CN201101893Y - Telecontrolled model helicopter - Google Patents
Telecontrolled model helicopter Download PDFInfo
- Publication number
- CN201101893Y CN201101893Y CNU2007200865223U CN200720086522U CN201101893Y CN 201101893 Y CN201101893 Y CN 201101893Y CN U2007200865223 U CNU2007200865223 U CN U2007200865223U CN 200720086522 U CN200720086522 U CN 200720086522U CN 201101893 Y CN201101893 Y CN 201101893Y
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- China
- Prior art keywords
- advance
- power component
- oar
- retreat
- remote control
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- Expired - Fee Related
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- 230000002457 bidirectional effect Effects 0.000 abstract 2
- 239000000725 suspension Substances 0.000 abstract 1
- 230000009467 reduction Effects 0.000 description 15
- 230000007704 transition Effects 0.000 description 7
- 239000007787 solid Substances 0.000 description 5
- 230000008859 change Effects 0.000 description 4
- 230000000694 effects Effects 0.000 description 2
- 241000220317 Rosa Species 0.000 description 1
- 230000003139 buffering effect Effects 0.000 description 1
- 238000000354 decomposition reaction Methods 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000005484 gravity Effects 0.000 description 1
- 230000001771 impaired effect Effects 0.000 description 1
- 230000035515 penetration Effects 0.000 description 1
- 230000000737 periodic effect Effects 0.000 description 1
- 230000001360 synchronised effect Effects 0.000 description 1
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Abstract
The utility model relates to a remote controlled model helicopter which comprises a balancing pole, a rotor wing, a connection shaft, a driving motor, a supporting frame, an engine frame, a punched tape suspension rod, a steering power subassembly, an advance and retreat power subassembly and an airplane, wherein, a crashworthy spring is arranged below the rotor wing; the steering power subassembly and the advance and retreat power subassembly are respectively installed at the front part and the tail part of the airframe; the bidirectional oars of the steering power subassembly and the advance and retreat power subassembly can be over two oars and include two oars. The oar of the advance and retreat power subassembly can be a bidirectional oar or a monodirectional oar. The engine frame can adopt a blowmobile type or an airplane wheel type. The remote controlled model helicopter provided according to the utility model can be used for two or more persons to fight in the sky, the entertainment property is strong, the operation is simple, the control is easy, the flying is stable, the price is cheap, and popularization and generalization are easy.
Description
One, technical field
The utility model relates to a kind of remote control model helicopter, the especially a kind of remote control model helicopter that can aloft fight.
Two, background technology
The principle of existing coaxial double-rotary wing remote control model helicopter is to utilize two pairs of rotors to make positive and reverse return then generation lift variation and direction change, and when two pairs of rotors quickened simultaneously or slow down, helicopter rose or descends.When a pair of rotor slowed down, helicopter just turned to.Positive rotor is made periodic angle of attack variation under the effect of pitch, generation is advanced or retreated thus, and the left side is moved or the right side is moved.Existing coaxial double-rotary wing remote control model helicopter ubiquity is following not enough: the amusement unicity; Model plane are strongly professional, regulate complexity, generally control well without the very difficult operation of the people of training; Use expensive device, cost an arm and a leg.
Three, utility model content
The purpose of this utility model is to provide a kind of and can aloft fights, and has stability and remote control model helicopter simple to operate.
For achieving the above object, the utility model adopts following technical scheme: a kind of remote control model helicopter comprises balancing pole, rotor, connecting axle, drive motors, support, frame, paper tape peg, direction Power Component, advance and retreat Power Component, fuselage.
Wherein, crashproof spring is housed under the rotor; Direction Power Component and advance and retreat Power Component are installed in the front portion and the afterbody of fuselage respectively; Drive motors drives the reverse drive train of reduction gears and drives positive rotor and the coaxial oppositely speed rotation together of the derotation wing; The paper tape peg is rack-mount, stretches out from afterbody.Described direction Power Component can be installed towards a left side or towards the right side; The two-way oar of direction Power Component and advance and retreat Power Component can be more than the two leaf oars, contains two leaf oars; The oar of advance and retreat Power Component can be two-way oar or unidirectional oar; Frame can adopt sledge form or wheel form.
Described crashproof spring is installed under positive rotor head and the anti-rotor head.Just changeing crashproof spring 5 with positive rotor head 3 with just changeing crashproof spring fixed column 6 and connect by just changeing crashproof spring staple 4; The crashproof spring 10 that reverses connects by the crashproof spring staple 9 of counter-rotating with anti-rotor head 8 and the crashproof spring fixed column 12 of counter-rotating; Balancing pole is installed in the rotor head top, and links with last rotor head; Described fuselage can be designed to the shape of needs.
Described drive motors is contained in upper bracket platform front upper part, the reverse drive under drive gear is assembled between upper bracket and the lower carriage, drive motors gear and the engagement of counter-rotating transition reduction gearing, counter-rotating transition reduction gearing is through counter-rotating deceleration gear wheel deceleration rear drive counter-rotating hollow shaft, and the counter-rotating hollow shaft drives anti-rotor head despining; Counter-rotating transition reduction gearing is crossed the reduction gearing engagement with just turning over, and is just turning over to cross reduction gearing and just changeing solid shafting through just changeing deceleration gear wheel deceleration rear drive, is just changeing solid shafting and is driving positive rotor head positive rotation.
The utility model compared with prior art has the following advantages:
1, because the direction Power Component is contained in fore-body, the advance and retreat Power Component is contained in afterbody, has divided the weight of model of an airplane front and rear greatly, makes the center of gravity of the model of an airplane adjust easily, and aircraft flight stability is better, and controls flexibly.Simultaneously also widen the space of aircraft appearance design, made the model of an airplane can adopt the fuselage cover of emulation, strengthened the fidelity of aircraft outward appearance.
2, because crashproof spring has been installed under rotor, when the rotor of single motor synchronous driving double-vane reverse rotation bumps, plays the effect of buffering, thereby protected rotor and gear not to be damaged.
3, realize that two pairs of coaxial reverse speed together of rotor are to changeing owing to only drive reduction gearing with a drive motors, well overcome the disorderly problem of pendulum of opposing torque imbalance, fuselage, by the remote control adjustment motor speed, function such as realize the lifting of this helicopter and hover makes aircraft that the good lifting and the stability of hovering be arranged.
4, regulate by the two-way speed of remote control control fore-body direction motor, the two-way oar rotating of direction driven by motor direction produce left thrust or pulling force to the right, simply realize the control of helicopter direction.
5, regulate by the two-way speed of control afterbody advance and retreat motor, drive the two-way oar of advance and retreat and produce pulling force upwards or downward thrust, make body tilt forward or backward, make rotor obtain forward or backward component, also simply realize flying before the aircraft and after the function that flies.Make that airplane operation control is very simple, do not need artificial adjusting, can also solve like product and realize the high price that this function is brought because of adopting expensive devices such as steering wheel.
Remote control model helicopter provided by the utility model has just in time remedied the deficiency of like product on the market, it has three big characteristics: 1. not only can be for sole flight's amusement, can also fight in the air simultaneously for two or many people, rule is: by the aircraft of remote control oneself, destroy the paper tape that adversary's airplane tail group is hung with the rotor of aircraft, after fighting end, according to remaining how many decision triumph sides of paper tape; 2. this aircraft flight good stability, simple to operate, easy control, can finish vertical lift, hover, turn to, advance, retreat etc. a series of actions.General layman sees that specification need not trained guidance and exercise just can independently be controlled its flight.3. price is low, and good cost performance is arranged, but penetration and promotion.
Four, description of drawings
Fig. 1 is a remote control model helicopter structural representation described in the utility model.
Fig. 2 is the three-dimensional decomposition texture schematic diagram of remote control model helicopter described in the utility model.
Five, the specific embodiment
The utility model is described in further detail below in conjunction with accompanying drawing embodiment:
Contrast Fig. 2, remote control model helicopter described in the utility model is by balancing pole 1, positive rotor 2, positive rotor head 3, just changeing crashproof spring staple 4, just changeing crashproof spring 5, just changeing crashproof spring fixed column 6, the derotation wing 7, anti-rotor head 8, crashproof spring staple 9 reverses, crashproof spring 10 reverses, just changeing solid shafting 11, crashproof spring fixed column 12 reverses, counter-rotating hollow shaft 13, drive motors 14, drive motors gear 15, upper bracket 16, counter-rotating transition reduction gearing 17, counter-rotating deceleration gear wheel 18, just turning over and crossing reduction gearing 19, just changeing deceleration gear wheel 20, lower carriage 21, frame 22, paper tape peg 23, direction Power Component 24, direction motor 25, duct housing 26, the two-way oar 27 of direction, advance and retreat Power Component 28, the two-way oar 29 of advancing and retreat, advance and retreat motor 30, fuselage 31 parts such as grade constitute.
Contrast Fig. 2 illustrates the concrete connected mode between each parts:
Among Fig. 2, direction Power Component 24 is made of direction motor 25, duct housing 26, the two-way oar 27 of direction, is installed in the front portion of fuselage 31.Regulate by the two-way speed of remote control control fore-body direction motor, the two-way oar rotating of direction driven by motor direction produce left thrust or pulling force to the right, realize the control of helicopter direction.
Among Fig. 2, advance and retreat Power Component 28 is made of the two-way oar 29 of advance and retreat, advance and retreat motor 30, is contained in the afterbody of fuselage 31.Regulate by the two-way speed of control afterbody advance and retreat motor, drive the two-way oar of advance and retreat and produce pulling force upwards or downward thrust, make body tilt forward or backward, make rotor obtain forward or backward component, realize flying before the aircraft and after the function that flies.
Among Fig. 2, just changeing crashproof spring 5 with positive rotor head 3 with just changeing crashproof spring fixed column 6 and connect by just changeing crashproof spring staple 4; The crashproof spring 10 that reverses connects by the crashproof spring staple 9 of counter-rotating with anti-rotor head 8 and the crashproof spring fixed column 12 of counter-rotating; By above-mentioned connection, make and play buffer protection rotor and the not impaired effect of gear when rotor bumps.
Among Fig. 2, counter-rotating transition reduction gearing 17 engagements between drive motors gear 15 and upper bracket 16 and the lower carriage 21, counter-rotating transition reduction gearing 17 and 18 engagements of counter-rotating deceleration gear wheel, counter-rotating deceleration gear wheel 18 and counter-rotating hollow shaft 13 bottom close-coupled, counter-rotating hollow shaft 13 tops connect by the crashproof spring staple 9 of counter-rotating with the crashproof spring fixed column 12 of counter-rotating, the crashproof spring 10 of counter-rotating, anti-rotor head 8; Counter-rotating transition reduction gearing 17 is crossed reduction gearing 19 engagements with just turning over, just turning over and crossing reduction gearing 19 and just change 20 engagements of deceleration gear wheel, just changeing deceleration gear wheel 20 and just changeing solid shafting 11 bottom close-coupled, just changeing solid shafting 11 tops with just change crashproof spring fixed column 6, just change crashproof spring 5, just rotor head 3 connects by just changeing crashproof spring staple 4.By above-mentioned connection, realize drive motors drive the reverse drive reduction gearing make positive and negative two pairs of rotors coaxial oppositely with speed to changeing, by the remote control adjustment motor speed, function such as realize the lifting of this helicopter and hover.
Claims (6)
1, a kind of remote control model helicopter, comprise balancing pole, rotor, connecting axle, drive motors, support, frame, paper tape peg, direction Power Component, advance and retreat Power Component, fuselage, it is characterized in that: described direction Power Component and advance and retreat Power Component are installed in the front portion and the afterbody of fuselage respectively, and crashproof spring is housed under the described rotor.
2, remote control model helicopter according to claim 1, it is characterized in that: described crashproof spring is installed under positive rotor head and the anti-rotor head, is just changeing crashproof spring (5) with positive rotor head (3) with just changeing crashproof spring fixed column (6) and connect by just changeing crashproof spring staple (4); The crashproof spring (10) that reverses connects by the crashproof spring staple of counter-rotating (9) with anti-rotor head (8) and the crashproof spring fixed column of counter-rotating (12).
3, remote control model helicopter according to claim 1 is characterized in that: described direction Power Component can be installed towards a left side or towards the right side.
4, remote control model helicopter according to claim 1 is characterized in that: the two-way oar of direction Power Component and advance and retreat Power Component can be more than the two leaf oars, contains two leaf oars.
5, remote control model helicopter according to claim 1 is characterized in that: the oar of advance and retreat Power Component can be two-way oar or unidirectional oar.
6, remote control model helicopter according to claim 1 is characterized in that: frame can adopt sledge form or wheel form.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNU2007200865223U CN201101893Y (en) | 2007-08-14 | 2007-08-14 | Telecontrolled model helicopter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNU2007200865223U CN201101893Y (en) | 2007-08-14 | 2007-08-14 | Telecontrolled model helicopter |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201101893Y true CN201101893Y (en) | 2008-08-20 |
Family
ID=39948911
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNU2007200865223U Expired - Fee Related CN201101893Y (en) | 2007-08-14 | 2007-08-14 | Telecontrolled model helicopter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201101893Y (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101912688A (en) * | 2010-08-13 | 2010-12-15 | 倪康汉 | Linkage for remote control coaxial twin-screw reversal helicopter model |
| CN104524785A (en) * | 2014-12-05 | 2015-04-22 | 张立 | Connection device for tail rotor of helicopter model |
| CN109304041A (en) * | 2018-11-14 | 2019-02-05 | 郑岚心 | A kind of model plane power component for preventing from fractureing when collision |
-
2007
- 2007-08-14 CN CNU2007200865223U patent/CN201101893Y/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101912688A (en) * | 2010-08-13 | 2010-12-15 | 倪康汉 | Linkage for remote control coaxial twin-screw reversal helicopter model |
| CN104524785A (en) * | 2014-12-05 | 2015-04-22 | 张立 | Connection device for tail rotor of helicopter model |
| CN109304041A (en) * | 2018-11-14 | 2019-02-05 | 郑岚心 | A kind of model plane power component for preventing from fractureing when collision |
| CN109304041B (en) * | 2018-11-14 | 2019-08-27 | 郑岚心 | A kind of model plane power component for preventing from fractureing when collision |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20080820 Termination date: 20130814 |