CN104724292A - Bypass power device and aircraft - Google Patents
Bypass power device and aircraft Download PDFInfo
- Publication number
- CN104724292A CN104724292A CN201510186070.5A CN201510186070A CN104724292A CN 104724292 A CN104724292 A CN 104724292A CN 201510186070 A CN201510186070 A CN 201510186070A CN 104724292 A CN104724292 A CN 104724292A
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- China
- Prior art keywords
- duct
- engine installation
- sleeve
- rotor
- length adjustment
- 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.)
- Granted
Links
- 238000009434 installation Methods 0.000 claims description 57
- 230000001105 regulatory effect Effects 0.000 claims description 3
- 239000013536 elastomeric material Substances 0.000 claims description 2
- 238000000034 method Methods 0.000 description 4
- 230000005540 biological transmission Effects 0.000 description 2
- 238000006243 chemical reaction Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- FWQHNLCNFPYBCA-UHFFFAOYSA-N fluoran Chemical compound C12=CC=CC=C2OC2=CC=CC=C2C11OC(=O)C2=CC=CC=C21 FWQHNLCNFPYBCA-UHFFFAOYSA-N 0.000 description 1
- 238000011900 installation process Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 230000000630 rising effect Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D29/00—Power-plant nacelles, fairings, or cowlings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Exhaust Silencers (AREA)
- Ventilation (AREA)
- Duct Arrangements (AREA)
Abstract
The invention relates to a bypass power device and an aircraft. A rotor wing is arranged in a bypass which is divided into an intake section and an exhaust section, a length adjusting mechanism is used for adjusting the length of the bypass and enabling the specific value of the intake section and the exhaust section to change. By the arrangement of the length adjusting mechanism, the length of the bypass can be adjusted in the axial direction, the specific value of the intake section and the exhaust section can be changed, and the location of the rotor wing in the axial direction of the bypass can be assuredly optimized. The bypass power device is adopted to the aircraft.
Description
Technical field
The invention belongs to aircraft field, specifically, relate to a kind ofly to there is the engine installation of duct and use the aircraft of this duct engine installation.
Background technology
Shown in Fig. 1, Fig. 2 and Fig. 3 is a kind of duct engine installation of the prior art, and this duct engine installation includes duct 10, admission port 20 and exhausr port 30.Be provided with rotor 40 and motor 50 in duct 10 inside, the rarest two panels blade 41 of rotor 40, the rotary power of rotor 40 is provided by motor 50, and rotor 40 and motor 50 are arranged in duct 10 in the mode of coaxial line.Duct 10 overall length is in the axial direction the length of duct 10.
Duct 10 is divided into air inlet section 60 and exhaust section 70 by rotor 40, air inlet section 60 is positioned at the fluoran stream surface side of rotor 40, one section of namely admission port 20 to rotor 40, what exhaust section 70 was positioned at rotor 40 goes to stream interface side, a section of namely rotor 40 to exhausr port 30.When rotor 40 position is arranged near admission port 20, the length of air inlet section 60 is shorter, admission port 20 place of duct 10 due to the negative pressure region that streams generation less and make the additional pulling force of duct 10 less, simultaneously, exhaust section is longer, and exhaust streams resistance comparatively greatly, and duct 10 total thrust is little.On the other hand, when the setting of rotor 40 is away from duct 10 admission port 20, air inlet section 60 is longer, flow-disturbing resistance when air-flow enters is comparatively large, and air-flow divergently discharges duct 10 too early, and thrust is difficult to the axis direction concentrating on duct 10, thus causing thrust loss, duct 10 total pulling force is also less.
In view of above-mentioned conclusion, those skilled in the art form following common recognition, the installation site of rotor 40 in duct 10 is an important parameter, when other parameter remains unchanged, for obtaining the Best Thrust of duct engine installation, on the axis direction of duct 10, the installation site of rotor 40 has optimum position, and namely the ratio of air inlet section 60 and exhaust section 70 has optimized ratio.For example, for certain specific rotor 40, installation site can be that distance admission port 20 is apart from 1/3rd places for duct 10 length, when rotor 40 is positioned at best position, the thrust produced during the work of duct engine installation is maximum, and namely the energy conversion efficiency of duct engine installation is best.
But, existing duct engine installation in use, owing to being subject to the combined influence of many kinds of parameters, the factor such as weight, blade quantity of such as duct engine installation, these parameters all can have influence on rotor 40 optimum position of installation site on axis direction in duct 10.
Visible, the length due to duct 10 is fixed value, and when some variable parameters change, such as, when changing different rotors 40, the rotor 40 after replacing is just no longer positioned on the optimum position of duct 10, and duct 10 also just can not produce maximum thrust.
In view of the problems referred to above that existing duct engine installation exists, in the urgent need to providing a kind of duct engine installation, the installation site of rotor 40 can be made to be in optimum position all the time, thus produce maximum thrust, to improve the energy conversion efficiency of duct engine installation.
Summary of the invention
The first object of the present invention is to provide a kind of duct engine installation;
Another object of the present invention is to provide a kind of aircraft using this duct engine installation.
Duct engine installation provided by the invention comprises duct, and rotor is arranged in duct, and makes duct be divided into air inlet section and exhaust section, and length adjustment mechanism is used for regulating the length of duct, and the ratio of air inlet section and exhaust section is changed.
Above scheme is visible, owing to being provided with length adjustment mechanism, duct can be enable to adjust in the length of axis direction, and the ratio of air inlet section and exhaust section is changed, thus can ensure that rotor finds the best in the position of the axis direction of duct, make duct engine installation obtain optimum pneumatic efficiency.
A preferred scheme is, length adjustment mechanism is axial telescopic sleeve, and sleeve docks with duct, and sleeve is flexible on the axis direction of duct.
Above scheme is visible, and tube-in-tube structure is simple, with low cost, on duct after relative movement, can complete the length adjustment of duct.
Preferred scheme is that sleeve is docked between the one or both ends of duct by the mode of screw thread fit further.
Above scheme is visible, and fixed form is simple, effectively, the stability that is fixedly connected with of sleeve on duct is high.
Preferred scheme is that sleeve is docked between the one or both ends of duct by the mode of interference fit further.
Above scheme is visible, and installation process is easy, and without the need to other attached attaching parts.
Preferred scheme is that sleeve is made up of elastomeric material further again.
Above scheme is visible, and resilient sleeve can also absorb the vibrations of duct engine installation, improves stability and the life-span of duct engine installation.
A preferred scheme is, the multistage cylinder that sleeve is increased step by step by radius is formed, and in multistage cylinder, the cylinder of minimum diameter is fixed in one end of duct.
Above scheme is visible, and the sleeve that radius progressively increases is conducive to the flowing of air-flow, avoids producing strong gas current friction.
A preferred scheme is, length adjustment mechanism is be serially connected in one section of spring tube in duct or bellows.
Above scheme is visible, and spring tube or bellows can absorb the vibrations of duct engine installation, improves stability and the life-span of duct engine installation.
Preferred scheme is provided with support tube in or beyond spring tube or bellows further.
Above scheme is visible, and the effect of support tube can prevent spring tube or bellows from when carrying out length adjustment, deformation occurring, thus ensures spring tube or bellows and duct coaxial line.
Aircraft provided by the invention comprises frame, and also comprise the duct engine installation of duct engine installation provided by the invention or any one preferred version, duct engine installation is arranged in frame.
A preferred scheme is, also comprise the sleeve travel mechanism that arrange corresponding to duct engine installation, sleeve travel mechanism is arranged in frame, and the adjustable side of sleeve travel mechanism is connected with length adjustment mechanism, for manipulating length adjustment mechanism.
Above scheme is visible, and sleeve travel mechanism can regulate the length of the length adjustment mechanism on duct, achieves mechanized operation process.
Accompanying drawing explanation
Fig. 1 is a kind of constructional drawing of existing duct engine installation.
Fig. 2 is the front view that Fig. 1 shows duct engine installation.
Fig. 3 is the A-A cutaway view of Fig. 2.
Fig. 4 is the constructional drawing of duct engine installation first embodiment provided by the invention.
Fig. 5 is the front view of the first embodiment.
Fig. 6 is the B-B cutaway view of Fig. 5.
Fig. 7 is the constructional drawing of aircraft first embodiment provided by the invention.
Fig. 8 is the birds-eye view of aircraft first embodiment provided by the invention.
Fig. 9 is the front view of aircraft first embodiment provided by the invention.
Detailed description of the invention
Duct engine installation first embodiment
As shown in Figure 4, Figure 5 and Figure 6, duct engine installation has duct 100, admission port 110 and exhausr port 120.Be provided with rotor 200 and motor 210 in duct 100 inside, rotor 200 has six blades 220, and rotor 200 is driven by motor 210, and rotor 200 and motor 210 are arranged in duct 100 in the mode of coaxial line.
Duct engine installation also comprises length adjustment mechanism, and the length adjustment mechanism of the present embodiment is sleeve 300, and sleeve 300 is the multistage sleeve increased step by step, and the hop count of sleeve can be 3 sections, and according to the actual requirements, the hop count of sleeve 300 can increase or reduce.One end and duct 100 end of sleeve 300 are socketed, and on the axis direction of duct 100, sleeve 300 can stretch by duct 100 relatively.Sleeve 300 is socketed in duct 100 end by screw thread fit, also can the mode of both interference fit be socketed.Sleeve 300 also can optional position between duct 100 two ends in the fixing position of duct 100.Preferably, one end of the minimum diameter of sleeve 300 is fixed in the exit of duct 100.Sleeve 300 when in use, manually can elongate or compression sleeve 300, thus adjust the length of air outlet section.Obviously, sleeve 300 also can be arranged on admission port side, thus adjusts the length of the air inlet section of admission port side.
Duct engine installation second embodiment
The length adjustment mechanism of the present embodiment is be serially connected in one section of spring tube in duct or bellows, spring tube and bellows are under the effect of external force, length can regulate, and after length adjustment, spring tube or bellows can keep this length and not change.Spring tube or bellows can be arranged on admission port or the air extractor duct of duct, thus adjust the length of air inlet section or air outlet section.As preferred scheme, spring tube or the inner or outer of bellows can also arrange the shorter support tube of a segment length, and support tube is preferably hard material.Other architectural feature do not described of the present embodiment should with reference to the first embodiment.
Aircraft first embodiment
As shown in Figure 7, Figure 8 and Figure 9, the aircraft sleeve travel mechanism that has a cross frame 400 and four duct engine installations 610 and sleeve 610 length is regulated.Duct engine installation adopts its first embodiment or the second embodiment.
Sleeve travel mechanism is made up of drive motor 410, screw mandrel 420 and the portable bar 430 be set on screw mandrel 420, and one end of portable bar 430 is the screw with screw mandrel 420 screw thread fit, and the other end is connected with the end of sleeve 610.When drive motor 410 works, drive the rotation of screw mandrel 420, and then drive rising or the decline of portable bar 430, therefore, can regulate the length of sleeve 610, thus the ratio of adjustment duct air inlet section and air outlet section, and make rotor to be in optimum position.At the admission port place of duct, also another one sleeve can be set.Sleeve travel mechanism can also be cylinder, is carried out the adjustment of sleeve 610 length by the piston rod of cylinder.
Aircraft second embodiment
On the basis of aircraft first embodiment, a thrust pickup is installed, thrust pickup is for detecting the real-time thrust signal of duct engine installation, in the process of sleeve travel mechanism movement, namely adjust in the air inlet section of duct and the ratio process of air outlet section gradually, the real-time thrust signal detected is transferred to control center, control center is a PLC system, control center compares the rear optimum position determining to control sleeve travel mechanism to real-time thrust signal, and then makes rotor be in optimum position.
In addition, drive the motor of rotor be not limited to rotor arch arrange, drive the motor of rotor can also be arranged in outside duct, drive by the mode of transmission shaft or V belt translation the rotor being positioned at duct.Rotor is also not limited to be driven by motor, also can be driven by oil machine.
Duct engine installation of the present invention is not limited to use on board the aircraft, can also be used in by the ship of air stream drives or car, e.g., and air cushion vehicle and pneumatic scooter.
When in the body that duct engine installation is arranged on duct aircraft, duct length can regulate according to actual needs, and visible duct engine installation of the present invention is not only beneficial to and obtains best performance, also has higher compatibility.
For tilting duct engine installation, under vertical mode of operation, need shorter duct, under horizontal operation state, need longer duct.Aircraft of the present invention can according to the length of the duct of the status adjustment duct engine installation that verts of state of flight and duct engine installation.
Finally it should be noted that; the invention is not restricted to above-mentioned embodiment; such as sleeve travel mechanism is arranged to the control method of belt pulley transmission; or two or more rotor is set at duct; the air inlet section of the duct of multiple rotor and air outlet section also have adjustable best proportion, and these schemes are also within claims of the present invention.
Claims (10)
1. duct engine installation, comprises
Duct;
Rotor, described rotor is arranged in described duct, makes described duct be divided into air inlet section and exhaust section;
It is characterized in that:
Length adjustment mechanism, described length adjustment mechanism is used for regulating the length of described duct, and the ratio of described air inlet section and described exhaust section is changed.
2. duct engine installation as claimed in claim 1, is characterized in that:
Described length adjustment mechanism is axial telescopic sleeve, and described sleeve docks with described duct;
Described sleeve is flexible on the axis direction of described duct.
3. duct engine installation as claimed in claim 2, is characterized in that:
Described sleeve is docked between the one or both ends of described duct by the mode of screw thread fit.
4. duct engine installation as claimed in claim 2, is characterized in that:
Described sleeve is docked between the one or both ends of described duct by the mode of interference fit.
5. duct engine installation as claimed in claim 4, is characterized in that:
Described sleeve is made up of elastomeric material.
6. duct engine installation as claimed in claim 2, is characterized in that:
The multistage cylinder that described sleeve is increased step by step by radius is formed;
In described multistage cylinder, the cylinder of minimum diameter is fixed in one end of described duct.
7. duct engine installation as claimed in claim 1, is characterized in that:
Described length adjustment mechanism is be serially connected in one section of spring tube in described duct or bellows.
8. duct engine installation as claimed in claim 7, is characterized in that:
Support tube is provided with in or beyond described spring tube or described bellows.
9. aircraft, comprises frame,
It is characterized in that:
Also comprise duct engine installation as described in any one of claim 1 to 8, described duct engine installation is arranged in described frame.
10. aircraft as claimed in claim 9, is characterized in that:
Also comprise the sleeve travel mechanism that arrange corresponding to described duct engine installation, described sleeve travel mechanism is arranged in described frame, and the adjustable side of described sleeve travel mechanism is connected with described length adjustment mechanism, for manipulating described length adjustment mechanism.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510186070.5A CN104724292B (en) | 2015-04-17 | 2015-04-17 | Duct power set and aircraft |
| CN201710492193.0A CN107458613A (en) | 2015-04-17 | 2015-04-17 | Aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510186070.5A CN104724292B (en) | 2015-04-17 | 2015-04-17 | Duct power set and aircraft |
Related Child Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710492193.0A Division CN107458613A (en) | 2015-04-17 | 2015-04-17 | Aircraft |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104724292A true CN104724292A (en) | 2015-06-24 |
| CN104724292B CN104724292B (en) | 2017-08-15 |
Family
ID=53448826
Family Applications (2)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510186070.5A Active CN104724292B (en) | 2015-04-17 | 2015-04-17 | Duct power set and aircraft |
| CN201710492193.0A Pending CN107458613A (en) | 2015-04-17 | 2015-04-17 | Aircraft |
Family Applications After (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710492193.0A Pending CN107458613A (en) | 2015-04-17 | 2015-04-17 | Aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (2) | CN104724292B (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106628249A (en) * | 2017-01-17 | 2017-05-10 | 深圳市哈威飞行科技有限公司 | Test device for duct aircraft and test method thereof |
| 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 |
| CN108528713A (en) * | 2017-03-03 | 2018-09-14 | 珠海磐磊智能科技有限公司 | Flight luggage and its control method |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110775260B (en) * | 2019-12-02 | 2024-06-04 | 北京玮航科技有限公司 | Ducted fan and aircraft |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5228641A (en) * | 1991-08-15 | 1993-07-20 | Rohr, Inc. | Cascade type aircraft engine thrust reverser with hidden link actuator |
| CN2804543Y (en) * | 2005-06-03 | 2006-08-09 | 刘汉奎 | Support adjustable corrugated pipe |
| US20100148012A1 (en) * | 2008-12-17 | 2010-06-17 | Mcdonough Michael Patrick | Aircraft engine nacelle with translating inlet cowl |
| CN101973391A (en) * | 2010-10-15 | 2011-02-16 | 北京理工大学 | Lip and spread angle variable efficient duct |
| CN102826220A (en) * | 2012-09-14 | 2012-12-19 | 西北工业大学 | Thrust device capable of balancing reactive torque |
| CN103939234A (en) * | 2014-04-24 | 2014-07-23 | 北京航空航天大学 | Common drive type rear duct ejector in adjustable mechanism of variable cycle engine |
| CN204548496U (en) * | 2015-04-17 | 2015-08-12 | 何春旺 | Duct engine installation and aircraft |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN201917426U (en) * | 2010-12-27 | 2011-08-03 | 朱力 | Performance testing platform for miniature propulsion system |
| CN202006875U (en) * | 2011-01-21 | 2011-10-12 | 许群伟 | Ducted fan |
| CN202848026U (en) * | 2012-09-14 | 2013-04-03 | 西北工业大学 | Thrusting device capable of balancing reaction torque |
| ITTO20121152A1 (en) * | 2012-12-27 | 2014-06-28 | Alenia Aermacchi Spa | MOTOR GONDOLA FOR AN AIRCRAFT, EQUIPPED WITH AN INTEGRATED PROTECTION SYSTEM FOR ANTI-ICE AND ACOUSTIC ABSORPTION. |
-
2015
- 2015-04-17 CN CN201510186070.5A patent/CN104724292B/en active Active
- 2015-04-17 CN CN201710492193.0A patent/CN107458613A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5228641A (en) * | 1991-08-15 | 1993-07-20 | Rohr, Inc. | Cascade type aircraft engine thrust reverser with hidden link actuator |
| CN2804543Y (en) * | 2005-06-03 | 2006-08-09 | 刘汉奎 | Support adjustable corrugated pipe |
| US20100148012A1 (en) * | 2008-12-17 | 2010-06-17 | Mcdonough Michael Patrick | Aircraft engine nacelle with translating inlet cowl |
| CN101973391A (en) * | 2010-10-15 | 2011-02-16 | 北京理工大学 | Lip and spread angle variable efficient duct |
| CN102826220A (en) * | 2012-09-14 | 2012-12-19 | 西北工业大学 | Thrust device capable of balancing reactive torque |
| CN103939234A (en) * | 2014-04-24 | 2014-07-23 | 北京航空航天大学 | Common drive type rear duct ejector in adjustable mechanism of variable cycle engine |
| CN204548496U (en) * | 2015-04-17 | 2015-08-12 | 何春旺 | Duct engine installation and aircraft |
Non-Patent Citations (2)
| Title |
|---|
| 竺培国: "《精密仪器结构设计基础》", 30 September 1988, 哈尔滨工业大学出版社 * |
| 陈刚: "《机电一体化技术》", 31 March 2010, 清华大学出版社 * |
Cited By (5)
| 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 |
| CN106628249A (en) * | 2017-01-17 | 2017-05-10 | 深圳市哈威飞行科技有限公司 | Test device for duct aircraft and test method thereof |
| CN106628249B (en) * | 2017-01-17 | 2023-08-15 | 深圳市哈威飞行科技有限公司 | Ducted aircraft testing device and testing method thereof |
| CN108528713A (en) * | 2017-03-03 | 2018-09-14 | 珠海磐磊智能科技有限公司 | Flight luggage and its control method |
| CN108528713B (en) * | 2017-03-03 | 2022-11-08 | 珠海磐磊智能科技有限公司 | Flight case and control method thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104724292B (en) | 2017-08-15 |
| CN107458613A (en) | 2017-12-12 |
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Effective date of registration: 20170406 Address after: 519000 Guangdong city of Zhuhai province Hengqin Baohua Road No. 6, room 105 -14724 Applicant after: Zhuhai pan Lei 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. Applicant before: He Chunwang |
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