CN207580153U - A kind of aircraft takeoffs and landings rack device with heat sinking function - Google Patents
A kind of aircraft takeoffs and landings rack device with heat sinking function Download PDFInfo
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- CN207580153U CN207580153U CN201721636020.3U CN201721636020U CN207580153U CN 207580153 U CN207580153 U CN 207580153U CN 201721636020 U CN201721636020 U CN 201721636020U CN 207580153 U CN207580153 U CN 207580153U
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- storage tank
- aircraft
- connecting plate
- idler wheel
- connecting rod
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Abstract
The utility model discloses a kind of aircraft takeoffs and landings rack device with heat sinking function, including fixing bracket, connector, connecting rod, idler wheel, diagonal brace bar assembly, spring, cooling mechanism, lockable mechanism etc..Its by between fixing bracket and connecting rod set diagonal brace bar assembly, connecting rod and idler wheel can be placed in the second storage tank and third storage tank of aircraft compartment when taking off, it is simple in structure, small, easy to operate；It can play certain cushioning effect by setting spring in diagonal brace bar assembly；It is by setting cooling mechanism, when idler wheel is recovered to third storage tank, can radiate to idler wheel, avoid temperature excessively high, influence device service life；Idler wheel when idler wheel is recovered to third storage tank, can be parked on lockable mechanism by setting lockable mechanism, reduce the pressure of diagonal brace bar assembly, extend the service life of device by it.
Description
Technical field：
The utility model belongs to airplane equipment technical field, and it is rack-mounted to be specifically related to a kind of aircraft takeoffs and landings with heat sinking function
It puts.
Background technology：
Undercarriage is one of important safety feature of aircraft, is to take off, land, ground taxi and parking
When main load-carrying member, undercarriage during aircraft landing and sliding, to absorb and dissipate from ground shock
Energy, safety during ensureing aircraft landing and slide, the performance level of undercarriage are directly related to aircraft overall performance and fly
Row safety, is always that domestic and international large aircraft manufacturing company endeavours one of improved key member.
Undercarriage is movable between scrolling position and deposit position, and in scrolling position, undercarriage causes aircraft
It can ensure to roll on runway during landing or taking off；In deposit position, when aircraft flight, undercarriage is contained
Into in undercarriage compartment.Existing aircraft landing gear structures are complicated, and skeleton is big, it is not easy to be placed in undercarriage compartment；It is and existing
Be not provided with radiator in undercarriage compartment on some undercarriages, the landing gear risen after taking off take off go to it is sliding
Temperature is high after row, particularly summer, be easy to cause component and crosses cause thermal damage.
Utility model content：
For this purpose, the technical problem to be solved by the utility model is to the complexity of aircraft landing gear structures in the prior art, bones
Frame is big, is not easy to be placed in undercarriage compartment, radiator is not provided with, so as to propose a kind of aircraft takeoffs and landings with heat sinking function
Rack device.
In order to achieve the above objectives, the technical solution of the utility model is as follows：
A kind of aircraft takeoffs and landings rack device with heat sinking function, including：
Fixing bracket, the fixing bracket are fixedly mounted on by connector in the first storage tank of aircraft compartment.
Connecting rod and idler wheel, the first end of the connecting rod are hinged with the fixing bracket, and the second end of the connecting rod is connected with
Idler wheel, the connecting rod are arranged in the second storage tank of the aircraft compartment, and the idler wheel is arranged on the of the aircraft compartment
In three storage tanks.
Diagonal brace bar assembly, the diagonal brace bar assembly include the first connecting plate, damper, the second connecting plate, and described first connects
The first end of fishplate bar is hinged on the support bracket fastened side wall, and the first of the second end connection damper of first connecting plate
End, the second end of the damper connect the first end of second connecting plate, and the second end of second connecting plate is hinged on
On the side wall of the connecting rod.
Spring, for the spring sleeve on the damper, the first end of the spring connects first connecting plate
Second end, the second end of the spring connect the first end of second connecting plate.
Cooling mechanism, the cooling mechanism include wind turbine, and the wind turbine is arranged on the 4th appearance on the third storage tank
It puts in slot, the third storage tank both sides have been separately formed ventilation slot, and multiple ventilation holes are formed on the side wall of the ventilation slot,
The wind pipe of the wind turbine is connected with the ventilation slot.
Lockable mechanism, two lockable mechanisms are separately positioned on the opposite madial wall of the third storage tank, described
Lockable mechanism includes driving cylinder and snap-gauge, the first end of snap-gauge, the driving described in the output axis connection of the driving cylinder
Cylinder and the snap-gauge are arranged in the 5th storage tank of aircraft compartment.
As a preferred embodiment of the above technical solution, first storage tank in the aircraft compartment, second storage tank,
Third storage tank connects.
As a preferred embodiment of the above technical solution, the wheel fork being oppositely arranged there are two the second end moldings of the connecting rod, two
Roller bearing is provided between the wheel fork, the idler wheel sleeve is on the roller bearing.
As a preferred embodiment of the above technical solution, symmetrically arranged two first is formed on the support bracket fastened side wall
Ear and the first articulated shaft being arranged between described two first journal stirrups, the first end of first connecting plate are hinged on described
On one articulated shaft.
As a preferred embodiment of the above technical solution, formed on the side wall of the connecting rod symmetrically arranged two the second journal stirrups and
The second articulated shaft being arranged between described two second journal stirrups, the second end of second connecting plate are hinged on second hinge
In spindle.
As a preferred embodiment of the above technical solution, the second end of the snap-gauge forms multiple triangle clamping blocks, two pieces of cards
Triangle clamping block on plate mutually fastens.
The beneficial effects of the utility model are：It is risen by setting diagonal brace bar assembly between fixing bracket and connecting rod
Connecting rod and idler wheel can be placed in the second storage tank and third storage tank of aircraft compartment when winged, simple in structure, small,
It is easy to operate；It can play certain cushioning effect by setting spring in diagonal brace bar assembly；It is by setting heat dissipation machine
Structure when idler wheel is recovered to third storage tank, can radiate to idler wheel, avoid temperature excessively high, influence device service life；Its
By setting lockable mechanism, when idler wheel is recovered to third storage tank, idler wheel can be parked on lockable mechanism, reduce diagonal brace
The pressure of bar assembly extends the service life of device.
Description of the drawings：
The following drawings is only intended in doing schematic illustration and explanation to the utility model, does not limit the model of the utility model
It encloses.Wherein：
Fig. 1 is a kind of undercarriage apparatus structure schematic diagram with heat sinking function of the utility model one embodiment；
Fig. 2 is the third groove sectional view of the utility model one embodiment；
Fig. 3 is the hound component structure diagram of the utility model one embodiment.
Symbol description in figure：
1- fixing brackets, 2- aircraft compartments, 3- connectors, 4- connecting rods, 5- diagonal brace bar assemblies, the first connecting plates of 6-, 7- resistances
Buddhist nun's device, the second connecting plates of 8-, 9- springs, 10- idler wheels, 11- cooling mechanisms, 12- wind turbines, 13- lockable mechanisms, 14- driving cylinders,
15- snap-gauges, 16- wheel forks, 17- roller bearings, the first journal stirrups of 101-, the first articulated shafts of 102-, the second journal stirrups of 401-, 402- second are hinged
Axis, the first storage tanks of 201-, the second storage tanks of 202-, 203- third storage tanks, the 4th storage tanks of 204-, 205- ventilation slots,
206- ventilation holes, the 5th storage tanks of 207-, 1501- clamping blocks.
Specific embodiment：
As shown in Figure 1, a kind of aircraft takeoffs and landings rack device with heat sinking function of the utility model, including：
Fixing bracket 1, the fixing bracket 1 are fixedly mounted on the first storage tank 201 of aircraft compartment 2 by connector 3
It is interior.
Connecting rod 4 and idler wheel 10, the first end of the connecting rod 4 is hinged with the fixing bracket 1, the second end of the connecting rod 4
Idler wheel 10 is connected with, the connecting rod 4 is arranged in the second storage tank 202 of the aircraft compartment 2, and the idler wheel 10 is arranged on institute
It states in the third storage tank 203 of aircraft compartment 2.It is first storage tank 201 in the aircraft compartment 2, described second accommodating
Slot 202, third storage tank 203 connect.The wheel fork 16 that there are two the second end moldings of the connecting rod 4 is oppositely arranged, described in two
Roller bearing 17 is provided between wheel fork 16,10 sleeve of idler wheel is on the roller bearing 17.
Diagonal brace bar assembly 5, as shown in figure 3, the diagonal brace bar assembly 5 includes the first connecting plate 6, damper 7, second connects
Plate 8, the first end of first connecting plate 6 are hinged on the side wall of the fixing bracket 1, and the second of first connecting plate 6
The first end of end connection damper 7, the first end of second end connection second connecting plate 8 of the damper 7, described second
The second end of connecting plate 8 is hinged on the side wall of the connecting rod 4.
Symmetrically arranged two the first journal stirrups 101 are formed on the side wall of the fixing bracket 1 and are arranged on described two
The first articulated shaft 102 between first journal stirrup 101, the first end of first connecting plate 6 are hinged on first articulated shaft 102
On.Symmetrically arranged two the second journal stirrups 401 are formed on the side wall of the connecting rod 4 and are arranged on described two second journal stirrups
The second articulated shaft 402 between 401, the second end of second connecting plate 8 are hinged on second articulated shaft 402.
Spring 9,9 sleeve of spring is on the damper 7, first end connection first connection of the spring 9
The second end of plate 6, the second end of the spring 9 connect the first end of second connecting plate 8.
Cooling mechanism 11, the cooling mechanism 11 include wind turbine 12, and the wind turbine 12 is arranged on the third storage tank 203
On the 4th storage tank 204 in, 203 both sides of third storage tank have been separately formed ventilation slot 205, the ventilation slot 205
Multiple ventilation holes 206 are formed on side wall, the wind pipe of the wind turbine 12 is connected with the ventilation slot 205.
Lockable mechanism 13, as shown in Fig. 2, two lockable mechanisms 13 are separately positioned on 203 phase of third storage tank
To madial wall on, the lockable mechanism 13 includes driving cylinder 14 and snap-gauge 15, the output axis connection of the driving cylinder 14
The first end of the snap-gauge 15, the driving cylinder 14 and the snap-gauge 15 are arranged on the 5th storage tank 207 of aircraft compartment 2
It is interior.The second end of the snap-gauge 15 forms multiple triangle clamping blocks 1501, the triangle clamping block on two pieces of snap-gauges 15
1501 mutually fasten.
A kind of aircraft takeoffs and landings rack device with heat sinking function described in the present embodiment, including fixing bracket, connector, company
Bar, idler wheel, diagonal brace bar assembly, spring, cooling mechanism, lockable mechanism etc..It is oblique by being set between fixing bracket and connecting rod
Connecting rod and idler wheel can be placed in the second storage tank and third storage tank of aircraft compartment, structure by strut component when taking off
Simply, it is small, easy to operate；It can play certain cushioning effect by setting spring in diagonal brace bar assembly；It is logical
Setting cooling mechanism is crossed, when idler wheel is recovered to third storage tank, can be radiated to idler wheel, be avoided temperature excessively high, influence device
Part service life；Idler wheel when idler wheel is recovered to third storage tank, can be parked in locking machine by it by setting lockable mechanism
On structure, reduce the pressure of diagonal brace bar assembly, extend the service life of device.
Obviously, the above embodiments are merely examples for clarifying the description, and is not intended to limit the embodiments.It is right
For those of ordinary skill in the art, can also make on the basis of the above description it is other it is various forms of variation or
It changes.There is no necessity and possibility to exhaust all the enbodiments.And the obvious variation thus extended out or
Among the protection domain that variation is created still in the utility model.
Claims (6)
1. a kind of aircraft takeoffs and landings rack device with heat sinking function, which is characterized in that including：
Fixing bracket (1), the fixing bracket (1) are fixedly mounted on the first storage tank of aircraft compartment (2) by connector (3)
(201) in；
Connecting rod (4) and idler wheel (10), the first end and the fixing bracket (1) of the connecting rod (4) are hinged, the connecting rod (4)
Second end is connected with idler wheel (10), and the connecting rod (4) is arranged in the second storage tank (202) of the aircraft compartment (2), described
Idler wheel (10) is arranged in the third storage tank (203) of the aircraft compartment (2)；
Diagonal brace bar assembly (5), the diagonal brace bar assembly (5) include the first connecting plate (6), damper (7), the second connecting plate (8),
The first end of first connecting plate (6) is hinged on the side wall of the fixing bracket (1), and the of first connecting plate (6)
The first end of two end connection dampers (7), the second end of the damper (7) connect the first end of second connecting plate (8),
The second end of second connecting plate (8) is hinged on the side wall of the connecting rod (4)；
Spring (9), spring (9) sleeve is on the damper (7), the first end connection described first of the spring (9)
The second end of connecting plate (6), the second end of the spring (9) connect the first end of second connecting plate (8)；
Cooling mechanism (11), the cooling mechanism (11) include wind turbine (12), and the wind turbine (12) is arranged on the third and houses
In the 4th storage tank (204) on slot (203), third storage tank (203) both sides have been separately formed ventilation slot (205), institute
It states and multiple ventilation holes (206) is formed on the side wall of ventilation slot (205), wind pipe and the ventilation slot of the wind turbine (12)
(205) it connects；
Lockable mechanism (13), two lockable mechanisms (13) are separately positioned on the opposite inside of the third storage tank (203)
On wall, the lockable mechanism (13) includes driving cylinder (14) and snap-gauge (15), the output axis connection of the driving cylinder (14)
The first end of the snap-gauge (15), the driving cylinder (14) and the snap-gauge (15), which are arranged on the 5th of aircraft compartment (2), to be held
It puts in slot (207).
2. a kind of aircraft takeoffs and landings rack device with heat sinking function according to claim 1, it is characterised in that：
First storage tank (201) in the aircraft compartment (2), second storage tank (202), third storage tank
(203) it connects.
3. a kind of aircraft takeoffs and landings rack device with heat sinking function according to claim 1, it is characterised in that：
The second end molding of the connecting rod (4) is set between two wheel forks (16) there are two the wheel fork (16) that is oppositely arranged
There is roller bearing (17), idler wheel (10) sleeve is on the roller bearing (17).
4. a kind of aircraft takeoffs and landings rack device with heat sinking function according to claim 1, it is characterised in that：
Symmetrically arranged two the first journal stirrups (101) are formed on the side wall of the fixing bracket (1) and are arranged on described two
The first articulated shaft (102) between first journal stirrup (101), the first end of first connecting plate (6) are hinged on first hinge
In spindle (102).
5. a kind of aircraft takeoffs and landings rack device with heat sinking function according to claim 1, it is characterised in that：
Symmetrically arranged two the second journal stirrups (401) are formed on the side wall of the connecting rod (4) and are arranged on described two second
The second articulated shaft (402) between journal stirrup (401), the second end of second connecting plate (8) are hinged on second articulated shaft
(402) on.
6. a kind of aircraft takeoffs and landings rack device with heat sinking function according to claim 1, it is characterised in that：
The second end of the snap-gauge (15) forms multiple triangle clamping blocks (1501), the triangle card on two pieces of snap-gauges (15)
Block (1501) is closed mutually to fasten.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721636020.3U CN207580153U (en) | 2017-11-30 | 2017-11-30 | A kind of aircraft takeoffs and landings rack device with heat sinking function |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201721636020.3U CN207580153U (en) | 2017-11-30 | 2017-11-30 | A kind of aircraft takeoffs and landings rack device with heat sinking function |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN207580153U true CN207580153U (en) | 2018-07-06 |
Family
ID=62734474
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201721636020.3U Active CN207580153U (en) | 2017-11-30 | 2017-11-30 | A kind of aircraft takeoffs and landings rack device with heat sinking function |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN207580153U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114275150A (en) * | 2022-01-19 | 2022-04-05 | 中国商用飞机有限责任公司 | Cabin door device for assisting emergency landing gear release and airplane comprising cabin door device |
-
2017
- 2017-11-30 CN CN201721636020.3U patent/CN207580153U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114275150A (en) * | 2022-01-19 | 2022-04-05 | 中国商用飞机有限责任公司 | Cabin door device for assisting emergency landing gear release and airplane comprising cabin door device |
| CN114275150B (en) * | 2022-01-19 | 2024-05-14 | 中国商用飞机有限责任公司 | Cabin door device for assisting in emergency release of landing gear and aircraft comprising such a device |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20190724 Address after: 312500 No. 1 Aofeng Road, Xinchang Industrial Park, Xinchang County, Shaoxing City, Zhejiang Province Patentee after: Wanfeng Aircraft Industry Co., Ltd. Address before: 312500 No. 1 Aofeng Road, Xinchang Industrial Park, Xinchang County, Shaoxing City, Zhejiang Province Patentee before: Wanfeng Aviation Industry Co Ltd |
|
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20220217 Address after: 312500 No.1-3 (building 1-5), Aofeng Road, Wozhou Town, Xinchang County, Shaoxing City, Zhejiang Province Patentee after: Zhejiang Wanfeng Aircraft Manufacturing Co.,Ltd. Address before: 312500 No.1 Aofeng Road, Xinchang Industrial Park, Xinchang County, Shaoxing City, Zhejiang Province Patentee before: Wanfeng Aircraft Industry Co.,Ltd. |