CN201124928Y - Power transmission system for aerocraft - Google Patents
Power transmission system for aerocraft Download PDFInfo
- Publication number
- CN201124928Y CN201124928Y CNU2007203052253U CN200720305225U CN201124928Y CN 201124928 Y CN201124928 Y CN 201124928Y CN U2007203052253 U CNU2007203052253 U CN U2007203052253U CN 200720305225 U CN200720305225 U CN 200720305225U CN 201124928 Y CN201124928 Y CN 201124928Y
- Authority
- CN
- China
- Prior art keywords
- aircraft
- fuselage
- main rotor
- fluted disc
- tail
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Fee Related
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Abstract
The utility model relates to a power transmission system for an aircraft, which is arranged inside the aircraft and is provided with a driving motor. A driving shaft is arranged on the driving motor, and a gear portion and a belt wheel portion are arranged on the driving shaft for respectively driving a fluted disc and a belt to drive a main rotor blade and a tail rotor blade to rotate. The power transmission system for the aircraft has simple structure.
Description
Technical field
The utility model relates to a kind of aircraft power drive system, refers to a kind of main rotor of simple mechanism drive aircraft and power drive system of tail rotor rotation of utilizing especially.
Background technology
Figure 2 shows that the aircraft power drive system of commonly using, aircraft 9 has a main rotor 92 in a fuselage 91 tops, and in addition in the tail tail rotor 93 that is pivoted, this main rotor 92 is articulated in the fuselage 91 with a rotating shaft 921.Be installed with a CD-ROM drive motor 94 in the fuselage 91, it has one and is the axle drive shaft 941 of dentation for first fluted disc 95 of driving one with main rotor 92 coaxial settings, this first fluted disc 95 drives main rotor 92 rotations with these axle drive shaft 941 engagements when rotating, one second fluted disc 96 and these first fluted disc, 95 coaxial being arranged in the fuselage 91, and when rotating, drive a driven gear 97 and rotate, 97 of this driven gears drive a drive belt 98, and it then drives tail rotor 93 rotations in the other end.
By said structure as seen, as desire the dismounting driving system and then must dismantle in regular turn or assemble at respective components, therefore must expend certain time and cost, and the utility model is promptly being simplified its driving system member, during with the reduction dismounting the time and the cost of palpus cost.
The utility model content
Main purpose of the present utility model is to solve the above problems and a kind of aircraft power drive system is provided, and it utilizes better simply transmission device to drive main rotor and tail rotor rotation, and makes aircraft comparatively simple and easy when dismounting, and cost is minimized.
For reaching aforementioned purpose, the utility model by the following technical solutions:
A kind of aircraft power drive system, this aircraft comprises fuselage, the side has main rotor thereon, has tail rotor in tail, and this main rotor is articulated in fuselage with rotating shaft, and coaxial in fuselage a fluted disc is set, it is characterized in that: the power drive system of this aircraft lies in fuselage and is fixed with a CD-ROM drive motor, it has an axle drive shaft, have a gear part and a belt wheel portion on this axle drive shaft, this gear part and the engagement of this fluted disc are for driving the main rotor rotation, and the then sheathed belt of belt wheel portion is for driving the tail rotor rotation.
The utility model has the advantages that: have the assembly of comparatively simplifying, because main rotor and tail rotor are only utilized a fluted disc and belt driven rotary simultaneously respectively, and must be not again through other assembly transmission, therefore on structure, can reduce weight, and also can reduce relatively in costs such as material and group upright man-hours, and also can finish more easily when the user must carry out dismounting to the assembly of power drive system, and the loss of the transmission power of aircraft power also can reduce with the simplification of assembly.
Description of drawings
Fig. 1 is a power drive system disposition plan of the present utility model.
Fig. 2 is a planar view of commonly using the aircraft power drive system.
The specific embodiment
See also Fig. 1, person shown in the figure is the selected example structure of the utility model, and this only for the usefulness of explanation, is not subjected to the restriction of this kind structure in patent application.
Present embodiment provides a kind of aircraft power drive system, mean cyclogyro in this described aircraft, it has a fuselage 1 as the skeleton of cyclogyro moulding and for fixing each spare part, this fuselage 1 top is provided with a main rotor 2, it is articulated in the front end of fuselage 1 with a upright rotating shaft 21, and this rotating shaft 21 is provided with the fluted disc 3 of a cross-drive near the articulated section of fuselage 1.
Fuselage 1 is fixed with a CD-ROM drive motor 4 between rotating shaft 21 and tail, it has an axle drive shaft 41 that is pivoted to fuselage 1 bottom direction, the leading portion of this axle drive shaft 41 is a belt wheel portion 411, it is a gear part 412 that its back segment is in close proximity to 411 in belt wheel portion, the tooth portion of the tooth portion of this gear part 412 and this rotating shaft 21 bottom fluted discs 3 is positive engagement, this belt wheel portion 411 is then for belt 5 of socket, and leather sheath 5 other ends then are connected in fuselage 1 afterbody for 6 rotations of interlock tail rotor.
By said structure and annexation thereof as seen, when CD-ROM drive motor 4 runnings, 41 of its axle drive shafts begin to rotate, this moment, 411 drives of belt wheel portion tail rotor 6 of being connected in belt 5 other ends of its leading portion rotated, and the gear part 412 of these axle drive shaft 41 back segments also drives the fluted disc 3 coaxial bonded assembly main rotors 2 with rotating shaft 21 bottoms simultaneously.
Therefore, be not difficult to find that via above-mentioned the utility model is compared to the power drive system of commonly using, it has the assembly of comparatively simplifying and main rotor 2 and tail rotor 6 is only utilized a fluted disc 3 and a belt 5 driven rotary simultaneously respectively, and must be not again through other assembly transmission, this shows on structure and can reduce weight, and also can reduce relatively in costs such as material and group upright man-hours, and also can finish more easily when the user must carry out dismounting for the assembly of power drive system, and the loss of the transmission power of aircraft power also can reduce with the simplification of assembly.
Claims (1)
1. aircraft power drive system, this aircraft comprises fuselage, the side has main rotor thereon, has tail rotor in tail, and this main rotor is articulated in fuselage with rotating shaft, and coaxial in fuselage a fluted disc is set, it is characterized in that: the power drive system of this aircraft lies in fuselage and is fixed with a CD-ROM drive motor, it has an axle drive shaft, have a gear part and a belt wheel portion on this axle drive shaft, this gear part and the engagement of this fluted disc are for driving the main rotor rotation, and the then sheathed belt of belt wheel portion is for driving the tail rotor rotation.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNU2007203052253U CN201124928Y (en) | 2007-11-23 | 2007-11-23 | Power transmission system for aerocraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNU2007203052253U CN201124928Y (en) | 2007-11-23 | 2007-11-23 | Power transmission system for aerocraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201124928Y true CN201124928Y (en) | 2008-10-01 |
Family
ID=39998344
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNU2007203052253U Expired - Fee Related CN201124928Y (en) | 2007-11-23 | 2007-11-23 | Power transmission system for aerocraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN201124928Y (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103818552A (en) * | 2013-12-17 | 2014-05-28 | 湖北易瓦特科技有限公司 | Transmission device of rotorcraft |
| CN104401482A (en) * | 2014-10-28 | 2015-03-11 | 燕山大学 | Fully-differential coaxial helicopter operating mechanism |
| CN104943868A (en) * | 2015-07-15 | 2015-09-30 | 合肥工业大学 | Transmission system device of light unmanned helicopter |
| CN108657448A (en) * | 2018-06-04 | 2018-10-16 | 北京海空行科技有限公司 | A kind of electronic coaxial unmanned helicopter transmission system |
-
2007
- 2007-11-23 CN CNU2007203052253U patent/CN201124928Y/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103818552A (en) * | 2013-12-17 | 2014-05-28 | 湖北易瓦特科技有限公司 | Transmission device of rotorcraft |
| CN104401482A (en) * | 2014-10-28 | 2015-03-11 | 燕山大学 | Fully-differential coaxial helicopter operating mechanism |
| CN104943868A (en) * | 2015-07-15 | 2015-09-30 | 合肥工业大学 | Transmission system device of light unmanned helicopter |
| CN108657448A (en) * | 2018-06-04 | 2018-10-16 | 北京海空行科技有限公司 | A kind of electronic coaxial unmanned helicopter transmission system |
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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: 20081001 Termination date: 20101123 |