KR102041192B1 - A sharing method of satellite testing and operation system using modularization. - Google Patents

Abstract

The present invention relates to a method of joint testing and control system of the satellite body through modularization, and more specifically, to operate the satellite body from the construction stage of the satellite body test system which is provided in the test building and consists of ground support equipment for performing the satellite body test. By developing the test system using the commonized modules modularized by function in mind, the selective testing and operation of the satellite body is made possible by selectively using the commonized module having the reliability verified in the ground test of the satellite body only for the modules necessary for the satellite control system. The present invention relates to a method for joint utilization of satellite test and control systems through modularization to have consistent and high reliability.

Description

A sharing method of satellite testing and operation system using modularization.

The present invention relates to a method of joint utilization of satellite test and control system through modularization, and more specifically, by using a cavitation module that is classified and modularized by the ground support equipment for performing a functional test of the satellite body, before launching the satellite body. In addition, the present invention relates to a test system for a satellite body constructed in a test building and a method of joint utilization in a control system constructed at a ground station after the launch of the satellite body.

Industrially, the aerospace sector is not only one of the core industries of high added value and driving other industrial development, but also a highly concentrated knowledge-intensive advanced country. Although it has been developed mainly in developed countries due to the characteristics of high-risk industries, which have long and long-term investments and large investment funds, but the possibility of success is low, once the technology development and market entry are successful, the added value and technology level are higher than those of other industries. It has a powerful effect of driving national economic development and strengthening the national status, by strengthening the government, encouraging the pride of the people. Among them, the satellite fields that perform missions in space, such as space environment measurement, solar system and deep space observation, as well as various real-life areas such as broadcasting communication, earth observation, meteorological observation, ocean observation, and navigation, include security, industry, economy, and culture. Its use is expanding rapidly in various areas.

The launch of one of these satellites takes a large amount of capital and years, and due to the particularity that if a satellite fails in space, it can't be recovered and repaired to the ground. In addition to assembly, integration, and test, high safety and reliability are required just before launch of satellites, extensive tests and verifications are being performed during satellite development.

In general, the ground support equipment (EGSE) on the ground is used to verify that the satellite functions normally according to the requirements of the satellite power meter, attitude control system and telemetry command system before launching after the design and assembly of the satellite body. Satellite function tests are being carried out by using the system. If the satellite function test is conducted through the ground support equipment (EGSE) before the satellite launch, the satellite is launched into the space through the projectile. At this time, due to the characteristics of the satellite test that checks all the functions of the satellites in detail, after the same satellite is launched into space, the control system built on the ground ground station operating the corresponding function of the launched satellite is largely shared and utilized. exist.

In this regard, Korean Patent Publication No. 10-1401295 (Satellite Test Apparatus, May 23, 2014) is electrically connected between a satellite and a satellite control device that controls the satellite to perform various checks on the satellite until the satellite launches. A satellite test apparatus is disclosed, and Korean Patent Publication No. 10-0738335 (Satellite control system and method using a communication satellite, 2007.07.05.) Receives a command from a central monitoring station via a communication satellite. A satellite control system is disclosed which distinguishes a destination (satellite or control system) of the command and executes each command.

As in the above-mentioned documents, the satellite test system and control system perform similar functions in their functions, but each satellite test system and control system have different design concepts independently because they pursue different purposes. Has been developed. As the test system and the control system of the satellite body are independently developed with different design concepts, waste of duplicate development of the same function occurs, and the reliability of the control system equipment for the operation and mission of the satellite body in the process of constructing the control system. Accompanied testing results in significant losses in terms of cost and time.

Korean Registered Patent Publication No. 10-1401295 (Satellite test apparatus, 2014.05.23.) Korean Registered Patent Publication No. 10-0738335 (Satellite control system and method using communication satellite, 2007.07.05.)

The present invention has been made to solve the above problems, and is modularized by function in consideration of the operation of the satellite body from the construction stage of the satellite body test system, which is provided in the test building and composed of ground support equipment for performing the satellite body test. By developing a test system using the commonized module, by selectively using the commonized module that has been verified in the ground test of the satellite body only for the modules required by the satellite control system, it is possible to establish a consistent and unified system for testing and operating the satellite body. The present invention relates to a satellite test and control system with high reliability.

The present invention relates to a method for joint utilization of satellite test and control system through modularization, and more particularly, a test system 10 for performing a test of the satellite 1 and the operation and performance of the satellite 1. In the joint utilization method of the satellite body test and control system by modularization of the hardware and software for each function of the control system 20 to perform, the hardware and software of the ground support equipment 11 constituting the test system 10 The modularization step (S100) and the launching of the satellite body (1), which are classified based on the functions that can be utilized jointly with the control system (20) and constitute each independent cavitation module (100), are utilized in the test system (10). It characterized in that it comprises a joint utilization step (S300) for building the control system 20 by using the cavitation module 100.

In addition, the modularization step (S100) is characterized by configuring the cavitation module 100 by classifying based on the function of the software performed in the test system (10).

In addition, in another aspect of the present invention, the modularization step (S100) is characterized by constituting the cavitation module 100 by classifying based on the function of the hardware constituting the test system (10).

At this time, after the modularization step (S100), it may further include a test system building step (S200) for building the test system 10 for testing the satellite body 1 by using the cavitation module 100. .

In addition, the test system construction step (S200) is characterized in that it further comprises a reliability test step (S210) for verifying the suitability and safety between the satellite body (1) and the shared module (100).

In addition, the joint utilization step (S300) further comprises a module reconstruction step (S310) for constructing the control system 20 by selectively utilizing the commonization module 100 required in the control system 20. It is done.

The present invention according to the above-described configuration and method, from the construction phase of the satellite body test system in consideration of the joint utilization in the satellite body control system to build a test and control system of the satellite body by modularizing the hardware and software by function, the satellite body over the years High reliability and safety control system verified by recycling the highly reliable shared module verified at various test stages of the satellite system to the control system constructed at the ground station after launching the satellite body, and through this, consistent testing and operation of the satellite body There is an advantage to doing that.

1 is a flow chart in accordance with one embodiment of the present invention.
2 is a block diagram of a satellite body test system according to an embodiment of the present invention.
3 is a block diagram of a satellite control system according to an embodiment of the present invention.
4 is a block diagram illustrating a shared module classified by function of hardware according to an embodiment of the present invention.
FIG. 5 is a block diagram illustrating a shared module categorized by function of software according to an embodiment of the present invention. FIG.
6 is an exemplary view showing a module reconfiguration step according to an embodiment of the present invention.

Hereinafter, the technical spirit of the present invention will be described in more detail with reference to the accompanying drawings.

The accompanying drawings are only examples to illustrate the technical idea of the present invention in more detail, and thus the technical idea of the present invention is not limited to the forms of the accompanying drawings.

The present invention relates to a method for modular utilization of hardware and software constituting satellite test and control system by function, and more specifically, as shown in FIG. 1, to perform a test of satellite 1. In the method of joint utilization of the satellite body test and control system through the modularization of the hardware and software constituting the control system 20 that performs the operation and performance of the test system 10 and the satellite body 1, the satellite body test system (10) by using the modularization step (S100) and the cavitation module 100 to configure the ground support equipment (11) to each function by classifying each of the independent cavitation module 100, and the satellite body (1) A test system construction step (S200) for building the test system 10 for testing and verifying the suitability and safety between the satellite body (1) and the shared module (100) Module reconstruction step (S310) and the module reconstruction step (S310) to build the control system 20 by selectively utilizing the reliability test step (S210), and the commonization module 100 required in the control system 20 After the launch of the satellite body (1), including the control system building step (S320) to build the satellite control system 20 by using the reconstruction module 100 reconstructed in the, used in the test system 10 It may comprise a joint utilization step (S300) for building the control system 20 by using the cavitation module 100.

At this time, the satellite test system 10 and the control system 20 will be described in more detail below with reference to FIGS.

FIG. 2 is a block diagram illustrating a satellite body test system 10 according to an exemplary embodiment of the present invention. Referring to FIG. 2, the satellite body test system 10 may include the satellite body (before the launch of the satellite body 1). 1) It is built inside the test chamber 11 where various tests such as total assembly, alignment and structure, heat, vacuum, electromagnetic waves, etc. are performed, and are electrically connected to the satellite 1 using a cable and the satellite 1 ) And a ground support device 12 for testing various payloads mounted in the satellite 1.

In this case, the ground support device (12, EGSE) is developed for the satellite test period that occupies most of the satellite development program, is configured to perform a functional test electrically connected to the satellite body 1 and the payload, the satellite body (1) and lower ground test equipment (SCOE) for testing the payload, and higher ground equipment (OCOE, Overall Check-Out Equpment) that controls and manages them centrally and remotely. In general, the lower ground test equipment is composed of test equipment for measuring and verifying the satellite body 1, and the upper ground equipment is used by the operator of the test system 10 to control the lower ground equipment. It is configured as software on a comprehensive management server. Accordingly, the ground test equipment 12 may be composed of a plurality of shared modules 100, each of which is classified into a hardware and software constituting each functionalized, modularized, the functional configuration of the shared module 100 is described below It will be described in more detail with reference to.

The shared module 100 is configured as a separate module by classifying the hardware and software of the ground support device 12 by function, and are compatible with the satellite 1 and various payloads mounted on the satellite 1. It may be configured to be divided into, more preferably formed into one module compatible with the components of the various payload or satellites to perform the test, if the test is required to be performed simultaneously by additionally configuring the test Can be done. At this time, the shared module 100 is preferably classified in consideration of the functions that can be jointly utilized in the satellite control system 20 before the construction step (S200) of the satellite test system 10, any one of the shared module Each of the 100 may be modularized in the configuration of only one hardware or software, but a plurality of the shared modules 100 may be classified based on functions that can be jointly utilized in the test system 10 and the control system 20. It can be modularized, including the configuration of hardware or software, and it is desirable to select the configuration based on the higher reliability and efficiency according to each function. At this time, the commonization module 100 is classified by function and provided with hardware for testing the satellite 1, and software that interacts with the provided hardware is stored in a storage memory provided with each to perform a classified function. It can be configured to.

3 is a block diagram illustrating a satellite control system 20 according to an embodiment of the present invention. Referring to FIG. 3, the satellite control system 20 is configured to display the satellite body after the launch of the satellite body 1. It is built in the ground station 21 for the operation of 1) and performing a given task, and is provided outside of the ground station 21, the satellite antenna 22 for performing communication with the satellite body 1, and the ground station 21 And a plurality of signals configured to transmit and receive a signal from the satellite antenna 22 and receive and perform a take command from the satellite 1 or a payload mounted on the satellite 1. It may be configured to include a control equipment (23, Mission Control System) constituting the satellite control system 20 is connected to the client 25, the control equipment 23 is utilized in the satellite test system 10 Configured by utilizing the commonization module (100) As a result, there is an advantage of constructing a uniform system of satellite testing and operation having reliability and stability verified at the test stage of the satellite body 1.

4 is a block diagram illustrating the commonization module 100 classified based on the functions of the hardware of the ground support equipment 12 according to an embodiment of the present invention. Referring to FIG. 4, the commonization module ( 100 includes a measurement module 101, a frequency conversion module 102, a demodulation and decoding module 103, a modulation and encoding module 104, a storage module 105, a control module 106, a switching module 107, The attenuation module 108, the interface module 109, and the power module 110 may be classified.

The measurement module 101 is a module for measuring the satellite 1 or the payload of test devices such as a power meter or a spectrum analyzer, and measures various dynamic characteristics such as frequency, electromagnetic waves, heat, and vibration. Try it.

The frequency conversion module 102 is a configuration for converting the RF frequency, such as X-band / S-band / L-band to the IF frequency, converts the received RF or IF frequency to IF or RF frequency to convert the appropriate measurement value Perform a function to grant.

The demodulation and decoding module 103 is a component for processing a signal according to a pre-promised protocol for data-receiving the received satellite signal, and the modulation and encoding module 104 converts the digital signal into an analog signal to send the signal to the satellite. In order to generate a signal, the signal is processed and transmitted according to a predetermined protocol. In this case, the demodulation and decoding module 103 and the modulation and encoding module 104 may be configured as one module capable of simultaneously performing the above functions according to the protocol of the test system 10 and the control system 20. Can be.

The storage module 105 is configured to store the test data in the test step of the satellite body 1, by making the test data into a database to utilize the control system 20 after the launch of the satellite body (1) There is an advantage to have a high reliability and safety in the operation of the control system 20.

The control module 106 is a component for executing and controlling all hardware and software in the vicinity of a measuring instrument, a switch, an attenuator, a frequency converter, etc., and is organically connected to the commonization module 100 and the satellite 1 of each. And it performs a function to perform the test and control of the satellite body 1, it can be formed so that the operator can operate the control module 106.

The switching module 107 selects any one signal selected from signals input from a plurality of channels to test various channels of the satellite 1 and provides a proper path.

The attenuation module 108 may include a fixed value attenuator or a variable attenuator. The attenuation module 108 may be configured to verify the electrical and software design prior to the final assembly and test start of the satellite body 1 during the satellite test procedure. Electrical test bed (ETB) and launch environment test device (FM, which tests the launch environment such as vibration, sound, shock, etc.) by simulating the firing stage from the launch pad to the space orbit after leaving the launch pad. During the flight model, the output of the same channel may vary, or the output can vary depending on the point of the test point. At this time, the attenuation module 108 controls the attenuator and the variable attenuator to provide an appropriate value to protect the test equipment and the satellite.

The interface module 109 is configured to verify a signal coming down from the antenna of the satellite body 1, and provides an interface to a signal from the satellite body 1 to a worker to perform verification function more smoothly. do.

The power module 110 receives and distributes facility power as an input so that all components of the test equipment can operate smoothly, and uses an internal power to prevent loss of test data and damage to equipment.

As described above, the shared module 100 may be classified based on the hardware functions of the ground support equipment 12. In this case, the shared module 100 classified and sorted by function may be inserted into each rack. Produced in the form of a possible box can be inserted into the rack formed on the ground support equipment 12 and the control equipment (23).

In addition, the rack is preferably formed of a conventional 19 inches, so if the common module 100 is made of a box that can be inserted into the rack, the width, height and depth of each 48cm so that it can be inserted into the rack of 19 inches , 4.45cm and 80cm or less, and the height and depth of the box-shaped commonization module 100 can be changed according to the characteristics of the configured hardware, which is compatible with the configuration of the commonization module 100 on one side It is desirable to form the interface so that it can be connected to other components to be connected.

In addition, the switching module 106, the attenuation module 107, and the interface module 108 are essential for testing the satellite 1 and the payload in various channels with one device in the satellite test system 10. However, since the satellite control system 20 performs communication in a single channel from the satellite antenna 22 communicating with the satellite 1, a path through channel selection in the switching module 106 is required. The setting function becomes unnecessary. In addition, in the case of the attenuation module 107, during the period of the satellite test, the same channel, such as the output through the antenna cap, coupler and communication repeater of the satellite body 1, but should receive a variety of output, while in the satellite operation test Since the completed system is output through the antenna which is a normal path, there is no need to induce a proper change of output through the attenuator. In addition, in the case of the interface module 108, in the satellite test step, the interface should be prepared to receive the intermediate path data for the test directly from the satellite computer or at a data signal point in the telemetry command system. After the launch, since the control equipment 23 is operated through the operator controller of the control system 20, the interface module 108 is not necessary.

Thus, in the module reconstruction step (S310), it is preferable to selectively utilize only the necessary configuration by removing the cavitation module 100 that is not necessary on the satellite control system 20.

FIG. 5 is a block diagram illustrating the shared module 100 classified based on the functions of the software of the ground support equipment 12 according to an embodiment of the present invention. Referring to FIG. 5, the shared module 100 is shown. ) Control module 106, monitoring module 111, preprocessing module 112, storage module 105, backup module 113, logging and debugging module 114, H / L CMD module 115, H / L TLM module 116 may be configured to include. In this case, the shared module 100 may be modularized with the same equipment and configuration as the shared module 100 classified based on the functions of the hardware described above, but preferably classified into one shared module 100. By configuring hardware or software according to a function, compatibility and reliability of hardware and software in the one commonization module 100 may be improved.

The control module 106 allows the operator to control all components at a designated place through Ethernet communication without directly controlling the equipment, and to operate each equipment according to a predetermined signal and setting. To perform the function.

The monitoring module 111 also monitors the state of all the components and at the same time the monitoring of satellite telemetry (telemetry) coming down from the satellite, and in addition to the essential monitoring to perform the function of monitoring all engineering telemetry. Can be.

The preprocessing module 112 may classify the received data by each payload or deliver desired payload data to a specific client, perform functions such as format change and validation check of the received data, and fill other than essential data. By classifying and removing the value, it increases the processing speed and can be checked first before analyzing the error of the test data.

The backup module 113 transmits a semi-real time to a designated place for the dual storage and distribution of the data stored in the storage module 105. In this case, the designated place may be configured as a storage server or a clyde using a storage memory other than the storage module 105 or Ethernet communication.

The logging and debugging module 114 records all items related to equipment and data processing, and separates and records commands for an operator or a remote control.

The H / L CMD module 115 is configured to receive a command signal necessary for the control of the test equipment and to perform a command, the H / L TLM module 116 is a predetermined time information according to a predetermined table of the test equipment Perform the function of transmitting and displaying.

In this case, since the cavitation module 100 classified as the software function tracks the satellite body 1 through the satellite antenna 22 provided outside the ground station 21 and amplifies the signal, the signal is received. The tracking algorithm of the satellite antenna 22 is an essential component in the satellite control system 20, but in the satellite test system 10, the satellite 10 is fixed to the ground before launching the satellite 1. Since a signal is received using a cable, the satellite tracking module 117 may further include a tracking algorithm for tracking the satellite 1.

As described above, in the module reconstruction step (S310), when the satellite control system 20 is constructed by adding the cavitation module 100 necessary for the satellite control system 20, only necessary components may be selectively used.

6 is an exemplary view showing the module reconstruction step (S310) according to an embodiment of the present invention, referring to Figure 6, the satellite control system 20 is modularized by function in the test system 10 Of the utilization module 100 used, the configuration required in the satellite control system 20 is added, the configuration unnecessary in the satellite control system 20 is deleted, and if necessary, a new module is added to configure the satellite control. System 20 can be constructed.

In addition, the module reconstruction step (S310) is essentially utilized in the control device 23 of the control system 20 of the commonization module 100 utilized in the ground support equipment 12 of the test system 10. The control system 20 can be constructed by selecting and reconfiguring the shared module 100. At this time, by reusing the common module 100 utilized in the test system 10 to build a control device that ensures high reliability at the time of construction of the control system 20, the construction step of the control system 20 In order to further simplify the task of checking the reliability of the control device 23 there is an effect that can reduce the cost required.

In addition, in the module reconstruction step (S310), the test system 10 performs a test by directly connecting to the satellite body 1 through a cable, thereby communicating with the satellite body 1 that has entered a predetermined orbit after launch. It further includes an antenna module 118 for managing and controlling the satellite antenna 22 to perform and a satellite tracking module 117 for tracking the position of the satellite 1 in the satellite antenna 22. Can be configured. In this case, the antenna module 118 and the satellite tracking module 117 is a module classified into hardware and software, respectively, and is preferably added in consideration of the construction of the control system 20.

In the joint utilization method of the satellite body test and control system through the modularization using the commonization module 100 according to the above configuration, the modularization step (S100) is the ground support equipment 11 forming the satellite body test system (10) Are classified into respective functions and modularized into independent cavitation modules 100, and the hardware and software are modularized in consideration of the satellite test system 10 and the control system 20 to test the satellites. The system 10 and the control system 20 have a consistent and high reliability, and can prevent the redundant development of the equipment constituting each system that performs the same function, it is possible to build a more competitive control system 20 There is this.

The test system building step (S200) is a step of building the test system 10 for testing the satellite body 1 by using the modularization module (S100) and the modularization module 100 by using the common module (100). As an example, the satellite body 1 may be provided in a test cavity 11.

In addition, the test system building step (S200) may further include a reliability test step (S210) for verifying the suitability and stability between the satellite body 1 and the shared module 100. At this time, since the reliability of the shared module 100 is verified in the reliability test step (S210), it has a high reliability and stability in the construction of the control system 20, and commonized to configure the control system 20. There is an advantage that the verification of the reliability of the module 100 can be performed more quickly.

The joint utilization step (S300) is the step of building the control system 20 by using the cavitation module 100 utilized in the satellite body test system 10 after the launch of the satellite body (1), the control The module reconstruction step (S310) and the module reconstruction step (S310) reconfigured in the module reconstruction step (S310) to construct the control system 20 by selectively utilizing the commonization module 100 required in the system 20 It may include a control system building step (S320) to build the satellite control system 20 by utilizing.

Method of joint utilization of satellite test and control system through the modularization of the present invention by the above method is provided in the test building (11) is composed of ground support equipment 12 for performing the test of the satellite (1) From the construction stage of the satellite body test system 10 to be developed in the test system 10 by utilizing the shared module 100 modularized by function in consideration of the operation of the satellite body 1, the ground of the satellite body 1 By selectively using the commonization module 100 having the reliability verified in the test only for the modules required by the satellite control system 20, the test and operation of the satellite body 1 has an advantage of having consistent and high reliability.

The present invention is not limited to the above-described embodiments, and the scope of application is not limited, and various modifications can be made without departing from the gist of the present invention as claimed in the claims.

1: satellite
10: Satellite Test System
11: Test Building 12: Ground Support Equipment
20: satellite control system
21: ground station 22: satellite antenna
23: control equipment 24: client
100: shared module

Claims (6)

Satellite system testing and control system through functional modularization of hardware and software constituting a test system 10 for performing a test of the satellite body 1 and a control system 20 for performing operation and performance of the satellite body 1. In the joint use of
The modularization step of classifying the hardware and software of the ground support equipment (11) constituting the test system (10) based on the functions available in collaboration with the control system (20) as an independent cavitation module (100) ( S100); And
After the launch of the satellite body (1), the joint utilization step of building the control system (20) using the cavitation module 100 utilized in the test system (10) (S300);
Method of joint utilization of satellite test and control system through modularization comprising a.
The method of claim 1,
The modularization step (S100) is to classify based on the function of the software performed in the test system (10) to configure the cavitation module 100, characterized in that the joint utilization method of the satellite body test and control system through modularization.
The method of claim 1,
The modularization step (S100) is to classify based on the function of the hardware constituting the test system (10) based on the satellite module test and control system joint utilization method characterized in that for configuring the cavitation module (100).
According to claim 2 or 3, After the modularization step (S100),
A test system building step (S200) of constructing the test system (10) for testing the satellite body (1) using the cavitation module (100);
Method of joint utilization of satellite testing and control system through modularization further comprising a.
The method of claim 4, wherein
The test system building step (S200) further includes a satellite test and control system through modularization, characterized in that it further comprises a reliability test step (S210) for verifying the suitability and safety between the satellite body (1) and the cavitation module (100). How to share.
The method of claim 4, wherein
The joint utilization step (S300) further comprises a module reconstruction step (S310) for constructing the control system 20 by selectively utilizing the cavitation module 100 required in the control system 20. Co-utilization of satellite test and control system through modularization.

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