CN110703283B - Satellite identification method in one-rocket multi-satellite task - Google Patents

Satellite identification method in one-rocket multi-satellite task Download PDF

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Publication number
CN110703283B
CN110703283B CN201910758121.5A CN201910758121A CN110703283B CN 110703283 B CN110703283 B CN 110703283B CN 201910758121 A CN201910758121 A CN 201910758121A CN 110703283 B CN110703283 B CN 110703283B
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satellite
task
satellites
jth
arrow
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CN110703283A (en
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周欢
赵磊
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Emposat Co Ltd
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Emposat Co Ltd
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    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
    • G01S19/00—Satellite radio beacon positioning systems; Determining position, velocity or attitude using signals transmitted by such systems
    • G01S19/01—Satellite radio beacon positioning systems transmitting time-stamped messages, e.g. GPS [Global Positioning System], GLONASS [Global Orbiting Navigation Satellite System] or GALILEO
    • G01S19/13—Receivers
    • G01S19/24—Acquisition or tracking or demodulation of signals transmitted by the system
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
    • G01C21/00—Navigation; Navigational instruments not provided for in groups G01C1/00 - G01C19/00
    • G01C21/24—Navigation; Navigational instruments not provided for in groups G01C1/00 - G01C19/00 specially adapted for cosmonautical navigation
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
    • G01S19/00—Satellite radio beacon positioning systems; Determining position, velocity or attitude using signals transmitted by such systems
    • G01S19/01—Satellite radio beacon positioning systems transmitting time-stamped messages, e.g. GPS [Global Positioning System], GLONASS [Global Orbiting Navigation Satellite System] or GALILEO
    • G01S19/13—Receivers
    • G01S19/24—Acquisition or tracking or demodulation of signals transmitted by the system
    • G01S19/29—Acquisition or tracking or demodulation of signals transmitted by the system carrier including Doppler, related

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  • Engineering & Computer Science (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Remote Sensing (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Computer Networks & Wireless Communication (AREA)
  • Astronomy & Astrophysics (AREA)
  • Automation & Control Theory (AREA)
  • Position Fixing By Use Of Radio Waves (AREA)

Abstract

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.

Description

Satellite identification method in one-rocket multi-satellite task
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 ANWherein the jth satellite is denoted as satellite AjJ 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 BNWherein 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 0i；
And step 3: bonded satellite A1Satellite A2Satellite A3Up to satellite aNThe initial orbit and the geographic position of the ground measurement and control station, and the jth satellite A is calculatedjThe maximum elevation angle passing through the ground station and the corresponding time tj；
And 4, step 4: for the jth satellite AjI takes values 1, 2, 3 to N in sequence, and | t is calculatedj-Ti|2When | tj-Ti|2At the minimum, the jth satellite AjI.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 ANWherein the jth satellite is denoted as satellite AjJ 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 BNWherein 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 0i. 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 aNThe initial orbit and the geographic position of the ground measurement and control station, and the jth satellite A is calculatedjThe maximum elevation angle passing through the ground station and the corresponding time tj. 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-Ti|2If i is equal to n, | t1-Tn|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-Ti|2If i is m, | t2-Tm|2At minimum, then satellite A2Satellite B of corresponding recordm。
Step 6: for the 3 rd satellite A3I takes values 1, 2, 3 to N in sequence, and | t is calculated3-Ti|2If i is equal to k, | t3-Tk|2At minimum, then satellite A3Satellite B of corresponding recordk。
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.

Claims (1)

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 ANWherein the jth satellite is denoted as satellite AjJ 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 frequency spectrum signals of all visible satellites by using a broadband receiver or a frequency spectrograph, and each satellite is recordedAre sequentially marked as satellite B1Satellite B2Satellite B3Until satellite BNWherein 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 0i；
And step 3: bonded satellite A1Satellite A2Satellite A3Up to satellite aNThe initial orbit and the geographic position of the ground measurement and control station, and the jth satellite A is calculatedjThe maximum elevation angle passing through the ground station and the corresponding time tj；
And 4, step 4: for the jth satellite AjI takes values 1, 2, 3 to N in sequence, and | t is calculatedj-Ti|2When | tj-Ti|2At the minimum, the jth satellite AjI.e. recorded satellite Bi；
And 5: and repeating the step 4 to distinguish the position of each satellite.
CN201910758121.5A 2019-08-15 2019-08-15 Satellite identification method in one-rocket multi-satellite task Active CN110703283B (en)

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Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103064094A (en) * 2012-12-14 2013-04-24 北京邮电大学 Method of capturing satellite signals and receiver using the same
CN104180810A (en) * 2014-08-26 2014-12-03 上海微小卫星工程中心 Satellite measurement and control exit-entry judging method and device
CN106027138A (en) * 2016-05-05 2016-10-12 清华大学 Ground station system and method for avoiding collinear interference with geostationary satellite
CN106772466A (en) * 2016-11-17 2017-05-31 中国西安卫星测控中心 A kind of near-earth satellite target automatic capture algorithm based on shape facility search
JP2018109530A (en) * 2016-12-28 2018-07-12 国立研究開発法人宇宙航空研究開発機構 Flying body-purposed navigation unit, flying body, and flying body safety control system

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103064094A (en) * 2012-12-14 2013-04-24 北京邮电大学 Method of capturing satellite signals and receiver using the same
CN104180810A (en) * 2014-08-26 2014-12-03 上海微小卫星工程中心 Satellite measurement and control exit-entry judging method and device
CN106027138A (en) * 2016-05-05 2016-10-12 清华大学 Ground station system and method for avoiding collinear interference with geostationary satellite
CN106772466A (en) * 2016-11-17 2017-05-31 中国西安卫星测控中心 A kind of near-earth satellite target automatic capture algorithm based on shape facility search
JP2018109530A (en) * 2016-12-28 2018-07-12 国立研究開発法人宇宙航空研究開発機構 Flying body-purposed navigation unit, flying body, and flying body safety control system

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
动中通卫星识别跟踪系统的研究与设计;章彪等;《电光与控制》;20181231;第25卷(第12期);全文 *

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