CN104743141A - High-speed aircraft positioning method with satellite constellation - Google Patents
High-speed aircraft positioning method with satellite constellation Download PDFInfo
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- CN104743141A CN104743141A CN201510158049.4A CN201510158049A CN104743141A CN 104743141 A CN104743141 A CN 104743141A CN 201510158049 A CN201510158049 A CN 201510158049A CN 104743141 A CN104743141 A CN 104743141A
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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 aerocraft field of locating technology, particularly relate to a kind of high-speed aircraft pocket localization method adopting satellite constellation.
Background technology
Along with improving constantly of space-time duty requirements, day by day urgent to the location requirement of hyprsonic high-speed aircraft pocket.Existing GPS navigation system can meet this high dynamicpositioning demand 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, and wherein, operational satellites 21, backup satellite 3, is evenly distributed on 6 tracks, each track 4 satellites.But, also do not have the emergent of the location requirement beyond independent of GPS navigation system, high-speed aircraft pocket under high dynamic environment can be met at present and the position fixing system of economy.
In the research to high dynamicpositioning, design, develop beyond independent of GPS navigation system, adopt less satellite and the position fixing system of the location requirement of high-speed aircraft pocket under high dynamic environment can be met, be the technical matters needing solution at present badly.
Summary of the invention
The object of the invention is to, a kind of high-speed aircraft pocket localization method adopting satellite constellation is provided, adopt less satellite to meet the location requirement of high-speed aircraft pocket under high dynamic environment and not rely on GPS navigation system.
For achieving the above object, the invention provides a kind of high-speed aircraft pocket localization method adopting satellite constellation, comprise the steps: that (1) adopts and comprise the inclined plane satellite constellation of 8 satellites or sun-synchronous orbit satellite constellation positions; (2) on the star arranging described 8 satellites, beam angle is ± 60, satellite attitude adopts and point to the earth's core; (3) satellite orbital altitude arranging described 8 satellites is identical, is 400km-600km orbit altitude.
The invention has the advantages that: adopt and comprise the inclined plane satellite constellation of 8 satellites or sun-synchronous orbit satellite constellation all can meet the target positioned high-speed aircraft pocket, achieve independent of beyond GPS navigation system, the location requirement that adopts less satellite can realize high-speed aircraft pocket under high dynamic environment, meet emergent location requirement and possess good economy.
Accompanying drawing explanation
Fig. 1, the present invention adopts the diagram of circuit of the high-speed aircraft pocket 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.
Detailed description of the invention
Elaborate below in conjunction with the high-speed aircraft pocket localization method of accompanying drawing to employing satellite constellation provided by the invention.
The present invention, when positioning research to high-speed aircraft pocket, proposes one group independent of the satellite constellation localization method beyond GPS navigation system.With reference to figure 1, the present invention adopts the diagram of circuit of the high-speed aircraft pocket localization method of satellite constellation.Described localization method comprises the steps: S11: adopt and comprise the inclined plane satellite constellation of 8 satellites or sun-synchronous orbit satellite constellation positions; S12: on the star arranging described 8 satellites, beam angle is ± 60, satellite attitude adopts and point to the earth's core; S13: the satellite orbital altitude arranging described 8 satellites is identical, is 400km-600km orbit altitude.
When adopting the sun-synchronous orbit satellite constellation comprising 8 satellites to position, as optional embodiment, described 8 satellite distribution of described sun-synchronous orbit satellite constellation in 2 orthogonal orbital planes, adjacent satellite carrier phase shift 1 degree in same orbital plane; One orbital plane is 6:30 local time the in of the sun-synchronous orbit descending node of 4 satellites, and another orbital plane is 12:00 local time the in of the sun-synchronous orbit descending node of 4 satellites.
When adopting the sun-synchronous orbit satellite constellation comprising 8 satellites to position, as another optional embodiment, described 8 satellite distribution of described sun-synchronous orbit satellite constellation are in 1 orbital plane; Described 8 satellites are divided equally into 2 groups, adjacent satellite carrier phase shift 1 degree in same group, and two groups of Satellite Phase angles differ 180 degree; Be 6:30 local time the in of the sun-synchronous orbit descending node of described 8 satellites.
When adopting the inclined plane satellite constellation comprising 8 satellites to position, as optional embodiment, described 8 satellite distribution of described inclined plane satellite constellation at 2 in the orbital plane of space uniform distribution; Adjacent satellite carrier phase shift 1 degree in same orbital plane; The orbit inclination of described 8 satellites is identical, is between 40 degree of-55 degree.
Below in conjunction with accompanying drawing and form, to the present invention propose independent of beyond GPS navigation system, the covering performance of satellite constellation localization method to target area of less satellite (8) is adopted to emulate, to verify the validity that satellite constellation localization method provided by the invention positions high-speed aircraft pocket.Below emulate to position as target to certain spatial domain high-speed aircraft pocket, getting high-speed aircraft pocket flying height during emulation is about 40km, east longitude about 89 degree, and north latitude about 41 degree, flight track length is about 400km.
First carry out constellation satellite orbit decay emulation, emulate the satellite orbit stability of 400km, 500km, 600km orbit altitude respectively, getting atmospherical drag area-mass ratio during emulation is 0.005m
2/ kg, optical pressure area-mass ratio 0.04m
2/ kg.As in Figure 2-4, wherein, Fig. 2 is 600km orbit altitude decay schematic diagram in 2 years to simulation result; Fig. 3 is 500km orbit altitude decay schematic diagram in 2 years; Fig. 4 is 400km orbit altitude decay schematic diagram.Altitude decay's curve as can be seen from Fig. 2: in 2 years, 600km orbit altitude declines about 8km.Altitude decay's curve as can be seen from Fig. 3: in 2 years, 500km orbit altitude declines about 44km.Altitude decay's curve as can be seen from Fig. 4: 400km orbit altitude constellation satellite, after about 266 days, by the about 227km that declines, after this, falls entering rapidly atmospheric envelope.
From above-mentioned orbit altitude decay simulation result, the decay of 600km orbit altitude is minimum, and 500km decay is taken second place, and 400km attenuation ratio is more severe.Consider that between constellation satellite and 40km high-speed aircraft pocket highly, link should be as far as possible short again, to reduce link load, as preferred embodiment, in satellite constellation localization method of the present invention, the satellite orbital altitude of described 8 satellites is 500km orbit altitude.
Below carry out sun-synchronous orbit, the emulation of inclined plane both of these case constellation coverage property respectively, during emulation, choosing satellite orbital altitude is 500km orbit altitude.
First to adopting the coverage property comprising the sun-synchronous orbit satellite constellation of 8 satellites to emulate.
Sun-synchronous orbit satellite constellation embodiment one: described 8 satellite distribution of described sun-synchronous orbit satellite constellation are in 2 orthogonal orbital planes, adjacent satellite carrier phase shift 1 degree in same orbital plane, i.e. 120km (for 500km altitude satellite); One orbital plane is 6:30 local time the in of the sun-synchronous orbit descending node of 4 satellites, and another orbital plane is 12:00 local time the in of the sun-synchronous orbit descending node of 4 satellites.The revisit time of satellite to designated area of sun-synchronous orbit satellite constellation embodiment one is as shown in table 1, and it is as shown in table 2 that the satellite of sun-synchronous orbit satellite constellation embodiment one continues observation time to low target.
| Revisit time | Maximum | On average |
| 8 star/2 orbital planes | 65138s | 21339s (5.9 hours) |
The constellation satellite of table 1 sun-synchronous orbit satellite constellation embodiment one is to the revisit time of designated area
| SEE time | Maximum | On average | Minimum |
| 8 star/2 orbital planes | 261s | 224s | 111s |
The satellite of table 2 sun-synchronous orbit satellite constellation embodiment one continues observation time to low target
Sun-synchronous orbit satellite constellation embodiment two: described 8 satellite distribution of described sun-synchronous orbit satellite constellation are in 1 orbital plane; Described 8 satellites are divided equally into 2 groups, adjacent satellite carrier phase shift 1 degree in same group, i.e. 120km (for 500km altitude satellite), and two groups of Satellite Phase angles differ 180 degree; Be 6:30 local time the in of the sun-synchronous orbit descending node of described 8 satellites.The revisit time of satellite to designated area of sun-synchronous orbit satellite constellation embodiment two is as shown in table 3, and it is as shown in table 4 that the satellite of sun-synchronous orbit satellite constellation embodiment two continues observation time to low target.
| Revisit time | Maximum | On average |
| 8 star/1 orbital planes | 43956s | 23008s (6.4 hours) |
The satellite of table 3 sun-synchronous orbit satellite constellation embodiment two is to the revisit time of designated area
| SEE time | Maximum | On average | Minimum |
| 8 star/1 orbital planes | 261s | 216s | 119s |
The satellite of table 4 sun-synchronous orbit satellite constellation embodiment two continues observation time to low target
Next to adopting the coverage property comprising the inclined plane satellite constellation of 8 satellites to emulate.When adopting the inclined plane satellite constellation comprising 8 satellites to position, described 8 satellite distribution of described inclined plane satellite constellation are in 2 orbital planes, and two orbital planes distribute at space uniform; Adjacent satellite carrier phase shift 1 degree in same orbital plane, i.e. 120km (for 500km altitude satellite).
Inclined plane satellite constellation embodiment one: the orbit inclination of described 8 satellites is 55 degree.The revisit time of satellite to designated area of inclined plane satellite constellation embodiment one is as shown in table 5, and it is as shown in table 6 that the satellite of inclined plane satellite constellation embodiment one continues observation time to low target.
| Revisit time | Maximum | On average |
| 8 star/2 orbital planes | 33146s | 10206s (2.8 hours) |
The satellite of table 5 inclined plane satellite constellation embodiment one is to the revisit time of designated area
| SEE time | Maximum | On average | 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 of described 8 satellites is 45 degree.The revisit time of satellite to designated area of inclined plane satellite constellation embodiment two is as shown in table 7, and it is as shown in table 8 that the satellite of inclined plane satellite constellation embodiment two continues observation time to low target.
| Revisit time | Maximum | On average |
| 8 star/2 orbital planes | 44843s | 9951s (2.76 hours) |
The satellite of table 7 inclined plane satellite constellation embodiment two is to the revisit time of designated area
| SEE time | Maximum | On average | 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 of described 8 satellites is 40 degree.The revisit time of satellite to designated area of inclined plane satellite constellation embodiment three is as shown in table 9, and it is as shown in table 10 that the satellite of inclined plane satellite constellation embodiment three continues observation time to low target.
| Revisit time | Maximum | On average |
| 8 star/2 orbital planes | 44951s | 10157s (about 2.8 hours) |
The satellite of table 9 inclined plane satellite constellation embodiment three is to the revisit time of designated area
| SEE time | Maximum | On average | 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 above-mentioned inclined plane satellite constellation embodiment simulation result, the performance that when orbit inclination is 45 degree, satellite continues observation time to the revisit time of designated area and satellite to low target is all better.Therefore, as preferred embodiment, in satellite constellation localization method of the present invention, when adopting inclined plane satellite constellation, the orbit inclination of described 8 satellites is 45 degree.
Comprehensive above analysis of simulation result, can obtaining as drawn a conclusion: inclined plane satellite constellation and these two kinds of targeting schemes of sun-synchronous orbit satellite constellation all can realize the target positioned high-speed aircraft pocket, meeting emergent location requirement and possessing good economy.Wherein, when satellite orbit adopts inclined plane, the satellite constellation for high-speed aircraft pocket location preferentially adopts orbit inclination 45 degree.But, because the solar irradiation angle of the satellite of inclined plane changes greatly, energy stabilizing on star is obtained and has impact; Therefore obtain convenience from simplification design of satellite construction and the energy to consider, preferably adopt sun-synchronous orbit.When satellite orbit adopts sun-synchronous orbit, limited employing 8 satellites divide 2 orbital planes, and two orbital planes are vertical, same orbital plane, adjacent satellite carrier phase shift 1 degree, wherein 6:30 local time the in of 4 satellite descending nodes, the 12:00 local time in of another 4 satellite descending nodes.
The above is only the preferred embodiment of the present invention; it should be pointed out that for those skilled in the art, 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 considered as protection scope of the present invention.
Claims (6)
1. adopt a high-speed aircraft pocket localization method for satellite constellation, it is characterized in that, comprise the steps:
(1) the inclined plane satellite constellation comprising 8 satellites or sun-synchronous orbit satellite constellation is adopted to position;
(2) on the star arranging described 8 satellites, beam angle is ± 60, satellite attitude adopts and point to the earth's core;
(3) satellite orbital altitude arranging described 8 satellites is identical, is 400km-600km orbit altitude.
2. localization method according to claim 1, is characterized in that, the satellite orbital altitude of described 8 satellites is 500km orbit altitude.
3. localization method according to claim 2, is characterized in that, described 8 satellite distribution of described sun-synchronous orbit satellite constellation in 2 orthogonal orbital planes, adjacent satellite carrier phase shift 1 degree in same orbital plane; One orbital plane is 6:30 local time the in of the sun-synchronous orbit descending node of 4 satellites, and another orbital plane is 12:00 local time the in of the sun-synchronous orbit descending node of 4 satellites.
4. localization method according to claim 2, is characterized in that, described 8 satellite distribution of described sun-synchronous orbit satellite constellation are in 1 orbital plane; Described 8 satellites are divided equally into 2 groups, adjacent satellite carrier phase shift 1 degree in same group, and two groups of Satellite Phase angles differ 180 degree; Be 6:30 local time the in of the sun-synchronous orbit descending node of described 8 satellites.
5. localization method according to claim 2, is characterized in that, described 8 satellite distribution of described inclined plane satellite constellation at 2 in the orbital plane of space uniform distribution; Adjacent satellite carrier phase shift 1 degree in same orbital plane; The orbit inclination of described 8 satellites is identical, is between 40 degree of-55 degree.
6. localization method according to claim 5, is characterized in that, the orbit inclination of described 8 satellites is 45 degree.
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| CN105345453A (en) * | 2015-11-30 | 2016-02-24 | 北京卫星制造厂 | Position-posture determining method for automatically assembling and adjusting based on industrial robot |
| CN110754049A (en) * | 2017-04-24 | 2020-02-04 | 蓝色探索有限责任公司 | Sun synchronous rail |
| CN111650624A (en) * | 2018-09-29 | 2020-09-11 | 上海微小卫星工程中心 | Data filtering method based on projection variance discrimination and implementation device thereof |
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