CN114671007B - Long-baseline small-deformation array radome truss for three-dimensional imaging radar - Google Patents
Long-baseline small-deformation array radome truss for three-dimensional imaging radar Download PDFInfo
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- CN114671007B CN114671007B CN202210338352.2A CN202210338352A CN114671007B CN 114671007 B CN114671007 B CN 114671007B CN 202210338352 A CN202210338352 A CN 202210338352A CN 114671007 B CN114671007 B CN 114671007B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/36—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like adapted to receive antennas or radomes
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01S—RADIO DIRECTION-FINDING; RADIO NAVIGATION; DETERMINING DISTANCE OR VELOCITY BY USE OF RADIO WAVES; LOCATING OR PRESENCE-DETECTING BY USE OF THE REFLECTION OR RERADIATION OF RADIO WAVES; ANALOGOUS ARRANGEMENTS USING OTHER WAVES
- G01S7/00—Details of systems according to groups G01S13/00, G01S15/00, G01S17/00
- G01S7/02—Details of systems according to groups G01S13/00, G01S15/00, G01S17/00 of systems according to group G01S13/00
Abstract
The invention relates to a long-baseline small-deformation array antenna housing truss for a three-dimensional imaging radar, which comprises a truss component, a pull rod component, an antenna housing component, an antenna component and an electromagnetic wave absorption component, wherein the truss component is arranged on the truss component; wherein: the truss component is in a flat plate shape and comprises a truss, a partition frame, a cross beam and a hoop, wherein fairing supports formed by the partition frame and the cross beam are arranged at the front edge, the rear edge, the left side and the right side of the truss, and the hoop is arranged on a radar mounting surface and used for fixing and binding cables or pipelines; the truss assembly and the machine body are connected to the belly and the side wall stringer through the pull rod assembly; the antenna housing assembly comprises a plurality of antenna housings, the antenna housings are uniformly distributed and arranged on the bottom surface of the truss assembly, and the antenna housings are connected with the truss assembly through stainless steel bolts; the antenna assembly comprises a three-dimensional imaging radar array antenna and an installation structural member, the number of the antenna assemblies is consistent with that of the antenna housing, and the antenna assemblies are independently installed in the antenna housings respectively.
Description
Technical Field
The invention belongs to the field of aerial survey, particularly relates to an airplane refitting configuration required by a synthetic aperture radar, and particularly relates to a long-baseline small-deformation array radome truss for a three-dimensional imaging radar.
Background
The three-dimensional imaging radar needs to integrate airborne equipment and a plurality of sets of antennas in array layout on an airplane, and the array antennas require long baselines, small deformation and good multi-path effect suppression.
The three-dimensional imaging radar needs to realize accurate measurement of elevation precision and three-dimensional imaging capability, and has high requirements on baseline variation errors. When the ground elevation is measured, the phases of corresponding pixel points in an image pair are obtained by comparing two antennas with master-slave relation, namely the height information of a target corresponding to each pixel point can be determined by utilizing the interferometer principle, and the height information of each scattering point is obtained by specifically processing the phases of the two complex images, so that a three-dimensional digital topographic map with high precision is obtained. As shown in fig. 1, the related principle is as follows:
S 1 、S 2 the phase centers of two antennas at two ends are respectively, and the heights are h 0 The line between the two is a horizontal base line, the length is B, the point P is a certain measuring point on the ground, the height is h, and S 1 The included angle between the connecting line and the P and the vertical direction is theta, and the distance from the point S1 to the point P is R 1 ，S 2 Distance R from point P 2 。
Two antenna phase centers S according to FIG. 1 1 、S 2 The geometrical relationship with the scattering point P on the ground is known as:
h＝h 0 -R 1 cosθ
downward viewing angle theta, slope distance R 1 And height h 0 In relation therebetween, at Δ S 1 S 2 In P, the cosine theorem yields:
due to R 1 ≈R 2 And > B, we can:
based on the distance difference R 1 -R 2 Phase difference phi and wavelength lambda
Therefore, the following steps are carried out:
the sensitivity equation of elevation h with respect to base length B can be obtained:
according to the above formula, the flight height h 0 The height precision is 4km, the height precision requirement is 0.5m, the base line length B =4.2m, the lower view angle of the antenna center is 48 degrees, the distance beam width is 25 degrees, and when the ground height fluctuation is within 300m, the minimum error of the obtained base line length is 0.17mm. Other factors which have small influence on measurement errors such as baseline angle error, interference phase error and motion compensation phase error are considered, the baseline length error is set to be 0.1mm, namely the relative deformation between the phase centers of any two groups of antennas is not more than 0.1mm.
In the existing airplane refitting technology, the configuration meeting the requirement of the imaging radar on the long base line is basically a structural form that pod suspension is carried out at two ends of a truss structure, the base line level can only reach about 2 meters, the relative deformation can only reach the millimeter level, and the requirements that the three-dimensional imaging radar exceeds the base line of 3 meters and the relative deformation is 0.1mm cannot be met.
Disclosure of Invention
In order to solve the technical problem, the invention provides a long-baseline small-deformation array radome truss for a three-dimensional imaging radar. The invention can solve the problems of long baseline and strong rigidity of the flying platform, greatly improves the baseline and rigidity compared with the prior art, and meets the three-dimensional imaging requirement of the array radar.
In order to achieve the purpose, the invention has the following technical scheme:
a long-baseline small-deformation array radome truss for a three-dimensional imaging radar is used for being installed on a fixed-wing aircraft and comprises a truss assembly, a pull rod assembly, a radome assembly, an antenna assembly and an electromagnetic wave absorption assembly; wherein:
the number of the fixed-wing aircraft is 1, and the length of the fuselage and the span is not less than 10m;
the truss assembly provides an installation plane at the lower side of the belly of the flight platform, provides an integrated installation interface for carrying a task load, and provides installation and use spaces for the equipment cable assembly and the environmental control system;
the pull rod assembly connects the flying platform with the truss assembly;
the antenna housing assembly provides installation and use space for task load;
the electromagnetic wave absorption assembly plays a role in inhibiting multipath effect and ensures good imaging performance of task load;
preferably, the truss assembly is flat and comprises a truss, a partition frame, a cross beam and a hoop, is integrally machined from an aluminum alloy thick plate 7050-T7451, is not less than 3 m in length, is symmetrically installed below the belly of the airplane along the wingspan direction, and is provided with fairing supports formed by the partition frame and the cross beam on the front edge, the rear edge, the left side and the right side, and is machined from aluminum alloy plates 2024-T351 for butting and supporting the radome, and the hoop is arranged on a radar installation surface for fixing and binding cables or pipelines; the truss assembly is designed in a lightweight mode on the premise that the interface requirements are met, the H-shaped structure, the reinforcing beams and the reinforcing ribs are integrally arranged, stronger structural strength and rigidity can be guaranteed, and the purpose of reducing weight can be achieved.
Preferably, the number of the pull rod assemblies is 6, 4 sets of the pull rod assemblies are arranged on two sides of the airplane along the course in the front-back direction, 2 sets of the pull rod assemblies are arranged on the lower portion of the belly of the airplane along the course in the front-back direction and consist of a pull rod and a joint, the truss and the airplane body are connected to the belly and the side wall stringer in the form of the joint and the pull rod, the pull rod and the joint are formed by machining aluminum alloy plates 7050-T7451, and steel bushings are installed at bolt installation holes to reduce abrasion of an aluminum alloy structure; the truss structure is provided with 8 connecting joints, the pull rod adopts a water drop-shaped structure form, the pneumatic resistance is greatly reduced while the strength is ensured, the disassembly and the replacement are convenient, and the maintenance is easy; the truss assembly, the machine body and the pull rod assembly are connected with one another, four groups of triangular structural forms including the left front side, the left rear side, the right front side and the right rear side are formed, and the structural rigidity of the truss is greatly improved.
Preferably, the radome assembly is composed of a plurality of radomes, the radomes are uniformly distributed and arranged on the bottom surface of the truss assembly, the number of the radomes is not less than 3, each radome is composed of a flange, a uniform-section wave-transmitting area and front and rear fairings, the design of composite materials is adopted, the uniform-section wave-transmitting area adopts a honeycomb sandwich structure type and is formed by an inner-layer panel, an outer-layer panel and a paper honeycomb core in a dry method, the areas, where wave transmission is not needed, of the front and rear fairings are made of pure glass fiber reinforced plastic materials to improve the structural strength, the radomes are connected with the truss body through stainless steel bolts, the flange of each radome is provided with an electric lap joint hole to realize lightning protection design, and the bottom of each radome is provided with a drain hole to realize drainage design in a mode of embedding a nonmetal drain flange piece; the antenna housing configuration design not only ensures the usable space size and the wave-transmitting index requirement of the radar antenna, but also carries out the front and back rectification design, and the whole pneumatic appearance is good.
Preferably, the antenna assembly consists of three-dimensional imaging radar array antennas and mounting structural members, the antenna assembly and the antenna housings are consistent in number and are respectively and independently mounted in each antenna housing, the array antenna is integrally cuboid-shaped, mechanical, electrical, communication and environmental control interfaces can be integrated on the front end face and the rear end face, two side faces adjacent to an antenna emission face are provided, an interface can be provided on one side to be connected with the truss assembly, and a flat face is provided on the other side to facilitate the application of the electromagnetic wave absorption assembly; the transmitting surface or the receiving surface of the antenna is enveloped in the wave-transparent area with the equal section of the antenna cover, and cables or the ring control pipelines are bound and fixed on the structural member.
Preferably, the electromagnetic wave absorption assembly is attached to the inner side surface, the bottom flange surface and the surface of the antenna structure of the antenna housing, the working frequency band of the electromagnetic wave absorption assembly is consistent with that of the antenna, the electromagnetic wave reflection on the surfaces of the antenna housing assembly, the truss assembly and the antenna assembly is effectively reduced, and the phase error of an antenna phase directional diagram is reduced; the working frequency range of the electromagnetic wave absorption component is 230MHz to 40GHz, and the electromagnetic wave absorption component covers P wave band, L wave band, S wave band, C wave band, X wave band, ku wave band, K wave band and Ka wave band, and the material of the electromagnetic wave absorption component comprises RAT/RKT/RM/RAL/RAC/RACH/RAPH rubber flat plate, FCT/SAT/SML/FRT/FRC foam flat plate, EGT polymer sheet, resin wave absorption plate and macromolecule composite coating.
Preferably, the long-baseline small-deformation array radome truss structure for the three-dimensional imaging radar has the advantages that a plurality of radomes are arrayed, the length of the baseline is not less than 3000mm, and the relative deformation between any two groups of antenna phase centers is not more than 0.1mm.
Has the advantages that:
according to the technical scheme, the long-baseline small-deformation array radome truss structure for the three-dimensional imaging radar solves the problems of insufficient installation space and mutual interference of imaging among antennas of the existing observation platform, and has the advantages of simplicity in modification and flexibility in use.
Drawings
FIG. 1 is a schematic diagram of dual antenna interferometric elevation;
FIG. 2 is a schematic view of the entire truss;
FIG. 3 is an exploded view of the truss as a whole;
FIG. 4 is a schematic view of a truss assembly;
FIG. 5 is a schematic view of a drawbar assembly;
fig. 6 is a schematic view of a radome assembly;
FIG. 7 is a schematic view of an antenna assembly;
fig. 8 is a schematic view of an electromagnetic wave absorption assembly.
Wherein: in the figure, 1, a fixed-wing aircraft; 2. a truss assembly; 3. a drawbar assembly; 4. a radome assembly; 5. an antenna assembly; 6. an electromagnetic wave absorbing member; 7. a truss; 8. a bulkhead; 9. a cross beam; 10. clamping a hoop; 11. a pull rod; 12. a joint; 13. an electromagnetic wave absorbing material is arranged on the flange surface of the antenna housing; 14. an electromagnetic wave absorbing material on the inner side surface of the antenna housing; 15. an antenna support electromagnetic wave absorbing material.
Detailed Description
In order that the objects, technical solutions and advantages of the present invention will become more apparent, the present invention will be further described in detail with reference to the accompanying drawings in conjunction with the following specific embodiments.
According to the embodiment of the invention, as shown in fig. 2-8, the embodiment of the invention provides a long-baseline small-deformation array radome truss for a three-dimensional imaging radar, which comprises a fixed-wing aircraft 1, a truss component 2, a pull rod component 3, a radome component 4, an antenna component 5 and an electromagnetic wave absorption component 6. Wherein:
the fixed-wing aircraft 1 is based on a flying platform used by a national large scientific device, namely a new boat 60 remote sensing aircraft, and has a wing span of 29.2m and a machine length of 24.71m.
The truss component 2 is provided with an installation plane at the lower side of the belly of the flight platform, provides an integrated installation interface for carrying a task load, and provides an installation and use space for an equipment cable component and an environmental control system;
as shown in fig. 2 and 4, the truss assembly 2 is in a flat plate shape and comprises a truss 7, a spacer frame 8, a cross beam 9 and a hoop 10, wherein the truss 7 is integrally machined from aluminum alloy thick plates 7050-T7451, the outline dimension of the truss is 4626mm × 1087mm × 100mm, the truss is symmetrically installed below the belly of the aircraft along the wingspan direction, fairing supports formed by the spacer frame 8 and the cross beam 9 are arranged on the front edge, the rear edge, the left side and the right side of the truss 7, and are machined from aluminum alloy plates 2024-T351 and used for butting and supporting a radome, and the hoop 10 is arranged on a radar installation surface and used for fixing and binding cables or pipelines; the truss structure is designed in a lightweight mode on the premise that the requirement of the interface is met, the H-shaped structure, the reinforcing beams and the reinforcing ribs are integrally arranged, strong structural strength and rigidity can be guaranteed, and the purpose of reducing weight can be achieved.
The pull rod assembly 3 connects the flight platform with the truss structure, as shown in fig. 5, the pull rod assembly 3 has 6 sets, 4 sets are arranged at the front and back of the aircraft along the course at the two sides, 2 sets are arranged at the front and back of the aircraft along the course under the belly, the pull rod assembly 3 is composed of a pull rod 11 and a joint 12, the truss and the aircraft body are connected at the positions of a long truss 3 at the left and right sides of the belly and a long truss 15 at the side wall in a joint and pull rod mode, the pull rod 11 and the joint 12 are formed by machining aluminum alloy plates 7050-T7451, and steel bushings are arranged at bolt mounting holes to reduce the abrasion of the aluminum alloy structure; the trusses 7 are provided with 8 connecting points, the pull rod 11 adopts a water drop-shaped structural form, the pneumatic resistance is greatly reduced while the strength is ensured, the disassembly and the replacement are convenient, and the maintenance is easy; the truss 7, the fuselage and the pull rod assembly 3 are connected with one another, so that a triangular structural form with four groups of left front side, left rear side, right front side and right rear side is formed, and the structural rigidity of the truss is greatly improved.
The radome components 4 provide installation and use space for task load, as shown in fig. 6, the radome components 4 are located on the bottom surface of the truss, are uniformly distributed and arranged, and are 8 sets, wherein the outline size of 6 sets of radomes in the middle is 1355mm × 262mm × 600mm, the outline size of 2 sets of radomes at the left end and the right end is 1355mm × 262mm × 480mm, the available space for equipment installation is 1250mm × 254mm × 290mm, and the distance between two adjacent radomes is 600mm; the radome consists of a flange plate, a uniform-section wave-transmitting area and front and rear fairings, the design of composite materials is adopted, the uniform-section wave-transmitting area adopts a honeycomb sandwich structure type and is formed by an inner-layer panel, an outer-layer panel and a paper honeycomb core dry method, the areas, which do not need wave transmission, of the front and rear fairings are made of pure glass fiber reinforced plastics to improve the structural strength, and the radome is connected with the truss body through stainless steel bolts; an electric lap joint hole is arranged on the radome flange plate to realize the lightning protection design, and a drain hole is arranged at the bottom of the radome in a mode of embedding a non-metal drain flange part to realize the drain design; the antenna housing structural design not only ensures the available space size and the wave-transmitting index requirement of the radar antenna, but also carries out front and back rectification design, and the whole pneumatic appearance is good.
The antenna assembly 5 is mounted below the truss assembly 2 and consists of a three-dimensional imaging radar array antenna and a mounting structural member, as shown in fig. 7, the number of the antenna assemblies is consistent with that of the antenna housings, the antenna assemblies and the antenna housings are respectively and independently mounted in the antenna housings, the array antenna is integrally in a cuboid shape, mechanical, electrical, communication and environment control interfaces can be integrated on the front end face and the rear end face, two side faces adjacent to an antenna emission face are provided, an interface is provided on one side and connected with the truss assembly, and a flat face is provided on the other side so as to be convenient for pasting the electromagnetic wave absorption assembly; an antenna transmitting surface or a receiving surface is enveloped in an antenna cover constant-section wave-transparent area, and cables or an annular control pipeline are bound and fixed on a structural member; 8 groups of antenna components are divided into two types, one type is 'antenna 1' in figure 7, the number is 2, the envelope size is 600mm multiplied by 169mm multiplied by 115mm, the antenna components are installed in the 2 nd and 8 th antenna covers and mainly play a role in receiving and sending electromagnetic waves, the other type is 'antenna 2' in figure 7, the number is 6, the envelope size is 510mm multiplied by 144mm multiplied by 69mm, the antenna components are installed in the 1 st and 3-7 th antenna covers and mainly play a role in receiving electromagnetic waves, and the two types of antennas are matched with each other to form a three-dimensional imaging radar system.
The electromagnetic wave absorption assembly 6 plays a role in inhibiting multipath effect and ensures good imaging performance of task load; as shown in fig. 8, the electromagnetic wave absorbing assembly 6 includes an antenna housing flange surface electromagnetic wave absorbing material 13, an antenna housing inner side surface electromagnetic wave absorbing material 14, and an antenna bracket electromagnetic wave absorbing material 15, the wave absorbing material is bonded with the base body by an iron anchor 801 adhesive, the working frequency band of the electromagnetic wave absorbing assembly is consistent with the working frequency band of the antenna, the surface electromagnetic wave reflection of the antenna housing assembly, the truss assembly and the antenna assembly is effectively reduced, and the phase error of an antenna phase directional diagram is reduced; the working frequency range of the electromagnetic wave absorption component is 230MHz to 40GHz, and the electromagnetic wave absorption component covers a P wave band, an L wave band, an S wave band, a C wave band, an X wave band, a Ku wave band, a K wave band and a Ka wave band, and the electromagnetic wave absorption component material comprises a RAT/RKT/RM/RAL/RAC/RACH/RAPH rubber flat plate, a FCT/SAT/SML/FRT/FRC foam flat plate, an EGT polymer sheet, a resin wave absorption plate and a polymer composite coating; the scheme of pasting the wave-absorbing material on the surfaces of the antenna housing and the antenna structure effectively inhibits the influence of multipath effect, and is simple and easy to implement.
The antenna housing truss with the long base line and the small deformation for the three-dimensional imaging radar is characterized in that every two antenna housings are spaced by 600mm,8 antenna housings are arranged in an array mode, and the base line is as long as 4200mm; the truss structure is installed on the fuselage by adopting 8-point connection, firstly, a fuselage wallboard is subjected to reinforced design, the relative deformation of the fuselage is reduced, meanwhile, the rigidity optimization design is carried out on the truss structure, and then the calculation analysis is combined with the load, the mode, the strength and the rigidity of the whole fuselage to ensure that the designed structure meets the use deformation requirement; under the conditions that the equivalent airspeed is 420km/h, the attack angle of the machine body is 0-6 degrees, and the sideslip angle is-1 degrees, the relative deformation between the phase centers of any two groups of antennas is not more than 0.1mm. Checking and verifying relative deformation by adopting a frequency domain analysis method:
from the kinetic equation:
conversion to the modal space:
[-ω 2 M+iωB+K]{u(ω)}＝{P(ω)}
decoupling equation to obtain the modal coordinate of the single-degree-of-freedom system:
frequency response function:
ω n : natural frequency without damping of the system;
deducing p-th harmonic excitation from the above formula
The following system responses:
wherein:
system response calculation under random excitation:
self-power spectral density function of response:
and (3) carrying out Fourier transform, wherein the autocorrelation function of the response is as follows:
from the frequency response analysis:
S x (ω)＝|H(ω)| 2 S f (ω)
the following can be obtained:
wherein [ m ]]Is a quality matrix, [ c ]]Is a damping coefficient matrix, [ k ]]For the stiffness matrix, { F (t) } is the excitation vector,
and { x (t) } is a kinematic parameter vector, t is a time variable; omega is frequency variable, M, B and K respectively represent mass, damping and rigidity matrixes of a frequency domain, P (omega) is input excitation of the frequency domain, and xi i Representing the modal coordinates, H (ω) being a frequency response function, ω n Representing the natural frequency, ω 0 In order to be the initial frequency of the frequency,
representing the excitation of the p-th harmonic,
represents the p phases; s x (w) represents the self-power spectral density function, R x (τ) represents the autocorrelation function.
According to one embodiment of the invention, the truss integrated installation method comprises the following steps:
firstly, installing a truss assembly and a pull rod assembly, and connecting the truss assembly with a machine body through the pull rod assembly by using a tool;
then, carrying out cable laying work of the load equipment; secondly, according to a task load antenna directional diagram test scheme and a task load antenna directional diagram test result, an electromagnetic wave absorption material is pasted on the inner surface of the antenna housing, the bottom flange surface and the surface of the antenna structure;
and finally, mounting the antenna assembly and the antenna housing assembly coated with the electromagnetic wave absorbing material on a truss assembly.
It should be understood that the above-described embodiments of the present invention are merely examples for clearly illustrating the present invention and are not intended to limit the embodiments of the present invention. It will be apparent to those skilled in the art that other variations and modifications may be made in the foregoing disclosure, and it is not intended to be exhaustive or to limit all embodiments to the precise form disclosed. All obvious changes and modifications which are obvious to the technical scheme of the invention are covered by the protection scope of the invention.
Claims (10)
1. A long-baseline small-deformation array antenna housing truss for a three-dimensional imaging radar is characterized in that the truss is used for being installed on a fixed-wing aircraft and comprises a truss component, a pull rod component, an antenna housing component, an antenna component and an electromagnetic wave absorption component; wherein:
the truss component is shaped like a flat plate and comprises a truss, a partition frame, a cross beam and a hoop, the truss component is formed by integrally machining a first aluminum alloy plate, the length of the truss component is not less than 3 m, the truss component is symmetrically installed below the belly of an aircraft along the wingspan direction, fairing supports formed by the partition frame and the cross beam are arranged on the front edge, the rear edge, the left side and the right side of the truss component, the fairing supports are formed by machining a second aluminum alloy plate and are used for butt joint and support of an antenna housing, and the hoop is arranged on a radar installation surface and is used for fixing and binding cables or pipelines;
the number of the pull rod assemblies is 6, 4 sets of the pull rod assemblies are arranged on two sides of the airplane in the front-back direction, 2 sets of the pull rod assemblies are arranged under the belly of the airplane in the front-back direction, the pull rod assemblies comprise pull rods and joints, the truss assemblies and the airplane body are connected to the belly and the side wall stringer through the pull rod assemblies, the pull rods and the joints are formed by adding a first aluminum alloy plate machine, and steel bushings are arranged at bolt mounting holes so as to reduce abrasion of an aluminum alloy structure;
the radome assembly comprises a plurality of radomes, the radomes are uniformly distributed and arranged on the bottom surface of the truss assembly, the number of the radomes is not less than 3, each radome comprises a flange plate, a uniform-section wave-transmitting area and front and rear fairing covers, the radome is designed by adopting a composite material, the uniform-section wave-transmitting area adopts a honeycomb sandwich structure type and is formed by an inner-layer panel and an outer-layer panel and a paper honeycomb core in a dry method, the areas, which do not need wave transmission, of the front and rear fairing parts are made of pure glass fiber reinforced plastic materials to improve the structural strength, the radomes are connected with the truss assembly through stainless steel bolts, the flange plate of each radome is provided with an electric lap joint hole to realize a lightning protection design, and the bottom of each radome is provided with a drain hole to realize a drainage design in a mode of embedding a nonmetal drain flange part;
the antenna assembly comprises three-dimensional imaging radar array antennas and mounting structural members, the number of the antenna assemblies is consistent with that of the antenna housing, the antenna assemblies and the antenna housing are respectively and independently mounted in the antenna housings, the array antennas are integrally cuboid-shaped, mechanical, electrical, communication and environment-control interfaces are integrated on the front end face and the rear end face, two side faces adjacent to an antenna emission face are provided, an interface is provided on one side and connected with the truss assembly, and a flat face is provided on the other side so as to be convenient for pasting the electromagnetic wave absorption assembly;
the electromagnetic wave absorption assembly comprises an antenna housing inner surface, a bottom flange surface and wave absorption materials pasted on the antenna assembly, and the number of the assemblies is consistent with that of the antennas.
2. The long-baseline small-deformation array radome truss for the three-dimensional imaging radar as claimed in claim 1, wherein the truss provides an integrated interface for carrying the three-dimensional imaging radar and provides an installation and use space for equipment cable assemblies and an environmental control system.
3. The long-baseline small-deformation array radome truss for the three-dimensional imaging radar as claimed in claim 1, wherein the truss assembly is designed in a light weight manner on the premise of meeting the interface requirement, the truss assembly is integrally provided with an I-shaped structure, reinforcing beams and reinforcing ribs, fairing supports formed by bulkheads and cross beams are arranged on the front edge, the rear edge, the left side and the right side of the truss assembly, the fairing supports are used for butting and supporting the radome, and the hoops are arranged on a radar mounting surface and used for fixing and binding cables or pipelines.
4. The long-baseline small-deformation array radome truss for the three-dimensional imaging radar as claimed in claim 1, wherein the connection between the truss component and the airframe is in the form of a tie joint, the truss structure is provided with 8 connecting joints, and the tie is in the form of a water drop-shaped structure.
5. The long-baseline small-deformation array radome truss for the three-dimensional imaging radar as claimed in claim 1, wherein the truss assembly, the body and the tie rod assembly are connected with each other to form a structure form of four groups of 'triangle' structures, namely a left front side, a left rear side, a right front side and a right rear side.
6. The long-baseline small-deformation array radome truss for the three-dimensional imaging radar as claimed in claim 1, wherein the antenna assemblies are independently installed in each radome, an antenna emitting surface or a receiving surface is enveloped in a radome uniform-section wave-transmitting area, and cables or environmental control pipelines are bound and fixed on structural members.
7. The long-baseline small-deformation array radome truss for the three-dimensional imaging radar as claimed in claim 1, wherein the electromagnetic wave absorption assembly is attached to the inner side surface of the radome, the bottom flange surface and the surface of the antenna structure, and the working frequency band of the electromagnetic wave absorption assembly is consistent with that of the antenna.
8. The radome truss of long baseline small deformation array for the three-dimensional imaging radar of claim 1, wherein the working frequency range of the electromagnetic wave absorption component is from 230MHz to 40GHz, and the electromagnetic wave absorption component covers P wave band, L wave band, S wave band, C wave band, X wave band, ku wave band, K wave band and Ka wave band, and the material of the electromagnetic wave absorption component comprises RAT/RKT/RM/RAL/RAC/RACH/RAPH rubber flat plate, FCT/SAT/SML/FRT/FRC foam flat plate, EGT polymer sheet, resin wave absorption plate and macromolecule composite coating.
9. The long-baseline small-deformation array radome truss for the three-dimensional imaging radar as claimed in claim 1, wherein a plurality of radomes are arrayed, and the length of the baseline is not less than 3000mm.
10. The long-baseline small-deformation array radome truss for the three-dimensional imaging radar according to claim 1, wherein the relative deformation between any two groups of antenna phase centers is not more than 0.1mm.
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