阅读说明：本技术 一箭多星任务中的卫星识别方法 (Satellite identification method in one-rocket multi-satellite task ) 是由 周欢 赵磊 于 2019-08-15 设计创作，主要内容包括：本发明涉及航天测控领域,特别涉及在一箭多星任务中的卫星识别方法。为了快速从一箭多星任务发射的卫星中辨别每颗卫星位置,本发明提出一种一箭多星任务中的卫星识别方法,通过对卫星下行信号多普勒频率的跟踪,结合卫星初始轨道仅利用一个圈次的跟踪就可以快速分辨出每颗卫星位置。本发明无需特殊设备,操作简单,识别精确。(The invention relates to the field of aerospace measurement and control, in particular to a satellite identification method in a one-arrow multi-satellite task. In order to quickly distinguish the position of each satellite from the satellites transmitted by the one-arrow-multi-satellite task, the invention provides a satellite identification method in the one-arrow-multi-satellite task. The invention does not need special equipment, and has simple operation and accurate identification.)

1. The satellite identification method in the one-arrow-multi-satellite task is characterized by comprising the following steps of:

step 1: recording the total number of satellites in the one-arrow-multi-satellite task as N, and recording each satellite as a satellite A in sequence¹Satellite A²Satellite A³Until satellite A^NWherein the jth satellite is denoted as satellite A^jJ takes values from 1, 2, 3 up to N;

step 2: when a plurality of satellites enter the tracking range of the ground measurement and control station, the ground measurement and control station records the spectrum signals of all visible satellites by using a broadband receiver or a spectrometer, and each recorded satellite is sequentially recorded as a satellite B¹Satellite B²Satellite B³Until satellite B^NWherein the ith satellite is denoted as satellite BⁱThe values of i are 1, 2, 3 to N, and the ith satellite B is recordedⁱTime T at which the Doppler shift of the signal is 0_i；

And step 3: bonded satellite A¹Satellite A²Satellite A³Up to satellite a^NThe initial orbit and the geographic position of the ground measurement and control station, and the jth satellite A is calculated^jThe maximum elevation angle passing through the ground station and the corresponding time t_j；

And 4, step 4: for the jth satellite A^jI takes values 1, 2, 3 to N in sequence, and | t is calculated_j-T_i|²When | t_j-T_i|²At the minimum, the jth satellite A^jI.e. recorded satellite Bⁱ。

And 5: and repeating the step 4 to distinguish the position of each satellite.

Technical Field

The invention relates to the field of aerospace measurement and control, in particular to a satellite identification method in a one-arrow multi-satellite task.

Background

One rocket multi-satellite is a technology for simultaneously or sequentially sending a plurality of satellites into the earth orbit by using one carrier rocket. More and more launch tasks of the launch vehicle adopt a one-rocket multi-satellite launch mode, so that the launch capability of the launch vehicle can be fully utilized, and space launch car pooling is realized. In 2015, 20 small satellites are sent to the first flight task of a six-rocket of China in one time; in 2018, China successfully sends Saudi-5A/5B and 10 carried and launched small satellites into a preset orbit by using a Changchun No. two launch vehicle; in the long-standing No. eleven maritime launching task in 2019, 7 small satellites are launched into the space at one time.

In the one-arrow multi-satellite task, the separation time interval of each satellite is relatively small, and the distances in the first few days after the satellites are in orbit are very close, so that a plurality of small satellites usually enter the wave beam range of the ground measurement and control station at the same time, and the ground measurement and control station can receive signals of a plurality of satellites at the same time. How to quickly distinguish each satellite from multiple satellites is a difficult problem. The current main method utilizes a ground station measurement and control station to track and measure each satellite, and identifies each satellite after determining the accurate orbit of the satellite through a plurality of circles of measured values. This method requires many cycles of tracking measurements and is inefficient.

Disclosure of Invention

The invention aims to provide a satellite identification method in a one-arrow multi-satellite task, which can quickly identify each satellite by tracking the Doppler frequency of a satellite downlink signal and only using one circle of tracking in combination with the initial orbit of the satellite.

The object of the present invention can be achieved by the following means. The satellite identification method in the one-arrow-multi-satellite task is characterized by comprising the following steps of:

step 1: recording the total number of satellites in the one-arrow-multi-satellite task as N, and recording each satellite as a satellite A in sequence¹Satellite A²Satellite A³Until satellite A^NWherein the jth satellite is denoted as satellite A^jJ takes values from 1, 2, 3 up to N;

step 2: when a plurality of satellites enter the tracking range of the ground measurement and control station, the ground measurement and control station records the spectrum signals of all visible satellites by using a broadband receiver or a spectrometer, and each recorded satellite is sequentially recorded as a satellite B¹Satellite B²Satellite B³Until satellite B^NWherein the ith satellite is denoted as satellite BⁱThe values of i are 1, 2, 3 to N, and the ith satellite B is recordedⁱTime T at which the Doppler shift of the signal is 0_i；

And step 3: bonded satellite A¹Satellite A²Satellite A³Up to satellite a^NThe initial orbit and the geographic position of the ground measurement and control station, and the jth satellite A is calculated^jThe maximum elevation angle passing through the ground station and the corresponding timet_j；

And 4, step 4: for the jth satellite A^jI takes values 1, 2, 3 to N in sequence, and | t is calculated_j-T_i|²When | t_j-T_i|²At the minimum, the jth satellite A^jI.e. recorded satellite Bⁱ。

And 5: and repeating the step 4 to distinguish the position of each satellite.

The present invention has the following advantageous effects.

The method can distinguish the position of each satellite in the one-arrow multi-satellite task only by using the ground measurement and control station for one circle of tracking without special equipment, and has simple operation and accurate identification.

Drawings

FIG. 1 is a schematic illustration of the present invention.

Detailed Description

Referring to fig. 1, the present invention is implemented as follows:

step 1: recording the total number of satellites in the one-arrow-multi-satellite task as N, and recording each satellite as a satellite A in sequence¹Satellite A²Satellite A³Until satellite A^NWherein the jth satellite is denoted as satellite A^jJ takes values from 1, 2, 3 up to N.

Step 2: when a plurality of satellites enter the tracking range of the ground measurement and control station, the ground measurement and control station records the spectrum signals of all visible satellites by using a broadband receiver or a spectrometer, and each recorded satellite is sequentially recorded as a satellite B¹Satellite B²Satellite B³Until satellite B^NWherein the ith satellite is denoted as satellite BⁱThe values of i are 1, 2, 3 to N, and the ith satellite B is recordedⁱTime T at which the Doppler shift of the signal is 0_i. For example: satellite B¹The time T when the Doppler frequency shift of the satellite signal is 0₁Satellite B²The time T when the Doppler frequency shift of the satellite signal is 0₂。

And step 3: bonded satellite A¹Satellite A²Satellite A³Up to satellite a^NInitial orbit and ground station geographyPosition, calculate the jth satellite A^jThe maximum elevation angle passing through the ground station and the corresponding time t_j. For example: satellite A¹T is the time corresponding to the maximum elevation angle over the ground station₁Satellite A²T is the time corresponding to the maximum elevation angle over the ground station₂。

And 4, step 4: for the 1 st satellite A¹I takes values 1, 2, 3 to N in sequence, and | t is calculated₁-T_i|²If i is equal to n, | t₁-T_n|²At minimum, then satellite A¹Satellite B of corresponding recordⁿ。

And 5: for the 2 nd satellite A²I takes values 1, 2, 3 to N in sequence, and | t is calculated₂-T_i|²If i is m, | t₂-T_m|²At minimum, then satellite A²Satellite B of corresponding record^m。

Step 6: for the 3 rd satellite A³I takes values 1, 2, 3 to N in sequence, and | t is calculated₃-T_i|²If i is equal to k, | t₃-T_k|²At minimum, then satellite A³Satellite B of corresponding record^k。

And 7: similarly, by repeating the above steps, the position of each satellite can be identified.

While the embodiments of the present invention have been described in detail, those skilled in the art will recognize that the embodiments of the present invention can be practiced without limitation.

The technical features mentioned above are combined with each other to form various embodiments which are not listed above, and all of them are regarded as the scope of the present invention described in the specification; also, modifications and variations may be suggested to those skilled in the art in light of the above teachings, and it is intended to cover all such modifications and variations as fall within the true spirit and scope of the invention as defined by the appended claims.