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On-orbit high-speed injection system and method based on SpaceWire bus

A high-speed, bus-based technology, applied in the field of satellite data transmission, can solve the problems of not being able to support specified data frames for resuming transmission at breakpoints, low reliability of uploaded data, and single type of uploaded data, etc., so as to facilitate flexible arrangement and convenience Flexible arrangement and small system delay

Active Publication Date: 2021-03-09
XIAN INSTITUE OF SPACE RADIO TECH
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Problems solved by technology

[0003] The technical problem solved by the present invention is: overcome the deficiency of using the S measurement and control channel as the uplink, and focus on solving the following four problems: ①, solve the problem of low timeliness of uplink; ②, solve the problem of low reliability of upnote data; ③, Solve the problem of not being able to support breakpoint resuming and specifying data frames; ④ Solve the problem of a single data type in the above, and support the needs of multiple terminals

Method used

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  • On-orbit high-speed injection system and method based on SpaceWire bus
  • On-orbit high-speed injection system and method based on SpaceWire bus
  • On-orbit high-speed injection system and method based on SpaceWire bus

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Embodiment

[0077] The data upload link completes the conversion of the above service data packet to the above service data frame. After completing scrambling, code conversion, convolutional coding, SQPSK modulation, and power amplification, it is sent uplink to the relay satellite. The specific implementation is described in detail below with a specific example of a certain model.

[0078] ①. Business data block design

[0079] The above-mentioned business data packets are processed by the ground software according to the protocol approved by all parties on the satellite and ground, and then converted into a VCDU format conforming to the definition of CCSDS. The VCDU frame length is 896 bytes. VCDU frame format specific definition see figure 2 ,in:

[0080] 1) Synchronization header: 32bits, 1ACFFC1D(H);

[0081] 2) Transmission frame version number: 2 bits, set to '01';

[0082] 3) Spacecraft identifier SCID: 8 digits, 01(H), users can define it by themselves;

[0083] 4) Virtual...

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Abstract

The invention discloses an on-orbit high-speed injection system and an on-orbit high-speed injection method based on a SpaceWire bus. The system comprises a data uplink injection link module, a relaysatellite and a user satellite. The system provided by the invention is short in time delay, greatly shortens the uploading time, and is easy to use for a user; the data reliability is high, step-by-step verification based on an upper injection data frame and an upper injection data packet is completed, and the reliability of upper injection data transmission is ensured; breakpoint resume and specified data frame annotation can be realized, and flexible arrangement of annotation tasks of a user is facilitated; and the types of the uploaded data are variable, so that the maintenance requirements of on-orbit data of different satellite-borne equipment are met.

Description

technical field [0001] The invention relates to the technical field of satellite data transmission, and is applicable to the design of a satellite system equipped with relay satellite KSA data channel and space-borne SpaceWire bus network design. Background technique [0002] With the increasing complexity of spaceborne software functional requirements, it is bound to lead to a significant increase in software scale, and correspondingly, the size of software configuration data will also increase significantly. Traditionally, the satellite system is designed for uploading links, and adopts the S measurement and control channel design method. The uploading time often takes several months, which is not convenient for the planning and implementation of the uploading task, and also reduces the reliability of the uploading data. This shortcoming makes the actual engineering application, after the satellite is in orbit, very few models actually implement the on-orbit injection oper...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): H04B7/185
CPCH04B7/18513H04B7/18519H04B7/18521Y02D30/70
Inventor 赵妍郑小松陈安和王鸣涛武小栋袁小娜魏昕
Owner XIAN INSTITUE OF SPACE RADIO TECH
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