CN111891387A - Satellite layout method and system for satellite-borne full-airspace load - Google Patents
Satellite layout method and system for satellite-borne full-airspace load Download PDFInfo
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- CN111891387A CN111891387A CN202010717045.6A CN202010717045A CN111891387A CN 111891387 A CN111891387 A CN 111891387A CN 202010717045 A CN202010717045 A CN 202010717045A CN 111891387 A CN111891387 A CN 111891387A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
- B64G1/1007—Communications satellites
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
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Abstract
The invention provides a satellite layout method and a satellite layout system for satellite-borne full airspace loads, which comprise the following steps: step 1: analyzing the configuration characteristics of the satellite according to the configuration of the satellite platform and the effective load; step 2: according to the satellite configuration characteristics, the full airspace load is restrained; and step 3: constructing a load configuration which accords with the presetting according to the constrained full airspace load; and 4, step 4: and based on the configuration of the existing satellite platform and the effective load, carrying out the satellite layout of the full airspace load according to a preset load configuration. The invention solves the layout problem of the full airspace load of different frequency bands, systems and purposes on various satellite platforms of different types, has stronger universality and practicability, and can provide support for the design of the satellite overall and related load configurations.
Description
Technical Field
The invention relates to the technical field of satellite overall design, in particular to a satellite layout method and a satellite layout system for satellite-borne full airspace loads.
Background
With the rapid development of satellite technology, the networking and formation tasks of satellites are frequent, and higher requirements are put forward on inter-satellite communication, particularly the omni-directionality and the real-time performance of the inter-satellite communication. In order to meet the inter-satellite communication requirement for multi-satellite cluster formation of complex configurations, aiming at reducing on-satellite resource overhead, multi-satellite normalized chain building, self-adaptive tracking and chain rebuilding requirements, the development of the related global inter-satellite microwave communication under complex configurations becomes a trend. Generally, the satellite carries a load for full airspace communication (referred to as "full airspace load" for short), and is limited by constraints such as a satellite configuration, a load configuration, and an orbit condition, and how to design a full airspace load configuration satisfying the constraints according to the existing configuration of the satellite and perform on-satellite layout becomes one of the problems that needs to be solved urgently.
Patent document CN208209953U (application number: 201820572514.8) discloses a satellite-borne laser communication terminal array, but only laser communication in a certain angular range of a local direction can be realized, and the communication requirement of full spatial coverage in a rail space cannot be realized. The method provided by the invention effectively solves the problem of satellite layout design aiming at the full airspace load.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a satellite layout method and a satellite layout system for satellite-borne full airspace loads.
The satellite layout method for the satellite-borne full airspace load provided by the invention comprises the following steps:
step 1: analyzing the configuration characteristics of the satellite according to the configuration of the satellite platform and the effective load;
step 2: according to the satellite configuration characteristics, the full airspace load is restrained;
and step 3: constructing a load configuration which accords with the presetting according to the constrained full airspace load;
and 4, step 4: and based on the configuration of the existing satellite platform and the effective load, carrying out the satellite layout of the full airspace load according to a preset load configuration.
Preferably, the step 2 comprises: analyzing the safety distance allowance between the existing configuration of the satellite and the fairing by combining the enveloping of the fairing of the carrier rocket;
according to the safety distance allowance, the full airspace load is restricted, including a load system, load envelope size, quality and quantity;
the loading regime includes mechanical scanning and phased arrays.
Preferably, the mechanical scanning includes one-dimensional scanning and two-dimensional scanning, and the phased array includes a combination of a plurality of area array antennas;
if the load system is mechanical scanning, the star meets the envelope of the fairing when the load is in a folded state, and the star is compatible with other load fields on the star in a maneuvering range when the load is in an unfolded state;
and if the loading system is a phased array, analyzing the combination of the number configuration of the loading antennas and each antenna area array.
Preferably, the step 4 comprises: according to the basic principle of the preset load configuration and satellite configuration layout, the full-airspace 360-degree capturing communication simulation analysis of the load is carried out, the full-airspace load is laid out on each outer side face of the satellite, and the full-airspace 360-degree non-shielding communication is carried out by taking the satellite as the center.
Preferably, the full airspace load is a combination of a plurality of load heads to realize the communication of the full airspace of the satellite, and the communication comprises the following forms: 2 two-dimensional mechanical scanning type loading head combinations or 2 combinations of 3 planar array phased array antennas or 3 combinations of 2 planar array phased array antennas.
The satellite layout system of the satellite-borne full airspace load provided by the invention comprises:
module M1: analyzing the configuration characteristics of the satellite according to the configuration of the satellite platform and the effective load;
module M2: according to the satellite configuration characteristics, the full airspace load is restrained;
module M3: constructing a load configuration which accords with the presetting according to the constrained full airspace load;
module M4: and based on the configuration of the existing satellite platform and the effective load, carrying out the satellite layout of the full airspace load according to a preset load configuration.
Preferably, the module M2 includes: analyzing the safety distance allowance between the existing configuration of the satellite and the fairing by combining the enveloping of the fairing of the carrier rocket;
according to the safety distance allowance, the full airspace load is restricted, including a load system, load envelope size, quality and quantity;
the loading regime includes mechanical scanning and phased arrays.
Preferably, the mechanical scanning includes one-dimensional scanning and two-dimensional scanning, and the phased array includes a combination of a plurality of area array antennas;
if the load system is mechanical scanning, the star meets the envelope of the fairing when the load is in a folded state, and the star is compatible with other load fields on the star in a maneuvering range when the load is in an unfolded state;
and if the loading system is a phased array, analyzing the combination of the number configuration of the loading antennas and each antenna area array.
Preferably, the module M4 includes: according to the basic principle of the preset load configuration and satellite configuration layout, the full-airspace 360-degree capturing communication simulation analysis of the load is carried out, the full-airspace load is laid out on each outer side face of the satellite, and the full-airspace 360-degree non-shielding communication is carried out by taking the satellite as the center.
Preferably, the full airspace load is a combination of a plurality of load heads to realize the communication of the full airspace of the satellite, and the communication comprises the following forms: 2 two-dimensional mechanical scanning type loading head combinations or 2 combinations of 3 planar array phased array antennas or 3 combinations of 2 planar array phased array antennas.
Compared with the prior art, the invention has the following beneficial effects: the invention restrains and arranges the full airspace load, solves the arrangement problem of the full airspace load of different frequency bands, systems and purposes on various satellite platforms of different types, has stronger universality and practicability, and can provide support for the design of the satellite overall and related load configurations.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
FIG. 1 is a detailed flowchart of a satellite layout design method for satellite-borne full airspace loads;
FIG. 2 is a schematic diagram of a 3-plane phased array antenna microwave loading structure;
FIG. 3 is a schematic view of a 2-plane phased array antenna microwave loading structure;
FIG. 4 is a configuration diagram of 2 3-area array microwave loads in the A-star transmitting state;
FIG. 5 is a configuration diagram of 2 3-area array microwave loads in the flying state of the A star;
FIG. 6 is a configuration diagram of 3 2-area array microwave loads in a B-star transmitting state;
fig. 7 is a configuration diagram of 3 2-area array microwave loads in a B-star flight state.
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.
Example (b):
as shown in fig. 1, the satellite layout design method of the satellite-borne full airspace load of the present invention includes the following steps:
step 1: and analyzing the configuration characteristics of the satellite. Depending on the configuration of the satellite platform and payload, particular emphasis is placed on large expansion components, moving components, payload heads for wide field requirements, and the like.
Step 2: and (5) putting forward the design constraint of the full airspace load. Analyzing the safety distance allowance between the existing configuration of the satellite and the fairing by combining the enveloping of the fairing of the carrier rocket; according to the space allowance of the satellite, the design of the full airspace load is restrained, and the design comprises a load system (mechanical scanning or phased array), load envelope size, quality, quantity and the like.
And step 3: and (5) designing the configuration of the full airspace load. And (4) designing a load configuration meeting the requirement according to the design constraint of the full airspace load provided in the step (2). If the load system is mechanical scanning, not only the fact that the star meets the envelope of the fairing when the load is in a folded state is considered, but also the view field compatibility with other loads on the star in a maneuvering range when the load is in an unfolded state is considered; if the load is in a phased array system, the number configuration of load antennas, the area array combination of each antenna and the like can be analyzed.
And 4, step 4: and (4) on-satellite layout of full airspace load. Based on the configuration of the existing platform and the effective load of the satellite, the configuration scheme of the full airspace load is combined, the full airspace 360-degree capturing communication simulation analysis of the load is carried out according to the basic principle of the satellite configuration design, the full airspace load is reasonably distributed on each outer side face of the satellite, and the full airspace 360-degree non-shielding communication function with the satellite as the center is realized.
The satellite-borne full airspace load is not limited to a certain specific frequency band, load system and application.
The satellite is suitable for all satellites needing to carry full airspace loads and is not limited to a certain specific satellite platform and load configuration.
The design constraint of the full airspace load refers to all factors influencing the load configuration scheme, including but not limited to load system (mechanical scanning or phased array), envelope size, quality, quantity, heat consumption, working temperature and the like.
The full airspace load system comprises mechanical scanning and phased array. The mechanical scanning includes one-dimensional scanning, two-dimensional scanning, and the like, and the phased array system is a combination of a plurality of area array antennas.
The full airspace load is a combination of a plurality of loading heads to realize the communication of the satellite in the full airspace, and the communication comprises but is not limited to the following forms: 2 two-dimensional mechanical scanning type load head combinations, 2 combinations of 3 planar array phased array antennas, 3 combinations of 2 planar array phased array antennas and the like.
The detailed description is carried out by combining the laser and microwave full airspace load on-satellite layout of an electronic remote sensing satellite.
The electronic remote sensing satellite system consists of a plurality of satellites, and the inter-satellite microwave full airspace load of two satellites (A star and B star) is taken as an example. The microwave load of the selected 3-plane phased array antenna is shown in figure 2, and the wave beam of each plane array can cover 1/3 spherical space; with the 2-plane phased array antenna selected as shown in fig. 3, the beam of each plane array can cover 1/2 spherical space.
By analyzing the configuration characteristics of the A star, a large-scale expansion component on the A star only has two wings to drive a solar cell array in one dimension, 2 sides corresponding to the front and back directions of the flight of the satellite are distributed with laser loads, the laser loads need to have the view field requirement of 1/2 sphere areas, 2 sides corresponding to the two directions of the ground to the sky of the satellite are relatively open, the space constraint allowance of a fairing to the A star is comprehensively carried, so the A star adopts the configuration scheme of configuring 2 3-surface phased array antennas microwave loads, the 2 3-surface phased array antennas microwave loads are respectively distributed on the ground to the satellite and the sky to ensure that the microwave loads are higher than other loads, the beam coverage requirements of the A star to the space of the 1/2 sphere areas of the ground and the B day can be respectively met, and further the communication coverage of the 360-degree full airspace of the satellite can be realized. The configuration diagram of the satellite transmission state is shown in fig. 4, and the configuration diagram of the satellite flight state is shown in fig. 5.
By analyzing the configuration characteristics of the satellite B, a large-scale expansion part on the satellite B is provided with a two-wing one-dimensional driving solar cell array and a two-dimensional driving relay antenna which respectively occupy 3 side faces of the satellite, laser loads are distributed on 2 side faces corresponding to the front and back flying directions of the satellite, and the space constraint allowance of a comprehensive carrying fairing for the satellite B is calculated, so that the satellite B adopts a scheme of configuring 3 2-face phased array antenna microwave loads, the 3 2-face phased array antenna microwave loads are respectively distributed in the middle area of the satellite on the ground and the side areas close to the front and back flying directions on the sky, the full airspace space is uniformly divided into 3 blocks along the rotating shaft direction of the solar cell array by the distribution, each 2-face phased array antenna respectively covers the corresponding 1/3 spherical space, and further the communication coverage of the satellite 360-degree full airspace is realized. The configuration diagram of the satellite transmission state is shown in fig. 6, and the configuration diagram of the satellite flight state is shown in fig. 7.
The invention provides a new design idea for a satellite layout method of satellite-borne full airspace load, the design method becomes the first choice of a satellite general designer, and the invention can be widely applied in the field.
Those skilled in the art will appreciate that, in addition to implementing the systems, apparatus, and various modules thereof provided by the present invention in purely computer readable program code, the same procedures can be implemented entirely by logically programming method steps such that the systems, apparatus, and various modules thereof are provided in the form of logic gates, switches, application specific integrated circuits, programmable logic controllers, embedded microcontrollers and the like. Therefore, the system, the device and the modules thereof provided by the present invention can be considered as a hardware component, and the modules included in the system, the device and the modules thereof for implementing various programs can also be considered as structures in the hardware component; modules for performing various functions may also be considered to be both software programs for performing the methods and structures within hardware components.
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.
Claims (10)
1. A satellite layout method of satellite-borne full airspace load is characterized by comprising the following steps:
step 1: analyzing the configuration characteristics of the satellite according to the configuration of the satellite platform and the effective load;
step 2: according to the satellite configuration characteristics, the full airspace load is restrained;
and step 3: constructing a load configuration which accords with the presetting according to the constrained full airspace load;
and 4, step 4: and based on the configuration of the existing satellite platform and the effective load, carrying out the satellite layout of the full airspace load according to a preset load configuration.
2. The satellite layout method of the satellite-borne full airspace load according to claim 1, wherein the step 2 comprises: analyzing the safety distance allowance between the existing configuration of the satellite and the fairing by combining the enveloping of the fairing of the carrier rocket;
according to the safety distance allowance, the full airspace load is restricted, including a load system, load envelope size, quality and quantity;
the loading regime includes mechanical scanning and phased arrays.
3. The method according to claim 2, wherein the mechanical scanning comprises one-dimensional scanning and two-dimensional scanning, and the phased array comprises a combination of a plurality of area array antennas;
if the load system is mechanical scanning, the star meets the envelope of the fairing when the load is in a folded state, and the star is compatible with other load fields on the star in a maneuvering range when the load is in an unfolded state;
and if the loading system is a phased array, analyzing the combination of the number configuration of the loading antennas and each antenna area array.
4. The satellite layout method of the satellite-borne full airspace load according to claim 1, wherein the step 4 comprises: according to the basic principle of the preset load configuration and satellite configuration layout, the full-airspace 360-degree capturing communication simulation analysis of the load is carried out, the full-airspace load is laid out on each outer side face of the satellite, and the full-airspace 360-degree non-shielding communication is carried out by taking the satellite as the center.
5. The method according to claim 1, wherein the satellite-borne full airspace load is a combination of a plurality of loading heads to realize the communication of the satellite full airspace, and the form of the communication comprises: 2 two-dimensional mechanical scanning type loading head combinations or 2 combinations of 3 planar array phased array antennas or 3 combinations of 2 planar array phased array antennas.
6. A satellite layout system of satellite-borne full airspace load is characterized by comprising:
module M1: analyzing the configuration characteristics of the satellite according to the configuration of the satellite platform and the effective load;
module M2: according to the satellite configuration characteristics, the full airspace load is restrained;
module M3: constructing a load configuration which accords with the presetting according to the constrained full airspace load;
module M4: and based on the configuration of the existing satellite platform and the effective load, carrying out the satellite layout of the full airspace load according to a preset load configuration.
7. The system according to claim 6, wherein the module M2 comprises: analyzing the safety distance allowance between the existing configuration of the satellite and the fairing by combining the enveloping of the fairing of the carrier rocket;
according to the safety distance allowance, the full airspace load is restricted, including a load system, load envelope size, quality and quantity;
the loading regime includes mechanical scanning and phased arrays.
8. The system according to claim 7, wherein the mechanical scanning comprises one-dimensional scanning and two-dimensional scanning, and the phased array comprises a combination of multiple area array antennas;
if the load system is mechanical scanning, the star meets the envelope of the fairing when the load is in a folded state, and the star is compatible with other load fields on the star in a maneuvering range when the load is in an unfolded state;
and if the loading system is a phased array, analyzing the combination of the number configuration of the loading antennas and each antenna area array.
9. The system according to claim 6, wherein the module M4 comprises: according to the basic principle of the preset load configuration and satellite configuration layout, the full-airspace 360-degree capturing communication simulation analysis of the load is carried out, the full-airspace load is laid out on each outer side face of the satellite, and the full-airspace 360-degree non-shielding communication is carried out by taking the satellite as the center.
10. The system according to claim 6, wherein the full airspace load is a combination of multiple loading heads to realize satellite full airspace communication, and the form comprises: 2 two-dimensional mechanical scanning type loading head combinations or 2 combinations of 3 planar array phased array antennas or 3 combinations of 2 planar array phased array antennas.
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| CN109665118A (en) * | 2019-01-28 | 2019-04-23 | 上海卫星工程研究所 | Embedded Solar and Heliospheric Observatory configuration |
| RU2725824C1 (en) * | 2020-01-10 | 2020-07-06 | Акционерное общество "Научно-производственное объединение им. С.А. Лавочкина" | Device for group launch of satellites and reinforced frame |
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2020
- 2020-07-23 CN CN202010717045.6A patent/CN111891387B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN203589185U (en) * | 2013-11-19 | 2014-05-07 | 中国电子科技集团公司第五十四研究所 | Multi-plane full-airspace-covering satellite mobile communication phased-array antenna |
| CN104092485A (en) * | 2014-05-30 | 2014-10-08 | 中国电子科技集团公司第十研究所 | Distributed communication-in-motion light shaped antenna |
| CN109018432A (en) * | 2018-06-19 | 2018-12-18 | 上海卫星工程研究所 | The high-precision comprehensive remote sensing satellite of multi-load synergistic observation is laid out |
| CN109159925A (en) * | 2018-07-02 | 2019-01-08 | 上海卫星工程研究所 | A kind of load that meets is to the satellite sun wing configuration designing method of day observation requirements |
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| RU2725824C1 (en) * | 2020-01-10 | 2020-07-06 | Акционерное общество "Научно-производственное объединение им. С.А. Лавочкина" | Device for group launch of satellites and reinforced frame |
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