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A relative delay control method between high-precision satellite navigation signals

A satellite navigation signal and relative time delay technology, applied in the field of satellite navigation signal generation, can solve problems such as not meeting the synchronization requirements, and achieve the effect of improving positioning accuracy and convergence time

Active Publication Date: 2021-03-26
XIAN INSTITUE OF SPACE RADIO TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] At present, the general method is to use a third-party start signal, but there is a metastable problem in this way, and the relative delay can only be controlled within one clock cycle at most, which does not meet the synchronization requirements

Method used

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  • A relative delay control method between high-precision satellite navigation signals
  • A relative delay control method between high-precision satellite navigation signals
  • A relative delay control method between high-precision satellite navigation signals

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Experimental program
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Embodiment

[0080] The invention provides a method for controlling relative time delay between satellite navigation signals, comprising the following steps:

[0081] Let the two signal generation clock frequency be 122.76MHz (period is about T 1 =8.146ns) and 163.68MHz (the period is about T 2 =6.109ns), then its greatest common divisor frequency is 40.92MHz, then T y = M·T 1 = N·T 2 = 3·T 1 = 4·T 2 = 24.44ns.

[0082] calculate

[0083] [x(1), ind(1)]=min{abs[1T 1 -[0 1 2 … N]·T 2 ]}

[0084] [x(2), ind(2)]=min{abs[2T 1 -[0 1 2 … N]·T 2 ]}

[0085] ...

[0086] [x(M-1), ind(M-1)]=min{abs[(M-1)T 1 -[0 1 2 … N]·T 2 ]}

[0087] There are tables:

[0088]

[0089] The minimum absolute value of the first line is 2.037, and the minimum absolute value of the second line is -2.035, so the adjusted threshold of this step is 2.035 / 2=1.017ns, that is, the maximum precision is 1.017ns.

[0090] Generate two pseudo-random codes at these two clock frequencies, and use a third-part...

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Abstract

The invention relates to a high-precision satellite navigation signal relative time delay control method. The method comprises the following steps: determining an initial adjustment threshold value according to clock frequencies generated by two paths of satellite navigation signals; generating two paths of pseudo-random codes under the two clock frequencies; adjusting a starting signal to carry out delay control on the generated pseudo-random codes according to the pseudo-random code delay inequality measurement result; according to the code delay inequality measurement result obtained afteradjustment, calculating filter impulse response parameters and impulse response parameters required by delay fine adjustment; carrying out convolution on the filter impulse response parameters and thefirst path of satellite navigation signal, and carrying out convolution on the impulse response parameters required by delay fine adjustment and the second path of satellite navigation signal; and carrying out digital-to-analog conversion on the two paths of satellite navigation signals to obtain a satellite navigation signal for delay fine adjustment.

Description

technical field [0001] The invention relates to satellite navigation signal generation technology, in particular to a relative time delay synchronization control method between high-precision satellite navigation signals. Background technique [0002] The navigation signal is composed of multiple frequency points, and the baseband signal elements of different frequency points have different requirements that the signals must be generated in different clock domains, resulting in delay differences in signals in different clock domains. How to reduce the delay difference through relative delay control is a problem that must be solved in signal generation. [0003] At present, the general method is to use a third-party start signal, but there is a metastable problem in this way, and the relative delay can only be controlled within one clock cycle at most, which does not meet the synchronization requirement. Contents of the invention [0004] The technical problem to be solved...

Claims

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Application Information

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IPC IPC(8): G01S19/01H03H17/06
Inventor 王瑛刘文山马文龙王磊李毅松蒙艳松
Owner XIAN INSTITUE OF SPACE RADIO TECH
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