CN113942642B - Helicopter blade with pneumatic pressure measurement sensor - Google Patents
Helicopter blade with pneumatic pressure measurement sensor Download PDFInfo
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- CN113942642B CN113942642B CN202111376485.0A CN202111376485A CN113942642B CN 113942642 B CN113942642 B CN 113942642B CN 202111376485 A CN202111376485 A CN 202111376485A CN 113942642 B CN113942642 B CN 113942642B
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- blade
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- pressure measurement
- pneumatic pressure
- helicopter
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- 238000009530 blood pressure measurement Methods 0.000 title claims abstract description 17
- 239000004744 fabric Substances 0.000 claims description 6
- 239000011521 glass Substances 0.000 claims description 6
- 230000005484 gravity Effects 0.000 claims description 5
- 239000003973 paint Substances 0.000 claims description 3
- 230000003068 static effect Effects 0.000 claims description 3
- 238000005507 spraying Methods 0.000 claims description 2
- 238000013461 design Methods 0.000 abstract description 6
- 238000011160 research Methods 0.000 abstract description 4
- 238000011161 development Methods 0.000 abstract description 3
- 238000005259 measurement Methods 0.000 abstract description 3
- 238000000034 method Methods 0.000 abstract description 2
- 238000004519 manufacturing process Methods 0.000 abstract 1
- 238000012545 processing Methods 0.000 abstract 1
- 238000012360 testing method Methods 0.000 description 3
- 230000007547 defect Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000007789 sealing Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000000748 compression moulding Methods 0.000 description 1
- WABPQHHGFIMREM-UHFFFAOYSA-N lead(0) Chemical compound [Pb] WABPQHHGFIMREM-UHFFFAOYSA-N 0.000 description 1
- 230000000737 periodic effect Effects 0.000 description 1
- 230000010349 pulsation Effects 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
- 238000006467 substitution reaction Methods 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
- B64C27/46—Blades
- B64C27/467—Aerodynamic features
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L11/00—Measuring steady or quasi-steady pressure of a fluid or a fluent solid material by means not provided for in group G01L7/00 or G01L9/00
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Landscapes
- Physics & Mathematics (AREA)
- Engineering & Computer Science (AREA)
- Fluid Mechanics (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- General Physics & Mathematics (AREA)
- Force Measurement Appropriate To Specific Purposes (AREA)
- Measuring Fluid Pressure (AREA)
Abstract
The invention belongs to the technical field of helicopter rotor blade design, and discloses a helicopter blade with a pneumatic pressure measurement sensor. The sensor capable of measuring the dynamic pressure of the blade surface is arranged on the surface of the rotor blade, the sensor is fixed by adopting special wax, the shape and the shape of the pneumatic surface of the blade are maintained, and the data support is provided for the research on the influence relationship between the pneumatic noise of the rotor and the pulsating pressure of the blade surface through the development processes of pneumatic layout design, structural design, dynamic design, fatigue strength check and processing manufacture of the rotor blade, thereby realizing the accurate measurement of the dynamic pressure of the blade surface in the high-speed rotation state of the rotor.
Description
Technical Field
The invention belongs to the technical field of helicopter rotor blade design, and particularly relates to a helicopter blade with a pneumatic pressure measurement sensor.
Background
The rotor is a key component of the helicopter, the aerodynamic load on the blades of the rotor changes in an unsteady periodic manner during the operation of the rotor, and the unsteady pressure distribution on the surfaces of the blades of the rotor is directly measured, so that the rotor has a very important meaning for researching the aerodynamic performance and aerodynamic noise of the rotor. However, due to the high-speed rotation characteristic of the rotor wing, the pneumatic pressure of the blades at different spanwise positions is different under different rotation directions, and the characteristic of high-frequency change is presented; and because the blade rotates at a high speed and is accompanied with complex pitch-changing motion, waving, shimmy and torsional deformation, the airflow environment is extremely complex, and great difficulty is brought to high-frequency accurate measurement of the surface pressure of the blade.
The development of microchip pressure measuring sensor technology provides important technical support for rotor blade surface pressure measurement; the developed nations abroad begin the measurement and research of the surface pressure of the rotor blade very early, so that the pressure measurement of hundreds of measuring points of a single rotor is realized; the scientific research institutions in China begin to conduct the technical research of rotor blade surface dynamic pressure measurement from the last century, but are limited by sensors and test conditions, particularly, a large number of sensors are very difficult to arrange on the blade, and the pneumatic appearance of the blade surface and the structural parameters of the blade, namely the blade strength and the service life are easily damaged, so that the technology has slow development.
Disclosure of Invention
The invention relates to a helicopter blade with a pneumatic pressure measuring sensor, which is a rotor blade capable of measuring and obtaining high-frequency pulsation pressure on the surface of the blade.
A helicopter blade with a pneumatic pressure measurement sensor comprises four groups, wherein the four groups are distributed at (0.5+/-0.01) R, (0.75+/-0.01) R, (0.87+/-0.01) R and (0.95+/-0.01) R in turn along the span direction of a rotor, and R is the total length of the blade.
Further, the R sensor group (0.5+/-0.01) comprises eleven sensors, and the upper airfoil surface is distributed at 0.06c along the chord direction in sequence 1 、0.15c 1 、0.27c 1 、0.36c 1 、0.45c 1 、0.66c 1 C at 1 Blade chord length at (0.5+ -0.01) R; the lower airfoil surface is distributed at 0.11c along the chord direction 1 、0.22c 1 、0.32c 1 、0.5c 1 、0.72c 1 A place;
the sensors at (0.75 + -0.01) R and (0.87 + -0.01) R are arranged in the chord direction at the same positions as the sensors at (0.5 + -0.01) R are arranged in the chord direction;
the (0.95+/-0.01) R sensor group comprises six sensors, and the upper airfoil surface is distributed at 0.15c along the chord direction 2 、0.29c 2 、0.45c 2 、0.6c 2 C at 2 Blade chord length at (0.95+ -0.01) R; the lower airfoil surface is distributed at 0.22c along the chord direction 2 、0.36c 2 Where it is located.
Further, a sensor pressing groove is formed in each sensor arrangement position, and the connection part of the pressing groove and the blade surface is rounded.
Further, the surface of the blade is also provided with a wiring groove, and the wiring groove is used for accommodating a sensor connecting wire; .
Further, the sensor is secured within the sensor indent by wax and maintains the aerodynamic profile by the wax.
Further, the sensor connecting wires are arranged in the wiring grooves and then seal the wiring grooves through puttying, and the pneumatic appearance is maintained.
Further, the blade surface maintains the blade static balance by the secondary paint spray.
Further, placing 19.4g of a tuning weight on the blades 0.755R-0.863R to improve the dynamics of the rotor so that it does not resonate near the rated rotational speed;
further, a layer of 0/90 DEG and a layer of glass cloth with the thickness of + -45 DEG and 0.31mm are paved below the blade front edge skin, and two layers of glass cloth with the thickness of 0/90 DEG and 0.31mm are paved at the blade root, so that the defect of waving rigidity caused by blade pressing grooves is overcome, and the bearing capacity of the blade is improved.
Further, the counter weights are arranged in the front edge girders at the positions of 0.31R-0.49R, 0.51R-0.74R and 0.88R-0.94R of the blade to ensure that the counter weight of the chord-wise gravity center of the blade is 15.28g in total, so that the distance between the chord-wise gravity center of the blade and the chord-wise position of the pneumatic center of the blade is reduced, and the blade is ensured not to vibrate under the working states of each rotating speed and the total distance.
The invention has the beneficial effects that: the pressure measuring blade disclosed by the invention can realize pressure test of the blade surface in a rotor wing hovering state and a forward flying state through wind tunnel pressure measuring tests, the number of the blade pressure measuring sensors is large, the pneumatic pressure data of the rotor blade surface in a large range can be acquired and obtained for relevant theoretical analysis, and the pneumatic shape of the blade can be trimmed to be within a tolerance range of 0.2 mm; the damaged sensor can be replaced conveniently by adopting a wax sealing mode or replaced by a sensor with better performance.
Drawings
FIG. 1 is a schematic view of an airfoil chord-wise routing location layering;
FIG. 2 is a schematic cross-sectional lay-up of an airfoil section with sensors;
FIG. 3 is a schematic illustration of a groove of a bucket upper and lower airfoil arrangement.
Detailed Description
The helicopter blade with a pneumatic pressure measurement sensor according to the present invention will be described in further detail with reference to the accompanying drawings.
The diameter of the blade is 2m, the number of the blades is 5, the rotation direction is clockwise in overlook, no hinge connection exists, the chord length of the main wing section of the blade is 0.063m, the chord length of the root section is 32.76mm, the rated rotation speed is 2064r/min, and the OA series wing section is mainly adopted.
The blade surface pressure sensor is mainly arranged at the airfoil shape front edge and the blade outer side area with severe blade aerodynamic force change, and specifically comprises:
eleven sensors are arranged on the 0.5R section, and the upper airfoil surface is distributed on 0.06c in sequence along the chord direction 1 、0.15c 1 、0.27c 1 、0.36c 1 、0.45c 1 、0.66c 1 The lower airfoil surface is distributed at 0.11c along the chord direction 1 、0.22c 1 、0.32c 1 、0.5c 1 、0.72c 1 C at 1 The chord length of the blade at 0.5R, wherein R is the radius of the blade;
the chordwise placement of the sensors at 0.75R and 0.87R is the same as the chordwise placement of the sensors at 0.5R;
six sensors are arranged on the 0.95R section, and the upper airfoil surface is distributed on 0.15c in sequence along the chord direction 2 、0.29c 2 、0.45c 2 、0.6c 2 A place; the lower airfoil surface is distributed at 0.22c along the chord direction 2 、0.36c 2 C at 2 Is 0.95R blade chord length.
In order to achieve mass balance, a section of each blade is provided with a pressure sensor, redundant sensor pressing grooves are filled with mass blocks (wax blocks) which are equivalent to the mass and the size of the sensors, 39 pressure sensors are pre-embedded on 5 blades of the rotor, and the model of each sensor is a Kulite-LPS072 type sensor.
In the blade compression molding process, a pressing groove capable of being provided with a miniature pressure sensor is pre-pressed on the surface, the size of the pressing groove is 10mm (spanwise direction) 2mm (chordwise direction) 1.5mm (depth), and a rounded corner with the diameter of 0.45mm is arranged at the joint of the pressing groove and the blade surface.
In the aspect of pressure sensor lead wire scheme design, a scheme of conducting leads on a blade surface pressing groove is adopted. Firstly, arranging grooves of wire chordwise wires on the surfaces of the upper airfoil surface and the lower airfoil surface of the blade, so that sensor wires with the same section are led to the same chordwise position for concentration; grooves from the tip to the root are arranged in the radial direction of the blade, and sensor leads are led to the blade root from the chord-wise concentrated position through the radial grooves and led out to the data acquisition system from the root.
19.4g of frequency modulation counterweight is placed on 0.755R-0.863R of the blade, a layer of 0/90 DEG and a layer of glass cloth with the thickness of +/-45 DEG and 0.31mm are paved below the front edge skin of the blade, and two layers of glass cloth with the thickness of 0/90 DEG and 0.31mm are paved on the blade root so as to make up the defect of waving rigidity caused by blade pressing grooves and improve the bearing capacity of the blade; the balance weights are arranged in the front edge girders at the positions of 0.31R-0.49R, 0.51R-0.74R and 0.88R-0.94R of the blade to ensure the balance weight of the chord-wise gravity center of the blade, and the total of 15.28g is ensured, so that the distance between the chord-wise gravity center of the blade and the chord-wise position of the pneumatic center of the blade is reduced, and the blade is ensured not to flutter under the working conditions of each rotating speed and total distance.
The sensor and the wires thereof are fixed in the sensor pressing groove in a wax sealing mode, and the pneumatic shape is maintained through wax, so that the wiring groove is sealed through puttying, and the pneumatic shape is maintained.
And keeping the static balance of each blade by secondary paint spraying.
After the blade is designed, the phenomenon of unstable gas bomb can not occur in the range of each using rotating speed and total distance, and the service life of the blade is estimated to be 122 hours.
The foregoing is merely a detailed description of the invention, which is not a matter of routine skill in the art. However, the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily contemplated by those skilled in the art within the scope of the present invention should be included in the scope of the present invention. The protection scope of the present invention shall be subject to the protection scope of the claims.
Claims (8)
1. A helicopter blade with a pneumatic pressure measurement sensor, characterized by: the sensors comprise four groups, and are sequentially distributed at (0.5+/-0.01) R, (0.75+/-0.01) R, (0.87+/-0.01) R and (0.95+/-0.01) R along the span direction of the rotating blade, wherein R is the total length of the blade; the (0.5+/-0.01) R sensor group comprises eleven sensors, and the upper airfoil surface is distributed at 0.06c along the chord direction 1 、0.15c 1 、0.27c 1 、0.36c 1 、0.45c 1 、0.66c 1 C at 1 Blade chord length at (0.5+ -0.01) R; the lower airfoil surface is distributed at 0.11c along the chord direction 1 、0.22c 1 、0.32c 1 、0.5c 1 、0.72c 1 A place;
the sensors at (0.75 + -0.01) R and (0.87 + -0.01) R are arranged in the chord direction at the same positions as the sensors at (0.5 + -0.01) R are arranged in the chord direction;
the (0.95+/-0.01) R sensor group comprises six sensors, and the upper airfoil surface is distributed at 0.15c along the chord direction 2 、0.29c 2 、0.45c 2 、0.6c 2 C at 2 Blade chord length at (0.95+ -0.01) R; the lower airfoil surface is distributed at 0.22c along the chord direction 2 、0.36c 2 A place;
a sensor pressing groove is formed at each sensor arrangement position, and the sensor is fixed in the sensor pressing groove through wax and maintains the pneumatic shape through the wax.
2. The helicopter blade with a pneumatic pressure measurement sensor of claim 1 wherein: and the joint of the sensor pressing groove and the blade surface is rounded.
3. A helicopter blade with a pneumatic pressure measurement sensor as claimed in claim 2 wherein: the surface of the blade is also provided with a wiring groove, and the wiring groove is used for accommodating a sensor connecting wire.
4. A helicopter blade with a pneumatic pressure measurement sensor as claimed in claim 3 wherein: the sensor connecting wires are arranged in the wiring grooves and then seal the wiring grooves through puttying, and the pneumatic appearance is maintained.
5. The helicopter blade with a pneumatic pressure measurement sensor of claim 4 wherein: the static balance of the blade is maintained on the surface of the blade through secondary paint spraying.
6. The helicopter blade with a pneumatic pressure measurement sensor of claim 5 wherein: and placing a frequency modulation counterweight on the blade 0.755R-0.863R.
7. The helicopter blade with a pneumatic pressure measurement sensor of claim 6 wherein: a layer of 0/90 DEG and a layer of glass cloth with the thickness of +/-45 DEG and 0.31mm are paved below the blade front edge skin, and two layers of glass cloth with the thickness of 0/90 DEG and 0.31mm are paved at the blade root.
8. The helicopter blade with a pneumatic pressure measurement sensor of claim 7 wherein: the arrangement of the counterweight in the leading edge girder at the positions of 0.31R-0.49R, 0.51R-0.74R and 0.88R-0.94R ensures the counterweight of the chord-wise gravity center of the blade.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111376485.0A CN113942642B (en) | 2021-11-19 | 2021-11-19 | Helicopter blade with pneumatic pressure measurement sensor |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111376485.0A CN113942642B (en) | 2021-11-19 | 2021-11-19 | Helicopter blade with pneumatic pressure measurement sensor |
Publications (2)
| Publication Number | Publication Date |
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| CN113942642A CN113942642A (en) | 2022-01-18 |
| CN113942642B true CN113942642B (en) | 2023-09-08 |
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| Application Number | Title | Priority Date | Filing Date |
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Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4668169A (en) * | 1983-07-04 | 1987-05-26 | Westland Plc | Helicopter rotor blade |
| CN103712745A (en) * | 2013-12-26 | 2014-04-09 | 哈尔滨工业大学 | Device and device for measuring gravity center parameters of helicopter rotor blades |
| CN108082534A (en) * | 2017-12-03 | 2018-05-29 | 中国直升机设计研究所 | A kind of lifting airscrew combined load test fiber arrangement and group bridge method |
| EP3633154A1 (en) * | 2018-10-05 | 2020-04-08 | Safran Aero Boosters S.A. | Blade of an aircraft turbomachine including at least one pressure sensor |
| CN111537186A (en) * | 2020-06-23 | 2020-08-14 | 中国空气动力研究与发展中心低速空气动力研究所 | Helicopter rotor blade model with embedded pressure sensor and manufacturing process thereof |
| CN111579204A (en) * | 2020-05-29 | 2020-08-25 | 南京航空航天大学 | Sensing mechanism of two-dimensional airfoil model |
-
2021
- 2021-11-19 CN CN202111376485.0A patent/CN113942642B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4668169A (en) * | 1983-07-04 | 1987-05-26 | Westland Plc | Helicopter rotor blade |
| CN103712745A (en) * | 2013-12-26 | 2014-04-09 | 哈尔滨工业大学 | Device and device for measuring gravity center parameters of helicopter rotor blades |
| CN108082534A (en) * | 2017-12-03 | 2018-05-29 | 中国直升机设计研究所 | A kind of lifting airscrew combined load test fiber arrangement and group bridge method |
| EP3633154A1 (en) * | 2018-10-05 | 2020-04-08 | Safran Aero Boosters S.A. | Blade of an aircraft turbomachine including at least one pressure sensor |
| CN111579204A (en) * | 2020-05-29 | 2020-08-25 | 南京航空航天大学 | Sensing mechanism of two-dimensional airfoil model |
| CN111537186A (en) * | 2020-06-23 | 2020-08-14 | 中国空气动力研究与发展中心低速空气动力研究所 | Helicopter rotor blade model with embedded pressure sensor and manufacturing process thereof |
Non-Patent Citations (1)
| Title |
|---|
| 林永峰 ; 陈平剑 ; 招启军 ; .抛物线后掠桨尖旋翼悬停气动特性试验及理论分析研究.直升机技术.2008,(第03期),第69-73页. * |
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| CN113942642A (en) | 2022-01-18 |
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