 may convert the total force and moment of the satellite into time series data according to a specified period. In this case, the generated time series data may be stored in the force moment storage unit 240 . The force moment calculation logic unit 220 according to an embodiment may process calculation logic using hardware such as FPGA. In this case, the time required between input and output can be reduced compared to the case of processing calculation logic using software. However, the FPGA is only an example of calculation logic hardware, and the configuration of the force moment calculation logic unit 220 according to the present embodiment is not limited thereto, and a separate dedicated chip may be designed and configured. Through this, the scalability of applying various equations to the arrangement shape of the plurality of force sensors may be improved.

For example, when the force moment calculation logic unit 220 is implemented using an FPGA, the amount of logic that can be placed in the FPGA is limited, so to improve the efficiency of the operation speed, a fixed point operation is performed. can In addition, in order to prevent overloading of calculations due to high-speed sampling of a plurality of force sensor signals, the FPGA program according to an embodiment may be written in parallel code.

The vibration control unit 260 may control the vibration signal applied to the artificial satellite after performing comparison with a specified target value for the total force and moment of the artificial satellite.

In one embodiment, the force moment monitoring unit 230 may monitor in real time a plurality of force sensor data (201, 202, 203, 204) and the total force and moment data of the artificial satellite. In another embodiment, the force moment monitoring unit 230 may be provided as separate hardware, and in this case, data transmission/reception to the force moment monitoring unit 230 may be performed through a communication unit (not shown). That is, in this embodiment, the satellite vibration excitation test apparatus and the force moment monitoring unit 230 and the force moment storage unit 240 according to some embodiments of the present invention are provided as separate hardware for stability of the satellite vibration excitation test process. can be In this case, the satellite vibration excitation test device, the force moment monitoring unit 230 and the force moment storage unit 240 may perform communication through a network. Through this, even if an error occurs in the force moment monitoring unit 230 and the force moment storage unit 240, it is possible to prevent an error from occurring in the satellite vibration test control process performed by the satellite vibration excitation test device, and through this, the satellite vibration excitation It can improve the accuracy of the test.

In addition, the total force moment measuring unit 250 may measure the total force moment of the artificial satellite using a plurality of voltage signals output from the plurality of charge signal amplifiers 211 , 212 , 213 , and 214 .

4 is a view for explaining a force moment monitoring method according to an embodiment of the present invention.

The satellite vibration excitation test apparatus according to an embodiment may further include a force moment monitoring unit of the satellite. In addition, the satellite vibration test apparatus according to another embodiment may communicate with a separate force moment monitoring apparatus through a network.

4 is a diagram illustrating an example of an interface of the device 120 for performing force moment monitoring. If the artificial intelligence force moment monitoring software is separately provided as shown, time series data for a plurality of force sensors can be monitored in real time during the satellite vibration excitation test process. For example, time series data of a plurality of force sensor data received through 72 channels may be sampled at a maximum of 25.4 kHz. In this case, the device for measuring the force moment is a device for monitoring the force moment, and converts the force and moment of a plurality of force sensor data and the satellite stagnation into time series data and transmits the data.

The device described above may be implemented as a hardware component, a software component, and/or a combination of the hardware component and the software component. For example, devices and components described in the embodiments may include, for example, a processor, a controller, an arithmetic logic unit (ALU), a digital signal processor, a microcomputer, a field programmable gate array (FPGA). , a programmable logic unit (PLU), a microprocessor, or any other device capable of executing and responding to instructions, may be implemented using one or more general purpose or special purpose computers. The processing device may execute an operating system (OS) and one or more software applications running on the operating system. The processing device may also access, store, manipulate, process, and generate data in response to execution of the software. For convenience of understanding, although one processing device is sometimes described as being used, one of ordinary skill in the art will recognize that the processing device includes a plurality of processing elements and/or a plurality of types of processing elements. It can be seen that can include For example, the processing device may include a plurality of processors or one processor and one controller. Other processing configurations are also possible, such as parallel processors.

The software may comprise a computer program, code, instructions, or a combination of one or more thereof, which configures a processing device to operate as desired or is independently or collectively processed You can command the device. The software and/or data may be any kind of machine, component, physical device, virtual equipment, computer storage medium or device, to be interpreted by or to provide instructions or data to the processing device. , or may be permanently or temporarily embody in a transmitted signal wave. The software may be distributed over networked computer systems, and stored or executed in a distributed manner. Software and data may be stored in one or more computer-readable recording media.

The method according to the embodiment may be implemented in the form of program instructions that can be executed through various computer means and recorded in a computer-readable medium. The computer-readable medium may include program instructions, data files, data structures, and the like, alone or in combination. The program instructions recorded on the medium may be specially designed and configured for the embodiment, or may be known and available to those skilled in the art of computer software. Examples of the computer-readable recording medium include magnetic media such as hard disks, floppy disks and magnetic tapes, optical media such as CD-ROMs and DVDs, and magnetic such as floppy disks. - includes magneto-optical media, and hardware devices specially configured to store and execute program instructions, such as ROM, RAM, flash memory, and the like. Examples of program instructions include not only machine language codes such as those generated by a compiler, but also high-level language codes that can be executed by a computer using an interpreter or the like. The hardware devices described above may be configured to operate as one or more software modules to perform the operations of the embodiments, and vice versa.

As described above, although the embodiments have been described with reference to the limited embodiments and drawings, various modifications and variations are possible from the above description by those skilled in the art. For example, the described techniques are performed in a different order than the described method, and/or the described components of the system, structure, apparatus, circuit, etc. are combined or combined in a different form than the described method, or other components Or substituted or substituted by equivalents may achieve an appropriate result.

Therefore, other implementations, other embodiments, and equivalents to the claims are also within the scope of the following claims.

Claims (17)

A sensor data receiving unit for receiving a plurality of force sensor data from the satellite;
a plurality of charge signal amplifiers corresponding to each of the plurality of force sensor data;
a force moment calculation logic unit for calculating the total force and moment of the satellite using the voltage signal output from the charge signal amplifier;
a vibration control unit for controlling vibration using the force moment of the artificial satellite output from the force moment calculation logic unit; and
Including; a communication unit for performing network communication with the force moment monitoring device
Test device with satellite vibration.
According to claim 1,
The sensor data receiving unit,
receiving sensor data from a plurality of force sensors of the satellite at specified intervals;
Test device with satellite vibration.
3. The method of claim 2,
The force moment calculation logic unit,
Converting the total force and moment of the satellite into time series data according to the specified period,
Test device with satellite vibration.
According to claim 1,
The charge signal amplifier,
amplifying the charge signal included in the plurality of force sensor data and changing it into a voltage signal,
Test device with satellite vibration.
According to claim 1,
The force moment calculation logic unit,
converting the voltage signal output from the charge signal amplifier into a digital signal, calculating the total force and moment of the satellite, and outputting a voltage signal,
Test device with satellite vibration.
According to claim 1,
The vibration control unit,
Comparing a specified target value with respect to the total force and moment of the satellite, and controlling the vibration signal applied to the satellite,
Test device with satellite vibration.
According to claim 1,
The communication unit,
Transmitting a plurality of force sensor data received from the satellite and the total force and moment of the satellite in real time to the force moment monitoring device,
Test device with satellite vibration.
8. The method of claim 7,
The communication unit,
Transmitting the plurality of force sensor data and the total force and moment as time series data to the force moment monitoring device,
Test device with satellite vibration.
A satellite vibration excitation test method performed in a satellite vibration excitation test apparatus, comprising:
receiving a plurality of force sensor data from the satellite;
generating a voltage signal by amplifying each of the charge signals of the plurality of force sensor data;
calculating the total force and moment of the satellite using the voltage signal;
controlling vibration using the calculated force moment of the satellite; and
Transmitting a plurality of force sensor data received from the satellite and the total force and moment of the satellite to an external server,
Test method with satellite vibration.
10. The method of claim 9,
Receiving the sensor data comprises:
receiving sensor data from a plurality of force sensors of the satellite at designated intervals;
Test method with satellite vibration.
11. The method of claim 10,
Calculating the total force and moment of the satellite comprises:
Including the step of converting the total force and moment of the satellite into time series data according to the specified period,
Test method with satellite vibration.
10. The method of claim 9,
The generating of the voltage signal comprises:
Comprising the step of amplifying the charge signal included in the plurality of force sensor data and changing it into a voltage signal,
Test method with satellite vibration.
10. The method of claim 9,
Calculating the total force and moment of the satellite comprises:
converting the voltage signal into a digital signal, calculating the total force and moment of the satellite, and outputting a voltage signal,
Test method with satellite vibration.
10. The method of claim 9,
The step of controlling the vibration,
Comprising the step of comparing a specified target value for the total force and moment of the satellite, and controlling the vibration signal applied to the satellite,
Test method with satellite vibration.
10. The method of claim 9,
The step of sending to the external server is,
Transmitting a plurality of force sensor data received from the satellite and the total force and moment of the satellite to an external server in real time
Test method with satellite vibration.
16. The method of claim 15,
The step of sending to the external server comprises:
Transmitting the plurality of force sensor data and the total force and moment as time series data to the external server,
Test method with satellite vibration.
A computer program stored in a recording medium for executing the method of claims 9 to 16 using a computer.

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