CN114735198A - Propeller structure and rapid development and shaping method - Google Patents
Propeller structure and rapid development and shaping method Download PDFInfo
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- CN114735198A CN114735198A CN202210471110.0A CN202210471110A CN114735198A CN 114735198 A CN114735198 A CN 114735198A CN 202210471110 A CN202210471110 A CN 202210471110A CN 114735198 A CN114735198 A CN 114735198A
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- 238000000034 method Methods 0.000 title claims abstract description 21
- 238000011161 development Methods 0.000 title claims abstract description 10
- 238000007493 shaping process Methods 0.000 title abstract description 6
- 239000011295 pitch Substances 0.000 claims abstract description 42
- 238000004519 manufacturing process Methods 0.000 claims abstract description 8
- 230000004308 accommodation Effects 0.000 claims abstract description 6
- 238000011056 performance test Methods 0.000 claims abstract description 6
- 238000010276 construction Methods 0.000 claims abstract 2
- 238000009434 installation Methods 0.000 claims description 24
- 238000012360 testing method Methods 0.000 claims description 23
- 238000013461 design Methods 0.000 claims description 10
- 238000012795 verification Methods 0.000 claims description 6
- 238000009826 distribution Methods 0.000 claims description 3
- 238000005259 measurement Methods 0.000 claims description 3
- 238000003825 pressing Methods 0.000 claims 1
- 229920000049 Carbon (fiber) Polymers 0.000 description 4
- 239000004917 carbon fiber Substances 0.000 description 4
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 description 4
- 230000008569 process Effects 0.000 description 4
- 238000012545 processing Methods 0.000 description 4
- 230000000694 effects Effects 0.000 description 3
- 230000000052 comparative effect Effects 0.000 description 2
- 230000007246 mechanism Effects 0.000 description 2
- 238000002360 preparation method Methods 0.000 description 2
- 230000008859 change Effects 0.000 description 1
- 230000001143 conditioned effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 230000013011 mating Effects 0.000 description 1
- 230000003647 oxidation Effects 0.000 description 1
- 238000007254 oxidation reaction Methods 0.000 description 1
- 238000012827 research and development Methods 0.000 description 1
- 238000004513 sizing Methods 0.000 description 1
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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
- B64C11/02—Hub construction
- B64C11/04—Blade mountings
- B64C11/06—Blade mountings for variable-pitch blades
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention discloses a propeller construction and rapid development and shaping method, which comprises a blade and a blade clamp; the positioning block also comprises a plurality of matching surfaces with different inclination angles; the two sides of the paddle clamp are provided with accommodating holes for accommodating the paddles, the paddle clamp is provided with positioning holes for installing the positioning blocks, the positioning holes are communicated with the accommodating holes, and the positioning blocks are detachably arranged in the positioning holes; the oar presss from both sides and is equipped with the location pivot with accommodation hole complex one end, thereby be equipped with on the location pivot with the fitting surface cooperation of locating piece realizes the spacing face of the radial positioning of location pivot. The invention can directly operate the positioning and fastening work of the screw pitch in an external field without a special large positioning tool; only one die is needed to manufacture one sample, and then performance tests can be rapidly carried out under different screw pitches and working conditions by adjusting the screw pitches.
Description
Technical Field
The invention relates to the technical field of aircrafts, in particular to a propeller structure and a rapid development and shaping method.
Background
The existing integrated carbon fiber propeller development process is that a corresponding design scheme is required to be processed into a sample after a mould is opened for each designed blade. This process requires sample preparation and testing of various comparative protocols at an early stage of development, which consumes considerable time and processing expense.
The existing blade scheme for manually adjusting the pitch needs a specific blade positioning tool to position the blade and then tighten the screw to compress the blade, and the positioning tool has a large positioning error due to the fact that the positioning tool is large in overall size and is in contact positioning with the surface of the carbon fiber blade. The positioning of the respective pitch can only be carried out at the factory or at an indoor conditioned control station, and the inability to carry out the pitch positioning operation at the outfield is less than the inability to adjust the propellers already mounted on the aircraft.
Disclosure of Invention
The invention aims to solve the problems that: the method for constructing and rapidly developing and shaping the propeller can directly operate the positioning and fastening work of the screw pitch in an external field without a special large positioning tool; only need open a pair mould preparation a pair sample then through adjusting the screw pitch just can carry out performance test under different screw pitches and operating mode condition fast.
The technical scheme provided by the invention for solving the problems is as follows: a propeller configuration comprising a blade and a blade clamp; the positioning block also comprises a plurality of matching surfaces with different inclination angles;
the two sides of the paddle clamp are provided with accommodating holes for accommodating the paddles, the paddle clamp is provided with positioning holes for installing the positioning blocks, the positioning holes are communicated with the accommodating holes, and the positioning blocks are detachably arranged in the positioning holes;
the oar presss from both sides and is equipped with the location pivot with accommodation hole complex one end, thereby be equipped with on the location pivot with the fitting surface cooperation of locating piece realizes the spacing face of the radial positioning of location pivot.
Preferably, the oar presss from both sides including the oar and presss from both sides upper plate and oar and press from both sides the hypoplastron, the oar presss from both sides upper plate and the oar and presss from both sides all to be equipped with bolt hole one on the hypoplastron, be equipped with in the bolt hole one and be used for connecting the oar and press from both sides the bolt one that upper plate and oar pressed from both sides the hypoplastron.
Preferably, the positioning hole is formed in the upper end face of the upper plate of the paddle clamp, the positioning block and the lower plate of the paddle clamp are provided with second bolt holes, and the second bolt holes are used for connecting the positioning block and the lower plate of the paddle clamp.
Preferably, the positioning rotating shaft is cylindrical, and the limiting surface is arranged on the outer circumferential surface of the positioning rotating shaft.
Preferably, the circumferential surface of the positioning rotating shaft is provided with a positioning protrusion, and the accommodating hole is internally provided with an annular groove matched with the positioning protrusion.
It is a further object of the present invention to provide a method of development styling using an adjustable pitch propeller arrangement as defined in any of the above, said method comprising the steps of
S1, preparing multiple sets of blade schemes and manufacturing samples in a manufacturing stage at the initial stage of a project, wherein each sample integrates the same positioning rotating shaft structure at the root in advance, a plurality of sets of blade clamps with different installation lengths and a plurality of sets of positioning blocks with matching surfaces with different inclination angles are processed simultaneously, the maximum diameter of the blade can be adjusted after the blade clamps with different lengths are assembled by using the same blade, scheme verification of different blade lengths can be quickly realized in a short period, and the positioning blocks with matching surfaces with different inclination angles can quickly realize the installation and positioning of the blade with different screw pitches;
s2, the project enters the actual measurement stage, and the performance test of the motor or the engine matched with different blade schemes in the wind tunnel is carried out firstly; acquiring performance envelope lines of different blade schemes under different rotating speeds and different flow speeds under corresponding installation lengths and different installation screw pitches;
s3, at the stage of building the verification machine and actually measuring the flight, selecting several installation configurations with prior tests according to different blade scheme samples and performance envelope data of the wind tunnel test in the step S2 to carry out the actual flight test of the whole machine; recording, analyzing and comparing flight test data; after all needed configurations are tested, full data comparison and analysis are carried out, and blade configurations which are most suitable for all flight conditions of the prototype are evaluated;
and S4, finally, designing a blade scheme of a fixed pitch version aiming at the evaluated optimal blade configuration according to parameters under the common flight working condition and the blade performance envelope under each configuration in the wind tunnel.
Preferably, in step S1, the multiple sets of blade schemes are designed by using different local airfoils, chord length distributions and blade tips.
Preferably, in step S1, the paddle clips with different installation lengths and the positioning blocks with matching surfaces with different inclination angles can adjust corresponding blade performances, including tension and torque characteristics at different rotation speeds.
Preferably, in step S3, after the flight is completed, if it is found that it is necessary to adjust the blade installation parameters, the blade installation parameters can be replaced immediately on site, and then the newly configured flight test is supplemented.
Preferably, in step S4, designing a blade scheme with a fixed pitch version for the blade configuration that has been evaluated as optimal includes adjusting the airfoil-attack angle-chord length-tip design.
Compared with the prior art, the invention has the advantages that:
1. the invention can directly operate the positioning and fastening work of the screw pitch in an external field without a special large positioning tool.
2. The positioning is carried out by relying on the surface of a workpiece after CNC machining and anodic oxidation, the repeated positioning precision is high, the operation of replacing the positioning block is convenient and rapid, and the requirement on operators is low.
3. The positioning and fastening of different screw pitches can be quickly realized in a short time, so that a plurality of moulds of blade schemes do not need to be opened to manufacture samples, performance tests can be quickly carried out under different screw pitches and working conditions only by opening one mould to manufacture one sample and then adjusting the screw pitches, a large amount of mould opening cost and mould opening time can be saved, errors generated by the samples in different schemes can be greatly reduced, the final optimal scheme result and the final design target are misled, and the more basic schemes are, the more time and the cost are saved by the method.
4. To adorning the screw on the aircraft, unmanned aerial vehicle is because need the reliability high, and the simple and convenient easy maintenance of structure, low-cost requirement, and this technical scheme is very suitable for being used for unmanned aerial vehicle to adjust at the pitch of different flight conditions, for example in high altitude district, because the air is thin, the locating piece of the bigger pitch of quick replacement before taking off, just can obtain a section more suitable for the screw of plateau operating mode fast and satisfy corresponding user demand.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the invention and not to limit the invention.
FIG. 1 is an exploded view of the propeller structure of the present invention;
FIG. 2 is a top view of the propeller structure of the present invention;
FIG. 3 is a schematic view of the mounting mating surfaces of the present invention at 15, 5 and 0 degrees;
FIG. 4 is a schematic diagram of a development process of a prior art integrated carbon fiber propeller;
fig. 5 is a schematic view of the development process of the integrated carbon fiber propeller of the present invention.
The attached drawings are marked as follows: 1. the positioning device comprises a first bolt, a second bolt, a third bolt, a fourth bolt, a positioning block, a fourth bolt, a positioning rotating shaft, a fourth bolt, a positioning hole, a fourth bolt, a positioning rotating shaft, a fourth bolt, a fourth.
Detailed Description
The embodiments of the present invention will be described in detail with reference to the accompanying drawings and examples, so that how to implement the technical means for solving the technical problems and achieving the technical effects of the present invention can be fully understood and implemented.
In the description of the present invention, it should be noted that, for the terms of orientation, such as "central", "lateral", "longitudinal", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", etc., it indicates that the orientation and positional relationship shown in the drawings are based on the orientation or positional relationship shown in the drawings, and is only for the convenience of describing the present invention and simplifying the description, but does not indicate or imply that the device or element referred to must have a specific orientation, be constructed in a specific orientation, and be operated without limiting the specific scope of protection of the present invention.
Furthermore, if the terms "first" and "second" are used for descriptive purposes only, they are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features. Thus, a definition of "a first" or "a second" feature may explicitly or implicitly include one or more of the features, and in the description of the invention, "a number" means two or more unless explicitly defined otherwise.
In the present invention, unless otherwise expressly specified or limited, the terms "assembled", "connected", and "connected" are to be construed broadly, e.g., as meaning fixedly connected, detachably connected, or integrally connected; or may be a mechanical connection; the two elements can be directly connected or connected through an intermediate medium, and the two elements can be communicated with each other. The specific meanings of the above terms in the present invention can be understood by those of ordinary skill in the art according to specific situations.
Example 1
Detailed description of the inventionas shown in the drawings, a propeller configuration comprises a blade 7 and a blade clamp; the positioning block 4 is provided with a plurality of matching surfaces 5 with different inclination angles;
two sides of the paddle clamp are provided with accommodating holes for accommodating the paddles 7, the paddle clamp is provided with a positioning hole 14 for installing the positioning block 4, the positioning hole 14 is communicated with the accommodating holes, and the positioning block 4 is detachably arranged in the positioning hole 14;
the oar presss from both sides and is equipped with location pivot 10 with accommodation hole complex one end, thereby be equipped with on the location pivot 10 with the cooperation of fitting surface 5 of locating piece 4 realizes the spacing face 6 of the radial positioning (restriction location pivot rotation) of location pivot.
Further, in this embodiment, the oar presss from both sides upper plate 8 and oar and presss from both sides hypoplastron 9 including the oar, all be equipped with bolt hole one 13 on oar presss from both sides upper plate 8 and the oar presss from both sides hypoplastron 9, be equipped with bolt one 1 that is used for connecting oar clamp upper plate 8 and oar and presss from both sides hypoplastron 9 in the bolt hole one 13.
Further, in this embodiment, the positioning hole 14 is disposed on the upper end surface of the paddle clamp upper plate 8, the positioning block 4 and the paddle clamp lower plate 9 are provided with a second bolt hole 3, and the second bolt hole 3 for connecting the positioning block 4 and the paddle clamp lower plate 9 is disposed in the second bolt hole 3.
Further, in this embodiment, the positioning rotating shaft 10 is cylindrical, and the limiting surface 6 is disposed on the outer circumferential surface of the positioning rotating shaft 10.
Further, in this embodiment, be equipped with the location arch on the periphery of location pivot 10, the accommodation hole is including setting up at the half slot 12 that the terminal surface presss from both sides terminal surface under the upper plate and oar pressed from both sides the upper end surface of hypoplastron at the oar, be equipped with in the half slot 12 with protruding complex annular groove 11 in location.
Example 2
A method of developing and sizing a propeller configuration, the method comprising the steps of
1. At the manufacturing stage of the initial stage of the project, at least 2 to 3 sets of blade schemes are prepared and samples are manufactured (several schemes are preferred main schemes, different local wing profiles are used, chord length distribution and blade tip design are adopted), each scheme integrates the same positioning rotating shaft structure at the root in advance, and several sets of blade clamps with different installation lengths and several sets of positioning blocks with different angles are manufactured. The maximum diameter of the paddle can be adjusted after the paddle clamps with different lengths are assembled by using the same paddle, and scheme verification of different paddle lengths can be quickly realized in a short period. The positioning blocks at different angles can quickly realize the installation and positioning of the blades at different pitches. Both of which can adjust the corresponding blade performance including drag and torque characteristics at different rotational speeds.
2. And (3) when the project enters an actual measurement stage, firstly, a motor (engine) is matched with different blade schemes for performance test in the wind tunnel. And acquiring performance envelopes of different blade schemes under different rotating speeds-different incoming flow speeds under corresponding installation lengths and different installation screw pitches.
3. At the stage of building the verification machine and actually measuring the flight, different blade scheme samples are respectively used, and according to performance envelope data of previous wind tunnel tests, installation configurations of a plurality of prior tests (for example, configurations under a plurality of installation lengths and a plurality of installation screw pitches) are selected to carry out actual flight tests of the whole machine. The comparative flight test data was recorded and analyzed. After the flight is finished, if necessary adjustment of blade installation parameters is found, the blade can be replaced on site immediately, and then a newly configured flight test is supplemented. And after all needed configurations are tested, carrying out sufficient data comparison and analysis, and evaluating the blade configuration which is most suitable for each flight condition of the prototype.
4. And then designing a blade scheme of a fixed pitch version aiming at the evaluated optimal blade configuration according to parameters under the common flight working condition and the blade performance envelope under each configuration in the wind tunnel, wherein the scheme comprises the adjustment of airfoil profile-angle of attack-chord length-blade tip design and the like. Because the actual samples are tested before, the finally verified performance of the subsequent new optimized scheme is basically close to the final design requirement, and the research and development risk is greatly reduced.
The improvement effect is as follows.
1. The aircraft and blade performance is verified faster by developers in preliminary prototype tests, and the attack angle-chord length design of the blade allows better performance in a wider working range. The blade pitch is adjustable, and the special structure of this scheme allows at the on-the-spot manual regulation blade pitch of test, tests out the blade performance under the different pitch fast, and then tests out the matching nature of driving motor (or engine) under the different blade performance to and the flight characteristic of aircraft under the different pitch. The pitch adjusting structure allows the paddle not to be detached from a driving motor (or an engine), does not need a specific large-size positioning tool, and only needs a very small positioning block (corresponding positioning blocks are manufactured according to different angles in advance, and the cost is very low) to be mounted by selecting the specification of a specified pitch angle. Therefore, 5-10 schemes may need to be developed and samples are manufactured before, and only 1-2 schemes and corresponding samples are needed to realize the shaping of the final scheme, so that the processing cost of the die, the finished product manufactured by the samples and the time cost of the experimental test are obviously reduced, wherein the processing cost of the die is not reduced by 50-90%, the processing time of the samples is reduced by more than 80%, and the time of the experimental test is reduced by 30% -50%.
2. It is known in the art to use a continuously variable pitch mechanism (such as a hydraulic or steering engine drive) to effect pitch adjustment during flight testing, but this requires a complete set of variable pitch hubs, which requires that the engine or motor driving the propeller must be a hollow shaft and that there must be sufficient space inside the engine or motor compartment to accommodate the drive mechanism and the piping. This is difficult to achieve for certain smaller size aircraft and very costly for large aircraft. The manual adjusting structure can quickly realize variable pitch and accurate positioning, and does not need additional positioning tool design.
3. The propeller has great performance difference under different altitudes and different temperature and humidity environments, and can be more easily adapted to different environments through the function of adjustable pitch. Especially under the high altitude condition, need not prepare in addition to design the paddle to the coarse pitch under the high altitude operating mode, only need to change the locating piece and adjust can satisfy new operating mode requirement behind the bigger pitch.
The foregoing is merely illustrative of the preferred embodiments of the present invention and is not to be construed as limiting the claims. The present invention is not limited to the above embodiments, and its specific structure is allowed to vary. All changes which come within the scope of the invention as defined by the independent claims are intended to be embraced therein.
Claims (10)
1. A propeller construction comprising a blade (7) and a blade clip; the method is characterized in that: the positioning device also comprises a plurality of positioning blocks (4) with matching surfaces (5) with different inclination angles;
accommodating holes for accommodating the paddles (7) are formed in two sides of the paddle clamp, positioning holes (14) for installing the positioning blocks (4) are formed in the paddle clamp, the positioning holes (14) are communicated with the accommodating holes, and the positioning blocks (4) are detachably arranged in the positioning holes (14);
the oar presss from both sides and is equipped with location pivot (10) with accommodation hole complex one end, be equipped with on location pivot (10) with thereby realize location pivot's radial positioning's spacing face (6) with fitting surface (5) cooperation of locating piece (4).
2. A propeller arrangement according to claim 1, wherein: the oar presss from both sides including the oar and presss from both sides upper plate (8) and oar and press from both sides hypoplastron (9), the oar presss from both sides upper plate (8) and oar and all is equipped with bolt hole one (13) on pressing from both sides hypoplastron (9), be equipped with in bolt hole one (13) and be used for connecting oar and press from both sides upper plate (8) and oar and press from both sides bolt one (1) of hypoplastron (9).
3. A propeller arrangement according to claim 2, wherein: the locating hole (14) sets up the up end of oar clamp upper plate (8), be equipped with bolt hole two (3) on locating piece (4) and the oar clamp hypoplastron (9), be equipped with bolt hole two (3) that are used for connecting locating piece (4) and oar clamp hypoplastron (9) in bolt hole two (3).
4. A propeller arrangement according to claim 1, wherein: the positioning rotating shaft (10) is cylindrical, and the limiting surface (6) is arranged on the outer circumferential surface of the positioning rotating shaft (10).
5. A propeller arrangement according to claim 2, wherein: be equipped with location arch (15) on the periphery of location pivot (10), the accommodation hole is including setting up semicircle groove (12) that terminal surface and oar pressed from both sides the hypoplastron up end under the oar pressed from both sides the upper plate, be equipped with in semicircle groove (12) with protruding (15) complex annular groove (11) in location.
6. A method of development styling using an adjustable pitch propeller arrangement as claimed in any one of claims 1 to 5, characterised in that: the method comprises the following steps
S1, preparing multiple sets of blade schemes and manufacturing samples in a manufacturing stage at the initial stage of a project, wherein each sample integrates the same positioning rotating shaft structure at the root in advance, a plurality of sets of blade clamps with different installation lengths and a plurality of sets of positioning blocks with matching surfaces with different inclination angles are processed simultaneously, the maximum diameter of the blade can be adjusted after the blade clamps with different lengths are assembled by using the same blade, scheme verification of different blade lengths can be quickly realized in a short period, and the positioning blocks with matching surfaces with different inclination angles can quickly realize the installation and positioning of the blade with different screw pitches;
s2, the project enters the actual measurement stage, and the performance test of the motor or the engine matched with different blade schemes in the wind tunnel is carried out firstly; acquiring performance envelope lines of different blade schemes under different rotating speeds and different flow speeds under corresponding installation lengths and different installation screw pitches;
s3, at the stage of building the verification machine and actually measuring the flight, selecting several installation configurations with prior tests according to different blade scheme samples and performance envelope data of the wind tunnel test in the step S2 to carry out the actual flight test of the whole machine; recording and analyzing and comparing flight test data; after all needed configurations are tested, performing sufficient data comparison and analysis, and evaluating the blade configuration most suitable for each flight condition of the prototype;
and S4, finally, designing a blade scheme of a fixed pitch version aiming at the evaluated optimal blade configuration according to parameters under the common flight working condition and the blade performance envelope under each configuration in the wind tunnel.
7. The method of developing a stereotype of claim 6, wherein: in step S1, the multiple sets of blade schemes are designed using different local airfoils, chord length distributions, and blade tips.
8. The method of developing a stereotype of claim 6, wherein: in step S1, the paddle clips with different installation lengths and the positioning blocks with matching surfaces with different inclination angles can adjust corresponding blade performances, including tension and torque characteristics at different rotation speeds.
9. The method of developing a stereotype of claim 6, wherein: in step S3, after the flight is completed, if it is found that it is necessary to adjust the blade installation parameters, the blade installation parameters can be replaced immediately on site, and then a newly configured flight test is supplemented.
10. The method of developing a stereotype of claim 6, wherein: in step S4, designing a fixed pitch version of the blade plan for the blade configuration that has been evaluated as optimal includes adjusting the airfoil-angle of attack-chord length-tip design.
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| CN202210471110.0A CN114735198B (en) | 2022-04-28 | 2022-04-28 | Propeller structure and rapid development and shaping method |
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| CN202210471110.0A CN114735198B (en) | 2022-04-28 | 2022-04-28 | Propeller structure and rapid development and shaping method |
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| CN217227899U (en) * | 2022-04-28 | 2022-08-19 | 南昌三瑞智能科技有限公司 | Propeller structure |
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