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Platform for simulating link satellite photo-communication terminal-to-terminal relative sighting angle movement

A satellite optical communication and analog link technology, which is applied to the platform field of the relative aiming angle movement between satellite optical communication terminals of the analog link, and can solve the problems of inability to simulate and detect the dynamic tracking performance of the satellite link.

Active Publication Date: 2013-06-19
HARBIN INST OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] In order to solve the problem that the existing platform for simulating the relative angular movement between satellites cannot simulate and detect the whole process of the dynamic tracking performance of the satellite link, the present invention provides a platform for simulating the relative aiming angle movement between the satellite optical communication terminals of the link

Method used

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  • Platform for simulating link satellite photo-communication terminal-to-terminal relative sighting angle movement
  • Platform for simulating link satellite photo-communication terminal-to-terminal relative sighting angle movement

Examples

Experimental program
Comparison scheme
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specific Embodiment approach 1

[0008] Specific implementation mode one: according to the instructions attached figure 1 Describe this embodiment in detail, a kind of platform described in this embodiment simulates the relative aiming angle movement between link satellite optical communication terminals, it is composed of host computer 1, guide rail controller 2, turntable controller 3, one-dimensional guide rail 4 and The two-axis turntable 5 is composed of a pitch axis and an azimuth axis, the motion range of the pitch axis is at least -60°~+60°, and the motion range of the azimuth axis is at least -180°~+ 180°, a signal output end of the host computer 1 is connected to the signal input end of the guide rail controller 2, and the signal output end of the guide rail controller 2 is connected to the mover movement control signal input end of the one-dimensional guide rail 4 on the guide rail , another signal output end of host computer 1 is connected with the signal input end of turntable controller 3, and t...

specific Embodiment approach 2

[0011] Specific implementation mode two: according to the instructions attached figure 2 Describe this embodiment in detail. The difference between this embodiment and Embodiment 1 is that the two-axis turntable 5 includes a turntable pitch axis 5-1, a moving frame 5-3, a pitch frame 5-4, a base 5-5 and a turntable. The azimuth axis, the turntable azimuth axis includes the turntable azimuth shaft sleeve 5-2 and the azimuth axis R, the optical communication terminal 7 under test includes the signal receiving terminal 7-1, the terminal pitch axis 7-2 and the terminal azimuth axis, the terminal azimuth The shaft includes a terminal azimuth shaft sleeve 7-3, the pitch axis 5-1 of the turntable is located on the mobile frame 5-3, and the mobile frame 5-3 and the pitch frame 5-4 are hinged through the pitch axis 5-1 of the turntable, and the terminal azimuth The shaft sleeve 7-3 is located between the base 5-5 and the turntable azimuth shaft sleeve 5-2, and the terminal azimuth sha...

specific Embodiment approach 3

[0012] Specific implementation mode three: according to the instructions attached figure 2 Describe this embodiment in detail. This embodiment is a further description of Embodiment 2. In this embodiment, the pitch axis 5-1 of the turntable and the pitch axis 7-2 of the terminal have a range of motion of -80° to +80°. The motion ranges of the azimuth axis of the turntable and the terminal azimuth axis are both -180°~+180°.

[0013] In this embodiment, the one-dimensional guide rail 4 is also used to compensate the translation error of the aiming beam of the optical communication terminal 7 under test.

[0014] For this implementation mode, carry out example analysis:

[0015] The pitching frame 5-4 is a tuning-fork-type open structure, which enables the optical communication terminal 7 under test to communicate without obstruction within the range of motion, and the tuning-fork-type open structure facilitates the installation and debugging of the optical communication termin...

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Abstract

The invention discloses a platform for simulating link satellite photo-communication terminal-to-terminal relative sighting angle movement, relating to the field of satellite photo communication and solving the problem that the overall process of the satellite link dynamic tracking performance can not be simulated and detected by utilizing the prior platform for simulating satellite-to-satellite relative sighting angle movement. The platform consists of an upper computer 1, a lead rail controller 2, a rotary table controller 3, a one-dimensional lead rail 4 and a double-shaft rotary table 5. The upper computer 1 works out a group of expected positions corresponding to the double-shaft rotary table 5 and the one-dimensional lead rail 4; the rotary table controller 3 is utilized to control the double-shaft rotary table 5 to move so as to enable the double-shaft rotary table 5 to reach the self corresponding expected position, and the lead rail controller 2 is utilized to control the one-dimensional lead rail 4 to enable the one-dimensional lead rail 4 to reach the self corresponding expected position, and thereby, the simulation of the sighting angle deviation generated by a measured photo-communication terminal 7 is completed. The invention is suitable for simulation experiments of conditions of satellite-to-satellite photo-communication terminal links.

Description

technical field [0001] The invention relates to the field of satellite optical communication, in particular to a platform for simulating relative aiming angle movement between satellite optical communication terminals of a link. Background technique [0002] The inter-satellite laser link refers to the transmission of information between two or more satellites through light as a carrier. During the satellite link process, the terminal needs to perform real-time compensation for the relative angular motion caused by the satellite orbit and attitude changes. Sufficient testing on the ground is usually required to ensure success before a satellite link trial in space is conducted. Due to the long distance between the two link satellites and the high relative motion rate, it is difficult to directly simulate the space satellite link test on the ground. Therefore, a platform for simulating the relative angular motion between satellites is built to complete the space satellite lin...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): H04B10/118
Inventor 于思源马晶谭立英宋义伟武凤
Owner HARBIN INST OF TECH