CN101567721B - Beam-capturing scanning method for rapidly establishing laser link between relay satellite and user satellite - Google Patents
Beam-capturing scanning method for rapidly establishing laser link between relay satellite and user satellite Download PDFInfo
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- CN101567721B CN101567721B CN2009100719220A CN200910071922A CN101567721B CN 101567721 B CN101567721 B CN 101567721B CN 2009100719220 A CN2009100719220 A CN 2009100719220A CN 200910071922 A CN200910071922 A CN 200910071922A CN 101567721 B CN101567721 B CN 101567721B
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Abstract
A beam acquisition scanning method for rapidly establishing laser link between a relay satellite and a user satellite relates to a beam acquisition scanning method between satellites. The invention solves the problem that the acquisition time is long in the existing acquisition method of the relay satellite against the user satellite. The method comprises the following steps: step 1. a terminal ofthe relay satellite gives out a beacon light beam to a scanning spot of a region to be scanned; step 2. the terminal of the relay satellite gives out a beacon light beam to a next scanning point of t he region to be scanned according to time intervals; step 3. when the beacon light beam of step 1 or 2 reaches the region to be scanned, a terminal of the user satellite gives out a return light beam simultaneously; and step 4. the terminal of the relay satellite judges whether the return light beam of step 3 is received or not, if not, step 2 is executed again; if so, the terminal of the relay satellite stops giving out the beacon light beam, and the user satellite is at a previous scanning point and the acquisition of the relay satellite against the user satellite is successful. The method is applicable to the process of rapidly establishing a laser link between the relay satellite and the user satellite.
Description
Technical field
The present invention relates to beam-capturing scanning method between a kind of star.
Background technology
Laser link is mainly set up through the scanning of catching of link terminal between star, and the key technical indexes comprises acquisition probability and capture time.Generally require under the condition that satisfies certain acquisition probability requirement, capture time is short as far as possible.Because transmission range (about 45000km) far away between relaying star and user satellite (GEO-LEO), to catch when scanning, the optical signal transmission time, (time delay, the about 0.15s of unidirectional transmission time delay) was bigger to the influence of capture time.Existing scan capture method is: GEO sends at the terminal beacon beam signal, is transmitted into the scope (be defined as and catch uncertain angle) that the LEO terminal possibly exist.Because beacon beam signals diverging angle, GEO terminal is less than catching uncertain angle, the GEO terminal need be jumped to sweep with covering and caught uncertain angle.It is relevant with the rail control precision of GEO and LEO satellite to catch uncertain angle, is generally 8mrad.Existing laser link capture terminal beacon beam about 0.7mrad, consider seamless covering after, it is 0.4mrad that sweep spacing is set, and then in whole 8mrad catches uncertain angular range, need carry out at least 400 jumpings and sweep; Per step jumping for the GEO terminal is swept, if do not cover the LEO terminal, then carries out next step jumping and sweeps.The GEO terminal does not have heliogram in order to confirm the LEO terminal, each time delay (0.15s * 2) and terminal response time, control and time synchronous error (0.05s) of jumping the time interval considered light signal round-trip transmission of sweeping.That is to say that the time interval that per step at GEO terminal jumps between sweeping is 0.35s; If beacon beam is responded and sent in the LEO terminal just in the beacon beam coverage and receive the beacon beam signal.If the GEO terminal also receives the beacon beam signal, then think acquisition success.The maximum capture time of said method single game in catching uncertain region is 400 * 0.35s=140s.This catching method capture time is longer, causes the efficient communication time of laser inter-satellite link to shorten, and number biography ability is restricted.
Summary of the invention
The present invention has the relaying star problem long to the catching method capture time of user satellite now in order to solve, thereby proposes a kind of beam-capturing scanning method of setting up laser link between relaying star and user satellite fast.
Set up the beam-capturing scanning method of laser link between relaying star and user satellite fast, its step is:
Step 1: the scanning element of relaying star terminal in zone to be scanned sends beacon light beam;
Step 2: beacon light beam is sent by the time interval next scanning element in zone to be scanned in relaying star terminal;
Step 3: when step 1 or the described beacon light beam of step 2 arrived the scanning element in the zone to be scanned, the light echo light beam was sent at the user satellite terminal;
Step 4: whether relaying star terminal judges receives the light echo light beam described in the step 3, if judged result is for denying execution in step two; If judged result is for being, relaying star terminal then stops to send beacon light beam, and at this moment, user satellite is positioned at the previous scanning point place, and the relaying star is to the user satellite acquisition success;
The scope of the angle of visual field at relaying star terminal be can guarantee previous scanning point heliogram within relaying star capture range; Jump flyback time at interval greater than user satellite light echo propagation delay time.
Beneficial effect: capturing scanning method of the present invention; In jumping inswept journey, only need consider unidirectional transmission time delay; Jumping flyback time shortens at interval; Maximum capture time will have the used time of scan capture method now and improve more than 43%, improve the efficient communication time of laser inter-satellite link greatly, increase several biography abilities of system.
Description of drawings
Fig. 1 is the flow chart of method of the present invention.
Embodiment
Embodiment one: combine Fig. 1 that this embodiment is described, set up the beam-capturing scanning method of laser link between relaying star and user satellite fast, its step is:
Step 1: the scanning element of relaying star terminal in zone to be scanned sends beacon light beam;
Step 2: beacon light beam is sent by the time interval next scanning element in zone to be scanned in relaying star terminal;
Step 3: when step 1 or the described beacon light beam of step 2 arrived the scanning element in the zone to be scanned, the light echo light beam was sent at the user satellite terminal;
Step 4: whether relaying star terminal judges receives the light echo light beam described in the step 3, if judged result is for denying execution in step two; If judged result is for being, relaying star terminal then stops to send beacon light beam, and at this moment, user satellite is positioned at the previous scanning point place, and the relaying star is to the user satellite acquisition success;
The scope of the angle of visual field at relaying star terminal be can guarantee previous scanning point heliogram within relaying star capture range; Jump flyback time at interval greater than user satellite light echo propagation delay time.
This embodiment is carrying out at first carrying out orbital prediction according to prior art between the beam flying, guarantees that relaying star and user satellite get into link range.
Embodiment two: the difference of this embodiment and embodiment one is that described difference of setting up the beam-capturing scanning method of laser link between relaying star and user satellite fast is, the size of the angle of visual field at relaying star terminal is-4mrad～4mrad between.
Embodiment three: this embodiment and embodiment one or two described differences of setting up the beam-capturing scanning method of laser link between relaying star and user satellite fast are that the user satellite light echo propagation delay time time is 0.15s; Relaying star terminal in the step 2 is sent and jumped the time interval that clears off bundle is 0.2s.
Embodiment four: this embodiment is utilized the method for embodiment one, and combines concrete parameter to explain:
Emission beacon beam in relaying star terminal carries out helical scanning, and the user satellite terminal is carried out big visual field receive mode and caught, and concrete parameter sees the following form:
Maximum capture time implementation is analyzed:
The purpose that beacon beam scanning is carried out at relaying star terminal is in the short as far as possible time, to accomplish to catch.Therefore; Require of the maximum capture time restriction of relaying star terminal according to the practical laser link; Reasonably optimize the parameters such as respective cycle, scanning subarea quantity in beamwidth, each scanning subarea of beacon beam, and take all factors into consideration the influence of the factors such as pointing accuracy, platform stable degree at laser communication terminal.
Scanning angle scope and angle are overlapping:
According to the overall given uncertain angle of catching, carry out gamut scanning (8mrad).The beam divergence angle of relaying star capture terminal beacon beam is 700 μ rad, and in order to guarantee to scan catching the seamless covering at uncertain angle, the step pitch of helical scanning is not higher than at interval
Simultaneously, consider factors such as scan control error, satellite platform vibration, the scanning overlapping (promptly the step pitch of scanning is spaced apart 400 μ rad) of 95 μ rad is set.The maximum scan time:
In sum; In catching uncertain angle 8mrad scope (corresponding diameter is the round territory of 360km near the user satellite terminal); Beacon beam beam spreading angle is near 700 μ rad (corresponding diameter is the round territory of 31.5km the user satellite terminal), considers overlapping, the scan control sum of errors platform vibration compensation of scanning, and the covering of realization gamut need be carried out the scanning of 400 steps; Total time is about 80s, is merely about 57% of the conventional method time spent.In addition, spiral scan is owing to begin scanning from the higher place of satellite probability of occurrence, and therefore short time IT success often.
Claims (3)
1. set up the beam-capturing scanning method of laser link between relaying star and user satellite fast, it is characterized in that its step is:
Step 1: the scanning element of relaying star terminal in zone to be scanned sends beacon light beam;
Step 2: beacon light beam is sent by the time interval next scanning element in zone to be scanned in relaying star terminal;
Step 3: when step 1 or the described beacon light beam of step 2 arrive the scanning element in the zone to be scanned,, then send the light echo light beam if the user satellite terminal is positioned at the coverage of this scanning element and receives this beacon light beam;
Step 4: whether relaying star terminal judges receives the light echo light beam described in the step 3, if judged result is for denying execution in step two; If judged result is for being, relaying star terminal then stops to send beacon light beam, and at this moment, user satellite is positioned at the previous scanning point place, and the relaying star is to the user satellite acquisition success;
The scope of the angle of visual field at relaying star terminal be can guarantee previous scanning point heliogram within relaying star capture range; Jump flyback time at interval greater than user satellite light echo propagation delay time.
2. the beam-capturing scanning method of setting up laser link between relaying star and user satellite fast according to claim 1, the scope of the angle of visual field that it is characterized in that relaying star terminal is between-4mrad～4mrad.
3. the beam-capturing scanning method of setting up laser link between relaying star and user satellite fast according to claim 1 and 2 is characterized in that the user satellite light echo propagation delay time time is 0.15s; Relaying star terminal in the step 2 is sent and jumped the time interval that clears off bundle is 0.2s.
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| CN101567721B true CN101567721B (en) | 2012-03-28 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN109543292A (en) * | 2018-11-21 | 2019-03-29 | 哈尔滨工业大学 | The emulation mode of inter-satellite link signal capture process based on orbital prediction |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN101793526B (en) * | 2010-04-12 | 2011-10-26 | 哈尔滨工业大学 | Autonomous relative navigation method for multi-information fusion formation spacecrafts |
| CN106788657B (en) * | 2016-11-11 | 2019-06-11 | 浙江大学 | Spaceborne low-power consumption light beacon system and its implementation |
| CN113507579B (en) * | 2021-08-04 | 2023-05-12 | 上海交通大学 | Inter-satellite laser link capturing method and system for space gravitational wave detection |
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| CN1825787A (en) * | 2006-04-03 | 2006-08-30 | 哈尔滨工业大学 | Method for establishing laser link between low orbit safellite and ground station |
| CN101072072A (en) * | 2007-06-15 | 2007-11-14 | 哈尔滨工业大学 | Space optical communication terminal scanning acquisition performance ground test method |
| CN101207440A (en) * | 2007-12-19 | 2008-06-25 | 哈尔滨工业大学 | Capture performance test method of space optical communication system |
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Patent Citations (4)
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| CN1300012A (en) * | 1999-12-16 | 2001-06-20 | Actv公司 | Intensified video programming system and method using tocal host computer to conduct network communication |
| CN1825787A (en) * | 2006-04-03 | 2006-08-30 | 哈尔滨工业大学 | Method for establishing laser link between low orbit safellite and ground station |
| CN101072072A (en) * | 2007-06-15 | 2007-11-14 | 哈尔滨工业大学 | Space optical communication terminal scanning acquisition performance ground test method |
| CN101207440A (en) * | 2007-12-19 | 2008-06-25 | 哈尔滨工业大学 | Capture performance test method of space optical communication system |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN109543292A (en) * | 2018-11-21 | 2019-03-29 | 哈尔滨工业大学 | The emulation mode of inter-satellite link signal capture process based on orbital prediction |
| CN109543292B (en) * | 2018-11-21 | 2022-04-29 | 哈尔滨工业大学 | Simulation method of inter-satellite link signal capturing process based on orbit prediction |
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