CN102755750A - Model airplane helicopter - Google Patents
Model airplane helicopter Download PDFInfo
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- CN102755750A CN102755750A CN2012102424127A CN201210242412A CN102755750A CN 102755750 A CN102755750 A CN 102755750A CN 2012102424127 A CN2012102424127 A CN 2012102424127A CN 201210242412 A CN201210242412 A CN 201210242412A CN 102755750 A CN102755750 A CN 102755750A
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Abstract
The invention relates to a model airplane helicopter. The model airplane helicopter comprises an airframe, wherein the airframe is internally provided with a main shaft and a hollow shaft, and the main shaft is arranged in the hollow shaft; the hollow shaft is provided with a main screw propeller, and the main shaft is provided with a subsidiary screw propeller; the airframe is internally provided with an electronic gyroscope, and a swashplate and a steering engine are arranged below the main screw propeller; the swashplate and the steering engine are connected through a pull rod, the swashplate is provided with a turning disc, and the turning disc is connected with the main screw propeller through a first connecting rod; an upper disc and a lower disc are arranged above the main screw propeller, and the lower disc is arranged on the hollow shaft and is connected with the main screw propeller through a second connecting rod; the upper disc is arranged on the main shaft and is connected with the subsidiary screw propeller through a third connecting rod, and the main screw propeller and the subsidiary screw propeller are composed of horizontal shafts, blade clamps, blades, rotor wing heads and the like, and the blade clamps are arranged on the horizontal shafts and can rotate relative to the horizontal shafts. The model airplane helicopter provided by the invention has no balanced rod, adopts electronic and automatic control on balance, can lighten load, and can finish eight motions.
Description
Technical field
The present invention 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 more common have a 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 is one group of screw mostly, the wind loading rating of outdoor flight a little less than, the green hand is restive, causes the damage or the damage of model helicopter easily.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 through balancing pole.Yet when model helicopter received 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, causes the damage or the damage of model helicopter easily.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 bigger influence, is unfavorable for flight.
In addition; In view of model helicopter is not easy control flight; The flare maneuver of most model helicopter is too simple, and operating pattern is single, such as about can only accomplishing, all around several actions of tilting; For some airplane hobbyists, lack interest and challenge, do not meet the demand of market diversification.
Summary of the invention
In order to overcome the deficiency of prior art, the present invention provides a kind of coaxial pair of oar, no balancing pole, adopts electronics to control balance automatically, and load reduction can be accomplished eight actions, has more interesting model helicopter.
The technical solution adopted for the present invention to solve the technical problems is: a kind of model helicopter, comprise body, and be provided with main shaft and hollow shaft in the said body; Said main shaft is located in the said hollow shaft, and said hollow shaft is provided with main screw, and said main shaft is provided with secondary screw; Be provided with electronic gyroscope in the said body, said main screw below is provided with pitch and steering wheel, and said pitch is connected through pull bar with steering wheel; Said pitch is provided with the break-in dish, and said break-in dish is through head rod and said main screw interlock, and said main screw top is provided with dish and lower wall; Said lower wall is located on the hollow shaft, and through second connecting rod and said main screw interlock, the said dish of going up is placed on the hollow shaft; Through the 3rd connecting rod and said secondary screw interlock; Said main screw and said secondary screw are made up of transverse axis, blade folder, blade, rotor head, and said blade is located on the transverse axis, and can relatively rotate around transverse axis.
The present invention is through being provided with electronic gyroscope in body; It can detect the flight attitude of model helicopter automatically and control helicopter automatically; When model helicopter receives extraneous larger interference (such as strong wind or collision); Deviation appears in flare maneuver, and electronic gyroscope can produce induction immediately, handles said steering wheel then and fascinates; The pitch that links to each other with steering wheel through pull bar fascinates immediately; Be located at break-in dish on the pitch simultaneously, with the main screw of break-in dish interlock, with the lower wall of main screw interlock, be located at going up dish, also fascinate synchronously on the lower wall with the secondary screw of last dish interlock, thereby make whole helicopter change incline direction, correct the action deviation.In whole adjustment process; Because main screw and secondary screw fascinate synchronously; The Plane of rotation of main screw and the Plane of rotation of secondary screw keep fascinating synchronously always; So model helicopter can ensure having a smooth flight property when correcting the action deviation, be easy to control, improves the wind loading rating of outdoor flight greatly.No longer need simultaneously balancing pole, model helicopter load reduction.
When model helicopter need be done tilting action; Handling said steering wheel fascinates; The pitch that links to each other with steering wheel through pull bar fascinates immediately; Be located at break-in dish on the pitch simultaneously, with the main screw of break-in dish interlock, with the lower wall of main screw interlock, be located at going up dish, also fascinate synchronously on the lower wall with the secondary screw of last dish interlock, thereby make whole helicopter change incline direction, accomplish tilting action.Wherein accomplish fascinating of tilting action compare the adjustment balance the amplitude of fascinating bigger, the adjustment equilibrium process only be to finely tune through electronic gyroscope.
In addition, the airplane hobbyist can handle steering wheel and rotate to an angle around transverse axis through connecting rod control main screw and the monolateral blade folder of secondary screw, and monolateral blade folder is after transverse axis rotates to an angle; Monolateral blade also and then rotates to an angle; Cause the bilateral vane stress area of screw different, and then cause a direction stressed bigger, thereby whole model helicopter is turned to; The action of accomplishing or turning right has more interest.
In one embodiment; Said body comprises frame, is located at Power Component, steering assembly, two oar rotary components in the frame and the electronic building brick that can receive external signal; Said Power Component drives said pair of oar rotary components; Said electronic building brick is controlled said Power Component and steering assembly, said pair of oar rotary components of said steering assembly control.
In one embodiment, said 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 implementation, said motor adopts high-effect brush motor, is made as two.Adopt the double motor power drive, powerful motivation can be provided, promote the rotating speed of helicopter flight, strengthen the helicopter wind loading rating.
In one embodiment, said steering assembly comprises two said steering wheels, said pitch, said break-in dish, is provided with steering ball in the said pitch, and said break-in dish is socketed on the said steering ball.Said pitch is succinct cross plate structure, pushes away one through two steering wheels one and draws in capable fascinating.Said pitch drives the break-in dish through steering ball and fascinates.
In one embodiment, the said pair of oar rotary components comprise said hollow shaft, said main shaft, be located at main screw and lower wall on the hollow shaft, be placed on the hollow shaft on coil, be located at the secondary screw on the main shaft.Said hollow shaft is connected with said master gear and with the master gear rotation, said main shaft is connected with said pinion and rotates with pinion.Said break-in dish, main screw, lower wall rotate with hollow shaft, and said dish, the secondary screw gone up is with main axis rotation.Need to prove that said pitch only fascinates through steering wheel, does not rotate with hollow shaft.
In one embodiment, said pair of oar rotary components is provided with fixed block and fixed bar, makes can not swing along with the rotation of screw with the break-in dish of main screw interlock and lower wall and with the last dish of secondary screw interlock, and structure is fastening.
In a preferred implementation, said main screw and said 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.
In a preferred implementation, said blade folder is the metal blade folder, and said rotor head is the metal rotor head, strengthens the fastness of helicopter, guarantees that flight safety is reliable.
In one embodiment, said electronic building brick comprises electronic gyroscope, and said electronic building brick is handled said steering wheel through electronic gyroscope and controlled said steering assembly.
The invention has the beneficial effects as follows: the present invention is through being provided with electronic gyroscope in body; It can detect the flight attitude of model helicopter automatically and control helicopter automatically; When model helicopter receives extraneous larger interference (such as strong wind or collision); Deviation appears in flare maneuver, and electronic gyroscope can produce induction immediately, handles said steering wheel then and fascinates; The pitch that links to each other with steering wheel through pull bar fascinates immediately; Be located at break-in dish on the pitch simultaneously, with the main screw of break-in dish interlock, with the lower wall of main screw interlock, be located at going up dish, also fascinate synchronously on the lower wall with the secondary screw of last dish interlock, thereby make whole helicopter change incline direction, correct the action deviation.In whole adjustment process; Because main screw and secondary screw fascinate synchronously; The Plane of rotation of main screw and the Plane of rotation of secondary screw keep fascinating synchronously always; So model helicopter can ensure having a smooth flight property when correcting the action deviation, be easy to control, improves the wind loading rating of outdoor flight greatly.No longer need simultaneously balancing pole, model helicopter load reduction.
In addition, the airplane hobbyist can handle steering wheel and rotate to an angle around transverse axis through connecting rod control main screw and the monolateral blade folder of secondary screw, and monolateral blade folder is after transverse axis rotates to an angle; Monolateral blade also and then rotates to an angle; Cause the bilateral vane stress area of screw different, and then cause a direction stressed bigger, thereby whole model helicopter is turned to; The action of accomplishing or turning right has more interest.
Description of drawings
Fig. 1 is the complete machine planar structure sketch map of one embodiment of the invention.
Fig. 2 is the schematic perspective view of part-structure in the one embodiment of the invention.
Fig. 3 is the decomposing schematic representation of part-structure in the one embodiment of the invention.
Omitted among the figure and the irrelevant miscellaneous part of key points in design of the present invention.
The specific embodiment
Below in conjunction with accompanying drawing and specific embodiment, the present invention is explained further details.
Like Fig. 1, Fig. 2, shown in Figure 3, a kind of model helicopter 100 of the present invention comprises body; Be provided with main shaft 101 and hollow shaft 102 in the said body, said main shaft 101 is located in the said hollow shaft 102, and said hollow shaft 102 is provided with main screw 103; Said main shaft 101 is provided with secondary screw 104, is provided with the electronic gyroscope (not shown) in the said body, and said main screw 103 belows are provided with pitch 105 and steering wheel (not shown); In the present embodiment, said steering wheel is made as two, and said pitch 105 is connected through pull bar 106 with steering wheel; Said pitch 105 is provided with break-in dish 108; Said break-in dish 108 is through head rod 109 and said main screw 103 interlocks, and said main screw 103 tops are provided with dish 111 and lower wall 110, and said lower wall 110 is located on the hollow shaft 102; Through second connecting rod 112 and said main screw 103 interlocks; The said dish 111 of going up is placed on the hollow shaft 102, and through the 3rd connecting rod 113 and said secondary screw 104 interlocks, said main screw 103 is made up of transverse axis 114, blade folder 115, blade 116, rotor head 117 with said secondary screw 104; Said blade folder 115 is located on the transverse axis 114, and can relatively rotate around transverse axis 114.
The present invention is through being provided with electronic gyroscope in body; It can detect the flight attitude of model helicopter automatically and control helicopter automatically; When model helicopter receives extraneous larger interference (such as strong wind or collision); Deviation appears in flare maneuver, and electronic gyroscope can produce induction immediately, handles said steering wheel then and fascinates; The pitch 105 that links to each other with steering wheel through pull bar 106 fascinates immediately; Be located at break-in dish 108 on the pitch 105 simultaneously, with the main screw 103 of break-in dish 108 interlocks, with the lower wall 110 of main screw 103 interlocks, be located at going up dish 111, also fascinate synchronously on the lower wall 110 with the secondary screw 104 of last dish 111 interlocks, thereby make whole helicopter change incline direction, correct the action deviation.In whole adjustment process; Because main screw 103 fascinates with secondary screw 104 synchronously; The Plane of rotation of the Plane of rotation of main screw 103 and secondary screw 104 keeps fascinating synchronously always; So model helicopter can ensure having a smooth flight property when correcting the action deviation, be easy to control, improves the wind loading rating of outdoor flight greatly.No longer need simultaneously balancing pole, model helicopter load reduction.
When model helicopter need be done tilting action; Handling said steering wheel fascinates; The pitch 105 that links to each other with steering wheel through pull bar 106 fascinates immediately; Be located at break-in dish 108 on the pitch 105 simultaneously, with the main screw 103 of break-in dish 108 interlocks, with the lower wall 110 of main screw 103 interlocks, be located at going up dish 111, also fascinate synchronously on the lower wall 110 with the secondary screw 104 of last dish 111 interlocks, thereby make whole helicopter change incline direction, accomplish tilting action.Wherein accomplish fascinating of tilting action compare the adjustment balance the amplitude of fascinating bigger, the adjustment equilibrium process only be to finely tune through electronic gyroscope.
In addition, the airplane hobbyist can handle steering wheel and rotate to an angle around transverse axis 114 through the monolateral blades folder of connecting rod control main screw 103 and secondary screw 104 115, and monolateral blade folder 115 is after transverse axis 114 rotates to an angle; Monolateral blade 116 also and then rotates to an angle; Cause the bilateral vane stress area of screw different, and then cause a direction stressed bigger, thereby whole model helicopter is turned to; The action of accomplishing or turning right has more interest.
In the present embodiment; Said body comprises frame, is located at Power Component, steering assembly, two oar rotary components in the frame and the electronic building brick that can receive external signal; Said Power Component drives said pair of oar rotary components; Said electronic building brick is controlled said Power Component and steering assembly, said pair of oar rotary components of said steering assembly control.
As shown in Figure 3, in the present embodiment, said Power Component comprises battery (not shown), motor 118, motor gear 119, master gear 120, pinion 121.Said motor 118 adopts high-effect brush motor, is made as two, and motor gear 119 also is made as two simultaneously.Motor 118 links to each other with motor gear 119, and CD-ROM drive motor gear 119, motor gear 119 mesh with master gear 120 and pinion 121 respectively.Adopt the double motor power drive, powerful motivation can be provided, promote the rotating speed of helicopter flight, strengthen the helicopter wind loading rating.
Like Fig. 2, shown in Figure 3, in the present embodiment, said steering assembly comprises two steering wheels, the pitch 105 that links to each other with steering wheel, break-in dish 108, is provided with steering ball 107 in the said pitch 105, and said break-in dish 108 is socketed on the said steering ball 107.Said pitch 105 is succinct cross plate structure, pushes away one through two steering wheels one and draws in capable fascinating.Said pitch 105 drives break-in dish 108 through steering ball 107 and fascinates.
Like Fig. 2, shown in Figure 3, in the present embodiment, the said pair of oar rotary components comprise hollow shaft 102, main shaft 101, be located at main screw 103 and lower wall 110 on the hollow shaft 102, be placed in going up dish 111, be located at the secondary screw 104 on the main shaft 101 on the hollow shaft 102.Said hollow shaft 102 is connected with said master gear 120 and with master gear 120 rotations, said main shaft 101 is connected with said pinion 121 and rotates with pinion 121.Said break-in dish 108, main screw 103, lower wall 110 are with hollow shaft 102 rotations, and said dish 111, the secondary screw 104 gone up is with main shaft 101 rotations.Need to prove that 105 of said pitches fascinate through steering wheel, not with hollow shaft 102 rotations.
Like Fig. 2, shown in Figure 3, in the present embodiment, said pair of oar rotary components is provided with fixed block and fixed bar.Said main screw 103 below hollow shafts 102 are provided with first fixed block 122, through first fixed bar 123 and said break-in dish 108 interlocks.Said main screw 103 top hollow shafts 102 are provided with second fixed block 124, through second fixed bar 125 and said lower wall 110 interlocks.Said secondary screw 104 below main shafts 101 are provided with the 3rd fixed block 126, through the 3rd fixed bar 127 and said dish 111 interlocks of going up.Like this with regard to make with the break-in dish 108 of main screw 103 interlocks and lower wall 110 and with the going up dish 111 and can not swing of secondary screw 104 interlocks along with the rotation of screw, structure is fastening.
As shown in Figure 3, in the present embodiment, said main screw 103 is the symmetrical airfoil screw that load is light, lift is strong with said secondary screw 104, can promote the rotating speed of helicopter flight, strengthens the helicopter wind loading rating.Said blade folder 115 is the metal blade folder, and said rotor head 117 is the metal rotor head, strengthens the fastness of helicopter, guarantees that flight safety is reliable.
In the present embodiment, said electronic building brick comprises electronic gyroscope, and said electronic building brick is handled said steering wheel through electronic gyroscope and controlled said steering assembly.
More than be merely the preferred embodiments of the present invention, but design concept of the present invention is not limited thereto, allly utilizes this design, also all fall within protection scope of the present invention the insubstantial modifications that the present invention makes.
Claims (10)
1. a model helicopter comprises body, is provided with main shaft and hollow shaft in the said body; Said main shaft is located in the said hollow shaft, and said hollow shaft is provided with main screw, and said main shaft is provided with secondary screw; It is characterized in that, be provided with electronic gyroscope in the said body, said main screw below is provided with pitch and steering wheel; Said pitch is connected through pull bar with steering wheel, and said pitch is provided with the break-in dish, and said break-in dish is through head rod and said main screw interlock; Said main screw top is provided with dish and lower wall, and said lower wall is located on the hollow shaft, through second connecting rod and said main screw interlock; The said dish of going up is placed on the hollow shaft, and through the 3rd connecting rod and said secondary screw interlock, said main screw and said secondary screw are made up of transverse axis, blade folder, blade, rotor head; Said blade is located on the transverse axis, and can relatively rotate around transverse axis.
2. model helicopter according to claim 1; It is characterized in that; Said body comprises frame, is located at Power Component, steering assembly, two oar rotary components in the frame and the electronic building brick that can receive external signal; Said Power Component drives said pair of oar rotary components, and said electronic building brick is controlled said Power Component and steering assembly, said pair of oar rotary components of said steering assembly control.
3. model helicopter according to claim 2; It is characterized in that; Said Power Component comprises battery, motor, motor gear, master gear, pinion, and said battery is that said motor provides power, and said motor links to each other with motor gear; CD-ROM drive motor gear, said motor gear mesh with master gear and pinion respectively.
4. model helicopter according to claim 3 is characterized in that said motor adopts high-effect brush motor, is made as two.
5. model helicopter according to claim 2 is characterized in that, said steering assembly comprises said steering wheel, said pitch, said break-in dish, is provided with steering ball in the said pitch, and said break-in dish is socketed on the said steering ball.
6. model helicopter according to claim 2 is characterized in that, the said pair of oar rotary components comprise said hollow shaft, said main shaft, be located at main screw and lower wall on the hollow shaft, be placed on the hollow shaft on coil, be located at the secondary screw on the main shaft.
7. model helicopter according to claim 6 is characterized in that, said pair of oar rotary components is provided with fixed block and fixed bar.
8. model helicopter according to claim 1 is characterized in that, said main screw and said secondary screw are the symmetrical airfoil screw that load is light, lift is strong.
9. model helicopter according to claim 1 is characterized in that, said blade folder is the metal blade folder, and said rotor head is the metal rotor head.
10. according to each described model helicopter of claim 1 to 9, it is characterized in that said electronic building brick comprises said electronic gyroscope, said electronic building brick is handled said steering wheel through electronic gyroscope and is controlled said steering assembly.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210242412.7A CN102755750B (en) | 2012-07-13 | 2012-07-13 | Model airplane helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210242412.7A CN102755750B (en) | 2012-07-13 | 2012-07-13 | Model airplane helicopter |
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| Publication Number | Publication Date |
|---|---|
| CN102755750A true CN102755750A (en) | 2012-10-31 |
| CN102755750B CN102755750B (en) | 2014-12-10 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201210242412.7A Active CN102755750B (en) | 2012-07-13 | 2012-07-13 | Model airplane helicopter |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106540461A (en) * | 2015-09-20 | 2017-03-29 | 许美兰 | Model plane with integrated chip |
| CN106606872A (en) * | 2015-10-23 | 2017-05-03 | 许美兰 | A multi-stage decelerator model airplane |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2759542Y (en) * | 2005-01-24 | 2006-02-22 | 罗之洪 | Electromotive toy helicopter |
| CN2873279Y (en) * | 2005-09-21 | 2007-02-28 | 罗之洪 | Electric toy helicopter |
| CN201253484Y (en) * | 2008-08-15 | 2009-06-10 | 罗之洪 | Helicopter model |
| EP2394914A1 (en) * | 2010-06-12 | 2011-12-14 | Promark Sp. z o.o. | A rotorcraft with a coaxial rotor system |
| CN202666404U (en) * | 2012-07-13 | 2013-01-16 | 罗之洪 | Aeromodelling helicopter |
-
2012
- 2012-07-13 CN CN201210242412.7A patent/CN102755750B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2759542Y (en) * | 2005-01-24 | 2006-02-22 | 罗之洪 | Electromotive toy helicopter |
| CN2873279Y (en) * | 2005-09-21 | 2007-02-28 | 罗之洪 | Electric toy helicopter |
| CN201253484Y (en) * | 2008-08-15 | 2009-06-10 | 罗之洪 | Helicopter model |
| EP2394914A1 (en) * | 2010-06-12 | 2011-12-14 | Promark Sp. z o.o. | A rotorcraft with a coaxial rotor system |
| CN202666404U (en) * | 2012-07-13 | 2013-01-16 | 罗之洪 | Aeromodelling helicopter |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106540461A (en) * | 2015-09-20 | 2017-03-29 | 许美兰 | Model plane with integrated chip |
| CN106606872A (en) * | 2015-10-23 | 2017-05-03 | 许美兰 | A multi-stage decelerator model airplane |
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| Publication number | Publication date |
|---|---|
| CN102755750B (en) | 2014-12-10 |
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Owner name: GUANGZHOU WALKERA TECHNOLOGY CO., LTD. Free format text: FORMER OWNER: LUO ZHIHONG Effective date: 20150807 |
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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 |
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Address after: 511475 Nansha District, Guangdong, Tung Chung Town, Tai Po Industrial Zone Patentee after: Guangzhou city huakeer Polytron Technologies Inc 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. |