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Whole-spacecraft single-particle soft error time-frequency fault ground-based simulation system

A ground simulation, single particle technology, applied in the field of space satellite navigation, can solve problems such as large size, inflexible number of interfaces, and inability to complete functional indicators.

Active Publication Date: 2015-12-16
BEIJING INSTITUTE OF TECHNOLOGYGY +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The test platform built with general-purpose instruments can complete most of the functional indicators of time-frequency fault simulation, but functional indicators such as frequency drift, 1PPS phase change caused by 10.23MHz frequency anomalies, and input reference compatible with 10.23MHz are still unable to be completed. There are disadvantages such as high cost, large volume, low integration, inflexible number of interfaces, and complicated operation

Method used

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  • Whole-spacecraft single-particle soft error time-frequency fault ground-based simulation system

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Embodiment 1

[0041] Embodiment 1, as figure 1 The ground simulation system of a whole satellite single event soft error time-frequency fault is shown. The system includes a single-pole three-throw switch, a direct digital frequency synthesizer DDS, a micro control unit chip MCU, an FPGA chip, a narrow-band phase-locked crystal oscillator and a driver circuit.

[0042] One end of the single-pole three-throw switch is connected to three frequency standards, and the other end is connected to the DDS, which is used to select one of the three frequency standards as a reference clock for the DDS.

[0043] The output terminal of DDS is connected to FPGA, and the control terminal of DDS is connected to MCU through SPI bus.

[0044]The MCU receives the preset output frequency and preset output phase of the external input through the RS232 bus, connects the control terminal of the DDS through the SPI bus, and connects it to the FPGA through the MCU interface; the MCU inputs the frequency to the DDS...

Embodiment 2

[0055] Embodiment 2, in the present embodiment, two external frequency standards are respectively 10MHz and 10.23MHz, and the first counter is a modulo 10 counter, and the second counter is a modulo 10230000 counter, and the concrete working process of this system is as follows:

[0056] The core component of the frequency standard part is a 10MHz rubidium atomic clock. This rubidium atomic clock is used as the input of DDS, which can provide ultra-high long-term stability and low phase noise.

[0057] At the input ends of the two external frequency standards, there are couplers to send the signal to the detection circuit. When the detection voltage is greater than the set threshold, the system determines that the external frequency standard is online. The user can choose any one between the internal atomic clock and the external online frequency standard according to the needs, and send the selected signal to the DDS as a reference clock through the single-pole three-throw sw...

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Abstract

The invention discloses a whole-spacecraft single-particle soft error time-frequency fault ground-based simulation system. The system adopts a DDS (Direct Digital Synthesizer) to connect with an external frequency marker; the DDS is controlled by an MCU (Micro-programmed Control Unit), and the output of the DDS is connected to an FPGA (Field Programmable Gate Array). An output signal of the DDS after subjected to frequency multiplication by a PLL (Phase Locked Loop) serves as a work clock signal of the FPGA; besides outputting, the output end of a first counter also drives a second counter; the output end of the second counter is connected with an input end of a pulse width counter; a reference 1pps counter outputs a 1pps counting signal; the output end of the pulse width counter outputs while the reset end of the pulse width counter is connected with the work clock signal of the FPGA; an output end of an adding and subtracting period control counter is connected with the period control end of the first counter; the MCU inputs an adding and subtracting period control drive signal, a 1pps whole phase signal and a reset request signal to the FPGA through an MCU interface; and the adding and subtracting period control drive signal, the 1pps whole phase signal and the reset request signal are respectively used for period control and restoration of the adding and subtracting period control counter, the first counter and the second counter. The whole-spacecraft single-particle soft error time-frequency fault ground-based simulation system can finish high-precision and comprehensive simulation of a single event upset effect time-frequency fault.

Description

technical field [0001] The invention belongs to the technical field of space satellite navigation, and in particular relates to a whole-satellite single particle soft error time-frequency fault ground simulation system. Background technique [0002] For the first time, China's new generation of Beidou-2 satellites have added space communication functions such as satellite links and inter-satellite links. The complex electronic environment in space may lead to unpredictable communication failures at the single-event level. In order to prevent the normal operation of each single machine in the entire star from being unable to correct errors when a fault occurs, it is necessary to design a single-event soft error system-level multi-level fault injection method to simulate the fault to test the performance of each single machine in the entire star. Among them, time-frequency equipment fault simulation is an important part. [0003] Time-frequency fault simulation equipment usua...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): H03L7/08H03L7/18G06F17/50
Inventor 宋媛媛毕少筠张培瑶
Owner BEIJING INSTITUTE OF TECHNOLOGYGY
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