CN114735198B - Propeller structure and rapid development and shaping method - Google Patents
Propeller structure and rapid development and shaping method Download PDFInfo
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- CN114735198B CN114735198B CN202210471110.0A CN202210471110A CN114735198B CN 114735198 B CN114735198 B CN 114735198B CN 202210471110 A CN202210471110 A CN 202210471110A CN 114735198 B CN114735198 B CN 114735198B
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- 238000000034 method Methods 0.000 title claims abstract description 20
- 238000011161 development Methods 0.000 title claims abstract description 17
- 238000007493 shaping process Methods 0.000 title abstract description 5
- 239000011295 pitch Substances 0.000 claims abstract description 39
- 238000004519 manufacturing process Methods 0.000 claims abstract description 8
- 238000011056 performance test Methods 0.000 claims abstract description 6
- 238000012360 testing method Methods 0.000 claims description 19
- 238000009434 installation Methods 0.000 claims description 14
- 238000013461 design Methods 0.000 claims description 12
- 238000012795 verification Methods 0.000 claims description 7
- 238000004513 sizing Methods 0.000 claims description 6
- 238000009826 distribution Methods 0.000 claims description 3
- 238000005259 measurement Methods 0.000 claims description 3
- 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
- 238000012545 processing Methods 0.000 description 4
- 230000013011 mating Effects 0.000 description 3
- 230000000052 comparative effect Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 230000007246 mechanism Effects 0.000 description 2
- 238000002360 preparation method Methods 0.000 description 2
- 238000005056 compaction Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 239000002360 explosive Substances 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 230000003647 oxidation Effects 0.000 description 1
- 238000007254 oxidation reaction Methods 0.000 description 1
Classifications
-
- 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
-
- 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
Landscapes
- 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 structure and a rapid development shaping method, comprising paddles and a paddle 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 paddle clamp is provided with a positioning rotating shaft at one end matched with the accommodating hole, and a limiting surface matched with the matching surface of the positioning block is arranged on the positioning rotating shaft so as to realize radial positioning of the positioning rotating shaft. The invention can directly operate the positioning and fastening work of the screw pitch in the external field without a special large positioning tool; only one auxiliary mould is required to be opened to manufacture one auxiliary sample, and then the performance test 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 development flow of the integrated carbon fiber propeller is that each blade is designed, the corresponding design scheme is opened out of a die and then a sample is processed. 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 manual pitch-adjusting blade scheme requires a specific blade positioning tool to position the blade and then tightly tightening the screw for compaction, and the positioning tool can form a large positioning error due to the fact that the whole size is large and the positioning tool is in contact with the surface of the carbon fiber blade. The positioning of the corresponding pitch can only be performed at a factory or at an indoor conditional operating station, and the pitch positioning operation cannot be performed at an external field, and the adjustment of the propeller already mounted on the aircraft cannot be performed.
Disclosure of Invention
The invention aims to solve the problems that: the screw propeller structure and the rapid development shaping method can directly operate the positioning and fastening work of the screw pitch in an external field without a special large positioning tool; only one auxiliary mould is required to be opened to manufacture one auxiliary sample, and then the performance test can be rapidly carried out under different screw pitches and working conditions by adjusting the screw pitches.
The technical scheme provided by the invention for solving the problems is as follows: a propeller arrangement 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 paddle clamp is provided with a positioning rotating shaft at one end matched with the accommodating hole, and a limiting surface matched with the matching surface of the positioning block is arranged on the positioning rotating shaft so as to realize radial positioning of the positioning rotating shaft.
Preferably, the paddle clamp comprises an upper paddle clamp plate and a lower paddle clamp plate, wherein first bolt holes are formed in the upper paddle clamp plate and the lower paddle clamp plate, and first bolts used for connecting the upper paddle clamp plate and the lower paddle clamp plate are arranged in the first bolt holes.
Preferably, the positioning hole is formed in the upper end face of the upper plate of the paddle clamp, a second bolt hole is formed in the positioning block and the lower plate of the paddle clamp, and a second bolt hole for connecting the positioning block and the lower plate of the paddle clamp is formed in the second bolt hole.
Preferably, the positioning rotating shaft is cylindrical, and the limiting surface is arranged on the outer circumferential surface of the positioning rotating shaft.
Preferably, a positioning protrusion is arranged on the circumferential surface of the positioning rotating shaft, and an annular groove matched with the positioning protrusion is arranged in the accommodating hole.
Another object of the present invention is to provide a method of development and sizing using the adjustable pitch propeller configuration as described in any one of the above, the method comprising the steps of
S1, preparing a plurality of sets of blade schemes and manufacturing samples at the initial manufacturing stage of a project, wherein each sample is integrated with the same positioning rotating shaft structure at the root part in advance, simultaneously, 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, the maximum diameters of the blades can be adjusted after the blade clamps with different lengths are assembled by using the same blade, the scheme verification of different blade lengths can be rapidly realized in a short period, and the positioning blocks with the matching surfaces with different inclination angles can rapidly realize the installation and the positioning of the blades with different pitches;
s2, the project enters an actual measurement stage, and firstly, a motor or an engine is matched with performance tests of different blade schemes in a wind tunnel; acquiring performance envelope lines of different blade schemes under different rotating speeds and different flow speeds under corresponding installation lengths and installation pitches;
S3, when the stage of building the verification machine and actually measuring the flight is reached, respectively using different blade scheme samples and selecting a plurality of mounting configurations which are tested in priority according to performance envelope data of the hole test in the step S2 to carry out actual flight test of the whole machine; recording and analyzing and comparing flight test data; after all required configurations are tested, carrying out full data comparison analysis, and evaluating the blade configuration most suitable for each flight working condition of the prototype;
And S4, finally, designing a blade scheme with a fixed pitch version according to the parameters under the common flight working condition and the blade performance envelope under each configuration in the wind tunnel, and aiming at the blade configuration which is evaluated to be optimal.
Preferably, in the step S1, the multiple blade set schemes are multiple blade sets designed by using different local airfoils, chord length distributions and blade tips.
Preferably, in step S1, the blade clamps with different mounting lengths and the positioning blocks with the mating surfaces with different inclination angles can adjust the performance of the corresponding blade, including the tension and torque characteristics at different rotation speeds.
Preferably, in the step S3, after the flight is completed, if it is found that it is necessary to adjust the blade installation parameters, the stand-up horse may be replaced on site, and then a newly configured flight test may be supplemented.
Preferably, in said step S4, the blade solution for designing a fixed pitch version for the blade configuration for which an optimum has been evaluated comprises an adjustment of the airfoil-angle of attack-chord-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 the external field without a special large positioning tool.
2. The workpiece surface after CNC machining and anodic oxidation is used for positioning, the repeatability positioning accuracy is high, the positioning block replacement operation is convenient and rapid, and the requirement on operators is low.
3. The method can quickly realize the positioning and fastening of different screw pitches in a short time, thus a mold for multiple blade schemes is not required to be opened, then a sample is manufactured, only a mold is required to be opened to manufacture a sample, then performance test can be quickly performed under different screw pitches and working conditions by adjusting the screw pitches, a large amount of mold opening cost and mold opening time can be saved, errors generated by the sample when different schemes are performed can be greatly reduced, the final optimal scheme result and design target are misled, and the more basic schemes are, the more time and cost are saved.
4. For the propeller arranged on the aircraft, the unmanned aerial vehicle has the advantages of high reliability, simple and convenient structure, easy maintenance and low cost, and the technical scheme is very suitable for adjusting the screw pitch of the unmanned aerial vehicle under different flight conditions, for example, in high altitude areas, due to thin air, the propeller which is more suitable for the plateau working condition can be quickly obtained and corresponding use requirements can be met by quickly replacing a positioning block with a larger screw pitch before taking off.
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 do not constitute a limitation on the invention.
FIG. 1 is a schematic view of the explosive structure of the propeller configuration of the present invention;
FIG. 2 is a top view of the propeller configuration of the present invention;
FIG. 3 is a schematic view of the 15 degree, 5 degree and 0 degree mating of the mounting mating surfaces of the present invention;
FIG. 4 is a schematic diagram of a development flow of a prior art integrated carbon fiber propeller;
fig. 5 is a schematic development flow of the integrated carbon fiber propeller of the present invention.
The drawings are marked: 1. a first bolt, a second bolt, a third bolt, a fourth bolt, a positioning block, a fourth matching surface, a fourth limiting surface, a fourth blade and a fourth blade clamping upper plate, 9, a paddle clamp lower plate, 10, a positioning rotating shaft, 11, an annular groove, 12, a semicircular groove, 13, a first bolt hole, 14, a positioning hole, 15 and a positioning protrusion.
Detailed Description
The following detailed description of embodiments of the present invention will be given with reference to the accompanying drawings and examples, by which the implementation process of how the present invention can be applied to solve the technical problems and achieve the technical effects can be fully understood and implemented.
In the description of the present invention, it should be noted that, for the azimuth words such as "center", "lateral", "longitudinal", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", etc., the azimuth and positional relationships are based on the azimuth or positional relationships shown in the drawings, it is merely for convenience of describing the present invention and simplifying the description, and it is not to be construed as limiting the specific scope of protection of the present invention that the device or element referred to must have a specific azimuth configuration and operation.
Furthermore, the terms "first," "second," and the like, are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features. Thus, the definition of "a first", "a second" or "a second" feature may explicitly or implicitly include one or more such feature, and in the description of the invention, the meaning of "a number" is two or more, unless otherwise specifically defined.
In the present invention, unless explicitly stated and limited otherwise, the terms "assembled," "connected," and "connected" are to be construed broadly, e.g., as being either fixedly connected, detachably connected, or integrally connected; or may be a mechanical connection; can be directly connected or connected through an intermediate medium, and can be communicated with the inside of the two elements. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art according to the specific circumstances.
Example 1
In a particular embodiment of the invention, shown in the drawings, a propeller construction comprises a blade 7 and a blade holder; the positioning block 4 also comprises a plurality of matching surfaces 5 with different inclination angles;
The two sides of the paddle clamp are provided with accommodating holes for accommodating the paddles 7, the paddle clamp is provided with positioning holes 14 for mounting the positioning blocks 4, the positioning holes 14 are communicated with the accommodating holes, and the positioning blocks 4 are detachably arranged in the positioning holes 14;
one end of the paddle clamp, which is matched with the accommodating hole, is provided with a positioning rotating shaft 10, and the positioning rotating shaft 10 is provided with a limiting surface 6 which is matched with the matching surface 5 of the positioning block 4 so as to realize radial positioning of the positioning rotating shaft (limit the rotation of the positioning rotating shaft).
Further, in this embodiment, the paddle clip includes an upper paddle clip plate 8 and a lower paddle clip plate 9, bolt holes 13 are formed in the upper paddle clip plate 8 and the lower paddle clip plate 9, and bolts 1 for connecting the upper paddle clip plate 8 and the lower paddle clip plate 9 are disposed in the first bolt holes 13.
Further, in this embodiment, the positioning hole 14 is disposed on an upper end surface of the upper paddle clip plate 8, the positioning block 4 and the lower paddle clip plate 9 are provided with a second bolt hole 3, and the second bolt hole 3 is provided with a second bolt hole 3 for connecting the positioning block 4 and the lower paddle clip plate 9.
Further, in this embodiment, the positioning shaft 10 is cylindrical, and the limiting surface 6 is disposed on an outer circumferential surface of the positioning shaft 10.
Further, in this embodiment, the circumferential surface of the positioning rotating shaft 10 is provided with a positioning protrusion, the accommodating hole includes a semicircular groove 12 disposed on the lower end surface of the upper plate of the paddle clamp and the upper end surface of the lower plate of the paddle clamp, and an annular groove 11 matched with the positioning protrusion is disposed in the semicircular groove 12.
Example 2
A method of developing and sizing a propeller configuration, the method comprising the steps of
1. At the initial manufacturing stage of the project, at least 2 to 3 sets of blade schemes are prepared and samples are manufactured (several schemes are preferable main schemes, different local wing profiles are used, chord length distribution and blade tip design), and each scheme is integrated with the same positioning rotating shaft structure at the root in advance, so that several sets of blade clamps with different mounting lengths and several sets of positioning blocks with different angles are manufactured. The paddle clamps with different lengths can adjust the maximum diameter of the paddles after being assembled by using the same paddles, and can rapidly realize scheme verification of different paddle lengths in a short period. The positioning blocks with different angles can quickly realize the installation and positioning of the blades with different pitches. Both can adjust corresponding paddle performance, including pulling force, torque characteristic at different rotational speeds.
2. The project enters the actual measurement stage, firstly, the motor (engine) is matched with the performance test of different blade schemes in the wind tunnel. And obtaining the performance envelope of different blade schemes under different rotating speeds-different incoming flow speeds of the corresponding installation lengths and installation pitches.
3. And at the stage of building the verification machine and actually measuring the flight, selecting a plurality of mounting configurations (such as configurations under a plurality of mounting lengths and a plurality of mounting pitches) with priority to perform actual flight test of the whole machine by using different blade scheme samples and according to the performance envelope data of the previous wind tunnel test. The comparative flight test data was recorded and analyzed. After the flight is completed, if the blade installation parameters are found to be necessary to adjust, the horses can be replaced on site, and then newly configured flight tests are supplemented. After all the needed configurations are tested, the full data comparison analysis is carried out, and the blade configuration most suitable for each flight working condition of the prototype is estimated.
4. And then, according to parameters under the common flight working condition and blade performance envelope lines under each configuration in the wind tunnel, designing a blade scheme with a fixed pitch version for the blade configuration which has been evaluated to be optimal, wherein the blade scheme comprises wing profile-angle of attack-chord length-blade tip design adjustment and the like. Because there has been a prior test of the actual sample, the performance of the final verification of the subsequent new optimized solution has been substantially close to the final design requirements, greatly reducing the risk of development.
The improvement effect is as follows.
1. Helping developers verify the performance of the aircraft and the blade in preliminary prototype testing more quickly, and the attack angle-chord design of the blade allows better performance in a wider working range. The special structure of the scheme allows the blade pitch to be manually adjusted at a test site, so that the blade performance under different pitches is rapidly tested, and then the matching performance of a driving motor (or an engine) under different blade performances and the flight characteristics of an aircraft under different pitches are tested. The pitch adjusting structure allows the blade to be assembled and disassembled from the driving motor (or the engine) without a specific large-size positioning tool, and only a small positioning block (corresponding positioning blocks are prepared in advance according to different angles, so that the cost is extremely low) is required to be assembled by adopting the specification of a specified pitch angle. Thus, 5-10 schemes may need to be developed and samples are prepared in the past, and the final scheme can be shaped by only 1-2 schemes and corresponding samples, so that the mold processing cost, the sample preparation finished product and the experimental test time cost are obviously reduced, wherein the mold processing is not reduced by 50-90%, the sample processing time is reduced by more than 80%, and the experimental test time is reduced by 30-50%.
2. The prior art has available continuous pitch control mechanisms (such as hydraulic or steering drives) for pitch adjustment in flight testing, but that requires a complete set of pitch hubs, which requires that the engine or motor driving the propeller must be a hollow shaft and that there be sufficient space within the nacelle or motor compartment to accommodate the drive mechanism and piping. This is difficult to achieve for some smaller sized aircraft, and is very costly for large aircraft. The manual adjustment structure of the scheme can quickly realize distance changing and accurate positioning, and does not need additional positioning tool design.
3. The propeller has larger performance difference under different altitudes and different temperature and humidity environments, and can be more easily adapted to different environments through the function of adjusting the pitch. Especially under the high altitude condition, the blade is not required to be designed for the large pitch under the high altitude working condition, and the new working condition requirement can be met only by replacing the positioning block to adjust the larger pitch.
The foregoing is 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 the specific structure thereof is allowed to vary. All changes which come within the meaning and range of equivalency of the claims are to be embraced within their scope.
Claims (10)
1. A propeller arrangement comprising a blade (7) and a blade clamp; the method is characterized in that: the positioning block (4) also comprises a plurality of matching surfaces (5) with different inclination angles;
The two sides of the paddle clamp are provided with accommodating holes for accommodating the paddles (7), the paddle clamp is provided with positioning holes (14) for mounting the positioning blocks (4), the positioning holes (14) are communicated with the accommodating holes, and the positioning blocks (4) are detachably arranged in the positioning holes (14);
One end of the paddle clamp, which is matched with the accommodating hole, is provided with a positioning rotating shaft (10), and the positioning rotating shaft (10) is provided with a limiting surface (6) which is matched with the matching surface (5) of the positioning block (4) so as to realize radial positioning of the positioning rotating shaft;
the screw pitch is adjustable to the screw structure, the screw structure is used for realizing quick development design method, quick development design method includes:
S1, preparing a plurality of sets of blade schemes and manufacturing samples at the initial manufacturing stage of a project, wherein each sample is integrated with the same positioning rotating shaft structure at the root part in advance, simultaneously, 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, the maximum diameters of the blades can be adjusted after the blade clamps with different lengths are assembled by using the same blade, the scheme verification of different blade lengths can be rapidly realized in a short period, and the positioning blocks with the matching surfaces with different inclination angles can rapidly realize the installation and the positioning of the blades with different pitches;
s2, the project enters an actual measurement stage, and firstly, a motor or an engine is matched with performance tests of different blade schemes in a wind tunnel; acquiring performance envelope lines of different blade schemes under different rotating speeds and different flow speeds under corresponding installation lengths and installation pitches;
S3, when the stage of building the verification machine and actually measuring the flight is reached, respectively using different blade scheme samples and selecting a plurality of mounting configurations which are tested in priority according to performance envelope data of the hole test in the step S2 to carry out actual flight test of the whole machine; recording and analyzing and comparing flight test data; after all required configurations are tested, carrying out full data comparison analysis, and evaluating the blade configuration most suitable for each flight working condition of the prototype;
And S4, finally, designing a blade scheme with a fixed pitch version according to the parameters under the common flight working condition and the blade performance envelope under each configuration in the wind tunnel, and aiming at the blade configuration which is evaluated to be optimal.
2. A propeller arrangement according to claim 1, wherein: the paddle clamp comprises an upper paddle clamp plate (8) and a lower paddle clamp plate (9), bolt holes I (13) are formed in the upper paddle clamp plate (8) and the lower paddle clamp plate (9), and bolts I (1) used for connecting the upper paddle clamp plate (8) and the lower paddle clamp plate (9) are arranged in the bolt holes I (13).
3. A propeller arrangement according to claim 2, wherein: the positioning hole (14) is formed in the upper end face of the upper paddle clamp plate (8), the positioning block (4) and the lower paddle clamp plate (9) are provided with a second bolt hole (3), and the second bolt hole (3) used for connecting the positioning block (4) and the lower paddle clamp plate (9) is arranged in the second bolt hole (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: the positioning rotary shaft (10) is characterized in that a positioning bulge (15) is arranged on the circumferential surface of the positioning rotary shaft (10), the accommodating hole comprises a semicircular groove (12) arranged on the lower end surface of the upper plate of the paddle clamp and the upper end surface of the lower plate of the paddle clamp, and an annular groove (11) matched with the positioning bulge (15) is arranged in the semicircular groove (12).
6. A rapid prototyping method, characterized in that it is implemented with a propeller configuration according to any one of claims 1-5.
7. The rapid development and sizing method according to claim 6, wherein: in the step S1, the multiple sets of blade schemes are multiple sets of blade schemes which use different local wing profiles, chord length distribution and blade tip designs.
8. The rapid development and sizing method according to claim 6, wherein: in step S1, the blade clamps with different mounting lengths and the positioning blocks with the matching surfaces with different inclination angles can adjust the corresponding blade performances, including the tension and torque characteristics at different rotation speeds.
9. The rapid development and sizing method according to claim 6, wherein: in the step S3, after the flight is completed, if it is found that it is necessary to adjust the blade installation parameters, the stand horse may be replaced on site, and then the newly configured flight test may be supplemented.
10. The rapid development and sizing method according to claim 6, wherein: in said step S4, the blade scheme of designing a fixed pitch version for the blade configuration that has been evaluated to be optimal comprises an adjustment of the airfoil-angle of attack-chord-tip design.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210471110.0A CN114735198B (en) | 2022-04-28 | 2022-04-28 | Propeller structure and rapid development and shaping method |
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| Application Number | Priority Date | Filing Date | Title |
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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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| CN114735198A CN114735198A (en) | 2022-07-12 |
| CN114735198B true CN114735198B (en) | 2024-04-26 |
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| WO2013011338A1 (en) * | 2011-07-18 | 2013-01-24 | Max Prop S.R.L. | Feathering propeller with adjustable abutment |
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| CN214986028U (en) * | 2021-04-13 | 2021-12-03 | 南昌三瑞智能科技有限公司 | Novel folding screw oar presss from both sides structure and unmanned aerial vehicle |
| CN113815842A (en) * | 2021-09-17 | 2021-12-21 | 南昌三瑞智能科技有限公司 | Propeller quick assembly disassembly structure and aircraft that is equipped with this structure |
| CN215475734U (en) * | 2021-10-12 | 2022-01-11 | 陕西星辰时代科技发展有限公司 | Unmanned aerial vehicle screw fixing device |
| CN217227899U (en) * | 2022-04-28 | 2022-08-19 | 南昌三瑞智能科技有限公司 | Propeller structure |
-
2022
- 2022-04-28 CN CN202210471110.0A patent/CN114735198B/en active Active
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4009874A (en) * | 1976-04-26 | 1977-03-01 | Emerson Dee Hughey | Propeller making apparatus |
| WO2013011338A1 (en) * | 2011-07-18 | 2013-01-24 | Max Prop S.R.L. | Feathering propeller with adjustable abutment |
| CN210413507U (en) * | 2019-06-21 | 2020-04-28 | 江西洪都航空工业集团有限责任公司 | Quick clamping and positioning device for angle head |
| WO2021016881A1 (en) * | 2019-07-30 | 2021-02-04 | 深圳市大疆创新科技有限公司 | Power assembly and unmanned aerial vehicle |
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| CN113815842A (en) * | 2021-09-17 | 2021-12-21 | 南昌三瑞智能科技有限公司 | Propeller quick assembly disassembly structure and aircraft that is equipped with this structure |
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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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| Publication number | Publication date |
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| CN114735198A (en) | 2022-07-12 |
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