CN113013633B - Conformal design method for large-caliber reflector antenna with pointing mechanism - Google Patents
Conformal design method for large-caliber reflector antenna with pointing mechanism Download PDFInfo
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q15/00—Devices for reflection, refraction, diffraction or polarisation of waves radiated from an antenna, e.g. quasi-optical devices
- H01Q15/14—Reflecting surfaces; Equivalent structures
- H01Q15/16—Reflecting surfaces; Equivalent structures curved in two dimensions, e.g. paraboloidal
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- 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
- H01Q19/12—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 wherein the surfaces are concave
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Abstract
The invention provides a conformal design method of a large-caliber reflector antenna with a pointing mechanism, which comprises the following steps: s1: designing a large-caliber reflector antenna with a pointing mechanism; s2: according to the structural characteristics of the reflector antenna, the satellite structure is subjected to adaptive reconstruction; s3: modeling the reflector antenna to obtain an antenna structure model, carrying out single-level mechanical simulation analysis on the antenna structure module, and checking the antenna structure model; s4: the antenna structure model participates in satellite system level mechanical simulation analysis, and mechanical response conditions of the reflector antenna are analyzed; confirming that the reflector antenna and the satellite whole satellite structure can meet the requirement of a satellite mechanical environment; s5: aiming at the reflector antenna, carrying out antenna installation process design and whole-star state antenna test scheme design after the antenna is provided with a star; s6: the reflector antenna participates in a satellite mechanical test, and the reflector antenna is confirmed to meet the requirement of a satellite system mechanical test environment.
Description
Technical Field
The invention relates to the technical field of antennas for satellites, in particular to a conformal design method of a large-caliber reflector antenna with a pointing mechanism.
Background
In some experimental satellite engineering, a high-gain large-caliber reflector antenna with a pointing mechanism needs to be developed to meet the requirement of satellite to ground pointing communication. According to the index requirement, the antenna has the design aperture of 2.5m, the working frequency is X frequency band, the antenna aperture is large, the gain is high, and the capability of scanning and pointing to the earth in a large range is required during the in-orbit period. The overall design size of the antenna (including the pointing mechanism) is approximately Φ 2.5m by 1.16 m.
The side face of the whole satellite of the model is of a 6-face structure, the maximum width of a single face is 2.3m, and the maximum allowable enveloping diameter of overlooking is 4.5 m. According to the normal design requirement, the surface of the satellite only has a fan-shaped surface installation space with the width of about 2.5m and the maximum center height of about 0.5m, and the antenna designed by the conventional design method can be normally installed on the surface of the existing satellite and seriously exceed the envelope range of the satellite, so that the task requirement cannot be met.
At present, the known large-aperture reflector antenna with the pointing mechanism for the satellite directly starts from the design of a satellite structure body during development, and a sufficient installation platform is reserved to meet the installation envelope requirement of the large-aperture antenna. Some types of satellites are limited by the design of the overall satellite configuration, and a standard mounting platform cannot be provided for mounting a large-aperture antenna according to the conventional method. If the aperture of the antenna is reduced, the communication requirement cannot be met.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a conformal design method for a large-caliber reflector antenna with a pointing mechanism. The technical scheme of the invention is as follows:
a conformal design method of a large-caliber reflector antenna with a pointing mechanism comprises the following design steps:
s1: designing a large-caliber reflector antenna with a pointing mechanism;
s2: according to the structural characteristics of the reflector antenna designed in the step S1, the satellite structure is adaptively modified;
s3: modeling the reflector antenna designed in the step S1 to obtain an antenna structure model, carrying out single-level mechanical simulation analysis on the antenna structure module, and checking the antenna structure model;
s4: the antenna structure model participates in satellite system level mechanical simulation analysis, and mechanical response conditions of the reflector antenna are analyzed; confirming that the reflector antenna and the satellite whole satellite structure can meet the requirement of a satellite mechanical environment;
s5: aiming at the reflector antenna, carrying out antenna installation process design and whole-star state antenna test scheme design after the antenna is provided with a star;
s6: the reflector antenna participates in a satellite mechanical test, and the reflector antenna is confirmed to meet the requirement of a satellite system mechanical test environment.
Optionally, in step S2, the method further includes:
and embedding and installing the large-caliber reflector antenna with the pointing mechanism in a satellite, wherein the maximum envelope of the installed antenna does not exceed the maximum allowable envelope range of the satellite.
Optionally, in step S4, the "analyzing the mechanical response condition of the reflector antenna" includes at least: and analyzing the mechanical response conditions of the reflecting surface, the feed source and the pointing mechanism of the reflecting surface antenna.
Optionally, the step S2 further includes: and removing the original satellite deck, and providing antenna mounting point fixing positions in multiple dimensions according to the requirements of the reflecting surface antenna mounting point.
Optionally, the step S3 further includes: and (4) aiming at the structural design model of the reflector antenna designed in the step (S1), establishing a finite element simulation model, carrying out antenna modal and mechanical response analysis, and verifying the structural strength adaptability of the reflector antenna.
Optionally, the step S4, further includes: the antenna structure model participates in the mechanical simulation analysis of the satellite system, and the antenna structure model of the reflector antenna is provided for the satellite system for the mechanical simulation analysis of the satellite system, so that the mechanical response condition of the reflector antenna can be obtained; and confirming that the reflector antenna and the satellite whole satellite structure can meet the requirement of a satellite mechanical environment.
Optionally, in step S5, when the antenna installation process design is performed, according to the requirement of the installation fixing position of the reflector antenna, an operation process hole and a satellite deck reserved operation process hole may be opened on the reflector of the antenna for installation and use of the reflector antenna; the operation process hole on the reflecting surface can be used as an air discharge channel at the same time, and the influence of gas accumulation is prevented.
Optionally, the step S6 further includes: the reflector antenna participates in a satellite mechanical test, the real mechanical response condition of the antenna on the satellite is verified when the reflector antenna is installed on a satellite system for the mechanical test, and the structural strength of the reflector antenna is verified to meet the requirement of the satellite system on the use environment.
Compared with the prior art, the invention has the following beneficial effects:
when the design of the large-caliber reflector antenna with the pointing mechanism is developed, the cooperative design of a stand-alone and a satellite system is developed from an initial design stage, the antenna design is combined with the structural design of the satellite system, and the conformal design is developed. According to the curved surface characteristics of the parabolic reflector antenna, the maximum allowable envelope range of the satellite is fully utilized. The antenna is embedded in the satellite whole satellite structure, and the structural design target of the antenna and the satellite system is met. When the large-aperture reflector antenna is used in an orbit, the large-aperture reflector antenna extends out of the conformal surface of the satellite by virtue of the pointing mechanism embedded in the satellite and far away from the satellite body, and the large-aperture reflector antenna has large-angle pointing tracking capability. The design method fully utilizes the limited satellite space resources and realizes the design target of the antenna.
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 flowchart of a conformal design method of a large-aperture reflector antenna with a pointing mechanism according to an embodiment of the present invention;
fig. 2 is a schematic structural diagram of the large-aperture reflector antenna with a pointing mechanism according to an embodiment of the present invention;
fig. 3 is a schematic view of a conformal design and installation state of the large-aperture reflector antenna with the pointing mechanism on a satellite according to an embodiment of the present invention.
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.
As shown in fig. 1 to fig. 3, the present embodiment discloses a conformal design method for a large-aperture reflector antenna with a pointing mechanism, which includes the following steps:
s1: designing a large-caliber reflector antenna with a pointing mechanism; the reflector antenna at least comprises a pointing mechanism, a reflector and a feed source. Wherein, the reflecting surface is a large-caliber reflecting surface.
The feed source refers to a continuous caliber antenna or a primary radiator of an antenna array.
The reflecting surface is a conductive curved surface or plane used for intensively reflecting the electromagnetic waves emitted by the feed source to a certain direction according to a certain requirement in the planar antenna so as to enhance the emission effect.
The pointing mechanism is an actuating mechanism for tracking and positioning the ground station by the large-caliber reflecting surface antenna.
S2: according to the structural characteristics of the reflector antenna designed in the step S1, the satellite structure is adaptively modified; embedding and installing the large-caliber reflector antenna with the pointing mechanism in a satellite, wherein the maximum envelope of the installed antenna does not exceed the maximum allowable envelope range of the satellite;
s3: modeling the reflector antenna designed in the step S1 to obtain an antenna structure model, carrying out single-level mechanical simulation analysis on the antenna structure model, and checking the antenna structure model; here, "single-machine-level mechanical simulation analysis" refers to performing modal analysis and vibrational mechanical response analysis on a single-machine structural model.
"checking the antenna structure model" further comprises: and calculating the antenna modal result, the vibration response magnitude and the structural stress. Each calculation result needs to meet the technical index requirement (the technical index requirement is determined by a specific use scene during specific implementation), and the requirement of the strength safety extreme value of the material used by the antenna cannot be exceeded.
S4: the antenna structure model participates in the satellite system level mechanical simulation analysis, and the mechanical response conditions of main components such as a pointing mechanism, a reflecting surface and a feed source of the reflecting surface antenna are analyzed; confirming that the reflector antenna and the satellite whole satellite structure can meet the requirement of a satellite mechanical environment; the satellite system-level mechanical simulation analysis is vibration mechanical response analysis for satellite system structure modeling.
It should be noted that "confirming that the reflector antenna and the satellite whole satellite structure can meet the requirement of the satellite mechanical environment" means: and evaluating a calculation result through simulation calculation to see whether the data meet the requirements, and concluding that the task requirements are ensured to be met. This method is common knowledge in the art and will not be described in detail herein.
S5: aiming at the reflector antenna, carrying out antenna installation process design and whole-star state antenna test scheme design after the antenna is provided with a star; because the reflector antenna is embedded in the satellite system, the antenna star-mounting process and the test scheme of the antenna after star mounting in the whole satellite state need to be designed in a targeted manner so as to meet the requirements of assembling, testing and testing the reflector antenna on the satellite system.
S6: the reflector antenna participates in a satellite mechanical test, and the reflector antenna is confirmed to meet the requirement of a satellite system mechanical test environment.
Wherein the step S1 further includes:
firstly, according to the technical index requirements of the antenna for high gain and large caliber and needing to have a two-dimensional pointing function, the electrical property design of the antenna is developed, and the structural design of the large-caliber reflector antenna with the pointing mechanism is developed. The antenna is designed with a caliber of 2.5m, and the antenna is required to have the capability of wide-range scanning pointing to the earth communication during the orbit. The overall design size of the antenna (including the pointing mechanism) is approximately Φ 2.5m by 1.16 m.
Antenna mechanisms and the like are designed to fit the arc of the reflecting surface. And the space occupied by the antenna in a folded state is saved under the condition of meeting the on-orbit use requirement.
The outline structure of the reflector antenna in a folded state is shown in fig. 2. The size of the antenna body is 2.5m by 0.8m, and the diameter of the reflecting surface of the antenna is 2.5 m; the pointing mechanism comprises a stretching mechanism 1, a supporting arm 2 with the length of 1m and a two-dimensional mechanism 3, and the two-dimensional mechanism and the supporting arm are both attached to the reflecting surface in an arc design, so that occupied space resources are reduced. The overall size of the reflector antenna is 2.5m by 1.16 m. The extension mechanism 1 and the two-dimensional mechanism 3 are both arranged on the supporting arm 2. The antenna is characterized in that 6 pressing points are arranged on the reflecting surface corresponding to the antenna, as shown in figure 2, wherein the pressing points 1 are fixed on the extension mechanism 1, the pressing points 2 are fixed on the two-dimensional mechanism, and the rest pressing points 3-6 are symmetrically distributed on the reflecting surface. From the perspective of fig. 2, the pressing points 3 and 4 are symmetrical front to back, the pressing points 5 and 6 are symmetrical front to back, the pressing points 3 and 5 are symmetrical left to right, and the pressing points 4 and 6 are symmetrical left to right.
Wherein the step S2 further includes: and removing the original satellite deck, and providing antenna mounting point fixing positions in multiple dimensions according to the requirements of the reflecting surface antenna mounting point.
Specifically, according to the structural characteristics of the large-caliber reflector antenna with the pointing mechanism, the satellite structure is adaptively transformed: the cabin plate is concave corresponding to the satellite mounting position, an antenna mounting space is provided, and the antenna mounting positions on multiple dimensions are provided by adopting multipoint dispersion constraint fixation. The mounting points are shown as compression points 1-6 in FIG. 2.
The installation state of the antenna on the satellite aims at that the mechanism and the cambered surface structure of the main reflecting surface are all installed on the concave part of the satellite, the outer envelope meets the requirement, and the surface achieves the conformal design goal. The schematic diagram of the reflector antenna after installation is shown in fig. 3. An antenna with the external dimension of 2.5m by 1.16m is embedded into the allowable envelope range of a satellite system with the diameter of 4.5 m.
Wherein the step S3 further includes: and (4) aiming at the structural design model of the reflector antenna designed in the step (S1), establishing a finite element simulation model, namely an antenna structure model, carrying out antenna modal and mechanical response analysis, and verifying the structural strength adaptability of the reflector antenna.
Specifically, through single-level mechanical simulation analysis of the antenna, the current antenna structure is ensured to have strong vibration and impact resistance.
Wherein, the step S4 further includes: the antenna model participates in the satellite system-level mechanical simulation analysis, and a finite element simulation model of the reflector antenna, namely an antenna structure model, is provided for a satellite system to perform the system mechanical simulation analysis, so that the mechanical response conditions of main structural components such as a pointing mechanism, a reflector and a feed source of the reflector antenna can be obtained; and confirming that the reflector antenna and the satellite whole satellite structure can meet the requirement of a satellite mechanical environment. And carrying out local optimization or structural reinforcement on the structure with part of indexes critical or potential strength hazards.
In step S5, when the antenna installation process design is performed, according to the requirement of the installation fixing position of the reverse-side antenna, an operation process hole and a satellite deck reserved operation process hole may be opened on the reflection surface of the antenna for installation and use of the reflection-side antenna; the operation process hole on the reflecting surface can be used as an air discharge channel at the same time, and the influence of gas accumulation is prevented.
Specifically, when the antenna installation process design is carried out, 2 operation process holes with the diameter of 50mm are formed in the corresponding positions of the antenna reflecting surface according to the installation and fixation requirements of 2 initiating explosive devices compression points on the two-dimensional mechanism and the supporting arm on the antenna, and the operation process holes are used for installing and fixing the initiating explosive devices in the compression state. The difficult problem that the operation cannot be realized because the device is invisible at other positions is solved.
Specifically, in step S5, an antenna installation process and a test scheme design need to be comprehensively developed, so as to meet the requirements of satellite loading and on-satellite testing of the large-aperture reflector conformal antenna product with the pointing mechanism and the on-orbit antenna unfolding tracking pointing communication function.
Wherein the step S6 further includes: the reflector antenna participates in a satellite mechanical test, the real mechanical response condition of the antenna on the satellite is verified when the reflector antenna is installed on a satellite system for the mechanical test, and the structural strength of the reflector antenna is verified to meet the requirement of the satellite system on the use environment.
Satellite mechanics testing is a routine test in the art and is not further developed here.
Specifically, after the product of the large-aperture reflector antenna with the pointing mechanism is delivered, the product participates in a satellite mechanical test, the position response of the antenna mounting point and the response condition of each main component in the product are observed, and the antenna and the satellite system structure are evaluated and confirmed to meet the environmental requirements of the satellite mechanical test.
By adopting the embodiment of the invention, the 2.5m large-caliber reflector antenna with the pointing mechanism is embedded in the satellite whole satellite structure, and the structural design target of the antenna and the satellite system is met. When the large-aperture reflector antenna is used in an orbit, the large-aperture reflector antenna extends out of the conformal surface of the satellite by virtue of the pointing mechanism embedded in the satellite and far away from the satellite body, and the large-aperture reflector antenna has large-angle pointing tracking capability. The design method fully utilizes the limited satellite space resources and realizes the design target of the antenna.
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 (7)
1. A conformal design method of a large-aperture reflector antenna with a pointing mechanism is characterized by comprising the following steps:
s1: designing a large-caliber reflector antenna with a pointing mechanism; the reflector antenna at least comprises a pointing mechanism, a reflector and a feed source; the pointing mechanism comprises a stretching mechanism, a supporting arm and a two-dimensional mechanism, the stretching mechanism, the supporting arm and the two-dimensional mechanism are all designed to be attached to the reflecting surface arc line, and the stretching mechanism and the two-dimensional mechanism are both arranged on the supporting arm; the stretching mechanism, the two-dimensional mechanism and the reflecting surface are distributed with pressing points;
s2: according to the structural characteristics of the reflector antenna designed in the step S1, the satellite structure is adaptively modified;
removing the original satellite deck, and providing antenna mounting point fixing positions in multiple dimensions according to the requirements of the reflecting surface antenna mounting point; providing an antenna mounting space corresponding to the inward recess of the cabin plate at the satellite mounting position, and providing antenna mounting positions on multiple dimensions by adopting multipoint dispersion constraint fixation; the mounting state of the antenna on the satellite aims at that the mechanism and the cambered surface structure of the main reflecting surface are all mounted on the concave part of the satellite, the outer envelope meets the requirement, and the surface realizes the conformal design target;
s3: modeling the reflector antenna designed in the step S1 to obtain an antenna structure model, carrying out single-level mechanical simulation analysis on the antenna structure module, and checking the antenna structure model;
s4: the antenna structure model participates in satellite system level mechanical simulation analysis, and mechanical response conditions of the reflector antenna are analyzed; confirming that the reflector antenna and the satellite whole satellite structure can meet the requirement of a satellite mechanical environment;
s5: aiming at the reflector antenna, carrying out antenna installation process design and whole-star state antenna test scheme design after the antenna is provided with a star;
s6: the reflector antenna participates in a satellite mechanical test, and the reflector antenna is confirmed to meet the requirement of a satellite system mechanical test environment.
2. The method of claim 1, wherein step S2 further comprises:
and embedding and installing the large-caliber reflector antenna with the pointing mechanism in a satellite, wherein the maximum envelope of the installed antenna does not exceed the maximum allowable envelope range of the satellite.
3. The method according to claim 1, wherein the step S4 of analyzing the mechanical response of the reflector antenna at least comprises: and analyzing the mechanical response conditions of the reflecting surface, the feed source and the pointing mechanism of the reflecting surface antenna.
4. The method of claim 1, wherein the step S3 further comprises: and (4) aiming at the structural design model of the reflector antenna designed in the step (S1), establishing a finite element simulation model, carrying out antenna modal and mechanical response analysis, and verifying the structural strength adaptability of the reflector antenna.
5. The method of claim 1, wherein the step S4, further comprises: the antenna structure model participates in the mechanical simulation analysis of the satellite system, and the antenna structure model of the reflector antenna is provided for the satellite system for the mechanical simulation analysis of the satellite system, so that the mechanical response condition of the reflector antenna can be obtained; and confirming that the reflector antenna and the satellite whole satellite structure can meet the requirement of a satellite mechanical environment.
6. The method according to claim 1, wherein in step S5, when the antenna installation process design is carried out, according to the requirement of the installation and fixing position of the reflector antenna, an operation process hole and a satellite deck reserved operation process hole can be opened on the reflector of the antenna for installation and use of the reflector antenna; the operation process hole on the reflecting surface can be used as an air discharge channel at the same time, and the influence of gas accumulation is prevented.
7. The method of claim 1, wherein the step S6 further comprises: the reflector antenna participates in a satellite mechanical test, the real mechanical response condition of the antenna on the satellite is verified when the reflector antenna is installed on a satellite system for the mechanical test, and the structural strength of the reflector antenna is verified to meet the requirement of the satellite system on the use environment.
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