CN116534266B - Airborne high-rigidity and lightweight electronic nacelle body and assembly method - Google Patents
Airborne high-rigidity and lightweight electronic nacelle body and assembly method Download PDFInfo
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- CN116534266B CN116534266B CN202310819932.8A CN202310819932A CN116534266B CN 116534266 B CN116534266 B CN 116534266B CN 202310819932 A CN202310819932 A CN 202310819932A CN 116534266 B CN116534266 B CN 116534266B
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- girder
- frame
- upper girder
- lifting lug
- nacelle
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- 230000003014 reinforcing effect Effects 0.000 claims abstract description 89
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- 238000007789 sealing Methods 0.000 claims description 13
- 239000002184 metal Substances 0.000 claims description 4
- 239000004636 vulcanized rubber Substances 0.000 claims description 4
- 230000008569 process Effects 0.000 claims description 3
- 239000011248 coating agent Substances 0.000 claims description 2
- 238000000576 coating method Methods 0.000 claims description 2
- 238000007493 shaping process Methods 0.000 claims description 2
- 230000000694 effects Effects 0.000 description 9
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 8
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 4
- 230000005540 biological transmission Effects 0.000 description 4
- 238000009434 installation Methods 0.000 description 4
- 238000005457 optimization Methods 0.000 description 4
- 238000005452 bending Methods 0.000 description 3
- 238000009826 distribution Methods 0.000 description 3
- 239000003292 glue Substances 0.000 description 3
- 239000007788 liquid Substances 0.000 description 3
- 230000002787 reinforcement Effects 0.000 description 3
- 125000006850 spacer group Chemical group 0.000 description 3
- 239000000725 suspension Substances 0.000 description 3
- 230000007704 transition Effects 0.000 description 3
- 239000013585 weight reducing agent Substances 0.000 description 3
- 229910000831 Steel Inorganic materials 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 2
- 239000002131 composite material Substances 0.000 description 2
- 238000001816 cooling Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 229910052757 nitrogen Inorganic materials 0.000 description 2
- 239000007787 solid Substances 0.000 description 2
- 229910001220 stainless steel Inorganic materials 0.000 description 2
- 239000010935 stainless steel Substances 0.000 description 2
- 239000010959 steel Substances 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000000903 blocking effect Effects 0.000 description 1
- 238000007796 conventional method Methods 0.000 description 1
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- 230000014759 maintenance of location Effects 0.000 description 1
- 238000005192 partition Methods 0.000 description 1
- 238000004080 punching Methods 0.000 description 1
- 238000010008 shearing Methods 0.000 description 1
- 239000003351 stiffener Substances 0.000 description 1
- 238000005728 strengthening Methods 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS 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
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Abstract
The invention belongs to the technical field of avionics pods, and particularly relates to an airborne high-rigidity and lightweight electronic pod body and an assembly method thereof. The technical proposal is as follows: an airborne high-rigidity and lightweight electronic nacelle cabin comprises an upper girder, a lower girder, a side cover plate connected between the upper girder and the lower girder, a plurality of frames connected between the upper girder and the lower girder, and a lifting lug assembly connected on the upper girder; the main bodies of the upper girder and the lower girder are thin walls, a plurality of reinforcing ribs which are transversely arranged and a plurality of reinforcing ribs which are longitudinally arranged are arranged on the thin walls, the upper girder is provided with a thickened reinforcing area, and the lifting lug assembly is connected with the reinforcing area of the upper girder; the main body of the frame is a thin plate, and flanging is arranged around the thin plate. The invention provides an airborne high-rigidity and lightweight electronic nacelle body and an assembly method.
Description
Technical Field
The invention belongs to the technical field of avionics pods, and particularly relates to an airborne high-rigidity and lightweight electronic pod body and an assembly method thereof.
Background
The airborne electronic nacelle is generally hung on the bottom surface of an airplane wing or a fuselage, and can realize the expansion of the electronic functions of the airplane along with the airplane. Because of the flexible mounting characteristic, the universality is strong. The nacelle body is a supporting structure of the electronic nacelle, and electronic equipment is installed inside the nacelle body, so that electronic functions are realized.
The nacelle body in the prior art is of a conventional truss structure and mainly comprises a frame, a beam, a suspension structure, a skin and an antenna housing, wherein the frame formed by the frame and the beam is of a main bearing structure, so that the nacelle body bears the force load of internally installed equipment and the nacelle body, and the strength and the rigidity of the nacelle structure are greatly affected. The suspension structure is located in a suspension area of the nacelle and connects the nacelle and the carrier. The hanging structure is generally composed of a lifting lug and a swinging stopping area. The skin and the antenna housing assist in bearing force and isolate the electronic equipment from the external environment, so that the electronic equipment is protected. The radome also has a wave-transmitting function, so that electromagnetic wave signals in a required frequency band can pass through. A flap is designed on the skin of the nacelle for mounting and maintaining the electronic equipment. The electronics are mounted on the upper beam, lower beam or frame of the nacelle. However, as electronic pods become more powerful, the integration requirements become higher and higher, and the pod body needs to be increased in strength and rigidity and reduced in weight.
The conventional method of increasing the rigidity of the nacelle body is to increase the support or increase the thickness of the material, which is contrary to the weight reduction requirements of the nacelle body, and the effect is limited. The nacelle needs to be optimized in terms of its structural form. Existing nacelle technology, such as: patent application number: 202210661632.7, a cabin reinforcing rib optimization method, a cabin reinforcing rib optimization device and cabin reinforcing rib optimization equipment. The patent performs performance analysis on initial structural parameters of the cabin reinforcing ribs, and performs parameter optimization on a cabin reinforcing rib model to be optimized. This patent optimizes the structure from local stiffener, does not take into account the rigidity of the whole nacelle body, and has limited effect. Patent number: CN103523240B, aviation geophysical prospecting equipment supports the nacelle structure. The nacelle described in this patent is integrated with the aircraft wing, the structure is connected to the wing by means of the front and rear girders, the profile conforms to the smooth transition of the wing, and there is no hanging form. Patent number: CN114229010B, a low cost simple unmanned aerial vehicle nacelle structure. The design is a nacelle for throwing, which has a simpler structure form and is used for loading cargoes. Patent application number: 202110018157.7A composite nacelle structure reduces the weight of the nacelle body but has a through structure inside and low rigidity.
The above patents focus on the functional servicing of the nacelle by the nacelle structure, either by reducing the weight of the nacelle through composite materials, or by locally optimizing the added local stiffness, without considering the stiffness of the structure as a whole, in particular the lateral stiffness of the nacelle, and therefore with limited scope of use.
Disclosure of Invention
In order to solve the problems in the prior art, the invention aims to provide an airborne high-rigidity and lightweight electronic nacelle body and an assembly method.
The technical scheme adopted by the invention is as follows:
an airborne high-rigidity and lightweight electronic nacelle cabin comprises an upper girder, a lower girder, a side cover plate connected between the upper girder and the lower girder, a plurality of frames connected between the upper girder and the lower girder, and a lifting lug assembly connected on the upper girder; the main bodies of the upper girder and the lower girder are thin walls, a plurality of reinforcing ribs which are transversely arranged and a plurality of reinforcing ribs which are longitudinally arranged are arranged on the thin walls, the upper girder is provided with a thickened reinforcing area, and the lifting lug assembly is connected with the reinforcing area of the upper girder; the main body of the frame is a thin plate, and flanging is arranged around the thin plate.
The main bodies of the upper girder and the lower girder are thin, and the main body of the frame is a thin plate, so that the nacelle body is weight-reduced, and the light weight design is realized. The upper girder is provided with a reinforcing area for connecting the lifting lug assembly, so that the main bearing area of the nacelle body is reinforced, and the force transmission effect is effectively improved. The upper girder and the lower large number of thin walls are provided with a plurality of reinforcing ribs which are transversely arranged and a plurality of reinforcing ribs which are longitudinally arranged, so that the rigidity of the upper girder and the lower large number of thin walls is improved. The main body of the frame is a thin plate, and flanging is arranged on the periphery of the thin plate, so that the lateral swing resistance of the nacelle body is enhanced. On the whole, on the basis of guaranteeing the lightweight, through setting up the turn-ups of reinforcing district, strengthening rib and frame, the overall rigidity of nacelle cabin body obtains improving.
As a preferable scheme of the invention, the type of the frame comprises a lifting lug frame, the upper end of the lifting lug frame is provided with a horizontal butt joint surface, the horizontal butt joint surface is connected with the bottom surface of the reinforcing area in a matched manner, the lower end of the lifting lug frame is provided with an avoidance groove for avoiding the reinforcing rib on the lower girder, the sheet of the lifting lug frame is provided with a plurality of wire passing pipe holes, and the edges of the wire passing pipe holes are provided with flanges. The horizontal butt joint surface is reliably connected with the reinforcing area, and the situation that a connecting piece for connecting a lifting lug frame is independently arranged on an upper girder is avoided. And the thickness of the reinforcing area is larger, so that the connection reliability of the lifting lug frame can be enhanced. The horizontal butt joint surface is connected with the reinforcing area through the fastener after being attached, so that the contact area of the horizontal butt joint surface and the reinforcing area is increased. The fastener between the horizontal butt joint face and the reinforcing area is arranged around the lifting lug assembly, the arrangement quantity and arrangement range of the fastener are increased, and connection reliability between the horizontal butt joint face and the reinforcing area is further improved.
As a preferable scheme of the invention, the lifting lug frame is provided with a longitudinal butt joint surface which is perpendicular to the horizontal butt joint surface, and the longitudinal butt joint surface is connected with the side surface of the reinforcing area. The upper end of lug frame not only is connected with the enhancement district bottom surface, and the level butt joint face on the lug frame still is connected with the side in enhancement district, further improves the connection reliability.
As a preferable scheme of the invention, the frame further comprises a bulkhead, the upper end of the bulkhead is connected with the transverse reinforcing rib of the upper girder, the lower end of the bulkhead is provided with an avoidance groove for avoiding the longitudinal reinforcing rib on the lower girder, and the thin plate of the bulkhead is provided with a plurality of wire passing pipe holes. The bulkhead is connected with the transverse reinforcing rib on the upper girder, so that the transverse reinforcing rib is effectively utilized.
As a preferable scheme of the invention, through holes are arranged at the bottoms of the transverse reinforcing ribs of the lower girder, and drain holes are arranged at the two ends of the lower girder. The bottom of the lower girder is provided with a drain hole to prevent the condensed water in the hanging cabin from accumulating to cause a short circuit. In order to ensure that the accumulated water is communicated among the grooves, through holes are arranged at the bottoms of the transverse reinforcing ribs of the lower girder.
As a preferable scheme of the invention, the frame further comprises an end frame, wherein the end frame is respectively connected with the ends of the upper girder and the lower girder, the other side of the end frame is connected with an antenna housing, and the upper girder, the lower girder, the side cover plate and the end frame are all made of metal. A double-pass connector is arranged on a thin plate of the end frame, the front side of the double-pass connector is directly in blind insertion with the antenna array, and the rear side of the double-pass connector is connected with a cable. The flange of the connector is provided with an electromagnetic sealing gasket, so that the thin plate of the end frame realizes electromagnetic sealing.
As a preferable scheme of the invention, an electromagnetic sealing gasket is arranged at the joint of the end frame and the antenna housing to prevent electromagnetic leakage.
As a preferable scheme of the invention, the lifting lug assembly comprises a lifting lug, a connecting hole is formed in the reinforcing area, a sleeve is connected in the connecting hole, the sleeve is connected with the lifting lug, and a weight reducing groove is dug at the bottom of the lifting lug. Under the condition that strength is not affected, a weight-reducing groove is dug at the bottom of the lifting lug, and a die is pulled out in the groove, so that the stress distribution of threads on the lifting lug is effectively optimized.
As a preferable scheme of the invention, the upper girder is provided with a swing stopping cushion block which is attached to a supporting rod of the aircraft hanger. The anti-swing cushion block is attached to the supporting rod of the hanger to prevent the nacelle from swinging left and right, and plays a role in resisting bending moment in the hanging structure.
An assembly method of an airborne high-rigidity and lightweight electronic nacelle comprises the following steps:
s1: fixing each frame in the nacelle body to the assembly truss;
s2: mounting a lifting lug assembly on the upper girder;
s3: the upper girder and the lower girder are respectively assembled with the frame in trial, and if interference exists at the joint, the joint structure is repaired;
s4: fixing the positions of the upper girder, the lower girder and the frame by using a process clamp, and matching with a mounting pre-hole, reaming and hinging for forming;
s5: the upper girder and the lower girder are disassembled, vulcanized glue is coated on the joint surfaces of the frames and the upper girder and the lower girder respectively, and then the upper girder, a plurality of frames and the lower girder are installed;
s6: coating vulcanized rubber on the joint of the upper girder and the frame and the side cover plate respectively, shaping by using a tooling die, and curing for more than 48 hours;
s7: and (5) demolding.
The beneficial effects of the invention are as follows:
the main bodies of the upper girder and the lower girder are thin, and the main body of the frame is a thin plate, so that the nacelle body is weight-reduced, and the light weight design is realized. The upper girder is provided with a reinforcing area for connecting the lifting lug assembly, so that the main bearing area of the nacelle body is reinforced, and the force transmission effect is effectively improved. The upper girder and the lower large number of thin walls are provided with a plurality of reinforcing ribs which are transversely arranged and a plurality of reinforcing ribs which are longitudinally arranged, so that the rigidity of the upper girder and the lower large number of thin walls is improved. The main body of the frame is a thin plate, and flanging is arranged on the periphery of the thin plate, so that the lateral swing resistance of the nacelle body is enhanced. On the whole, on the basis of ensuring the light weight, the overall rigidity of the nacelle body is improved through the arrangement of the reinforcing area, the reinforcing ribs and the flanging of the frame.
Drawings
FIG. 1 is a schematic view of the first direction of the present invention with one side cover removed;
FIG. 2 is an enlarged view of a portion of FIG. 1 at A;
FIG. 3 is a partial enlarged view at B in FIG. 1;
FIG. 4 is a schematic view of the structure of the lifting lug;
FIG. 5 is a schematic view of the structure of the upper girder and the sleeve;
FIG. 6 is a schematic view of a shackle frame;
FIG. 7 is a schematic view of the second direction of the present invention with one side cover removed;
FIG. 8 is an enlarged view of a portion of FIG. 7 at C;
FIG. 9 is a schematic view of the shackle frame and upper girder at D in FIG. 7;
FIG. 10 is a schematic view of the structure of the lower girder;
fig. 11 is a schematic view of the structure of the present invention when the built-in device is installed.
In the figure: 1-side cover plate; 2-upper girder; 3-a lower girder; 4-lifting lug assembly; 5-lifting lug frames; 6-a spacer; 7-end frames; 8-radome; 9-installing equipment; 21-a reinforcing zone; 22-a swing stopping cushion block; 31-a drain hole; 41-lifting lugs; 42-sleeve; 43-a weight-reducing tank; 51-a horizontal butt surface; 52-longitudinal abutment; 71-corner pieces; a 72-connector; 91-an adapter; a1-thin wall; a2-a sheet; a3-avoiding grooves; a4-a wire passing pipe hole; a 5-an antenna array; a6-reinforcing ribs.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the embodiments of the present invention more apparent, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention, and it is apparent that the described embodiments are some embodiments of the present invention, but not all embodiments of the present invention. The components of the embodiments of the present invention generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations.
Thus, the following detailed description of the embodiments of the invention, as presented in the figures, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention. It should be noted that, without conflict, the embodiments of the present invention and features of the embodiments may be combined with each other.
As shown in fig. 1 and 5, the airborne high-rigidity and lightweight electronic nacelle of the embodiment comprises an upper girder 2, a lower girder 3, a side cover plate 1 connected between the upper girder 2 and the lower girder 3, a plurality of frames connected between the upper girder 2 and the lower girder 3, a lifting lug assembly 4 connected on the upper girder 2 and antenna covers on two sides; the main bodies of the upper girder 2 and the lower girder 3 are thin walls a1, a plurality of reinforcing ribs a6 which are transversely arranged and a plurality of reinforcing ribs which are longitudinally arranged are arranged on the thin walls a1, the upper girder 2 is provided with a thickened reinforcing area 21, and the lifting lug assembly 4 is connected with the reinforcing area 21 of the upper girder 2; the main body of the frame is a thin plate a2, and flanging is arranged around the thin plate a 2.
According to the invention, the main bodies of the upper girder 2 and the lower girder 3 are thin walls a1, and the main body of the frame is a thin plate a2, so that the nacelle body is reduced in weight, and the light weight design is realized. The upper girder 2 is provided with a reinforcing area 21 for connecting the lifting lug assembly 4, so that the main bearing area of the nacelle body is reinforced, and the force transmission effect is effectively improved. The upper girder 2 and the lower large number of thin walls a1 are provided with a plurality of reinforcing ribs a6 which are arranged transversely and a plurality of reinforcing ribs which are arranged longitudinally, so that the rigidity of the upper girder 2 and the lower large number of the thin walls a1 is improved. The main body of the frame is a thin plate a2, and flanging is arranged on the periphery of the thin plate a2, so that the side swing resistance of the nacelle body is enhanced. On the whole, on the basis of ensuring the light weight, the overall rigidity of the nacelle body is improved through the arrangement of the reinforcing areas 21, the reinforcing ribs a6 and the flanging of the frame.
Specifically, as shown in fig. 2 to 4, the lifting lug assembly 4 is connected with the hanger of the aircraft, and the lifting lug assembly 4 is composed of 2 lifting lugs 41, 2 sleeves 42 and 4 anti-swing cushion blocks 22. The reinforcing area 21 is provided with a connecting hole, a sleeve 42 is connected in the connecting hole, and the sleeve 42 is in threaded connection with the lifting lug 41. The bottom of the sleeve 42 is provided with a flange to prevent the sleeve 42 from being pulled out from the upper side by the lifting lugs 41. The lifting lug assembly 4 is made of high-strength and high-hardness stainless steel, and has the strength and anti-corrosion functions. When the hanger is hung, the hanger hooks the lifting lug 41 through the inner hook, so that the lifting lug 41 can only bear the force load, but cannot bear the bending moment load. The anti-swing cushion block 22 is attached to the support rod of the hanger near the two lifting lugs 41 to prevent the nacelle from swinging left and right and play a role in resisting bending moment. The anti-swing cushion block 22 is fixed with the upper girder 2 through screws, and the load of the bearing support rod is transferred to the upper girder 2 and then transferred to other parts of the nacelle. The lifting lug 41 is made of stainless steel with high density, and under the condition that strength is not affected, the weight-reducing groove 43 is dug at the bottom of the lifting lug 41, and a die is pulled in the weight-reducing groove 43, so that the stress distribution of threads on the lifting lug 41 is effectively optimized.
As shown in fig. 5, the upper girder 2 has a structure of an integrally machined elongated structure. For weight reduction, the combined structure of the thin wall a1 and the reinforcing rib a6 is designed, and the wall thickness is 2-4 mm. The two areas of the middle section of the upper girder 2 connected with the lifting lugs 41 are reinforcing areas 21, and the thickness of the reinforcing areas 21 is thicker and is made of solid metal. The thickness of the transition region of the solid reinforcing region 21 and the thin wall a1 transitions uniformly. The connecting hole of the reinforcing area 21 is provided with a sleeve 42, and the sleeve 42 is in interference fit with the connecting hole of the reinforcing area 21 after being cooled and contracted by liquid nitrogen at low temperature. The reinforcing area 21 is provided with a butt joint surface and a mounting hole which are fixed with the lifting lug frame 5, and the structure and the fastener are combined to bear force, so that stress concentration caused by independent stress of the bolts is avoided.
The kinds of frames include a shackle frame 5, a spacer frame 6 and an end frame 7. In order to increase the lateral stiffness of the nacelle body, the frame is in the form of a box structure. The box body type structure is characterized in that the web plate is an integral thin plate a2, and the thickness range is 0.5-6 mm according to different bearing of the nacelle body. The integral sheet a2 has strong shearing action, and the rigidity of the structure can be improved in the whole nacelle structure.
Specifically, as shown in fig. 6 to 8, the upper end of the shackle frame 5 is provided with a horizontal abutment surface 51, and the horizontal abutment surface 51 is screwed to the bottom surface of the reinforcing region 21. The lifting lug frame 5 is provided with a longitudinal butt joint surface 52 perpendicular to the horizontal butt joint surface 51, and the longitudinal butt joint surface 52 is connected with the side surface of the reinforcing area through a fastener. The upper end of lug frame 5 is connected with the bottom surface of reinforcing district 21 not only, and the vertical butt joint face 52 on the lug frame 5 still is connected with the side of reinforcing district 21, further improves the connection reliability. The horizontal abutment surface 51 also prevents serious conditions of the nacelle coming off as a result of the interference fit failure of the sleeve 42 with the attachment hole and accidental drop. The horizontal abutment surface 51 and the longitudinal abutment surfaces 52 on both sides form a groove structure which allows the reinforcement area 21 on the upper girder 2 to be avoided.
The horizontal abutment surface 51 is reliably connected to the reinforcing area 21, avoiding the separate provision of a connecting piece for connecting the shackle frame 5 to the upper girder 2. And, the thickness of the reinforcing area 21 is larger, so that the connection reliability of the lifting lug frame 5 can be enhanced. The horizontal abutting surface 51 is attached to the reinforcing section 21 and then connected by a fastener, so that the contact area between the two is increased. The fasteners between the horizontal abutment surface 51 and the reinforcing section 21 are disposed around the shackle assembly 4, and the number and arrangement range of the fasteners are increased, further improving the connection reliability between the horizontal abutment surface 51 and the reinforcing section 21.
According to the wiring requirements of cables and liquid cooling pipes of the internal equipment of the nacelle, corresponding wire passing pipe holes a4 are reserved on the thin plate a2 of the lifting lug frame 5, and reinforcing flanging is designed around the wire passing pipe holes a4 for local reinforcement. The conventional frame structure is a ring structure, and compared with the conventional frame, the structure of the frame provided by the invention has the advantages that the position of the wire passing pipe hole a4 is easy to adjust, and the strength of the frame is not easy to damage.
In order to enable the reinforcing rib a6 of the lower girder 3 to be continuous at the butt joint position with the lower girder 3, the bottom of the lifting lug frame 5 and the bottom of the bulkhead 6 are provided with avoiding grooves a3.
Specifically, as shown in fig. 7 and 9, the spacer frame 6 has a smaller bearing force than the shackle frame 5, and functions as a structural shape retention. The structure of the partition frame 6 is a single-sided box structure, and only one side is provided with a flanging. The upper end of the bulkhead 6 is connected with the transverse reinforcing rib a6 of the upper girder 2, so that the connecting point is increased, and the connection is more reliable. The lower end of the bulkhead 6 is also provided with an avoidance groove a3 for avoiding the longitudinal reinforcing rib a6 on the lower girder 3, and a plurality of wire passing pipe holes a4 are arranged on the thin plate a2 of the bulkhead 6.
Specifically, as shown in fig. 3, the end frame 7 is also in a box body type structure, and may be a single flanging or a double flanging. The end frame 7 is connected to the antenna housing 8 in addition to the upper girder 2, the lower girder 3 and the side cover plate 1, and the antenna array a5 is generally connected to the middle of the end frame 7. At the connection of the upper girder 2, the lower girder 3 and the end frame 7, the longitudinal reinforcing ribs a6 of the upper girder 2, the lower girder 3 are connected with the ribs of the end frame 7 through the corner pieces 71 to transmit load. The connection of the end frame 7 and the antenna housing 8 is provided with a rubber pad and an electromagnetic sealing pad to prevent water and electromagnetic leakage. A two-way connector 72 is provided on the sheet a2 of the end frame 7, and the front side of the connector 72 is directly blind-plugged with the antenna array a5, and the rear side of the connector 72 is connected with a cable. The flange of the connector 72 is provided with an electromagnetic sealing gasket, so that the electromagnetic sealing of the whole end frame 7 is realized, the upper girder, the lower girder, the side cover plate and the end frame are continuous in metal, and an electric continuous sealing body is formed at the part except the antenna housing, so that the electromagnetic sealing effect can be achieved. The rubber pad and the electromagnetic sealing pad are made into a whole, waterproof layers are arranged on two sides, and a conductive layer is arranged in the middle.
Further, as shown in FIG. 10, the lower girder 3 and the upper girder 2 are similar in structure except that the reinforcing region 21 is not provided, and the thickness of the lower girder 3 and the reinforcing rib a6 are also relatively thin, typically 1.5 to 3mm. The bottom of the transverse reinforcing rib a6 of the lower girder 3 is provided with a through hole, and both ends of the lower girder 3 are provided with drain holes 31. The bottom of the lower girder 3 is provided with a drain hole 31 to prevent the condensed water in the hanging cabin from accumulating to cause short circuit. In order to allow water to communicate between the various channels, through holes are provided in the bottom of the transverse reinforcing bars a6 of the lower girder 3. An L-shaped wind cap is arranged at the bottom of the drain hole 31, and the outlet is backwards, so that air is prevented from flowing backwards to blow water into the cabin during flying.
In order to avoid blocking drainage by the lifting lug frame 5 and the bulkhead 6, when gaps can be reserved between the avoidance groove a3 of the lifting lug frame 5 and the avoidance groove a3 of the bulkhead 6 and the longitudinal reinforcing rib a6 of the lower girder 3, the avoidance groove a3 can also give consideration to the effect of communicating all cabin sections. When condensed water exists in the nacelle, the condensed water cannot accumulate in one nacelle section to cause the accident of short circuit of equipment cables.
As shown in fig. 11, the interior equipment 9 of the nacelle body is installed between the upper girder 2 and the lower girder 3, and is connected by an adapter 91. The built-in equipment 9 is connected with the upper girder 2 and the lower connection respectively, so that the rigidity of the whole nacelle can be increased, and the installation of the built-in equipment 9 is reliable.
The assembly method of the airborne high-rigidity and lightweight electronic nacelle body of the embodiment comprises the following steps:
s1: preparing a nacelle assembly truss and an assembly tooling die, wherein the assembly truss is used for fixing the relative positions of each frame of the nacelle, and the tooling die is used for assisting in punching or smearing waterproof glue;
fixing each frame in the nacelle body to the assembly truss;
s2: the sleeve 42 is placed in liquid nitrogen for cooling, the sleeve is contracted to reduce the size, and then the lifting lug 41 is connected with the sleeve 42;
s3: the upper girder 2 and the lower girder 3 are respectively assembled with the frame in trial, and if interference exists at the joint, the joint structure is repaired;
s4: fixing the positions of the upper girder 2, the lower girder 3 and the frame by using a process clamp, and matching with a mounting pre-hole, reaming and hinging for forming;
s5: the upper girder 2 and the lower girder 3 are disassembled, vulcanized glue is coated on the joint surfaces of the frames and the upper girder 2 and the lower girder 3 respectively, and then the upper girder 2, a plurality of frames and the lower girder 3 are installed;
s6: the upper girder 2 and the frame are respectively coated with vulcanized rubber at the joint of the side cover plate 1 and the installation of the antenna housing 8, and are shaped by a tooling die and cured for more than 48 hours;
s7: demolding; and other structures are machined.
The invention is characterized by high rigidity of the nacelle body, reduced weight of the nacelle body and improved electromagnetic sealing effect.
First, in terms of high rigidity, the main bearing area of the nacelle body is designed to be relatively strong, and the main bearing area contributes to the rigidity of the whole nacelle. The connection area between the upper girder 2 and the lifting lug assembly 4 is a reinforcing area 21, which plays a role in local reinforcement. The anti-sway pad 22 is designed as a relatively high hardness steel structure. The structure near the anti-swing area of the upper girder 2 is designed into thicker reinforcing ribs a6, so that the local rigidity is increased, and the force transmission effect is effectively improved. The structural form of the frame is a box body type structure, and the integral side swing resistance is enhanced. Since the middle web of the frame is a thin plate a2, the wire pipe holes a4 are partially opened, and the weight is further reduced.
Secondly, in terms of weight reduction, the nacelle non-bearing area is reduced in weight. The weight-reducing groove 43 is dug in the middle of the lifting lug 41, the weight of the steel structure is reduced, and the die is pulled out in the weight-reducing groove 43, so that the stress distribution of threads on the lifting lug 41 is effectively optimized. Because the nacelle main bearing area is relatively rigid, other structures can be properly lightened, and the influence on the overall rigidity of the nacelle is small. The installation of the built-in equipment 9 adopts an up-and-down installation mode, the supporting points of the nacelle body and the built-in equipment 9 are increased, and the rigidity of the nacelle body and the built-in equipment 9 is enhanced, so that the material can be reduced when the equipment structure is designed, and the weight of the whole system is reduced.
After the rigidity of the nacelle body is improved, the vibration frequency is improved, the resonance probability is reduced, and the reliability of the nacelle is enhanced. The electromagnetic sealing structure is designed on the nacelle structure, which is beneficial to the electromagnetic compatibility of the whole nacelle.
The integral natural frequency of the nacelle is improved by 15%, the weight is reduced by 8%, and the nacelle is resistant to marine environment and completely meets the electrical performance requirements.
The invention is not limited to the above-described alternative embodiments, and any person who may derive other various forms of products in the light of the present invention, however, any changes in shape or structure thereof, all falling within the technical solutions defined in the scope of the claims of the present invention, fall within the scope of protection of the present invention.
Claims (3)
1. An airborne high-rigidity and lightweight electronic nacelle cabin body comprises an upper girder (2), a lower girder (3), a side cover plate (1) connected between the upper girder (2) and the lower girder (3), a plurality of frames connected between the upper girder (2) and the lower girder (3) and a lifting lug assembly (4) connected on the upper girder (2); the method is characterized in that: the main bodies of the upper girder (2) and the lower girder (3) are thin walls (a 1), a plurality of reinforcing ribs (a 6) which are transversely arranged and a plurality of reinforcing ribs which are longitudinally arranged are arranged on the thin walls (a 1), the upper girder (2) is provided with a thickened reinforcing area (21), and the lifting lug assembly (4) is connected with the reinforcing area (21) of the upper girder (2); the main body of the frame is a thin plate (a 2), and flanging is arranged around the thin plate (a 2);
the kinds of the frames comprise lifting lug frames (5); the upper end of the lifting lug frame (5) is provided with a horizontal butt joint surface (51), the horizontal butt joint surface (51) is connected with the bottom surface of the reinforcing area (21) in a matched mode, the lower end of the lifting lug frame (5) is provided with an avoidance groove (a 3) for avoiding a reinforcing rib (a 6) on the lower girder (3), a thin plate (a 2) of the lifting lug frame (5) is provided with a plurality of wire passing pipe holes (a 4), and the edges of the wire passing pipe holes (a 4) are provided with flanging;
the lifting lug frame (5) is provided with a longitudinal butt joint surface (52) perpendicular to the horizontal butt joint surface (51), and the longitudinal butt joint surface (52) is connected with the side surface of the reinforcing area (21);
the fastener between the horizontal butt surface (51) and the reinforcing area (21) is arranged around the lifting lug assembly (4);
the frame comprises a frame body, wherein the frame body comprises a lower girder (3) and a plurality of thin plates (a 2) which are arranged on the lower girder (3), the upper ends of the upper girder (2) are connected with transverse reinforcing ribs (a 6) of the upper girder, the lower ends of the upper girder (2) are provided with avoidance grooves (a 3) for avoiding longitudinal reinforcing ribs (a 6) on the lower girder (3), and a plurality of wire passing holes (a 4) are formed in the thin plates (a 2) of the upper girder (2);
the type of the frame also comprises an end frame (7), wherein the end frame (7) is respectively connected with the ends of the upper girder (2) and the lower girder (3), the other side of the end frame (7) is connected with an antenna housing (8), and the upper girder (2), the lower girder (3), the side cover plate (1) and the end frame (7) are all made of metal; an electromagnetic sealing gasket is arranged at the joint of the end frame (7) and the antenna housing (8); the main body of the end frame (7) is a thin plate, the periphery of the main body is flanged, a bi-pass connector is arranged on the thin plate of the end frame (7), the front side of the connector is directly and blindly inserted with the antenna array, the rear side of the connector is connected with a cable, and an electromagnetic sealing gasket is arranged on a flange of the connector;
the built-in equipment (9) of the nacelle cabin body is arranged between the upper girder (2) and the lower girder (3), and the upper girder (2) and the lower girder (3) are respectively connected with the built-in equipment (9) through the adapter (91);
a swing stopping cushion block (22) which is attached to the support rod of the aircraft hanger is arranged on the upper girder (2);
the lifting lug assembly (4) comprises a lifting lug (41), a connecting hole is formed in the reinforcing area (21), a sleeve (42) is connected in the connecting hole, the sleeve (42) is connected with the lifting lug (41), a weight-reducing groove (43) is formed in the bottom of the lifting lug (41), and an inner cylindrical surface of the weight-reducing groove (43) is formed in a pattern drawing mode.
2. The on-board high-rigidity and lightweight electronic nacelle according to claim 1 wherein: the bottom of the transverse reinforcing rib (a 6) of the lower girder (3) is provided with a through hole, and both ends of the lower girder (3) are provided with drain holes (31).
3. An assembly method of an airborne high-rigidity and lightweight electronic nacelle body is characterized by comprising the following steps of: -a cabin for assembling the onboard high-rigidity and lightweight electronic nacelle according to any one of claims 1 to 2; the method comprises the following steps:
s1: fixing each frame in the nacelle body to the assembly truss;
s2: a lifting lug assembly (4) is arranged on the upper girder (2);
s3: the upper girder (2) and the lower girder (3) are respectively assembled with the frame in a trial mode, and if interference exists at the joint, the joint structure is repaired;
s4: fixing the positions of the upper girder (2), the lower girder (3) and the frame by using a process clamp, and matching with a mounting pre-hole, reaming and hinging for forming;
s5: the upper girder (2) and the lower girder (3) are disassembled, vulcanized rubber is coated on the joints of the frames with the upper girder (2) and the lower girder (3) respectively, and then the upper girder (2), a plurality of frames and the lower girder (3) are installed;
s6: coating vulcanized rubber on the joint of the upper girder (2) and the frame and the side cover plate (1), shaping by using a tooling die, and curing for more than 48 hours;
s7: and (5) demolding.
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