CN202783777U - Unmanned aerial vehicle undercarriage - Google Patents
Unmanned aerial vehicle undercarriage Download PDFInfo
- Publication number
- CN202783777U CN202783777U CN 201220427044 CN201220427044U CN202783777U CN 202783777 U CN202783777 U CN 202783777U CN 201220427044 CN201220427044 CN 201220427044 CN 201220427044 U CN201220427044 U CN 201220427044U CN 202783777 U CN202783777 U CN 202783777U
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- CN
- China
- Prior art keywords
- damper
- unmanned plane
- alighting gear
- unmanned aerial
- dampers
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- 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.)
- Expired - Lifetime
Links
- 238000013016 damping Methods 0.000 claims description 13
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 4
- 229910052782 aluminium Inorganic materials 0.000 claims description 4
- 239000000956 alloy Substances 0.000 claims description 3
- 229910045601 alloy Inorganic materials 0.000 claims description 3
- 230000000694 effects Effects 0.000 abstract description 3
- 238000000034 method Methods 0.000 description 8
- 230000006378 damage Effects 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- 229910000831 Steel Inorganic materials 0.000 description 1
- 238000010521 absorption reaction Methods 0.000 description 1
- 239000004411 aluminium Substances 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 230000009514 concussion Effects 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 230000002950 deficient Effects 0.000 description 1
- 238000012827 research and development Methods 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
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- Vibration Dampers (AREA)
Abstract
The utility model relates to an unmanned aerial vehicle undercarriage, which comprises wheels, slide pinch bars, diagonal draw bars and dampers that are all symmetrically arranged along the axis of a vehicle body, as well as a front cross bar and a rear cross bar that are both mounted at the bottom of the vehicle body, wherein the top ends of piston rods of the dampers are connected with the end parts of the rear cross bar, and the bottom ends of the dampers are rotationally connected with the wheels; the top ends of the slide pinch bars are rotationally connected with the front cross bar, and the bottom ends thereof are connected with the bottom ends of the dampers; and the top ends of the diagonal draw bars are connected with the middle part of the rear cross bar, and the bottom ends thereof are connected with the bottom ends of the dampers. The unmanned aerial vehicle undercarriage has the advantages light weight, excellent vibration reduction effect, convenience in mounting, adaptability to unmanned aerial vehicles with different weights through adjustment, attractive and elegant appearance, reasonable stress, high reliability, and capability of preventing the unmanned aerial vehicle from off-tracking.
Description
Technical field
The utility model relates to the unmanned plane technical field, particularly relates to a kind of unmanned plane alighting gear.
Background technology
SUAV (small unmanned aerial vehicle) is the general flying method that adopts downhill race in the landing process, in the process of rising and falling, the unmanned plane alighting gear is the important devices in the takeoff and landing process, to its weight, buffer capacity, mounting means and reliability have strict technical requirements, otherwise can have a negative impact to whole landing process, even cause the damage of unmanned plane.
Above-mentioned unmanned plane alighting gear, though the user can be provided a kind of unmanned plane alighting gear, when using, reality finds also to have some shortcomings in its structure, thereby fail to reach best result of use, its shortcoming can be summarized as follows:
Present stage, common unmanned plane alighting gear was generally steel wire or carbon plate and/or aluminium sheet, was made by Laos's bending process, was fixed on the fuselage with rubber band or screw, although structure is simple, poor-performing causes the alighting gear distortion, sideslip, the situations such as fracture easily; Because alighting gear does not have good shock absorption device, in comparatively rough landing process, often cause the fuselage damage, alighting gear is difficult to the phenomenons such as reparation; The outward appearance of alighting gear is simple and crude coarse, affects the unmanned plane overall appearance.
This shows that above-mentioned existing unmanned plane alighting gear obviously still has inconvenience and defective, and demands urgently further being improved in structure, method and use.How to found a kind of new unmanned plane alighting gear, real one of the current important research and development problem that belongs to.
The utility model content
The technical problems to be solved in the utility model provides a kind of unmanned plane alighting gear, it is lightweight that it is had, good damping effect, be convenient to install, can be fit to by adjustment the unmanned plane of different take-off weights, and good looking appearance be generous, reasonable stress, have very high reliability, make unmanned plane deviation phenomenon can not occur, thereby overcome that existing unmanned plane alighting gear outward appearance is coarse and crude, poor-performing, easily cause the deficiency of fuselage damage.
For solving the problems of the technologies described above, a kind of unmanned plane alighting gear of the utility model, comprise along the symmetrically arranged wheel of fuselage axis, skid bar, digonal link, damper and the front rail and the rear transverse rod that are installed in fuselage bottom, wherein: the piston rod top of damper is connected with the rear transverse rod end, and damper bottom and wheel are rotatably connected; Skid masthead end and front rail are rotatably connected, and the bottom is connected with the bottom of damper; The digonal link top is connected with the rear transverse rod middle part, and the bottom is connected with the bottom of damper.
Further improve as the utility model, described digonal link, skid bar and air-pressure damping device are the thin wall alloy aluminum pipe.
Damping spring also is installed on the piston rod of described damper.
Described skid masthead end is rotatably connected by bulb bearing and front rail.
The bottom of described damper is equipped with oscillating bearing, and is connected with skid bar, digonal link by this oscillating bearing.
Described damper is hydraulic damper or air-pressure damping device.
Piston rod top and the rear transverse rod of described damper are rotatably connected, and described digonal link top and rear transverse rod are bolted.
The utility model compared with prior art has the following advantages:
1. this unmanned plane undercarriage cushioning is effective, lightweight, and good looking appearance is convenient to dismounting;
2. the alighting gear assembling and positioning is good, and unmanned plane landing direction is parallel with fuselage, the phenomenon of sideslip can not occur;
3. each parts of alighting gear are convenient to member replacing fully by machinework production;
4. alighting gear can adapt to by the model that changes the damper upper spring unmanned plane of Different Weight.
Description of drawings
Above-mentioned only is the general introduction of technical solutions of the utility model, and for can clearer understanding the utility model, the utility model is described in further detail below in conjunction with accompanying drawing and the specific embodiment.
Fig. 1 is the right elevation of the utility model unmanned plane alighting gear.
Fig. 2 is the front view of the utility model unmanned plane alighting gear.
The specific embodiment
See also Fig. 1, shown in Figure 2, a kind of unmanned plane alighting gear of the utility model comprises wheel 1, skid bar 2, digonal link 3, damper 4, front rail 5 and rear transverse rod 6.
Wherein, wheel 1, skid bar 2, digonal link 3 and damper 4 are symmetricly set on fuselage bottom 9 left and right sides along the fuselage axis, and front rail 5 and rear transverse rod 6 are installed in respectively the front and back side of unmanned aerial vehicle body bottom 9.
The piston rod top of damper 4 is connected with the end of rear transverse rod 6, and damper 4 bottoms and wheel 1 are connected by attaching partss such as wheel shafts.Skid bar 2 tops and front rail 5 are rotatably connected, and the bottom is connected with the bottom of damper 4.Digonal link 3 tops are connected with the middle part of rear transverse rod 6, and the bottom is connected with the bottom of damper 4.
Better, digonal link 3, skid bar 2 and air-pressure damping device 4 all can adopt the thin wall alloy aluminum pipe to make, with expendable weight.Skid bar 2 tops can be connected with front rail 5 by bulb bearing 21.
Damper 4 can adopt hydraulic damper or air-pressure damping device, and at the piston rod of damper damping spring 41 is installed.The bottom of damper 4 is equipped with oscillating bearing 42, and is connected with skid bar 2, digonal link 3 by this oscillating bearing 42, certain deflection is arranged after making alighting gear stressed, plays the effect that shock-absorbing releases energy.In addition, also can will be designed to be rotatably connected between the piston rod of damper 4 and the rear transverse rod 6, to be designed to removably connecting by parts such as bolts between digonal link 3 and the rear transverse rod 6, during dismounting, the bolt of digonal link 3 is unclamped, just alighting gear upwards can be folded to the fuselage both sides, be convenient to unmanned plane vanning transportation.
The utility model provides a kind of unmanned plane with air-pressure damping damping alighting gear, is connected on the fuselage by the front and back cross bar, forms general frame by digonal link, air-pressure damping device and skid bar.Damper is main energy-absorbing device, when unmanned plane takes off and land, aircraft be subject to backward and the impulse force that makes progress, and be delivered on damper and the relief spring, by the deflection of spring absorbed energy, reduce concussion with damper.In addition, also can by selecting different elastomeric springs, adapt to the unmanned plane of different take-off weights.
The above; it only is preferred embodiment of the present utility model; be not that the utility model is done any pro forma restriction, those skilled in the art utilize the technology contents of above-mentioned announcement to make a little simple modification, equivalent variations or modification, all drop in the protection domain of the present utility model.
Claims (7)
1. unmanned plane alighting gear is characterized in that comprising along the symmetrically arranged wheel of fuselage axis, skid bar, digonal link, damper and the front rail and the rear transverse rod that are installed in fuselage bottom, wherein:
The piston rod top of damper is connected with the rear transverse rod end, and damper bottom and wheel are rotatably connected;
Skid masthead end and front rail are rotatably connected, and the bottom is connected with the bottom of damper;
The digonal link top is connected with the rear transverse rod middle part, and the bottom is connected with the bottom of damper.
2. unmanned plane alighting gear according to claim 1, it is characterized in that: described digonal link, skid bar and air-pressure damping device are the thin wall alloy aluminum pipe.
3. unmanned plane alighting gear according to claim 1 is characterized in that: damping spring also is installed on the piston rod of described damper.
4. unmanned plane alighting gear according to claim 1, it is characterized in that: described skid masthead end is rotatably connected by bulb bearing and front rail.
5. unmanned plane alighting gear according to claim 1, it is characterized in that: the bottom of described damper is equipped with oscillating bearing, and is connected with skid bar, digonal link by this oscillating bearing.
6. unmanned plane alighting gear according to claim 1, it is characterized in that: described damper is hydraulic damper or air-pressure damping device.
7. unmanned plane alighting gear according to claim 1, it is characterized in that: piston rod top and the rear transverse rod of described damper are rotatably connected, and described digonal link top and rear transverse rod are bolted.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220427044 CN202783777U (en) | 2012-08-24 | 2012-08-24 | Unmanned aerial vehicle undercarriage |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220427044 CN202783777U (en) | 2012-08-24 | 2012-08-24 | Unmanned aerial vehicle undercarriage |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202783777U true CN202783777U (en) | 2013-03-13 |
Family
ID=47811092
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201220427044 Expired - Lifetime CN202783777U (en) | 2012-08-24 | 2012-08-24 | Unmanned aerial vehicle undercarriage |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202783777U (en) |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105644774A (en) * | 2016-02-02 | 2016-06-08 | 吴燕 | Multi-rotor flight vehicle undercarriage based on Stewart six-degree-of-freedom parallel mechanism |
| CN105775111A (en) * | 2016-05-13 | 2016-07-20 | 无锡商业职业技术学院 | Buffering structure of airplane wheel |
| CN105980250A (en) * | 2015-05-14 | 2016-09-28 | 深圳市大疆创新科技有限公司 | Landing gear and unmanned aerial vehicle using the landing gear |
| CN106241013A (en) * | 2016-08-31 | 2016-12-21 | 无锡优萌模塑制造有限公司 | A kind of plastic chain storage bin with shock-absorbing function |
| CN106477031A (en) * | 2016-11-30 | 2017-03-08 | 江西洪都航空工业集团有限责任公司 | A kind of SUAV landing buffer system |
| CN108036007A (en) * | 2017-11-30 | 2018-05-15 | 江西洪都航空工业集团有限责任公司 | A kind of damping device |
| CN106395147B (en) * | 2016-08-31 | 2018-09-04 | 无锡优萌模塑制造有限公司 | A kind of plastic wire spool placing box with shock-absorbing function |
| CN110758723A (en) * | 2019-12-06 | 2020-02-07 | 湖南浩天翼航空技术有限公司 | Unmanned aerial vehicle convenient to receive and release undercarriage |
| CN112224389A (en) * | 2020-10-09 | 2021-01-15 | 南京航空航天大学 | A retractable main landing gear that can adapt to different specifications and layout requirements |
-
2012
- 2012-08-24 CN CN 201220427044 patent/CN202783777U/en not_active Expired - Lifetime
Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105980250A (en) * | 2015-05-14 | 2016-09-28 | 深圳市大疆创新科技有限公司 | Landing gear and unmanned aerial vehicle using the landing gear |
| WO2016179827A1 (en) * | 2015-05-14 | 2016-11-17 | 深圳市大疆创新科技有限公司 | Undercarriage and unmanned aerial vehicle using same |
| CN105980250B (en) * | 2015-05-14 | 2018-09-04 | 深圳市大疆创新科技有限公司 | Landing gear and unmanned aerial vehicle using the landing gear |
| CN105644774A (en) * | 2016-02-02 | 2016-06-08 | 吴燕 | Multi-rotor flight vehicle undercarriage based on Stewart six-degree-of-freedom parallel mechanism |
| CN105644774B (en) * | 2016-02-02 | 2017-10-20 | 绍兴俪泰纺织科技有限公司 | A kind of multi-rotor aerocraft undercarriage based on Stewart six-degree-of-freedom parallel connection mechanisms |
| CN105775111A (en) * | 2016-05-13 | 2016-07-20 | 无锡商业职业技术学院 | Buffering structure of airplane wheel |
| CN106241013A (en) * | 2016-08-31 | 2016-12-21 | 无锡优萌模塑制造有限公司 | A kind of plastic chain storage bin with shock-absorbing function |
| CN106395147B (en) * | 2016-08-31 | 2018-09-04 | 无锡优萌模塑制造有限公司 | A kind of plastic wire spool placing box with shock-absorbing function |
| CN106477031A (en) * | 2016-11-30 | 2017-03-08 | 江西洪都航空工业集团有限责任公司 | A kind of SUAV landing buffer system |
| CN108036007A (en) * | 2017-11-30 | 2018-05-15 | 江西洪都航空工业集团有限责任公司 | A kind of damping device |
| CN110758723A (en) * | 2019-12-06 | 2020-02-07 | 湖南浩天翼航空技术有限公司 | Unmanned aerial vehicle convenient to receive and release undercarriage |
| CN112224389A (en) * | 2020-10-09 | 2021-01-15 | 南京航空航天大学 | A retractable main landing gear that can adapt to different specifications and layout requirements |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| EE01 | Entry into force of recordation of patent licensing contract |
Assignee: BEIJING SHUWEIXIANTU HIGH-TECH CO.,LTD. Assignor: Dong Tao Contract record no.: 2015370000113 Denomination of utility model: Unmanned plane undercarriage control system Granted publication date: 20130313 License type: Exclusive License Record date: 20150707 |
|
| LICC | Enforcement, change and cancellation of record of contracts on the licence for exploitation of a patent or utility model | ||
| C41 | Transfer of patent application or patent right or utility model | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20151221 Address after: 100000, Fengtai District, Beijing, a Garden District No. 2, building 2, 239 Patentee after: BEIJING SHUWEIXIANTU HIGH-TECH CO.,LTD. Address before: 102300 Beijing city Mentougou District No. 279 West store shop Patentee before: Dong Tao |
|
| CP01 | Change in the name or title of a patent holder |
Address after: 100000, Fengtai District, Beijing, a Garden District No. 2, building 2, 239 Patentee after: DIMENSION MAPPING HIGH TECH. CO.,LTD. Address before: 100000, Fengtai District, Beijing, a Garden District No. 2, building 2, 239 Patentee before: BEIJING SHUWEIXIANTU HIGH-TECH CO.,LTD. |
|
| CP01 | Change in the name or title of a patent holder | ||
| CP03 | Change of name, title or address |
Address after: 100067 room 13, 1301-1 room (Park), No. 18, District 18, district seventeen, South Fourth Ring Road, Fengtai District, Beijing Patentee after: AEROSPACE SHUWEI HIGH TECH. CO.,LTD. Address before: 100000, Fengtai District, Beijing, a Garden District No. 2, building 2, 239 Patentee before: DIMENSION MAPPING HIGH TECH. CO.,LTD. |
|
| CP03 | Change of name, title or address | ||
| CX01 | Expiry of patent term |
Granted publication date: 20130313 |
|
| CX01 | Expiry of patent term |