Spacecraft GNSS simulation system and simulation test method based on cloud architecture

Abstract

The invention discloses a spacecraft GNSS simulation system based on a cloud architecture and a simulation test method. Comprising a multichannel spacecraft GNSS simulation source host which generates navigation satellite simulation signals and navigation simulation data; a main switch and a plurality of satellite test subsystems, wherein the main switch and the switches in the satellite test subsystems form a bidirectional communication network; a plurality of satellite test subsystems, wherein the satellite test subsystems determine a navigation satellite simulation signal receiving mode based on the working mode of the spacecraft GNSS simulation system; the power of the received navigation satellite analog signal is adjusted through an attenuator to obtain an input signal of the tested satellite navigation terminal, and the tested satellite generates related telemetering data based on the input signal of the tested satellite navigation terminal; and the switch sends the telemetry data and the navigation simulation data to the test master control processing equipment in the satellite test subsystem for closed-loop comparison and interpretation. According to the invention, the independent or joint analog signal function of the multi-user channel is realized.

Description

Technical Field

[0001] The present application relates to the field of spacecraft system-level technology, and specifically to a spacecraft GNSS simulation system and simulation test method based on cloud architecture. Background Art

[0002] As the demand for space missions increases, the number of satellites waiting to be launched and tested in parallel is increasing rapidly. Various types of navigation terminals are widely used on spacecraft, but the existing GNSS signal simulation system cannot meet the needs of multi-user spacecraft parallel testing. Disadvantages: (1) In the traditional spacecraft integrated testing phase, each spacecraft needs to be equipped with a single-channel or dual-channel GNSS signal simulation source. Multiple spacecraft tests cannot share a simulation system, which is costly.

[0003] (2) The configuration of the GNSS signal simulation source is fixed. If the GNSS signal simulation source is used in a coordinated manner among different models, it is necessary to consider whether the hardware and software configuration of the device meets the requirements of the current model, and the versatility is poor.

[0004] (3) When large-scale spacecraft tests are transferred or when ground equipment is used in a coordinated manner, equipment losses caused by transportation must also be considered. Summary of the invention

[0005] In view of this, the present application provides a spacecraft GNSS simulation system and simulation test method based on cloud architecture, which can solve the technical problems of being unable to realize parallel testing of different spacecraft users based on one simulation source, being unable to realize user access at any time, being unable to simulate at any time, and the non-universality of navigation frequency signals required for multi-spacecraft testing.

[0006] In order to solve the above technical problems, this application is implemented as follows.

[0007] A spacecraft GNSS simulation system based on cloud architecture, comprising: The multi-channel spacecraft GNSS simulation source host generates navigation satellite simulation signals after obtaining simulation scenario configuration parameters from the satellite test subsystem's measurement, control and communication ground test equipment based on the main switch; it is also used to generate navigation simulation data and send it to the main switch; A main switch and multiple satellite test subsystems, the main switch and switches in each satellite test subsystem form a two-way communication network; Multiple satellite test subsystems. After the satellite test subsystem is connected to a user, it determines the navigation satellite simulation signal receiving method based on the working mode of the spacecraft GNSS simulation system, and the user is the satellite under test; the received navigation satellite simulation signal is adjusted in power by an attenuator to obtain the input signal of the navigation terminal of the satellite under test; the satellite under test generates telemetry data based on the input signal of the navigation terminal of the satellite under test and the remote control instructions of the measurement and control communication ground test equipment corresponding to the satellite under test, and sends the telemetry data to the switch through the measurement and control communication ground test equipment; the switch sends the telemetry data and the navigation simulation data sent by the main switch to the test master control processing equipment in the satellite test subsystem for closed-loop comparison and interpretation; the working modes include multi-spacecraft local testing and multi-spacecraft cross-domain testing.

[0008] Preferably, when the working mode is multi-spacecraft local testing: the main switch is directly communicated with each switch; the multi-channel spacecraft GNSS simulation source host generates multiple navigation satellite simulation signals, and each navigation satellite simulation signal is directly connected to the corresponding satellite test subsystem by a radio frequency cable.

[0009] Preferably, when the working mode is multi-spacecraft cross-domain testing: A pair of optical fiber transceivers including a first optical fiber transceiver and a second optical fiber transceiver are configured between the main switch and the switches of each satellite test subsystem. The main switch and the first optical fiber transceiver communicate bidirectionally, the second optical fiber transceiver and the switch communicate bidirectionally, and the first optical fiber transceiver and the second optical fiber transceiver communicate bidirectionally via a cross-domain network optical fiber link; the cross-domain network optical fiber link is configured for the satellite test subsystem corresponding to the switch; The spacecraft GNSS simulation system includes an optical transmitter subsystem, which includes a power supply and multiple optical transmitters, each of which corresponds to a satellite test subsystem; the optical transmitter performs electrical-to-optical conversion and data signal processing on the navigation satellite simulation signal it receives, and sends the generated optical signal to the optical receiver in the satellite test subsystem via the cross-domain network optical fiber link of the satellite test subsystem corresponding to the optical transmitter, and the optical receiver generates a radio frequency signal sent to the attenuator through photoelectric conversion and data signal processing.

[0010] Preferably, the spacecraft GNSS simulation system adopts a cloud architecture; the integrated management software deployed in the satellite subsystem under test serves as a cloud client; the GNSS simulation source host serves as a cloud server, supporting multiple cloud clients to simultaneously access and share the software and hardware resources of the spacecraft GNSS simulation system.

[0011] Preferably, the attenuation formula of the attenuator is:

[0012] in, The power attenuation value set for the attenuator, in dB; The maximum power of the spacecraft GNSS simulation system signal, in dBm; is the attenuation value of the program-controlled attenuator of the spacecraft GNSS simulation system, in dB; is the attenuation value of the digital attenuator of the spacecraft GNSS simulation system, in dB; is the total loss value of the RF cable, in dB; The total attenuation of radio frequency optical fiber forwarding, in dB; It is the nominal value of the navigation signal power received by the measured satellite, in dBm.

[0013] A cloud-based spacecraft GNSS simulation test method, based on the cloud-based spacecraft GNSS simulation system as described above, comprises: Step S21: determining the reconstruction parameters corresponding to each user according to the test requirements of the user, wherein the user is the satellite under test; Step S22: When the working mode is multi-spacecraft local test, the measurement and control communication ground test equipment sends the reconstruction parameters to the multi-channel spacecraft GNSS simulation source host through the main switch, the multi-channel spacecraft GNSS simulation source host generates a navigation satellite simulation signal based on the reconstruction parameters, transmits the navigation satellite simulation signal to the attenuator in the corresponding satellite test subsystem, and the multi-channel spacecraft GNSS simulation source host sends the real-time generated navigation simulation data to the remote control computer client software; Step S23: after the satellite under test is powered on, telemetry data is generated based on the remote control command of the measurement and control communication ground test equipment corresponding to the satellite under test; Step S24: Determine subsequent telemetry parameters based on the telemetry data, frame and modulate the subsequent telemetry parameters in a specified format, and transmit them to the measurement, control and communication ground test equipment; process the telemetry data, and visualize and display the processed telemetry data.

[0014] This application can effectively integrate scattered, remote, and cross-domain simulation resources to build a cross-domain collaborative spacecraft GNSS simulation system, forming simulation verification capabilities such as remote system joint debugging, remote signal observation, signal simulation, and fault reproduction. The spacecraft GNSS simulation system has large data transmission volume, long distance, and high real-time and reliability requirements. It has the advantages of long transmission distance, strong anti-interference ability, low line attenuation, and high reliability, and can meet the requirements of cross-domain and collaborative testing for data transmission.

[0015] This application adopts distributed reconfigurable navigation simulation technology to realize test resource sharing and reuse, online reconstruction of signal frequencies and test scenarios, and support for random access of multiple spacecraft. One test device is equivalent to the function of multiple test devices being used independently, thereby meeting the testing requirements of navigation subsystems on different spacecraft, reducing the total number of test equipment configurations, and realizing test equipment reconstruction and sharing to meet the parallel testing requirements of multiple spacecraft.

[0016] Beneficial effects: (1) This application supports multi-user random access, sharing of idle user resources of equipment, supports multi-user signal output, and realizes independent or joint analog signal functions of multi-user channels; (2) This application is based on the RF signal optical fiber forwarding system, which remotely transmits the simulated navigation signals of multiple users to different test areas at the same time, realizes the cross-regional support of the GNSS simulation source equipment RF signal level for multiple spacecraft to conduct remote tests in parallel, share GNSS simulation system signal test resources, and reduce equipment transportation losses; (3) This application is based on the fiber optic network communication mechanism, supports multi-user cross-regional and remote access to the GNSS simulation system, supports multiple remote control commands from different LAN users to be transmitted to the simulation system in real time, and reports the simulation system parameters to the remote computer for monitoring, thus realizing independent remote control of each user channel of the GNSS simulation source, as well as real-time comparison, interpretation and monitoring of the simulation data of each user's GNSS simulation source and the telemetry parameters of the spacecraft under test.

[0017] (4) This application changes the traditional test mode in which one user needs to configure a GNSS signal simulation source nearby to a test mode in which multiple users configure one simulation source, thereby improving the utilization rate of equipment hardware resources, reducing the number of equipment configurations, and reducing research and development costs. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 Schematic diagram of the structure of the spacecraft GNSS simulation system based on cloud architecture provided for this application; Figure 2 A schematic diagram of a local test of a spacecraft GNSS simulation system based on a cloud architecture for this application; Figure 3 This is a schematic diagram of cross-domain remote testing of a spacecraft GNSS simulation system based on a cloud architecture in this application. DETAILED DESCRIPTION

[0019] The present application is described in detail below in conjunction with the accompanying drawings and embodiments.

[0020] like Figure 1 As shown, the present application proposes a spacecraft GNSS simulation system based on cloud architecture, including: The multi-channel spacecraft GNSS simulation source host generates navigation satellite simulation signals after obtaining simulation scenario configuration parameters from the satellite test subsystem's measurement, control and communication ground test equipment based on the main switch; it is also used to generate navigation simulation data and send it to the main switch; A main switch and multiple satellite test subsystems, the main switch and switches in each satellite test subsystem form a two-way communication network; Multiple satellite test subsystems. After the satellite test subsystem is connected to a user, it determines the navigation satellite simulation signal receiving method based on the working mode of the spacecraft GNSS simulation system, and the user is the satellite under test; the received navigation satellite simulation signal is adjusted in power by an attenuator to obtain the input signal of the navigation terminal of the satellite under test; the satellite under test generates telemetry data based on the input signal of the navigation terminal of the satellite under test and the remote control instructions of the measurement and control communication ground test equipment corresponding to the satellite under test, and sends the telemetry data to the switch through the measurement and control communication ground test equipment; the switch sends the telemetry data and the navigation simulation data sent by the main switch to the test master control processing equipment in the satellite test subsystem for closed-loop comparison and interpretation; the working modes include multi-spacecraft local testing and multi-spacecraft cross-domain testing.

[0021] In the present invention, a multi-channel spacecraft GNSS simulation source host obtains simulation scenario configuration parameters based on the measurement and control communication ground test equipment in each satellite test subsystem, and generates a respective navigation satellite simulation signal for each satellite test subsystem.

[0022] When the working mode is multi-spacecraft local testing: the main switch is directly connected to each switch in communication; the multi-channel spacecraft GNSS simulation source host generates multiple navigation satellite simulation signals, and each navigation satellite simulation signal is directly connected to the corresponding satellite test subsystem by a RF cable.

[0023] When the working mode is multi-spacecraft cross-domain testing: A pair of optical fiber transceivers including a first optical fiber transceiver and a second optical fiber transceiver are configured between the main switch and the switches of each satellite test subsystem. The main switch and the first optical fiber transceiver communicate bidirectionally, the second optical fiber transceiver and the switch communicate bidirectionally, and the first optical fiber transceiver and the second optical fiber transceiver communicate bidirectionally via a cross-domain network optical fiber link; the cross-domain network optical fiber link is configured for the satellite test subsystem corresponding to the switch; The spacecraft GNSS simulation system includes an optical transmitter subsystem, which includes a power supply and multiple optical transmitters, each of which corresponds to a satellite test subsystem; the optical transmitter performs electrical-to-optical conversion and data signal processing on the navigation satellite simulation signal it receives, and sends the generated optical signal to the optical receiver in the satellite test subsystem via the cross-domain network optical fiber link of the satellite test subsystem corresponding to the optical transmitter, and the optical receiver generates a radio frequency signal sent to the attenuator through photoelectric conversion and data signal processing.

[0024] The spacecraft GNSS simulation system adopts a cloud architecture; the integrated management software deployed in the satellite subsystem under test serves as a cloud client; the GNSS simulation source host serves as a cloud server, supporting multiple cloud clients to simultaneously access and share the software and hardware resources of the spacecraft GNSS simulation system.

[0025] The spacecraft GNSS simulation system also includes multiple general simulation units with a unified interface. The spacecraft GNSS simulation system can be reconstructed by reconfiguring the user channel parameters corresponding to the spacecraft GNSS simulation system according to the test requirements of the satellite under test.

[0026] The spacecraft GNSS simulation system is equipped with multiple network cards. The software and hardware user channel resources can be used independently or jointly, supporting users in multiple network segments to use idle user resources through IP random access control.

[0027] In this application, the integrated management software is deployed on the satellite subsystem under test, that is, it can be on the local computer of the GNSS simulation system or the remote computer of the satellite subsystem under test. The integrated management software has the functions of operating and controlling the user channel resources of the GNSS simulation system used by the satellite subsystem under test, managing test items and processes, processing and evaluating test data, and outputting and storing test results, and supports multi-user access at any time. The multi-channel spacecraft GNSS simulation source host provides navigation satellite simulation signals for multiple users. According to actual simulation requirements, the signal generation module supports the generation of navigation signals of multi-user BDS: B1I, B2b, B3I, GPS: L1C / A, L2C and other frequency points, and supports reconstruction and generation of other frequency points. The switch supports multi-network user access, and users can support independent configuration (supporting different time, different location, and asynchronous start). The multi-channel spacecraft GNSS simulation source supports multiple users to independently use the corresponding user channel resources, supports different users to simulate at any time, and supports user trajectory access at any time.

[0028] The first optical fiber transceiver and the second optical fiber transceiver perform photoelectric signal conversion, and are suitable for network environments where optical fiber is needed to extend the transmission distance because Ethernet cables cannot cover the network.

[0029] The optical transmitter and its corresponding optical receiver not only perform photoelectric signal conversion, but also need to process data signals to achieve cross-domain synchronous transmission of original signals in different places, ensure the real-time and integrity of signal transmission, and realize signal mirror transmission in the simulation source simulation process. The optical transmitter performs electrical / optical conversion on the signal, converts the electrical signal into an optical signal and couples it into the optical fiber. The optical receiver converts the weak optical signal with attenuated amplitude and distorted waveform after optical fiber transmission into an electrical signal, and amplifies, shapes, and regenerates the signal to generate the same electrical signal as the sending end.

[0030] The measurement, control and communication ground test equipment is an indispensable and important part of the spacecraft system-level integrated test. On the one hand, it completes the function and performance inspection of the spacecraft system-level measurement, control and communication subsystems and cooperates to realize the automatic test and interpretation of the spacecraft. On the other hand, it establishes a unified uplink and downlink data communication channel for the spacecraft system-level integrated test, mainly including the uplink remote control channel and the downlink telemetry channel.

[0031] The attenuator is mainly used to complete the power adjustment of the navigation simulation signal directly output by the GNSS simulation system or output through the optical terminal to meet the input signal power range requirements of the satellite under test.

[0032] The switch is used to build the internal network of the satellite measurement, control and communication ground test equipment under test. It not only connects all the measurement, control and communication ground test equipment with network interfaces to manage ground equipment, but is also used for network communication with the spacecraft GNSS simulation system.

[0033] As a user of the spacecraft GNSS simulation system, the satellite under test receives navigation simulation signals, completes positioning and outputs telemetry data under the control of remote control commands sent by the measurement, control and communication ground test equipment, and transmits it to the measurement, control and communication ground test equipment in real time through the downlink telemetry channel.

[0034] Furthermore, the attenuation formula of the attenuator is:

[0035] in, The power attenuation value set for the attenuator, in dB; The maximum power of the spacecraft GNSS simulation system signal, in dBm; is the attenuation value of the program-controlled attenuator of the spacecraft GNSS simulation system, in dB; is the attenuation value of the digital attenuator of the spacecraft GNSS simulation system, in dB; is the total loss value of the RF cable, in dB; The total attenuation of radio frequency optical fiber forwarding, in dB; It is the nominal value of the navigation signal power received by the measured satellite, in dBm.

[0036] like Figure 2-Figure 3 As shown, the present application provides a spacecraft GNSS simulation test method based on a cloud architecture, based on the spacecraft GNSS simulation system based on the cloud architecture as described above, the method comprises: Step S21: determining the reconstruction parameters corresponding to each user according to the test requirements of the user, wherein the user is the satellite under test; Step S22: When the working mode is multi-spacecraft local test, the measurement and control communication ground test equipment sends the reconstruction parameters to the multi-channel spacecraft GNSS simulation source host through the main switch, the multi-channel spacecraft GNSS simulation source host generates a navigation satellite simulation signal based on the reconstruction parameters, transmits the navigation satellite simulation signal to the attenuator in the corresponding satellite test subsystem, and the multi-channel spacecraft GNSS simulation source host sends the real-time generated navigation simulation data to the remote control computer client software; When the working mode is multi-spacecraft cross-domain testing, the measurement and control communication ground test equipment sends the reconstruction parameters to the multi-channel spacecraft GNSS simulation source host through a pair of optical fiber transceivers configured between the main switch and the switch corresponding to the measurement and control communication ground test equipment. The multi-channel spacecraft GNSS simulation source host generates a navigation satellite simulation signal based on the reconstruction parameters. The navigation satellite simulation signal is optically converted through the optical transmitter corresponding to the navigation satellite simulation signal and the generated optical signal is coupled into the optical fiber. The optical signal is transmitted to the optical receiver in the satellite test subsystem corresponding to the navigation satellite simulation signal through the cross-domain radio frequency optical fiber link for electrical conversion. The generated electrical signal is input into the attenuator in the satellite test subsystem. The multi-channel spacecraft GNSS simulation source host sends the real-time navigation simulation data to the remote control computer client software. In the present application, the optical receiver converts the weak optical signal with attenuated amplitude and distorted waveform after optical fiber transmission into an electrical signal, and amplifies, shapes and regenerates the electrical signal, using an automatic gain control circuit to ensure stable output of the navigation satellite analog signal.

[0037] Step S23: after the satellite under test is powered on, telemetry data is generated based on the remote control command of the measurement and control communication ground test equipment corresponding to the satellite under test; Step S24: Determine subsequent telemetry parameters based on the telemetry data, frame and modulate the subsequent telemetry parameters in a specified format, and transmit them to the measurement, control and communication ground test equipment; process the telemetry data, and visualize and display the processed telemetry data.

[0038] In this application, the processing of the telemetry data includes: filtering, signal power adjustment, down-conversion, baseband processing, and demodulation of the acquired telemetry data signal to obtain telemetry data, and forwarding the telemetry data to the test master control processing device corresponding to the satellite test subsystem through a switch. After the test master control processing device extracts the effective data, it sends it to the visualization software of each ground test subsystem through multicast. The navigation terminal on the satellite under test performs closed-loop test interpretation, and the ground test equipment of measurement and control communication receives the telemetry parameters corresponding to the navigation terminal and the simulation data sent by the multi-channel spacecraft GNSS simulation source host, compares the two in real time, and sends the results to the test master control processing device.

[0039] The above specific embodiments only describe the design principles of this application. The shapes and names of the components in the description may be different and are not limited. Therefore, technicians in the field of this application can modify or replace the technical solutions recorded in the above embodiments; and these modifications and replacements do not deviate from the creative purpose and technical solutions of this application and should all fall within the scope of protection of this application.

Claims

1. A spacecraft GNSS simulation system based on cloud architecture, characterized in that: include: The multi-channel spacecraft GNSS simulation source host generates navigation satellite simulation signals after obtaining simulation scenario configuration parameters from the satellite test subsystem's measurement, control and communication ground test equipment based on the main switch; it is also used to generate navigation simulation data and send it to the main switch; A main switch and multiple satellite test subsystems, the main switch and switches in each satellite test subsystem form a two-way communication network; Multiple satellite test subsystems. After the satellite test subsystem is connected to a user, it determines the navigation satellite simulation signal receiving method based on the working mode of the spacecraft GNSS simulation system, and the user is the satellite under test; the received navigation satellite simulation signal is adjusted in power by an attenuator to obtain the input signal of the navigation terminal of the satellite under test; the satellite under test generates telemetry data based on the input signal of the navigation terminal of the satellite under test and the remote control instructions of the measurement and control communication ground test equipment corresponding to the satellite under test, and sends the telemetry data to the switch through the measurement and control communication ground test equipment; the switch sends the telemetry data and the navigation simulation data sent by the main switch to the test master control processing equipment in the satellite test subsystem for closed-loop comparison and interpretation; the working modes include multi-spacecraft local testing and multi-spacecraft cross-domain testing.

2. The system according to claim 1, characterized in that When the working mode is multi-spacecraft local testing: the main switch is directly connected to each switch in communication; the multi-channel spacecraft GNSS simulation source host generates multiple navigation satellite simulation signals, and each navigation satellite simulation signal is directly connected to the corresponding satellite test subsystem by a RF cable.

3. The system according to claim 1, characterized in that When the working mode is multi-spacecraft cross-domain testing: A pair of optical fiber transceivers including a first optical fiber transceiver and a second optical fiber transceiver are configured between the main switch and the switches of each satellite test subsystem. The main switch and the first optical fiber transceiver communicate bidirectionally, the second optical fiber transceiver and the switch communicate bidirectionally, and the first optical fiber transceiver and the second optical fiber transceiver communicate bidirectionally via a cross-domain network optical fiber link; the cross-domain network optical fiber link is configured for the satellite test subsystem corresponding to the switch; The spacecraft GNSS simulation system includes an optical transmitter subsystem, which includes a power supply and multiple optical transmitters, each of which corresponds to a satellite test subsystem; the optical transmitter performs electrical-to-optical conversion and data signal processing on the navigation satellite simulation signal it receives, and sends the generated optical signal to the optical receiver in the satellite test subsystem via the cross-domain network optical fiber link of the satellite test subsystem corresponding to the optical transmitter, and the optical receiver generates a radio frequency signal sent to the attenuator through photoelectric conversion and data signal processing.

4. The system according to claim 1, characterized in that The spacecraft GNSS simulation system adopts a cloud architecture; the integrated management software deployed in the satellite subsystem under test serves as a cloud client; the GNSS simulation source host serves as a cloud server, supporting multiple cloud clients to simultaneously access and share the software and hardware resources of the spacecraft GNSS simulation system.

5. The system according to any one of claims 1 to 4, characterized in that: The attenuation formula of the attenuator is: in, The power attenuation value set for the attenuator, in dB; The maximum power of the spacecraft GNSS simulation system signal, in dBm; is the attenuation value of the program-controlled attenuator of the spacecraft GNSS simulation system, in dB; is the attenuation value of the digital attenuator of the spacecraft GNSS simulation system, in dB; is the total loss value of the RF cable, in dB; The total attenuation of radio frequency optical fiber forwarding, in dB; It is the nominal value of the navigation signal power received by the measured satellite, in dBm.

6. A cloud-based spacecraft GNSS simulation test method, based on the cloud-based spacecraft GNSS simulation system according to any one of claims 1 to 5, characterized in that: The method comprises: Step S21: determining the reconstruction parameters corresponding to each user according to the test requirements of the user, wherein the user is the satellite under test; Step S22: When the working mode is multi-spacecraft local test, the measurement and control communication ground test equipment sends the reconstruction parameters to the multi-channel spacecraft GNSS simulation source host through the main switch, the multi-channel spacecraft GNSS simulation source host generates a navigation satellite simulation signal based on the reconstruction parameters, transmits the navigation satellite simulation signal to the attenuator in the corresponding satellite test subsystem, and the multi-channel spacecraft GNSS simulation source host sends the real-time generated navigation simulation data to the remote control computer client software; Step S23: after the satellite under test is powered on, telemetry data is generated based on the remote control command of the measurement and control communication ground test equipment corresponding to the satellite under test; Step S24: Determine subsequent telemetry parameters based on the telemetry data, frame and modulate the subsequent telemetry parameters in a specified format, and transmit them to the measurement, control and communication ground test equipment; process the telemetry data, and visualize and display the processed telemetry data.

7. A computer-readable storage medium, characterized in that: The storage medium stores a plurality of instructions; the plurality of instructions are used for the processor to load and execute the method as claimed in claim 6.

8. An electronic device, characterized in that: The electronic device comprises: A processor, which is used to execute multiple instructions; A memory for storing a plurality of instructions; Wherein, the multiple instructions are used to be stored by the memory, and loaded and executed by the processor as described in claim 6.

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