CN203891685U - Flap-down type cabin door structure of aircraft - Google Patents
Flap-down type cabin door structure of aircraft Download PDFInfo
- Publication number
- CN203891685U CN203891685U CN201420245487.5U CN201420245487U CN203891685U CN 203891685 U CN203891685 U CN 203891685U CN 201420245487 U CN201420245487 U CN 201420245487U CN 203891685 U CN203891685 U CN 203891685U
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- Prior art keywords
- doorframe
- door structure
- handle
- window
- hatch door
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- 239000011521 glass Substances 0.000 claims abstract description 50
- 238000007789 sealing Methods 0.000 claims abstract description 18
- 239000004033 plastic Substances 0.000 claims description 12
- 229910000831 Steel Inorganic materials 0.000 claims description 11
- 239000010959 steel Substances 0.000 claims description 11
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 6
- 229910052782 aluminium Inorganic materials 0.000 claims description 6
- 238000004026 adhesive bonding Methods 0.000 claims description 4
- 238000007665 sagging Methods 0.000 claims description 4
- 238000003466 welding Methods 0.000 claims description 3
- 230000000694 effects Effects 0.000 abstract description 2
- 238000003780 insertion Methods 0.000 abstract 1
- 230000037431 insertion Effects 0.000 abstract 1
- 238000004519 manufacturing process Methods 0.000 description 4
- 238000000034 method Methods 0.000 description 3
- 238000005299 abrasion Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 239000006260 foam Substances 0.000 description 2
- 230000000007 visual effect Effects 0.000 description 2
- 206010044565 Tremor Diseases 0.000 description 1
- 239000004411 aluminium Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 239000003795 chemical substances by application Substances 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000005086 pumping Methods 0.000 description 1
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- Specific Sealing Or Ventilating Devices For Doors And Windows (AREA)
- Special Wing (AREA)
Abstract
The utility model relates to a flap-down type cabin door structure of an aircraft. A glass panel (3) of the flap-down type cabin door structure is connected with a door frame (2), the door frame (2) is connected with an aircraft body (26) by first hinges (6), a handle system and a connecting rod lock system are respectively connected with the door frame (2), and a first handle (4) and a second handle (7) are respectively connected with the door frame (2); a third handle (24) and a fourth handle (25) are respectively connected with a connecting rod (9); a rotary shaft (27), the connecting rod (9) and an insertion rod (1) are sequentially connected with one another. The flap-down type cabin door structure has the advantages that a main cabin door structure is in a glass panel design, and accordingly the flap-down type cabin door structure is wide in vision and brings convenience for pilots during operation; finished tubular rubber sealing section bars cover the edges of the flap-down type cabin door structure in a sealed form, accordingly, good sealing effects can be realized, the flap-down type cabin door structure is firm and is convenient and quick to operate and excellent in locking performance, and the safety of the pilots can be guaranteed.
Description
Technical field
The utility model belongs to aircraft door structure design field, relates to a kind of aircraft door structure, particularly, relates to a kind of lower turning type aircraft door structure, is particularly useful for agricultural aircraft hatch door structure design.
Background technology
The hatch door form of existing aircraft cockpit has: the front formula of turning over--and be similar to automobile side and open forward, the impact that is subject to crosswind load during unlatching is large, visual field is limited to; Upper-turn-type--its sealing and presentation quality are better, but convenient not and hatch door exists potential safety hazard to the person of boarding while boarding.And traditional hatch door doorframe adopts hard polyaminoresin foam filling plastic formula structure, sight line is poor, and its sealing adopts aviation sponge rubber plate seal form in addition, and sealing effectiveness is undesirable, easily produces hidden danger.
Utility model content
For solving the problem of above-mentioned existence, the purpose of this utility model is to provide a kind of lower turning type aircraft door structure, hatch door agent structure designs for face glass, and broad view, facilitates driver's operation, its seal form adopts finished product tubulose rubber seal section bar bound edge, good sealing effect, stabilized structure, simple operation, lock functionally, guarantee driver safety.
For achieving the above object, the utility model is mainly taked following technical scheme:
A lower turning type aircraft door structure, is characterized in that, described hatch door structure comprises:
One for forming the doorframe of hatch door framework;
One for improving the face glass of driver's seat;
One first in command and the second in command who closes for controlling hatch door;
The one link lock system for locking hatch door;
One for connecting the first hinge of doorframe and fuselage;
Described connecting rod system comprises:
One the 3rd handle for opened door;
One the 4th handle for locking hatch door;
One inserted link for locking hatch door;
One for controlling the prerotation vane of inserted link direction;
One for controlling connecting rod and the rotating shaft of inserted link;
One dead bolt for matching with theftproof lock;
Described face glass is connected with doorframe, and described doorframe is connected with fuselage by the first hinge, and described handle system is connected with doorframe respectively with link lock system, between the described first in command, is connected with doorframe, and the second in command is connected with doorframe by brace;
Described the 3rd handle is connected with rotating shaft respectively with the 4th handle;
Rotating shaft, connecting rod and inserted link connect successively.Further preferably, described hatch door structure also comprises:
One for driver and the extraneous talking window contacting;
One lock of the window for locking talking window system;
One for connecting the second hinge of talking window and face glass;
One for antitheft theftproof lock;
One frame for the protection of talking window;
Described window lock system comprises:
One for controlling the window lock of talking window closure or openness;
One snap close for stationary window lock;
Described window lock is arranged on talking window, and described snap close is arranged on face glass;
Described talking window is connected with face glass by the second hinge, and described frame is arranged on talking window.
Further preferably, described doorframe comprises:
Skeleton;
The one doorframe panel for coated described skeleton;
The one sealing rubber and plastic section bar for the protection of doorframe;
Described sealing rubber and plastic section bar is gluing in doorframe edge;
Described skeleton is connected with doorframe panel;
Described skeleton is steel pipe skeleton, and described doorframe panel is aluminum deck;
Described skeleton is connected to form by welding manner by a straight steel pipe and a U-shaped steel pipe.
Further preferably, described face glass is aerial organic glass, and thickness is 3～5mm;
Described face glass is connected with doorframe by press strip, and described connected mode is that screw connects, and on described screw, is provided with rubber bushing;
Between described face glass and doorframe, be also provided with rubber tile, the thickness of described rubber tile is 0.5mm.
Further preferably, described link lock system also comprises:
One ring set for the protection of link lock system;
One rotating shaft for control link;
Described rotating shaft is connected with doorframe by angle box;
Described the 3rd handle is connected with connecting rod by rotating shaft respectively with the 4th handle.
Further preferably, described hatch door thickness is 21～23mm;
Described inserted link is connected with fuselage by prerotation vane.
Further preferably, the described first in command is connected with doorframe by sleeve pipe.
Further preferably, described the 4th handle set-up mode is longitudinal sagging setting.
Further preferably, described aircraft is agricultural aircraft.
Further preferably, described rubber tile is arranged at the both sides that doorframe contacts with face glass.
Compared with prior art, the beneficial effects of the utility model are:
1), lower turning type hatch door structure conveniently boards, low cost of manufacture, quality is easily controlled;
2), doorframe panel replaces interior exterior skin in the past with aerial organic glass panel
-+ hard polyaminoresin foam filling plastic formula structure, developing driver's seat, facilitate driver to control aircraft, can effectively reduce the thickness of hatch door simultaneously, by existing 42mm, be reduced to 21～23mm, simultaneously hatch door weight also greatly alleviates, in addition, and the reducing of hatch door thickness, also make limited passenger cabin space strengthen, improved the comfort level of passenger cabin;
3), the setting of rubber tile can guarantee the retentivity that face glass contacts with doorframe, while avoiding installing, staff is scratched, face glass is when being fixedly connected with by screw, rubber bushing is set, can have to offset and protect the stroke that glass expands with heat and contract with cold and produces, can reduce again the aircraft even resonance of trembling that face glass produces when flight, reduce flight noise;
4), set up glass on face glass and have openable glass talking window, facilitate personnel and extraneous speech quality in cabin, contact quick rapidly with the external world;
5), doorframe skeleton is welded to form by aluminium sheet and steel pipe skeleton, intensity and the stability of hatch door doorframe have been guaranteed, hatch door doorframe surrounding arranges the collision producing when sealing rubber and plastic section bar can effectively reduce hatch door and closes, and makes hatch door sealing tight, has improved hatch door edge abrasion resistance and safety;
6), hatch door inner side arranges the first in command and the second in command, be convenient to staff in cabin and close hatch door;
7), link lock system is set, the link lock mechanism operation of 2 contact self-lockings is simple, state is clear and definite, only need the 3rd handle and the 4th handle to be rotated in place the opening and closing that can realize hatch door, self-locking performance when latch mechanism locking had both been considered in the longitudinal sagging setting of the 4th handle, takes driver's safety into account again;
8), the setting of theftproof lock can increase the locking of hatch door, possesses anti-theft feature.
Accompanying drawing explanation
Fig. 1 is the structural representation of link lock in closed condition in a kind of lower turning type aircraft door structure provided by the utility model.
Fig. 2 is the structural representation of link lock in opening in a kind of lower turning type aircraft door structure provided by the utility model.
Fig. 3 is that in Fig. 1, A-A is to partial sectional view, and hatch door and fuselage are by the structural representation of the first gemel connection.
Fig. 4 be in Fig. 1 B-B to partial sectional view, i.e. talking window scheme of installation.
Fig. 5 is that in Fig. 1, C-C is to partial sectional view, and link lock system overlaps schematic diagram with fuselage after locking.
Fig. 6 be in Fig. 1 D-D to partial sectional view, link lock system lock after the position view of the 3rd handle and the 4th handle.
Fig. 7 be in Fig. 1 E-E to partial sectional view, i.e. doorframe and face glass syndeton schematic diagram.
Fig. 8 is the structural representation that in a kind of lower turning type aircraft door structure provided by the utility model, doorframe is connected with the first in command.
Fig. 9 is the structural representation of the 3rd handle and the 4th handle in a kind of lower turning type aircraft door structure provided by the utility model.
In Figure 10 Fig. 1, F-F is to partial sectional view, the structural representation that second in command is connected with doorframe.
The specific embodiment
Below in conjunction with accompanying drawing, a kind of lower turning type aircraft door structure provided by the utility model is further explained.
The structure of a kind of lower turning type aircraft door structure provided by the utility model is as follows:
As depicted in figs. 1 and 2, face glass 3 is connected with doorframe 2, described doorframe 2 is connected with fuselage 26 by the first hinge 6, and described handle system is connected with doorframe 2 respectively with link lock system, and described first in command 4(is as shown in Figure 8) with second in command 7(as shown in figure 10) be connected with doorframe 2 respectively; Described face glass 3 is aerial organic glass, and thickness is 3～5mm; Wherein, as shown in Figure 3, the first hinge 6 is connected with poker 5.
As shown in Figure 9, described the 3rd handle 24 is connected with rotating shaft 27 respectively with the 4th handle 25;
As shown in Figure 1, described rotating shaft 27, connecting rod 9 and inserted link 1 once connect.
As shown in Figure 5, described inserted link 1 is connected with fuselage 26 by prerotation vane 15.
As shown in Figure 4, described window lock 13 is arranged on talking window 10, and described snap close 12 is arranged on face glass 3; Described talking window 10 is connected with face glass 3 by the second hinge 28.As shown in Figure 1, on talking window 10, be provided with frame 11, to protect the stability of talking window 10.As shown in Figure 4, on described talking window 10, be also provided with pad 14, for further protection talking window 10, prevent contact because of vibrations or miscellaneous part, collide with, and it be damaged to cause talking window 10 to occur.
As shown in figure 10, the described second in command 7 is connected with brace 29.
Described hatch door thickness is 21～23mm.
As shown in Figure 1, described sealing rubber and plastic section bar 19 is gluing in doorframe 2 edges; Described skeleton 201 is connected with doorframe panel 202; Described skeleton 201 is steel pipe skeleton, and described doorframe panel 202 is aluminum deck; Described skeleton 201 is connected to form by welding manner by a straight steel pipe 2011 and a U-shaped steel pipe 2012.Described sealing rubber and plastic section bar 19 is B052 finished product tubulose rubber seal section bar.
As shown in Figure 7, described face glass 3 is connected with doorframe 2 by press strip 301, and described connected mode is that screw connects, and is provided with rubber bushing 18 on described screw; Between described face glass 3 and doorframe 2, be also provided with rubber tile 17, the thickness of described rubber tile 17 is 0.5mm.Described rubber tile 17 is arranged at the both sides that doorframe 2 contacts with face glass.
As shown in Fig. 6 and Fig. 9, described connecting rod 27 is connected with doorframe 2 by angle box 23; Described the 3rd handle 24 is connected with connecting rod 9 by connecting rod 27 respectively with the 4th handle 25.As shown in Figure 9, described the 3rd handle 24 is connected with ring set 22 by screw 21, and described ring set 22 is for the protection of described link lock system.Wherein, described angle box is the thin wall construction part in aircraft, requires mechanical strength high and lightweight, and shape is more complicated, with machine tool, is difficult to processing.
As shown in Figure 8, the described first in command 4 is connected with doorframe 2 by sleeve pipe 20.
As shown in Figure 9, described the 4th handle 25 set-up modes are longitudinal sagging setting.
As shown in figure 10,
Wherein, described aircraft is agricultural aircraft.
In a kind of lower turning type aircraft door structure provided by the utility model, hatch door doorframe 2 is guaranteeing under the prerequisite of rigidity and intensity, adopt doorframe panel 202(to be preferably aluminum deck) and skeleton 201 weldments pumping nail riveted structure, hatch door thickness is 22mm only, and hatch door weight also alleviates greatly.Hatch door reduced thickness strengthens limited passenger cabin space, has improved the comfort level of passenger cabin.
Between face glass 3 and doorframe 2, after overlap joint, be spirally connected with press strip, the both sides that contact with doorframe 2 at face glass 3 are stained with respectively 0.5mm rubber tile 17 and guarantee the retentivity of face glass 3 contacts and be not scratched again.On face glass 3, have screw connecting hole; and on screw, rubber bushing 18 is installed when connecting; in the situation that guaranteeing conventional fixation; both protected the stroke expanding with heat and contract with cold of face glass 3; reduced again flutter and the resonance of glass when flight; reduce flight noise, rubber bushing 18 increases the contact area of screw and glass simultaneously, makes glass orifice edge bear extruding and participates in stressed.Hatch door doorframe 2 surroundings are preferably B052 finished product tubulose rubber seal section bar with sealing rubber and plastic section bar 19() with JX-15 gluing (not shown), be attached to around doorframe 2 after bound edge, its soft elasticity and the large feature of compressibilty have reduced collision at closing time, make hatch door sealing more tight, and again little on closing hatch door impact, after doorframe 2 bound edges, improved hatch door edge abrasion resistance and safety, made the presentation quality of hatch door reach high requirement.
This hatch door structure is greatly improved the operation and maintenance of aircraft door, and technique is relatively simple simultaneously, low cost of manufacture, and quality is easily controlled.Lower turning type structure makes staff pass in and out passenger cabin safe ready, adopt the latch mechanism of 2 contact self-lockings simple to operate, state is clear and definite, Internal handle is designed to the self-locking performance of downward lowering while both having considered latch mechanism locking, again driver's safety is taken into account, hatch door upper right side is provided with theftproof lock 8, has possessed general anti-theft feature, in order not take hatch door sight line, lock seat has been arranged on fuselage 26.When hatch door assembles, for providing technological compensa tion the doorframe panel 202(of doorframe 2 can be preferably to aluminum deck) edge has a mind to stay surplus, and make the gap of doorframe 2 edges and fuselage 26 repair surplus by file and guarantee.Doorframe 2 and fuselage 26 gaps after repairing file are even, and presentation quality is guaranteed.The method that this file is repaiied surplus makes to assemble easy realization coordination.Hatch door doorframe 2 surroundings are preferably B052 finished product tubulose rubber seal section bar with sealing rubber and plastic section bar 19(in addition) bound edge, because of soft elasticity and the compressibilty of sealing rubber and plastic section bar 19 large, do not need complicated manufacture and assembly technology just can guarantee that the jump between hatch door and fuselage is very little, presentation quality also just well guaranteed, cost of production is minimized.
The mode of occupation of a kind of lower turning type aircraft door structure provided by the utility model is as follows:
The more traditional hatch doors in aspect such as the opening direction of hatch door and link lock system, encapsulating method, visual field, safety, presentation quality have larger improvement.Hatch door is mainly preferably non-comminuted safe aerial organic glass by doorframe 2 and the thick face glass 3(of 3mm), link lock system, handle system, the first hinge 6 form, left side is provided with talking window 10, by opening window lock 13, can open talking window 10, can make correspondent just quick.
Driver, after unlocking anti-theft lock 8 out of my cabin, rotates counterclockwise the 3rd handle 24, the three handles 24 in link lock system by rotating shaft 27 drivening rods 9, and connecting rod 9 drives inserted links 1, thereby makes link lock system in opening, makes hatch door to opening completely.After entering in cabin, when closing hatch door, first draw the second in command 7 to make hatch door slowly closed, strain again the first in command 4, clockwise rotate the 4th handle 25, the four handles 25 by rotating shaft 27 drivening rods 9, connecting rod 9 drives inserted link 1 simultaneously, make inserted link 1 insert completely steel framework on fuselage 26 inner side to the 4th handle 25 in longitudinal hang, complete locking of hatch door.In cabin, can open talking window 10 by rotating window lock 13, and extraneous call, convenient and safe.
It should be noted that; above content is in conjunction with concrete embodiment further detailed description of the utility model; can not assert that the specific embodiment of the present utility model only limits to this; under above-mentioned guidance of the present utility model; those skilled in the art can carry out various improvement and distortion on the basis of above-described embodiment, and these improvement or distortion drop in protection domain of the present utility model.
Claims (10)
1. a lower turning type aircraft door structure, is characterized in that, described hatch door structure comprises:
One for forming the doorframe (2) of hatch door framework;
One for improving the face glass (3) of driver's seat;
One first in command (4) and the second in command (7) who closes for controlling hatch door;
The one link lock system for locking hatch door;
One for connecting first hinge (6) of doorframe (2) and fuselage (26);
Connecting rod system comprises:
One the 3rd handle (24) for opened door;
One the 4th handle (25) for locking hatch door;
One inserted link for locking hatch door (1);
One for controlling the prerotation vane (15) of inserted link (1) direction;
One for controlling connecting rod (9) and the rotating shaft (27) of inserted link (1);
One dead bolt (16) for matching with theftproof lock;
Described face glass (3) is connected with doorframe (2), described doorframe (2) is connected with fuselage (26) by the first hinge (6), handle system is connected with doorframe (2) respectively with link lock system, the described first in command (4) is connected with doorframe (2), and the second in command (7) is connected with doorframe (2) by brace (29);
Described the 3rd handle (24) is connected with rotating shaft (27) respectively with the 4th handle (25);
Rotating shaft (27), connecting rod (9) and inserted link (1) connect successively.
2. a kind of lower turning type aircraft door structure according to claim 1, is characterized in that,
Described hatch door structure also comprises:
One for driver and the extraneous talking window (10) contacting;
One lock of the window for locking talking window (10) system;
One for connecting second hinge (28) of talking window (10) and face glass (3);
One for antitheft theftproof lock (8);
One frame for the protection of talking window (10) (11);
Described window lock system comprises:
One for controlling the window lock (13) of talking window (10) closure or openness;
One snap close (12) for stationary window lock (13);
It is upper that described window lock (13) is arranged at talking window (10), and described snap close (12) is arranged on face glass (3);
Described talking window (10) is connected with face glass (3) by the second hinge (28), and described frame (11) is arranged on talking window (10).
3. a kind of lower turning type aircraft door structure according to claim 1, is characterized in that,
Described doorframe (2) comprising:
Skeleton (201);
The one doorframe panel (202) for coated described skeleton (201);
The one sealing rubber and plastic section bar (19) for the protection of doorframe (2);
Described sealing rubber and plastic section bar (19) is gluing in doorframe (2) edge;
Described skeleton (201) is connected with doorframe panel (202);
Described skeleton (201) is steel pipe skeleton, and described doorframe panel (202) is aluminum deck;
Described skeleton (201) is connected to form by welding manner by a straight steel pipe (2011) and a U-shaped steel pipe (2012).
4. a kind of lower turning type aircraft door structure according to claim 1, is characterized in that,
Described face glass (3) is aerial organic glass, and thickness is 3～5mm;
Described face glass (3) is connected with doorframe (2) by press strip (301), and described connected mode is that screw connects, and is provided with rubber bushing (18) on described screw;
Between described face glass (3) and doorframe (2), be also provided with rubber tile (17), the thickness of described rubber tile (17) is 0.5mm.
5. a kind of lower turning type aircraft door structure according to claim 1, is characterized in that:
Described link lock system also comprises:
One ring set for the protection of link lock system (22);
One rotating shaft for control link (9) (27);
Described rotating shaft (27) is connected with doorframe (2) by angle box (23);
Described the 3rd handle (24) is connected with connecting rod (9) by rotating shaft (27) respectively with the 4th handle (25).
6. a kind of lower turning type aircraft door structure according to claim 1, is characterized in that,
Described hatch door thickness is 21～23mm;
Described inserted link (1) is connected with fuselage (26) by prerotation vane (15).
7. a kind of lower turning type aircraft door structure according to claim 1, is characterized in that,
The described first in command (4) is connected with doorframe (2) by sleeve pipe (20).
8. a kind of lower turning type aircraft door structure according to claim 1, is characterized in that, described the 4th handle (25) set-up mode is longitudinal sagging setting.
9. a kind of lower turning type aircraft door structure according to claim 1, is characterized in that,
Described aircraft is agricultural aircraft.
10. a kind of lower turning type aircraft door structure according to claim 4, is characterized in that,
Described rubber tile (17) is arranged at the both sides that doorframe (2) contacts with face glass.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420245487.5U CN203891685U (en) | 2014-05-14 | 2014-05-14 | Flap-down type cabin door structure of aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420245487.5U CN203891685U (en) | 2014-05-14 | 2014-05-14 | Flap-down type cabin door structure of aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN203891685U true CN203891685U (en) | 2014-10-22 |
Family
ID=51718101
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420245487.5U Expired - Lifetime CN203891685U (en) | 2014-05-14 | 2014-05-14 | Flap-down type cabin door structure of aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN203891685U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105752312A (en) * | 2016-03-04 | 2016-07-13 | 江西洪都航空工业集团有限责任公司 | Glass compartment door structure of agriculture and forestry plane |
| CN106927015A (en) * | 2017-04-18 | 2017-07-07 | 河北天启通宇航空器材科技发展有限公司 | The control opener of rotor cabin door |
-
2014
- 2014-05-14 CN CN201420245487.5U patent/CN203891685U/en not_active Expired - Lifetime
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105752312A (en) * | 2016-03-04 | 2016-07-13 | 江西洪都航空工业集团有限责任公司 | Glass compartment door structure of agriculture and forestry plane |
| CN106927015A (en) * | 2017-04-18 | 2017-07-07 | 河北天启通宇航空器材科技发展有限公司 | The control opener of rotor cabin door |
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| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term |
Granted publication date: 20141022 |
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| CX01 | Expiry of patent term |