CN213705810U - Hanging rack structure for connecting airplane with plug-in equipment - Google Patents
Hanging rack structure for connecting airplane with plug-in equipment Download PDFInfo
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- CN213705810U CN213705810U CN202022305435.0U CN202022305435U CN213705810U CN 213705810 U CN213705810 U CN 213705810U CN 202022305435 U CN202022305435 U CN 202022305435U CN 213705810 U CN213705810 U CN 213705810U
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Abstract
The hanging rack structure comprises a mounting seat, a vertical beam and a horizontal box section, wherein the mounting seat is fixed on the airplane belly body, the upper end of the vertical beam is fixed with the mounting seat, the lower end of the vertical beam is fixed with the horizontal box section, and equipment hanging points are arranged on two sides of the horizontal box section.
Description
Technical Field
The utility model belongs to the technical field of aircraft structural design, concretely relates to stores pylon structure of external equipment is connected to aircraft.
Background
The special function aircraft needs to mount a plurality of special devices outside an aircraft body, the lower part of a wing is often used as an optimal region for mounting the devices, and the region for mounting the devices outside the limited part of the wing is usually not much excluded. When the mounting equipment is few or other interference structures do not exist around, the mounting position can be reasonably selected. When more mounting devices are needed and the weight difference is large or other structures are arranged around the mounting devices, the common symmetrical device mounting arrangement occupies more space adjacent to the mounting devices, and the problems of mounting of multiple devices and weight matching are difficult to solve. In the face of the mounting of more equipment with different weights, the provided structure hanging frame ensures that the equipment can be reasonably mounted in a matching way, and also ensures that the mounted equipment cannot conflict in space and function.
Disclosure of Invention
An object of the utility model is to provide a stores pylon structure of externally-hanging equipment is connected to aircraft according to the demand of externally-hanging equipment of aircraft and the problem that prior art exists.
The hanging rack structure is characterized by comprising a mounting seat, a vertical beam and a horizontal box section, wherein the mounting seat is fixed on the airplane belly body, the upper end of the vertical beam is fixed with the mounting seat, the lower end of the vertical beam is fixed with the horizontal box section, and equipment hanging points are arranged on two sides of the horizontal box section.
The horizontal box section is of a box-shaped structure consisting of a right reinforcing rib, a left reinforcing rib, a front beam, a rear beam and an outer skin, equipment hanging points are arranged on the outer sides of the reinforcing ribs on the two sides, and an ear piece joint and a cable through hole which are connected with the lower end of the vertical beam are arranged at the top of the horizontal box section.
And the top of the reinforcing rib on the right side of the horizontal box section extends to form a lug plate joint, and the lower end of the vertical beam is fixedly connected with the horizontal box section through the lug plate structure.
The cross section of the vertical beam is of a fusiform flat structure consisting of a rigid beam main body and a skin covering cover, the cross section of the beam main body is of a semi-fusiform surrounding frame, a cable channel is arranged between the beam main body and the skin covering cover, and cable passing openings are further formed in two ends of the vertical beam.
The upper end of the beam main body is an upper joint of a vertical beam, the upper joint is matched with a notch of the mounting seat, the lower end of the beam main body is a lower joint of the vertical beam, the lower joint is provided with a mounting groove hole, and the mounting groove hole is matched with a lug joint at the top of the horizontal box section.
The beneficial effects of the utility model reside in that: the hanging rack structure is an asymmetric structure relative to the vertical beam, and equipment hanging points with different distances from the vertical beam are selected for equipment with large weight difference, so that the requirement of balanced matching of the gravity center of the hanging rack structure can be met; the whole hanging rack can be disassembled from the machine body wall plate mounting seat, so that the inspection and maintenance are convenient; the vertical beam and the horizontal box section are in shuttle shapes and flat box shapes along the course respectively, so that the pneumatic resistance can be reduced; the horizontal box section and the equipment are away from the lower surface of the machine body by the length of the vertical beam, so that the pneumatic action of the machine body is slightly influenced; the box-type structure of the horizontal box section can resist the torsional deformation of the hanging rack; the cavity structure of the vertical beam and the box structure of the horizontal box section can play a role in reducing weight of the whole hanging rack; the cable through holes arranged on the vertical beam and the horizontal box section can facilitate the dismounting and the maintenance of the equipment cable; maintenance opening covers are arranged on the vertical beams and the horizontal box sections. The wing hanging rack can meet the requirements of matching installation and reasonable space utilization of equipment with different weights, and can also meet the design requirements of static strength and dynamic strength.
The present application is described in further detail below with reference to the accompanying drawings of embodiments.
Drawings
FIG. 1 is a schematic view of the assembly relationship of the structure of a pylon for connecting an aircraft to a plug-in device.
Fig. 2 is a schematic view of a vertical beam structure.
Fig. 3 is a schematic view of a cross-sectional structure of a vertical beam.
Fig. 4 is a schematic structural diagram of a main body of a semi-fusiform girt beam of a vertical beam.
Fig. 5 is a schematic view of the internal structure of the horizontal box section.
FIG. 6 is a diagram of the horizontal box section structure assembly relationship.
The numbering in the figures illustrates: the aircraft comprises an aircraft belly body 1, a mounting seat 2, a vertical beam 3, a horizontal box section 4, a device hanging point 5, a beam main body 6, a skin covering cap 7, an upper connector 8, a cable hole 9, a lower connector 10, a mounting slotted hole 11, a cable channel 12, a right reinforcing rib 13, a left reinforcing rib 14, a front beam 15, a rear beam 16, a lug plate connector 17, a front edge covering 18, a rear edge covering 19, an upper wallboard covering 20 and a covering cap 21.
Detailed Description
Referring to the accompanying drawings, the hanging rack structure of the aircraft connecting plug-in equipment is hung on an aircraft belly machine body 1 and comprises a mounting seat 2, a vertical beam 3 and a horizontal box section 4, the mounting seat 2 is fixed on the aircraft belly machine body 1, the hanging rack structure is fixed on a side wall plate on the lower side of an aircraft wing in an embodiment, the upper end of the vertical beam 3 is fixed with the mounting seat 2, the lower end of the vertical beam 3 is fixed with the horizontal box section 4, and equipment hanging points 5 are arranged on two sides of the horizontal box section 4. In practice, the horizontal box section 4 is a box-shaped structure consisting of a right reinforcing rib 13, a left reinforcing rib 14, a front beam 15, a rear beam 16 machining part and an outer skin sheet metal part, wherein the outer skin sheet metal part comprises an upper wallboard skin 20, a cover skin 21, a front edge skin 18 and a rear edge skin 19. The outer sides of the reinforcing ribs on the two sides are respectively provided with equipment hanging points 5, and the top of the horizontal box section 4 is provided with a lug plate joint 17 and a cable through hole 9 which are connected with the lower end of the vertical beam 3. The lug joint 17 is formed by extending the top of the right reinforcing rib 13 of the horizontal box section 4, and the lower end of the vertical beam 3 is fixedly connected with the horizontal box section 4 through the lug structure 17.
The vertical beam 3 in implementation is of a fusiform flat structure formed by a rigid beam main body 6 and a skin cover 7, the cross section of the beam main body 6 is of a half fusiform enclosure frame, one side of the beam main body 6 is opened to be matched with the skin cover 7, the beam main body 6 is of a main structure of the vertical beam 3, a cable channel 12 is arranged between the beam main body 6 and the skin cover 7, cable passing ports 9 are further arranged at two ends of the vertical beam 6, in implementation, the beam main body 6 is of an machined half fusiform enclosure frame structure, two vertical ribs are arranged on the inner side wall of the beam main body, the rigidity of the beam main body 6 can be improved, and installation positions are also provided for clamps for fixing cables. In order to ensure the connection strength of the vertical beam 2, the upper end of the beam main body 6 is an upper joint 8 of the vertical beam 3, and the upper joint 8 is matched with the connection notch of the mounting seat 2 and is connected through a fastener. The lower end of the beam body 6 is provided with a lower joint 10 of the vertical beam 3, the lower joint 10 is provided with a mounting slotted hole 11, and the mounting slotted hole 11 is matched with a lug joint 17 at the top of the horizontal box section 4 and is connected through a fastener.
The horizontal box section 4 in the embodiment carries equipment on the left and right sides, and the box structure can effectively resist bending moment and torque encountered in a flight environment. The large space inside the box structure, and the detachable lower flap, are very advantageous for the arrangement and maintenance of the equipment cables.
The serrated sealing strip is arranged between the beam main body 6 and the skin flap 7 of the vertical beam in the embodiment, so that the invasion of external moisture can be effectively prevented, and good waterproof sealing is realized on equipment cables inside the structure. The control cables pass from the aircraft fuselage through the cable passage holes and cable channels in the vertical beams into the horizontal box sections.
Claims (5)
1. The hanging rack structure is characterized by comprising a mounting seat, a vertical beam and a horizontal box section, wherein the mounting seat is fixed on the airplane belly body, the upper end of the vertical beam is fixed with the mounting seat, the lower end of the vertical beam is fixed with the horizontal box section, and equipment hanging points are arranged on two sides of the horizontal box section.
2. The structure of an aircraft pylon for connecting an external hanging device according to claim 1, wherein the horizontal box section is a box-shaped structure consisting of a right reinforcing rib, a left reinforcing rib, a front beam, a rear beam and an outer skin, the outer sides of the reinforcing ribs on the two sides are provided with device hanging points, and the top of the horizontal box section is provided with a lug joint and a cable through hole which are connected with the lower end of the vertical beam.
3. The hanging rack structure for connecting the aircraft with the plug-in equipment according to claim 2, wherein a lug joint is formed by extending the top of the reinforcing rib at the right side of the horizontal box section, and the lower end of the vertical beam is fixedly connected with the horizontal box section through the lug joint.
4. A pylon structure for an aircraft to connect plug-in equipment according to claim 1, 2 or 3 wherein the vertical beam is a flat structure with a fusiform cross section, which is composed of a beam main body and a skin flap, the beam main body has a semi-fusiform cross section, a cable channel is provided between the beam main body and the skin flap, and cable through ports are provided at both ends of the vertical beam.
5. The pylon structure of claim 4 wherein the upper end of the beam body is an upper tab of the vertical beam that mates with a slot of the mount, and the lower end of the beam body is a lower tab of the vertical beam that has a mounting slot that mates with a tab joint at the top of the horizontal box section.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022305435.0U CN213705810U (en) | 2020-10-16 | 2020-10-16 | Hanging rack structure for connecting airplane with plug-in equipment |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202022305435.0U CN213705810U (en) | 2020-10-16 | 2020-10-16 | Hanging rack structure for connecting airplane with plug-in equipment |
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| Publication Number | Publication Date |
|---|---|
| CN213705810U true CN213705810U (en) | 2021-07-16 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202022305435.0U Active CN213705810U (en) | 2020-10-16 | 2020-10-16 | Hanging rack structure for connecting airplane with plug-in equipment |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113911361A (en) * | 2021-09-13 | 2022-01-11 | 中国航空工业集团公司沈阳飞机设计研究所 | Double-hanging-point parallel connection large-span hanging object hanging and throwing device |
| CN113998131A (en) * | 2021-11-26 | 2022-02-01 | 昌河飞机工业（集团）有限责任公司 | Universal hanging rack for helicopter ventral |
-
2020
- 2020-10-16 CN CN202022305435.0U patent/CN213705810U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113911361A (en) * | 2021-09-13 | 2022-01-11 | 中国航空工业集团公司沈阳飞机设计研究所 | Double-hanging-point parallel connection large-span hanging object hanging and throwing device |
| CN113911361B (en) * | 2021-09-13 | 2024-01-30 | 中国航空工业集团公司沈阳飞机设计研究所 | Double-hanging-point parallel large-span store hanging and throwing device |
| CN113998131A (en) * | 2021-11-26 | 2022-02-01 | 昌河飞机工业（集团）有限责任公司 | Universal hanging rack for helicopter ventral |
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