WO2015035850A1 - Système permettant de mesurer la courbure d'une surface d'avion et procédé correspondant - Google Patents

Système permettant de mesurer la courbure d'une surface d'avion et procédé correspondant Download PDF

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Publication number
WO2015035850A1
WO2015035850A1 PCT/CN2014/084792 CN2014084792W WO2015035850A1 WO 2015035850 A1 WO2015035850 A1 WO 2015035850A1 CN 2014084792 W CN2014084792 W CN 2014084792W WO 2015035850 A1 WO2015035850 A1 WO 2015035850A1
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WO
WIPO (PCT)
Prior art keywords
waviness
aircraft
data
point
convex
Prior art date
Application number
PCT/CN2014/084792
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English (en)
Chinese (zh)
Inventor
曹喜锋
金鼎
李启明
丁玲
马明
Original Assignee
中国商用飞机有限责任公司
中国商用飞机有限责任公司上海飞机设计研究院
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Application filed by 中国商用飞机有限责任公司, 中国商用飞机有限责任公司上海飞机设计研究院 filed Critical 中国商用飞机有限责任公司
Publication of WO2015035850A1 publication Critical patent/WO2015035850A1/fr

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Classifications

    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
    • G01B11/00—Measuring arrangements characterised by the use of optical techniques
    • G01B11/24—Measuring arrangements characterised by the use of optical techniques for measuring contours or curvatures
    • G01B11/25—Measuring arrangements characterised by the use of optical techniques for measuring contours or curvatures by projecting a pattern, e.g. one or more lines, moiré fringes on the object
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01B—MEASURING LENGTH, THICKNESS OR SIMILAR LINEAR DIMENSIONS; MEASURING ANGLES; MEASURING AREAS; MEASURING IRREGULARITIES OF SURFACES OR CONTOURS
    • G01B11/00—Measuring arrangements characterised by the use of optical techniques
    • G01B11/30—Measuring arrangements characterised by the use of optical techniques for measuring roughness or irregularity of surfaces
    • G01B11/306—Measuring arrangements characterised by the use of optical techniques for measuring roughness or irregularity of surfaces for measuring evenness

Definitions

  • the present invention relates to the detection of aircraft, and more particularly to the detection of aircraft surfaces. Background technique
  • the waviness is used to measure the undulation of the outer surface of the aircraft, reflecting the surface quality of the aircraft.
  • the waviness of certain special areas on the surface of the aircraft will have a large impact on the aerodynamic characteristics and flight performance of the aircraft. For example: The waviness near the static pressure port directly affects the airworthiness of the civil aircraft to reduce the minimum vertical spacing (RVSM) operating capacity. Forensics.
  • the present project proposes an optical waviness measuring instrument, which can effectively improve various drawbacks of the existing measuring tools.
  • a system for measuring waviness of an aircraft surface comprising: a laser contour scanning module for emitting laser light to an aircraft surface, receiving laser light reflected back from the surface of the aircraft, and obtaining a representative aircraft Data of the surface profile line; a digital signal processor for processing data from the laser profile scanning module to obtain data that the waviness calculation module can process; a waviness calculation module for representing the surface of the representative aircraft The data of the section line profile calculates the waviness of the surface of the aircraft.
  • This aspect of the invention uses a laser to scan the contour of the surface of the aircraft and calculate the waviness of the surface of the aircraft from the contour, increasing the degree of automation of the measurement and shortening the measurement time. Increased measurement efficiency and reduced sampling errors that can be caused by manual sampling.
  • the system of at least one of the following components is also included:
  • the waviness calculation module is configured to perform the following operations:
  • Iv. Calculate the amplitude and wavelength as the waviness of the waviness based on the spline and the envelope.
  • the convex hull is also identified and screened, so that the envelope of the convex hull has the convexity, and the measurement accuracy of the waviness is improved.
  • the step ii includes the following sub-steps:
  • the spline curve is discretized into a set of measurement points of equal spacing according to a certain density
  • the other measurement point sets are all located on the same side of the read ray, and the read point is determined as the vertice of the next convex hull;
  • next convex hull as the current convex hull, repeating the above steps d and e in the same direction to find the vertices of the next convex hull;
  • Step f is repeated until the vertex of the newly found convex hull is another measurement point on the boundary of the rectangle, and the vertices of all the found convex hulls are the set of points of the bulge vertices.
  • This embodiment provides a specific embodiment for screening convex hulls in order to ensure convexity.
  • the step i includes interpolating the data points using a spline curve.
  • This embodiment provides a specific implementation for converting data points into spline curves using interpolation. More specifically, cubic splines can be used, and the cubic splines can be more accurately fitted to the curve, and the amount of calculation is also moderate. It can be understood that any other spline interpolation method can be applied.
  • the step iv includes:
  • the step of calculating the amplitude includes:
  • the waviness calculation module is configured to perform the following operations before performing the i operation:
  • the processed data points representing the contour line profile of the aircraft surface are pre-screened to remove the measurement dead pixels.
  • the measurement of the dead pixels that may occur is considered, and it is screened and removed, improving the accuracy of the measured data.
  • This embodiment provides a specific embodiment for screening measurement dead spots: Since the aircraft surface is generally continuous, this embodiment uses discontinuous data points as measurement dead spots, Have better accuracy.
  • the waviness calculation module is configured to perform the following operations after performing the i operation, before the ii operation:
  • the small fluctuations in the sample curve are also filtered out, which avoids the influence of minute fluctuations on the waviness and also reduces the amount of calculation.
  • the step of filtering out the small fluctuations in the spline curve comprises: using the wavelet filtering method, generating a cubic spline curve of the effective measurement points to filter out the small fluctuations included in the spline curve, excluding the roughness Degree of interference. More preferably, the small fluctuations in the spline curve are filtered out, using db6, sym6, or coi wavelets, and the number of decomposition layers is adjusted to 1 to 3 layers.
  • a second aspect of the present invention provides a method of measuring waviness of an aircraft surface, comprising the steps of: emitting a laser to an aircraft surface, receiving a laser reflected back from the surface of the aircraft, and obtaining a representative aircraft surface Data of the profile line profile; calculating the waviness of the surface of the aircraft based on the processed data representing the contour line profile of the aircraft surface; wherein the step of calculating the waviness comprises: processing the data point representing the profile line profile of the aircraft surface Perform pre-screening to remove measurement dead spots; concatenate the data points after the measurement of the dead pixels into spline curves; filter out small fluctuations in the spline curve; perform convex hulls in the read spline curve after filtering out small fluctuations Identifying and screening, ignoring some of the convex hulls, so that the envelope of the remaining convex hull has conve
  • FIG. 1 is a view showing the appearance and operation of a laser profile scanning module used in an embodiment of the present invention
  • FIG. 2 is a schematic view showing the operation of measuring the surface of an aircraft according to an embodiment of the present invention
  • FIG. 3 is a schematic view showing data points, convex hulls, and envelopes of the surface of the aircraft measured by the embodiment of the present invention
  • FIG. 4 is a flow chart for calculating waviness in accordance with an embodiment of the present invention.
  • a basic embodiment of the present invention provides a system for measuring the waviness of an aircraft surface, which includes the following components:
  • a laser profile scanning module for emitting laser light to the surface of the aircraft, receiving laser light reflected from the surface of the aircraft, and obtaining data representative of the profile of the surface profile of the aircraft surface;
  • a digital signal processor for processing data from the laser contour scanning module to obtain data that the waviness calculation module can process
  • a waviness calculation module for calculating the waviness of the surface of the aircraft based on the processed data representing the profile of the surface profile of the aircraft.
  • Figure 1 shows the appearance and operation of the laser profile scanning module.
  • the scanning module typically comes with a laser source, lens group, and sensor.
  • the lens group collects the laser light reflected from the surface of the object to be tested and supplies it to the sensor, and the sensor detects the laser to obtain data representing the contour of the surface line of the aircraft.
  • the laser profile scanning module itself is already an existing product, such as ZSYS210 large-scale laser two-dimensional contour scanning sensor of ZSY. It can be understood that any laser scanner capable of obtaining surface profile line profile data is suitable for the present invention. .
  • the system further comprises:
  • a system equipment box for accommodating the digital signal processor, the waviness calculation module and the power supply module.
  • FIG. 2 is a schematic illustration of the operation of measuring the surface of an aircraft in accordance with an embodiment of the present invention.
  • the laser profile scanning sensor is fixed on the movable bracket. By adjusting the height and angle of the bracket, the laser contour scanning sensor can illuminate the area of the aircraft surface to be measured.
  • the digital signal processor, the waviness calculation module, and the power supply are installed in the system equipment box.
  • the laser profile scanning sensor transmits the acquired image information data to the digital signal processor via a cable.
  • the digital signal processor processes the received image information data into data that the waviness calculation module can process, and transmits the processed data to the waviness calculation module.
  • the waviness calculation module can be embodied in a data processing computer such as an industrial PC or a tablet PC, and the waviness calculation module can be implemented in the form of processed software that processes the received data by an algorithm.
  • the waviness measurement results, the results are saved and the results are displayed on a display (not shown) connected to the data processing computer.
  • the waviness calculation module implemented by the tablet PC can be easily taken out from the system equipment box.
  • the acquired image information data is stored in the data processing computer implementing the waviness calculation module by the digital signal processor;
  • the waviness calculation module in the data processing computer operates, and the acquired image information data is processed according to the post-processing intelligent algorithm to obtain the waviness measurement result.
  • waviness information of a certain section of the surface of the body to be tested can be instantaneously acquired without contact.
  • the information collection process is fast and efficient, and can effectively avoid errors generated during the data acquisition process.
  • the waviness measurement result can be quickly obtained based on the acquired image information due to the embedding of the post-processing intelligent algorithm, and the result is obtained. Output as graphics, reports.
  • the waviness calculation module receives the discrete data points provided by the laser profile scanner representing a section line of the aircraft surface, as shown by the measured data marked by the dashed points in FIG.
  • the waviness calculation module requires a well-established algorithm to analyze the waviness characteristics of the measured data.
  • FIG. 4 is a flow chart for calculating waviness in accordance with an embodiment of the present invention.
  • the part is located on the same side of the ray, and the Pi point is the convex hull vertex Q2. Then use the new convex hull vertex Q2 as the starting point to find the next convex hull vertex Q3 along the same spiral direction, ... until the newly found convex hull vertex is
  • the adjacent convex hull is a corrugation, and measure the length of the envelope between the apex of the adjacent convex hull, which is the wavelength of the ripple.
  • an embodiment of the present invention also provides a method for measuring the waviness of the surface of the aircraft, comprising the following steps:
  • the steps of calculating the waviness include:

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  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Engineering & Computer Science (AREA)
  • Computer Vision & Pattern Recognition (AREA)
  • Length Measuring Devices By Optical Means (AREA)

Abstract

Système de mesure de la courbure d'une surface d'avion, et procédé correspondant. Ledit système comprend les composants suivants : un module de balayage laser de contour servant à émettre un rayon laser vers une surface d'avion, à recevoir le rayon laser réfléchi par la surface de l'avion, et à obtenir les données représentant une section transversale de contour de la surface de l'avion; un processeur de signaux numériques destiné à traiter les données provenant du module de balayage laser de contour et à fournir des données qui peuvent être traitées par un module de calcul de contour, ledit module de calcul de contour servant à calculer la courbure de la surface de l'avion selon les données traitées représentant la section transversale de contour de la surface de l'avion. Ledit système permet d'obtenir instantanément des informations de courbure d'une section transversale de la surface de fuselage de l'avion mesurée, aucun contact n'étant nécessaire. Le processus de collecte d'informations est rapide et efficace et peut éviter efficacement les erreurs générées pendant le processus de collecte de données.
PCT/CN2014/084792 2013-09-10 2014-08-20 Système permettant de mesurer la courbure d'une surface d'avion et procédé correspondant WO2015035850A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CN201310410669.3A CN103471532B (zh) 2013-09-10 2013-09-10 测量飞行器表面波纹度的系统以及相应方法
CN201310410669.3 2013-09-10

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WO2015035850A1 true WO2015035850A1 (fr) 2015-03-19

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Publication number Priority date Publication date Assignee Title
CN103471532B (zh) * 2013-09-10 2017-01-04 中国商用飞机有限责任公司 测量飞行器表面波纹度的系统以及相应方法
CN106568379B (zh) * 2015-10-10 2019-02-15 陕西飞机工业（集团）有限公司 一种基于空间定位的测量飞机部件对接面外形的方法
CN108080898A (zh) * 2017-12-18 2018-05-29 中国航发贵州黎阳航空动力有限公司 一种压气机转子叶片叶身波纹度加工工艺及检测方法
CN109443258A (zh) * 2018-12-29 2019-03-08 芜湖哈特机器人产业技术研究院有限公司 一种背板平面度检测装置及其检测方法
CN114136205B (zh) * 2021-10-25 2024-04-09 中航通飞华南飞机工业有限公司 一种波纹度测量装置及使用方法
CN114659464B (zh) * 2022-03-25 2023-03-07 南京航空航天大学 一种基于实测三维数据的飞机整机外形波纹度测量方法

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