CN106143880A - Depopulated helicopter undercarriage - Google Patents
Depopulated helicopter undercarriage Download PDFInfo
- Publication number
- CN106143880A CN106143880A CN201610596157.4A CN201610596157A CN106143880A CN 106143880 A CN106143880 A CN 106143880A CN 201610596157 A CN201610596157 A CN 201610596157A CN 106143880 A CN106143880 A CN 106143880A
- Authority
- CN
- China
- Prior art keywords
- motion bar
- cavity volume
- depopulated helicopter
- baffle plate
- hole
- 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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C25/00—Alighting gear
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/58—Arrangements or adaptations of shock-absorbers or springs
- B64C25/62—Spring shock-absorbers; Springs
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Vibration Dampers (AREA)
Abstract
The invention discloses depopulated helicopter undercarriage, including: underframe, connect post, motion bar, damping spring, connecting plate and baffle plate, connect post and be vertically arranged in the upper surface of underframe, connect and be vertically provided with cavity volume inside post, connect post upper end and be provided with the first through hole, first through hole is connected with cavity volume, motion bar passes vertically through the first through hole, and motion bar is at least partially disposed in cavity volume, the lower end of motion bar and the upper surface Joint of connecting plate, damping spring is arranged in cavity volume, and the lower surface of one end of damping spring and connecting plate fixes, the other end is fixed on the bottom of cavity volume, motion bar is positioned on the body of rod outside cavity volume and is socketed with baffle plate, connect post at least provided with two.This depopulated helicopter undercarriage overcomes in prior art, does not has buffer unit and be connected the most loosening between helicopter landing gear with body, when helicopter lands, and the problem that body is caused damage by temporary impact.
Description
Technical field
The present invention relates to depopulated helicopter field, in particular it relates to depopulated helicopter undercarriage.
Background technology
The most conventional unmanned helicopter landing gear all uses metal material to make, and is directly installed on helicopter body
Both sides, lower section, Hard link structure commonly used with helicopter.The undercarriage rigidity of this material and structure is too strong, and helicopter rises and falls
There is no buffer unit between frame with body and be connected the most loosening.The slow of landing gear structure buffering is only relied on when helicopter lands
Punching effect can not preferably solve the temporary impact damage to body, even can destroy the built-in equipment of body or instrument.?
This it is rigidly connected under mounting means, owing to vibrations, the undercarriage of aircraft wear and tear with body coupling part, causes undercarriage to connect
Loosen, make aircraft flight unstable under helicopter loading condition.
Therefore provide a kind of and efficiently solve the temporary impact damage to body when unmanned helicopter lands, thus
Protection body, the depopulated helicopter undercarriage extending unmanned helicopter service life is the problem that the present invention needs solution badly.
Summary of the invention
For above-mentioned prior art, it is an object of the invention to, overcome in prior art, unmanned helicopter landing gear with
Helicopter commonly used Hard link structure, does not has buffer unit and is connected the most loosening between helicopter landing gear with body, when
During helicopter landing, the temporary impact problem to the damage of body, thus provide a kind of when unmanned helicopter lands, effectively
Ground solves the temporary impact damage to body, thus protects body, extends the depopulated helicopter in unmanned helicopter service life
Undercarriage.
To achieve these goals, the invention provides a kind of depopulated helicopter undercarriage, described depopulated helicopter rises and falls
Frame includes: underframe, connection post, motion bar, damping spring, connecting plate and baffle plate, described connection post is vertically arranged in the described end
The upper surface of frame, is vertically provided with cavity volume inside described connection post, described connection post upper end is provided with the first through hole, institute
Stating the first through hole to be connected with described cavity volume, described motion bar passes vertically through described first through hole, and described motion bar at least portion
Dividing and be arranged in described cavity volume, the lower end of described motion bar and the upper surface Joint of described connecting plate, described damping spring sets
Putting in described cavity volume, and the lower surface of one end of described damping spring and described connecting plate fixes, the other end is fixed on institute
Stating the bottom of cavity volume, described motion bar is positioned on the body of rod outside described cavity volume and is socketed with described baffle plate, and described connection post is at least
Arrange two.
Preferably, the upper surface of described connection post is provided with on cushion pad, and described cushion pad and is provided with and described first
The second through hole that through hole matches.
Preferably, described motion bar is cylinder, and described motion bar is positioned on the side face of the body of rod above described baffle plate
It is provided with external screw thread.
Preferably, described depopulated helicopter undercarriage also includes the self-locking nut matched with described external screw thread, described from
Split nut is arranged on described motion bar, and is positioned at above described baffle plate.
Preferably, the upper surface of described baffle plate is provided with multiple projection.
Preferably, the lower surface of described underframe is provided with rubber sheet gasket.
According to technique scheme, the depopulated helicopter undercarriage that the present invention provides is by arranging described motion bar and described
Damping spring matches, thus when being landed by depopulated helicopter, ground is inhaled effectively in the face of the instantaneous impulse force of depopulated helicopter landing
Receipts are fallen, then protect the body of depopulated helicopter, extend the service life of depopulated helicopter, and arrange described on described connection post
Baffle plate, impulse force when preventing depopulated helicopter from landing is too big, and described damping spring cannot effectively absorb impulse force, then arrange institute
State baffle plate to coordinate described damping spring to protect described body together.The depopulated helicopter undercarriage of the present invention overcomes existing skill
In art, unmanned helicopter landing gear and helicopter commonly used Hard link structure, do not have between helicopter landing gear and body
Buffer unit and connection easily loosen, when helicopter lands, and the temporary impact problem to the damage of body.
Other features and advantages of the present invention will be described in detail in detailed description of the invention part subsequently.
Accompanying drawing explanation
Accompanying drawing is used to provide a further understanding of the present invention, and constitutes the part of description, with following tool
Body embodiment is used for explaining the present invention together, but is not intended that limitation of the present invention.In the accompanying drawings:
Fig. 1 is the structural representation of a kind of preferred embodiment middle depopulated helicopter undercarriage provided of the present invention；
Fig. 2 is the section view connecting post on a kind of preferred embodiment middle depopulated helicopter undercarriage provided of the present invention
Figure.
Description of reference numerals
1 underframe 2 connects post
3 rubber sheet gasket 4 motion bars
5 connecting plate 6 damping springs
7 cushion pad 8 baffle plates
9 cavity volumes
Detailed description of the invention
Below in conjunction with accompanying drawing, the detailed description of the invention of the present invention is described in detail.It should be appreciated that this place is retouched
The detailed description of the invention stated is merely to illustrate and explains the present invention, is not limited to the present invention.
In the present invention, in the case of illustrating on the contrary, the noun of locality that " upper and lower " etc. is included in term only represents
This term orientation under normal service condition, or for being commonly called as of skilled artisan understands that, and be not construed as this term
Restriction.
Such as Fig. 1, the invention provides a kind of depopulated helicopter undercarriage, described depopulated helicopter undercarriage includes: underframe
1, connecting post 2, motion bar 4, damping spring 6, connecting plate 5 and baffle plate 8, described connection post 2 is vertically arranged in described underframe 1
Upper surface, described connection post 2 is internal is vertically provided with cavity volume 9, and described connection post 2 upper end is provided with the first through hole, institute
Stating the first through hole to be connected with described cavity volume 9, described motion bar 4 passes vertically through described first through hole, and described motion bar 4 is at least
Part is arranged in described cavity volume 9, the lower end of described motion bar 4 and the upper surface Joint of described connecting plate 5, described damping bullet
Spring 6 is arranged in described cavity volume 9, and the lower surface of one end of described damping spring 6 and described connecting plate 5 fixes, the other end
Being fixed on the bottom of described cavity volume 9, described motion bar 4 is positioned on the body of rod outside described cavity volume 9 and is socketed with described baffle plate 8, institute
State connection post 2 at least provided with two.
According to technique scheme, the depopulated helicopter undercarriage that the present invention provides is by arranging described motion bar 4 and institute
State damping spring 6 to match, thus when being landed by depopulated helicopter, the instantaneous impulse force of depopulated helicopter landing faced by ground is effectively
Sponge, then protect the body of depopulated helicopter, extend the service life of depopulated helicopter, and arrange on described connection post 2
Described baffle plate 8, impulse force when preventing depopulated helicopter from landing is too big, and described damping spring 6 cannot effectively absorb impulse force, then
Described baffle plate 8 is set to coordinate described damping spring 6 to protect described body together.Such as Fig. 2, the depopulated helicopter of the present invention rises
The frame that falls overcomes in prior art, unmanned helicopter landing gear and helicopter commonly used Hard link structure, helicopter landing gear
Easily loosening with not having buffer unit and being connected between body, when helicopter lands, temporary impact is asked the damage of body
Topic.
The present invention one preferred embodiment in, the upper surface of described connection post 2 is provided with cushion pad 7, and institute
Stating and be provided with the second through hole matched with described first through hole on cushion pad 7, described motion bar 4 sequentially passes through institute from top to bottom
Stating the second through hole and described first through hole enters in described cavity volume 9, wherein said cushion pad 7 matches with described baffle plate 8, nothing
During the landing of people's helicopter, if impulse force is excessive, described baffle plate 8 moves downward and strikes on described cushion pad 7, plays certain delaying
Punching and protective effect.
The present invention one preferred embodiment in, described motion bar 4 is cylinder, and described motion bar 4 is positioned at institute
State and be provided with external screw thread on the side face of the body of rod above baffle plate 8, during use, described motion bar 4 upper end is gone straight up to through nobody
The body of machine, is then effectively secured to described motion bar 4 on described body with upper end nut, and screw-type connects more square
Just dismounting and change, and fixing more firm.
The present invention one preferred embodiment in, described depopulated helicopter undercarriage also includes and described external screw thread
The self-locking nut matched, described self-locking nut is arranged on described motion bar 4, and is positioned at above described baffle plate 8, described from
Self can be locked on described motion bar 4 by split nut, relatively common screw thread, described self-locking nut make described body with
Fix the most firm between described motion bar 4.
The present invention one preferred embodiment in, the upper surface of described baffle plate 8 is provided with multiple projection, this
In bright, described body is to be matched with described self-locking nut by described baffle plate 8, and described body is clamped in centre, thus
Playing fixing effect, the most described projection effectively increases the frictional force between described baffle plate 8 and described body, so that
Obtain described body the most firm.
The present invention one preferred embodiment in, the lower surface of described underframe 1 is provided with rubber sheet gasket 3, unmanned
Helicopter is when landing, and described rubber sheet gasket 3 can play certain cushioning effect, and the described underframe of described protection 1 is not subject to
Abrasion, effectively increases the service life of described underframe 1.
The preferred embodiment of the present invention is described in detail above in association with accompanying drawing, but, the present invention is not limited to above-mentioned reality
Execute the detail in mode, in the technology concept of the present invention, technical scheme can be carried out multiple letter
Monotropic type, these simple variant belong to protection scope of the present invention.
It is further to note that each the concrete technical characteristic described in above-mentioned detailed description of the invention, at not lance
In the case of shield, can be combined by any suitable means, in order to avoid unnecessary repetition, the present invention to various can
The compound mode of energy illustrates the most separately.
Additionally, combination in any can also be carried out between the various different embodiment of the present invention, as long as it is without prejudice to this
The thought of invention, it should be considered as content disclosed in this invention equally.
Claims (6)
1. a depopulated helicopter undercarriage, it is characterised in that described depopulated helicopter undercarriage includes: underframe (1), connection post
(2), motion bar (4), damping spring (6), connecting plate (5) and baffle plate (8), described connection post (2) is vertically arranged in the described end
The upper surface of frame (1), described connection post (2) is internal is vertically provided with cavity volume (9), and described connection post (2) upper end is arranged
Having the first through hole, described first through hole to be connected with described cavity volume (9), described motion bar (4) passes vertically through described first through hole,
And described motion bar (4) is at least partially disposed in described cavity volume (9), the lower end of described motion bar (4) and described connecting plate (5)
Upper surface Joint, in described damping spring (6) is arranged on described cavity volume (9), and one end of described damping spring (6) and institute
The lower surface stating connecting plate (5) fixes, and the other end is fixed on the bottom of described cavity volume (9), and described motion bar (4) is positioned at described
Being socketed with described baffle plate (8) on cavity volume (9) body of rod outward, described connection post (2) is at least provided with two.
Depopulated helicopter undercarriage the most according to claim 1, it is characterised in that the upper surface of described connection post (2) sets
It is equipped with and on cushion pad (7), and described cushion pad (7), is provided with the second through hole matched with described first through hole.
Depopulated helicopter undercarriage the most according to claim 2, it is characterised in that described motion bar (4) is cylinder, institute
State and be provided with external screw thread on the side face of the body of rod that motion bar (4) is positioned at described baffle plate (8) top.
Depopulated helicopter undercarriage the most according to claim 3, it is characterised in that described depopulated helicopter undercarriage also wraps
Including the self-locking nut matched with described external screw thread, described self-locking nut is arranged on described motion bar (4), and is positioned at described stopping
Baffle plate (8) top.
Depopulated helicopter undercarriage the most according to claim 1, it is characterised in that the upper surface of described baffle plate (8) sets
It is equipped with multiple projection.
Depopulated helicopter undercarriage the most according to claim 1, it is characterised in that the lower surface of described underframe (1) is arranged
There is rubber sheet gasket (3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610596157.4A CN106143880A (en) | 2016-07-27 | 2016-07-27 | Depopulated helicopter undercarriage |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610596157.4A CN106143880A (en) | 2016-07-27 | 2016-07-27 | Depopulated helicopter undercarriage |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106143880A true CN106143880A (en) | 2016-11-23 |
Family
ID=58060439
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610596157.4A Pending CN106143880A (en) | 2016-07-27 | 2016-07-27 | Depopulated helicopter undercarriage |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106143880A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108163186A (en) * | 2018-01-16 | 2018-06-15 | 安徽翼讯飞行安全技术有限公司 | A kind of unmanned plane landing damping device |
| CN108784529A (en) * | 2018-05-25 | 2018-11-13 | 安徽风向标清洁设备有限公司 | Sweeper |
| CN112027066A (en) * | 2020-09-15 | 2020-12-04 | 惠州众合航空科技有限公司 | Stable unmanned aerial vehicle landing device |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB745915A (en) * | 1953-02-09 | 1956-03-07 | British Messier Ltd | Improvements in or relating to shock absorbers for aircraft |
| CN105292446A (en) * | 2015-11-16 | 2016-02-03 | 吉林大学 | Damping undercarriage of quadrotor |
| CN205076034U (en) * | 2015-10-16 | 2016-03-09 | 河南翱翔航空科技有限公司 | Unmanned aerial vehicle nose -gear |
| CN105416576A (en) * | 2015-11-25 | 2016-03-23 | 上海云犀智能系统有限公司 | Multi-stage buffering undercarriage of unmanned aerial vehicle |
| CN205113694U (en) * | 2015-11-21 | 2016-03-30 | 长沙学院 | Buffering foot rest of rotor craft |
| CN205345324U (en) * | 2015-11-30 | 2016-06-29 | 无锡觅睿恪科技有限公司 | Bottom protection frame is protected to unmanned aerial vehicle elasticity |
-
2016
- 2016-07-27 CN CN201610596157.4A patent/CN106143880A/en active Pending
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB745915A (en) * | 1953-02-09 | 1956-03-07 | British Messier Ltd | Improvements in or relating to shock absorbers for aircraft |
| CN205076034U (en) * | 2015-10-16 | 2016-03-09 | 河南翱翔航空科技有限公司 | Unmanned aerial vehicle nose -gear |
| CN105292446A (en) * | 2015-11-16 | 2016-02-03 | 吉林大学 | Damping undercarriage of quadrotor |
| CN205113694U (en) * | 2015-11-21 | 2016-03-30 | 长沙学院 | Buffering foot rest of rotor craft |
| CN105416576A (en) * | 2015-11-25 | 2016-03-23 | 上海云犀智能系统有限公司 | Multi-stage buffering undercarriage of unmanned aerial vehicle |
| CN205345324U (en) * | 2015-11-30 | 2016-06-29 | 无锡觅睿恪科技有限公司 | Bottom protection frame is protected to unmanned aerial vehicle elasticity |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108163186A (en) * | 2018-01-16 | 2018-06-15 | 安徽翼讯飞行安全技术有限公司 | A kind of unmanned plane landing damping device |
| CN108784529A (en) * | 2018-05-25 | 2018-11-13 | 安徽风向标清洁设备有限公司 | Sweeper |
| CN112027066A (en) * | 2020-09-15 | 2020-12-04 | 惠州众合航空科技有限公司 | Stable unmanned aerial vehicle landing device |
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| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20161123 |
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| RJ01 | Rejection of invention patent application after publication |