CN100497090C - Low-reynolds number highly effective three blade propeller adapted for stratosphere - Google Patents
Low-reynolds number highly effective three blade propeller adapted for stratosphere Download PDFInfo
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- CN100497090C CN100497090C CNB2007101214737A CN200710121473A CN100497090C CN 100497090 C CN100497090 C CN 100497090C CN B2007101214737 A CNB2007101214737 A CN B2007101214737A CN 200710121473 A CN200710121473 A CN 200710121473A CN 100497090 C CN100497090 C CN 100497090C
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- blade
- half slot
- propeller
- attaching parts
- circular hole
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Abstract
The invention discloses a high-efficiency three-blade propeller suitable for stratosphere low Reynolds number, consisting of an A blade, a B blade, a C blade, an oar cap, an oar hub, a connecting part and a connecting column; the A blade, the B blade and the C blade have the same structure; the front end of the oar hub is provided with the oar cap; the rear end of the oar hub is provided with the connecting part; the A blade, the B blade and the C blade are respectively arranged in an A round hole, a B round hole and a C round hole formed by the oar hub and the connecting part; the A round hole is formed by an A half-round trough arranged on the rear end surface of the oar hub and a D half-round trough arranged at the front end surface of the connecting part; the B round hole is formed by a B half-round trough arranged at the rear end surface of the oar hub and an E half-round trough arranged at the front end of the connecting part; the C round hole is formed by a C half-round trough arranged on the rear end surface of the oar hub and an F half-round trough arranged at the front end of the connecting part; one end of the connecting column is buckled in a concave trough at the edge of the through hole of a round convex platform of the connecting part by a clamp pin while the other end of the connecting column is connected with an output shaft of the motor by a coupler.
Description
Technical field
The present invention relates to a kind of screw propeller that is applicable to that the aviation dirigible uses, more particularly say, is at advection layer 11～32Km, lower density 0.36391～0.01323Kg/m
3, low reynolds number Re=10
5～10
6, stride the novel three bladed propeller structure of flying height 0m～32Km, slow speed of revolution 200～500rpm greatly.
Background technology
The existing screw propeller that is used for the aircraft use, it is leaf to provide according to strip theory result of calculation, it requires on blade length L direction, and its blade width b, torsional angle χ and stagger angle θ are that non-LINEAR CONTINUOUS changes, and this blade is rational on Pneu.Generally speaking,,, make the screw propeller processing time consuming take a lot of work, and the aerofoil profile precision of blade and intensity are difficult to improve because of the requirement of lightweight and structural strength because the torsional angle χ of screw propeller changes greatly.
During the low dynamic aircraft flight of advection layer, because atmospheric density is little, air pressure is low, and is little according to conventional approach design-calculated propeller thrust, efficiency eta (η=50%～65%) is on the low side.Simultaneously in lift-off, removal process, aerodynamic parameter
The bigger variation of (as density p, pressure P, temperature t etc.) also can bring appreciable impact to the efficiency eta and the thrust T of screw propeller.Therefore, carry out the high-performance airscrew research that the adaptation large span flies the peaceful fluid layer lower density air environment of high flight, to reducing energy demand and flight load, the lightness of promotion general design is significant.
Summary of the invention
The purpose of this invention is to provide a kind of stratospheric low reynolds number, efficient three bladed propeller of being applicable to, this three bladed propeller is at advection layer H=11～32Km, lower density ρ=0.36391～0.01323Kg/m
3, low reynolds number Re=10
5～10
6, stride flying height H greatly
1The flight environment of vehicle of=0m～32Km and propeller efficiency reach 80% designing requirement, and the contriver adopts the S1223 Airfoil Design to go out to have the new and effective three bladed propeller structure of the big abdominal configuration of tip fine stern based on strip theory.This three bladed propeller has efficiently, lightweight, adaptable advantage.
The present invention is a kind of stratospheric low reynolds number, efficient three bladed propeller of being applicable to, is made up of A blade, B blade, C blade, spinner, propeller hub, attaching parts and joint pin, and the structure of A blade, B blade and C blade is identical; The front end of propeller hub is equipped with spinner, and the rear end of propeller hub is equipped with attaching parts; A blade, B blade, C blade are installed in respectively in A circular hole that propeller hub and attaching parts form, B circular hole, the C circular hole, the D half slot that the A half slot that described A circular hole is provided with by the aft end face of propeller hub and the front end face of attaching parts are provided with forms, the E half slot that the B half slot that described B circular hole is provided with by the aft end face of propeller hub and the front end face of attaching parts are provided with forms, and the F half slot that the C half slot that described C circular hole is provided with by the aft end face of propeller hub and the front end face of attaching parts are provided with forms; One end of joint pin is fastened on by bayonet lock in the groove at through hole edge of boss platform of attaching parts, and the other end of joint pin is connected with the output shaft of motor by coupler.
Three bladed propeller diameter of the present invention is 4500～7500mm, the effectiveness factor 62.3, and maximum chord length 357～595mm, pulling force are 250～600N, efficient is 80%.
The curve f of the relative thickness C/b of the A blade in the three bladed propeller of the present invention
1(r)=38.7917-74.8483 * r/R+40.36 * (r/R)
2
The curve of the relative width b/D of the A blade in the three bladed propeller of the present invention
, shape coefficient, m
c=0.6～1.5.
The advantage of three bladed propeller of the present invention is: (1) reaches 80% designing requirement at advection layer air environment and efficient, goes out the blade of the big abdominal configuration of tip fine stern based on strip theory, employing S1223 Airfoil Design; (2) adopt carbon fiber processing blade, alloy in lightweight processing propeller hub to alleviate the weight of three bladed propeller effectively, thereby reduced energy demand and flight load; (3) the three bladed propeller pulling force is 250～600N, and efficient is 80%; (4) three bladed propeller has adopted and has decided square variable speed design scheme to adapt to advection layer H=11～32Km, lower density ρ=0.36391～0.01323Kg/m
3, low reynolds number Re=10
5～10
6, stride flying height H greatly
1The flight environment of vehicle of=0m～32Km.
Description of drawings
Fig. 1 is the main TV structure figure of screw propeller of the present invention.
Figure 1A is the backsight constructional drawing of screw propeller of the present invention.
Fig. 2 is the constructional drawing that spinner, propeller hub, attaching parts are assembled together.
The constructional drawing that propeller hub, attaching parts were assembled together when Fig. 2 A was no spinner.
Fig. 2 B is propeller hub, attaching parts, joint pin blast diagrammatic sketch.
Fig. 2 C is the spinner back view.
Fig. 3 is propeller hub structure figure.
Fig. 4 is the Facad structure figure of attaching parts.
Fig. 4 A is the structure figure of attaching parts.
Fig. 5 is blade master TV structure figure.
Fig. 5 A is a blade backsight constructional drawing.
Fig. 6 is the curve of the relative thickness C/b of A blade.
Fig. 7 is the curve of the relative width b/D of A blade.
Among the figure: 1.A blade 101. blade tips 102. blade roots 103. conical sections 104. flanges 105. profile 2.B blade 3.C blades 4. spinners 401. interior table top 402.D circular hole 403. linkage sections 404. internal thread 405.E circular holes 5. propeller hub 501.A half slot 502.B half slot 503.C half slots 504. counter sinks 505. rear end faces 6. connector 601.D half slot 602.E half slot 603.F half slots 604. screwed holes 605. through holes 606. grooves 607. front end faces 608. circular bosses 7. joint pins 701. bayonet locks 8. axle center O 9.A circular hole 10.B circular hole 11.C circular holes
The specific embodiment
The present invention is described in further detail below in conjunction with drawings and Examples.
The present invention is a kind of stratospheric low reynolds number, efficient three bladed propeller of being applicable to, (shown in Fig. 1, Figure 1A) is made up of A blade 1, B blade 2, C blade 3, spinner 4, propeller hub 5, attaching parts 6 and joint pin 7, and the structure of A blade 1, B blade 2 and C blade 3 is identical; The front end of (referring to shown in Figure 2) propeller hub 5 is equipped with spinner 4 (outside thread by propeller hub 5 is realized being connected with the negative thread of the linkage section 403 of spinner 4 404), and the rear end of propeller hub 5 is equipped with attaching parts 6 (passing counter sink 504 realizations being connected propeller hub 5 and attaching parts 6 of tapped bore 604, the propeller hub 5 of attaching parts 6 by screw); (shown in Fig. 2 A) A blade 1, B blade 2, C blade 3 is installed in the A circular hole 9 of propeller hub 5 and attaching parts 6 formation respectively, B circular hole 10, C circular hole interior 11, the A half slot 501 that described A circular hole 9 is provided with by the aft end face 505 of propeller hub 5 forms with the D half slot 601 that the front end face 607 of attaching parts 6 is provided with, the B half slot 502 that described B circular hole 10 is provided with by the aft end face 505 of propeller hub 5 forms with the E half slot 602 that the front end face 607 of attaching parts 6 is provided with, and the F half slot 603 that the C half slot 503 that described C circular hole 11 is provided with by the aft end face 505 of propeller hub 5 and the front end face 607 of attaching parts 6 are provided with forms; One end of joint pin 7 is fastened on by bayonet lock 701 in the groove 606 at through hole 605 edges of boss platform 608 of attaching parts 6, and the other end of joint pin 7 is connected with the output shaft of motor by coupler.In the present invention, the motor horsepower output is 6.5～15.5kW, and it can provide propeller speed n=200～500rpm.
In the present invention, shown in Fig. 2 C, the front of spinner 4 is designed to bullet shape, its back has E circular hole 405, table top 401 in being provided with in the E circular hole 405, the center of interior table top 401 is provided with D circular hole 402 (D circular hole 402 is used for supplying joint pin 7 to have living space can make rotation) under the drive of motor, the linkage section 403 of spinner 4 is provided with negative thread 404.
In the present invention, referring to shown in Figure 3, the outside of propeller hub 5 is an annulus, and inside is the hexagon of rule; Rectangular distribution is provided with A half slot 501, B half slot 502, C half slot 503 on the aft end face 505 of propeller hub 5, and has two counter sinks 504 in the both sides of A half slot 501, B half slot 502, C half slot 503.
In the present invention, shown in Fig. 4, Fig. 4 A, the outside of attaching parts 6 is an annulus, inside is the hexagon of rule, the center is provided with boss platform 608, is through hole 605 (passing through for joint pin 7) in the boss platform 608, and the edge of through hole 605 is provided with groove 606 (for 701 engagings of the bayonet lock on the joint pin 7); Rectangular distribution is provided with D half slot 601, E half slot 602, F half slot 603 on the front end face 607 of attaching parts 6, and has two tapped bore 604 in the both sides of D half slot 601, E half slot 602, F half slot 603.
In the present invention, shown in Fig. 5, Fig. 5 A, Fig. 5 B, Fig. 5 C, one end of A blade 1 is a blade root 102, the other end of A blade 1 is a blade tip 101, be based on strip theory between blade root 102 and the blade tip 101 and design the big belly of tip fine stern, and the screw propeller torsional angle is 32.8 ° a nonlinear geometry profile; Screw propeller torsional angle angle is angle poor of the stagger angle of the stagger angle of blade root and blade tip; Because the screw propeller torsional angle between blade root 102 and the blade tip 101 makes appearance one profile 105 on the blade; The outer rim of blade root 102 is conical sections 103, and the end face of conical section 103 is a flange 104; The cross section aerofoil profile of A blade 1 adopts the S1223 aerofoil profile.Screw propeller of the present invention is when assembling, be that the conical section on each blade (A blade 1, B blade 2 and C blade 3) is fastened in A circular hole 9, B circular hole 10, the C circular hole interior 11, three blades are when high-speed cruising, realize that by flange 104 blade is not fallen out, solved the fixed setting method of tradition simultaneously to blade, as adopting the cooperation of screw, nut, pin-and-hole cooperates with pin, and welding is rigidly connected etc.
The curve f of the relative thickness C/b of the A blade 1 in the three bladed propeller of the present invention
1(r)=38.7917-74.8483 * r/R+40.36 * (r/R)
2, r represents the foline radius, R represents propeller radius, referring to shown in Figure 6.
The curve of the relative width b/D of the A blade 1 in the three bladed propeller of the present invention
Show propeller radius, m
cThe blade type shape coefficient of expression screw propeller, m
c=0.6～1.5, referring to shown in Figure 7.
Three bladed propeller diameter of the present invention is 4500～7500mm, the effectiveness factor 62.3, and maximum chord length 357～595mm, pulling force are 250～600N, efficient is 80%.
Through the experiment of ground low speed wind tunnel, record three bladed propeller of the present invention and can be applicable to advection layer H=11～32Km, lower density ρ=0.36391～0.01323Kg/m
3, low reynolds number Re=10
5～10
6, stride flying height H greatly
1The flight environment of vehicle of=0m～32Km, flying speed v=15～25m/s.
By the aeroperformance test to three bladed propeller of the present invention, it has low reynolds number Re=10
5～10
6(conventional Re=10
6～10
7So the present invention is called low reynolds number).Because the Aerodynamic optimization design of blade makes three bladed propeller of the present invention have high efficiency 80% (conventional efficiency η=50%～65%).
Claims (4)
1, a kind of advection layer low reynolds number, efficient three bladed propeller of being applicable to, it is characterized in that: form by A blade (1), B blade (2), C blade (3), spinner (4), propeller hub (5), attaching parts (6) and joint pin (7), and A blade (1), B blade (2) and the structure of C blade (3) are identical; The front end of propeller hub (5) is equipped with spinner (4), and the rear end of propeller hub (5) is equipped with attaching parts (6); A blade (1), B blade (2), C blade (3) is installed in the A circular hole (9) of propeller hub (5) and attaching parts (6) formation respectively, B circular hole (10), in the C circular hole (11), the A half slot (501) that described A circular hole (9) is provided with by the aft end face (505) of propeller hub (5) forms with the D half slot (601) that the front end face (607) of attaching parts (6) is provided with, the B half slot (502) that described B circular hole (10) is provided with by the aft end face (505) of propeller hub (5) forms with the E half slot (602) that the front end face (607) of attaching parts (6) is provided with, and the F half slot (603) that the C half slot (503) that described C circular hole (11) is provided with by the aft end face (505) of propeller hub (5) and the front end face (607) of attaching parts (6) are provided with forms; One end of joint pin (7) is fastened on by bayonet lock (701) in the groove (606) at through hole (605) edge of boss platform (608) of attaching parts (6), and the other end of joint pin (7) is connected with the output shaft of motor by coupler;
The front of described spinner (4) is designed to bullet shape, its back has E circular hole (405), be provided with interior table top (401) in the E circular hole (405), the center of interior table top (401) is provided with D circular hole (402), and the linkage section (403) of spinner (4) is provided with negative thread (404);
The outside of described propeller hub (5) is an annulus, and inside is the hexagon of rule; The aft end face (505) of propeller hub (5) is gone up rectangular distribution and is provided with A half slot (501), B half slot (502), C half slot (503), and has two counter sinks (504) in the both sides of A half slot (501), B half slot (502), C half slot (503);
The outside of described attaching parts (6) is an annulus, and inside is the hexagon of rule, and the center is provided with boss platform (608), is through hole (605) in the boss platform (608), and the edge of through hole (605) is provided with groove (606); The front end face (607) of attaching parts (6) is gone up rectangular distribution and is provided with D half slot (601), E half slot (602), F half slot (603), and has two tapped bore (604) in the both sides of D half slot (601), E half slot (602), F half slot (603);
One end of described A blade (1) is blade root (102), the other end of A blade (1) is blade tip (101), be based on strip theory between blade root (102) and the blade tip (101) and design the big belly of tip fine stern, and the screw propeller torsional angle is 32.8 ° a nonlinear geometry profile; Because the screw propeller torsional angle between blade root (102) and the blade tip (101) makes appearance one profile (105) on the blade; The outer rim of blade root (102) is conical section (103), and the end face of conical section (103) is flange (104).
2, three bladed propeller according to claim 1 is characterized in that: the curve f of the relative thickness C/b of the A blade (1) in the three bladed propeller
1(r)=38.7917-74.8483 * r/R+40.36 * (r/R)
2, in the formula, r represents the foline radius, R represents propeller radius.
3, three bladed propeller according to claim 1 is characterized in that: the curve of the relative width b/D of the A blade (1) in the three bladed propeller
In the formula, r represents the foline radius, and R represents propeller radius, m
cThe blade type shape coefficient of expression screw propeller, m
c=0.6～1.5.
4, three bladed propeller according to claim 1 is characterized in that: the three bladed propeller diameter is 4500～7500mm, the effectiveness factor 62.3, and maximum chord length 357～595mm, lift are 250～600N, efficient is 80%.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2007101214737A CN100497090C (en) | 2007-09-06 | 2007-09-06 | Low-reynolds number highly effective three blade propeller adapted for stratosphere |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2007101214737A CN100497090C (en) | 2007-09-06 | 2007-09-06 | Low-reynolds number highly effective three blade propeller adapted for stratosphere |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101112914A CN101112914A (en) | 2008-01-30 |
| CN100497090C true CN100497090C (en) | 2009-06-10 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNB2007101214737A Expired - Fee Related CN100497090C (en) | 2007-09-06 | 2007-09-06 | Low-reynolds number highly effective three blade propeller adapted for stratosphere |
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Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN203306224U (en) | 2013-05-31 | 2013-11-27 | 深圳市大疆创新科技有限公司 | Propeller and aircraft provided with same |
| CN104684805B (en) * | 2014-05-21 | 2016-08-31 | 深圳市大疆创新科技有限公司 | A kind of power set and aircraft |
| CN106741974A (en) * | 2016-12-12 | 2017-05-31 | 惠阳航空螺旋桨有限责任公司 | A kind of propeller composite radome fairing |
| CN109606645A (en) * | 2018-12-28 | 2019-04-12 | 成都纵横大鹏无人机科技有限公司 | Paddle blade structure and unmanned plane |
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- 2007-09-06 CN CNB2007101214737A patent/CN100497090C/en not_active Expired - Fee Related
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| Publication number | Publication date |
|---|---|
| CN101112914A (en) | 2008-01-30 |
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Granted publication date: 20090610 Termination date: 20120906 |