CN114056589A - Airborne lightweight composite material direction-finding antenna array nacelle body - Google Patents
Airborne lightweight composite material direction-finding antenna array nacelle body Download PDFInfo
- Publication number
- CN114056589A CN114056589A CN202111493534.9A CN202111493534A CN114056589A CN 114056589 A CN114056589 A CN 114056589A CN 202111493534 A CN202111493534 A CN 202111493534A CN 114056589 A CN114056589 A CN 114056589A
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- strength glass
- upper cover
- glass fiber
- layer high
- nacelle
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- 239000002131 composite material Substances 0.000 title claims abstract description 21
- 239000003365 glass fiber Substances 0.000 claims abstract description 47
- 239000011162 core material Substances 0.000 claims abstract description 20
- 239000004760 aramid Substances 0.000 claims abstract description 14
- 229920003235 aromatic polyamide Polymers 0.000 claims abstract description 14
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 8
- 239000004917 carbon fiber Substances 0.000 claims description 8
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 8
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 7
- 229920007790 polymethacrylimide foam Polymers 0.000 claims description 6
- 230000002209 hydrophobic effect Effects 0.000 claims description 4
- 239000011152 fibreglass Substances 0.000 claims 1
- 230000001105 regulatory effect Effects 0.000 claims 1
- 238000009434 installation Methods 0.000 abstract description 7
- 238000013461 design Methods 0.000 description 14
- 241000264877 Hippospongia communis Species 0.000 description 11
- 239000000463 material Substances 0.000 description 8
- 238000010586 diagram Methods 0.000 description 6
- 238000000034 method Methods 0.000 description 4
- 210000001015 abdomen Anatomy 0.000 description 3
- 229920006231 aramid fiber Polymers 0.000 description 2
- 210000001503 joint Anatomy 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 238000007789 sealing Methods 0.000 description 2
- 229920006934 PMI Polymers 0.000 description 1
- 239000011157 advanced composite material Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 239000000203 mixture Substances 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000003032 molecular docking Methods 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 239000005871 repellent Substances 0.000 description 1
- 239000011347 resin Substances 0.000 description 1
- 229920005989 resin Polymers 0.000 description 1
- 230000035945 sensitivity Effects 0.000 description 1
- 230000000087 stabilizing effect Effects 0.000 description 1
- 239000013585 weight reducing agent Substances 0.000 description 1
Images
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D47/00—Equipment not otherwise provided for
-
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U2101/00—UAVs specially adapted for particular uses or applications
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Laminated Bodies (AREA)
- Woven Fabrics (AREA)
Abstract
The invention discloses an airborne lightweight composite material direction finding antenna array pod body, and belongs to the field of airborne avionic pods. The nacelle comprises an upper cover, a lower cover and a switch array, wherein the upper cover and the lower cover are buckled to form a cabin body; the switch array is positioned in the cabin body and is fixed on the top of the inner wall of the upper cover through bolts; the upper cover and the lower cover are of laminated structures and respectively comprise inner-layer high-strength glass fibers, aramid paper honeycomb core materials and outer-layer high-strength glass fibers which are sequentially laminated from inside to outside; wherein the thickness of the inner layer high-strength glass fiber is 0.3mm, the thickness of the outer layer high-strength glass fiber is 0.2mm, and the thickness of the aramid paper honeycomb core material is 4.5 mm. The invention reduces weight to the maximum extent and realizes the light weight of the cabin body. The nacelle body has the characteristics of rapidness in installation, light weight, universality and the like.
Description
Technical Field
The invention relates to the field of airborne avionic pod, in particular to an airborne lightweight pod body of a direction-finding antenna array made of composite materials.
Background
The avionic pod is a high-tech weapon equipment which is actively developed in developed countries in the last two decades and is put into practical use, is usually hung below the belly or wing of an airplane, expands the use function of the airplane and is a relatively independent electronic device. At present, China also develops electronic pods for various types of airborne platforms. Due to the sensitivity of aviation products to weight, when the electronic pod is applied to an unmanned aerial vehicle platform, in order to guarantee the cruising ability of the unmanned aerial vehicle and meet the requirements of electrical performance of equipment in the cabin, installation usability and the like, the light-weight design of a pod body of the pod, the selection of materials of the pod body, the structural characteristics, the requirement of electrical performance of the equipment in the cabin and the like are more and more important.
Disclosure of Invention
In view of the above, the invention provides an airborne light-weight composite material direction finding antenna array nacelle body. The nacelle body is subjected to maximum weight reduction, and the light weight of the nacelle body is realized. The nacelle body has the characteristics of rapidness in installation, light weight, universality and the like.
In order to achieve the purpose, the technical scheme adopted by the invention is as follows:
an airborne lightweight composite material direction-finding antenna array pod body comprises an upper cover, a lower cover and a switch array, wherein the upper cover and the lower cover are buckled to form a pod body; the switch array is positioned in the cabin body and is fixed on the top of the inner wall of the upper cover through bolts; the upper cover and the lower cover are of laminated structures and respectively comprise inner-layer high-strength glass fibers, aramid paper honeycomb core materials and outer-layer high-strength glass fibers which are sequentially laminated from inside to outside; wherein the thickness of the inner layer high-strength glass fiber is 0.3mm, the thickness of the outer layer high-strength glass fiber is 0.2mm, and the thickness of the aramid paper honeycomb core material is 4.5 mm.
Furthermore, the bottom of the lower cover is provided with a drain hole for adjusting pressure difference and draining condensed water.
Furthermore, the inner wall of the drain hole is provided with a high-strength glass fiber layer, and the high-strength glass fiber layer, the inner-layer high-strength glass fiber of the lower cover and the outer-layer high-strength glass fiber are of an integrated structure.
Furthermore, the inner side of the inner layer high-strength glass fiber of the lower cover is also provided with a hydrophobic layer for gathering condensed water.
Further, the sections of the upper cover and the lower cover are both arc-shaped structures, wherein a first outer edge is arranged at the edge of the upper cover, and a second outer edge is arranged at the edge of the lower cover; the first outer edge and the second outer edge are both attached to each other and are inclined downwards.
Furthermore, the first outer edge and the second outer edge are both made of high-strength glass fibers, and the first outer edge, the inner-layer high-strength glass fibers and the outer-layer high-strength glass fibers of the upper cover are of an integrated structure; the second outer edge is integrated with the inner-layer high-strength glass fiber and the outer-layer high-strength glass fiber of the lower cover.
Further, the aramid paper honeycomb core material, the carbon fiber laminated plate and the PMI foam core material are sequentially arranged between the inner-layer high-strength glass fiber and the outer-layer high-strength glass fiber of the upper cover from the edge to the center; and the carbon fiber laminated plate is provided with a through threaded hole, and the switch array is fixed on the inner wall of the upper cover through a bolt matched with the threaded hole.
Furthermore, the first outer edge and the second outer edge are provided with through holes which correspond to each other and are used for fixing.
The invention adopts the technical scheme to produce the beneficial effects that:
the invention brings the electric module-switch array into the overall design through the overall appearance design and the structural manufacturability design, so that the electric module-switch array has the electric function and the structural bearing function, thereby reducing the number of parts, optimizing the structural design of the bearing surface, reducing the weight of the cabin body, simultaneously reducing the weight of the cabin body by using large-scale composite materials, further reducing the weight of the cabin body, realizing the aim of light weight and realizing the wave-transmitting efficiency requirement of the antenna which is more than or equal to 90 percent in the working frequency band of 30 MHz-18 GHz.
The overlook of the invention is a round structure, the upper and lower cover connecting flanges are umbrella-shaped, the overall structure adopts modularized and universal design, the design is novel and simple, the whole cabin and the airplane can be quickly installed, and the installation and maintenance of equipment in the cabin are convenient. The application of a large amount of advanced composite materials effectively reduces the weight of the cabin body.
Drawings
Fig. 1 is a schematic structural diagram of an appearance of an embodiment of the present invention.
Fig. 2 is a cross-sectional view of fig. 1.
Fig. 3 is a top view of fig. 1.
Fig. 4 is a schematic structural diagram of the upper cover section material in fig. 1.
Fig. 5 is a schematic structural diagram of the cross-sectional material of the lower cover in fig. 1.
Fig. 6 is a schematic sectional view of the upper housing of fig. 1.
Fig. 7 is a cross-sectional view of the lower housing of fig. 1.
In the figure: 101. the switch array comprises a switch array body 301, a lower cover 302, an upper cover 601, a carbon fiber laminate 602, a PMI foam core material 603, an aramid paper honeycomb core material 604, high-strength glass fibers 201, a first outer edge 202, a second outer edge 605 and a hydrophobic layer.
Detailed Description
The present invention will be further described with reference to the accompanying drawings and specific embodiments.
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings of the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and it is obvious for those skilled in the art that other drawings can be obtained according to these drawings without creative efforts.
In the embodiment, the unmanned helicopter is mainly used as a carrier, the cabin body is circular, and the edge flange of the shape is of an umbrella-shaped structure with good rainproof performance; the nacelle body is connected with the airplane through the upper cover and the switch array by using the metal studs, and the installation is quick, convenient and reliable.
The nacelle body mainly comprises an upper cover 302 and a lower cover 301; the supporting structure assembly inside the cabin body mainly comprises a switch array 101, a pull rod, a supporting plate, an upper connecting column, a lower connecting column and the like, and plays a role in stabilizing the structural rigidity and bearing the antenna as a carrier.
The cabin body is circular in shape, can meet the pneumatic requirements of airborne products to the maximum extent, is concise and compact in overall shape, and can well envelop the cabin structure and the antenna.
The edge mounting flanges of the upper cover and the lower cover are of umbrella-shaped structures, so that the rainproof effect can be achieved, the sealing requirement is reduced, and meanwhile, the installation and the transportation of the whole pod can be facilitated for personnel; the lower part of the nacelle (namely the bottom of the lower cover) is provided with a small hole which can play the roles of adjusting the pressure difference inside and outside the cabin and draining condensed water.
The nacelle body is connected with the airplane through the bolt at the top of the nacelle body and the belly in a threaded connection mode, and the connection mode is fast and reliable. The top of the cabin body is of a composite material laminated plate structure, so that the strength of a connecting surface can be improved; the upper cover, the lower cover and the supporting parts in the cabin are in modular design, all the parts and the components are in threaded connection through fasteners, and the design is easy to disassemble, assemble and maintain.
The switch array is taken into the structural design of the cabin body besides being independently used as an electrical functional part, and also used as a connecting and bearing unit. Designing a threaded through hole at the edge of the switch array for mounting an airplane docking stud; a threaded blind hole is designed on the side vertical surface of the switch array and used for installing a pull rod; and a threaded blind hole is designed in the center of the bottom surface of the switch array and used for installing a connecting column. The design can reduce the number of parts and optimize the design of the butt joint surface of the upper cover, thereby playing a role in reducing weight.
The main structural component of the nacelle body is made of composite materials. The upper cover and the lower cover are of a composite sandwich structure and mainly comprise S-level high-strength glass fibers, PMI, aramid fiber paper honeycombs and the like; the pull rod, the support plate, the upper connecting column, the lower connecting column and the like are of S-level high-strength glass fiber laminated plate structures.
Fig. 1 is a general outline diagram of an unmanned aerial vehicle pod according to an embodiment of the invention, and as shown in fig. 1, the pod is circular in general outline, and has dimensions of 1090mm × 406mm, so that aerodynamic requirements of airborne products can be met to the maximum extent, the overall outline is simple and compact, and equipment such as an in-cabin structure and an antenna can be well enveloped.
The butt joint flange of the upper cover and the lower cover of the cabin body is umbrella-shaped, can play a role in preventing rain, reduces the sealing requirement, and can be used as a handle to facilitate installation and transportation; the lower part of the nacelle is partially concave, and the concave center is provided with
The small holes can play a role in adjusting the pressure difference inside and outside the cabin and draining condensed water. The sections of the upper cover and the lower cover are both arc-shaped structures, wherein a first outer edge 201 is arranged at the edge of the upper cover, and a second outer edge 202 is arranged at the edge of the lower cover; the first outer edge and the second outer edge are both attached to each other and are inclined downwards.
Fig. 2 is a cross-sectional view according to one embodiment of the present invention. It can be seen from the figure that the switch array in the cabin body is fixed on the upper cover, wherein the inside can be provided with an antenna, a low-section antenna, a middle-section antenna, a high-section antenna, a monitoring antenna and the like which are used for realizing the functions of the ultra-wideband direction-finding antenna array. The cabin body mainly comprises an upper cabin body cover and a lower cabin body cover, and the metal studs for fixing the switch array and the upper cover are exposed at the top of the cabin body.
The nacelle body is connected with the airplane through the bolt at the top of the nacelle body and the belly in a threaded connection mode, and the connection mode is fast and reliable. The upper cover, the lower cover and the supporting parts in the cabin are in modular design, all the parts and the components are in threaded connection through fasteners, and the design is easy to disassemble, assemble and maintain.
Fig. 3 is a top view structural view of an upper cover according to one embodiment of the present invention. As can be seen from the figure, the aramid paper honeycomb core material and the carbon fiber laminate are both in a ring structure, and the PMI foam core material 602 is in a circular structure.
Fig. 4 and 5 are material structure composition diagrams of the embodiment, and it can be seen from the diagrams that the upper cover and the lower cover both comprise an inner layer high-strength glass fiber 604, an aramid paper honeycomb core material 603 and an outer layer high-strength glass fiber which are sequentially laminated from inside to outside; the aramid paper honeycomb core material, the carbon fiber laminated plate and the PMI foam core material are sequentially arranged between the inner-layer high-strength glass fiber and the outer-layer high-strength glass fiber of the upper cover from the edge to the center; the inner side of the inner layer high-strength glass fiber of the lower cover is also provided with a hydrophobic layer for gathering condensed water. In this embodiment, the material of the water-repellent layer 605 is resin.
Fig. 6 is a schematic view of an upper cover of a cabin according to an embodiment of the invention, and fig. 7 is a schematic view of a lower cover of the cabin according to an embodiment of the invention. As can be seen from the figure, the upper cover and the lower cover of the cabin body are both of composite sandwich structures. Wherein the main materials of the upper cover are as follows: the composite material comprises a carbon fiber laminated board, a PMI foam core material, an aramid fiber honeycomb core material and S-level high-strength glass fiber, and is prepared by combining a front skin autoclave molding process and a mold-assembling curing furnace process. The use of the material and the structural process can effectively reduce the weight of the cover while ensuring the strength. The cabin body lower cover is required to meet the requirement of electric wave transmission performance except for certain rigidity, the cabin body lower cover is mainly made of S-level high-strength glass fibers and aramid honeycomb core materials, a skin-sandwich structure mode is adopted, the thicknesses of inner and outer skins are 0.3mm and 0.2mm respectively, S-level high-strength glass fibers are sandwiched by 4.5mm aramid paper honeycombs, and the selected materials and the structural process form not only can meet the requirement of electric performance, but also can greatly reduce the weight of products.
The working frequency range of the antenna unit in the cabin is 30 MHz-18 GHz. The wave-transparent rate of the cabin body is more than or equal to 90 percent.
The above description is only a preferred embodiment of the present invention, and all equivalent changes and modifications within the scope of the claims of the present invention should be covered by the claims of the present invention.
Claims (8)
1. An airborne lightweight composite material direction-finding antenna array pod body comprises an upper cover, a lower cover and a switch array, wherein the upper cover and the lower cover are buckled to form a pod body; the switch array is positioned in the cabin body and is fixed on the top of the inner wall of the upper cover through bolts; the high-strength glass fiber reinforced plastic composite material is characterized in that the upper cover and the lower cover are of a laminated structure, and both the upper cover and the lower cover comprise inner-layer high-strength glass fibers, aramid paper honeycomb core materials and outer-layer high-strength glass fibers which are sequentially laminated from inside to outside; wherein the thickness of the inner layer high-strength glass fiber is 0.3mm, the thickness of the outer layer high-strength glass fiber is 0.2mm, and the thickness of the aramid paper honeycomb core material is 4.5 mm.
2. The nacelle body of an airborne light weight composite direction finding antenna array as claimed in claim 1 wherein the bottom of the lower shroud is provided with drain holes for regulating pressure differential and draining condensed water.
3. The nacelle body of airborne lightweight composite direction-finding antenna array pod of claim 2, wherein the inner wall of the drain hole is provided with a high-strength glass fiber layer, and the high-strength glass fiber layer is integrated with the inner-layer high-strength glass fiber and the outer-layer high-strength glass fiber of the lower cover.
4. The nacelle body of the airborne light-weight composite direction-finding antenna array nacelle of claim 2, wherein a hydrophobic layer for collecting condensed water is further arranged on the inner side of the inner high-strength glass fiber of the lower cover.
5. The nacelle body of the airborne lightweight composite direction-finding antenna array nacelle according to claim 1, wherein the upper cover and the lower cover are both arc-shaped in cross section, wherein a first outer edge is arranged at the edge of the upper cover, and a second outer edge is arranged at the edge of the lower cover; the first outer edge and the second outer edge are both attached to each other and are inclined downwards.
6. The nacelle body of the airborne lightweight composite direction-finding antenna array nacelle of claim 5, wherein the first outer edge and the second outer edge are both made of high-strength glass fibers, and the first outer edge is integrated with the inner-layer high-strength glass fibers and the outer-layer high-strength glass fibers of the upper cover; the second outer edge is integrated with the inner-layer high-strength glass fiber and the outer-layer high-strength glass fiber of the lower cover.
7. The nacelle body of the airborne lightweight composite direction-finding antenna array nacelle according to claim 5, wherein the nacelle body comprises an aramid paper honeycomb core material, a carbon fiber laminate and a PMI foam core material in sequence from edge to center between the inner-layer high-strength glass fiber and the outer-layer high-strength glass fiber of the upper cover; and the carbon fiber laminated plate is provided with a through threaded hole, and the switch array is fixed on the inner wall of the upper cover through a bolt matched with the threaded hole.
8. The nacelle body of airborne lightweight composite direction-finding antenna array nacelle according to claim 5, wherein the first outer edge and the second outer edge are provided with through holes corresponding to each other and used for fixing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111493534.9A CN114056589A (en) | 2021-12-08 | 2021-12-08 | Airborne lightweight composite material direction-finding antenna array nacelle body |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111493534.9A CN114056589A (en) | 2021-12-08 | 2021-12-08 | Airborne lightweight composite material direction-finding antenna array nacelle body |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114056589A true CN114056589A (en) | 2022-02-18 |
Family
ID=80229435
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202111493534.9A Pending CN114056589A (en) | 2021-12-08 | 2021-12-08 | Airborne lightweight composite material direction-finding antenna array nacelle body |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114056589A (en) |
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2021
- 2021-12-08 CN CN202111493534.9A patent/CN114056589A/en active Pending
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