CN202682789U - Model helicopter - Google Patents
Model helicopter Download PDFInfo
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- CN202682789U CN202682789U CN 201220339310 CN201220339310U CN202682789U CN 202682789 U CN202682789 U CN 202682789U CN 201220339310 CN201220339310 CN 201220339310 CN 201220339310 U CN201220339310 U CN 201220339310U CN 202682789 U CN202682789 U CN 202682789U
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- screw
- helicopter
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- model helicopter
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- 239000011469 building brick Substances 0.000 claims description 8
- 239000011295 pitch Substances 0.000 description 24
- 230000009471 action Effects 0.000 description 9
- 230000008859 change Effects 0.000 description 7
- 230000009467 reduction Effects 0.000 description 4
- 230000006698 induction Effects 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000008569 process Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000000354 decomposition reaction Methods 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
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Abstract
The utility model relates to a model helicopter, which comprises a helicopter body, wherein the inside of the helicopter body is provided with a main shaft and a hollow shaft, the main shaft is arranged in the hollow shaft, the hollow shaft is provided with a main propeller, the main shaft is provided with an auxiliary propeller, the inside of the helicopter body is provided with an electronic gyroscope, a tilting disc and a steering gear are arranged under the main propeller and are connected with a pull rod, the tilting disc is provided with a reversing disc, the reversing disc is in linkage with the main propeller, a headframe cap is arranged on the auxiliary propeller, and the auxiliary propeller is in linkage with the headframe cap by an elastic connecting element. The model helicopter has the advantages that the inside of the helicopter body is provided with the electronic gyroscope, so the flying attitude of the model helicopter is automatically detected, and the helicopter is automatically controlled, and meanwhile, the balance rod is replaced by the elastic connecting element to maintain the stability of the helicopter, so the balance rod is not required, and the load of the model helicopter is reduced.
Description
Technical field
The utility model relates to a kind of model plane, particularly a kind of model helicopter.
Background technology
Model plane, a kind of model of an airplane that can aloft fly wherein relatively common are model helicopter.The development of model plane is the interesting and intellectual of it, is not that the model aircraft that simply can not fly can be compared, and particularly model helicopter by increasing people are liked, is not limited only to child.The developer is in view of the marketability of model helicopter, continually develops to have the more model helicopter of high-tech.
Present model helicopter mostly is greatly one group of screw, the wind loading rating of outdoor flight a little less than, the green hand is restive, easily causes damage or the damage of model helicopter.The part model helicopter is provided with two groups of screws, and the helicopter wind loading rating strengthens.Yet in order to keep the stationarity of model helicopter flight, model helicopter is provided with balancing pole, comprises counterweight, keeps the balance of model helicopter by balancing pole.Yet when model helicopter was subject to extraneous larger interference (such as strong wind or collision), deviation appearred in flare maneuver, and balancing pole is corrected flare maneuver needs the regular hour, and the green hand is restive equally, easily causes damage or the damage of model helicopter.In addition, balancing pole itself is heavier, and model helicopter has higher requirement for the weight of self, and self overweight flight for model helicopter has larger impact, is unfavorable for flight.
Summary of the invention
In order to overcome the deficiencies in the prior art, the utility model provides a kind of coaxial pair of oar, without balancing pole, adopt the Electric automatic control balance, substitute balancing pole by Flexible Connector simultaneously and keep having a smooth flight property, the model helicopter of load reduction.
The technical scheme that its technical problem that solves the utility model adopts is: a kind of model helicopter, comprise body, be provided with main shaft and hollow shaft in the described body, described main shaft is located in the described hollow shaft, described hollow shaft is provided with main screw, described main shaft is provided with secondary screw, be provided with electronic gyroscope in the described body, described main screw below is provided with pitch and steering wheel, described pitch is connected by pull bar with steering wheel, and described pitch is provided with the break-in dish, described break-in dish and described main screw interlock, described secondary screw top is provided with headstock cap, and described secondary screw and described headstock cap are by the Flexible Connector interlock.
The utility model is by being provided with electronic gyroscope in body, it can automatically detect the flight attitude of model helicopter and automatically control helicopter, when model helicopter is subject to extraneous larger interference (such as strong wind or collision), deviation appears in flare maneuver, electronic gyroscope can produce induction immediately, then handling described steering wheel fascinates, the pitch that links to each other with steering wheel by pull bar fascinates immediately, be located at simultaneously the break-in dish on the pitch, also fascinate synchronously with the main screw of break-in dish interlock, thereby make whole helicopter change incline direction, correct the action deviation.Be in course of adjustment, hollow shaft, main shaft and headstock cap are positioned on the vertical axis of helicopter always, can not fascinate, spur secondary screw by Flexible Connector, secondary screw is got back on original relative position, thereby make helicopter keep having a smooth flight property, be easy to control, greatly improve the wind loading rating of outdoor flight.No longer need simultaneously balancing pole, model helicopter load reduction.
When model helicopter need to be done tilting action, handling described steering wheel fascinates, the pitch that links to each other with steering wheel by pull bar fascinates immediately, be located at simultaneously break-in dish on the pitch, also fascinate synchronously with the main screw of break-in dish interlock, thereby make whole helicopter change incline direction, finish tilting action.Equally in the action complete process, hollow shaft, main shaft and headstock cap are positioned on the vertical axis of helicopter always, can not fascinate, and spur secondary screw by Flexible Connector, secondary screw is got back on original relative position, thereby made helicopter keep having a smooth flight property.
In one embodiment, described Flexible Connector is made as spring or cushion rubber.The good springiness of spring, cushion rubber, gradual change is steady, and elasticity is difficult for losing efficacy simultaneously.Certainly in other embodiments, can use other Flexible Connectors, such as elastic threads etc.
In one embodiment, described body comprises frame, is located at Power Component, steering assembly, the two oar rotary components in the frame and the electronic building brick that can receive external signal, described Power Component drives described pair of oar rotary components, described electronic building brick is controlled described Power Component and steering assembly, described pair of oar rotary components of described steering assembly control.
In one embodiment, described Power Component comprises battery, motor, motor gear, master gear, pinion.Motor links to each other with motor gear, and CD-ROM drive motor gear, motor gear mesh with master gear and pinion respectively.
In a preferred embodiment, described motor adopts high-effect brush motor, is made as two.Adopt the double motor power drive, powerful power can be provided, promote the rotating speed of helicopter flight, strengthen the helicopter wind loading rating.
In one embodiment, described steering assembly comprises two steering wheels, the pitch that links to each other with steering wheel, is located at the break-in dish on the pitch.Described pitch is succinct cross plate structure, push away one by two steering wheels one and draw in capable fascinating, and drive break-in dish fascinates synchronously.
In a preferred embodiment, described break-in dish is provided with connecting rod, and described break-in dish is by connecting rod and described main screw interlock.Simple and reasonable, stable connection.
In one embodiment, the described pair of oar rotary components comprises hollow shaft, main shaft, is located at main screw on the hollow shaft, is located at secondary screw and headstock cap on the main shaft.Described hollow shaft is connected with described master gear and with the master gear rotation, described main shaft is connected with described pinion and rotates with pinion.Described break-in dish and described main screw rotate with hollow shaft, and described secondary screw and described headstock cap rotate with main shaft.Need to prove, described pitch only fascinates by steering wheel, does not rotate with hollow shaft.
In one embodiment, described main screw and described secondary screw comprise blade, blade folder.
In a preferred embodiment, described main screw and described secondary screw are the symmetrical airfoil screw that load is light, lift is strong, can promote the rotating speed of helicopter flight, strengthen the helicopter wind loading rating.
The beneficial effects of the utility model are: the utility model is by being provided with electronic gyroscope in body, it can automatically detect the flight attitude of model helicopter and automatically control helicopter, when model helicopter is subject to extraneous larger interference (such as strong wind or collision), deviation appears in flare maneuver, electronic gyroscope can produce induction immediately, then handling described steering wheel fascinates, the pitch that links to each other with steering wheel by pull bar fascinates immediately, be located at simultaneously the break-in dish on the pitch, also fascinate synchronously with the main screw of break-in dish interlock, thereby make whole helicopter change incline direction, correct the action deviation.Be in course of adjustment, hollow shaft, main shaft and headstock cap are positioned on the vertical axis of helicopter always, can not fascinate, spur secondary screw by Flexible Connector, secondary screw is got back on original relative position, thereby make helicopter keep having a smooth flight property, be easy to control, greatly improve the wind loading rating of outdoor flight.No longer need simultaneously balancing pole, model helicopter load reduction.
Description of drawings
Fig. 1 is the complete machine planar structure schematic diagram of an embodiment of the utility model.
Fig. 2 is the complete machine decomposition texture schematic diagram of an embodiment of the utility model.
Omitted the miscellaneous part irrelevant with the utility model design main points among the figure.
The specific embodiment
Below in conjunction with the drawings and specific embodiments, the utility model is described in further details.
As shown in Figure 1 and Figure 2, a kind of model helicopter 100 of the present utility model, comprise body, be provided with main shaft 101 and hollow shaft 102 in the described body, described main shaft 101 is located in the described hollow shaft 102, and described hollow shaft 102 is provided with main screw 103, and described main shaft 101 is provided with secondary screw 104, be provided with the electronic gyroscope (not shown) in the described body, described main screw 103 belows are provided with pitch 105 and steering wheel 106.In the present embodiment, described steering wheel 106 is made as two, described pitch 105 is connected by pull bar 107 with steering wheel 106, described pitch 105 is provided with break-in dish 108, described break-in dish 108 and described main screw 103 interlocks, described secondary screw 104 tops are provided with headstock cap 109, and described secondary screw 104 passes through Flexible Connector 110 interlocks with described headstock cap 109.
The utility model is by being provided with electronic gyroscope in body, it can automatically detect the flight attitude of model helicopter and automatically control helicopter, when model helicopter is subject to extraneous larger interference (such as strong wind or collision), deviation appears in flare maneuver, electronic gyroscope can produce induction immediately, then handling described steering wheel 106 fascinates, the pitch 105 that links to each other with steering wheel 106 by pull bar 107 fascinates immediately, be located at simultaneously the break-in dish 108 on the pitch 105, also fascinate synchronously with the main screw 103 of break-in dish 108 interlocks, thereby make whole helicopter change incline direction, correct the action deviation.Be in course of adjustment, hollow shaft 102, main shaft 101 and headstock cap 109 are positioned on the vertical axis of helicopter always, can not fascinate, by the secondary screw 104 of Flexible Connector 110 pullings, secondary screw 104 is got back on original relative position, thereby make helicopter keep having a smooth flight property, be easy to control, greatly improve the wind loading rating of outdoor flight.No longer need simultaneously balancing pole, model helicopter load reduction.
When model helicopter need to be done tilting action, handling described steering wheel 106 fascinates, the pitch 105 that links to each other with steering wheel 106 by pull bar 107 fascinates immediately, be located at simultaneously break-in dish 108 on the pitch 105, also fascinate synchronously with the main screw 103 of break-in dish 108 interlocks, thereby make whole helicopter change incline direction, finish tilting action.Equally in the action complete process, hollow shaft 102, main shaft 101 and headstock cap 109 are positioned on the vertical axis of helicopter always, can not fascinate, by the secondary screw 104 of Flexible Connector 110 pullings, secondary screw 104 is got back on original relative position, thereby made helicopter keep having a smooth flight property.
In the present embodiment, described Flexible Connector 110 is made as spring.The good springiness of spring, gradual change is steady, and elasticity is difficult for losing efficacy simultaneously.Certainly in other embodiments, can use other Flexible Connectors, such as cushion rubber, elastic threads etc.
In the present embodiment, described body comprises frame, is located at Power Component, steering assembly, the two oar rotary components in the frame and the electronic building brick that can receive external signal, described Power Component drives described pair of oar rotary components, described electronic building brick is controlled described Power Component and steering assembly, described pair of oar rotary components of described steering assembly control.Described electronic building brick comprises electronic gyroscope, and described electronic building brick is handled described steering wheel by electronic gyroscope and controlled described steering assembly.
In the present embodiment, described Power Component comprises battery 111, motor 112, motor gear 113, master gear 114, pinion 115.Described motor 112 adopts high-effect brush motor, is made as two, and motor gear 113 also is made as two simultaneously.Motor 112 links to each other with motor gear 113, and CD-ROM drive motor gear 113, motor gear 113 mesh with master gear 114 and pinion 115 respectively.Described body below is provided with battery carrier 116, and described battery 111 places in the described battery carrier 116, for described motor 112 provides electric power.Adopt the double motor power drive, powerful power can be provided, promote the rotating speed of helicopter flight, strengthen the helicopter wind loading rating.
In the present embodiment, described steering assembly comprises two steering wheels 106, the pitch 105 that links to each other with steering wheel 106, is located at the break-in dish 108 on the pitch 105.Described pitch 105 is succinct cross plate structure, push away one by two steering wheels 106 1 and draw in capable fascinating, and drive break-in dish 108 fascinates synchronously.
In the present embodiment, described break-in dish 108 is provided with connecting rod 117, and described break-in dish 108 is by connecting rod 117 and described main screw 103 interlocks.Simple and reasonable, stable connection.
In the present embodiment, the described pair of oar rotary components comprise hollow shaft 102, main shaft 101, be located at main screw 103 on the hollow shaft 102, be located at secondary screw 104 and headstock cap 109 on the main shaft 101.Described hollow shaft 102 is connected with described master gear 114 and with master gear 114 rotations, described main shaft 101 is connected with described pinion 115 and rotates with pinion 115.Described break-in dish 108 and described main screw 103 are with hollow shaft 102 rotations, and described secondary screw 104 and described headstock cap 109 are with main shaft 101 rotations.Need to prove, 105 of described pitches fascinate by steering wheel 106, with hollow shaft 102 rotations.
In the present embodiment, described main screw 103 and described secondary screw 104 comprise blade 118, blade folder 119.The blade 118 of described main screw 103 and described secondary screw 104 all is made as two, and described main screw 103 and described secondary screw 104 " cross " arrange, and overlook just as " a ten " word from the top.In other embodiments, the blade of described main screw and described secondary screw also can be set to three or more.
Described main screw 103 and described secondary screw 104 are the symmetrical airfoil screw that load is light, lift is strong, can promote the rotating speed of helicopter flight, strengthen the helicopter wind loading rating.
Only be preferred embodiment of the present utility model below, but design concept of the present utility model is not limited to this, all insubstantial modifications of utilizing this design that the utility model is made also all fall within the protection domain of the present utility model.
Claims (10)
1. model helicopter, comprise body, be provided with main shaft and hollow shaft in the described body, described main shaft is located in the described hollow shaft, described hollow shaft is provided with main screw, described main shaft is provided with secondary screw, it is characterized in that, be provided with electronic gyroscope in the described body, described main screw below is provided with pitch and steering wheel, and described pitch is connected by pull bar with steering wheel, described pitch is provided with the break-in dish, described break-in dish and described main screw interlock, described secondary screw top is provided with headstock cap, and described secondary screw and described headstock cap are by the Flexible Connector interlock.
2. model helicopter according to claim 1 is characterized in that, described Flexible Connector is made as spring or cushion rubber.
3. model helicopter according to claim 1, it is characterized in that, described body comprises frame, is located at Power Component, steering assembly, the two oar rotary components in the frame and the electronic building brick that can receive external signal, described Power Component drives described pair of oar rotary components, described electronic building brick is controlled described Power Component and steering assembly, described pair of oar rotary components of described steering assembly control.
4. model helicopter according to claim 3, it is characterized in that, described Power Component comprises battery, motor, motor gear, master gear, pinion, described battery provides power for described motor, described motor links to each other with motor gear, CD-ROM drive motor gear, described motor gear mesh with master gear and pinion respectively.
5. model helicopter according to claim 4 is characterized in that, described motor adopts high-effect brush motor, is made as two.
6. model helicopter according to claim 3 is characterized in that, described steering assembly comprises two described steering wheels, the pitch that links to each other with steering wheel, is located at the break-in dish on the pitch.
7. model helicopter according to claim 6 is characterized in that, described break-in dish is provided with connecting rod, and described break-in dish is by connecting rod and described main screw interlock.
8. model helicopter according to claim 3 is characterized in that, the described pair of oar rotary components comprise described hollow shaft, described main shaft, be located at main screw on the hollow shaft, be located at secondary screw and headstock cap on the main shaft.
9. model helicopter according to claim 8 is characterized in that, described main screw and described secondary screw comprise blade, blade folder.
10. according to claim 1 to 9 each described model helicopters, it is characterized in that, described main screw and described secondary screw are the symmetrical airfoil screw that load is light, lift is strong.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220339310 CN202682789U (en) | 2012-07-13 | 2012-07-13 | Model helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201220339310 CN202682789U (en) | 2012-07-13 | 2012-07-13 | Model helicopter |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202682789U true CN202682789U (en) | 2013-01-23 |
Family
ID=47538467
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201220339310 Expired - Lifetime CN202682789U (en) | 2012-07-13 | 2012-07-13 | Model helicopter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202682789U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102743883A (en) * | 2012-07-13 | 2012-10-24 | 罗之洪 | Model airplane helicopter |
| CN106621383A (en) * | 2015-11-04 | 2017-05-10 | 许美兰 | Aircraft stable flying system |
| CN108327899A (en) * | 2018-01-29 | 2018-07-27 | 陈铭 | A kind of coaxial double-oar helicopter rotor method for arranging and coaxial double-oar helicopter up and down |
-
2012
- 2012-07-13 CN CN 201220339310 patent/CN202682789U/en not_active Expired - Lifetime
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102743883A (en) * | 2012-07-13 | 2012-10-24 | 罗之洪 | Model airplane helicopter |
| CN102743883B (en) * | 2012-07-13 | 2014-12-10 | 罗之洪 | Model airplane helicopter |
| CN106621383A (en) * | 2015-11-04 | 2017-05-10 | 许美兰 | Aircraft stable flying system |
| CN108327899A (en) * | 2018-01-29 | 2018-07-27 | 陈铭 | A kind of coaxial double-oar helicopter rotor method for arranging and coaxial double-oar helicopter up and down |
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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: GUANGZHOU WALKERA TECHNOLOGY Co.,Ltd. Assignor: Luo Zhihong Contract record no.: 2013440000619 Denomination of utility model: Model airplane helicopter Granted publication date: 20130123 License type: Exclusive License Record date: 20131231 |
|
| LICC | Enforcement, change and cancellation of record of contracts on the licence for exploitation of a patent or utility model | ||
| EE01 | Entry into force of recordation of patent licensing contract |
Assignee: GUANGZHOU WALKERA TECHNOLOGY Co.,Ltd. Assignor: Luo Zhihong Contract record no.: 2013440000619 Denomination of utility model: Model airplane helicopter Granted publication date: 20130123 License type: Exclusive License Record date: 20131231 |
|
| LICC | Enforcement, change and cancellation of record of contracts on the licence for exploitation of a patent or utility model | ||
| ASS | Succession or assignment of patent right |
Owner name: GUANGZHOU WALKERA TECHNOLOGY CO., LTD. Free format text: FORMER OWNER: LUO ZHIHONG Effective date: 20150807 |
|
| C41 | Transfer of patent application or patent right or utility model | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20150807 Address after: 511453 Nansha District, Guangzhou, Tung Chung Town, Tai Po Industrial Zone, Guangzhou Walkera Technology Co Ltd, Patentee after: GUANGZHOU WALKERA TECHNOLOGY Co.,Ltd. Address before: Guangdong city of Guangzhou province Panyu District 511430 Guangzhou Walkera Technology Co Ltd yuwotou Taishi Industrial Zone Patentee before: Luo Zhihong |
|
| CP03 | Change of name, title or address |
Address after: 511475 Nansha District, Guangdong, Tung Chung Town, Tai Po Industrial Zone Patentee after: GUANGZHOU WALKERA TECHNOLOGY Co.,Ltd. Address before: 511453 Nansha District, Guangzhou, Tung Chung Town, Tai Po Industrial Zone, Guangzhou Walkera Technology Co Ltd, Patentee before: GUANGZHOU WALKERA TECHNOLOGY Co.,Ltd. |
|
| CP03 | Change of name, title or address | ||
| CX01 | Expiry of patent term |
Granted publication date: 20130123 |
|
| CX01 | Expiry of patent term |