CN113381203A - Large-scale satellite-borne phased array radar antenna subarray area integration method and device - Google Patents
Large-scale satellite-borne phased array radar antenna subarray area integration method and device Download PDFInfo
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- CN113381203A CN113381203A CN202110543419.1A CN202110543419A CN113381203A CN 113381203 A CN113381203 A CN 113381203A CN 202110543419 A CN202110543419 A CN 202110543419A CN 113381203 A CN113381203 A CN 113381203A
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q21/00—Antenna arrays or systems
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/12—Supports; Mounting means
- H01Q1/22—Supports; Mounting means by structural association with other equipment or articles
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- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q3/00—Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system
- H01Q3/26—Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system varying the relative phase or relative amplitude of energisation between two or more active radiating elements; varying the distribution of energy across a radiating aperture
- H01Q3/30—Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system varying the relative phase or relative amplitude of energisation between two or more active radiating elements; varying the distribution of energy across a radiating aperture varying the relative phase between the radiating elements of an array
- H01Q3/34—Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system varying the relative phase or relative amplitude of energisation between two or more active radiating elements; varying the distribution of energy across a radiating aperture varying the relative phase between the radiating elements of an array by electrical means
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Abstract
The invention discloses a large-scale satellite-borne phased array radar antenna subarray integration method and a device thereof, relating to the technical field of satellite-borne phased array radar antenna integration, comprising a general support base, a subarray connection frame, a switching frame and a connecting seat, wherein the subarray connection frame is connected with the general support base through the switching frame, can freely rotate around the central axis of a rotating shaft of the switching frame and is locked and fixed at the positions of 0 degree, 90 degrees, 180 degrees and 270 degrees with the ground, an antenna subarray carbon fiber frame is fixed with the subarray connection frame into a whole through the connecting seat, can freely rotate around the central axis of the rotating shaft of the switching frame together with the subarray connection frame and is locked and fixed at four positions of 0 degree, 90 degrees, 180 degrees and 270 degrees, thereby realizing the attitude turnover and assembly measurement required by antenna subarray integration, and realizing the bearing fixed array surface, the position and the position of the array surface of the large-scale satellite-borne phased array radar antenna, The attitude overturning, measuring and assembling are integrated, the integration efficiency is improved, and the assembling deformation of the antenna sub array surface is reduced to the maximum extent.
Description
Technical Field
The invention relates to the technical field of satellite-borne phased array radar antenna integration, in particular to a large satellite-borne phased array radar antenna sub-array integration method and device.
Background
The satellite-borne phased array radar antenna is the most important and complex subsystem for determining the performance of a radar satellite, and consists of a plurality of antenna sub-array surfaces, and the folded antenna sub-array surfaces are unfolded through an unfolding mechanism on a spatial orbit, so that a complete radar antenna array surface is formed. With the development of phased array radar antenna technology, the size and the weight of a satellite-borne phased array radar antenna are larger and larger, and the technical index requirements are also continuously improved. The conventional method for integrating the subarray of the satellite-borne phased array radar antenna is based on a working table and a supporting tool, and an operator grips a handle and an antenna frame to turn over the subarray, so that the method is convenient to operate and low in equipment requirement, but is only suitable for small-sized satellite-borne phased array radar antennas with small size and light weight, and cannot meet the requirements of the size (3.5m multiplied by 2.5m) and the weight (250kg) of a large-sized satellite-borne phased array radar antenna subarray. In addition, with the improvement of the technical indexes of the antenna, higher requirements are put on the flatness and pointing accuracy of the antenna sub-array, so that more effective control on deformation in the process of integrating the antenna sub-array is required. Therefore, a novel integration method and device for a large-scale satellite-borne phased array radar antenna sub-array surface are urgently needed to be invented.
Disclosure of Invention
Aiming at the problems in the prior art, the invention aims to provide a method and a device for integrating a large-scale satellite-borne phased array radar antenna subarray, so that the support fixation, the posture overturning and the assembly measurement of the antenna subarray are realized, the integration efficiency is improved, the assembly deformation of the antenna subarray is reduced to the maximum extent, and the integration requirement of the large-scale satellite-borne phased array radar antenna subarray is met.
In order to achieve the purpose, the invention provides the following technical scheme: the specific integration steps of the large-scale satellite-borne phased array radar antenna subarray integration method are as follows:
the method comprises the following steps: adjusting the size of the integrated universal support base of the antenna sub array surface to a proper size, then connecting the sub array surface connecting frame 1 with the universal support base, turning to a 0-degree horizontal position, and locking the sub array surface connecting frame by using a locking pin;
step two: horizontally arranging an antenna sub-array carbon fiber frame into a sub-array connecting frame, completing the support of the antenna sub-array carbon fiber frame through four horizontal fixed connecting seats on the sub-array connecting frame, positioning the antenna sub-array carbon fiber frame through a vertical fixed connecting seat, adjusting the position of an adjustable connecting seat simultaneously to ensure that a connecting surface of the adjustable connecting seat is attached to a mounting surface of the antenna sub-array carbon fiber frame, arranging a threaded mounting hole in the screw-connected antenna sub-array carbon fiber frame, and fixing the antenna sub-array carbon fiber frame and the sub-array connecting frame into a whole;
step three: detaching the locking pin, rotating the sub array surface connecting frame to a 90-degree vertical position, re-installing the locking pin for locking, measuring the planeness of the antenna sub array surface carbon fiber frame, and checking whether the planeness of the antenna sub array surface carbon fiber frame meets the index requirement and whether the deformation trend is consistent with that before assembly;
step four: rotating the sub array surface connecting frame to 0 degree horizontal position and locking by using a locking pin, alternately and sequentially loading two rows of 22 antenna units in the middle along the length direction from the center of the array surface, fastening by using a corresponding fastener, then overturning the sub array surface connecting frame to 180 degree horizontal position and locking by using the locking pin, alternately and sequentially loading two rows of 6 active integrated modules in the middle along the length direction from the center of the array surface, and connecting the antenna units with cable assemblies and thermal control cables of the active integrated modules;
step five: rotating the sub array surface connecting frame to a 180-degree horizontal position again and locking the sub array surface connecting frame by using a locking pin, alternately and sequentially loading the remaining two rows of 22 antenna units in the length direction from the center of the array surface, fastening the antenna units by using corresponding fasteners, turning over the sub array surface connecting frame to the 180-degree horizontal position and locking the sub array surface connecting frame by using the locking pin, alternately and sequentially loading the remaining two rows of 6 active integrated modules in the length direction from the center of the array surface, and connecting the antenna units with cable assemblies and thermal control cables of the active integrated modules;
step six: and respectively rotating the sub-array connecting frame to 90-degree and 270-degree vertical positions and locking by using a locking pin to complete the installation of other single machines such as high-low frequency cable assemblies, thermal control systems and the like.
The invention provides the following technical scheme: the utility model provides a large-scale satellite-borne phased array radar antenna subarray integrated device includes general support base, subarray face linking frame and switching frame, subarray face linking frame passes through the switching frame to be connected with general support base, and antenna subarray face carbon fiber frame is fixed as an organic whole through perpendicular fixed connection seat and horizontal fixed connection seat and subarray face linking frame simultaneously to realize that antenna subarray is integrated required gesture upset and assembly measurement.
As a further scheme of the invention: the left end and the right end of the sub array surface connecting frame are connected with the universal supporting base through the adapter rack, the sub array surface connecting frame can rotate freely around the center of a rotating shaft of the adapter rack, so that the sub array surface connecting frame is locked and fixed at positions which are 0 degree, 90 degree, 180 degree and 270 degree with the ground, meanwhile, the sub array surface carbon fiber frame is fixed with the sub array surface connecting frame into a whole through the connecting seat, the sub array surface carbon fiber frame can rotate freely around the central axis of the rotating shaft of the adapter rack together with the sub array surface connecting frame, and the sub array surface carbon fiber frame is locked and fixed at four positions of 0 degree, 90 degree, 180 degree and 270 degree.
As a further scheme of the invention: sixteen adjustable connecting seats and ten fixed connecting seats are arranged on the sub array surface connecting frame, the number of the adjustable connecting seats is five on the left and right, the number of the adjustable connecting seats is three on the front and back, the fixed connecting seats are divided into four vertical fixed connecting seats and two horizontal fixed connecting seats, the number of the horizontal fixed connecting seats is four, the number of the horizontal fixed connecting seats is two on the left and right, and the number of the vertical fixed connecting seats is six, and the number of the vertical fixed connecting seats is three on the front and back.
As a further scheme of the invention: the universal supporting base comprises a supporting base connecting seat, a base supporting frame, a base supporting plate, a base right cross beam and a base left cross beam, wherein the base right cross beam and the base left cross beam are respectively provided with two base right cross beams, the base right cross beam is slidably mounted in the base left cross beam, meanwhile, the end parts of the two base right cross beams and the two base left cross beams, which deviate from each other, are fixedly mounted on the side wall of the supporting base connecting seat, the top of the supporting base connecting seat is fixedly provided with the base supporting frame, a plurality of groups of threaded holes are formed in the side wall, which is close to each other, of the two base supporting frames, the base supporting plate is mounted in the threaded holes, and the base supporting plate is connected with a switching frame through a locking pin.
As a further scheme of the invention: a plurality of through holes are formed in the top wall of the base left cross beam of the base right cross beam, a rectangular reinforcing plate is installed on bolts in the through holes, and meanwhile, the bottom of the base connecting seat is fixedly provided with universal wheels which are selected and used as wheels with a self-locking function.
As a further scheme of the invention: the side walls of the pair of base supporting plates, which deviate from each other, are fixedly provided with inclined supporting plates, and the other ends of the inclined supporting plates are fixedly arranged on the top wall of the base supporting frame.
As a further scheme of the invention: the inner chamber has been seted up to the inside of base left side crossbeam, and wherein the height of inner chamber is the same with the height of base right side crossbeam, including intracavity, base right side crossbeam slidable mounting has the rack on the wall of the left and right sides of base right side crossbeam simultaneously to the left and right sides of inner chamber is provided with a pair of gear, and wherein gear and rack toothing are in the same place, and fixed mounting has the pivot in the gear simultaneously, and the roof of base left side crossbeam is stretched out from at the top of pivot, and the end that stretches out of pivot links together with drive mechanism.
As a further scheme of the invention: the through-hole has been seted up to the inside of base right side crossbeam, and slidable mounting has the telescopic link in the through-hole, and the both ends of telescopic link are fixed mounting respectively on the lateral wall that supports the base connecting seat.
As a still further scheme of the invention: the transmission mechanism comprises a motor and a transmission rod, the motor is fixedly installed on the top wall of the left cross beam of the base, a first bevel gear is fixedly installed on an output shaft of the motor, a second bevel gear is meshed at the left end and the right end of the first bevel gear, the second bevel gear is fixedly installed on the transmission rod, a third bevel gear is fixedly installed at the other end of the transmission rod, a fourth bevel gear is meshed on the outer wall of the third bevel gear, and the fourth bevel gear is fixedly installed on the top wall of the rotating shaft.
Compared with the prior art, the invention has the beneficial effects that: compared with the prior art, the invention has the following remarkable advantages: the supporting fixation, posture overturning, measurement and assembly integration of the sub array surface of the large-scale satellite-borne phased array radar antenna with the width of 2.5m multiplied by 3.5m can be realized, the integration efficiency is improved, the assembly deformation of the sub array surface of the antenna is reduced to the maximum extent, and the problems of large size and weight, high requirements on flatness and pointing accuracy and low integration efficiency of the sub array surface of the large-scale satellite-borne phased array radar antenna are solved.
Drawings
Fig. 1 is a side view of the present invention.
Fig. 2 is a top view of the present invention.
FIG. 3 is a front view of the universal support base of the present invention.
FIG. 4 is a top view of the universal support base of the present invention.
FIG. 5 is a partial view of the right cross member of the base of the present invention.
FIG. 6 is a side view of the left cross beam of the base of the present invention.
Fig. 7 is a schematic view of the transmission mechanism of the present invention.
As shown in the figure: 1. the antenna array surface connecting frame comprises a sub array surface connecting frame, 2, a switching frame, 3, a vertical fixed connecting seat, 4, a horizontal fixed connecting seat, 5, an adjustable connecting seat, 6, an antenna sub array surface carbon fiber frame, 7, a supporting base connecting seat, 8, a base supporting frame, 9, a base supporting plate, 10, a base right cross beam, 11, a base left cross beam, 12, a reinforcing plate, 13, a locking pin, 14, an antenna array surface, 15, an inner cavity, 16, a rack, 17, a gear, 18, a rotating shaft, 19, a transmission mechanism, 20, a through hole, 21, a telescopic rod, 22, a motor, 23, an output shaft, 24, a bevel gear I, 25, a bevel gear II, 26, a transmission rod, 27, a bevel gear III, 28 and a bevel gear IV.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "disposed," "sleeved/connected," "connected," and the like are to be construed broadly, e.g., "connected," which may be fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
The first embodiment is as follows:
it should be noted that, in the embodiment of the present invention, a certain type of sub-array (size 3.5m × 2.5m) of a satellite-borne phased array radar antenna is taken as an example for description, where the antenna array is composed of a carbon fiber frame, antenna units, active integrated modules, high and low frequency cable assemblies, a thermal control system, and the like, where the antenna units (44 blocks in total) are installed on a support on the front side of the carbon fiber frame, the active integrated modules (12 blocks in total) are installed on a support on the back side of the frame, and the remaining components are installed on the active integrated modules and a frame of the carbon fiber frame, and the working principle and the installation manner of the antenna array all adopt the prior art, which is common knowledge of persons in the art, and no further description is given here.
Referring to fig. 1 to 4, the specific integration steps of the method for integrating the sub-array of the large-scale space-borne phased array radar antenna are as follows:
the method comprises the following steps: adjusting the integrated universal supporting base of the antenna sub-array to a proper size, in this embodiment, the length of the universal supporting base is 3864mm, and the height thereof is 1370mm, then the sub-array connecting frame 1 is connected with the universal supporting base, and is turned to a 0-degree horizontal position, and the sub-array connecting frame 1 is locked by a locking pin 13;
step two: horizontally arranging an antenna sub-array carbon fiber frame 6 into a sub-array surface connecting frame 1, completing the support of the antenna sub-array carbon fiber frame 6 through four horizontal fixed connecting seats 4 on the sub-array surface connecting frame 1, positioning the antenna sub-array carbon fiber frame 6 through a vertical fixed connecting seat 3, adjusting the position of an adjustable connecting seat 5 at the same time, enabling a connecting surface of the adjustable connecting seat 5 to be attached to a mounting surface of the antenna sub-array carbon fiber frame 6, installing a threaded mounting hole in the screw-connected antenna sub-array carbon fiber frame 6, and fixing the antenna sub-array carbon fiber frame 6 and the sub-array connecting frame 1 into a whole;
step three: detaching the locking pin 13, rotating the vertical position of the sub array surface connecting frame 1 to 90 degrees, re-installing the locking pin 13 for locking, measuring the planeness of the antenna sub array surface carbon fiber frame 6, checking whether the planeness of the antenna sub array surface carbon fiber frame 6 meets the index requirement and whether the deformation trend is consistent with that before assembly (if necessary, adjusting the adjustable connecting seat 5 until the measurement result meets the requirement, and avoiding the carbon fiber frame from deforming without stress);
step four: rotating the sub array surface connecting frame 1 to 0 degree horizontal position and locking by a locking pin 13, alternately and sequentially loading two rows of 22 antenna units in the middle along the length direction from the center of the array surface, fastening by a corresponding fastener, then overturning the sub array surface connecting frame 1 to 180 degree horizontal position and locking by the locking pin 13, alternately and sequentially loading two rows of 6 active integrated modules in the middle along the length direction from the center of the array surface, and connecting the antenna units with cable assemblies and thermal control cables of the active integrated modules;
step five: rotating the sub array surface connecting frame 1 to 180 degrees of horizontal position again and locking by using a locking pin 13, alternately and sequentially loading the rest two rows of 22 antenna units along the length direction from the center of the array surface, fastening by using corresponding fasteners, then overturning the sub array surface connecting frame 1 to 180 degrees of horizontal position and locking by using the locking pin 13, alternately and sequentially loading the rest two rows of 6 active integrated modules along the length direction from the center of the array surface, and connecting the antenna units with the cable assemblies and the thermal control cables of the active integrated modules;
step six: the sub-array connecting frame is respectively rotated to the vertical positions of 90 degrees and 270 degrees and locked by the locking pin 13, and the installation of other single machines such as high-low frequency cable assemblies, thermal control systems and the like is completed.
The large-scale satellite-borne phased array radar antenna subarray integrated device comprises a general support base, a subarray connection frame 1 and a switching frame 2, wherein the subarray connection frame 1 is connected with the general support base through the switching frame 2, and meanwhile, an antenna subarray carbon fiber frame 6 is fixed into a whole with the subarray connection frame 1 through a vertical fixing connection seat 3 and a horizontal fixing connection seat 4, so that posture overturning and assembly measurement required by antenna subarray integration are achieved.
Wherein, the sub-array connection frame 1 is selected according to the antenna array 14 which is actually needed to be installed, wherein the sub array surface connecting frame 1 is the prior art, so the description is not needed, meanwhile, the left and right ends of the sub array surface connecting frame 1 are connected with the universal supporting base through the switching frame 2, and the sub array surface connecting frame 1 can freely rotate around the center of the rotating shaft of the switching frame 2, thereby leading the subarray connection frame 1 to be locked and fixed at the positions of 0 degree, 90 degrees, 180 degrees and 270 degrees with the ground, meanwhile, the sub-array carbon fiber frame 6 is fixed with the sub-array connecting frame 1 into a whole through the connecting seat, so that the subarray carbon fiber frame 6 and the subarray connection frame 1 can freely rotate around the central axis of the rotating shaft of the adapter frame 2, and the antenna is locked and fixed at four positions of 0 degree, 90 degrees, 180 degrees and 270 degrees, thereby realizing the attitude turning and assembly measurement required by the integration of the antenna sub-array.
Preferably, sixteen adjustable connecting seats 5 and ten fixed connecting seats are arranged on the subarray connecting frame 1, wherein the number of the adjustable connecting seats 5 is five on the left and right, the number of the adjustable connecting seats is three on the front and back, the fixed connecting seats are divided into vertical fixed connecting seats 3 and horizontal fixed seats, the number of the horizontal fixed connecting seats 4 is four, the number of the horizontal fixed connecting seats is two on the left and right, the number of the vertical fixed connecting seats 3 is six, the number of the vertical fixed connecting seats is three on the front and back, the antenna subarray carbon fiber frame 6 is accurately positioned on the subarray connecting frame 1 through the four horizontal fixed connecting seats 4 and the six vertical fixed connecting seats 3, meanwhile, the sixteen adjustable connecting seats 5 are connected with mounting holes of the antenna subarray carbon fiber frame 6, the positions of the adjustable connecting seats 5 can be accurately adjusted, so as to ensure that the connecting faces of the adjustable connecting seats 5 are attached to the mounting faces of the antenna subarray carbon fiber frame 6, and the carbon fiber frame 6 of the antenna sub-array is prevented from being deformed by stress when being connected.
Wherein, the universal supporting base comprises a supporting base connecting seat 7, a base supporting seat 8, a base supporting plate 9, a base right cross beam 10 and a base left cross beam 11, wherein two base right cross beams 10 and two base left cross beams 11 are respectively arranged, the base right cross beam 10 is slidably arranged in the base left cross beam 11, the length of the universal supporting base is filled through the relative sliding of the base right cross beam 10 in the base left cross beam 11, meanwhile, the end parts of the two base right cross beams 10 and the two base left cross beams 11 which are deviated from each other are symmetrically and fixedly arranged on the side wall of the supporting base connecting seat 7, the fixed connection of the supporting base connecting seat 7 on the left side and the right side is completed through the base right cross beam 10 on the base left cross beam 11, the base supporting seat 8 is fixedly arranged on the top of the supporting base connecting seat 7, wherein, a plurality of groups of threaded holes are arranged on the side walls of the two base supporting seats 8 which are close to each other, and threaded hole internal thread installs base support plate 9, and base support plate 9 links together through stop pin 13 and adapter rack 2, comes the adjustment of base support plate 9's height through the bolt fastening position of adjustment base support plate 9, and fixed mounting has the inclined support board on the lateral wall that a pair of base support plate 9 deviates from each other simultaneously, and the other end fixed mounting of inclined support board is on the roof of pedestal bracing frame 8, carries out the auxiliary stay to base support plate 9 through the inclined support board.
Preferably, a plurality of through-holes have been seted up to base right crossbeam 10 on the roof of base left crossbeam 11, and rectangular reinforcing plate 12 is installed to the bolt in the through-hole, links together two crossbeams around through rectangular reinforcing plate 12 to improve the rigidity and the stability of general support base, the bottom fixed mounting who supports base connecting seat 7 simultaneously has the universal wheel, and the universal wheel chooses for use the wheel that has self-locking function, has made things convenient for the removal and the fixing of device.
Example two:
referring to fig. 1 to 7, the main structure of the present embodiment is the same as the first embodiment, except that: considering that when the length of the antenna array face 14 is long, the length of the base right beam 10 remaining in the base left beam 11 in the general supporting base is short, so that the firmness of the general supporting base is greatly reduced, and the joint of the base right beam 10 and the base left beam 11 is easy to break, therefore, the base right beam 10 and the base left beam 11 are improved, and the firmness of the connection of the base right beam 10 and the base left beam 11 is improved.
Wherein, inner chamber 15 has been seted up to the inside of base left side crossbeam 11, wherein the height of inner chamber 15 is the same with the height of base right side crossbeam 10, base right side crossbeam 10 slidable mounting is in inner chamber 15, fixed mounting has rack 16 on the wall of the left and right sides of base right side crossbeam 10 simultaneously, and the left and right sides of inner chamber 15 is provided with a pair of gear 17, wherein gear 17 and rack 16 meshing are in the same place, fixed mounting has pivot 18 in the gear 17 simultaneously, the roof of base left side crossbeam 11 is stretched out from the top of pivot 18, and the end that stretches out of pivot 18 links together with drive mechanism 19, drive pivot 18 through drive mechanism 19 and rotate, drive gear 17 rotates, thereby drive base right side crossbeam 10 through rack 16 and carry out the horizontal motion, realize the length adjustment to general support base.
Preferably, through-hole 20 has been seted up to the inside of base right crossbeam 10, and slidable mounting has telescopic link 21 in the through-hole 20, and fixed mounting is on the lateral wall that supports base connecting seat 7 respectively at the both ends of telescopic link 21, carries out auxiliary stay to base right crossbeam 10 and base left crossbeam 11 through telescopic link 21, has increased the rigidity and the stability of base right crossbeam 10 and base left crossbeam 11, avoids base right crossbeam 10 and base left crossbeam 11 junction to take place cracked phenomenon.
The transmission mechanism 19 comprises a motor 22 and a transmission rod 26, the motor 22 is fixedly installed on the top wall of the left base beam 11, a first bevel gear 24 is fixedly installed on an output shaft 23 of the motor 22, the left end and the right end of the first bevel gear 24 are meshed with a second bevel gear 25, the second bevel gear 25 is fixedly installed on the transmission rod 26, a third bevel gear 27 is fixedly installed at the other end of the transmission rod 26, a fourth bevel gear 28 is meshed with the outer wall of the third bevel gear 27, and the fourth bevel gear 28 is fixedly installed on the top wall of the rotating shaft 18; when the length of the universal supporting base needs to be adjusted, the motor 22 is started to drive the first bevel gear 24 to rotate, the first bevel gear 24 drives the third bevel gear 27 to rotate through the second bevel gear 25, the third bevel gear 27 rotates and simultaneously rotates through the fourth bevel gear 28, so that the rotating shaft 18 is driven to rotate, the gear 17 is driven to rotate along the rack 16, and the extending length of the right beam 10 of the base is adjusted.
Although the present invention has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that various changes in the embodiments and/or modifications of the invention can be made, and equivalents and modifications of some features of the invention without departing from the spirit and scope of the invention.
Claims (10)
1. A sub-array integration method of a large-scale satellite-borne phased array radar antenna is characterized by comprising the following steps: the specific integration steps are as follows:
the method comprises the following steps: adjusting the size of the integrated universal support base of the antenna sub array surface to a proper size, then connecting the sub array surface connection frame (1) with the universal support base, turning to a 0-degree horizontal position, and locking the sub array surface connection frame (1) by using a locking pin (13);
step two: horizontally arranging an antenna sub-array carbon fiber frame (6) into a sub-array surface connecting frame (1), completing the support of the antenna sub-array carbon fiber frame (6) through four horizontal fixed connecting seats (4) on the sub-array surface connecting frame (1), positioning the antenna sub-array carbon fiber frame (6) through a vertical fixed connecting seat (3), adjusting the position of an adjustable connecting seat (5) simultaneously, enabling the connecting surface of the adjustable connecting seat (5) to be attached to the mounting surface of the antenna sub-array carbon fiber frame (6), arranging a threaded mounting hole in the screw connection antenna sub-array carbon fiber frame (6), and fixing the antenna sub-array carbon fiber frame (6) and the sub-array surface connecting frame (1) into a whole;
step three: detaching the locking pin (13), rotating the sub array surface connecting frame (1) to a 90-degree vertical position, re-installing the locking pin (13) for locking, measuring the planeness of the antenna sub array surface carbon fiber frame (6), and checking whether the planeness of the antenna sub array surface carbon fiber frame (6) meets the index requirement and whether the deformation trend is consistent with that before assembly;
step four: rotating the sub array surface connecting frame (1) to a horizontal position of 0 degree and locking the sub array surface connecting frame by using a locking pin (13), alternately and sequentially loading two rows of 22 antenna units in the middle along the length direction from the center of the array surface, fastening the antenna units by using corresponding fasteners, then overturning the sub array surface connecting frame (1) to a horizontal position of 180 degrees and locking the antenna units by using the locking pin (13), alternately and sequentially loading two rows of 6 active integration modules in the middle along the length direction from the center of the array surface, and connecting the antenna units with cable assemblies and thermal control cables of the active integration modules;
step five: rotating the sub array surface connecting frame (1) to a 180-degree horizontal position again and locking the sub array surface connecting frame by using a locking pin (13), alternately and sequentially loading the rest two columns of 22 antenna units in the length direction from the center of the array surface, fastening the antenna units by using corresponding fasteners, then overturning the sub array surface connecting frame (1) to the 180-degree horizontal position and locking the antenna units by using the locking pin (13), and alternately and sequentially loading the rest two columns of 6 active integrated modules in the length direction from the center of the array surface, and connecting the antenna units with cable assemblies and thermal control cables of the active integrated modules;
step six: and respectively rotating the sub-array connecting frame (1) to 90-degree and 270-degree vertical positions and locking by using a locking pin (13) to complete the installation of other high-low frequency cable assemblies, thermal control systems and other single machines.
2. The utility model provides a large-scale spaceborne phased array radar antenna sub-array face integrated device, includes general support base, sub-array face linking frame (1) and adapter rack (2), its characterized in that: the sub-array surface connecting frame (1) is connected with the universal supporting base through the adapter frame (2), and meanwhile, the antenna sub-array surface carbon fiber frame (6) is fixed with the sub-array surface connecting frame (1) into a whole through the vertical fixed connecting seat (3) and the horizontal fixed connecting seat (4), so that posture overturning and assembly measurement required by antenna sub-array surface integration are achieved.
3. The large space-borne phased array radar antenna sub-array integration device according to claim 2, wherein: the left end and the right end of the sub array surface connecting frame (1) are connected with the universal supporting base through the switching frame (2), and meanwhile, the sub array surface carbon fiber frame (6) is fixed with the sub array surface connecting frame (1) into a whole through the connecting seat, so that the sub array surface carbon fiber frame (6) and the sub array surface connecting frame (1) can freely rotate around the central axis of a rotating shaft of the switching frame (2) together, and are locked and fixed at four positions of 0 degree, 90 degrees, 180 degrees and 270 degrees.
4. The large space-borne phased array radar antenna sub-array integration device according to claim 3, wherein: sixteen adjustable connecting seats (5) and ten fixed connecting seats are installed on the sub array face connecting frame (1), the number of the adjustable connecting seats (5) is five about each, the number of the adjustable connecting seats is three in the front and back, the fixed connecting seats are divided into vertical fixed connecting seats (3) and horizontal fixed connecting seats (4) simultaneously, the number of the horizontal fixed connecting seats (4) is four, the number of the horizontal fixed connecting seats is two about each, and the number of the vertical fixed connecting seats (3) is six, and the number of the vertical fixed connecting seats is three in the front and back.
5. The large space-borne phased array radar antenna sub-array integration device according to claim 2, wherein: the universal supporting base comprises a supporting base connecting seat (7), a base supporting frame (8), a base supporting plate (9), a base right cross beam (10) and a base left cross beam (11), wherein the base right cross beam (10) and the base left cross beam (11) are respectively provided with two, the base right cross beam (10) is arranged inside the base left cross beam (11) in a sliding way, meanwhile, the end parts of the two base right cross beams (10) and the two base left cross beams (11) which are deviated from each other are symmetrically and fixedly arranged on the side wall of the supporting base connecting seat (7), and the top of the supporting base connecting seat (7) is fixedly provided with a base supporting frame (8), wherein the side walls of the two base supporting frames (8) which are close to each other are provided with a plurality of groups of threaded holes, and a base support plate (9) is arranged in the threaded hole, and the base support plate (9) is connected with the adapter rack (2) through a locking pin (13).
6. The large space-borne phased array radar antenna sub-array integration device according to claim 5, wherein: a plurality of through holes are formed in the top wall of the base right cross beam (10) on the top wall of the base left cross beam (11), a rectangular reinforcing plate (12) is installed on bolts in the through holes, and meanwhile, the bottom of the base connecting seat (7) is fixedly provided with universal wheels which have a self-locking function.
7. The large space-borne phased array radar antenna sub-array integration device according to claim 5, wherein: the side walls of the pair of base supporting plates (9) which deviate from each other are fixedly provided with inclined supporting plates, and the other ends of the inclined supporting plates are fixedly arranged on the top wall of the base supporting frame (8).
8. The large space-borne phased array radar antenna sub-array integration device according to claim 5, wherein: inner chamber (15) have been seted up to the inside of base left side crossbeam (11), wherein the height of inner chamber (15) is the same with the height of base right side crossbeam (10), base right side crossbeam (10) slidable mounting is in inner chamber (15), fixed mounting has rack (16) on the left and right sides wall of base right side crossbeam (10) simultaneously, and the left and right sides of inner chamber (15) is provided with a pair of gear (17), wherein gear (17) and rack (16) meshing are in the same place, fixed mounting has pivot (18) in gear (17) simultaneously, the roof of base left side crossbeam (11) is stretched out from at the top of pivot (18), and the end that stretches out of pivot (18) links together with drive mechanism (19).
9. The large space-borne phased array radar antenna sub-array integration device according to claim 8, wherein: through-hole (20) have been seted up to the inside of base right beam (10), and slidable mounting has telescopic link (21) in through-hole (20), and the both ends of telescopic link (21) are fixed mounting respectively on the lateral wall that supports base connecting seat (7).
10. The large space-borne phased array radar antenna sub-array integration device according to claim 8, wherein: the transmission mechanism (19) comprises a motor (22) and a transmission rod (26), the motor (22) is fixedly installed on the top wall of the base left cross beam (11), meanwhile, a first bevel gear (24) is fixedly installed on an output shaft (23) of the motor (22), a second bevel gear (25) is meshed at the left end and the right end of the first bevel gear (24), the second bevel gear (25) is fixedly installed on the transmission rod (26), a third bevel gear (27) is fixedly installed at the other end of the transmission rod (26), a fourth bevel gear (28) is meshed on the outer wall of the third bevel gear (27), and the fourth bevel gear (28) is fixedly installed on the top wall of the rotating shaft (18).
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| CN113381203B (en) | 2022-12-09 |
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