Data transmission method for low-orbit satellites oriented to mission delay constraints
A data transmission method and technology of low-orbit satellites, applied in transmission systems, radio transmission systems, network traffic/resource management, etc., can solve problems such as lack of task delay constraints, loss of timeliness, and excessive delay
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Embodiment 1
[0058] Embodiment 1, can finish k max A data transmission method for low-orbit satellites with mission delay constraints carried by hopping integers
[0059] The example of the present invention illustrates the implementation process of the present invention from a single-track Iridium satellite communication network scene. Suppose there are M=11 satellite nodes in the network {Sa 1 ,Sa 2 ,…Sa 11} are located on the same orbit with an inclination angle of 90° and a height of 780km, and the storage capacity of each satellite is 40Gb. According to the initial position of the satellite, 11 ground station sets can be obtained {GS 1 ,GS 2 ,…GS 11} position information, and establish a ground-fixed star-ground visible relationship. The transmission capacity of the inter-satellite link is 25Mbps, and the transmission capacity of the satellite-ground link is 50Mbps. The spatial information network will complete the end-to-end transmission of the service according to the initial...
Embodiment 2
[0151] Embodiment 2, can finish k max A data transmission method for low-orbit satellites with mission delay constraints carried by hopping integers
[0152] The spatial information network scenario of this embodiment is the same as that of Embodiment 1, but the generation time CT of the data packet is different, and the data packet needs to use a transmission method different from that of Embodiment 1. Its implementation steps are as follows:
[0153] Step 1, initialize the satellite collection of the spatial information network, and establish the inter-satellite topology relationship.
[0154] The specific implementation of this step is the same as step 1 of Embodiment 1.
[0155] Step 2. Calculate the position of the ground station under each orbit and deploy the ground station on the surface of the earth to construct a fixed time-varying star-ground connection relationship on the ground.
[0156] The specific implementation of this step is the same as step 2 of Embodime...
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