CN109677591A - A kind of aircraft landing gear folding and unfolding method and structure - Google Patents
A kind of aircraft landing gear folding and unfolding method and structure Download PDFInfo
- Publication number
- CN109677591A CN109677591A CN201910077124.2A CN201910077124A CN109677591A CN 109677591 A CN109677591 A CN 109677591A CN 201910077124 A CN201910077124 A CN 201910077124A CN 109677591 A CN109677591 A CN 109677591A
- Authority
- CN
- China
- Prior art keywords
- upper rack
- rack posts
- free end
- fulcrum bar
- lower fulcrum
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
- B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
- B64C25/12—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like sideways
Abstract
The invention discloses a kind of aircraft landing gear folding and unfolding method and structure, including undercarriage, the undercarriage includes action barrel, upper rack posts, lower fulcrum bar, supporting plate and tire, the action barrel includes fixing end and free end, the upper rack posts include fixing end and free end, the free end of the action barrel is located at the position fixed ends of upper rack posts, the lower fulcrum bar includes fixing end and free end, the free end of the upper rack posts and the free end of lower fulcrum bar connect, the fixing end of the lower fulcrum bar and one end of supporting plate connect, the other end of the supporting plate is located at the middle position on tire front end surface；Guard shield and blocking shell, which are all provided with, is set to intermediate half arc in left side and the outward shape in front and back end, influence of the unmanned plane tire awing by foreign objects such as branches is avoided to a certain extent, when unmanned plane failure is fallen, bumper housings bottom out, slide post movement and the first spring contraction reduce unmanned plane by the breakage for hitting generation to a certain extent.
Description
Technical field
The invention belongs to unmanned plane undercarriage technical fields, and in particular to aircraft landing gear.
Background technique
UAV referred to as " unmanned plane ", is manipulated using radio robot and the presetting apparatus provided for oneself
Not manned aircraft, or fully or intermittently automatically operated by car-mounted computer, unmanned plane presses application field, can be divided into
It is military with it is civilian, military aspect, unmanned plane is divided into reconnaissance plane and target drone；Civilian aspect, unmanned plane are unmanned planes in industrial application
Really just need；It taking photo by plane, agricultural, plant protection, miniature self-timer, express transportation, disaster relief, observation wild animal, monitoring at present
The application in infectious disease, mapping, news report, electric inspection process, the disaster relief, movies-making, manufacture romance etc. field, is greatly expanded
The purposes of unmanned plane itself, developed country also in actively extension industrial application and develop unmanned air vehicle technique；
The motion mode of the undercarriage of existing aircraft is using being upwards collected through to inboard, then just must be
The abdomen of unmanned aerial vehicle body designs accommodating chamber, will be open in the abdomen of unmanned aerial vehicle body, for aircraft, abdomen
Opening waterproof be very difficult problem, due to inside the particularity unmanned plane of aircraft use environment once intake, it will
The work of unmanned plane is seriously affected, while there are problems that tire is influenced by foreign object strikes such as branches in flight course, is
This is it is proposed that a kind of aircraft landing gear and its pack up mode.
Summary of the invention
The purpose of the present invention is to provide aircraft landing gear, mode and structure are packed up from newly devise undercarriage, with
The abdomen design accommodating chamber mentioned above in the background art avoided in unmanned aerial vehicle body is solved, water is can effectively prevent and passes through abdomen
Opening enters inside unmanned aerial vehicle body, while solving aircraft there are tires by the foreign object strikes shadow such as branch in flight course
Loud problem.
To achieve the above object, the invention provides the following technical scheme: aircraft landing gear, including undercarriage, described
Falling frame includes action barrel, upper rack posts, lower fulcrum bar, supporting plate and tire, and the action barrel includes fixing end and free end, the upper branch
Bar includes fixing end and free end, and the free end of the action barrel is located at the position fixed ends of upper rack posts, and the lower fulcrum bar includes
Fixing end and free end, the free end of the upper rack posts and the free end of lower fulcrum bar connect, the fixing end and branch of the lower fulcrum bar
One end of plate connects, and the other end of the supporting plate is located at the middle position on tire front end surface.
Preferably, it is provided with hinge between the free end of the upper rack posts and the free end of lower fulcrum bar and is screwed by screw
Connection, the action barrel, upper rack posts and lower fulcrum bar are oblique.
Preferably, when the undercarriage is in collapsed state, there is angle between the upper rack posts and lower fulcrum bar, tire is located at
Between upper rack posts and lower fulcrum bar position and be in supporting plate slanted top end position.
Preferably, when the undercarriage is in down state, the upper rack posts and lower fulcrum bar are on the same line, institute
It states tire and is located at supporting plate inclination bottom position.
Preferably, the middle position of the upper rack posts is provided with bindiny mechanism, and the bindiny mechanism includes the first connection half
Ring, the second connection semi-ring, the second connection semi-ring surface opposite with the first connection semi-ring is symmetrically arranged with position-limiting ear, described
The first connection semi-ring surface opposite with the second connection semi-ring symmetrically offers rectangular recess, and the position-limiting ear is embedded in the rectangle
Inside grooves.
Preferably, the front surface of the first connection semi-ring is provided with firm block, and the front surface of the firm block is provided with
Guard shield, the guard shield front surface and rear surface are respectively arranged with buffer gear, the buffer gear include fixed column,
Slide post and bumper housings, the fixed column are connected to the surface of guard shield, and the fixed column is internally provided with the first bullet
Spring.
Preferably, the slide post is located at one end inside fixed column and is arranged to T-shape structure, one end of first spring
The surface and the other end that are connected to guard shield are connected to the surface of slide post, and one end of the slide post is connected to bumper housings
Inner surface, the bumper housings are semicircular structure.
Preferably, the left-hand face of the guard shield is provided with blocking mechanism, and the blocking mechanism includes link block, steady
Gu column, mobile column and blocking shell, the link block are tightly attached to the surface of guard shield, the stable column is connected to link block table
Face, the mobile column are internally provided with the first sliding shoe, second spring and the second sliding shoe.
Preferably, first sliding shoe and the second sliding shoe are distributed in the end position of mobile column, second sliding
Close to the position of stable column, the stable column passes through mobile column surface and is embedded in the second sliding shoe interior surface block, and described second
Spring is in position between the first sliding shoe and second spring, and the blocking shell is arranged to semicircular structure, outside the protection
The right lateral surface of shell and tire left-hand face are hung down away from for 0.5cm.
The motion mode of aircraft landing gear, the undercarriage are upwards collected through to fuselage outer side, thus are avoided that in unmanned plane
The abdomen of fuselage designs accommodating chamber, can effectively prevent water and is entered inside unmanned aerial vehicle body by abdomen opening.
Compared with prior art, the beneficial effects of the present invention are: when unmanned plane takes off, undercarriage is in collapsed state,
There is angle between upper rack posts and lower fulcrum bar at this time, tire position and is in supporting plate slanted top end between upper rack posts and lower fulcrum bar
Position, guard shield is located at the forward position of tire at this time, while shell being stopped to be located at the forward position of guard shield, protects outer
Shell and blocking shell, which are all provided with, is set to intermediate half arc in left side and the outward shape in front and back end, avoids nobody to a certain extent
Wheel tire is awing influenced by foreign objects such as branches；
When unmanned plane lands, undercarriage is in down state, and upper rack posts and lower fulcrum bar are on the same line at this time, wheel
The position of foetus tilts bottom position in supporting plate, and when unmanned plane failure is fallen, bumper housings are bottomed out, and slide post is mobile and the first spring is received
Contracting reduces unmanned plane by the breakage for hitting generation to a certain extent.
Detailed description of the invention
Fig. 1 is the structural diagram of the present invention；
Fig. 2 is gear up structural schematic diagram of the invention；
Fig. 3 is gear down structural schematic diagram of the invention；
Fig. 4 is guard shield overlooking structure diagram of the invention；
Fig. 5 is fixed column schematic cross-sectional view of the invention；
In figure: 1, undercarriage；2, action barrel；3, upper rack posts；4, lower fulcrum bar；5, supporting plate；6, tire；7, hinge；8, it protects
Shell；9, buffer gear；10, blocking mechanism；11, block is consolidated；12, bindiny mechanism；91, fixed column；92, slide post；93, it buffers
Shell；94, the first spring；101, link block；102, stable column；103, mobile column；104, stop shell；105, the first sliding
Block；106, second spring；107, the second sliding shoe；121, the first connection semi-ring；122, the second connection semi-ring；123, position-limiting ear.
Specific embodiment
Following will be combined with the drawings in the embodiments of the present invention, and technical solution in the embodiment of the present invention carries out clear, complete
Site preparation description, it is clear that described embodiments are only a part of the embodiments of the present invention, instead of all the embodiments.It is based on
Embodiment in the present invention, it is obtained by those of ordinary skill in the art without making creative efforts every other
Embodiment shall fall within the protection scope of the present invention.
Embodiment
Fig. 1, Fig. 2, Fig. 3, Fig. 4, Fig. 5 are please referred to, the present invention provides a kind of technical solution: aircraft landing gear, including rises
Frame 1 is fallen, undercarriage 1 includes action barrel 2, upper rack posts 3, lower fulcrum bar 4, supporting plate 5 and tire 6, and action barrel 2 includes fixing end and freedom
End, upper rack posts 3 include fixing end and free end, and the free end of action barrel 2 is located at the position fixed ends of upper rack posts 3, upper rack posts 3
Middle position is provided with bindiny mechanism 12, and bindiny mechanism 12 includes that the first connection semi-ring 121, second connects semi-ring 122, and first connects
The front surface for connecing semi-ring 121 is provided with firm block 11, and the front surface of firm block 11 is provided with guard shield 8, a left side for guard shield 8
Side surface is provided with blocking mechanism 10, and blocking mechanism 10 includes link block 101, stable column 102, mobile column 103 and stops shell
104,8 front surface of guard shield and rear surface are respectively arranged with buffer gear 9, and buffer gear 9 includes fixed column 91, slide post 92
And bumper housings 93, fixed column 91 are connected to the surface of guard shield 8, lower fulcrum bar 4 includes fixing end and free end, upper rack posts 3
Free end connect with the free end of lower fulcrum bar 4, the fixing end of lower fulcrum bar 4 is connect with one end of supporting plate 5, the other end of supporting plate 5
Positioned at the middle position of 6 front-end surface of tire.
In the present embodiment, it is preferred that be provided with hinge 7 between the free end of upper rack posts 3 and the free end of lower fulcrum bar 4 and lead to
It crosses screw and screws connection, action barrel 2, upper rack posts 3 and lower fulcrum bar 4 are oblique, when undercarriage 1 is in collapsed state, upper rack posts 3
There is angle between lower fulcrum bar 4, tire 6 position and is in 5 slanted top end position of supporting plate between upper rack posts 3 and lower fulcrum bar 4,
When undercarriage 1 is in down state, upper rack posts 3 and lower fulcrum bar 4 are on the same line, and tire 6 is located at supporting plate 5 and tilts bottom end
Position.
In the present embodiment, it is preferred that the second connection semi-ring 122 connect the opposite surface of semi-ring 121 with first and is symmetrical arranged
There is position-limiting ear 123, the first connection semi-ring 121 connect the opposite surface of semi-ring 122 with second and symmetrically offers rectangular recess, limits
Ear 123 is embedded in inside rectangular recess.
In the present embodiment, it is preferred that fixed column 91 is internally provided with the first spring 94, and slide post 92 is located at fixed column 91
Internal one end is arranged to T-shape structure, and one end of the first spring 94 is connected to the surface of guard shield 8 and the other end is connected to cunning
The surface of dynamic column 92, one end of slide post 92 are connected to 93 inner surface of bumper housings, and bumper housings 93 are semicircular structure.
In the present embodiment, it is preferred that link block 101 is tightly attached to the surface of guard shield 8, and stable column 102 is connected to connection
101 surface of block, mobile column 103 are internally provided with the first sliding shoe 105, second spring 106 and the second sliding shoe 107.
In the present embodiment, it is preferred that the first sliding shoe 105 and the second sliding shoe 107 are distributed in the end position of mobile column 103
It sets, close to the position of stable column 102, stable column 102 passes through 103 surface of mobile column and is embedded in the second sliding the second sliding shoe 107
107 interior surface of block, second spring 106 are in position between the first sliding shoe 105 and second spring 106, and shell 104 is stopped to set
It is set to semicircular structure, the right lateral surface of guard shield 8 and 6 left-hand face of tire are hung down away from for 0.5cm.
The undercarriage has upper fixing end and lower fixing end, and action barrel 2 is located on strut 3, the strut 3 and strut 4 by
Hinge 7 connects, and the tire 6 is fixed on supporting plate 5.1 undercarriage work when, action barrel 2 shorten, pull strut 3, strut 4 to
It inside packs up, strut 4 drives supporting plate 5, tire 6 to be upwards collected through, and until tire reaches designated position, undercarriage is upward to fuselage outer side
It packs up, thus is avoided that and designs accommodating chamber in the abdomen of unmanned aerial vehicle body, can effectively prevent water by abdomen opening and enter unmanned plane
Fuselage interior.Guard shield 8 is located at the forward position of tire 6 at this time, while shell 104 being stopped to be located at the front side of guard shield 8
Position, guard shield 8 and blocking shell 104, which are all provided with, is set to intermediate half arc in left side and the outward shape in front and back end, one
The influence by foreign objects such as branches awing of tire 6 that unmanned plane is avoided in degree is determined, when unmanned plane lands, at undercarriage 1
In down state, upper rack posts 3 and lower fulcrum bar 4 are on the same line at this time, and tire 6 is located at supporting plate 5 and tilts bottom position, when
When unmanned plane failure is fallen, bumper housings 93 are bottomed out, and slide post 92 is mobile and the first spring 94 is shunk, and are reduced to a certain extent
Unmanned plane is by the breakage for hitting generation.
It although an embodiment of the present invention has been shown and described, for the ordinary skill in the art, can be with
A variety of variations, modification, replacement can be carried out to these embodiments without departing from the principles and spirit of the present invention by understanding
And modification, the scope of the present invention is defined by the appended.
Claims (10)
1. a kind of aircraft landing gear structure, including undercarriage (1), it is characterised in that: the undercarriage (1) includes action barrel
(2), upper rack posts (3), lower fulcrum bar (4), supporting plate (5) and tire (6), the action barrel (2) include fixing end and free end, described
Upper rack posts (3) include fixing end and free end, and the free end of the action barrel (2) is located at the position fixed ends of upper rack posts (3), institute
Stating lower fulcrum bar (4) includes fixing end and free end, and the free end of the upper rack posts (3) is connect with the free end of lower fulcrum bar (4), institute
The fixing end for stating lower fulcrum bar (4) is connect with one end of supporting plate (5), and the other end of the supporting plate (5) is located at tire (6) front-end surface
Middle position.
2. aircraft landing gear according to claim 1, it is characterised in that: the free end of the upper rack posts (3) and lower branch
Be provided with hinge (7) between the free end of bar (4) and connection screwed by screw, the action barrel (2), upper rack posts (3) and under
Strut (4) is oblique.
3. aircraft landing gear according to claim 1, it is characterised in that: when the undercarriage (1) is in collapsed state,
Have angle between the upper rack posts (3) and lower fulcrum bar (4), tire (6) be located between upper rack posts (3) and lower fulcrum bar (4) position and
In supporting plate (5) slanted top end position.
4. aircraft landing gear according to claim 1, it is characterised in that: when the undercarriage (1) is in down state,
The upper rack posts (3) and lower fulcrum bar (4) are on the same line, and the tire (6) is located at supporting plate (5) inclination bottom position.
5. aircraft landing gear according to claim 1, it is characterised in that: the middle position of the upper rack posts (3) is arranged
Having bindiny mechanism (12), the bindiny mechanism (12) includes the first connection semi-ring (121), the second connection semi-ring (122), and described the
Two connections semi-ring (122) connect the opposite surface of semi-ring (121) with first and are symmetrically arranged with position-limiting ear (123), and described first connects
It connects semi-ring (121) and connect the opposite surface of semi-ring (122) with second and symmetrically offer rectangular recess, the position-limiting ear (123) is embedding
Enter inside the rectangular recess.
6. aircraft landing gear according to claim 5, it is characterised in that: the preceding table of first connection semi-ring (121)
Face is provided with firm block (11), and the front surface of the firm block (11) is provided with guard shield (8), before the guard shield (8)
Surface and rear surface are respectively arranged with buffer gear (9), the buffer gear (9) include fixed column (91), slide post (92) and
Bumper housings (93), the fixed column (91) are connected to the surface of guard shield (8), and fixed column (91) are internally provided with
First spring (94).
7. aircraft landing gear according to claim 6, it is characterised in that: the slide post (92) is located at fixed column (91)
Internal one end is arranged to T-shape structure, and one end of first spring (94) is connected to surface and the other end of guard shield (8)
It is connected to the surface of slide post (92), one end of the slide post (92) is connected to bumper housings (93) inner surface, the buffering
Shell (93) is semicircular structure.
8. aircraft landing gear according to claim 1, it is characterised in that: the left-hand face of the guard shield (8) is set
It is equipped with blocking mechanism (10), the blocking mechanism (10) includes link block (101), stable column (102), mobile column (103) and resistance
It keeps off shell (104), the link block (101) is tightly attached to the surface of guard shield (8), and the stable column (102) is connected to connection
Block (101) surface, the mobile column (103) are internally provided with the first sliding shoe (105), second spring (106) and the second cunning
Motion block (107).
9. aircraft landing gear according to claim 8, it is characterised in that: first sliding shoe (105) and the second cunning
Motion block (107) is distributed in the end position of mobile column (103), position of the second sliding shoe (107) close to stable column (102)
It sets, the stable column (102) passes through mobile column (103) surface and is embedded in the second sliding shoe (107) interior surface, second bullet
Spring (106) is in position between the first sliding shoe (105) and second spring (106), and the blocking shell (104) is arranged to semicircle
Shape structure, the right lateral surface of the guard shield (8) and tire (6) left-hand face are hung down away from for 0.5cm.
10. a kind of aircraft landing gear folding and unfolding method, it is characterised in that: the undercarriage is upwards collected through to fuselage outer side.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910077124.2A CN109677591A (en) | 2019-01-27 | 2019-01-27 | A kind of aircraft landing gear folding and unfolding method and structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910077124.2A CN109677591A (en) | 2019-01-27 | 2019-01-27 | A kind of aircraft landing gear folding and unfolding method and structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN109677591A true CN109677591A (en) | 2019-04-26 |
Family
ID=66194820
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201910077124.2A Pending CN109677591A (en) | 2019-01-27 | 2019-01-27 | A kind of aircraft landing gear folding and unfolding method and structure |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109677591A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114030593A (en) * | 2021-11-03 | 2022-02-11 | 南京甲子智能科技有限公司 | Vertical take-off and landing unmanned aerial vehicle |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN206367583U (en) * | 2016-12-23 | 2017-08-01 | 芜湖元一航空科技有限公司 | A kind of unmanned plane foot stool |
| CN207644629U (en) * | 2017-09-30 | 2018-07-24 | 深圳市本仕传动科技有限公司 | A kind of wheel-retracting gear |
| CN207943165U (en) * | 2017-10-30 | 2018-10-09 | 深圳市大疆创新科技有限公司 | A kind of unmanned vehicle and its ascending, descending frame |
| CN208086000U (en) * | 2018-04-17 | 2018-11-13 | 江西中轻智能设备有限公司 | A kind of scape unmanned plane undercarriage |
| EP3418188A1 (en) * | 2017-06-19 | 2018-12-26 | Airbus Operations Limited | Landing gear |
-
2019
- 2019-01-27 CN CN201910077124.2A patent/CN109677591A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN206367583U (en) * | 2016-12-23 | 2017-08-01 | 芜湖元一航空科技有限公司 | A kind of unmanned plane foot stool |
| EP3418188A1 (en) * | 2017-06-19 | 2018-12-26 | Airbus Operations Limited | Landing gear |
| CN207644629U (en) * | 2017-09-30 | 2018-07-24 | 深圳市本仕传动科技有限公司 | A kind of wheel-retracting gear |
| CN207943165U (en) * | 2017-10-30 | 2018-10-09 | 深圳市大疆创新科技有限公司 | A kind of unmanned vehicle and its ascending, descending frame |
| CN208086000U (en) * | 2018-04-17 | 2018-11-13 | 江西中轻智能设备有限公司 | A kind of scape unmanned plane undercarriage |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114030593A (en) * | 2021-11-03 | 2022-02-11 | 南京甲子智能科技有限公司 | Vertical take-off and landing unmanned aerial vehicle |
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| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20190426 |
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