CN104724292B - Duct power set and aircraft - Google Patents
Duct power set and aircraft Download PDFInfo
- Publication number
- CN104724292B CN104724292B CN201510186070.5A CN201510186070A CN104724292B CN 104724292 B CN104724292 B CN 104724292B CN 201510186070 A CN201510186070 A CN 201510186070A CN 104724292 B CN104724292 B CN 104724292B
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- Prior art keywords
- duct
- sleeve
- power set
- rotor
- air inlet
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- 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.)
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- 230000033001 locomotion Effects 0.000 claims description 6
- 230000000630 rising effect Effects 0.000 claims description 2
- 238000009434 installation Methods 0.000 description 4
- 230000005540 biological transmission Effects 0.000 description 2
- 238000006243 chemical reaction Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000033228 biological regulation Effects 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 239000012141 concentrate Substances 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000013536 elastomeric material Substances 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
- 238000005457 optimization Methods 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)
- Duct Arrangements (AREA)
- Ventilation (AREA)
Abstract
The present invention relates to duct power set and aircraft, rotor is arranged in duct, and duct is divided into air inlet section and exhaust section, and length adjustment mechanism is used to the length of duct is adjusted, and the ratio of air inlet section and exhaust section is changed.Due to being provided with length adjustment mechanism, duct can be enable to be adjusted in the length of axis direction, and the ratio of air inlet section and exhaust section is changed, so as to ensure that rotor is found most preferably in the position of the axis direction of duct.Aircraft uses above-mentioned duct power set.
Description
Technical field
It is to be related to a kind of power set with duct and use this specifically the invention belongs to aircraft field
Plant the aircraft of duct power set.
Background technology
Shown in Fig. 1, Fig. 2 and Fig. 3 is a kind of duct power set of the prior art, and this duct power set include
Duct 10, air inlet 20 and exhaust outlet 30.Rotor 40 and motor 50, a minimum of two panels of rotor 40 are installed inside duct 10
Blade 41, the rotary power of rotor 40 is provided by motor 50, and rotor 40 and motor 50 are arranged on duct 10 in the way of coaxial line
It is interior.The overall length of duct 10 in the axial direction is the length of duct 10.
Duct 10 is divided into air inlet section 60 and exhaust section 70 by rotor 40, and air inlet section 60 is located at the fluoran stream surface one of rotor 40
Side, that is, air inlet 20 is to one section of rotor 40, what exhaust section 70 was located at rotor 40 goes to stream interface side, that is, rotor 40 to
One section of exhaust outlet 30.When rotor 40, which is located proximate to air inlet 20, to be set, the length of air inlet section 60 is shorter, the air inlet of duct 10
Because the negative pressure region for streaming generation is smaller and makes the additional pulling force of duct 10 smaller at mouth 20, meanwhile, exhaust section is longer, exhaust
Stream resistance larger, the gross thrust of duct 10 is small.On the other hand, when the setting of rotor 40 is away from 10 air inlet 20 of duct, air inlet
Section is 60 longer, and air-flow enters that fashionable flow-disturbing resistance is larger, and air-flow divergently discharges duct 10 too early, and thrust is difficult to concentrate on duct
10 axis direction, so as to cause thrust loss, the total pulling force of duct 10 is also smaller.
In view of above-mentioned conclusion, those skilled in the art form following common recognition, installation site of the rotor 40 in duct 10 is
One important parameter, in the case where other parameters keep constant, to obtain the Best Thrust of duct power set, in duct
On 10 axis direction, the installation site of rotor 40 has optimum position, that is, air inlet section 60 and the ratio of exhaust section 70 tool
There is the ratio of optimization.For example, for certain specific rotor 40, installation site can be apart from air inlet 20 apart from for
At 1/3rd of the length of duct 10, when rotor 40 is located at best position, the thrust that duct power set are produced when working
Maximum, that is, the energy conversion efficiency of duct power set are optimal.
However, existing duct power set are in use, due to the combined influence by many kinds of parameters, such as duct
The factors such as weight, the blade quantity of power set, these parameters can all have influence on rotor 40 and pacify in duct 10 on axis direction
The optimum position of holding position.
It can be seen that, it is when some variable parameters change, such as different when changing because the length of duct 10 is fixed value
Rotor 40 when, the rotor 40 after replacing is just no longer on the optimum position of duct 10, and duct 10 cannot also produce maximum
Thrust.
In view of the above mentioned problem that existing duct power set are present, in the urgent need to providing a kind of duct power set, with
Just the installation site of rotor 40 is enabled to be in optimum position all the time, so that the thrust of maximum is produced, to improve duct power
The energy conversion efficiency of device.
The content of the invention
The first object of the present invention is to provide a kind of duct power set；
It is a further object of the present invention to provide a kind of aircraft using this duct power set.
The duct power set that the present invention is provided include duct, and rotor is arranged in duct, and duct is divided into air inlet
Section and exhaust section, length adjustment mechanism are used to the length of duct is adjusted, and occur the ratio of air inlet section and exhaust section
Change.
Above scheme is visible, due to being provided with length adjustment mechanism, and duct can be enable to be carried out in the length of axis direction
Adjustment, and the ratio of air inlet section and exhaust section is changed, so as to ensure rotor in the position of the axis direction of duct
Find most preferably, duct power set is obtained optimum pneumatic efficiency.
One preferred scheme is that length adjustment mechanism is axially telescopic sleeve, and sleeve is docked with duct, and sleeve exists
Stretched on the axis direction of duct.
Above scheme is visible, and tube-in-tube structure is simple, with low cost, after being relatively moved on duct, can complete duct
Length adjustment.
Further preferred scheme is that sleeve is docked at by way of screw thread coordinates between the one or both ends of duct.
Above scheme is visible, and fixed form is simple, effective, and the stability that is fixedly connected of the sleeve on duct is high.
Further preferred scheme is that sleeve is docked between the one or both ends of duct by way of interference fit.
Above scheme is visible, and installation process is easy, and without other attached connectors.
Scheme still further preferably is that sleeve is made up of elastomeric material.
Above scheme is visible, and resilient sleeve can also absorb the vibrations of duct power set, improves the steady of duct power set
The qualitative and life-span.
One preferred scheme is that the multistage cylinder that sleeve is increased step by step by radius is constituted, the cylinder of minimum diameter in multistage cylinder
It is fixed in one end of duct.
Above scheme is visible, and the sleeve that radius is incrementally increased is conducive to the flowing of air-flow, it is to avoid produces strong air-flow and rubs
Wipe.
One preferred scheme is that length adjustment mechanism is the one section of elastic tube or bellows being serially connected in duct.
Above scheme is visible, and elastic tube or bellows can absorb the vibrations of duct power set, improve duct power set
Stability and the life-span.
Further preferred scheme is to be provided with support tube in or beyond elastic tube or bellows.
Above scheme is visible, and the effect of support tube can prevent elastic tube or bellows from occurring shape when carrying out length adjustment
Become, so as to ensure elastic tube or bellows and duct coaxial line.
The aircraft that the present invention is provided includes frame, in addition to the duct power set that provide of the present invention or any one
The duct power set of preferred scheme, duct power set are arranged in frame.
One preferred scheme is, in addition to the sleeve travel mechanism being correspondingly arranged with duct power set, sleeve movement
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 adjust the length of the length adjustment mechanism on duct, realize machine
Tool operating process.
Brief description of the drawings
Fig. 1 is a kind of structure chart of existing duct power set.
Fig. 2 is the front view that Fig. 1 shows duct power set.
Fig. 3 is Fig. 2 A-A sectional views.
Fig. 4 is the structure chart for the duct power set first embodiment that the present invention is provided.
Fig. 5 is the front view of first embodiment.
Fig. 6 is Fig. 5 B-B sectional views.
Fig. 7 is the structure chart for the aircraft first embodiment that the present invention is provided.
Fig. 8 is the top view for the aircraft first embodiment that the present invention is provided.
Fig. 9 is the front view for the aircraft first embodiment that the present invention is provided.
Embodiment
Duct power set first embodiment
As shown in Figure 4, Figure 5 and Figure 6, duct power set have duct 100, air inlet 110 and exhaust outlet 120.In duct
Rotor 200 and motor 210 are installed, rotor 200 there are six blades 220, and rotor 200 is driven by motor 210, rotor inside 100
200 and motor 210 be arranged in the way of coaxial line in duct 100.
Duct power set also include length adjustment mechanism, and the length adjustment mechanism of the present embodiment is sleeve 300, sleeve
The 300 multistage sleeve to increase step by step, the hop count of sleeve can be 3 sections, and according to the actual requirements, the hop count of sleeve 300 can increase
Plus or reduce.One end of sleeve 300 is socketed with the end of duct 100, on the axis direction of duct 100, and sleeve 300 can be relative
Duct 100 stretches.Sleeve 300 by screw thread coordinate is socketed in the end of duct 100, can also both interference fit mode set
Connect.Sleeve 300 can also be in the optional position between the two ends of duct 100 in the position that duct 100 is fixed.Preferably,
One end of the minimum diameter of sleeve 300 is fixed in the exit of duct 100.Sleeve 300 when in use, can be elongated manually
Or compression sleeve 300, so that the length to air outlet section is adjusted.Obviously, sleeve 300 can also be arranged on air inlet side,
So as to which the length of the air inlet section to air inlet side is adjusted.
Duct power set second embodiment
The length adjustment mechanism of the present embodiment is the one section of elastic tube or bellows, elastic tube and ripple being serially connected in duct
Pipe is in the presence of external force, and length can be adjusted, and after length adjustment, elastic tube or bellows can keep this
Length is planted without changing.Elastic tube or bellows may be mounted at air inlet or the gas outlet of duct, so as to air inlet
The length of section or air outlet section is adjusted.As preferred scheme, elastic tube or the inner or outer of bellows can also set one section
The shorter support tube of length, support tube is preferably hard material.The other architectural features not described of the present embodiment should refer to first
Embodiment.
Aircraft first embodiment
As shown in Figure 7, Figure 8 and Figure 9, aircraft have a cross frame 400 and four duct power set 610 with
And to sleeve travel mechanism that the length of sleeve 610 is adjusted.Duct power set are implemented using its first embodiment or second
Example.
Sleeve travel mechanism is made up of motor 410, screw mandrel 420 and the motion bar 430 being set on screw mandrel 420, living
One end of lever 430 is the screw coordinated with the screw thread of screw mandrel 420, and the other end is connected with the end of sleeve 610.Motor 410
During work, the rotation of screw mandrel 420 is driven, and then drives the rising or decline of motion bar 430, therefore, it is possible to sleeve 610
Length is adjusted, so as to adjust the ratio of duct air inlet section and air outlet section, and causes rotor to be at optimum position.Containing
Another sleeve can also be set at the air inlet in road.Sleeve travel mechanism can also be cylinder, pass through the piston rod of cylinder
To carry out the regulation of the length of sleeve 610.
Aircraft second embodiment
On the basis of aircraft first embodiment, a thrust pickup is installed, thrust pickup is used to detect duct
The real-time thrust signal of power set, during sleeve travel mechanism moves, i.e., gradually adjusts the air inlet section of duct and goes out
During the ratio of gas section, the real-time thrust signal detected is transmitted to control centre, control centre is a PLC system,
Control centre determines the optimum position of control sleeve travel mechanism after being compared to real-time thrust signal, and then causes at rotor
In optimum position.
In addition, the motor of driving rotor is not limited to arrange with rotor arch, the motor of driving rotor can also be arranged
On the outside of duct, the rotor in duct is driven by way of power transmission shaft or V belt translation.Rotor is also not necessarily limited to be driven by motor
It is dynamic, it can also be driven by oil machine.
The duct power set of the present invention are not limited to using on board the aircraft, can also use in the ship by air stream drives or
Che Shang, e.g., aircushion vehicle and pneumatic sleigh.
When duct power set are arranged in the body of duct aircraft, duct length can be adjusted according to actual needs,
It can be seen that duct power set of the invention are not only beneficial to obtain optimal performance, also with higher compatibility.
For tilting duct power set, it is necessary to shorter duct under vertical working condition, in horizontal operation state
Down, it is necessary to longer duct.The aircraft of the present invention can be according to state of flight and the status adjustment of verting of duct power set
The length of the duct of duct power set.
Finally it should be noted that the invention is not restricted to above-mentioned embodiment, being such as arranged to sleeve travel mechanism
The control method of belt pulley transmission, or set two or more rotor in duct, the duct of multiple rotors enters
Gas section and air outlet section also have adjustable best proportion, and these schemes are also within the claims of the present invention.
Claims (1)
1. aircraft, including cross frame,
It is characterized in that：
Also include four duct power set, four duct power set are arranged in the cross frame;
The duct power set include
Duct；
Rotor, the rotor is arranged in the duct, the duct is divided into air inlet section and exhaust section；
Length adjustment mechanism, the length adjustment mechanism is used to the length of the duct is adjusted, and makes the air inlet section
Changed with the ratio of the exhaust section;
The length adjustment mechanism is axially telescopic sleeve, and the sleeve is docked with the duct, and the sleeve is described
Stretched on the axis direction of duct；
Also include the sleeve travel mechanism being correspondingly arranged with the duct power set, the sleeve travel mechanism is arranged on described
In cross frame；
The sleeve travel mechanism includes motor, screw mandrel and the motion bar being set on screw mandrel, one end of motion bar and silk
Bar is connected, the other end and sleeve connection；Motor work when, drive screw mandrel rotation, and then drive motion bar rising or
Person declines；
The aircraft also includes thrust pickup, and the thrust pickup is used to detect pushing away in real time for the duct power set
Force signal, during the sleeve travel mechanism moves, i.e., gradually adjusts the air inlet section of the duct and the ratio of air outlet section
During example, the real-time thrust signal detected is transmitted to control centre, the control centre is carried out to real-time thrust signal
The optimum position of the control sleeve travel mechanism is determined more afterwards.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710492193.0A CN107458613A (en) | 2015-04-17 | 2015-04-17 | Aircraft |
| CN201510186070.5A CN104724292B (en) | 2015-04-17 | 2015-04-17 | Duct power set and 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 CN104724292A (en) | 2015-06-24 |
| CN104724292B true 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 |
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| CN (2) | CN104724292B (en) |
Families Citing this family (4)
| 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 |
| 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 |
| 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 |
| CN110775260B (en) * | 2019-12-02 | 2024-06-04 | 北京玮航科技有限公司 | Ducted fan and aircraft |
Citations (5)
| 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 |
| 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 (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2804543Y (en) * | 2005-06-03 | 2006-08-09 | 刘汉奎 | Support adjustable corrugated pipe |
| US8181905B2 (en) * | 2008-12-17 | 2012-05-22 | Rohr, Inc. | Aircraft engine nacelle with translating inlet cowl |
| 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 (5)
| 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 |
| 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 |
Also Published As
| Publication number | Publication date |
|---|---|
| CN104724292A (en) | 2015-06-24 |
| 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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