CN217554172U - Balance adjusting device of double-rotor unmanned helicopter - Google Patents
Balance adjusting device of double-rotor unmanned helicopter Download PDFInfo
- Publication number
- CN217554172U CN217554172U CN202221916314.2U CN202221916314U CN217554172U CN 217554172 U CN217554172 U CN 217554172U CN 202221916314 U CN202221916314 U CN 202221916314U CN 217554172 U CN217554172 U CN 217554172U
- Authority
- CN
- China
- Prior art keywords
- mounting groove
- end cover
- unmanned helicopter
- lead screw
- adjustment device
- 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.)
- Active
Links
Images
Landscapes
- Toys (AREA)
Abstract
The utility model discloses a two-rotor unmanned helicopter balance adjustment device, which relates to the technical field of unmanned helicopters, and comprises a two-rotor unmanned helicopter frame, wherein a balance adjustment device is arranged on the two-rotor unmanned helicopter frame, a secondary end cover mounting groove is arranged at one end of the two-rotor unmanned helicopter frame close to a tail, a main end cover mounting groove is arranged at one end of the two-rotor unmanned helicopter frame far away from the tail, one end of the balance adjustment device is arranged in the secondary end cover mounting groove and is fixed through a secondary end cover, and the other end of the balance adjustment device is arranged in the main end cover mounting groove and is fixed through a main end cover; the utility model discloses a gravity balance of regulation organism that balance adjustment device can be free, and the regulative mode is simple, effective.
Description
Technical Field
The utility model belongs to the technical field of unmanned helicopter, concretely relates to unmanned helicopter balance adjustment device of bispin wing.
Background
Because rotor unmanned aerial vehicle has can hover, can fly at arbitrary speed in certain speed range, be the platform of an aerial flight basically, can load sensor, camera of oneself on the platform, the characteristics of manipulator even, rotor unmanned aerial vehicle's development is very rapid.
Because rotor unmanned aerial vehicle wing generally has good symmetry, the lift that provides is also symmetrical, consequently when carrying the equipment of different weight, can cause rotor unmanned aerial vehicle's unbalance, and present solution is to increase the counter weight and balance, but current counter weight means is adjusted conveniently inadequately, and the flexibility is relatively poor.
SUMMERY OF THE UTILITY MODEL
The utility model provides a unmanned helicopter balance adjustment of bispin wing device has solved current technical problem.
In order to solve the technical problem, the utility model provides a pair of unmanned helicopter of bispin balance adjustment device, including the unmanned helicopter of bispin frame, be provided with balance adjustment device in the unmanned helicopter of bispin frame, the one end that is close to the tail in the unmanned helicopter of bispin frame is provided with secondary end cover mounting groove, the one end of keeping away from the tail in the unmanned helicopter of bispin frame is provided with main end cover mounting groove, balance adjustment device's one end is installed in secondary end cover mounting groove and is fixed through the secondary end cover, and balance adjustment device's the other end is installed in main end cover mounting groove and is fixed through the main end cover.
Preferably, the balance adjusting device comprises a positioning polished rod, a lead screw, a balancing weight, a driven gear, a motor and a driving gear, wherein a lead screw mounting groove and a polished rod mounting groove are formed in the bottom of the secondary end cover mounting groove, a lead screw mounting groove, a polished rod mounting groove, a gear mounting groove and a motor mounting groove are formed in the bottom of the primary end cover mounting groove, the lead screw mounting groove and the polished rod mounting groove on the primary end cover mounting groove correspond to the lead screw mounting groove and the polished rod mounting groove on the primary end cover mounting groove, the lead screw and the positioning polished rod are arranged between the primary end cover mounting groove and the secondary end cover mounting groove, the lead screw is mounted in the lead screw mounting groove through a bearing, the positioning polished rod is mounted in the polished rod mounting groove, the motor is mounted in the motor mounting groove, the driving gear is fixedly mounted on a power output shaft of the motor, the driven gear is fixedly arranged at one end of the lead screw arranged in the primary end cover mounting groove, the driving gear and the driven gear are both arranged in the gear mounting groove, the balancing weight is mounted between the lead screw and the positioning polished rod, the balancing weight is in threaded connection with the positioning polished rod, and the balancing weight is in sliding connection with the positioning polished rod.
Preferably, the secondary end cover and the main end cover are fixedly connected with the double-rotor unmanned helicopter frame through screws.
Preferably, the secondary end cover is provided with a screw rod mounting groove and a polished rod mounting groove which correspond to the screw rod mounting groove and the polished rod mounting groove on the secondary end cover mounting groove.
Preferably, the main end cover is provided with a screw rod mounting groove, a polished rod mounting groove, a gear mounting groove and a motor mounting groove which correspond to the screw rod mounting groove, the polished rod mounting groove, the gear mounting groove and the motor mounting groove on the main end cover mounting groove.
Preferably, the positioning polished rods are arranged in two and symmetrical positions.
Compared with the prior art, the utility model has the following advantages:
1. when the double-rotor unmanned helicopter is operated, the screw rod is driven to rotate through the work of the motor, and then the left and right movement of the balancing weight block is controlled, so that the self gravity balance of the double-rotor unmanned helicopter is realized, for example, when the head of the double-rotor unmanned helicopter is additionally provided with a camera, an agricultural chemical box and other equipment, so that the condition that the machine head is heavier and the machine tail is lighter is caused, the balancing weight block can be moved to the machine tail, and when the machine tail is heavier and the machine head is lighter, the balancing weight block can be moved to the machine head;
2. through the removal of location polished rod cooperation balancing weight, be favorable to guaranteeing the stability of balancing weight when removing.
Drawings
Fig. 1 is a schematic view of the overall structure of the unmanned helicopter of the present invention;
fig. 2 is an installation schematic diagram of the dual-rotor unmanned helicopter frame and the balance adjusting device of the present invention;
fig. 3 is a schematic structural view of the dual-rotor unmanned helicopter frame of the present invention;
fig. 4 is a schematic structural view of the main end cap of the present invention;
fig. 5 is a schematic structural view of the secondary end cap of the present invention.
Reference numbers in the figures: 1. a dual rotor unmanned helicopter frame; 11. a secondary end cover mounting groove; 12. a screw rod mounting groove; 13. a polished rod mounting groove; 14. a main end cover mounting groove; 15. a gear mounting groove; 16. a motor mounting groove; 2. a balance adjustment device; 21. positioning the polished rod; 22. a screw rod; 23. a balancing weight; 24. a driven gear; 25. a motor; 26. a driving gear; 3. a primary end cap; 4. a secondary end cap; 5. and (4) screws.
Detailed Description
The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.
Referring to fig. 1-5, the present invention provides a technical solution: the utility model provides a two rotor unmanned helicopter balance adjustment device, including two rotor unmanned helicopter frame 1, be provided with balance adjustment device 2 in the two rotor unmanned helicopter frame 1, the one end that is close to the tail in the two rotor unmanned helicopter frame 1 is provided with inferior end cover mounting groove 11, the one end of keeping away from the tail in the two rotor unmanned helicopter frame 1 is provided with main end cover mounting groove 14, balance adjustment device 2's one end is installed in inferior end cover mounting groove 11 and is fixed through inferior end cover 4, balance adjustment device 2's the other end is installed in main end cover mounting groove 14 and is fixed through main end cover 3.
Further, preferably, the balance adjusting device 2 is composed of a positioning polished rod 21, a lead screw 22, a balancing weight 23, a driven gear 24, a motor 25 and a driving gear 26, a lead screw mounting groove 12 and a polished rod mounting groove 13 are formed in the bottom of the secondary end cover mounting groove 11, a lead screw mounting groove 12, a polished rod mounting groove 13, a gear mounting groove 15 and a motor mounting groove 16 are formed in the bottom of the primary end cover mounting groove 14, the lead screw mounting groove 12 on the primary end cover mounting groove 14, the polished rod mounting groove 13 corresponds to the lead screw mounting groove 12 and the polished rod mounting groove 13 on the primary end cover mounting groove 14, the lead screw 22 and the positioning polished rod 21 are both arranged between the primary end cover mounting groove 14 and the secondary end cover mounting groove 11, the lead screw 22 is mounted in the lead screw mounting groove 12 through a bearing, the positioning polished rod 21 is mounted in the polished rod mounting groove 13, the motor 25 is mounted in the motor mounting groove 16, the driving gear 26 is fixedly mounted on a power output shaft of the motor 25, the driven gear 24 is fixedly mounted at one end of the lead screw 22 arranged in the primary end cover mounting groove 14, the driven gear 24, the driving gear 24 is fixedly provided with the driving gear 24, the driving gear 26 and the driving gear 24, the driving gear 26 are both arranged in the driving gear 24 are arranged in the gear 22, the gear is arranged in the main end cover mounting groove 14, the polished rod 23, the balancing weight 23 is in threaded connection with the balancing weight 21, and the polished rod 23, and the balancing weight 21, and the polished rod 23 are in a sliding connection, and the balancing weight 21 in a sliding connection, and the positioning polished rod 21.
Further, preferably, the secondary end cover 4 and the main end cover 3 are fixedly connected with the dual-rotor unmanned helicopter frame 1 through screws 5.
Further, preferably, the secondary end cover 4 is provided with a screw rod mounting groove 12 and a polished rod mounting groove 13 corresponding to the screw rod mounting groove 12 and the polished rod mounting groove 13 on the secondary end cover mounting groove 11.
Further, preferably, the main end cap 3 is provided with a lead screw mounting groove 12, a polish rod mounting groove 13, a gear mounting groove 15 and a motor mounting groove 16 corresponding to the lead screw mounting groove 12, the polish rod mounting groove 13, the gear mounting groove 15 and the motor mounting groove 16 on the main end cap mounting groove 14.
Further, it is preferable that the positioning polish rods 21 are provided in two and symmetrical.
The working principle is as follows: the utility model discloses when the operation, it is rotatory to drive lead screw 22 through the work of motor 25, and then control about balancing weight 23, realize the balance to the unmanned helicopter of bispin self gravity, for example, the head when the unmanned helicopter of bispin increases the camera, equipment such as pesticide case causes the aircraft nose heavy weight, during the condition that the tail is light on the fly, can remove balancing weight 23 to the tail, and the tail is heavy on the fly, when the aircraft nose is light on the fly, then can remove balancing weight 23 to the aircraft nose, through the removal of 21 cooperation balancing weights 23 of location polished rod, be favorable to guaranteeing the stability of balancing weight 23 when removing.
It is noted that, herein, relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation. The use of the phrase "comprising one of the elements does not exclude the presence of other like elements in the process, method, article, or apparatus that comprises the element.
Although embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that changes, modifications, substitutions and alterations can be made in these embodiments without departing from the principles and spirit of the invention, the scope of which is defined in the appended claims and their equivalents.
Claims (6)
1. The utility model provides an unmanned helicopter of two rotors balancing control device, includes unmanned helicopter of two rotors frame (1), its characterized in that: be provided with balance adjustment device (2) on bispin unmanned helicopter frame (1), the one end that is close to the tail on bispin unmanned helicopter frame (1) is provided with inferior end cover mounting groove (11), the one end of keeping away from the tail on bispin unmanned helicopter frame (1) is provided with main end cover mounting groove (14), the one end of balance adjustment device (2) is installed in inferior end cover mounting groove (11) and is fixed through inferior end cover (4), and the other end of balance adjustment device (2) is installed in main end cover mounting groove (14) and is fixed through main end cover (3).
2. The balance adjustment device for the twin-rotor unmanned helicopter according to claim 1, wherein the balance adjustment device (2) is composed of a positioning polish rod (21), a lead screw (22), a weight block (23), a driven gear (24), a motor (25) and a driving gear (26), the bottom of the secondary end cover mounting groove (11) is provided with a lead screw mounting groove (12) and a polish rod mounting groove (13), the bottom of the primary end cover mounting groove (14) is provided with a lead screw mounting groove (12), a polish rod mounting groove (13), a gear mounting groove (15) and a motor mounting groove (16), the lead screw mounting groove (12) and the polish rod mounting groove (13) on the primary end cover mounting groove (14) correspond to the lead screw mounting groove (12) and the polish rod mounting groove (13) on the secondary end cover mounting groove (11), the lead screw (22) and the positioning polish rod (21) are both disposed between the primary end cover mounting groove (14) and the secondary end cover mounting groove (11), the lead screw (22) is mounted in the lead screw mounting groove (12) through a bearing, the positioning polish rod (21) is mounted in the polish rod mounting groove (13), the motor (25) is mounted in the motor mounting groove (16), the driving gear mounting groove (26) is disposed in the driven end cover mounting groove (14), and the driven gear mounting groove (26) is disposed in the output shaft (14) in the driven end of the driven end cover mounting groove (24) is disposed in the lead screw mounting groove (22) ) The driving gear (26) and the driven gear (24) are arranged in the gear mounting groove (15), the driving gear (26) is meshed with the driven gear (24), the balancing weight (23) is mounted between the screw rod (22) and the positioning polished rod (21), the balancing weight (23) is in threaded connection with the screw rod (22), and the balancing weight (23) is in sliding connection with the positioning polished rod (21).
3. The twin-rotor unmanned helicopter aircraft of claim 1 wherein the secondary end cap (4) and the primary end cap (3) are both fixedly attached to the twin-rotor unmanned helicopter chassis (1) by screws (5).
4. The balance adjustment device for the twin-rotor unmanned helicopter according to claim 2, wherein the secondary end cap (4) is provided with a lead screw mounting groove (12) and a polished rod mounting groove (13) corresponding to the lead screw mounting groove (12) and the polished rod mounting groove (13) of the secondary end cap mounting groove (11).
5. The balance adjustment device for the twin rotor unmanned helicopter according to claim 2, wherein the main end cap (3) is formed with a lead screw mounting groove (12), a polish rod mounting groove (13), a gear mounting groove (15) and a motor mounting groove (16) corresponding to the lead screw mounting groove (12), the polish rod mounting groove (13), the gear mounting groove (15) and the motor mounting groove (16) of the main end cap mounting groove (14).
6. A twin-rotor unmanned helicopter regulating device according to claim 2, characterized in that said positioning polish rods (21) are arranged in two and symmetrical.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202221916314.2U CN217554172U (en) | 2022-07-20 | 2022-07-20 | Balance adjusting device of double-rotor unmanned helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202221916314.2U CN217554172U (en) | 2022-07-20 | 2022-07-20 | Balance adjusting device of double-rotor unmanned helicopter |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN217554172U true CN217554172U (en) | 2022-10-11 |
Family
ID=83505183
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202221916314.2U Active CN217554172U (en) | 2022-07-20 | 2022-07-20 | Balance adjusting device of double-rotor unmanned helicopter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN217554172U (en) |
-
2022
- 2022-07-20 CN CN202221916314.2U patent/CN217554172U/en active Active
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106240843B (en) | Multi-rotor unmanned aerial vehicle structured testing device and method based on reducing rack | |
| CN108839793A (en) | A kind of continue a journey for unmanned plane increases the generating equipment of journey | |
| CN104787327A (en) | Axle distance-variable multi-rotor aircraft | |
| CN109774507A (en) | A kind of small drone identical tension power supply system | |
| CN105151296A (en) | Multi-axis manned aircraft | |
| CN204548502U (en) | A kind of collapsible air-drop unmanned plane | |
| CN217554172U (en) | Balance adjusting device of double-rotor unmanned helicopter | |
| CN210526849U (en) | Fixed wing unmanned aerial vehicle of tilting-rotating force | |
| CN112224431A (en) | Unmanned aerial vehicle's take off and land platform device is patrolled and examined to electric power | |
| CN205770202U (en) | A kind of captive unmanned plane automatic deploying and retracting case | |
| CN205221109U (en) | Multiaxis manned vehicle | |
| CN206446806U (en) | A kind of flight control assemblies of three rotors frame structure matching | |
| CN204383745U (en) | A kind of engine installation of unmanned plane | |
| CN203593163U (en) | Multi-rotor unmanned aerial vehicle | |
| CN204507258U (en) | A kind of many rotor unmanned aircrafts | |
| CN116215848A (en) | Elastic shrinkage type shock absorption support for unmanned aerial vehicle | |
| CN205440866U (en) | Rotorcraft aircraft verts | |
| CN110203411A (en) | It is a kind of with the unmanned plane and UAV system that detachably take object manipulator | |
| CN210707885U (en) | Unmanned aerial vehicle is patrolled and examined to electric power | |
| CN115180148A (en) | Reconfigurable unmanned aerial vehicle applied to river channel garbage cleaning | |
| CN205931255U (en) | Spherical unmanned aerial vehicle based on ARM | |
| CN209776797U (en) | Multi-functional emergency rescue multi-rotor unmanned aerial vehicle | |
| CN204124363U (en) | A kind of multi-rotor aerocraft | |
| CN204776019U (en) | Multi -rotor aircraft | |
| CN105836118A (en) | Power device of unmanned aerial vehicle |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |