CN204998755U - Rotor unmanned aerial vehicle balance adjustment device - Google Patents
Rotor unmanned aerial vehicle balance adjustment device Download PDFInfo
- Publication number
- CN204998755U CN204998755U CN201520644104.6U CN201520644104U CN204998755U CN 204998755 U CN204998755 U CN 204998755U CN 201520644104 U CN201520644104 U CN 201520644104U CN 204998755 U CN204998755 U CN 204998755U
- Authority
- CN
- China
- Prior art keywords
- fuselage
- weight
- aerial vehicle
- equipment
- unmanned aerial
- 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.)
- Expired - Fee Related
Links
Landscapes
- Forklifts And Lifting Vehicles (AREA)
Abstract
The utility model discloses a rotor unmanned aerial vehicle balance adjustment device, the reciprocating impact tunnel drilling machine comprises a machine body, the front end of fuselage is equipped with equipment and carries the frame, and its rear end is equipped with the fin, equipment carries on the frame including support body and inside hollow telescopic link, the stiff end of telescopic link with fuselage fixed connection, its flexible end with the support body is connected to and including a weight box and a balancing weight, the weight box sets up the fuselage is relative equipment carries on one side of frame, the balancing weight is fixed in the weight box. The utility model discloses when carrying on the equipment of different weight, utilize lever principle, change the position of support body through the length of adjusting the telescopic link, and then change the moment of the equipment that carries on on the support body, make its balancing weight with the fuselage opposite side keep moment balance to realize the quick adjustment that unmanned aerial vehicle is balanced, and it does not need frequently to change the counter weight size, reduced the processing cost.
Description
Technical field
The utility model relates to unmanned air vehicle technique field, particularly relates to a kind of rotor wing unmanned aerial vehicle balance regulator.
Background technology
Single rotor wing unmanned aerial vehicle is under the prerequisite of not installing other equipment, and its center-of-gravity position is positioned at the axis of fuselage.But due to the difference of unmanned plane application, its weight of equipment of carrying has larger difference.Such as lift-launch digital camera or pick up camera all can affect the center-of-gravity position of single rotor wing unmanned aerial vehicle, thus balance when can affect unmanned plane during flying.In prior art, the general balance adopting the mode of counterweight to ensure unmanned plane, but because the weight of equipment of carrying is variant, the size of counterweight needs corresponding change, thus make troubles to the balance adjustment of unmanned plane.
Utility model content
The utility model mainly solves technical matters existing in prior art, thus provides a kind of convenient single rotor wing unmanned aerial vehicle balance regulator regulating, do not need frequently to change counterweight size.
Above-mentioned technical matters of the present utility model is mainly solved by following technical proposals:
The rotor wing unmanned aerial vehicle balance regulator that the utility model provides, comprise fuselage, the front end of described fuselage is provided with equipment and carries frame, its rear end is provided with empennage, described equipment carries the expansion link that frame comprises support body and inner hollow, the fixed end of described expansion link is fixedly connected with described fuselage, its telescopic end is connected with described support body, and comprise a weight box and a clump weight, described weight box is arranged on the side that the relatively described equipment of described fuselage carries frame, and described clump weight is fixed in described weight box.
Further, the telescopic end of described expansion link is provided with multiple telescopic section, and each described telescopic section is provided with pin and multiple pin-and-hole.
Further, described weight box is also provided with a closing door, described closing door adopts transparent material to make.
Further, described clump weight and weight box are bolted to connection, and described bolt is arranged on the bottom of described weight box.
Further, the fixed end of described expansion link is connected with described fuselage is detachable.
The beneficial effects of the utility model are: when carrying the equipment of Different Weight, utilize lever principle, the position of support body is changed by the length of adjustable telescopic rod, and then the moment of the equipment that change support body carries, the clump weight hold torque of itself and fuselage opposite side is balanced, thus realize the quick adjustment of unmanned plane balance, and it does not need frequently to change counterweight size, reduces tooling cost.
Accompanying drawing explanation
In order to be illustrated more clearly in the utility model embodiment or technical scheme of the prior art, be briefly described to the accompanying drawing used required in embodiment or description of the prior art below, apparently, accompanying drawing in the following describes is only embodiments more of the present utility model, for those of ordinary skill in the art, under the prerequisite not paying creative work, other accompanying drawing can also be obtained according to these accompanying drawings.
Fig. 1 is the structural representation of rotor wing unmanned aerial vehicle balance regulator of the present utility model.
Detailed description of the invention
Below in conjunction with accompanying drawing, preferred embodiment of the present utility model is described in detail, to make advantage of the present utility model and feature can be easier to be readily appreciated by one skilled in the art, thus more explicit defining is made to protection domain of the present utility model.
Consult shown in Fig. 1, rotor wing unmanned aerial vehicle balance regulator of the present utility model, comprise fuselage 1, the front end of fuselage 1 is provided with equipment and carries frame 2, and its rear end is provided with empennage 3, equipment carries the expansion link 5 that frame 2 comprises support body 4 and inner hollow, the fixed end of expansion link 5 is fixedly connected with fuselage 1, and its telescopic end is connected with support body 4, and comprises weight box 6 and a clump weight 7, weight box 6 is arranged on the side that fuselage 1 relative device carries frame 2, and clump weight 7 is fixed in weight box 6.The utility model is when carrying the equipment of Different Weight, utilize lever principle, the position of support body 4 is changed by the length of adjustable telescopic rod 5, and then change the moment of the equipment that support body 4 carries, clump weight 7 hold torque of itself and fuselage 1 opposite side is balanced, thus realize the quick adjustment of unmanned plane balance, and it does not need frequently to change counterweight size, reduces tooling cost.In the utility model, equipment carries frame 2 and adopts expansion link 5 to coordinate support body 4 carrying equipment, in the packaging and transportation of unmanned plane, and minimum position of expansion link 5 can being retracted, the monnolithic case size of unmanned plane can be reduced, facilitate packaging and the transport of unmanned plane.
Concrete, the telescopic end of expansion link 5 is provided with multiple telescopic section 8, and each telescopic section 8 is provided with pin 9 and multiple pin-and-hole 10.By by one of them pin-and-hole 10 of the insertion of pin 9 correspondence, just can adjust and fix the length of each telescopic section 8, and then the length of adjustment expansion link 5.Preferably, in order to improve safety and the convenient model to counterweight and size are observed, weight box 6 is also provided with a closing door 11, closing door 11 adopts transparent material to make.And in order to prevent clump weight 7 play in weight box 6, clump weight 7 is fixedly connected with by bolt 12 with weight box 6, and bolt 12 is arranged on the bottom of weight box 6, conveniently clump weight 7 is fixed.In the utility model, conveniently Assembly &Disassembly, the fixed end of expansion link 5 is connected with fuselage 1 is detachable.
Above, be only detailed description of the invention of the present utility model, but protection domain of the present utility model is not limited thereto, any change of expecting without creative work or replacement, all should be encompassed within protection domain of the present utility model.Therefore, the protection domain that protection domain of the present utility model should limit with claims is as the criterion.
Claims (5)
1. a rotor wing unmanned aerial vehicle balance regulator, comprise fuselage (1), the front end of described fuselage (1) is provided with equipment and carries frame (2), its rear end is provided with empennage (3), it is characterized in that: described equipment carries the expansion link (5) that frame (2) comprises support body (4) and inner hollow, the fixed end of described expansion link (5) is fixedly connected with described fuselage (1), its telescopic end is connected with described support body (4), and comprise a weight box (6) and a clump weight (7), described weight box (6) is arranged on the side that the relatively described equipment of described fuselage (1) carries frame (2), described clump weight (7) is fixed in described weight box (6).
2. rotor wing unmanned aerial vehicle balance regulator as claimed in claim 1, it is characterized in that: the telescopic end of described expansion link (5) is provided with multiple telescopic section (8), each described telescopic section (8) is provided with pin (9) and multiple pin-and-hole (10).
3. rotor wing unmanned aerial vehicle balance regulator as claimed in claim 2, is characterized in that: described weight box (6) is also provided with a closing door (11), and described closing door (11) adopts transparent material to make.
4. rotor wing unmanned aerial vehicle balance regulator as claimed in claim 3, it is characterized in that: described clump weight (7) is fixedly connected with by bolt (12) with weight box (6), described bolt (12) is arranged on the bottom of described weight box (6).
5. rotor wing unmanned aerial vehicle balance regulator as claimed in claim 1, is characterized in that: the fixed end of described expansion link (5) is connected with described fuselage (1) is detachable.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520644104.6U CN204998755U (en) | 2015-08-24 | 2015-08-24 | Rotor unmanned aerial vehicle balance adjustment device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520644104.6U CN204998755U (en) | 2015-08-24 | 2015-08-24 | Rotor unmanned aerial vehicle balance adjustment device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204998755U true CN204998755U (en) | 2016-01-27 |
Family
ID=55155656
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520644104.6U Expired - Fee Related CN204998755U (en) | 2015-08-24 | 2015-08-24 | Rotor unmanned aerial vehicle balance adjustment device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204998755U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107010207A (en) * | 2017-04-19 | 2017-08-04 | 四川智航慧飞无人机科技有限公司 | Automatic balancing bracket for balancing unmanned plane during flying state |
| CN107182442A (en) * | 2017-06-24 | 2017-09-22 | 匡致宇 | Pluck unmanned plane |
| 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 |
-
2015
- 2015-08-24 CN CN201520644104.6U patent/CN204998755U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107010207A (en) * | 2017-04-19 | 2017-08-04 | 四川智航慧飞无人机科技有限公司 | Automatic balancing bracket for balancing unmanned plane during flying state |
| CN107182442A (en) * | 2017-06-24 | 2017-09-22 | 匡致宇 | Pluck unmanned plane |
| 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 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN205087137U (en) | Single rotor unmanned aerial vehicle balance adjustment device | |
| CN205418138U (en) | Triaxial optoelectronic pod | |
| CN204998755U (en) | Rotor unmanned aerial vehicle balance adjustment device | |
| CN206939031U (en) | A kind of electronic unmanned plane of fixed-wing | |
| WO2018071592A3 (en) | Apparatus and method for balancing aircraft with robotic arms | |
| CN203996917U (en) | A kind of unmanned vehicle | |
| CN204998767U (en) | Double -deck rotor unmanned aerial vehicle of modified | |
| CN205554623U (en) | Optical zoom nacelle | |
| CN106394882A (en) | Sliding groove type unmanned aerial vehicle skid collecting and releasing mechanism | |
| CN105501440A (en) | Unmanned aerial vehicle | |
| CN104908936A (en) | Unmanned helicopter | |
| CN202429344U (en) | Unmanned aerial vehicle | |
| CN105486484A (en) | Pylon pitching modal simulation device suitable to be used for flutter wind tunnel model | |
| CN104608917A (en) | Tail wing structure of fixed wing unmanned aerial vehicle | |
| CN207496919U (en) | A kind of aircraft counter weight device | |
| CN207496927U (en) | A kind of fixed-wing unmanned plane for adapting to a variety of environment that take off | |
| CN105564661A (en) | Transport helicopter task load hanging point | |
| CN202666408U (en) | Six-arm model aerial propeller | |
| CN203996872U (en) | A kind of unmanned airplane empennage balance adjusting structure | |
| CN105836147B (en) | A kind of rotor wing unmanned aerial vehicle protective device | |
| CN104476993A (en) | Extensible tail wing structure | |
| CN203402385U (en) | Single-axis aircraft | |
| CN206446797U (en) | A kind of banner draw off gear based on multi-rotor unmanned aerial vehicle | |
| CN207417114U (en) | A kind of telescopic unmanned plane of empennage | |
| CN208530862U (en) | A kind of unmanned plane searchlighting lamp support |
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: 20160127 Termination date: 20160824 |