CN110422318B - Coaxial contra-rotating propeller with self-adaptive variable axial spacing - Google Patents
Coaxial contra-rotating propeller with self-adaptive variable axial spacing Download PDFInfo
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- CN110422318B CN110422318B CN201910618320.6A CN201910618320A CN110422318B CN 110422318 B CN110422318 B CN 110422318B CN 201910618320 A CN201910618320 A CN 201910618320A CN 110422318 B CN110422318 B CN 110422318B
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- propeller
- guide sliding
- front propeller
- hub
- pretightening
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/46—Arrangements of, or constructional features peculiar to, multiple propellers
- B64C11/48—Units of two or more coaxial propellers
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- Aviation & Aerospace Engineering (AREA)
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Abstract
A self-adaptive coaxial contra-rotating propeller with variable axial spacing is characterized in that a switching sleeve is sleeved at the rear end of a front propeller hub, a plurality of guide slide rails are uniformly and fixedly arranged on the side surface of the front propeller hub, and the guide slide rails are parallel to the central axis of the front propeller hub; the inner surface of the side wall of the adapter sleeve is provided with a plurality of guide sliding chutes, the guide sliding chutes and the guide sliding rails are equal in quantity, parallel and in one-to-one correspondence in position, the guide sliding rails are positioned in the guide sliding chutes, and the adapter sleeve can linearly move along the guide sliding rails; a plurality of pre-tightening springs are connected between the inner surface of the cylinder bottom of the adapter sleeve and the rear end surface of the front paddle hub; the rear propeller hub is fixedly connected to the outer surface of the cylinder bottom of the adapter sleeve; when the aircraft is in a takeoff state, the maximum thrust of the front propeller is larger than the pretightening force of the pretightening spring, and the pretightening spring is in an extension state, so that the axial distance between the front propeller and the rear propeller is increased; when the aircraft is in a cruising state, the thrust of the front propeller is smaller than the pretightening force of the pretightening spring, and the pretightening spring is in a retraction state, so that the axial distance between the front propeller and the rear propeller is reduced.
Description
Technical Field
The invention belongs to the technical field of air propellers, and particularly relates to a coaxial contra-rotating propeller with self-adaptive variable axial spacing.
Background
Currently, the airscrew is one of the main power devices of an aircraft, and is widely applied in the fields of transport planes, civil aircraft, general aircraft, unmanned aerial vehicles and the like, while the coaxial contra-rotating airscrew belongs to one type of airscrew.
The coaxial contra-rotating propellers are air propellers consisting of two single-row propellers which rotate around the same rotating shaft and have opposite rotating directions, the upstream single-row propeller is called front propeller, the downstream single-row propeller is called rear propeller, the front propeller and the rear propeller can have the same geometric parameters or blade shapes, and the like, and different geometric parameters or blade shapes can be used according to aerodynamic performance requirements.
However, since the rear propeller of the coaxial counter-rotating propellers is completely in the slipstream generated by the front propeller, the aerodynamic performance of the rear propeller is directly affected by the front propeller, and at the same time, if the axial distance between the front and rear propellers is small, the aerodynamic performance of the front propeller is also affected by the rear propeller.
Research shows that the coaxial contra-rotating propeller has higher aerodynamic efficiency compared with an isolated single-row propeller, the axial distance between the front propeller and the rear propeller is one of important parameters influencing the aerodynamic performance of the coaxial contra-rotating propeller, and the aerodynamic performance can also influence other parameters such as thrust, efficiency and the like.
At present, the axial distance of the existing coaxial contra-rotating propellers is fixed and unchanged, so that the existing coaxial contra-rotating propellers only have the best performance in a single flight state, but cannot be matched with the best aerodynamic performance according to the flight state.
Disclosure of Invention
Aiming at the problems in the prior art, the invention provides a coaxial contra-rotating propeller with self-adaptive variable axial spacing, which can self-adaptively change the axial spacing of a front propeller and a rear propeller according to take-off, cruise and other states; when the aircraft takes off, the propeller is in a state of maximum thrust, and the axial distance between the front propeller and the rear propeller can be increased in a self-adaptive manner, so that the thrust of the propeller is further increased, and the take-off of the aircraft is facilitated; when the aircraft navigates, the thrust of the propeller is reduced, and the axial distance between the front propeller and the rear propeller can be reduced in a self-adaptive manner, so that the pneumatic efficiency of the propeller is higher, and the flight economy is improved.
In order to achieve the purpose, the invention adopts the following technical scheme: a self-adaptive variable axial spacing coaxial contra-rotating propeller comprises a front propeller and a rear propeller, wherein the front propeller and the rear propeller are coaxially arranged, a plurality of front propeller blades are uniformly distributed on a front propeller hub, a plurality of rear propeller blades are uniformly distributed on a rear propeller hub, a switching sleeve is sleeved at the rear end of the front propeller hub, a plurality of guide slide rails are uniformly distributed and fixedly arranged on the side surface of the front propeller hub, and the guide slide rails are parallel to the central axis of the front propeller hub; the inner surface of the side wall of the adapter sleeve is provided with a plurality of guide sliding grooves, the number of the guide sliding grooves is equal to that of the guide sliding rails, the guide sliding grooves correspond to the guide sliding rails one by one, the guide sliding rails are parallel to the guide sliding rails, the guide sliding rails are positioned in the guide sliding grooves, and the adapter sleeve can linearly move along the guide sliding rails; a plurality of pre-tightening springs are connected between the inner surface of the cylinder bottom of the adapter sleeve and the rear end surface of the front paddle hub; the rear propeller hub is fixedly connected to the outer surface of the cylinder bottom of the adapter sleeve.
When the aircraft is in a takeoff state, the maximum thrust of the front propeller is larger than the pretightening force of the pretightening spring, and the pretightening spring is in an extension state, so that the axial distance between the front propeller and the rear propeller is increased.
When the aircraft is in a cruising state, the thrust of the front propeller is smaller than the pretightening force of the pretightening spring, and the pretightening spring is in a retraction state, so that the axial distance between the front propeller and the rear propeller is reduced.
The number of the front paddle blades and the number of the rear paddle blades are 2-16.
The number of the guide sliding grooves and the number of the guide sliding rails are 2-16.
The ratio of the axial distance variation range of the front paddle and the rear paddle to the rotating diameter of the front paddle blade/the rear paddle blade is 10%.
The invention has the beneficial effects that:
the self-adaptive coaxial contra-rotating propeller with variable axial spacing can self-adaptively change the axial spacing between the front propeller and the rear propeller according to the taking-off, cruising and other states; when the aircraft takes off, the propeller is in a maximum thrust state, and the axial distance between the front propeller and the rear propeller can be adaptively increased, so that the thrust of the propeller is further increased, and the takeoff of the aircraft is facilitated; when the aircraft is cruising, the thrust of the propeller is reduced, the axial distance between the front propeller and the rear propeller can be reduced in a self-adaptive mode, the pneumatic efficiency of the propeller is higher, and the flight economy is improved.
Drawings
FIG. 1 is a perspective view of an adaptive variable axial spacing coaxial contra-rotating propeller of the present invention;
FIG. 2 is a front view of an adaptive variable axial spacing coaxial contra-rotating propeller of the present invention;
in the figure, 1-front propeller hub, 2-front propeller blade, 3-rear propeller hub, 4-rear propeller blade, 5-adapter sleeve, 6-guide sliding rail, 7-guide sliding groove and 8-pre-tightening spring.
Detailed Description
The invention is described in further detail below with reference to the figures and the specific embodiments.
As shown in fig. 1 and 2, a self-adaptive variable axial spacing coaxial contra-rotating propeller comprises a front propeller and a rear propeller, wherein the front propeller and the rear propeller are coaxially arranged, a plurality of front propeller blades 2 are uniformly distributed on a front propeller hub 1, a plurality of rear propeller blades 4 are uniformly distributed on a rear propeller hub 3, a switching sleeve 5 is sleeved at the rear end of the front propeller hub 1, a plurality of guide slide rails 6 are uniformly distributed and fixedly arranged on the side surface of the front propeller hub 1, and the guide slide rails 6 are parallel to the central axis of the front propeller hub 1; a plurality of guide sliding grooves 7 are formed in the inner surface of the side wall of the adapter sleeve 5, the number of the guide sliding grooves 7 is equal to that of the guide sliding rails 6, the guide sliding grooves 7 correspond to the guide sliding rails 6 one by one, the guide sliding rails 7 are parallel to the guide sliding rails 6, the guide sliding rails 6 are located in the guide sliding grooves 7, and the adapter sleeve 5 can move linearly along the guide sliding rails 6; a plurality of pre-tightening springs 8 are connected between the inner surface of the cylinder bottom of the adapter sleeve 5 and the rear end surface of the front paddle wheel hub 1; the rear propeller hub 3 is fixedly connected to the outer surface of the cylinder bottom of the adapter sleeve 5.
When the aircraft is in a take-off state, the maximum thrust of the front propeller is larger than the pretightening force of the pretightening spring 8, and the pretightening spring 8 is in an extension state, so that the axial distance between the front propeller and the rear propeller is increased.
When the aircraft is in a cruising state, the thrust of the front propeller is smaller than the pretightening force of the pretightening spring 8, and the pretightening spring 8 is in a retraction state, so that the axial distance between the front propeller and the rear propeller is reduced.
The number of the front paddle blade 2 and the number of the rear paddle blade 4 are both 2.
The number of the guide sliding chutes 7 and the number of the guide sliding rails 6 are 4.
The ratio of the change range of the axial distance between the front propeller and the rear propeller to the rotating diameter of the front propeller blade 2/the rear propeller blade 4 is 10%.
When the coaxial contra-rotating propeller is installed on an aircraft, the front propeller and the rear propeller are in the maximum thrust state when the aircraft takes off, the maximum thrust of the front propeller is larger than the pretightening force of the pretightening spring 8, the pretightening spring 8 stretches and lengthens under the action of the maximum thrust force of the front propeller, so that the axial distance between the front propeller and the rear propeller is increased, the thrust between the front propeller and the rear propeller is further increased along with the increase of the axial distance between the front propeller and the rear propeller, and the takeoff of the aircraft is facilitated although the starting efficiency of the propeller is reduced at the moment; and when the aircraft navigated, the thrust of preceding oar and back oar can reduce, and the thrust of preceding oar will be less than pretension of pretension spring 8 this moment, and pretension spring 8 will resume to the state of contracting under the pretension effect to make the axial interval of preceding oar and back oar reduce, the aerodynamic efficiency of screw this moment is higher, and then can improve flight economy.
The embodiments are not intended to limit the scope of the present invention, and all equivalent implementations or modifications without departing from the scope of the present invention are intended to be included in the scope of the present invention.
Claims (4)
1. The utility model provides a coaxial contra-rotating propeller of self-adaptation variable axial interval which characterized in that: the front propeller and the rear propeller are coaxially arranged, a plurality of front propeller blades are uniformly distributed on a front propeller hub, a plurality of rear propeller blades are uniformly distributed on a rear propeller hub, a switching sleeve is sleeved at the rear end of the front propeller hub, a plurality of guide slide rails are uniformly distributed and fixedly arranged on the side surface of the front propeller hub, and the guide slide rails are parallel to the central axis of the front propeller hub; the inner surface of the side wall of the adapter sleeve is provided with a plurality of guide sliding grooves, the number of the guide sliding grooves is equal to that of the guide sliding rails, the guide sliding grooves correspond to the guide sliding rails one by one, the guide sliding rails are parallel to the guide sliding rails, the guide sliding rails are positioned in the guide sliding grooves, and the adapter sleeve can linearly move along the guide sliding rails; a plurality of pre-tightening springs are connected between the inner surface of the cylinder bottom of the adapter sleeve and the rear end surface of the front propeller hub; the rear propeller hub is fixedly connected to the outer surface of the cylinder bottom of the adapter sleeve; when the aircraft is in a takeoff state, the maximum thrust of the front propeller is larger than the pretightening force of the pretightening spring, and the pretightening spring is in an extension state, so that the axial distance between the front propeller and the rear propeller is increased; when the aircraft is in a cruising state, the thrust of the front propeller is smaller than the pretightening force of the pretightening spring, and the pretightening spring is in a retraction state, so that the axial distance between the front propeller and the rear propeller is reduced.
2. An adaptive variable axial spacing coaxial contra-rotating propeller as claimed in claim 1, wherein: the number of the front paddle blades and the number of the rear paddle blades are both 2-16.
3. An adaptive variable axial pitch coaxial contra-rotating propeller as claimed in claim 1, wherein: the number of the guide sliding grooves and the number of the guide sliding rails are 2-16.
4. An adaptive variable axial spacing coaxial contra-rotating propeller as claimed in claim 1, wherein: the ratio of the axial distance variation range value of the front paddle and the rear paddle to the rotating diameter of the front paddle blade is 10%, and the ratio of the axial distance variation range value of the front paddle and the rear paddle to the rotating diameter of the rear paddle blade is 10%.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910618320.6A CN110422318B (en) | 2019-07-10 | 2019-07-10 | Coaxial contra-rotating propeller with self-adaptive variable axial spacing |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201910618320.6A CN110422318B (en) | 2019-07-10 | 2019-07-10 | Coaxial contra-rotating propeller with self-adaptive variable axial spacing |
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| CN110422318A CN110422318A (en) | 2019-11-08 |
| CN110422318B true CN110422318B (en) | 2022-07-19 |
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| CN201910618320.6A Active CN110422318B (en) | 2019-07-10 | 2019-07-10 | Coaxial contra-rotating propeller with self-adaptive variable axial spacing |
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Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111114764B (en) * | 2020-02-10 | 2024-04-19 | 中国工程物理研究院总体工程研究所 | Disposable propeller conversion device of unmanned aerial vehicle |
| CN113184167B (en) * | 2021-05-24 | 2022-08-02 | 北京航空航天大学 | Coaxial equidirectional propeller with variable phase difference |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5054998A (en) * | 1988-09-30 | 1991-10-08 | The Boeing Company, Inc. | Thrust reversing system for counter rotating propellers |
| CN201907646U (en) * | 2010-11-25 | 2011-07-27 | 沈武铮 | Full-rotation propelling device for rotating propellers with front-rear propellers with adjustable power and rotating speed |
| CN204916160U (en) * | 2015-06-23 | 2015-12-30 | 胡茂东 | Coaxial anti - oar |
| CN105523160A (en) * | 2016-01-05 | 2016-04-27 | 上海船舶研究设计院 | Hub connecting structure of forward propeller and rear propeller of contrarotating propeller |
| CN108327899A (en) * | 2018-01-29 | 2018-07-27 | 陈铭 | A kind of coaxial double-oar helicopter rotor method for arranging and coaxial double-oar helicopter up and down |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20090026310A1 (en) * | 2007-07-23 | 2009-01-29 | Linn Romeo S | Variable pitch anti torque coaxial counter rotation bi-prop rotor |
| FR3009578B1 (en) * | 2013-08-12 | 2018-06-15 | Safran Aircraft Engines | ASSEMBLY FOR CONTROLLING THE VARIATION OF THE STEP OF A TURBOMACHINE PROPELLER, AND TURBOMACHINE EQUIPPED WITH SUCH AN ASSEMBLY |
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2019
- 2019-07-10 CN CN201910618320.6A patent/CN110422318B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5054998A (en) * | 1988-09-30 | 1991-10-08 | The Boeing Company, Inc. | Thrust reversing system for counter rotating propellers |
| CN201907646U (en) * | 2010-11-25 | 2011-07-27 | 沈武铮 | Full-rotation propelling device for rotating propellers with front-rear propellers with adjustable power and rotating speed |
| CN204916160U (en) * | 2015-06-23 | 2015-12-30 | 胡茂东 | Coaxial anti - oar |
| CN105523160A (en) * | 2016-01-05 | 2016-04-27 | 上海船舶研究设计院 | Hub connecting structure of forward propeller and rear propeller of contrarotating propeller |
| CN108327899A (en) * | 2018-01-29 | 2018-07-27 | 陈铭 | A kind of coaxial double-oar helicopter rotor method for arranging and coaxial double-oar helicopter up and down |
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| CN110422318A (en) | 2019-11-08 |
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