CN211893630U - Unmanned aerial vehicle frame base bradyseism device - Google Patents
Unmanned aerial vehicle frame base bradyseism device Download PDFInfo
- Publication number
- CN211893630U CN211893630U CN202020189196.4U CN202020189196U CN211893630U CN 211893630 U CN211893630 U CN 211893630U CN 202020189196 U CN202020189196 U CN 202020189196U CN 211893630 U CN211893630 U CN 211893630U
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- unmanned aerial
- aerial vehicle
- frame base
- vehicle frame
- undercarriage
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Abstract
The utility model discloses an unmanned aerial vehicle frame base bradyseism device, include the shell and connect the frame base on the shell, the frame base includes crossbeam, support and undercarriage, the crossbeam with the shell is connected, the crossbeam is connected to support one end, and the undercarriage is connected to the other end, a support is respectively connected at the both ends of crossbeam, the undercarriage is provided with disconnected point, the cross-section of disconnected point is the arc. Through the utility model discloses can improve the bradyseism ability of unmanned aerial vehicle frame base.
Description
Technical Field
The utility model relates to a technical field such as unmanned aerial vehicle technique, mechanical part, shock attenuation, concretely relates to unmanned aerial vehicle frame base bradyseism device.
Background
An unmanned aircraft, abbreviated as "drone", and abbreviated in english as "UAV", is an unmanned aircraft that is operated by a radio remote control device and a self-contained program control device, or is operated autonomously, either completely or intermittently, by an onboard computer.
Drones tend to be more suitable for tasks that are too "fool, dirty, or dangerous" than are manned aircraft. Unmanned aerial vehicles can be classified into military and civil applications according to the application field. For military use, unmanned aerial vehicles divide into reconnaissance aircraft and target drone. In the civil aspect, the unmanned aerial vehicle + the industry application is really just needed by the unmanned aerial vehicle; at present, the unmanned aerial vehicle is applied to the fields of aerial photography, agriculture, plant protection, miniature self-timer, express transportation, disaster relief, wild animal observation, infectious disease monitoring, surveying and mapping, news reporting, power inspection, disaster relief, film and television shooting, romantic manufacturing and the like, the application of the unmanned aerial vehicle is greatly expanded, and developed countries actively expand industrial application and develop unmanned aerial vehicle technology.
Unmanned aerial vehicle's control technology adopts automatic data adjustment or manual control more, and under the relevant technological rapid development of unmanned aerial vehicle, the kind of unmanned aerial vehicle system also increases gradually, the usage characteristics are distinct, and according to flight platform configuration classification, unmanned aerial vehicle can divide into fixed wing unmanned aerial vehicle, rotor unmanned aerial vehicle, unmanned airship, umbrella wing unmanned aerial vehicle, flapping wing unmanned aerial vehicle etc.. The rotor unmanned aerial vehicle is the most widely used one, but the shortcoming of rotor unmanned aerial vehicle is still many, and the place that needs to improve is also many.
SUMMERY OF THE UTILITY MODEL
To the defect among the prior art, the utility model provides an unmanned aerial vehicle frame base bradyseism device to shock-absorbing capacity when improving unmanned aerial vehicle and descending.
The utility model provides an unmanned aerial vehicle frame base bradyseism device, includes the shell and connects the frame base on the shell, the frame base includes crossbeam, support and undercarriage, the crossbeam with the shell is connected, the crossbeam is connected to support one end, and the undercarriage is connected to the other end, a support is respectively connected at the both ends of crossbeam, the undercarriage is provided with disconnected point, the cross-section of disconnected point is the arc.
Through the utility model discloses can improve the bradyseism ability of unmanned aerial vehicle frame base, the undercarriage of this design adopts the mode that increases disconnected point to realize passive fracture, when unmanned aerial vehicle descends, because the operation is improper or environmental factor leads to falling speed too big, undercarriage contact ground can produce great pressure, when pressure breaks through the power that the undercarriage can bear, disconnected point fracture falls pressure release to reduce the impact to unmanned aerial vehicle, the undercarriage after the fracture divide into two parts, and it itself has certain elasticity, can further play the cushioning effect.
Further, in order to improve the cushioning capacity, a shock absorber is arranged between the support and the undercarriage.
Preferably, for convenience of installation and cost reduction, the shock absorber is a spring piece.
Further, in order to improve the cushioning effect, the breaking point is arranged at the midpoint of the undercarriage.
Furthermore, the landing gear is made of plastic.
Preferably, a firmer material is adopted, the service life can be prolonged, and the landing gear is made of carbon fiber.
Further, in order to improve the overall cushioning effect, the unmanned aerial vehicle further comprises a cantilever, the cantilever is connected with the shell, and the cross beam is connected with the cantilever.
The beneficial effects of the utility model are embodied in:
the utility model discloses can improve the bradyseism ability of unmanned aerial vehicle frame base, the undercarriage of this design adopts the mode that increases disconnected point to realize passive fracture, when unmanned aerial vehicle descends, because the operation is improper or environmental factor leads to falling speed too big, undercarriage contact ground can produce great pressure, when pressure breaks through the power that the undercarriage can bear, disconnected point fracture falls pressure release to reduce the impact to unmanned aerial vehicle, the undercarriage after the fracture divide into two parts, and it itself has certain elasticity, can further play the cushioning effect.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the embodiments or the technical solutions in the prior art will be briefly described below. Throughout the drawings, like elements or portions are generally identified by like reference numerals. In the drawings, elements or portions are not necessarily drawn to scale.
Fig. 1 is a schematic structural diagram of an embodiment of the present invention;
fig. 2 is a schematic structural view of the rack base shown in fig. 1.
In the drawing, 1-shell, 2-frame base, 21-beam, 22-bracket, 23-shock absorber, 24-landing gear, 241-disconnection point, 3-rotor, 4-motor, 5-rotor base and 6-cantilever.
Detailed Description
Embodiments of the present invention will be described in detail below with reference to the accompanying drawings. The following examples are only for illustrating the technical solutions of the present invention more clearly, and therefore are only examples, and the protection scope of the present invention is not limited thereby.
It is to be noted that unless otherwise specified, technical or scientific terms used herein shall have the ordinary meaning as understood by those skilled in the art to which the present invention belongs.
Examples
As shown in fig. 1 and 2, an unmanned aerial vehicle frame base cushioning device, includes shell 1 and connects the frame base 2 on shell 1, frame base 2 includes crossbeam 21, support 22 and undercarriage 24, crossbeam 21 with shell 1 is connected, crossbeam 21 is connected to support 22 one end, and undercarriage 24 is connected to the other end, a support 22 is respectively connected at the both ends of crossbeam 21, undercarriage 24 is provided with disconnected point 241, the cross-section of disconnected point 241 is the arc. The disconnection point 241 may employ a conventional snap-fit technique.
Through the utility model discloses can improve the bradyseism ability of unmanned aerial vehicle frame base, undercarriage 24 of this design adopts the mode that increases disconnected point 241 to realize breaking passively, when unmanned aerial vehicle descends, because the operation is improper or environmental factor leads to falling speed too big, undercarriage 24 contact ground can produce great pressure, when pressure breaks through the power that undercarriage 24 can bear, disconnected point 241 splits, releases pressure to reduce the impact to unmanned aerial vehicle, undercarriage 24 after the fracture divide into two parts, and it itself has certain elasticity, can further play the cushioning effect.
In order to improve the cushioning capacity, a shock absorber 23 is provided between the carrier 22 and the landing gear 24. The disconnection point 241 is provided at the midpoint of the landing gear 24, and the shock absorber 23 may be implemented according to the prior art.
For convenience of installation and cost reduction, the damper 23 is a spring plate.
The service life can be prolonged by adopting firmer materials, and the landing gear 24 is made of carbon fiber.
As shown in fig. 1, in order to improve the overall cushioning effect, the unmanned aerial vehicle further comprises a cantilever 6 and a rotor 3, wherein the cantilever 6 is connected with the housing 1, and the cross beam 21 is connected with the cantilever 6. 6 one end of cantilever is connected shell 1, and the other end is connected with rotor base 5, install motor 4 in rotor base 5, rotor 3 is connected to motor 4.
Finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit the same; although the present invention has been described in detail with reference to the foregoing embodiments, it should be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; such modifications and substitutions do not substantially depart from the scope of the embodiments of the present invention, and are intended to be covered by the claims and the specification.
Claims (7)
1. The utility model provides an unmanned aerial vehicle frame base bradyseism device which characterized in that: including shell (1) and frame base (2) of connection on shell (1), frame base (2) include crossbeam (21), support (22) and undercarriage (24), crossbeam (21) with shell (1) is connected, crossbeam (21) is connected to support (22) one end, and undercarriage (24) is connected to the other end, a support (22) is respectively connected at the both ends of crossbeam (21), undercarriage (24) are provided with disconnected point (241), the cross-section of disconnected point (241) is the arc.
2. The unmanned aerial vehicle frame base bradyseism device of claim 1, characterized in that: a shock absorber (23) is arranged between the support (22) and the landing gear (24).
3. The unmanned aerial vehicle frame base bradyseism device of claim 2, characterized in that: the shock absorber (23) is a spring piece.
4. The unmanned aerial vehicle frame base bradyseism device of claim 1, characterized in that: the disconnection point (241) is arranged at the midpoint of the undercarriage (24).
5. The unmanned aerial vehicle frame base bradyseism device of claim 1, characterized in that: the landing gear (24) is made of plastic.
6. The unmanned aerial vehicle frame base bradyseism device of claim 1, characterized in that: the landing gear (24) is made of carbon fiber.
7. The unmanned aerial vehicle frame base bradyseism device of claim 1, characterized in that: the cantilever (6) is connected with the shell (1), and the cross beam (21) is connected with the cantilever (6).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020189196.4U CN211893630U (en) | 2020-02-20 | 2020-02-20 | Unmanned aerial vehicle frame base bradyseism device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020189196.4U CN211893630U (en) | 2020-02-20 | 2020-02-20 | Unmanned aerial vehicle frame base bradyseism device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN211893630U true CN211893630U (en) | 2020-11-10 |
Family
ID=73292309
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202020189196.4U Expired - Fee Related CN211893630U (en) | 2020-02-20 | 2020-02-20 | Unmanned aerial vehicle frame base bradyseism device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN211893630U (en) |
-
2020
- 2020-02-20 CN CN202020189196.4U patent/CN211893630U/en not_active Expired - Fee Related
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20201110 |
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| CF01 | Termination of patent right due to non-payment of annual fee |