CN204822065U - Unmanned aerial vehicle's undercarriage - Google Patents
Unmanned aerial vehicle's undercarriage Download PDFInfo
- Publication number
- CN204822065U CN204822065U CN201520550185.3U CN201520550185U CN204822065U CN 204822065 U CN204822065 U CN 204822065U CN 201520550185 U CN201520550185 U CN 201520550185U CN 204822065 U CN204822065 U CN 204822065U
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- China
- Prior art keywords
- support rod
- spring
- front support
- fuselage
- fixed mount
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- 229910000831 Steel Inorganic materials 0.000 claims abstract description 38
- 239000010959 steel Substances 0.000 claims abstract description 38
- 238000009434 installation Methods 0.000 abstract description 5
- 230000035939 shock Effects 0.000 abstract description 3
- 230000008878 coupling Effects 0.000 abstract 2
- 238000010168 coupling process Methods 0.000 abstract 2
- 238000005859 coupling reaction Methods 0.000 abstract 2
- 230000000694 effects Effects 0.000 description 10
- 238000000034 method Methods 0.000 description 7
- 230000003139 buffering effect Effects 0.000 description 3
- 238000013016 damping Methods 0.000 description 3
- 230000000630 rising effect Effects 0.000 description 3
- 238000010521 absorption reaction Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
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Abstract
The utility model relates to an unmanned aerial vehicle's undercarriage, it includes the fuselage, fuselage head installation wing, the afterbody installation fin of fuselage, the balanced wing of top installation of afterbody, fuselage installation horizontal pole A and horizontal pole B, horizontal pole A's both ends hinge preceding bracing piece A and preceding bracing piece B respectively, horizontal pole B's both ends hinge back bracing piece A and back bracing piece B respectively, preceding bracing piece A and back bracing piece A all hinge connecting rod A, connecting rod A connects mount A, wheel A is connected to mount A's one end, the other end sets up fixed block A, fixed block A coupling spring A, preceding bracing piece B and back bracing piece B all hinge connecting rod B, connecting rod B connects mount B, wheel B is connected to mount B's one end, the other end sets up fixed block B, fixed block B coupling spring B, the steel loop is all connected to spring A and spring B's end, spacing wire rope A and spacing wire rope B are connected respectively to the steel loop, the utility model relates to a simply, shock -absorbing structure is simple, and light in weight is with low costs.
Description
Technical field
The utility model belongs to aircraft field, is specifically related to alighting gear, particularly a kind of alighting gear of unmanned plane.
Background technology
Robot airplane is called for short " unmanned plane ", is the not manned aircraft utilizing radio robot to handle with the process controller provided for oneself.Without driving compartment on machine, but the equipment such as autopilot, process controller is installed.On ground, naval vessels or machine tool command and control station personnel by equipment such as radars, it is followed the tracks of, locates, remote control, remote measurement and digital communication.The alighting gear of unmanned plane is a very important part, due to alighting gear not arranging shock absorption device, such unmanned plane shakes strongly in landing process, causes very large shock damage to aircraft, and this vibrations or an important sources of takeoff and landing noise.
Summary of the invention
The purpose of this utility model is to overcome the deficiencies in the prior art, and provides the alighting gear of the unmanned plane that a kind of simplicity of design, cost are low, quality is light, easy to use.
The purpose of this utility model is achieved in that a kind of alighting gear of unmanned plane, it comprises fuselage, described fuselage head both sides are provided with into the wing of symmetrical structure, the two sides of tail of described fuselage is provided with into the empennage of symmetrical structure, the top of described afterbody is provided with balance wing, the downside of described fuselage head is provided with cross bar A and cross bar B, the two ends of described cross bar A are hinged with front support rod A and front support rod B respectively, the two ends of described cross bar B are hinged with back support rod A and back support rod B respectively, described front support rod A and back support rod A is all hinged with pipe link A, described pipe link A is connected with fixed mount A, described pipe link A is interspersed in fixed mount A and two ends are hinged with front support rod A and back support rod A respectively, one end of described fixed mount A is connected with wheel A, the other end is provided with fixed block A, described fixed block A is connected with spring A, described front support rod B and back support rod B is all hinged with pipe link B, described pipe link B is connected with fixed mount B, described pipe link B is interspersed in fixed mount B and two ends are hinged with front support rod B and back support rod B respectively, one end of described fixed mount B is connected with wheel B, the other end is provided with fixed block B, described fixed block B is connected with spring B, described spring A and the end of spring B are all connected with steel loop, described steel loop is connected to spacing steel rope A and spacing steel rope B, described spacing steel rope A and spacing steel rope B is individually fixed in the two ends of cross bar A.
Described front support rod A and front support rod B is all perpendicular to fuselage.
Described back support rod A and the angle of front support rod A and back support rod B and front support rod B are 30 °.
Described fixed mount A is identical with fixed mount B structure.
Described spring A is identical with spring B structure.
The beneficial effects of the utility model: the utility model simplicity of design, before and after strut bar all with cross bar and pipe link hinged, such front and back strut bar is for being flexibly connected, angle can change, certain buffer action is played like this in the process of rising and falling, be provided with spring vibration damper in addition, steel rope can play spacing effect, spring plays the effect of buffering, whole Landing Gear Design is simple, and cost is low, and quality is light, very easy to use, the utility model has simplicity of design in a word, cost is low, quality is light, good damping effect, advantage easy to use.
Accompanying drawing explanation
Fig. 1 is the front elevation of the alighting gear of a kind of unmanned plane of the utility model.
Fig. 2 is the left view of the alighting gear of a kind of unmanned plane of the utility model.
Fig. 3 is the block diagram of the alighting gear of a kind of unmanned plane of the utility model.
In figure: 1, fuselage 2, wing 3, empennage 4, balance wing 5, cross bar A6, cross bar B 7, front support rod A8, front support rod B9, back support rod A10, back support rod B11, pipe link A12, fixed mount A13, wheel A14, fixed block A15, spring A16, pipe link B17, fixed mount B18, wheel B19, fixed block B20, spring B 21, steel loop 22, spacing steel rope A23, spacing steel rope B.
Detailed description of the invention
Below in conjunction with accompanying drawing, the utility model is described further.
Embodiment 1
As Figure 1-3, a kind of alighting gear of unmanned plane, it comprises fuselage 1, described fuselage 1 head both sides are provided with into the wing 2 of symmetrical structure, the two sides of tail of described fuselage 1 is provided with into the empennage 3 of symmetrical structure, the top of described fuselage 1 afterbody is provided with balance wing 4, the downside of described fuselage 1 head is provided with cross bar A5 and cross bar B 6, the two ends of described cross bar A5 are hinged with front support rod A7 and front support rod B8 respectively, the two ends of described cross bar B 6 are hinged with back support rod A9 and back support rod B10 respectively, described front support rod A7 and back support rod A9 is all hinged with pipe link A11, described pipe link A11 is connected with fixed mount A12, described pipe link A11 is interspersed in fixed mount A12 and two ends are hinged with front support rod A7 and back support rod A9 respectively, one end of described fixed mount A12 is connected with wheel A13, the other end is provided with fixed block A14, described fixed block A14 is connected with spring A15, described front support rod B8 and back support rod B10 is all hinged with pipe link B16, described pipe link B16 is connected with fixed mount B17, described pipe link B16 is interspersed in fixed mount B17 and two ends are hinged with front support rod B8 and back support rod B10 respectively, one end of described fixed mount B17 is connected with wheel B18, the other end is provided with fixed block B19, described fixed block B19 is connected with spring B 20, described spring A15 and the end of spring B 20 are all connected with steel loop 21, described steel loop 21 is connected to spacing steel rope A22 and spacing steel rope B23, described spacing steel rope A22 and spacing steel rope B23 is individually fixed in the two ends of cross bar A5.
The utility model simplicity of design, before and after strut bar all with cross bar and pipe link hinged, such front and back strut bar is for being flexibly connected, angle can change, certain buffer action is played like this in the process of rising and falling, front and back strut bar is connected with wheel, such unmanned plane can slide a segment distance, alleviate the vibration of unmanned plane, be provided with spring vibration damper in addition, steel rope can play spacing effect, spring plays the effect of buffering, whole Landing Gear Design is simple, cost is low, quality is light, very easy to use, the utility model has simplicity of design in a word, cost is low, quality is light, good damping effect, advantage easy to use.
Embodiment 2
As Figure 1-3, a kind of alighting gear of unmanned plane, it comprises fuselage 1, described fuselage 1 head both sides are provided with into the wing 2 of symmetrical structure, the two sides of tail of described fuselage 1 is provided with into the empennage 3 of symmetrical structure, the top of described fuselage 1 afterbody is provided with balance wing 4, the downside of described fuselage 1 head is provided with cross bar A5 and cross bar B 6, the two ends of described cross bar A5 are hinged with front support rod A7 and front support rod B8 respectively, the two ends of described cross bar B 6 are hinged with back support rod A9 and back support rod B10 respectively, described front support rod A7 and back support rod A9 is all hinged with pipe link A11, described pipe link A11 is connected with fixed mount A12, described pipe link A11 is interspersed in fixed mount A12 and two ends are hinged with front support rod A7 and back support rod A9 respectively, one end of described fixed mount A12 is connected with wheel A13, the other end is provided with fixed block A14, described fixed block A14 is connected with spring A15, described front support rod B8 and back support rod B10 is all hinged with pipe link B16, described pipe link B16 is connected with fixed mount B17, described pipe link B16 is interspersed in fixed mount B17 and two ends are hinged with front support rod B8 and back support rod B10 respectively, one end of described fixed mount B17 is connected with wheel B18, the other end is provided with fixed block B19, described fixed block B19 is connected with spring B 20, described spring A15 and the end of spring B 20 are all connected with steel loop 21, described steel loop 21 is connected to spacing steel rope A22 and spacing steel rope B23, described spacing steel rope A22 and spacing steel rope B23 is individually fixed in the two ends of cross bar A5.
Described front support rod A7 and front support rod B8 is all perpendicular to fuselage 1.
Described back support rod A9 and the angle of front support rod A7 and back support rod B10 and front support rod B8 are 30 °.
Described fixed mount A12 is identical with fixed mount B17 structure.
Described spring A15 is identical with spring B structure.
The utility model simplicity of design, before and after strut bar all with cross bar and pipe link hinged, such front and back strut bar is for being flexibly connected, angle can change, certain buffer action is played like this in the process of rising and falling, front and back strut bar is connected with wheel, such unmanned plane can slide a segment distance, alleviate the vibration of unmanned plane, the two ends of crossbearer A are provided with spacing steel rope in addition, so spacing effect is played to front and back strut bar, spacing steel rope is connected to two springs by steel loop, such spring and steel loop and spacing steel rope and steel loop all constitute triangular structure, not only Stability Analysis of Structures, and be provided with spring and serve cushioning effect, steel rope can play the effect of buffering by spring, spring A and spring B, structure is identical, easy for installation, fixed mount A is identical with fixed mount B structure, easy to process, whole Landing Gear Design is simple, cost is low, quality is light, very easy to use, the utility model has simplicity of design in a word, cost is low, quality is light, good damping effect, advantage easy to use.
Claims (5)
1. the alighting gear of a unmanned plane, it comprises fuselage, it is characterized in that: described fuselage head both sides are provided with into the wing of symmetrical structure, the two sides of tail of described fuselage is provided with into the empennage of symmetrical structure, the top of described afterbody is provided with balance wing, the downside of described fuselage head is provided with cross bar A and cross bar B, the two ends of described cross bar A are hinged with front support rod A and front support rod B respectively, the two ends of described cross bar B are hinged with back support rod A and back support rod B respectively, described front support rod A and back support rod A is all hinged with pipe link A, described pipe link A is connected with fixed mount A, described pipe link A is interspersed in fixed mount A and two ends are hinged with front support rod A and back support rod A respectively, one end of described fixed mount A is connected with wheel A, the other end is provided with fixed block A, described fixed block A is connected with spring A, described front support rod B and back support rod B is all hinged with pipe link B, described pipe link B is connected with fixed mount B, described pipe link B is interspersed in fixed mount B and two ends are hinged with front support rod B and back support rod B respectively, one end of described fixed mount B is connected with wheel B, the other end is provided with fixed block B, described fixed block B is connected with spring B, described spring A and the end of spring B are all connected with steel loop, described steel loop is connected to spacing steel rope A and spacing steel rope B, described spacing steel rope A and spacing steel rope B is individually fixed in the two ends of cross bar A.
2. the alighting gear of a kind of unmanned plane according to claim 1, is characterized in that: described front support rod A and front support rod B is all perpendicular to fuselage.
3. the alighting gear of a kind of unmanned plane according to claim 1, is characterized in that: described back support rod A and the angle of front support rod A and back support rod B and front support rod B are 30 °.
4. the alighting gear of a kind of unmanned plane according to claim 1, is characterized in that: described fixed mount A is identical with fixed mount B structure.
5. the alighting gear of a kind of unmanned plane according to claim 1, is characterized in that: described spring A is identical with spring B structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520550185.3U CN204822065U (en) | 2015-07-28 | 2015-07-28 | Unmanned aerial vehicle's undercarriage |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520550185.3U CN204822065U (en) | 2015-07-28 | 2015-07-28 | Unmanned aerial vehicle's undercarriage |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204822065U true CN204822065U (en) | 2015-12-02 |
Family
ID=54679691
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520550185.3U Expired - Fee Related CN204822065U (en) | 2015-07-28 | 2015-07-28 | Unmanned aerial vehicle's undercarriage |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204822065U (en) |
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105480410A (en) * | 2015-12-15 | 2016-04-13 | 西北工业大学 | Take-off and landing device for small-sized unmanned aerial vehicle |
| CN105775111A (en) * | 2016-05-13 | 2016-07-20 | 无锡商业职业技术学院 | Buffering structure of airplane wheel |
| CN107792351A (en) * | 2017-10-16 | 2018-03-13 | 肇庆高新区国专科技有限公司 | A kind of unmanned plane |
| CN109592024A (en) * | 2016-07-05 | 2019-04-09 | 金福珍 | A kind of Intelligent unattended machine |
| CN109747821A (en) * | 2017-11-02 | 2019-05-14 | 智飞智能装备科技东台有限公司 | A kind of unmanned plane for plant protection sprinkling |
| CN111976969A (en) * | 2020-09-22 | 2020-11-24 | 复旦大学 | Undercarriage damping device of fixed wing gasoline power unmanned aerial vehicle |
| WO2021189165A1 (en) * | 2020-03-22 | 2021-09-30 | 南京唐壹信息科技有限公司 | Unmanned aerial vehicle provided with thrower |
| CN113928545A (en) * | 2021-11-23 | 2022-01-14 | 复旦大学 | Many rotor unmanned aerial vehicle with shock attenuation undercarriage structure |
-
2015
- 2015-07-28 CN CN201520550185.3U patent/CN204822065U/en not_active Expired - Fee Related
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105480410A (en) * | 2015-12-15 | 2016-04-13 | 西北工业大学 | Take-off and landing device for small-sized unmanned aerial vehicle |
| CN105480410B (en) * | 2015-12-15 | 2017-05-24 | 西北工业大学 | Take-off and landing device for small-sized unmanned aerial vehicle |
| CN105775111A (en) * | 2016-05-13 | 2016-07-20 | 无锡商业职业技术学院 | Buffering structure of airplane wheel |
| CN109592024A (en) * | 2016-07-05 | 2019-04-09 | 金福珍 | A kind of Intelligent unattended machine |
| CN107792351A (en) * | 2017-10-16 | 2018-03-13 | 肇庆高新区国专科技有限公司 | A kind of unmanned plane |
| CN109747821A (en) * | 2017-11-02 | 2019-05-14 | 智飞智能装备科技东台有限公司 | A kind of unmanned plane for plant protection sprinkling |
| WO2021189165A1 (en) * | 2020-03-22 | 2021-09-30 | 南京唐壹信息科技有限公司 | Unmanned aerial vehicle provided with thrower |
| CN111976969A (en) * | 2020-09-22 | 2020-11-24 | 复旦大学 | Undercarriage damping device of fixed wing gasoline power unmanned aerial vehicle |
| CN113928545A (en) * | 2021-11-23 | 2022-01-14 | 复旦大学 | Many rotor unmanned aerial vehicle with shock attenuation undercarriage structure |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20151202 |