CN102353314B - Detection method for outline of main blade of helicopter - Google Patents

Detection method for outline of main blade of helicopter Download PDF

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Publication number
CN102353314B
CN102353314B CN2011101540253A CN201110154025A CN102353314B CN 102353314 B CN102353314 B CN 102353314B CN 2011101540253 A CN2011101540253 A CN 2011101540253A CN 201110154025 A CN201110154025 A CN 201110154025A CN 102353314 B CN102353314 B CN 102353314B
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CN
China
Prior art keywords
main blade
airfoil
clamp
strong point
blade
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CN2011101540253A
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Chinese (zh)
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CN102353314A (en
Inventor
李丽丽
张凯
王妍
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哈尔滨飞机工业集团有限责任公司
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Priority to CN2011101540253A priority Critical patent/CN102353314B/en
Publication of CN102353314A publication Critical patent/CN102353314A/en
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Publication of CN102353314B publication Critical patent/CN102353314B/en

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Abstract

The invention relates to a detection method for an outline of a main blade of a helicopter. According to the method, four supporting points are utilized as basic starting points; an outline difference between an actual blade and a theoretical blade is detected; and then detection is gradually carried out from the leading edge of the main blade and gaps that are recorded every 10 mms and are used for recording an actual blade outline and an outline tool are recorded. Compared with the prior art, the technology employed in the invention enables the method has the following characteristics that: the design ides is novel and the detection method can be operated simply; and repeatability of detection results can be ensured.

Description

A kind of helicopter master blade method for detecting shape
Technical field
The present invention is a kind of helicopter master blade method for detecting shape, belongs to field of measuring technique.
Background technology
Rotor blade be have aerodynamic configuration, the transverse section is the straight strip structural member of aerofoil profile, complex geometry.Because blade is to the strict demand of aerodynamic configuration, the compound substance rotor blade selects to adopt close die hot-press solidifying forming technology, reaches designing requirement to guarantee blade aerofoil profile precision, torsion angle and surfaceness.In order to improve the pneumatic efficiency of blade, require blade adopt advanced aerofoil profile, blade profile error little, have certain roughness, the distortion of the profile under local aerodynamic loading effect little.Blade adopts the close die hot-press solidifying to be shaped.Close die is made of upper die and lower die, and cavity mold surface guarantees that blade is in strict conformity with the aerodynamic configuration requirement of design.In the hot-press solidifying forming process, pressure applies the profile that makes the blade profile strictly meet die cavity internally, reaches the accuracy requirement of blade twist angle, surfaceness and blade aerofoil profile.The quality of blade aeroperformance depends on aerofoil profile.The working environment that rotor blade is special requires the blade aerofoil profile should satisfy the requirement of retreating blade workspace (low mach, big Cy value), satisfies advancing blade workspace (high Mach number, little Cy value) again, and the requirement of floating state.So study reliable profile frock, feasible detection method, at different blade aerofoil profiles excessively and the plane alteration of form all be very important to helicopter rotor blade.Before, though drawing has clear and definite geometric shape inspection requirements, breathe out and fly to never have feasible profile frock and reliable detection method.
Summary of the invention
The present invention designs at above-mentioned the deficiencies in the prior art just a kind of helicopter master blade method for detecting shape is provided, and its objective is that the profile for various compound substance helicopter master blades detects.
The objective of the invention is to be achieved through the following technical solutions:
This kind helicopter master blade method for detecting shape, it is characterized in that: the step of this method is:
⑴ in the frock that is made of upper and lower two parts of installing of main blade, the interior profile of frock is the theoretical profile of main blade, the Support Position that the interior profile of frock is provided with on the outer mold surface of four strong points and main blade coincide, these four strong points are respectively the strong point and the preceding strong points of lower aerofoil behind the strong point before the strong point behind the top airfoil, the top airfoil, the lower aerofoil, the leading edge of frock is concordant with " 0-0 " section of main blade, and spacing as the leading edge of frock;
⑵ four strong points of adjustment contact with the upper and lower aerofoil of main blade, the strong point contacts with main blade lower aerofoil fully with the preceding strong point of lower aerofoil after guaranteeing lower aerofoil, observe the space of the preceding strong point of top airfoil and main blade top airfoil, if the space is mild slit, detection method is pressed a scheme and is carried out, if the space is significantly to cave in, detection method is carried out by sequence number b scheme;
⑶ if the space of the strong point and main blade top airfoil is mild slit before the top airfoil, the step that a scheme detects is:
3.1 use clearance gauge to measure the space of the preceding strong point of top airfoil and main blade top airfoil, read accumulating values A1 and calculate mean value X;
3.2 the gap of using clearance gauge to adjust the preceding strong point of top airfoil and main blade back, the preceding strong point of lower aerofoil and main blade lower surface is respectively X1, X2, locking detects clamp;
3.3 REF1000, REF5120, REF5860, the line of REF6262.5 section at main blade, and lay the detection clamp consistent with the theoretical profile of main blade at its profile position place, leading edge with main blade is spacing, adjust the accurate angle that detects clamp, determine to detect " 0 " scale mark position of illustrating on the clamp, again from the leading edge of main blade, along tangential every interval 10mm, use columned feeler gauge to record main blade and detect distance value D between the clamp profile N, N is respectively 10,20,30 ..., detect the scale mark value on the clamp;
3.4 record data, if D N2mm, namely be recorded as-D N, if D N≤ 2mm namely is recorded as D N
⑷ if the space of the strong point and main blade top airfoil is significantly to cave in before the top airfoil, the step that the b scheme detects is:
4.1 use feeler gauge to measure the depression size of the top airfoil of the preceding master of the strong point place blade of top airfoil, directly read the feeler gauge diameter and be deviate B1, and the particular location of record depressed deformation, indicate deflection numerical value=2mm-B1;
4.2 REF1000, REF5120, REF5860, the line of REF6262.5 section at main blade, and lay the detection clamp consistent with the theoretical profile of main blade at its profile position place, leading edge with main blade is spacing, adjust the accurate angle that detects clamp, determine to detect " 0 " scale mark position of illustrating on the clamp, again from the leading edge of main blade, along tangential every interval 10mm, use columned feeler gauge to record main blade and detect distance value D between the clamp profile N, N is respectively 10,20,30 ..., detect the scale mark value on the clamp;
4.3 record data D=2mm-D N
Above-mentioned four REF1000, REF5120, REF5860, REF6262.5 section are the positions that requires detection in the design, detect clamp and also should have four, its external form is the theoretical profile of section, and detecting the clamp surface has scale mark accurately, carries out the data read of relevant position when the aspect detects.By detecting the difference that clamp can reflect mold pressing blade and theoretical profile intuitively.The profile of main blade is the curved surface that radian is arranged, and the profile of frock also is curved surface, has just limited employed testing tool, can not be common clearance gauge commonly used, and can only be bar-shaped, such as feeler gauge.
Four support sections and blade aerofoil profile match;
The advantage of technical solution of the present invention is that the frock mentality of designing is clear and definite, and detection method is simple to operate, can guarantee the repeatability of testing result, can directly reflect the geometric shape of composite material blade on the data.
Description of drawings
Fig. 1 is the synoptic diagram of profile frock of the present invention
Embodiment
Below with reference to drawings and Examples technical solution of the present invention is further described:
This kind helicopter master blade method for detecting shape, it is characterized in that: the step of this method is:
⑴ in the frock 2 that is made of upper and lower two parts of installing of main blade 1, the interior profile of frock 2 is the theoretical profile of main blade 1, the Support Position that the interior profile of frock 2 is provided with on the outer mold surface of four strong points and main blade 1 coincide, these four strong points are respectively the strong point 5 and the preceding strong points 6 of lower aerofoil behind the strong point 4 before the strong point 3 behind the top airfoil, the top airfoil, the lower aerofoil, the leading edge of frock 2 is concordant with " 0-0 " section of main blade 1, and spacing as the leading edge of frock;
⑵ four strong points of adjustment contact with main blade 1 upper and lower aerofoil, the strong point 5 contacts with main blade 1 lower aerofoil fully with the preceding strong point 6 of lower aerofoil after guaranteeing lower aerofoil, observe the space of the preceding strong point 4 of top airfoil and main blade 1 top airfoil, if the space is mild slit, detection method is pressed a scheme and is carried out, if the space is significantly to cave in, detection method is carried out by sequence number b scheme;
⑶ if the space of the strong point 4 and main blade 1 top airfoil is mild slit before the top airfoil, the step that a scheme detects is:
3.1 use clearance gauge to measure the space of the preceding strong point 4 of top airfoil and main blade 1 top airfoil, read accumulating values A1 and calculate mean value X;
3.2 the strong point 4 is respectively X1, X2 with main blade 1 upper surface, the preceding strong point 6 of lower aerofoil with the gap of main blade 1 lower surface before using clearance gauge to adjust top airfoil, locking detects clamp;
3.3 REF1000, REF5120, REF5860, the line of REF6262.5 section at main blade 1, and lay the detection clamp consistent with main blade 1 theoretical profile at its profile position place, leading edge with main blade 1 is spacing, adjust the accurate angle that detects clamp, determine to detect " 0 " scale mark position of illustrating on the clamp, again from the leading edge of main blade 1, along tangential every interval 10mm, use columned feeler gauge to record main blade 1 and detect distance value D between the clamp profile N, N is respectively 10,20,30 ..., detect the scale mark value on the clamp;
3.4 record data, if D N2mm, namely be recorded as-D N, if D N≤ 2mm namely is recorded as D N
⑷ if the strong point 4 is significantly to cave in the space of main blade 1 top airfoil before the top airfoil, the step that the b scheme detects is:
4.1 use feeler gauge to measure the depression size of the top airfoil of the preceding strong point 4 master of the place blades 1 of top airfoil, directly read the feeler gauge diameter and be deviate B1, and the particular location of record depressed deformation, indicate deflection numerical value=2mm-B1;
4.2 REF1000, REF5120, REF5860, the line of REF6262.5 section at main blade 1, and lay the detection clamp consistent with main blade 1 theoretical profile at its profile position place, leading edge with main blade 1 is spacing, adjust the accurate angle that detects clamp, determine to detect " 0 " scale mark position of illustrating on the clamp, again from the leading edge of main blade 1, along tangential every interval 10mm, use columned feeler gauge to record main blade 1 and detect distance value D between the clamp profile N, N is respectively 10,20,30 ..., detect the scale mark value on the clamp;
4.3 record data D=2mm-D N
Compared with prior art, mentality of designing novelty of the present invention, detection method is simple to operate, can guarantee the repeatability of testing result.

Claims (1)

1. helicopter master blade method for detecting shape, it is characterized in that: the step of this method is:
⑴ in the frock (2) that is made of upper and lower two parts of installing of main blade (1), the interior profile of frock (2) is the theoretical profile of main blade (1), the Support Position that the interior profile of frock (2) is provided with on the outer mold surface of four strong points and main blade (1) coincide, these four strong points are respectively the strong point (5) and the preceding strong points (6) of lower aerofoil behind the strong point (4) before the strong point (3) behind the top airfoil, the top airfoil, the lower aerofoil, the leading edge of frock (2) is concordant with " 0-0 " section of main blade (1), and spacing as the leading edge of frock;
⑵ four strong points of adjustment contact with main blade (1) upper and lower aerofoil, the strong point (5) contacts with main blade (1) lower aerofoil fully with the preceding strong point (6) of lower aerofoil after guaranteeing lower aerofoil, observe the space of the preceding strong point (4) of top airfoil and main blade (1) top airfoil, if the space is mild slit, detection method is pressed a scheme and is carried out, if the space is significantly to cave in, detection method is carried out by sequence number b scheme;
⑶ if the space of the strong point (4) and main blade (1) top airfoil is mild slit before the top airfoil, the step that a scheme detects is:
3.1 use clearance gauge to measure the space of the preceding strong point (4) of top airfoil and main blade (1) top airfoil, read accumulating values A1 and calculate mean value X;
3.2 the strong point (4) is respectively X1, X2 with main blade (1) upper surface, the preceding strong point (6) of lower aerofoil with the gap of main blade (1) lower surface before using clearance gauge to adjust top airfoil, locking detects clamp;
3.3 REF1000, REF5120, REF5860, the line of REF6262.5 section in main blade (1), and lay the detection clamp consistent with the theoretical profile of main blade (1) at its profile position place, leading edge with main blade (1) is spacing, adjust the accurate angle that detects clamp, determine to detect " 0 " scale mark position of illustrating on the clamp, again from the leading edge of main blade (1), along tangential every interval 10mm, use columned feeler gauge to record main blade (1) and detect distance value D between the clamp profile N, N is respectively 10,20,30 ..., detect the scale mark value on the clamp;
3.4 record data, if D N2mm, namely be recorded as-D N, if D N≤ 2mm namely is recorded as D N
⑷ if the strong point (4) is significantly to cave in the space of main blade (1) top airfoil before the top airfoil, the step that the b scheme detects is:
4.1 use feeler gauge to measure the depression size that the preceding strong point (4) of top airfoil is located the top airfoil of main blade (1), directly read the feeler gauge diameter and be deviate B1, and the particular location of record depressed deformation, indicate deflection numerical value=2mm-B1;
4.2 REF1000, REF5120, REF5860, the line of REF6262.5 section in main blade (1), and lay the detection clamp consistent with the theoretical profile of main blade (1) at its profile position place, leading edge with main blade (1) is spacing, adjust the accurate angle that detects clamp, determine to detect " 0 " scale mark position of illustrating on the clamp, again from the leading edge of main blade (1), along tangential every interval 10mm, use columned feeler gauge to record main blade (1) and detect distance value D between the clamp profile N, N is respectively 10,20,30 ..., detect the scale mark value on the clamp;
4.3 record data D=2mm-D N
CN2011101540253A 2011-06-10 2011-06-10 Detection method for outline of main blade of helicopter CN102353314B (en)

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CN104669153B (en) * 2013-12-02 2017-02-08 昌河飞机工业(集团)有限责任公司 Blade torsional angle measurement fixture and method
CN105783751B (en) * 2014-12-17 2018-12-18 中国航空工业集团公司沈阳发动机设计研究所 A kind of multi- scenarios method state lower fulcrum vector deformation test method
CN105157658B (en) * 2015-09-06 2018-05-01 中国商用飞机有限责任公司 Aircraft skin appearance detection apparatus
CN105252768B (en) * 2015-09-14 2017-06-27 沈阳飞机工业(集团)有限公司 A kind of verification cover plate and method of calibration for the shaping of special-shaped composite foam layer product
CN105953681A (en) * 2016-06-18 2016-09-21 无锡市翱宇特新科技发展有限公司 Rail supporting bench mold detection apparatus
CN108151618A (en) * 2016-12-06 2018-06-12 江西昌河航空工业有限公司 A kind of fixture being detected to foamed material part
CN109443139A (en) * 2018-12-07 2019-03-08 南通虹波机械有限公司 The pod line style method of inspection

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US4875777A (en) * 1987-09-30 1989-10-24 Industrial Technology Institute Off-axis high accuracy structured light profiler
CN1026471C (en) * 1990-08-07 1994-11-09 宫哲圣 Propeller line skeleton moulding method
DE10214984B4 (en) * 2002-04-04 2006-01-19 Eads Deutschland Gmbh Actuator and sensor system for composite structures
CN201795764U (en) * 2010-08-12 2011-04-13 四川省自贡市海川实业有限公司 Special measuring tool for radial inclined surface of blade basin

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Owner name: HAFEI AVIATION INDUSTRY CO., LTD.

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Patentee before: Harbin Aircraft Industrial (Group) Co., Ltd.

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