CN110994192B - Satellite-borne long-focus large-aperture antenna whole-satellite layout and expansion design method - Google Patents
Satellite-borne long-focus large-aperture antenna whole-satellite layout and expansion design method Download PDFInfo
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- CN110994192B CN110994192B CN201911043727.7A CN201911043727A CN110994192B CN 110994192 B CN110994192 B CN 110994192B CN 201911043727 A CN201911043727 A CN 201911043727A CN 110994192 B CN110994192 B CN 110994192B
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q19/00—Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic
- H01Q19/10—Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic using reflecting surfaces
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/27—Adaptation for use in or on movable bodies
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- H01Q1/288—Satellite antennas
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Abstract
A whole-satellite layout and expansion design method for a satellite-borne long-focus large-aperture antenna belongs to the field of satellite-borne large-scale expandable antennas. The method mainly comprises the following steps: 1) pre-mounting the unfolded reflecting surface on the whole star body according to input conditions; 2) translating the reflecting surface, and determining a layout mode according to the size relation; 3) preliminarily determining the positions of the reflecting surfaces (in a folded state and an unfolded state); 4) optimizing the lengths of the unfolding arm and the switching arm, and determining the positions of the reflecting surface and the feed source array; 5) carrying out antenna field inspection; 6) and determining the unfolding mode of the reflecting surface and the unfolding arm of the antenna. The calculation method is simple and effective, and the unfolding mode of the reflecting surface is given in detail.
Description
Technical Field
The invention relates to a whole satellite layout and expansion design method of a satellite-borne long-focus large-caliber antenna, and belongs to the field of satellite-borne large-scale expandable antennas.
Background
The satellite-borne large-scale deployable antenna generally means that a reflecting surface of the antenna is in an expanded form, the antenna mainly comprises a feed source array and the reflecting surface, and the focal ratio is generally 0.4-1.0. When the unfolded aperture of the reflecting surface is larger than 12 meters, the focal length of the antenna is at least 5 meters and exceeds the height of the satellite body, the reflecting surface is unfolded to a position far away from the satellite body by using the unfolding arm, the relative relation between the antenna feed source array and the reflecting surface can be ensured, and the layout and the unfolding mode of the reflecting surface, the unfolding arm and the feed source array on the whole satellite are of great importance.
A certain high-orbit satellite adopts a 20-meter-grade deployable antenna, and the focal length reaches 10 meters; the size of the whole satellite is 2.1 meters by 4.2 meters, the focal length is 2.5 times of the height of the whole satellite, and the index of the whole satellite is far higher than that of the prior art, so that the design method in the prior art is not applicable.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: the defects of the prior art are overcome, and a whole satellite layout and unfolding design method of a satellite-borne long-focus large-aperture antenna is provided, wherein the method mainly comprises the following steps: 1) pre-mounting the unfolded reflecting surface on the whole star body according to input conditions; 2) translating the reflecting surface, and determining a layout mode according to the size relation; 3) preliminarily determining the positions of the reflecting surfaces (in a folded state and an unfolded state); 4) optimizing the lengths of the unfolding arm and the switching arm, and determining the positions of the reflecting surface and the feed source array; 5) checking the antenna view field and rechecking the electrical design performance; 6) and determining the unfolding mode of the reflecting surface. The calculation method is simple and effective, and the unfolding mode of the reflecting surface is given in detail.
The purpose of the invention is realized by the following technical scheme:
a whole-satellite layout and expansion design method for a satellite-borne long-focus large-aperture antenna comprises the following steps:
s1, measuring the distance L0 between the reflecting surface and the star, and measuring the length L20 of an allowable arm pipe of the single-cabin plate surface of the star;
s2, determining the length L1 of a switching arm of the reflecting surface according to the carrying envelope, and determining the position relation between the reflecting surface and the feed source array layout; determining an unfolding area of the reflecting surface, and determining the position of an unfolding hinge at the root of the unfolding arm according to the unfolding area;
s3, determining the arm tube length L2, the adapting arm length L1, the total length and the unfolding angle of the unfolding arm according to the distance L0 in S1, the position of the unfolding hinge in the arm tube length L20 and S2;
and S4, determining the final position of the reflecting surface according to the position of the unfolding hinge in S2, the total length of the unfolding arm in S2 and the unfolding angle, and then determining the final position of the feed array.
Preferably, if the sum of the length L1 of the transfer arm and the length L20 of the arm tube is more than 1.1 times of L0, the reflecting surface in the folded state and the feed source array are arranged on the same side cabin plate of the star body; if the sum of the length L1 of the transfer arm and the length L20 of the arm tube is less than 0.9 times of L0, the reflecting surface and the feed source array in the folded state are arranged on the star body in a U-shaped layout; otherwise, the same side cabin board layout or U-shaped layout is selected according to the states of the actual feed source array, the star, the weight and the like.
Preferably, the expanded aperture of the reflecting surface is greater than 12 meters.
Preferably, the focal length of the reflecting surface is greater than 5 meters.
Preferably, the method for determining the value of the arm tube length L2 and the value of the transfer arm length L1 in S3 includes: the sum of the arm tube length L2 and the adapter arm length L1 is minimized.
Preferably, after S4, the antenna is inspected for a field of view.
Preferably, in S1, establishing a preliminary model of the reflector expansion state and the satellite whole star based on the antenna coordinate system, and then translating the antenna coordinate system based on the satellite coordinate system to determine the initial position relationship of the antenna coordinate system relative to the satellite coordinate system; for determining the spread area of the reflecting surface.
A computer-readable storage medium, on which a computer program is stored, which when executed by a processor implements the steps of the above-described method.
Compared with the prior art, the invention has the following beneficial effects:
(1) by adopting a U-shaped layout mode, the layout configuration design and the expansion mode of the ultra-large-caliber long-focus satellite-borne expandable antenna on the whole satellite body of the satellite are realized;
(2) the position relation between the reflector and the feed source array can be rapidly and effectively preliminarily determined by comparing the sum of the length L1 of the transfer arm and the length L2 of the single-cabin plate surface allowable arm rod with the distance L0 between the reflecting surface and the star body;
(3) the system provides a layout method, a flow, an algorithm and an expansion mode of the long-focus large-caliber expandable antenna on the whole satellite body.
Drawings
FIG. 1 is a flow chart of the steps of the method of the present invention;
FIG. 2 is a schematic diagram of the distance L0 between the reflecting surface 2 and the star 1 and the allowable arm tube length L20 of the single deck;
fig. 3 is a schematic diagram of a back-to-back (U-shaped) layout structure of the reflecting surface 2 and the feed array 3;
FIG. 4 is a schematic view of the reflection surface 2 rotated by an angle θ about the central axis A;
FIG. 5 is a schematic view of the position of the hinge at the root of the unfolding arm in the same deck layout;
FIG. 6 is a schematic view of the position of the hinge at the root of the unfolded arm in a back-to-back (U-shaped) layout;
fig. 7 is a schematic view of the unfolding process of the reflecting surface 2 in the same deck layout mode;
fig. 8 is a schematic view of the unfolding process of the reflective surface 2 in a back-to-back (U-shaped) layout.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, embodiments of the present invention will be described in detail with reference to the accompanying drawings.
A whole-satellite layout and expansion design method for a satellite-borne long-focus large-aperture antenna comprises the following steps:
first, the main input conditions are determined:
firstly, a satellite three-dimensional model and a satellite coordinate system;
secondly, the electrical design of the antenna provides a direction matrix of an antenna design coordinate system relative to a satellite coordinate system according to the requirements of the orbit position and the beam pointing;
thirdly, electrical design provides parameters of relation between the antenna reflecting surface and the feed source, such as caliber, focal length, offset and the like;
and fourthly, the whole star layout and the unfolding design need to consider that all unfolding shafts of the unfolding arms are parallel when unfolded and are vertical to the ground when the unfolding arms are unfolded in the ground unfolding test.
According to input conditions, carrying out layout configuration design and determining the unfolding mode of the reflecting surface according to the following steps:
the method comprises the following steps: establishing the size of a feed source array 3, the unfolding size of a reflecting surface 2 and the folding size of the reflecting surface 2 according to input conditions;
step two: establishing a preliminary reflector 2 unfolding state model according to the position relation parameters of the antenna reflector 2 and the feed source array 3, wherein the design reference is an antenna design coordinate system;
step three: according to the input conditions, on the basis of the direction matrix of the antenna design coordinate system relative to the satellite coordinate system, setting the initial position of the antenna design coordinate system relative to the satellite coordinate system to be (0, 0, 0), and assembling the reflection surface 2 unfolding state model on the satellite whole satellite model;
step four: translating the antenna design coordinate system by using the whole satellite coordinate system as a reference, so that the feed source array 3 is arranged at a proper position (the fixed installation position or the unfolded position of the feed source) on the satellite body, and determining the initial position relation of the antenna design coordinate system relative to the satellite coordinate system (Xa1, Ya1, Za 1);
step five: measuring the distance L0 between the reflecting surface 2 and the star 1 and the allowable arm tube length L20 of the single cabin plate surface, as shown in FIG. 2;
step six: mounting a fixing device and constraint limitation of satellite star catalogue layout according to the size of the folded state of the reflecting surface 2 and the folded state, and preliminarily laying out the position of the reflector 2 in the folded state;
step seven: determining the length L1 of the reflector 2 from the transfer arm 5 according to the carrying envelope;
step eight: determining a layout mode that if L1+ L20 is far more than 1.1 times of L0, the folded state reflecting surface 2 and the feed source 3 are laid on the same side deck; if L1+ L20 is smaller than 0.9 times of L0, the folded reflecting surface 2 and the feed source 3 are laid on a back-to-back cabin plate, and a back-to-back (U-shaped) layout mode is adopted; if the L1+ L20 is 0.9-1.1 times of the L0, determining in two ways according to the states of an actual feed source array, a star, weight and the like; as shown in fig. 3;
step nine: establishing a rotating shaft A which is perpendicular to the reflecting surface in the unfolded state and passes through the center of the reflecting surface;
step ten: rotating the reflecting surface by the angle theta around the axis A to enable the intersection line of the Xaza surface and the star surface to be positioned in the unfolding placeable area, as shown in FIG. 4;
step eleven: the position of the deployment hinge at the root of the deployment arm 4 is determined. If the reflecting surface 2 and the feed source array 3 are arranged on the same side of the cabin plate, the position of the root hinge is determined according to the actual length of the unfolding arm 4. The intersection of the Xaza surface and the star surface is a line, and the position of the unfolding hinge at the root part of the unfolding arm 4 can be determined according to the isosceles triangle principle (the unfolding arm is fixed in length), as shown in FIG. 5; if the reflecting surface 2 and the feed source 3 are arranged on back-to-back cabin plates and the Xaza surface intersects with the surface of the star body, the mounting position of the hinge at the root part of the unfolding arm 4 is shown in FIG. 6;
step twelve: according to the unfolding hinge position of the root part of the unfolding arm 4, the unfolding position and the folding position are combined, the sum of the length L2 of the arm tube of the unfolding arm and the reflecting surface L1 is optimized to be minimum (the weight is lightest, the weight is favorably reduced, the fundamental frequency of unfolding is favorably used), and the length and the unfolding angle of the arm tube of the unfolding arm 4 can be obtained;
step thirteen: determining the final position of the reflecting surface according to the position of the hinge at the root of the unfolding arm 4, the length of the unfolding arm 4 and the joint angle of the unfolding arm 4;
fourteen steps: determining the position of a feed source according to the final position of the reflecting surface;
step fifteen: checking the antenna view field and rechecking the electrical design performance;
sixthly, the steps are as follows: the manner of deployment of the reflecting surface and the deployment arm of the antenna is determined.
According to the different layout modes of the satellite-borne deployable antenna on the satellite, the deployment modes of the reflecting surface 2 are divided into the following two modes:
a) the reflecting surface 2 and the feed source array 3 are arranged on the same side of the cabin board, and the spreading mode is shown in fig. 7.
The folded reflector 2 and the feed source array 3 are arranged on a cabin plate on the same side of a satellite star body, the reflecting surface 2 firstly expands around a joint A at the root part of the expansion arm 4, then rotates around a joint B of the rotation arm 4 to a position shown in (3) in a figure 7, and then expands around a joint B of the rotation arm 5, and finally the reflecting surface 2 expands.
b) The reflecting surface 2 and the feed source array 3 are arranged in a back-to-back manner, and the spreading manner is as shown in fig. 8.
The folded reflector 2 and the feed source array 3 are arranged on a satellite body in a back-to-back mode, firstly the reflecting surface 2 sequentially expands around an arm shoulder joint B of an expansion arm 4 and a root joint A of the expansion arm 4, a secondary reflecting surface rotates around a shoulder joint B of the expansion arm 4 to a position shown in (5) in a figure 8, then the secondary reflecting surface 2 expands around a joint C of a transfer arm 5, and finally the reflecting surface 2 expands.
Those skilled in the art will appreciate that those matters not described in detail in the present specification are well known in the art.
Although the present invention has been described with reference to the preferred embodiments, it is not intended to limit the present invention, and those skilled in the art can make variations and modifications of the present invention without departing from the spirit and scope of the present invention by using the methods and technical contents disclosed above.
Claims (7)
1. A whole-satellite layout and expansion design method for a satellite-borne long-focus large-aperture antenna is characterized by comprising the following steps:
s1, measuring the distance L0 between the reflecting surface (2) and the star body (1), and measuring the length L20 of an allowable arm pipe of the single-cabin plate surface of the star body (1);
s2, determining the length L1 of a switching arm of the reflecting surface (2) according to the carrying envelope, and determining the position relation of the layout of the reflecting surface (2) and the feed source array (3); determining the unfolding area of the reflecting surface (2), and determining the position of an unfolding hinge at the root of the unfolding arm (4) according to the unfolding area;
s3, determining the arm tube length L2 of the unfolding arm, the length L1 of the connecting arm, the total length of the unfolding arm (4) and the unfolding angle according to the distance L0 in S1, the position of the unfolding hinge in the arm tube length L20 and S2;
s4, determining the final position of the reflecting surface (2) according to the position of the unfolding hinge in S2, the total length of the unfolding arm (4) in S2 and the unfolding angle, and then determining the final position of the feed array (3);
if the sum of the length L1 of the transfer arm and the length L20 of the arm tube is more than 1.1 times of L0, the reflecting surface (2) in the folded state and the feed source array (3) are arranged on the same side cabin plate of the star body; if the sum of the length L1 of the transfer arm and the length L20 of the arm tube is less than 0.9 times of L0, the reflecting surface (2) and the feed source array (3) in the folded state are distributed on the star body in a U-shaped layout, namely the reflecting surface (2) and the feed source array (3) in the folded state are distributed on two side deck plates opposite to the star body; otherwise, the same side cabin board layout or U-shaped layout is selected according to the states of the actual feed source array, the star, the weight and the like.
2. The whole satellite layout and expansion design method of the satellite-borne tele large-aperture antenna according to claim 1, wherein the expansion aperture of the reflecting surface (2) is larger than 12 meters.
3. The whole star layout and expansion design method of the spaceborne tele large-aperture antenna as claimed in claim 1, wherein the focal length of the reflecting surface (2) is larger than 5 m.
4. The on-board tele large-aperture antenna whole-satellite layout and deployment design method of claim 1, wherein the method for determining the value of the arm tube length L2 and the value of the transfer arm length L1 in S3 is as follows: the sum of the arm tube length L2 and the adapter arm length L1 is minimized.
5. The whole satellite layout and expansion design method of the satellite-borne tele large-aperture antenna as claimed in claim 1, wherein after S4, the antenna is inspected for field of view.
6. The whole satellite layout and expansion design method of the satellite-borne tele large-aperture antenna as claimed in claim 1, wherein between S1, a model of a preliminary reflecting surface (2) expansion state and a whole satellite is established with reference to an antenna coordinate system, and then the antenna coordinate system is translated with reference to the satellite coordinate system to determine an initial position relationship of the antenna coordinate system relative to the satellite coordinate system; for determining the spread area of the reflecting surface (2).
7. A computer-readable storage medium, on which a computer program is stored, characterized in that the steps of the method as claimed in claim 1 are implemented when the computer program is executed by a processor.
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| CN111591468B (en) * | 2020-05-06 | 2022-06-28 | 哈尔滨工业大学 | System and method for optimizing performance of spacecraft deployment mechanism |
| CN111653858B (en) * | 2020-05-27 | 2021-07-23 | 上海卫星工程研究所 | Satellite large-caliber deployable antenna positioning and mounting method |
| CN111697312B (en) * | 2020-06-22 | 2022-03-01 | 上海航天测控通信研究所 | Satellite-borne movable reflector antenna and compacting and manufacturing method |
| CN112407332A (en) * | 2020-09-29 | 2021-02-26 | 北京空间飞行器总体设计部 | U-shaped satellite-borne unfolding arm and unfolding method |
| CN112531319B (en) * | 2020-11-30 | 2021-09-21 | 西北工业大学 | Construction method of multisection expansion arm of satellite-borne mesh antenna |
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| JPS60233905A (en) * | 1984-05-04 | 1985-11-20 | Dx Antenna Co Ltd | Antenna system |
| KR20020032253A (en) * | 2000-10-26 | 2002-05-03 | 권태인 | Satellite antenna installed using astronomical object and its installation method |
| CN104183904B (en) * | 2014-09-01 | 2016-07-06 | 大连理工大学 | A kind of method for designing of deployable satellite antenna multi-joint directing mechanism space layout |
| CN104701630B (en) * | 2015-03-14 | 2017-06-16 | 西安电子科技大学 | Annulated column cable net structure varifocal reflecting surface device |
| CN109088149A (en) * | 2018-07-25 | 2018-12-25 | 中国空间技术研究院 | A kind of large-scale antenna systems fold dress star method |
| CN109818151B (en) * | 2019-02-19 | 2021-05-21 | 上海卫星工程研究所 | Satellite-borne deployable mesh antenna |
| CN109931917B (en) * | 2019-03-01 | 2021-07-13 | 中国空间技术研究院 | Pointing accuracy calculation method of satellite-borne deployable antenna system |
| CN110015444A (en) * | 2019-03-29 | 2019-07-16 | 上海卫星工程研究所 | Middle zero dip composition aperture radar satellite configuration of high orbit |
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