CN107524750A - Unmanned plane landing damping device - Google Patents
Unmanned plane landing damping device Download PDFInfo
- Publication number
- CN107524750A CN107524750A CN201710979234.9A CN201710979234A CN107524750A CN 107524750 A CN107524750 A CN 107524750A CN 201710979234 A CN201710979234 A CN 201710979234A CN 107524750 A CN107524750 A CN 107524750A
- Authority
- CN
- China
- Prior art keywords
- unmanned plane
- spring
- piston
- siphunculus
- sleeve
- 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.)
- Withdrawn
Links
- 238000013016 damping Methods 0.000 title claims abstract description 15
- 230000000694 effects Effects 0.000 claims abstract description 15
- 238000003780 insertion Methods 0.000 claims description 2
- 230000037431 insertion Effects 0.000 claims description 2
- 239000002775 capsule Substances 0.000 claims 1
- 239000012530 fluid Substances 0.000 abstract description 6
- 230000003139 buffering effect Effects 0.000 abstract description 3
- 238000005273 aeration Methods 0.000 abstract description 2
- 238000006243 chemical reaction Methods 0.000 abstract description 2
- 238000005516 engineering process Methods 0.000 description 3
- 238000000034 method Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- TVEXGJYMHHTVKP-UHFFFAOYSA-N 6-oxabicyclo[3.2.1]oct-3-en-7-one Chemical compound C1C2C(=O)OC1C=CC2 TVEXGJYMHHTVKP-UHFFFAOYSA-N 0.000 description 1
- 208000035473 Communicable disease Diseases 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 208000015181 infectious disease Diseases 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000013507 mapping Methods 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 210000003739 neck Anatomy 0.000 description 1
- 238000002360 preparation method Methods 0.000 description 1
Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
- B64D45/04—Landing aids; Safety measures to prevent collision with earth's surface
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D45/00—Aircraft indicators or protectors not otherwise provided for
- B64D45/04—Landing aids; Safety measures to prevent collision with earth's surface
- B64D45/06—Landing aids; Safety measures to prevent collision with earth's surface mechanical
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F13/00—Units comprising springs of the non-fluid type as well as vibration-dampers, shock-absorbers, or fluid springs
- F16F13/002—Units comprising springs of the non-fluid type as well as vibration-dampers, shock-absorbers, or fluid springs comprising at least one fluid spring
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F13/00—Units comprising springs of the non-fluid type as well as vibration-dampers, shock-absorbers, or fluid springs
- F16F13/005—Units comprising springs of the non-fluid type as well as vibration-dampers, shock-absorbers, or fluid springs comprising both a wound spring and a damper, e.g. a friction damper
- F16F13/007—Units comprising springs of the non-fluid type as well as vibration-dampers, shock-absorbers, or fluid springs comprising both a wound spring and a damper, e.g. a friction damper the damper being a fluid damper
Landscapes
- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Vibration Prevention Devices (AREA)
Abstract
The invention discloses unmanned plane landing damping device, including rotating disk, the rotating disk upper surface is connected with unmanned plane body centrally through second spring, the present invention is by adding rotating disk, the structure such as inserted link and first piston, in sleeve, the lower section of first piston is equipped with fluid, when unmanned plane body from airborne on ground when, 6th spring is stretched, convert kinetic energy into the interior energy of the 6th spring, play damping effect, and inserted link relative sleeve moves down, fluid is poured into cylinder by the first siphunculus, move down second piston, make airbag aeration, further function as the effect of buffering, the connection of unmanned plane body and multiple first springs, the connection of first pipeline and the 3rd spring, also kinetic energy conversion when unmanned plane body is landed, unmanned plane body is protected to be not damaged by, improve the service life of unmanned plane body.
Description
Technical field
The present invention relates to unmanned air vehicle technique field, specially unmanned plane landing damping device.
Background technology
Compared with manned aircraft, unmanned plane is often more suitable for the task of those too " slow-witted, dirty or dangerous ".Nobody
Machine presses application field, can be divided into it is military with it is civilian.Military aspect, unmanned plane are divided into reconnaissance plane and target drone.Civilian aspect, unmanned plane
It is that unmanned plane has really just needed with reference to sector application；At present take photo by plane, agricultural, plant protection, miniature self-timer, express transportation, disaster are rescued
Help, observe the necks such as wild animal, monitoring infectious disease, mapping, news report, electric inspection process, the disaster relief, movies-making, manufacture romance
The application in domain, has greatly expanded the purposes of unmanned plane in itself, and developed country also in actively extension sector application and develops nobody
Machine technology.Unmanned plane is fallen after aerial mission terminates from the air, affected by gravity due to highly higher, is easily broken
Unmanned plane, therefore, proposing unmanned plane landing damping device.
The content of the invention
It is an object of the invention to provide unmanned plane landing damping device, asked with solve to propose in above-mentioned background technology
Topic.
Unmanned plane landing damping device, including rotating disk, the rotating disk upper surface are connected with nobody centrally through second spring
Machine body, the lower end activity of the unmanned plane body are plugged in the first pipeline, and the lower end activity of the first pipeline is plugged on second
In pipeline, the second pipe is hollow structure, and the lower end of second pipe is fixedly connected with the upper surface of rotating disk, first pipe
One end that road is located in second pipe is connected on the bottom wall of inner cavity of second pipe by the 3rd spring, the unmanned plane body
Side wall lower ends are connected on the madial wall of the first pipeline by some first springs, and the lower surface of the rotating disk is centrally through pole
Be fixedly connected with cylinder, the inner bottom wall of the cylinder is connected with second piston by the 5th spring, second piston and cylinder it is interior
Wall is slidably connected, one end of two the first siphunculus of top plate through connection of the cylinder, the other end through connection of the first siphunculus
The side wall of sleeve, one end of the be hinged inserted link in lower surface both sides of the rotating disk, the other end activity of inserted link are plugged in sleeve
And the side of first piston is fixedly connected with, the opposite side of first piston is by the inner bottom wall of the 4th spring branch sleeve, and first
It is located at the lower section of first piston at the through connection of siphunculus and sleeve, is connected between two inserted links by the 6th spring, the
The inwall of one piston and sleeve is slidably connected, and the exterior bottom wall of the sleeve is connected with air bag, the siphunculus of air bag through connection second
One end, the other end of the second siphunculus and the bottom wall through connection of cylinder.
Preferably, the first spring more than three, and be distributed on second spring equidistant ring.
Preferably, first siphunculus and the second siphunculus are rubber hose.
Preferably, two sleeves are symmetrical arranged on cylinder.
Compared with prior art, the beneficial effects of the invention are as follows：The present invention is by adding rotating disk, inserted link and first piston etc.
Structure, in sleeve, the lower section of first piston is equipped with fluid, when unmanned plane body from airborne on ground when, sleeve with ground
Face is hit, and the rotation that two inserted links are located remotely from each other, the 6th spring is stretched, converts kinetic energy into the interior energy of the 6th spring, play
Damping effect, and inserted link relative sleeve moves down, fluid is poured into cylinder by the first siphunculus, makes second piston to moving down
It is dynamic, make airbag aeration, further function as the effect of buffering, the connection of unmanned plane body and multiple first springs, the first pipeline with
The connection of 3rd spring, kinetic energy conversion when also unmanned plane body is landed, protects unmanned plane body to be not damaged by, improves
The service life of unmanned plane body.
Brief description of the drawings
Fig. 1 is schematic structural view of the invention.
In figure：Unmanned plane body 1, the first spring 2, the first pipeline 3, second pipe 4, second spring 5, the 3rd spring 6, turn
Disk 7, inserted link 8, first piston 9, sleeve 10, the 4th spring 11, air bag 12, the first siphunculus 13, the second siphunculus 14, cylinder 15,
Two pistons 16, the 5th spring 17, the 6th spring 18.
Embodiment
Below in conjunction with the accompanying drawing in the embodiment of the present invention, the technical scheme in the embodiment of the present invention is carried out clear, complete
Site preparation describes, it is clear that described embodiment is only part of the embodiment of the present invention, rather than whole embodiments.One end be located at the second chute
Embodiment in the present invention, those of ordinary skill in the art are obtained every other under the premise of creative work is not made
Embodiment, belong to the scope of protection of the invention.
Referring to Fig. 1, the present invention provides a kind of technical scheme：
Unmanned plane landing damping device, including rotating disk 7, the upper surface of rotating disk 7 are connected with unmanned plane centrally through second spring 5
Body 1, the lower end activity of unmanned plane body 1 are plugged in the first pipeline 3, and the lower end activity of the first pipeline 3 is plugged on the second pipe
In road 4, second pipe 4 is hollow structure, and the lower end of second pipe 4 is fixedly connected with the upper surface of rotating disk 7, the first 3, pipeline
It is connected in one end in second pipe 4 by the 3rd spring 6 on the bottom wall of inner cavity of second pipe 4, the side wall of unmanned plane body 1
Lower end is connected to by some first springs 2 on the madial wall of first pipeline 3, the more than three of the first spring 2, and on the second bullet
The equidistant ring of spring 5 is distributed, and the lower surface of rotating disk 7 is fixedly connected with cylinder 15 centrally through pole, and the inner bottom wall of cylinder 15 passes through
5th spring 17 is connected with second piston 16, and second piston 16 and the inwall of cylinder 15 are slidably connected, the top plate insertion of cylinder 15
Connect one end of two the first siphunculus 13, the side wall of the other end through connection sleeve 10 of the first siphunculus 13, the lower surface of rotating disk 7
One end of the be hinged inserted link 8 in both sides, the other end activity of inserted link 8 are plugged in sleeve 10 and are fixedly connected with first piston 9
Side, the opposite side of first piston 9 are passed through by the inner bottom wall of the branch sleeve 10 of the 4th spring 11, the first siphunculus 13 with sleeve 10
Logical junction is located at the lower section of first piston 9, is connected between two inserted links 8 by the 6th spring 18, first piston 9 and sleeve 10
Inwall be slidably connected, two sleeves 10 are symmetrical arranged on cylinder 15, and the exterior bottom wall of sleeve 10 is connected with air bag 12, air bag 12
One end of the second siphunculus of through connection 14, the other end of the second siphunculus 14 and the bottom wall through connection of cylinder 15, the first siphunculus 13
It is rubber hose with the second siphunculus 14.
Operation principle：In sleeve 10, the lower section of first piston 9 is equipped with fluid, when unmanned plane body 1 exists from airborne
During ground, sleeve 10 makes impact with the ground, and the rotation that two inserted links 8 are located remotely from each other, the 6th spring 18 is stretched, and converts kinetic energy into
The interior energy of 6th spring 18, damping effect is played, and the relative sleeve 10 of inserted link 8 moves down, and fluid passes through the first siphunculus 13
Pour into cylinder 15, move down second piston 16, inflate air bag 12, further function as the effect of buffering, unmanned plane sheet
The connection of body 1 and multiple first springs 2, the connection of the first pipeline 3 and the 3rd spring 6 are dynamic when also unmanned plane body 1 is landed
It can convert, protect unmanned plane body 1 to be not damaged by, improve the service life of unmanned plane body 1.
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 changes, modification can be carried out to these embodiments, replace 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 (4)
- The damping device 1. unmanned plane lands, including rotating disk (7), it is characterised in that：Rotating disk (7) upper surface is centrally through second Spring (5) is connected with unmanned plane body (1), and the lower end activity of the unmanned plane body (1) is plugged in the first pipeline (3), the The lower end activity of one pipeline (3) is plugged in second pipe (4), and the second pipe (4) is hollow structure, second pipe (4) Lower end be fixedly connected with the upper surface of rotating disk (7), first pipeline (3) is located at one end in second pipe (4) by Three springs (6) are connected on the bottom wall of inner cavity of second pipe (4), and the side wall lower ends of the unmanned plane body (1) pass through some One spring (2) is connected on the madial wall of the first pipeline (3), and the lower surface of the rotating disk (7) is fixedly connected centrally through pole There is cylinder (15), the inner bottom wall of the cylinder (15) is connected with second piston (16), second piston by the 5th spring (17) (16) inwall with cylinder (15) is slidably connected, and the one of two the first siphunculus (13) of top plate through connection of the cylinder (15) End, the side wall of the other end through connection sleeve (10) of the first siphunculus (13), the lower surface both sides of the rotating disk (7) are be hinged to insert One end of bar (8), the other end activity of inserted link (8) are plugged in sleeve (10) and are fixedly connected with the side of first piston (9), The opposite side of first piston (9) passes through the inner bottom wall of the 4th spring (11) branch sleeve (10), the first siphunculus (13) and sleeve (10) it is located at the lower section of first piston (9) at through connection, is connected between two inserted links (8) by the 6th spring (18) Connect, the inwall of first piston (9) and sleeve (10) is slidably connected, and the exterior bottom wall of the sleeve (10) is connected with air bag (12), gas One end of capsule (12) the second siphunculus of through connection (14), the other end of the second siphunculus (14) connect with the bottom wall insertion of cylinder (15) Connect.
- The damping device 2. unmanned plane according to claim 1 lands, it is characterised in that：First spring (2) is more than three It is individual, and be distributed on second spring (5) equidistant ring.
- The damping device 3. unmanned plane according to claim 1 lands, it is characterised in that：First siphunculus (13) and second Siphunculus (14) is rubber hose.
- The damping device 4. unmanned plane according to claim 1 lands, it is characterised in that：Two sleeves (10) are on gas Cylinder (15) is symmetrical arranged.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710979234.9A CN107524750A (en) | 2017-10-19 | 2017-10-19 | Unmanned plane landing damping device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710979234.9A CN107524750A (en) | 2017-10-19 | 2017-10-19 | Unmanned plane landing damping device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107524750A true CN107524750A (en) | 2017-12-29 |
Family
ID=60685450
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710979234.9A Withdrawn CN107524750A (en) | 2017-10-19 | 2017-10-19 | Unmanned plane landing damping device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107524750A (en) |
Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108216663A (en) * | 2018-01-22 | 2018-06-29 | 深圳达芬奇创新科技有限公司 | A kind of Master Control Center device |
| CN108248878A (en) * | 2018-01-22 | 2018-07-06 | 深圳达芬奇创新科技有限公司 | A kind of unmanned plane Master Control Center device mechanically automatically controlled |
| CN108489458A (en) * | 2018-03-09 | 2018-09-04 | 深圳市律远汇智科技有限公司 | A kind of vehicle-mounted three-dimensional laser detection device that cruising ability is strong |
| CN109051257A (en) * | 2018-10-23 | 2018-12-21 | 郑州莱兹电子科技有限公司 | A kind of electronic product transfer transport case |
| CN109573049A (en) * | 2019-01-22 | 2019-04-05 | 马骏 | A kind of stable type unmanned flight's equipment with pooling feature for logistics |
| CN109626313A (en) * | 2019-01-14 | 2019-04-16 | 墨宝股份有限公司 | A kind of unmanned fuel charger with defencive function |
| CN109941427A (en) * | 2019-03-06 | 2019-06-28 | 深圳市律远汇智科技有限公司 | A kind of unmanned plane convenient for safe landing with pooling feature |
| CN110140532A (en) * | 2019-05-23 | 2019-08-20 | 刘泽锋 | A kind of soybean dries equipment |
| CN110946400A (en) * | 2019-11-22 | 2020-04-03 | 湖北三行科技股份有限公司 | Enamel cabinet convenient to dismantle |
| CN113306733A (en) * | 2021-07-29 | 2021-08-27 | 深圳市青之鸟科技有限公司 | Unmanned aerial vehicle with protection architecture |
-
2017
- 2017-10-19 CN CN201710979234.9A patent/CN107524750A/en not_active Withdrawn
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108248878B (en) * | 2018-01-22 | 2021-08-27 | 深圳达芬奇创新科技有限公司 | Mechanical automatic control unmanned aerial vehicle main control center device |
| CN108248878A (en) * | 2018-01-22 | 2018-07-06 | 深圳达芬奇创新科技有限公司 | A kind of unmanned plane Master Control Center device mechanically automatically controlled |
| CN108216663A (en) * | 2018-01-22 | 2018-06-29 | 深圳达芬奇创新科技有限公司 | A kind of Master Control Center device |
| CN108216663B (en) * | 2018-01-22 | 2021-12-03 | 深圳达芬奇创新科技有限公司 | Master control center device |
| CN108489458A (en) * | 2018-03-09 | 2018-09-04 | 深圳市律远汇智科技有限公司 | A kind of vehicle-mounted three-dimensional laser detection device that cruising ability is strong |
| CN109051257A (en) * | 2018-10-23 | 2018-12-21 | 郑州莱兹电子科技有限公司 | A kind of electronic product transfer transport case |
| CN109626313A (en) * | 2019-01-14 | 2019-04-16 | 墨宝股份有限公司 | A kind of unmanned fuel charger with defencive function |
| CN109573049A (en) * | 2019-01-22 | 2019-04-05 | 马骏 | A kind of stable type unmanned flight's equipment with pooling feature for logistics |
| CN109941427A (en) * | 2019-03-06 | 2019-06-28 | 深圳市律远汇智科技有限公司 | A kind of unmanned plane convenient for safe landing with pooling feature |
| CN110140532B (en) * | 2019-05-23 | 2020-12-08 | 安徽谷神种业有限公司 | Soybean sun-drying equipment |
| CN110140532A (en) * | 2019-05-23 | 2019-08-20 | 刘泽锋 | A kind of soybean dries equipment |
| CN110946400B (en) * | 2019-11-22 | 2021-08-03 | 湖北三行科技股份有限公司 | Enamel cabinet convenient to dismantle |
| CN110946400A (en) * | 2019-11-22 | 2020-04-03 | 湖北三行科技股份有限公司 | Enamel cabinet convenient to dismantle |
| CN113306733A (en) * | 2021-07-29 | 2021-08-27 | 深圳市青之鸟科技有限公司 | Unmanned aerial vehicle with protection architecture |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WW01 | Invention patent application withdrawn after publication |
Application publication date: 20171229 |
|
| WW01 | Invention patent application withdrawn after publication |