CN101112914A - 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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- CN101112914A CN101112914A CNA2007101214737A CN200710121473A CN101112914A CN 101112914 A CN101112914 A CN 101112914A CN A2007101214737 A CNA2007101214737 A CN A2007101214737A CN 200710121473 A CN200710121473 A CN 200710121473A CN 101112914 A CN101112914 A CN 101112914A
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- semicircular groove
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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 invention relates to a propeller suitable for an aviation airship, in particular to a propeller for a stratosphere of 11-32 Km and a low density of 0.36391-0.01323 Kg/m 3 Low Reynolds number Re =10 5 ～10 6 And the high-span flight is 0-32 Km, and the low-speed is 200-500 rpm.
Background
The blade shape of the existing propeller used for the aircraft is given according to the calculation result of a strip theory, the blade width b, the torsion angle x and the installation angle theta of the existing propeller are required to be nonlinearly and continuously changed in the length L direction of the blade, and the blade is reasonable in aerodynamics. Generally speaking, the twist angle x of the propeller is greatly changed, so that the propeller is time-consuming and labor-consuming to machine due to the requirements of light weight and structural strength, and the wing profile precision and strength of the blade are difficult to improve.
When the stratospheric low-dynamic aircraft flies, due to small atmospheric density and low air pressure, the propeller designed according to the conventional method has small thrust and low efficiency eta (eta =50% -65%). Meanwhile, in the lift-off and recovery processes, the efficiency eta and the thrust T of the propeller are also obviously influenced by large changes of pneumatic parameters (such as density rho, pressure P, temperature T and the like). Therefore, the research on the efficient propeller which is suitable for large-span flying high flight and stratosphere low-density atmospheric environment is developed, and the method has important significance for reducing energy requirements and flight loads and promoting the light weight of the overall design.
Disclosure of Invention
The invention aims to provide a low Reynolds number and high-efficiency three-blade propeller suitable for a stratosphere, and the three-blade propeller aims at the stratosphere H = 11-32 Km and the low density rho = 0.36391-0.01323 Kg/m 3 Low reynolds number Re =10 5 ～10 6 And large span flying height H 1 The flight environment of = 0-32 Km and the design requirement that the propeller efficiency reaches 80%, and the inventor designs a novel efficient three-blade propeller structure with a pointed tip tail large-belly shape by adopting an S1223 wing type based on a strip theory. The three-blade propeller has the advantages of high efficiency, light weight and strong adaptability.
The invention relates to a low Reynolds number and high-efficiency three-blade propeller suitable for a stratosphere, which consists of an A blade, a B blade, a C blade, a propeller cap, a propeller hub, a connecting piece and a connecting column, wherein the A blade, the B blade and the C blade have the same structure; the front end of the propeller hub is provided with a propeller cap, and the rear end of the propeller hub is provided with a connecting piece; the blade A, the blade B and the blade C are respectively arranged in a round hole A, a round hole B and a round hole C which are formed by the hub and the connecting piece, the round hole A is formed by a semicircular groove A arranged on the rear end face of the hub and a semicircular groove D arranged on the front end face of the connecting piece, the round hole B is formed by a semicircular groove B arranged on the rear end face of the hub and a semicircular groove E arranged on the front end face of the connecting piece, and the round hole C is formed by a semicircular groove C arranged on the rear end face of the hub and a semicircular groove F arranged on the front end face of the connecting piece; one end of the connecting column is clamped in a groove at the edge of the through hole of the circular boss of the connecting piece through a clamping pin, and the other end of the connecting column is connected with an output shaft of the motor through a coupler.
The diameter of the three-blade propeller is 4500-7500 mm, the utility factor is 62.3, the maximum chord length is 357-595 mm, the pulling force is 250-600N, and the efficiency is 80%.
Curve f of the relative thickness C/b of the A blades in the three-bladed propeller according to the invention 1 (r)＝38.7917-74.8483×r/R+40.36×(r/R) 2 。
Curve f of relative width b/D of A blade in three-blade propeller 2 (r)＝m c [-0.1495+1.25367×r/R-2.42365×(r/R) 2 In the formula, m c Blade type +1.86701 × (R/R) representing propeller 3 -0.5372×(r/R) 4 ]Form factor, m c ＝0.6～1.5。
The three-blade propeller has the advantages that: (1) Aiming at the design requirements of stratospheric atmospheric environment and efficiency reaching 80%, designing a blade with a sharp tip, a sharp tail and a large belly shape by adopting an S1223 wing type based on a strip theory; (2) Carbon fiber processing paddle and light alloy processing paddleThe hub effectively reduces the weight of the three-bladed propeller, thereby reducing energy requirements and flight loads; (3) The three-blade propeller pulling force is 250-600N, and the efficiency is 80%; (4) The three-blade propeller adopts a constant-torque variable-speed design scheme to adapt to stratosphere H = 11-32 Km and low density rho = 0.36391-0.01323 Kg/m 3 Low Reynolds number Re =10 5 ～10 6 And large span flying height H 1 And (4) a flying environment of 0-32 Km.
Drawings
Fig. 1 is a front view structural view of a propeller of the present invention.
Fig. 1A is a rear view structural view of the propeller of the present invention.
Figure 2 is a block diagram of the assembly of the cap, hub and connector.
Fig. 2A is a block diagram of the hub and connector assembled together without the cap.
Figure 2B is an exploded view of the hub, connectors, and attachment posts.
Figure 2C is a rear view of the paddle cap.
Figure 3 is a view of the hub back structure.
Fig. 4 is a front view of the connector.
Fig. 4A is a rear view of the connector.
Fig. 5 is a front view structural view of the blade.
Fig. 5A is a rear view structural view of the blade.
FIG. 6 is a graph of the relative thickness C/b of the A blade.
FIG. 7 is a graph of the relative width b/D of the A blade.
In the figure: 1.A blade 101, tip 102, root 103, tapered section
104. Flange 105 profile 2.B blade 3.C blade
4. Paddle cap 401, inner table 402.B round hole 403, connecting section 404 and internal thread
405.A circular hole 5, hub 501.A semicircular groove 502.B semicircular groove 503.C semicircular groove
504. Countersunk 505, rear end face 6, connector 601.D semicircular groove 602.E semicircular groove
603.F semi-circular groove 604, threaded hole 605, through hole 606, groove 607, front end face
608. Round boss 7, connecting column 701, bayonet 8, axis O9.A round hole
10.B round hole 11.C round hole
Detailed Description
The present invention will be described in further detail with reference to the drawings and examples.
The invention is a low Reynolds number, high-efficient three-bladed propeller suitable for stratosphere, (see fig. 1, 1A show) by A paddle 1, B paddle 2, C paddle 3, the blade cap 4, the propeller hub 5, the link 6 and the spliced pole 7 makes up, the A paddle 1, B paddle 2 and C paddle 3 structure are the same; (see fig. 2) the front end of hub 5 is fitted with a cap 4 (by means of the external thread of hub 5 being coupled with the internal thread 404 of the coupling section 403 of cap 4), and the rear end of hub 5 is fitted with a coupling 6 (by means of screws passing through the threaded holes 604 of coupling 6, through the countersunk holes 504 of hub 5, to couple hub 5 to coupling 6); (see fig. 2A) the a blade 1, the B blade 2, and the C blade 3 are respectively mounted in an a circular hole 9, a B circular hole 10, and a C circular hole 11 formed by the hub 5 and the connector 6, the a circular hole 9 is formed by an a semicircular groove 501 provided on the rear end surface 505 of the hub 5 and a D semicircular groove 601 provided on the front end surface 607 of the connector 6, the B circular hole 10 is formed by a B semicircular groove 502 provided on the rear end surface 505 of the hub 5 and an E semicircular groove 602 provided on the front end surface 607 of the connector 6, and the C circular hole 11 is formed by a C semicircular groove 503 provided on the rear end surface 505 of the hub 5 and an F semicircular groove 603 provided on the front end surface 607 of the connector 6; one end of the connecting column 7 is clamped in a groove 606 at the edge of a through hole 605 of a circular boss 608 of the connecting piece 6 through a clamping pin 701, and the other end of the connecting column 7 is connected with an output shaft of the motor through a coupler. In the invention, the output power of the motor is 6.5-15.5 kW, and the propeller rotating speed n = 200-500 rpm can be provided.
In the present invention, as shown in fig. 2C, the front surface of the paddle cap 4 is designed into a bullet shape, the back of the paddle cap is provided with an a circular hole 405, an inner table 401 is arranged in the a circular hole 405, the center of the inner table 401 is provided with a B circular hole 402 (the B circular hole 402 is used for allowing the connecting column 7 to have space under the driving of the motor so as to be rotated), and the connecting section 403 of the paddle cap 4 is provided with an internal thread 404.
In the present invention, as shown in fig. 3, the hub 5 is externally circular and internally regular hexagonal; the rear end face 505 of the propeller hub 5 is uniformly distributed with an A semicircular groove 501, a B semicircular groove 502 and a C semicircular groove 503, and two countersunk holes 504 are respectively arranged on two sides of the A semicircular groove 501, the B semicircular groove 502 and the C semicircular groove 503.
In the invention, as shown in fig. 4 and 4A, the outer part of the connecting piece 6 is a circular ring, the inner part is a regular hexagon, the center is provided with a circular boss 608, the middle of the circular boss 608 is a through hole 605 (for the connecting column 7 to pass through), and the edge of the through hole 605 is provided with a groove 606 (for the bayonet 701 on the connecting column 7 to be clamped); the front end surface 607 of the connecting piece 6 is uniformly distributed with a D semicircular groove 601, an E semicircular groove 602 and an F semicircular groove 603, and two threaded holes 604 are respectively arranged on two sides of the D semicircular groove 601, the E semicircular groove 602 and the F semicircular groove 603.
In the invention, as shown in fig. 5, 5A, 5B and 5C, one end of the blade a 1 is a blade root 102, the other end of the blade a 1 is a blade tip 101, a nonlinear geometric shape with a tip, a large abdomen and a tip tail is designed between the blade root 102 and the blade tip 101 based on a strip theory, and the twist angle of the propeller is 32.8 degrees; the propeller torsion angle is the difference between the installation angle of the propeller root and the installation angle of the propeller tip; a profile 105 appears on the blade due to the propeller twist angle between the root 102 and the tip 101; the outer edge of the propeller root 102 is a conical section 103, and the end surface of the conical section 103 is a flange 104; the section airfoil of the A blade 1 adopts an S1223 airfoil. When the propeller is assembled, the conical sections of the blades (the blade A1, the blade B2 and the blade C3) are clamped in the circular holes A9, B10 and C11, the three blades are prevented from falling out through the flange 104 when running at high speed, and meanwhile, the traditional fixed mounting method for the blades is solved, such as the matching of screws and nuts, the matching of pin holes and pins, rigid connection by welding and the like.
Curve f of the relative thickness C/b of the A blades 1 in the three-bladed propeller according to the invention 1 (r)＝38.7917-74.8483×r/R+40.36×(r/R) 2 R denotes the lutein radius and R denotes the propeller radius, see fig. 6.
Curve f of the relative width b/D of the A blades 1 in the three-bladed propeller according to the invention 2 (r)＝m c [-0.1495+1.25367×r/R-2.42365×(r/R) 2 Wherein R represents the phyllotacin radius, R represents +1.86701 × (R/R) 3 -0.5372×(r/R) 4 ]Radius of the propeller, m c Representing the blade form factor, m, of the propeller c =0.6 to 1.5, as shown in fig. 7.
The diameter of the three-blade propeller is 4500-7500 mm, the utility factor is 62.3, the maximum chord length is 357-595 mm, the pulling force is 250-600N, and the efficiency is 80%.
Through ground low-speed wind tunnel experiments, the three-blade propeller is proved to be suitable for stratosphere H = 11-32 Km and low density rho = 0.36391-0.01323 Kg/m 3 Low Reynolds number Re =10 5 ～10 6 And a large flying height H 1 And a flying environment where the velocity v =15 to 25m/s and 0 to 32 Km.
The three-blade propeller has low Reynolds number Re =10 through an aerodynamic performance test of the three-blade propeller 5 ～10 6 (conventional Re = 10) 6 ～10 7 Hence the present invention is referred to as low reynolds number). Due to the bladeThe aerodynamic optimization design of the three-blade propeller enables the three-blade propeller to have high efficiency of 80% (conventional efficiency eta =50% -65%).
Claims (6)
1. The utility model provides a be applicable to stratosphere low reynolds number, high-efficient three leaf screw which characterized in that: the propeller consists of a blade A (1), a blade B (2), a blade C (3), a propeller cap (4), a propeller hub (5), a connecting piece (6) and a connecting column (7), wherein the structures of the blade A (1), the blade B (2) and the blade C (3) are the same; the front end of the propeller hub (5) is provided with a propeller cap (4), and the rear end of the propeller hub (5) is provided with a connecting piece (6); the A blade (1), the B blade (2) and the C blade (3) are respectively arranged in an A round hole (9), a B round hole (10) and a C round hole (11) which are formed by a hub (5) and a connecting piece (6), the A round hole (9) is formed by an A semicircular groove (501) arranged on the rear end face (505) of the hub (5) and a D semicircular groove (601) arranged on the front end face (607) of the connecting piece (6), the B round hole (10) is formed by a B semicircular groove (502) arranged on the rear end face (505) of the hub (5) and an E semicircular groove (602) arranged on the front end face (607) of the connecting piece (6), and the C round hole (11) is formed by a C semicircular groove (503) arranged on the rear end face (505) of the hub (5) and an F semicircular groove (603) arranged on the front end face (607) of the connecting piece (6); one end of the connecting column (7) is clamped in a groove (606) at the edge of a through hole (605) of a circular boss (608) of the connecting piece (6) through a clamping pin (701), and the other end of the connecting column (7) is connected with an output shaft of the motor through a coupler;
the front surface of the paddle cap (4) is designed into a bullet shape, the back of the paddle cap is provided with an A round hole (405), an inner table top (401) is arranged in the A round hole (405), a B round hole (402) is arranged in the center of the inner table top (401), and an internal thread (404) is arranged on a connecting section (403) of the paddle cap (4);
the outer part of the propeller hub (5) is a circular ring, and the inner part of the propeller hub is a regular hexagon; a semicircular groove A (501), a semicircular groove B (502) and a semicircular groove C (503) are uniformly distributed on the rear end face (505) of the propeller hub (5), and two countersunk holes (504) are respectively formed in two sides of the semicircular groove A (501), the semicircular groove B (502) and the semicircular groove C (503);
the outer part of the connecting piece (6) is a circular ring, the inner part of the connecting piece is a regular hexagon, a circular boss (608) is arranged at the center of the connecting piece, a through hole (605) is arranged in the circular boss (608), and a groove (606) is arranged at the edge of the through hole (605); a D semicircular groove (601), an E semicircular groove (602) and an F semicircular groove (603) are uniformly distributed on the front end surface (607) of the connecting piece (6), and two threaded holes (604) are respectively formed in the two sides of the D semicircular groove (601), the E semicircular groove (602) and the F semicircular groove (603);
one end of the A blade (1) is a blade root (102), the other end of the A blade (1) is a blade tip (101), a pointed-end large-belly pointed tail is designed between the blade root (102) and the blade tip (101) based on a strip theory, and the torsion angle of the propeller is a nonlinear geometric shape of 32.8 degrees; a profile (105) is present on the blade due to the rotor twist angle between the root (102) and the tip 101; the outer edge of the paddle root (102) is a conical section (103), and the end surface of the conical section (103) is a flange (104).
2. The three-bladed propeller of claim 1, wherein: curve f of relative thickness C/b of A blades (1) in a three-bladed propeller 1 (r)＝38.7917-74.8483×r/R+40.36×(r/R) 2 。
3. The three-bladed propeller of claim 1, wherein: curve of relative width b/D of a blade (1) in a three-bladed propeller
In the formula (I), the compound is shown in the specification,
m c representing the blade form factor, m, of the propeller c ＝0.6～1.5。
4. The three-bladed propeller of claim 1 wherein: the section airfoil of the A blade (1) adopts an S1223 airfoil.
5. The three-bladed propeller of claim 1 wherein: the diameter of the three-blade propeller is 4500-7500 mm, the utility factor is 62.3, the maximum chord length is 357-595 mm, the lift force is 250-600N, and the efficiency is 80%.
6. The three-bladed propeller of claim 1, wherein: the three-blade propeller can be suitable for a stratosphere H = 11-32 Km, and the density rho = 0.36391-0.01323 Kg/m 3 Reynolds number Re =10 5 ～ 10 6 And large span flying height H 1 And (c) a flying environment where the flying speed v = 20-50 m/s is 0-32 Km.
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 |
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| Publication Number | Publication Date |
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| CN101112914A true CN101112914A (en) | 2008-01-30 |
| CN100497090C CN100497090C (en) | 2009-06-10 |
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| 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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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104684805A (en) * | 2014-05-21 | 2015-06-03 | 深圳市大疆创新科技有限公司 | Power device 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 |
| US10160538B2 (en) | 2013-05-31 | 2018-12-25 | SZ DJI Technology Co., Ltd. | Self-tightening rotor |
| 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 |
-
2007
- 2007-09-06 CN CNB2007101214737A patent/CN100497090C/en not_active Expired - Fee Related
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US10160538B2 (en) | 2013-05-31 | 2018-12-25 | SZ DJI Technology Co., Ltd. | Self-tightening rotor |
| US10196138B2 (en) | 2013-05-31 | 2019-02-05 | SZ DJI Technology Co., Ltd. | Self-tightening rotor |
| US10745119B2 (en) | 2013-05-31 | 2020-08-18 | SZ DJI Technology Co., Ltd. | Self-tightening rotor |
| US11267565B2 (en) | 2013-05-31 | 2022-03-08 | SZ DJI Technology Co., Ltd. | Self-tightening rotor |
| CN104684805A (en) * | 2014-05-21 | 2015-06-03 | 深圳市大疆创新科技有限公司 | Power device 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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| Publication number | Publication date |
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| CN100497090C (en) | 2009-06-10 |
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Granted publication date: 20090610 Termination date: 20120906 |