CN104743141B - High-speed aircraft positioning method with satellite constellation - Google Patents
High-speed aircraft positioning method with satellite constellation Download PDFInfo
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- CN104743141B CN104743141B CN201510158049.4A CN201510158049A CN104743141B CN 104743141 B CN104743141 B CN 104743141B CN 201510158049 A CN201510158049 A CN 201510158049A CN 104743141 B CN104743141 B CN 104743141B
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Abstract
The invention provides a high-speed aircraft positioning method with a satellite constellation; the method comprises the steps: (1) positioning by adopting an inclined orbit satellite constellation containing eight satellites or a Sun-synchronous orbit satellite constellation; (2) setting the on-the-star beam angle of eight satellites to be+-60 degrees and utilizing the direction toward the earth's core as the satellite altitude; and (3) setting the satellite orbital altitude of the eight satellites to be the same and to be 400-600km. The inclined orbit satellite constellation containing eight satellites or the Sun-synchronous orbit satellite constellation is capable of achieving the purpose of positioning a high-speed aircraft; the positioning requirement of the high-speed aircraft in an high-dynamic environment can be satisfied by being independent of an GPS navigation system and adopting less satellites; and the method has good economical efficiency.
Description
Technical field
The present invention relates to airborne vehicle field of locating technology, the high speed airborne vehicle positioning of more particularly, to a kind of employing satellite constellation
Method.
Background technology
With the continuous improvement of space-time duty requirements, increasingly urgent to the location requirement of supersonic speed high speed airborne vehicle.Existing
Gps navigation system can meet this high dynamic location requirement to a certain extent.Gps navigation system is made up of three parts:
Space segment gps constellation；Ground control segment ground monitoring system；Customer equipment part gps signal receiver.gps
Navigation system is made up of 24 satellites, wherein, operational satellites 21, backup satellite 3, it is evenly distributed on 6 tracks, each
4 satellites of track.But, beyond also not having independent of gps navigation system at present, disclosure satisfy that under high dynamic environment at a high speed
The emergent and economic alignment system of the location requirement of airborne vehicle.
In the research that high dynamic is positioned, design, exploitation independent of beyond gps navigation system, adopt less satellite
And disclosure satisfy that the alignment system of the location requirement of high speed airborne vehicle under high dynamic environment, it is that the technology of current urgent need to resolve is asked
Topic.
Content of the invention
It is an object of the invention to, a kind of high speed airborne vehicle localization method of employing satellite constellation is provided, is defended using less
Star is to meet under high dynamic environment the location requirement of high speed airborne vehicle and not rely on gps navigation system.
For achieving the above object, the invention provides a kind of high speed airborne vehicle localization method of employing satellite constellation, including
Following steps: (1) is positioned using the inclined plane satellite constellation or satellite in Sun-synchronous orbit constellation including 8 satellites；
(2) arranging field angle on the star of described 8 satellites is that ± 60, attitude of satellite is pointed to using to the earth's core；(3) described 8 of setting is defended
The satellite orbital altitude of star is identical, is 400km-600km orbit altitude.
It is an advantage of the current invention that: using the inclined plane satellite constellation or the satellite in Sun-synchronous orbit that include 8 satellites
Constellation all can meet the target that high speed airborne vehicle is positioned it is achieved that defending independent of beyond gps navigation system, using less
Star enables the location requirement to high speed airborne vehicle under high dynamic environment, meets emergent location requirement and possesses good economy
Property.
Brief description
Fig. 1, the flow chart that the present invention adopts the high speed airborne vehicle localization method of satellite constellation；
Fig. 2,600km orbit altitude decay schematic diagram in 2 years；
Fig. 3,500km orbit altitude decay schematic diagram in 2 years；
Fig. 4,400km orbit altitude decay schematic diagram.
Specific embodiment
The high speed airborne vehicle localization method using the satellite constellation below in conjunction with the accompanying drawings present invention being provided elaborates.
The present invention when Position Research is carried out to high speed airborne vehicle it is proposed that one group independent of gps navigation system beyond
Satellite constellation localization method.The flow chart adopting the high speed airborne vehicle localization method of satellite constellation with reference to Fig. 1, the present invention.Described
Localization method comprises the steps: s11: using the inclined plane satellite constellation or the satellite in Sun-synchronous orbit that include 8 satellites
Constellation is positioned；S12: arranging field angle on the star of described 8 satellites is that ± 60, attitude of satellite is pointed to using to the earth's core；
S13: the satellite orbital altitude arranging described 8 satellites is identical, is 400km-600km orbit altitude.
When being positioned using the satellite in Sun-synchronous orbit constellation including 8 satellites, as optional embodiment,
Described 8 satellite distribution of described satellite in Sun-synchronous orbit constellation in 2 orthogonal orbital planes, same orbital plane
1 degree of upper adjacent satellite carrier phase shift；It is 6:30 local time the sun-synchronous orbit southbound node of 4 satellites in one orbital plane, separately
It is 12:00 local time the sun-synchronous orbit southbound node of 4 satellites in one orbital plane.
When being positioned using the satellite in Sun-synchronous orbit constellation including 8 satellites, as another optional enforcement
Mode, described 8 satellite distribution of described satellite in Sun-synchronous orbit constellation are in 1 orbital plane；Described 8 satellites are divided equally into
2 groups, 1 degree of adjacent satellite carrier phase shift in same group, two groups of Satellite Phase angles differ 180 degree；The sun of described 8 satellites is same
Step descending node of orbit local time is 6:30.
When being positioned using the inclined plane satellite constellation including 8 satellites, as optional embodiment, described
Described 8 satellite distribution of inclined plane satellite constellation are in 2 orbital planes in space uniform distribution；In same orbital plane
1 degree of adjacent satellite carrier phase shift；The orbit inclination angle of described 8 satellites is identical, is between 40 degree of -55 degree.
Below in conjunction with accompanying drawing and form, beyond the navigation system independent of gps proposed by the present invention, using less satellite
The satellite constellation localization method of (8) emulates to the covering performance of target area, to verify the Satellite that the present invention provides
The effectiveness that seat localization method is positioned to high speed airborne vehicle.Hereinafter emulate to orientate as to certain spatial domain high speed airborne vehicle
Target, takes high speed airborne vehicle flying height to be 40km during emulation, about 89 degree of east longitude, about 41 degree of north latitude, flight track length
About 400km.
Enter the decay emulation of planetary satellite orbit, the satellite rail to 400km, 500km, 600km orbit altitude respectively first
Road stability is emulated, and takes atmospheric drag area-mass ratio to be 0.005m during emulation2/ kg, optical pressure area-mass ratio 0.04m2/kg.Emulation
As in Figure 2-4, wherein, Fig. 2 is 600km orbit altitude decay schematic diagram in 2 years to result；Fig. 3 is that in 2 years, 500km track is high
Degree decay schematic diagram；Fig. 4 is 400km orbit altitude decay schematic diagram.From altitude decay's curve of Fig. 2 it can be seen that in 2 years,
600km orbit altitude declines about 8km.From altitude decay's curve of Fig. 3 it can be seen that in 2 years, 500km orbit altitude declines about
44km.From altitude decay's curve of Fig. 4 it can be seen that 400km orbit altitude constellation satellite, after about 266 days, will decline about
227km, hereafter, will quickly enter atmosphere and fall.
From the point of view of above-mentioned orbit altitude decay simulation result, the decay of 600km orbit altitude is minimum, and 500km decay is taken second place,
400km attenuation ratio is more severe.Consider further that between constellation satellite and the high speed airborne vehicle of 40km height, link should be as far as possible short, with
Reduce link load, as preferred embodiment, in satellite constellation localization method of the present invention, described 8 satellites
Satellite orbital altitude is 500km orbit altitude.
Carry out sun-synchronous orbit, the emulation of inclined plane both of these case constellation coverage property, during emulation, choosing individually below
Satellite orbital altitude is taken to be 500km orbit altitude.
Emulate to using the coverage property of the satellite in Sun-synchronous orbit constellation including 8 satellites first.
Satellite in Sun-synchronous orbit constellation embodiment one: described 8 satellites of described satellite in Sun-synchronous orbit constellation
Be distributed in 2 orthogonal orbital planes, 1 degree of adjacent satellite carrier phase shift in same orbital plane, that is, 120km (for
For 500km altitude satellite)；It is 6:30 local time the sun-synchronous orbit southbound node of 4 satellites in one orbital plane, another track
It is 12:00 local time the sun-synchronous orbit southbound node of 4 satellites on face.Satellite in Sun-synchronous orbit constellation embodiment one
Satellite is as shown in table 1 to the revisit time of designated area, and the satellite of satellite in Sun-synchronous orbit constellation embodiment one is to low latitude
Target Continuous observation time is as shown in table 2.
| Revisit time | Maximum | Averagely |
| 8 star/2 orbital planes | 65138s | 21339s (5.9 hours) |
The revisit time to designated area for the constellation satellite of table 1 satellite in Sun-synchronous orbit constellation embodiment one
| SEE time | Maximum | Averagely | Minimum |
| 8 star/2 orbital planes | 261s | 224s | 111s |
The satellite of table 2 satellite in Sun-synchronous orbit constellation embodiment one continues observation time to low target
Satellite in Sun-synchronous orbit constellation embodiment two: described 8 satellites of described satellite in Sun-synchronous orbit constellation
It is distributed in 1 orbital plane；Described 8 satellites are divided equally into 2 groups, 1 degree of adjacent satellite carrier phase shift in same group, i.e. 120km
(for 500km altitude satellite), two groups of Satellite Phase angles differ 180 degree；The sun-synchronous orbit fall of described 8 satellites is handed over
Point local time is 6:30.The revisit time such as table 3 to designated area for the satellite of satellite in Sun-synchronous orbit constellation embodiment two
Shown, the satellite of satellite in Sun-synchronous orbit constellation embodiment two is as shown in table 4 to the lasting observation time of low target.
| Revisit time | Maximum | Averagely |
| 8 star/1 orbital planes | 43956s | 23008s (6.4 hours) |
The revisit time to designated area for the satellite of table 3 satellite in Sun-synchronous orbit constellation embodiment two
| SEE time | Maximum | Averagely | Minimum |
| 8 star/1 orbital planes | 261s | 216s | 119s |
The satellite of table 4 satellite in Sun-synchronous orbit constellation embodiment two continues observation time to low target
Next emulate to using the coverage property of the inclined plane satellite constellation including 8 satellites.Using bag
When including the inclined plane satellite constellation of 8 satellites and being positioned, described 8 satellite distribution of described inclined plane satellite constellation exist
In 2 orbital planes, two orbital planes are distributed in space uniform；1 degree of adjacent satellite carrier phase shift in same orbital plane, that is,
120km (for 500km altitude satellite).
Inclined plane satellite constellation embodiment one: the orbit inclination angle of described 8 satellites is 55 degree.Inclined plane satellite
The satellite of constellation embodiment one is as shown in table 5 to the revisit time of designated area, inclined plane satellite constellation embodiment one
Satellite to low target continue observation time as shown in table 6.
| Revisit time | Maximum | Averagely |
| 8 star/2 orbital planes | 33146s | 10206s (2.8 hours) |
The revisit time to designated area for the satellite of table 5 inclined plane satellite constellation embodiment one
| SEE time | Maximum | Averagely | Minimum |
| 8 star/2 orbital planes | 252s | 177s | 45s |
The satellite of table 6 inclined plane satellite constellation embodiment one continues observation time to low target
Inclined plane satellite constellation embodiment two: the orbit inclination angle of described 8 satellites is 45 degree.Inclined plane satellite
The satellite of constellation embodiment two is as shown in table 7 to the revisit time of designated area, inclined plane satellite constellation embodiment two
Satellite to low target continue observation time as shown in table 8.
| Revisit time | Maximum | Averagely |
| 8 star/2 orbital planes | 44843s | 9951s (2.76 hours) |
The revisit time to designated area for the satellite of table 7 inclined plane satellite constellation embodiment two
| SEE time | Maximum | Averagely | Minimum |
| 8 star/2 orbital planes | 275s | 256s | 236s |
The satellite of table 8 inclined plane satellite constellation embodiment two continues observation time to low target
Inclined plane satellite constellation embodiment three: the orbit inclination angle of described 8 satellites is 40 degree.Inclined plane satellite
The satellite of constellation embodiment three is as shown in table 9 to the revisit time of designated area, inclined plane satellite constellation embodiment three
Satellite to low target continue observation time as shown in table 10.
| Revisit time | Maximum | Averagely |
| 8 star/2 orbital planes | 44951s | 10157s (about 2.8 hours) |
The revisit time to designated area for the satellite of table 9 inclined plane satellite constellation embodiment three
| SEE time | Maximum | Averagely | Minimum |
| 8 star/2 orbital planes | 276s | 226s | 47s |
The satellite of table 10 inclined plane satellite constellation embodiment three continues observation time to low target
From the point of view of above-mentioned inclined plane satellite constellation embodiment simulation result, when orbit inclination angle is 45 degree, satellite is to finger
Revisit time and the satellite of determining region are all preferable to the performance of the lasting observation time of low target.Accordingly, as preferred reality
Apply mode, in satellite constellation localization method of the present invention, during using inclined plane satellite constellation, the rail of described 8 satellites
Road inclination is 45 degree.
Comprehensive above analysis of simulation result, can obtain as drawn a conclusion: inclined plane satellite constellation and sun-synchronous orbit
Satellite constellation both targeting schemes all enable the target that high speed airborne vehicle is positioned, and meet emergent location requirement and tool
Standby good economy.Wherein, when satellite orbit adopts inclined plane, the satellite constellation for high speed airborne vehicle positioning is preferential
Using 45 degree of orbit inclination angle.But, the solar irradiation angle due to the satellite of inclined plane changes greatly, and energy stabilizing on star is obtained
Take and have an impact；Therefore obtain convenience to consider from simplification design of satellite construction and the energy, it is preferred to use sun-synchronous orbit.When
When satellite orbit adopts sun-synchronous orbit, limited adopt 8 satellites to divide in 2 orbital planes, two orbital planes are vertical, same
Orbital plane, 6:30 local time 1 degree of adjacent satellite carrier phase shift, wherein 4 satellite southbound nodes, another 4 satellite southbound nodes are local
When 12:00.
The above is only the preferred embodiment of the present invention it is noted that ordinary skill people for the art
Member, under the premise without departing from the principles of the invention, can also make some improvements and modifications, these improvements and modifications also should be regarded as
Protection scope of the present invention.
Claims (6)
1. a kind of high speed airborne vehicle localization method using satellite constellation is it is characterised in that comprise the steps:
(1) positioned using the inclined plane satellite constellation or satellite in Sun-synchronous orbit constellation including 8 satellites；
(2) arrange described 8 satellites star on field angle be ± 60 degree, the attitude of satellite using to the earth's core sensing；
(3) satellite orbital altitude arranging described 8 satellites is identical, is 400km-600km orbit altitude.
2. localization method according to claim 1 is it is characterised in that the satellite orbital altitude of described 8 satellites is 500km
Orbit altitude.
3. localization method according to claim 2 it is characterised in that described satellite in Sun-synchronous orbit constellation described 8
Satellite distribution in 2 orthogonal orbital planes, 1 degree of adjacent satellite carrier phase shift in same orbital plane；One track
It is 6:30 local time the sun-synchronous orbit southbound node of 4 satellites on face, the sun-synchronous orbit of 4 satellites in another orbital plane
Southbound node local time is 12:00.
4. localization method according to claim 2 it is characterised in that described satellite in Sun-synchronous orbit constellation described 8
Satellite distribution is in 1 orbital plane；Described 8 satellites are divided equally into 2 groups, 1 degree of adjacent satellite carrier phase shift in same group, and two
Group Satellite Phase angle difference 180 degree；The sun-synchronous orbit southbound node of described 8 satellites local time is 6:30.
5. localization method according to claim 2 is it is characterised in that described 8 of described inclined plane satellite constellation are defended
Star is distributed in 2 orbital planes in space uniform distribution；1 degree of adjacent satellite carrier phase shift in same orbital plane；Described 8
The orbit inclination angle of satellite is identical, is between 40 degree of -55 degree.
6. localization method according to claim 5 is it is characterised in that the orbit inclination angle of described 8 satellites is 45 degree.
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| CN105345453B (en) * | 2015-11-30 | 2017-09-22 | 北京卫星制造厂 | A kind of pose debug that automated based on industrial robot determines method |
| US10807740B2 (en) * | 2017-04-24 | 2020-10-20 | Blue Digs LLC | Sun synchronous orbit |
| CN109163727B (en) * | 2018-09-29 | 2020-06-30 | 上海微小卫星工程中心 | Electronic reconnaissance satellite target track dynamic estimation method and implementation device thereof |
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