CN204623849U - Duct engine installation and aircraft - Google Patents
Duct engine installation and aircraft Download PDFInfo
- Publication number
- CN204623849U CN204623849U CN201520235400.0U CN201520235400U CN204623849U CN 204623849 U CN204623849 U CN 204623849U CN 201520235400 U CN201520235400 U CN 201520235400U CN 204623849 U CN204623849 U CN 204623849U
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- CN
- China
- Prior art keywords
- duct
- metal ring
- engine installation
- circle wall
- rotor
- 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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- 238000009434 installation Methods 0.000 title claims abstract description 43
- 239000002184 metal Substances 0.000 claims abstract description 44
- 239000007769 metal material Substances 0.000 claims abstract description 18
- LENZDBCJOHFCAS-UHFFFAOYSA-N tris Chemical compound OCC(N)(CO)CO LENZDBCJOHFCAS-UHFFFAOYSA-N 0.000 claims description 6
- 238000007493 shaping process Methods 0.000 description 6
- 230000003116 impacting effect Effects 0.000 description 5
- 230000015572 biosynthetic process Effects 0.000 description 3
- 239000004033 plastic Substances 0.000 description 2
- 229920003023 plastic Polymers 0.000 description 2
- 229920000049 Carbon (fiber) Polymers 0.000 description 1
- 238000005299 abrasion Methods 0.000 description 1
- 239000004917 carbon fiber Substances 0.000 description 1
- 238000000354 decomposition reaction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 1
- 230000000007 visual effect Effects 0.000 description 1
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- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Of the present utility model provide a kind of lightweight but the non-damageable duct engine installation of blade can be protected and there is the aircraft of this duct engine installation.Wherein duct engine installation, comprises duct and rotor, and the base portion of duct is made up of non-metallic material, the part being positioned at rotor periphery of its circle wall is provided with the metal ring around rotor.Thus duct engine installation is lightweight and blade is not fragile.
Description
Technical field
The utility model relates to aircraft field, specifically, relates to duct engine installation and has the aircraft of this duct engine installation.
Background technology
Duct engine installation a kind ofly arranges a kind of propelling unit of duct in rotor periphery, is widely used in the various vehicle especially in aircraft.Due to rotor blade tip, place limits by duct, and noise is little, and induced drag reduces, and efficiency is higher.Simultaneously because the ring of duct draws together effect, make that the compact conformation of engine installation, aerodynamics noise are low, safety in utilization good.
Duct engine installation comprises duct and the rotor be coaxially arranged in duct and motor, and rotor is driven by motor.Duct is made up of metallic material or non-metallic material usually.The duct intensity of metallic material is high, resistance to abrasion good, and heat conductivility is good.But the duct that metallic material manufactures, weight is comparatively large, needs to consume larger energy during flight.And the duct good moldability that the non-metallic materials such as plastics are made, lighter in weight, but intensity is low, and easy to wear, and heat conductivility is also poor.When being subject to impacting, duct inwall easily contacts with blade and damages blade and duct.
Summary of the invention
Main purpose of the present utility model is to provide a kind of lightweight but can protect the non-damageable duct engine installation of blade;
Another object of the present utility model is to provide a kind ofly to be had lightweight but can protect the aircraft of the non-damageable duct engine installation of blade.
For realizing above-mentioned main purpose, the utility model provides duct engine installation, comprise the duct with circle wall and be positioned at duct and the rotor coaxial with it, rotor has the paddle of more than two panels, the base portion of duct is made up of non-metallic material, the part being positioned at rotor periphery of circle wall is provided with the metal ring around rotor.
From above scheme, duct base portion is made up of non-metallic material, make the overall weight of duct light and good moldability, the setting of metal ring can increase the circle wall intensity of rotor periphery, when making this part duct be subject to impacting, duct inwall can not be out of shape and contact with blade, thus blade can not be made to be damaged, and be out of shape the rotation that also can not have influence on blade when even if other parts are hit to some extent, therefore duct engine installation is lightweight and blade is not fragile.
More particularly, metal ring can be arranged on the inner side of circle wall, inside or outside.No matter metal ring arranges the inner side of circle wall, inner or outside, when being subject to impacting, can support circle wall.
More specifically, circle wall is provided with groove, metal ring is entrenched in groove, and the inwall of the inwall of metal ring or outer wall and circle wall or outer wall concordant.As known from the above, metal ring setting concordant with circle wall, makes resistance when additionally can not increase flight.
Preferably, metal ring and circle wall one-body molded.As known from the above, by one-body molded, metal ring and circle wall can combine securely without the need to other anchor fittings.
Preferably, cylindrically, along the axis of duct, the length of metal ring is corresponding with the width of blade for metal ring.Metal ring is corresponding with blade width to be referred to, at duct axially, the length of metal ring is substantially equal with the width of blade, and namely the length of metal ring is slightly smaller than, is equal to or slightly greater than the width of blade, thus whole rotor is protected, therefore not fragile.
Further, the length of metal ring is a bit larger tham the width of blade.
For realizing another object, the utility model provides aircraft, comprise frame, frame is provided with duct engine installation, comprise the duct with circle wall and be positioned at duct and the rotor coaxial with it, rotor has the paddle of more than two panels, and the base portion of duct is made up of non-metallic material, the part being positioned at rotor periphery of circle wall is provided with the metal ring around rotor.
As seen from the above, the duct base portion of aircraft is made up of non-metallic material, make the overall weight of duct light and good moldability, the setting of metal ring can increase the circle wall intensity of rotor periphery, when making this part duct be subject to impacting, duct inwall can not be out of shape and contact with blade, thus blade can not be made to be damaged, and be out of shape the rotation that also can not have influence on blade when even if other parts are hit to some extent, therefore the duct engine installation of aircraft is lightweight and blade is not fragile.
Accompanying drawing explanation
Fig. 1 is the constructional drawing of the utility model duct engine installation first embodiment;
Fig. 2 is the constructional drawing at another visual angle of the utility model duct engine installation first embodiment;
Fig. 3 is the STRUCTURE DECOMPOSITION figure of the utility model duct engine installation first embodiment;
Fig. 4 is the attached view of the utility model duct engine installation first embodiment;
Fig. 5 is the A-A cutaway view of Fig. 4, and rotates;
Fig. 6 is the cutaway view of the utility model duct engine installation second embodiment;
Fig. 7 is the cutaway view of the utility model duct engine installation the 3rd embodiment.
Detailed description of the invention
Below in conjunction with drawings and Examples, the utility model is described in further detail.
Duct engine installation first embodiment
See Fig. 1 to Fig. 5, the present embodiment duct engine installation comprises duct 1, rotor 2 and motor 3, and wherein duct 1 has circle wall 11, and rotor 2 and motor 3 are coaxially arranged in circle wall 11 with circle wall 11.Rotor 2 has three blades 21, and motor 3 has axle 31, and drives rotor 2 to rotate by axle 31.Circle wall 11 arranged outside has installation portion 12, for duct engine installation being arranged on the frame of aircraft.The inside of circle wall is provided with bracing frame 13 and mount pad 14, and motor 3 is arranged in mount pad, and bracing frame 13 is for supporting mount pad 14 and motor 3.
The main body of duct 1 is by non-metallic material, as the materials such as PP, ABS, foamed plastic or carbon fiber are made, the position of the inner side of circle wall and blade 21 periphery of rotor 2 is provided with groove, the annulus 15 of metal material is embedded in groove, cylindrically, its inwall is concordant with the inwall of the circle wall of duct for metal ring 15.Along the axis of duct 1, the length of metal ring 15 annulus is a bit larger tham the width of blade 21.Metal ring 15 can be arranged in groove after the main body of duct 1 is formed, and with groove flush fit; Also can be placed in when duct 1 is shaping in the mould of formation duct 1, thus integrally shaping with duct 1.
In the present embodiment, rotor 2 has three blades 21, is understandable that, in other embodiments, the quantity of blade can be two panels or more sheet.In the present embodiment, the length of metal ring is a bit larger tham the width of blade, in other embodiments, the length of metal ring can be equal with the width of blade, or slightly little, as long as when duct is subject to impacting, the duct supporting blade periphery is indeformable, and duct is not contacted with blade.In addition, except being applied to aircraft, the present embodiment also can be arranged on by the ship of air stream drives or car, e.g., and air cushion vehicle and pneumatic scooter etc.
Duct engine installation second embodiment
The similar of the present embodiment and duct engine installation first embodiment, just metal ring is different from the position relationship of circle wall.
As shown in Figure 6, the main body of duct 1 is made up of non-metallic material, and circle wall 11 inherence and the position of blade 21 periphery of rotor 2 are provided with the annulus 15 of metal material, and metal ring 15 cylindrically, and along the axis of duct 1, the length of metal ring 15 annulus is a bit larger tham the width of blade 21.Metal ring 15 can be placed in when duct 1 is shaping in the mould of formation duct 1, thus integrally shaping with duct 1.
Duct engine installation the 3rd embodiment
The similar of the present embodiment and duct engine installation first embodiment, just metal ring is different from the position relationship of circle wall.
As shown in Figure 7, the main body of duct 1 is made up of non-metallic material, and the position of the outside of circle wall and blade 21 periphery of rotor 2 is provided with groove, and the annulus 15 of metal material is embedded in groove, cylindrically, its outer wall is concordant with the outer wall of the circle wall of duct for metal ring 15.Along the axis of duct 1, the length of metal ring 15 annulus is a bit larger tham the width of blade 21.Metal ring 15 can be arranged in groove after the main body of duct 1 is formed, and with groove flush fit; Also can be placed in when duct 1 is shaping in the mould of formation duct 1, thus integrally shaping with duct 1.
Aircraft embodiment
Aircraft comprises frame and is installed on the duct engine installation in frame, and wherein duct engine installation can be any one in above-described embodiment.
Claims (10)
1. duct engine installation, comprise the duct with circle wall and be positioned at described duct and the rotor coaxial with it, described rotor has the paddle of more than two panels, it is characterized in that:
The base portion of described duct is made up of non-metallic material, the part being positioned at described rotor periphery of described circle wall is provided with the metal ring around described rotor.
2. duct engine installation according to claim 1, is characterized in that:
Described metal ring is arranged on the inner side of described circle wall.
3. duct engine installation according to claim 2, is characterized in that:
The inwall of described circle wall is provided with groove, and described metal ring is entrenched in described groove, and the inwall of described metal ring is concordant with the inwall of described circle wall.
4. duct engine installation according to claim 1, is characterized in that:
Described metal ring is arranged on the inside of described circle wall.
5. duct engine installation according to claim 1, is characterized in that:
Described metal ring is arranged on the outside of described circle wall.
6. duct engine installation according to claim 5, is characterized in that:
The outer wall of described circle wall is provided with groove, and described metal ring is entrenched in described groove, and the outer wall of described metal ring is concordant with the outer wall of described circle wall.
7. the duct engine installation according to any one of claim 1 to 6, is characterized in that:
Described metal ring and described circle wall one-body molded.
8. the duct engine installation according to any one of claim 1 to 6, is characterized in that:
Cylindrically, along the axis of described duct, the length of described metal ring is corresponding with the width of described blade for described metal ring.
9. duct engine installation according to claim 8, is characterized in that:
The length of described metal ring is a bit larger tham the width of described blade.
10. aircraft, comprises frame, described frame is provided with duct engine installation, and comprise the duct with circle wall and be positioned at described duct and the rotor coaxial with it, described rotor has the paddle of more than two panels, it is characterized in that:
The base portion of described duct is made up of non-metallic material, the part being positioned at described rotor periphery of described circle wall is provided with the metal ring around described rotor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520235400.0U CN204623849U (en) | 2015-04-17 | 2015-04-17 | Duct engine installation and aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520235400.0U CN204623849U (en) | 2015-04-17 | 2015-04-17 | Duct engine installation and aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204623849U true CN204623849U (en) | 2015-09-09 |
Family
ID=54042902
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520235400.0U Expired - Fee Related CN204623849U (en) | 2015-04-17 | 2015-04-17 | Duct engine installation and aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204623849U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106672230A (en) * | 2016-12-07 | 2017-05-17 | 深圳市元征科技股份有限公司 | Ducted unmanned aerial vehicle |
-
2015
- 2015-04-17 CN CN201520235400.0U patent/CN204623849U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106672230A (en) * | 2016-12-07 | 2017-05-17 | 深圳市元征科技股份有限公司 | Ducted unmanned aerial vehicle |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20170419 Address after: 519000 Guangdong city of Zhuhai province Hengqin Baohua Road No. 6, room 105 -14724 Patentee after: ZHUHAI PANLEI INTELLIGENT TECHNOLOGY Co.,Ltd. Address before: 519000 Guangdong Province, Zhuhai city Xiangzhou District Road No. 2 Building 2 martyrs Tong En Culture Communication Co. Ltd. Patentee before: He Chunwang |
|
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20150909 |