CN204775980U - Airtight subdivision structure of frame is hanged to large -scale aircraft inflection formula half - Google Patents
Airtight subdivision structure of frame is hanged to large -scale aircraft inflection formula half Download PDFInfo
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- CN204775980U CN204775980U CN201520430428.XU CN201520430428U CN204775980U CN 204775980 U CN204775980 U CN 204775980U CN 201520430428 U CN201520430428 U CN 201520430428U CN 204775980 U CN204775980 U CN 204775980U
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Abstract
The utility model provides being connected through inflection roof beam, turning reinforced joint between an airtight subdivision structure of frame is hanged to large -scale aircraft inflection formula half, floor and second frame, being provided with the crossbeam on first frame, going up longeron, upper ledge web, the crossbeam is with the perpendicular zigzag connection of last longeron and on being fixed in the upper ledge web, be provided with crossbeam, lower longeron, lower frame web on second frame, the crossbeam on second frame is with the lower perpendicular zigzag connection of longeron and on being fixed in the lower frame web, it connects and is fixed in on the bottom plate panel to be provided with floor crossbeam, floor longeron vertical cross on the floor. First frame is through last band plate and covering wallboard fixed connection, second frame passes through band plate and covering wallboard fixed connection down. The utility model provides a pair of airtight subdivision structure of frame is hanged to large -scale aircraft inflection formula half reasonable in design has improved old configuration mode rigidity and has mated inhomogeneous, shortcomings such as structure weight big, distributing of stress inhomogeneities, has improved structure efficiency, satisfies the aircraft designing requirement.
Description
Technical field
The utility model relates to technical field of aircraft structure design, in particular to the outstanding frame airtight point of cabin structure of a kind of large aircraft inflection formula half.
Background technology
Pressure bulkhead form many employings holoventral plate frame of existing aircraft, as shown in Figure 4, such version is relatively simple, is easy to airtight, but runs through fuselage due to holoventral plate frame, makes the spatial accommodation on below driving compartment floor limited.Some large aircraft is due to general technical requirements such as subdivision is airtight, space layouts, head arranges the outstanding frame airtight point of cabin structure of inflection formula half, this block construction has layout uniqueness, size large, the advantages such as large equipment are arranged after being adapted at frame, shortcoming is that rigidity difficulty controls, weight indicator is harsh, and design difficulty is large.The topmost requirement of this part design is under the airtight load effect of complexity, has both met structure integrity requirement, and has had again enough reliability and life-span, and structural weight little as far as possible and low cost.This also never designed similar large parts at home and abroad.The problem needing now solution badly how to design the outstanding frame airtight point of cabin structure of a kind of inflection formula half, meets airplane design requirement, improve the problems such as old frame mode Rigidity Matching is uneven, structural weight large, distribution of stress irregularity, improve structure efficiency.
Utility model content
The purpose of this utility model is to solve above-mentioned deficiency of the prior art, provide a kind of simple and reasonable, Rigidity Matching is even, structural weight is little, the outstanding frame airtight point of cabin structure of distribution of stress uniform large aircraft inflection formula half.
The purpose of this utility model is achieved through the following technical solutions: the outstanding frame airtight point of cabin structure of a kind of large aircraft inflection formula half, comprise first frame, floor, second frame, wherein, first frame and floor perpendicular, second frame and floor perpendicular are arranged at the both sides that floor opposes, first frame is identical with lower half-frame structure, first frame and floor are by inflection beam, turning reinforced joint connects, by inflection beam between floor and second frame, turning reinforced joint connects, first frame is provided with crossbeam, upper longeron, upper ledge web, crossbeam is connected with upper longeron vertical interlaced and is fixed on upper ledge web, second frame is provided with crossbeam, lower longeron, lower frame web, the crossbeam on second frame is connected with lower longeron vertical interlaced and is fixed on lower frame web, floor is provided with floor crossmember, longitudinal floor beam square crossing is connected and fixed on floor board.
Preferably, first edge edge is fixedly connected with band plate, and first frame is fixedly connected with skinpiston by upper band plate; Second edge edge is fixedly connected with lower band plate, and second frame is fixedly connected with skinpiston by lower band plate.
In above-mentioned either a program preferably, upper band plate is fixedly connected with aircraft skin wallboard by rivet with described lower band plate.
The beneficial effect of the outstanding frame airtight point of cabin structure of large aircraft inflection formula provided by the utility model half is: structure is simple, reasonable in design, not only improve the shortcomings such as old frame mode Rigidity Matching is uneven, structural weight large, distribution of stress irregularity, also effectively control the stress level of inflection place, and solve the airtight complexity of old frame mode, space layout requires the problems such as high, improve structure efficiency, meet airplane design requirement.
Accompanying drawing explanation
Fig. 1 is the structural representation hanging a preferred embodiment of frame airtight point of cabin structure according to the large aircraft inflection formula half of utility model;
Fig. 2 is the birds-eye view embodiment illustrated in fig. 1 of the outstanding frame airtight point of cabin structure of large aircraft inflection formula half according to utility model;
Fig. 3 is the lateral plan embodiment illustrated in fig. 1 of the outstanding frame airtight point of cabin structure of large aircraft inflection formula half according to utility model;
Fig. 4 is the structural representation of the pressure bulkhead adopting holoventral plate frame in prior art.
Reference numeral:
Band plate, 12-turning reinforced joint under longeron, 4-upper ledge web, 5-lower frame web, 6-inflection beam, 7-floor crossmember, 8-longitudinal floor beam, 9-floor panel, the upper band plate of 10-, 11-under the upper longeron of 1-crossbeam, 2-, 3-.
Detailed description of the invention
In order to understand the outstanding frame airtight point of cabin structure of large aircraft inflection formula half according to the utility model scheme better, be further elaborated explanation below in conjunction with the preferred embodiment of accompanying drawing to the outstanding frame airtight point of cabin structure of large aircraft inflection formula of the present utility model half.
The outstanding frame airtight point of cabin structure of the large aircraft inflection formula that the utility model provides half, comprise first frame, floor, second frame, wherein, first frame and floor perpendicular, second frame and floor perpendicular are arranged at the both sides that floor opposes, first frame is identical with lower half-frame structure, first frame is connected by inflection beam 6, turning reinforced joint 12 with floor, be connected by inflection beam 6, turning reinforced joint 12 between floor with second frame, first frame is provided with crossbeam 1, upper longeron 2, upper ledge web 4, crossbeam 1 is connected with upper longeron 2 vertical interlaced and is fixed on upper ledge web 4; Second frame is provided with crossbeam 1, lower longeron 3, lower frame web 5, the crossbeam 1 on second frame is connected with lower longeron 3 vertical interlaced and is fixed on lower frame web 5; Floor is provided with floor crossmember 7, longitudinal floor beam 8 square crossing is connected and fixed on floor board 9.First edge edge is fixedly connected with band plate 10, and first frame is fixedly connected with skinpiston by upper band plate 10; Second edge edge is fixedly connected with lower band plate 11, and second frame is fixedly connected with skinpiston by lower band plate 11.Upper band plate 10 is fixedly connected with aircraft skin wallboard by rivet with lower band plate 11.
The outstanding frame airtight point of cabin structure of large aircraft inflection formula half adopting the utility model to provide is that bottom, driving compartment floor reserves larger equipment spatial accommodation, solve that the Rigidity Matching that inflection beam 6 brings is uneven, corner stress is concentrated simultaneously, the complicated problem such as airtight, effectively transmit the normal direction uniform load in plane.According to engineering beam theory, vertical and horizontal support frame to be arranged in plane, normal load is converted into flexure stress, be diffused as the friction stress that frame takes plate, expand step by step, be finally diffused as covering shearing flow.Outstanding frame airtight point of cabin structure of inflection formula half that the outstanding frame airtight point of cabin structure of the large aircraft inflection formula that the utility model provides half is divided into first frame, second frame, floor is formed.Be fixedly connected with turning reinforced joint 12 by inflection beam 6 between first frame with floor, between floor with second frame.Turning reinforced joint 12 is fixedly connected with by rivet with the perpendicular joints of upper ledge web 4, floor panel 9.Turning reinforced joint 12 is fixedly connected with by rivet with the perpendicular joints of lower frame web 5, floor panel 9, turning reinforced joint 12 had both played the effect connecting floor and first frame, second frame, and played and safeguard that first frame and floor, second frame and floor show the effect to invariant position.
With crossbeam 1 and upper longeron 2 on first frame web 4, with crossbeam 1 and lower longeron 3 on second frame web 5, floor there are floor crossmember 7 and longitudinal floor beam 8 are vertically installed on floor panel 9.The crossbeam that first frame, second frame, floor are arranged respectively is vertical with longeron to be set to the space of a whole page and to provide support frame, support first frame, second frame, floor profile can not change due to external force load.The both sides that first frame and floor, second frame and floor perpendicular are arranged at floor are connected by inflection beam 6 and turning reinforced joint 12.
The edge of first frame, second frame is respectively arranged with band plate 10, lower band plate 11, and upper band plate 10 is connected aircraft fuselage skin wallboard with lower band plate 11.Like this, floor method phase load is converted into flexure stress.Due to first frame and floor, floor and second frame is vertical is fixedly connected with, flexure stress is diffused as the friction stress of first frame, second frame.First frame, second edge edge are respectively arranged with band plate 10, lower band plate 11, and the friction stress of first frame, the friction stress of second frame are converted into the covering shearing flow of fuselage skin by upper band plate 10, lower band plate 11.
The outstanding frame airtight point of cabin structure of large aircraft inflection formula half adopting the utility model to provide is that bottom, driving compartment floor leaves larger equipment spatial accommodation, solves that the Rigidity Matching that inflection frame brings is uneven, corner is concentrated, the complicated problem such as airtight simultaneously.
More than be described in detail in conjunction with the outstanding airtight subdivision construction embodiment of frame of large aircraft inflection formula of the present utility model half, but be not to restriction of the present utility model, everyly according to technical spirit of the present utility model, technical scope of the present utility model is all belonged to any simple modification made for any of the above embodiments, also it should be noted that, comprise the combination in any between each part mentioned above according to the category of the outstanding frame airtight subdivision structure technology scheme of large aircraft inflection formula of the present utility model half.
Claims (3)
1. outstanding frame airtight point of cabin structure of large aircraft inflection formula half, it is characterized in that, comprise first frame, floor, second frame, wherein, first frame and floor perpendicular, second frame and floor perpendicular are arranged at the both sides that floor opposes, first frame is identical with lower half-frame structure, first frame and floor are by inflection beam (6), turning reinforced joint (12) connects, by inflection beam (6) between floor and second frame, turning reinforced joint (12) connects, first frame is provided with crossbeam (1), upper longeron (2), upper ledge web (4), crossbeam (1) is connected with upper longeron (2) vertical interlaced and is fixed on upper ledge web (4), second frame is provided with crossbeam (1), lower longeron (3), lower frame web (5), the crossbeam (1) on second frame is connected with lower longeron (3) vertical interlaced and is fixed on lower frame web (5), floor is provided with floor crossmember (7), longitudinal floor beam (8) square crossing is connected and fixed on floor board (9).
2. the outstanding frame airtight point of cabin structure of the large aircraft inflection formula according to claims 1 half, it is characterized in that, first edge edge is fixedly connected with band plate (10), and first frame is fixedly connected with skinpiston by upper band plate (10); Second edge edge is fixedly connected with lower band plate (11), and second frame is fixedly connected with skinpiston by lower band plate (11).
3. the outstanding frame airtight point of cabin structure of the large aircraft inflection formula according to claims 2 half, it is characterized in that, described upper band plate (10) is fixedly connected with aircraft skin wallboard by rivet with described lower band plate (11).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520430428.XU CN204775980U (en) | 2015-06-23 | 2015-06-23 | Airtight subdivision structure of frame is hanged to large -scale aircraft inflection formula half |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520430428.XU CN204775980U (en) | 2015-06-23 | 2015-06-23 | Airtight subdivision structure of frame is hanged to large -scale aircraft inflection formula half |
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| Publication Number | Publication Date |
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| CN204775980U true CN204775980U (en) | 2015-11-18 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201520430428.XU Active CN204775980U (en) | 2015-06-23 | 2015-06-23 | Airtight subdivision structure of frame is hanged to large -scale aircraft inflection formula half |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107944167A (en) * | 2017-11-30 | 2018-04-20 | 中国航空工业集团公司西安飞机设计研究所 | A kind of airtight subdivision construction design method of vertical inflection |
| CN110920858A (en) * | 2019-12-09 | 2020-03-27 | 中航沈飞民用飞机有限责任公司 | Detachable firewall of compact passenger plane and use method thereof |
-
2015
- 2015-06-23 CN CN201520430428.XU patent/CN204775980U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107944167A (en) * | 2017-11-30 | 2018-04-20 | 中国航空工业集团公司西安飞机设计研究所 | A kind of airtight subdivision construction design method of vertical inflection |
| CN110920858A (en) * | 2019-12-09 | 2020-03-27 | 中航沈飞民用飞机有限责任公司 | Detachable firewall of compact passenger plane and use method thereof |
| CN110920858B (en) * | 2019-12-09 | 2024-01-23 | 中航沈飞民用飞机有限责任公司 | Detachable firewall of compact passenger plane and application method thereof |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |