CN103887605A - Wing antenna integrating structures and functions - Google Patents

Abstract

The invention discloses a structure-function integrated wing antenna, comprising: a wing frame, a wing skin, a control and signal processing system, and the wing skin sequentially includes: an upper panel, an upper honeycomb/foam layer from top to bottom , a radio frequency functional layer, a lower honeycomb/foam layer and a lower panel, the lower panel is laid with optical fibers, and a Bragg grating is arranged at intervals on each optical fiber; the aforementioned radio frequency functional layer includes: a radio frequency circuit layer, a wave control circuit layer and packaging The frame and the radio frequency functional layer are made with liquid cooling channels inside; the aforementioned radio frequency circuit layer includes an antenna array composed of a number of antenna sub-arrays arranged in a distributed layout, and the antenna sub-array is composed of a number of microstrip radiating units. The invention is beneficial in that it reduces the weight of the fuselage, improves the aerodynamic performance of the aircraft, and has good heat dissipation; it can monitor the deformation and strength of the wing structure in real time, automatically compensate the influence of structural vibration and deformation on the electrical performance, and ensure that the antenna is in the air. Electromagnetic performance stability in harsh environments.

Description

Structure and function integrated wing antenna

technical field

The invention relates to a wing antenna, in particular to a structure-function integrated wing antenna, which belongs to the technical field of aircraft antennas.

Background technique

The structure-function integrated wing antenna refers to the embedding of the radio frequency functional parts of the integrated microstrip antenna array into the wing structure of the aircraft. The highly integrated skin antenna manufactured by the integrated compound molding process can be used as a weapon platform The mechanical load-bearing functional parts of the structure can also be used as electromagnetic functional parts for sending and receiving wireless electromagnetic waves. Compared with traditional antennas, the structure-function integrated wing antenna has the characteristics of high integration of structure and circuit. It can be applied to future aircraft such as variant aircraft, unmanned aerial vehicles, airship early warning aircraft, etc. It is the key technology to realize the stealth, multi-function and high maneuverability of the aircraft, and can effectively reduce the weight of the aircraft and maintain the good aerodynamic shape of the aircraft .

The structure-functional integrated wing antenna can be used not only as the wing of the aircraft, but also as the antenna device for transmitting and receiving electromagnetic waves, so as to meet the requirements of the aircraft's aerodynamic performance, electromagnetic stealth and adaptability.

In related research, NASA has developed a long-range UAV wing, whose microstrip antenna array, solar cell array and wing structure are fully integrated. The research is published in the open literature "Structurally Integrated antenna concepts for hale UAVS.NASAReport-2006-214513.Langley Research Center, Virginia, 2006:23681-2199" (Structurally Integrated antenna concepts for hale UAVS.NASAReport-2006-214513. Langley Research Center, Virginia, 23681-2199).

Boeing has developed a honeycomb sandwich wing structure that integrates X-band microstrip antenna arrays. 8." (M.Urcia, D.Banks. Structural Integrated Phased Array. 2011 IEEE Aviation Conference, Big Sky, MT, United states, 2011:1-8.) Reported.

The Northwestern Polytechnical University in China proposed a new configuration in which the microstrip antenna is pre-packaged and embedded in a composite sandwich structure. This configuration can realize the conformal shape of the antenna array and the body structure. The research was published in the invention patent "Xie Zonghong, Zhao Wei, Zhang Peng, Li Lei. A new type of embedded composite material smart skin antenna structure, application time: 2010-6-10, patent country: China, patent application number: 201010197298.1" is reported.

The technical scheme of embedding the microstrip antenna array into the wing structure has been disclosed at home and abroad, but the existing technology still has the following deficiencies:

1. In the technical solutions disclosed in the existing documents, only the method of integrating the microstrip antenna array into the wing structure is given. However, the layout method of the antenna in the wing structure, the radio frequency signal connection method and the production method are not described. method.

2. Since the microstrip antenna is highly integrated into the wing structure, when the antenna is working, the radio frequency device will heat up, resulting in reduced radiation performance of the antenna, or even complete failure. The existing literature does not provide a structural design method to reduce the temperature of the antenna.

3. During service, the wing structure will inevitably be affected by aerodynamic loads, which will cause vibration and deformation of the wing structure, resulting in changes in the position of the antenna radiation unit embedded in the structure, affecting electromagnetic radiation performance. These phenomena have been mentioned in the reports of NASA and Boeing, however, they have not proposed an effective structure to compensate the influence of the vibration and deformation of the structure on the electromagnetic performance.

Contents of the invention

The purpose of the present invention is to provide a novel integrated microstrip antenna array and fiber grating structure-function integrated wing antenna, which can not only reduce the weight of the fuselage, but also realize the real-time detection and electrical performance of the vibration and deformation of the wing structure. Compensation, and at the same time, it can effectively reduce the antenna heat dissipation problem caused by high-density integration.

In order to achieve the above object, the present invention adopts the following technical solutions:

A structure-function integrated wing antenna, comprising: a wing frame and a wing skin covering the aforementioned wing frame, characterized in that,

The aforementioned wing skeleton comprises: several wing ribs arranged in parallel, a hollow triangular spar passing through and connecting the aforementioned wing ribs, a leading edge of the wing installed at the front end of the aforementioned wing ribs, and a trailing edge of the wing installed at the rear end of the aforementioned wing ribs ;

The aforementioned wing skin is a composite structure, including from top to bottom: an upper panel, an upper honeycomb/foam layer, a radio frequency functional layer, a lower honeycomb/foam layer and a lower panel; the aforementioned lower panel is in contact with the lower honeycomb/foam layer A number of optical fibers are laid at the interface, the aforementioned optical fibers are parallel to the ribs, and a Bragg grating is arranged at intervals on each optical fiber;

The aforementioned radio frequency functional layer includes: a radio frequency circuit layer located on the upper layer, a wave control circuit layer located on the lower layer, and a packaging frame. The aforementioned radio frequency circuit layer and the wave control circuit layer are connected by pins; cold aisle;

The aforementioned radio frequency circuit layer is a composite structure, and the uppermost layer is an antenna array. The aforementioned antenna array is composed of a number of antenna sub-arrays. Each microstrip radiating element in the array is plated with a layer of copper;

The structure and function integrated wing antenna also includes: control and signal processing system, the aforementioned control and signal processing system is installed in the hollow of the aforementioned spar, the control signals in each antenna sub-array and the measurement signals of optical fibers are unified to the aforementioned control and the signal processing system for centralized processing, and the aforementioned control and signal processing system also provides control signals to the aforementioned wave control circuit layer.

The aforementioned structure and function integrated wing antenna is characterized in that the aforementioned radio frequency circuit layer also includes: a T/R circuit layer positioned below the antenna front, a power division circuit layer positioned below the T/R circuit layer, and the aforementioned T/R circuit layer The circuit layer and the power division circuit layer are signal-connected to the wave control circuit layer through low-frequency lines and high-frequency lines respectively.

The aforementioned structure and function integrated wing antenna is characterized in that, between the microstrip radiation unit in the aforementioned antenna array and the T/R circuit layer, a microstrip antenna-coaxial-microstrip line or a microstrip antenna-coupling small The hole-microstrip connection structure is interconnected to realize electrical signal connection.

The aforementioned structure-function integrated wing antenna is characterized in that, between the aforementioned T/R circuit layer and the power division circuit layer, a microstrip-coaxial-stripline or microstrip-coaxial-stripline The electrical signal connection is realized by vertical interconnection.

The aforementioned structure-function integrated wing antenna is characterized in that the aforementioned liquid cooling channel is composed of: several microchannels arranged in parallel, a liquid outlet cavity and a liquid inlet cavity respectively arranged at both ends of the aforementioned microchannel, and the aforementioned liquid outlet cavity and the liquid inlet cavity respectively. The liquid-cooling channel outlet and the liquid-cooling channel inlet connected by the liquid inlet are composed of; the aforementioned liquid-cooling channel outlet and the liquid-cooling channel inlet pass through the aforementioned wave control circuit layer and are connected to an external hydraulic circuit.

The aforementioned structure-function integrated wing antenna is characterized in that the aforementioned microchannel is rectangular.

The aforementioned structure-function integrated wing antenna is characterized in that the length and width of the aforementioned microchannel are 0.1 mm and 0.5 mm, respectively.

The aforementioned structure-function integrated wing antenna is characterized in that the aforementioned radio frequency circuit layer is manufactured and formed by sintering low temperature co-fired ceramic materials.

The aforementioned structure-function integrated wing antenna is characterized in that the aforementioned wave control circuit layer is made of glass fiber epoxy resin copper-clad laminate.

The aforementioned structure-function integrated wing antenna is characterized in that the aforementioned microstrip radiation unit is rectangular or circular.

The benefits of the present invention are:

1. The structure-function integrated wing antenna of the present invention can be used as an aircraft wing or as a transceiver antenna. It not only removes a large number of external antennas and mounting bases, reduces the weight of the fuselage, but also improves the aerodynamic performance of the aircraft. Performance, and the antenna sub-arrays are arranged in a distributed layout, which increases the antenna aperture.

2. The structure-function integrated wing antenna of the present invention has optical fiber and Bragg grating embedded in its structure, which can not only monitor the deformation and strength of the wing structure in real time, and realize the health monitoring of the wing structure, but also, through the optical fiber and Bragg grating The signal processing of the test data of the grating can automatically compensate the influence of structural vibration and deformation on the electrical performance, and ensure the stability of the electromagnetic performance of the antenna in the harsh service environment.

3. The structure-function integrated wing antenna of the present invention has a micro-channel structure designed in its structure, and the heat of the radio-frequency functional layer device is taken away by the liquid in the micro-channel through heat conduction, which reduces the heat caused by high-density integration. The temperature of the microstrip antenna front leads to the disadvantages of the performance degradation or failure of the antenna.

Description of drawings

Fig. 1 is the composition structure schematic diagram of the structural function integrated wing antenna of the present invention;

Fig. 2 is the general assembly rendering of the wing antenna in Fig. 1;

Fig. 3 is the wing skeleton diagram in Fig. 2;

Fig. 4 is the wing skin figure in Fig. 2;

Fig. 5 is a schematic diagram of the layout of the microstrip antenna array embedded in Fig. 4;

Fig. 6 is a sectional view of the wing skin in Fig. 4;

Fig. 7 is an exploded schematic view of the wing skin in Fig. 6;

Fig. 8 is a schematic composition diagram of the lower panel structure in Fig. 7;

Fig. 9 is a schematic diagram of the microstrip antenna front on the upper surface of the radio frequency functional layer;

Fig. 10 is a schematic diagram of the liquid cooling channel inside the radio frequency functional layer;

Fig. 11 is a schematic diagram of the electrical connection relationship of the radio frequency functional layer;

Fig. 12 is a geometric structure diagram of the rectangular microstrip radiation unit in Fig. 7;

Fig. 13 is a geometric structure diagram of the circular microstrip radiation unit in Fig. 7;

FIG. 14 is a geometric structure diagram of the aperture coupling feed connection of the microstrip antenna in FIG. 7 .

The meanings of reference signs in the figure: 101-wing leading edge, 102-wing trailing edge, 103-rib, 104-spar, 105-upper skin, 106-lower skin, 107-control and signal processing System, 301-upper panel, 302-upper honeycomb/foam layer, 303-encapsulation frame, 304-radio frequency circuit layer, 305-liquid cooling channel, 306-wave control circuit layer, 307-lower honeycomb/foam layer, 308-bottom Panel, 309-microstrip radiation unit, 310-optical fiber, 311-Bragg grating, 401-microchannel, 402-liquid outlet, 403-liquid cooling channel outlet, 404-liquid cooling channel inlet, 405-liquid inlet, 601 -T/R circuit layer, 602-power division circuit layer, 603-antenna array, 801-feed point, 802-dielectric plate, 803-ground plane, 804-coaxial feed interface, 805-coupling hole, 806 - Feed microstrip line.

Detailed ways

The present invention will be specifically introduced below in conjunction with the accompanying drawings and specific embodiments.

Referring to FIG. 1 , FIG. 2 and FIG. 3 , the structure-function integrated wing antenna of the present invention includes: a wing frame, a wing skin, and a control and signal processing system 107 . The wing skin covers the outside of the wing skeleton, and the wing skin is divided into an upper skin 105 and a lower skin 106 according to the positions covering the wing skeleton, both of which have identical structures. The structure of the wing skeleton, the wing skin, and the control and signal processing system 107 will be introduced respectively below.

Referring to FIG. 1 , FIG. 2 and FIG. 3 , the wing skeleton includes: ribs 103 , spars 104 , wing leading edge 101 and wing trailing edge 102 . There are several ribs 103 arranged in parallel; the spar 104 is triangular in shape and is a hollow structure, which is used to place the control and signal processing system 107, and the spar 104 passes through the ribs 103 to connect the ribs The effect of 103; Wing leading edge 101 is installed in the front end of wing rib 103, and wing trailing edge 102 is installed in the rear end of wing rib 103.

4 to 7, the wing skin is a composite structure, including from top to bottom: upper panel 301, upper honeycomb/foam layer 302, radio frequency functional layer, lower honeycomb/foam layer 307 and lower panel 308. The upper panel 301 and the lower panel 308 are used to realize the mechanical bearing function, the upper honeycomb/foam layer 302 and the lower honeycomb/foam layer 307 are used to realize the heat insulation function, and the radio frequency function layer mainly realizes the function of transmitting and receiving electromagnetic signals. The upper panel 301 and the upper honeycomb/foam layer 302, the lower panel 308 and the lower honeycomb/foam layer 307 are preferably connected by bonding, and the upper panel 301 and the lower panel 308 are preferably made of carbon fiber composite materials, or Made of fiberglass composite. Wherein, referring to FIG. 8 , the lower panel 308 is laid with several optical fibers 310 at the interface in contact with the lower honeycomb/foam layer 307 , the optical fibers 310 are parallel to the ribs 103 , and each optical fiber 310 is provided with a Bragg grating 311 at intervals. The optical fiber 310 and the Bragg grating 311 can detect the strain of the deformation of the wing structure in real time, realizing the intelligent monitoring of the wing structure, and the measurement signal of the optical fiber 310 can automatically compensate the structural vibration and deformation after being processed by the algorithm of the control and signal processing system 107 The impact on electrical performance ensures the stability of the electromagnetic performance of the antenna in harsh service environments.

Referring to FIG. 7 , the radio frequency functional layer includes: a radio frequency circuit layer 304 , a wave control circuit layer 306 and a packaging frame 303 . Among them, the radio frequency circuit layer 304 is located on the upper layer, and the wave control circuit layer 306 is located on the lower layer. The radio frequency circuit layer 304 and the wave control circuit layer 306 are connected by pins. The radio frequency circuit layer 304 can realize the transmission and radiation functions of electromagnetic signals. The circuit layer 306 can implement functions such as beam steering, channel and power control. The radio frequency circuit layer 304 is preferably manufactured by sintering low-temperature co-fired ceramic materials. The wave control circuit layer 306 is preferably made of glass fiber epoxy resin copper clad laminate. The encapsulation frame 303 uses a bonding process to realize the connection between the radio frequency functional layer and the upper panel 301, the upper honeycomb/foam layer 302, the lower panel 308, and the lower honeycomb/foam layer 307. The encapsulation frame 303 protects the circuit of the radio frequency functional layer on the one hand, and on the other hand On the one hand, it provides the grounding requirements required by the radio frequency functional layer. The inside of the radio frequency functional layer is made with a liquid cooling channel 305 and embedded with chips. The liquid cooling channel 305 is a miniature rectangular channel made inside the radio frequency circuit layer 304, which is used to cool and dissipate the components in the radio frequency functional layer to ensure that the radio frequency The temperature required for the functional layer to work.

Referring to FIG. 10 , the liquid cooling channel 305 is composed of: a micro channel 401 , a liquid outlet 402 , a liquid inlet 405 , a liquid cooling channel outlet 403 and a liquid cooling channel inlet 404 . There are several microchannels 401, and they are arranged in parallel; the liquid outlet cavity 402 and the liquid inlet cavity 405 are respectively arranged at the two ends of the microchannel 401, and both play the function of buffering liquid; the outlet 403 of the liquid cooling channel communicates with the liquid outlet cavity 402 , the liquid inlet 405 communicates with the liquid cooling channel inlet 404, and at the same time, the liquid cooling channel outlet 403 and the liquid cooling channel inlet 404 pass through the wave control circuit layer 306 and are connected to an external hydraulic circuit.

The structure and function integrated wing antenna of the present invention has a microchannel 401 structure designed in its structure, and the heat of the radio frequency functional layer device is taken away by using the liquid in the microchannel 401 through heat conduction, which reduces the heat caused by high-density integration. The temperature of the microstrip antenna front 603 leads to the disadvantages of performance degradation or failure of the antenna.

As a preferred solution, the microchannel 401 is rectangular, and its length and width are preferably 0.1 mm and 0.5 mm, respectively.

Referring to FIG. 7 and FIG. 11 , the radio frequency circuit layer 304 is a composite structure, and the uppermost layer is an antenna front 603 . The antenna array 603 is composed of several antenna sub-arrays. The antenna sub-arrays are arranged in a distributed layout, as shown in FIG. Each antenna sub-array is made up of some microstrip radiating units 309, and the microstrip radiating unit 309 is formed on the surface of the radio frequency functional layer by using a screen printing process to plate a microwave circuit, and each microstrip radiating unit 309 is plated with a layer of copper, Thereby realizing the radiation and transmission of electrical signals. As shown in FIG. 9 , the microstrip radiating units 309 are arranged according to the design index and installation space, so as to form an antenna sub-array.

Referring to Fig. 11, the radio frequency circuit layer 304 also includes: a T/R circuit layer 601 (that is, a radio frequency signal transceiver layer, on which there are radio frequency signal transceiver components, and the liquid cooling channel 305 mainly transmits and receives radio frequency signals in the T/R circuit layer 601 components for cooling and heat dissipation) and the power division circuit layer 602 (that is, the power distribution/synthesis network layer). The T/R circuit layer 601 is located below the antenna array 603 , and the power dividing circuit layer 602 is located below the T/R circuit layer 601 . Wherein, the microstrip radiating unit 309 in the antenna front 603 realizes electrical signal connection with the T/R circuit layer 601 through the connection structure of microstrip antenna-coaxial-microstrip line, and the T/R circuit layer 601 and the power dividing circuit layer 602 realizes electrical signal connection through the vertical interconnection mode of microstrip line-coaxial-stripline or microstrip line-coaxial-stripline, and the T/R circuit layer 601 and the power division circuit layer 602 respectively pass low-frequency lines, The high frequency line is connected to the wave control circuit layer 306 for signals.

As a preferred solution, referring to Fig. 11, a vertical interconnection structure of microstrip antenna-coaxial-microstrip line is adopted between the microstrip radiating unit 309 and the T/R circuit layer 601; the T/R circuit layer 601 and the power divider A vertical interconnection structure of microstrip-coaxial-stripline is adopted between the circuit layers 602 .

In the present invention, the microstrip radiation unit 309 is rectangular. As shown in Figure 9 and Figure 12, the long side of the microstrip radiating unit 309 is a, and the broad side is b, and the microstrip radiating unit 309 is manufactured on the upper surface of a dielectric board 802 with a thickness h by using a copper-clad laminate production process Conductive patches, and the feed point 801 in the microstrip radiation unit 309 is connected to the T/R circuit layer 601 for electromagnetic signals through the coaxial feed interface 804 , and the bottom surface of the dielectric board 802 is a ground plane 803 .

As an alternative, the microstrip radiation unit 309 is circular. As shown in FIG. 13 , the radius of the microstrip radiating unit 309 is r, and a feeding point 801 is arranged on it, and other structures are the same as above, and will not be repeated here.

As an alternative, the microstrip radiating unit 309 and the T/R circuit layer 601 do not use the connection structure of microstrip antenna-coaxial-microstrip line, but use the connection structure of microstrip antenna-coupling hole-microstrip line The connection structure is shown in Figure 14. This feeding method is beneficial to the feeding microstrip line 806 printed on the lower surface of the lower dielectric board 802 to realize the electromagnetic signal connection between the T/R circuit layer 601 and the coupling hole 805, and to couple the electromagnetic signal through the coupling hole 805. to the radiation unit 309 to realize the radiation or reception of electromagnetic signals. The upper dielectric plate uses a low dielectric constant to facilitate electromagnetic radiation, and the lower dielectric plate uses a high dielectric constant to facilitate field confinement on the feeding microstrip line 806 .

Referring to FIGS. 3 and 11 , the control and signal processing system 107 is mounted in the hollow of the spar 104 . The control signals in each antenna sub-array and the measurement signals of the optical fiber 310 are all unified to the control and signal processing system 107 for centralized processing. At the same time, the control and signal processing system 107 also provides control signals to the wave control circuit layer 306. The signal processing system 107 and the wave control circuit layer 306 are connected by cables.

In summary, the structure-function integrated wing antenna of the present invention can be used as an aircraft wing or as a transceiver antenna, which not only removes a large number of external antennas and mounting bases, reduces the weight of the fuselage, and improves the Excellent aerodynamic performance, and the distributed antenna array layout increases the antenna aperture; at the same time, through the processing of optical fiber 310 and Bragg grating 311 test data, it can automatically compensate for the influence of structural vibration and deformation on electrical performance, ensuring that the antenna can be used in harsh service environments. In addition, the microchannel 401 designed in the radio frequency functional layer can take away the heat of the device through the liquid in it, which reduces the disadvantages of the high-density integrated device temperature that causes the antenna performance to decrease or fail.

It should be noted that the above embodiments do not limit the present invention in any form, and all technical solutions obtained by means of equivalent replacement or equivalent transformation fall within the protection scope of the present invention.

Claims (10)

1. a structure-function integration wing antenna, comprising: the wing cover of wing skeleton and the described wing skeleton of covering, it is characterized in that,

Described wing skeleton comprises: the some ribs (103) that are arranged in parallel, pass and connect the hollow triangle spar (104) of described rib (103), be arranged on the leading edge of a wing (101) of described rib (103) front end, and be arranged on the trailing edge (102) of described rib (103) rear end;

Described wing cover is composite construction, comprises successively from top to bottom: top panel (301), upper honeycomb/froth bed (302), radio-frequency enabled layer, lower honeycomb/froth bed (307) and lower panel (308); Described lower panel (308) is equipped with some optical fiber (310) in the interface contacting with lower honeycomb/froth bed (307), described optical fiber (310) is parallel with rib (103), and every optical fiber (310) is upper arranges a Bragg grating (311) every an intersegmental distance;

Described radio-frequency enabled layer comprises: is positioned at the radio circuit layer (304) on upper strata, is positioned at the ripple control circuit layer (306) of lower floor, and packaging frame (303), between described radio circuit layer (304) and ripple control circuit layer (306), use contact pin to be connected; The internal production of described radio-frequency enabled layer has liquid cooling passage (305);

Described radio circuit layer (304) is composite construction, the superiors are antenna array (603), described antenna array (603) is made up of some antenna submatrixs, described antenna submatrix is made up of some micro-band radiating elements (309), described antenna submatrix adopts distributed layout mode to arrange, and the each micro-band radiating element (309) in antenna submatrix is all coated with layer of copper;

Structure-function integration wing antenna also comprises: control and signal processing system, described control and signal processing system are arranged in described spar (104) hollow, control signal in each antenna submatrix, the measuring-signal of optical fiber (310) are all unified to be focused on to described control and signal processing system, and described control and signal processing system also provide control signal to described ripple control circuit layer (306).

2. structure-function integration wing antenna according to claim 1, it is characterized in that, described radio circuit layer (304) also comprises: the T/R circuit layer (601) that is positioned at antenna array (603) below, the merit parallel circuit layer (602) that is positioned at T/R circuit layer (601) below, described T/R circuit layer (601) is connected with ripple control circuit layer (306) signal by low frequency wire, high-frequency line respectively with merit parallel circuit layer (602).

3. structure-function integration wing antenna according to claim 2, it is characterized in that, between the micro-band radiating element (309) in described antenna array and T/R circuit layer (601), adopt the interconnected signal of telecommunication of realizing of syndeton of microstrip antenna-coaxial-microstrip line or microstrip antenna-coupling aperture-microstrip line to be connected.

4. structure-function integration wing antenna according to claim 3, it is characterized in that, between described T/R circuit layer (601) and merit parallel circuit layer (602), adopt the vertical interconnect mode of microstrip line-coaxial-strip line or microstrip line-coaxial-strip line to realize the signal of telecommunication and be connected.

5. structure-function integration wing antenna according to claim 1, it is characterized in that, liquid cooling channel outlet (403) and liquid cooling feeder connection (404) that described liquid cooling passage (305) is communicated with described liquid discharge oral cavity (402) and chamber, liquid inlet (405) by: some microchannels that be arranged in parallel (401), the liquid discharge oral cavity (402) that is separately positioned on two ends, described microchannel (401) and chamber, liquid inlet (405), respectively form; Described liquid cooling channel outlet (403) and liquid cooling feeder connection (404) pass described ripple control circuit layer (306), and connect outside hydraulic circuit.

6. structure-function integration wing antenna according to claim 5, is characterized in that, described microchannel (401) are rectangular.

7. structure-function integration wing antenna according to claim 6, is characterized in that, the length of described microchannel (401) and wide 0.1mm and the 0.5mm of being respectively.

8. according to the structure-function integration wing antenna described in claim 1 to 7 any one, it is characterized in that, described radio circuit layer (304) is manufactured moulding by low-temperature co-burning ceramic material sintering.

9. according to the structure-function integration wing antenna described in claim 1 to 7 any one, it is characterized in that, described ripple control circuit layer (306) is formed by glass-epoxy copper-clad plate manufacture.

10. according to the structure-function integration wing antenna described in claim 1 to 7 any one, it is characterized in that, described micro-band radiating element (309) is rectangular or circular.

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