CN205203346U - Close section baggage compartment bearing structure - Google Patents
Close section baggage compartment bearing structure Download PDFInfo
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- CN205203346U CN205203346U CN201520996431.8U CN201520996431U CN205203346U CN 205203346 U CN205203346 U CN 205203346U CN 201520996431 U CN201520996431 U CN 201520996431U CN 205203346 U CN205203346 U CN 205203346U
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- attaching parts
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- floor
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Abstract
The utility model discloses a close section baggage compartment bearing structure belongs to aircraft safety design field, installs between floor crossbeam and fuselage frame for support the floor crossbeam. The structure includes closes section support frame (1), first connecting piece (21) and second connecting piece (22), closes the one end of section support frame (1) and connects on the crossbeam of floor, and the other end is fixed on first connecting piece (21), and the other end of first connecting piece (21) forms first hinge fulcrum, and the one end of second connecting piece (22) is fixed on the fuselage frame, and the other end forms and the first second hinge fulcrum that cuts with scissors the fulcrum adaptation, first hinge fulcrum with the connection of second hinge fulcrum hinge. The utility model discloses the fuselage frame that closes section support frame and second frame of fuselage adopts the hinge to be connected for close the section support frame and only transmit the axle power that comes from structure more than the floor, and do not hold the flexural square, reduced the overall rigidity of the following structure in floor, improved the crash -worthiness of the following structure in fuselage floor.
Description
Technical field
The utility model belongs to aircraft safety design field, is specifically related to one and closes section boot compartment supporting construction.
Background technology
Safety is the basic demand of civil aircraft operation, and in order to ensure that occupant can be able to survived in existence accident, civil aircraft must meet crash-worthiness requirement.The general layout of airline carriers of passengers fuselage is more than floor is main cabin, is boot compartment (cargo hold) below floor.The following structure of fuselage floor improves the important area of aircraft crash-worthiness design, and it is then one of significant design unit that boot compartment supports.
Boot compartment supports and is positioned at bottom, floor, is connected, plays a supportive role to floor, the load on floor be delivered in lower wall panels with the form of axial force with floor crossmember and second frame of fuselage.Existing aircarrier aircraft boot compartment supports and is generally out section girder structure or closes section thin-wall pipe, and adopt clamped connection with floor crossmember and second frame of fuselage, make to form firm trigonum outside boot compartment support and floor crossmember, second frame of fuselage, integral rigidity is large, hit both sides boot compartment in process at aircraft pendant to be supported on ground and to form two strong points, second frame of fuselage and lower wall panels distortion are affected, and energy-absorbing effect is not good, eventually reduces the crash-worthiness of airframe structure.
Utility model content
In order to solve the problem, the utility model proposes one and closing section boot compartment supporting construction, for improving fuselage crash-worthiness.
The utility model closes section boot compartment supporting construction, be arranged between floor crossmember and fuselage frame, for supporting floor crossmember, comprise and close section bracing frame, the first attaching parts and the second attaching parts, the one end closing section bracing frame is connected on floor crossmember, the other end is fixed on the first attaching parts, the other end of the first attaching parts forms the first coercive mechanism, one end of second attaching parts is fixed on fuselage frame, the other end forms the second coercive mechanism with the first coercive mechanism adaptation, and described first coercive mechanism is connected with described second coercive mechanism is hinged.
Preferably, described first coercive mechanism is monaural sheet, and described second coercive mechanism is ears sheet, described ears sheet and the middle correspondence position expense hole of described monaural sheet, and passes through pinned connection.
, close one end that section bracing frame is being connected with the first attaching parts and be provided with outside thread in such scheme preferably, the first attaching parts also comprises adaptive and described externally threaded nut.
In such scheme preferably, monaural sheet and nut one-body molded.
In such scheme preferably, one end that described second attaching parts is being connected with described fuselage frame is provided with base, base comprises the first plate face and the second plate face, described first plate face is fastened on the inner edge of fuselage frame, described second plate face is vertical with described first plate face, and is fastened on the web of fuselage frame.
In such scheme preferably, ears sheet and base one-body molded.
In such scheme preferably, floor crossmember with close section bracing frame bolt and be connected.
The utility model has the advantage of:
Close section bracing frame and adopt hinged connection with the fuselage frame of second frame of fuselage, make to close section bracing frame and only transmit axle power from the above structure in floor, and do not bear moment of flexure, reduce the global stiffness of the following structure in floor, improve the crash-worthiness of the following structure of fuselage floor.
Accompanying drawing explanation
Fig. 1 is the structural representation that the utility model closes a preferred embodiment of section boot compartment supporting construction.
Fig. 2 is the first connecting-piece structure schematic diagram embodiment illustrated in fig. 1.
Fig. 3 is the second connecting-piece structure schematic diagram embodiment illustrated in fig. 1.
Fig. 4 is boot compartment supporting construction scheme of installation embodiment illustrated in fig. 1.
Wherein, 1 for closing section bracing frame, and 2 is attaching parts assembly, and 3 is floor crossmember, and 4 is fuselage frame, and 21 is the first attaching parts, and 22 is the second attaching parts, and 23 is bearing pin, and 211 is monaural sheet, and 212 is nut, and 221 is ears sheet, and 222 is base.
Detailed description of the invention
The object implemented for making the utility model, technical scheme and advantage clearly, below in conjunction with the accompanying drawing in the utility model embodiment, are further described in more detail the technical scheme in the utility model embodiment.In the accompanying drawings, same or similar label represents same or similar element or has element that is identical or similar functions from start to finish.Described embodiment is the utility model part embodiment, instead of whole embodiments.Be exemplary below by the embodiment be described with reference to the drawings, be intended to for explaining the utility model, and can not be interpreted as restriction of the present utility model.Based on the embodiment in the utility model, those of ordinary skill in the art are not making the every other embodiment obtained under creative work prerequisite, all belong to the scope of the utility model protection.Below in conjunction with accompanying drawing, embodiment of the present utility model is described in detail.
In description of the present utility model, it will be appreciated that, term " " center ", " longitudinal direction ", " transverse direction ", " front ", " afterwards ", " left side ", " right side ", " vertically ", " level ", " top ", " end " " interior ", orientation or the position relationship of the instruction such as " outward " are based on orientation shown in the drawings or position relationship, only the utility model and simplified characterization for convenience of description, instead of indicate or imply that the device of indication or element must have specific orientation, with specific azimuth configuration and operation, therefore the restriction to the utility model protection domain can not be interpreted as.
The utility model gives one and closes section boot compartment supporting construction, as shown in Figure 4, be arranged between floor crossmember 3 and fuselage frame 4, for supporting floor crossmember 3, it comprises and closes section bracing frame 1 and attaching parts assembly 2, described attaching parts assembly comprises again the first attaching parts 21, second attaching parts 22 and bearing pin 23, with reference to figure 1, the one end closing section bracing frame 1 is connected on floor crossmember 3, the other end is fixed on the first attaching parts 21, the other end of the first attaching parts 21 forms the first coercive mechanism, one end of second attaching parts 22 is fixed on fuselage frame 4, the other end forms the second coercive mechanism with the first coercive mechanism adaptation, described first coercive mechanism is connected with described second coercive mechanism is hinged.
Described first coercive mechanism is monaural sheet 211, and described second coercive mechanism is ears sheet 221, described ears sheet 221 and described monaural sheet 211 middle correspondence position expense hole, and is connected by bearing pin 23.
As an alternate embodiment of the present embodiment, bearing pin 23 can replace with bolt, to dismantle.On the same axis, and bore dia is equal, is bolted together, boot compartment is supported and forms hinged structure with fuselage frame for three earhole centers on first attaching parts 21 and the second attaching parts 22.
In the present embodiment, close one end that section bracing frame 1 is being connected with the first attaching parts 21 and be provided with outside thread, with reference to figure 2, first attaching parts 21 also comprises adaptive and described externally threaded nut 212, by the matching relationship between nut 212 and above-mentioned outside thread, described in being tightened in by the first attaching parts, close section bracing frame 1.It should be noted that, monaural sheet 211 is one-body molded with nut 212, nut 212 perforate direction deviates from the first attaching parts 21, the auricle of monaural sheet 211 towards deviating from the first attaching parts 21, thus make the two ends of the first attaching parts 21 formed respectively can with close the nut 212 that section bracing frame 1 is connected and the monaural sheet 211 that can be connected with the second attaching parts 22.
With reference to figure 3, in the present embodiment, one end that described second attaching parts 22 is being connected with described fuselage frame 4 is provided with base 222, base 222 comprises the first plate face and the second plate face, described first plate face is fastened on the inner edge of fuselage frame 4, described second plate face is vertical with described first plate face, and is fastened on the web of fuselage frame 4.
Be understandable that, inner edge and the web of fuselage frame 4 are L-shaped, so the base 222 in the present embodiment is set to the L shape matched with fuselage frame 4 equally, thus two faces are adjacent to mutually, increase area of thrust surface.In the present embodiment, ears sheet 221 is processed with base 222 one.
As the alternate embodiment in the present embodiment, ears sheet 221 welds with base 222.
In addition, floor crossmember 3 with close section bracing frame 1 and be fixedly connected with, such as bolt connects or welding.
The utility model closes in section boot compartment supporting construction, close section bracing frame and adopt hinged connection with the fuselage frame of second frame of fuselage, make to close section bracing frame and only transmit axle power from the above structure in floor, and do not bear moment of flexure, reduce the global stiffness of the following structure in floor, improve the crash-worthiness of the following structure of fuselage floor.
After forming hinged connection, result of finite element shows that this type of attachment can significantly improve the crash-worthiness of airframe structure.In raising airframe structure crash-worthiness, be better than boot compartment support situation about being connected clamped with second frame of fuselage, and the requirement of transmitting floor load with axle power form can be met, namely can meet the requirement of static strength.
Finally it is to be noted: above embodiment only in order to the technical solution of the utility model to be described, is not intended to limit.Although be described in detail the utility model with reference to previous embodiment, those of ordinary skill in the art is to be understood that: it still can be modified to the technical scheme described in foregoing embodiments, or carries out equivalent replacement to wherein portion of techniques feature; And these amendments or replacement, do not make the essence of appropriate technical solution depart from the spirit and scope of each embodiment technical scheme of the utility model.
Claims (7)
1. one kind is closed section boot compartment supporting construction, be arranged between floor crossmember (3) and fuselage frame (4), for supporting floor crossmember (3), it is characterized in that: comprise and close section bracing frame (1), first attaching parts (21) and the second attaching parts (22), the one end closing section bracing frame (1) is connected on floor crossmember (3), the other end is fixed on the first attaching parts (21), the other end of the first attaching parts (21) forms the first coercive mechanism, one end of second attaching parts (22) is fixed on fuselage frame (4), the other end forms the second coercive mechanism with the first coercive mechanism adaptation, described first coercive mechanism is connected with described second coercive mechanism is hinged.
2. close section boot compartment supporting construction as claimed in claim 1, it is characterized in that: described first coercive mechanism is monaural sheet (211), described second coercive mechanism is ears sheet (221), described ears sheet (221) correspondence position expense hole middle with described monaural sheet (211), and connected by bearing pin (23).
3. close section boot compartment supporting construction as claimed in claim 2, it is characterized in that: close one end that section bracing frame (1) is being connected with the first attaching parts (21) and be provided with outside thread, the first attaching parts (21) also comprises adaptive and described externally threaded nut (212).
4. close section boot compartment supporting construction as claimed in claim 3, it is characterized in that: monaural sheet (211) is one-body molded with nut (212).
5. close section boot compartment supporting construction as claimed in claim 2, it is characterized in that: one end that described second attaching parts (22) is being connected with described fuselage frame (4) is provided with base (222), base (222) comprises the first plate face and the second plate face, described first plate face is fastened on the inner edge of fuselage frame (4), described second plate face is vertical with described first plate face, and is fastened on the web of fuselage frame (4).
6. close section boot compartment supporting construction as claimed in claim 5, it is characterized in that: ears sheet (221) is one-body molded with base (222).
7. close section boot compartment supporting construction as claimed in claim 1, it is characterized in that: floor crossmember (3) with close section bracing frame (1) bolt and be connected.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520996431.8U CN205203346U (en) | 2015-12-04 | 2015-12-04 | Close section baggage compartment bearing structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520996431.8U CN205203346U (en) | 2015-12-04 | 2015-12-04 | Close section baggage compartment bearing structure |
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| Publication Number | Publication Date |
|---|---|
| CN205203346U true CN205203346U (en) | 2016-05-04 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520996431.8U Active CN205203346U (en) | 2015-12-04 | 2015-12-04 | Close section baggage compartment bearing structure |
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| CN (1) | CN205203346U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110466744A (en) * | 2019-08-12 | 2019-11-19 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of undercarriage actuating cylinder erection joint |
| CN113501138A (en) * | 2021-09-13 | 2021-10-15 | 成都飞机工业（集团）有限责任公司 | Method for increasing rigidity of finishing process of aircraft component |
-
2015
- 2015-12-04 CN CN201520996431.8U patent/CN205203346U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110466744A (en) * | 2019-08-12 | 2019-11-19 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of undercarriage actuating cylinder erection joint |
| CN110466744B (en) * | 2019-08-12 | 2022-11-22 | 中国航空工业集团公司沈阳飞机设计研究所 | Undercarriage actuator cylinder erection joint |
| CN113501138A (en) * | 2021-09-13 | 2021-10-15 | 成都飞机工业（集团）有限责任公司 | Method for increasing rigidity of finishing process of aircraft component |
| CN113501138B (en) * | 2021-09-13 | 2021-11-30 | 成都飞机工业（集团）有限责任公司 | Method for increasing rigidity of finishing process of aircraft component |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |