CN105806234A - Automatic detection device and detection method for thickness of solid rocket engine coating - Google Patents
Automatic detection device and detection method for thickness of solid rocket engine coating Download PDFInfo
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- CN105806234A CN105806234A CN201610268322.3A CN201610268322A CN105806234A CN 105806234 A CN105806234 A CN 105806234A CN 201610268322 A CN201610268322 A CN 201610268322A CN 105806234 A CN105806234 A CN 105806234A
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- 238000001514 detection method Methods 0.000 title claims abstract description 56
- 239000011248 coating agent Substances 0.000 title claims abstract description 41
- 238000000576 coating method Methods 0.000 title claims abstract description 41
- 239000007787 solid Substances 0.000 title abstract description 32
- 238000005259 measurement Methods 0.000 claims abstract description 34
- 229910000831 Steel Inorganic materials 0.000 claims description 9
- 239000010959 steel Substances 0.000 claims description 9
- 238000000034 method Methods 0.000 claims description 8
- 238000012360 testing method Methods 0.000 claims description 4
- 239000004449 solid propellant Substances 0.000 claims 9
- 239000011247 coating layer Substances 0.000 claims 3
- 238000013480 data collection Methods 0.000 claims 1
- 239000000523 sample Substances 0.000 description 6
- 238000005516 engineering process Methods 0.000 description 3
- 238000006073 displacement reaction Methods 0.000 description 2
- 239000002184 metal Substances 0.000 description 2
- 239000003380 propellant Substances 0.000 description 2
- 238000005507 spraying Methods 0.000 description 2
- 238000005253 cladding Methods 0.000 description 1
- 239000002131 composite material Substances 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000009413 insulation Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000000691 measurement method Methods 0.000 description 1
- 238000010998 test method Methods 0.000 description 1
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- 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
- G01B11/02—Measuring arrangements characterised by the use of optical techniques for measuring length, width or thickness
- G01B11/06—Measuring arrangements characterised by the use of optical techniques for measuring length, width or thickness for measuring thickness ; e.g. of sheet material
- G01B11/0616—Measuring arrangements characterised by the use of optical techniques for measuring length, width or thickness for measuring thickness ; e.g. of sheet material of coating
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Abstract
本发明属于工业检测装置及检测方法技术领域，具体涉及一种固体火箭发动机涂层厚度自动检测装置及检测方法。本发明解决了现有固体火箭发动机涂层厚度的检测方法存在易受涂层软硬程度影响、易造成涂层污染、检测步骤繁琐和无法实现随机点的检测的技术问题。本发明结合激光测距和涡流测厚的原理，利用激光测距测头和环状涡流测头组成的组合传感器，实现对固体火箭发动机内涂层厚度的一次检测；采用控制测量系统、主测量臂、辅助测量臂和可旋转的组合传感器结构，实现了固体火箭发动机内涂层厚度的任意点检测。本发明操作方便、快捷、检测精度高，使用范围广。
The invention belongs to the technical field of industrial detection devices and detection methods, and in particular relates to a solid rocket motor coating thickness automatic detection device and detection method. The invention solves the technical problems that the existing solid rocket motor coating thickness detection method is easily affected by the softness and hardness of the coating, easily causes coating pollution, has cumbersome detection steps and cannot realize random point detection. The present invention combines the principles of laser distance measurement and eddy current thickness measurement, and uses a combined sensor composed of a laser distance measurement head and an annular eddy current measurement head to realize a detection of the thickness of the inner coating of a solid rocket motor; a control measurement system, a main measurement The arm, the auxiliary measuring arm and the rotatable combined sensor structure realize the arbitrary point detection of the inner coating thickness of the solid rocket motor. The invention has the advantages of convenient and fast operation, high detection precision and wide application range.
Description
技术领域technical field
本发明属于工业检测装置及检测方法技术领域，具体涉及一种固体火箭发动机涂层厚度自动检测装置及检测方法。The invention belongs to the technical field of industrial detection devices and detection methods, and in particular relates to a solid rocket motor coating thickness automatic detection device and detection method.
背景技术Background technique
固体火箭发动机一般由金属壳体、涂层(绝热层、衬层或包覆层)和推进剂组成，涂层一般是由胶状的复合材料经过特定工艺固化到金属壳体上，其固化后的厚度具有严格的要求，因此在生产过程中，需要在填装推进剂前进行涂层厚度的检测，检测时不能改变涂层的内部状态和表面结构。A solid rocket motor generally consists of a metal shell, a coating (insulation layer, lining or cladding) and a propellant. The coating is generally made of a gel-like composite material that is cured onto the metal shell through a specific process. The thickness of the coating has strict requirements, so in the production process, it is necessary to detect the thickness of the coating before filling the propellant, and the internal state and surface structure of the coating cannot be changed during the detection.
现有的检测方法有超声检测方法、涡流检测方法和激光检测方法。华北工学院采用“板波诱发纵波超声检测技术”可以检测钢壳体内涂层厚度(见中国专利号93118358.8)，但该方法需要接触钢质壳体，其适用性与涂层的声衰减系数和厚度有关；涡流检测方法是将涡流探头直接接触涂层测量钢质壳体内的涂层厚度，但该方法容易受涂层软硬强度的影响，且属于接触测量，会造成涂层表面的污染；激光测厚方法是采用激光位移传感器通过测量涂层喷涂前、后传感器到表面的位移，将两次所测量的值相减即可得到涂层厚度值(见中国专利号CN201310137425.2)，但该方法在喷涂前后都需要测量，增加了检测负担，且不能实现喷涂后随机点的检测。The existing detection methods include ultrasonic detection method, eddy current detection method and laser detection method. North China Institute of Technology adopts "plate wave induced longitudinal wave ultrasonic testing technology" to detect the thickness of the inner coating of the steel shell (see Chinese Patent No. 93118358.8), but this method needs to contact the steel shell, and its applicability is related to the sound attenuation coefficient and the sound attenuation coefficient of the coating. The thickness is related; the eddy current test method is to directly contact the eddy current probe with the coating to measure the coating thickness in the steel shell, but this method is easily affected by the soft and hard strength of the coating, and it belongs to contact measurement, which will cause pollution on the coating surface; The laser thickness measurement method uses a laser displacement sensor to measure the displacement of the sensor to the surface before and after the coating is sprayed, and subtracts the two measured values to obtain the coating thickness value (see Chinese Patent No. CN201310137425.2), but This method needs to be measured before and after spraying, which increases the detection burden, and cannot realize the detection of random points after spraying.
发明内容Contents of the invention
本发明的目的是解决现有固体火箭发动机涂层厚度的检测方法存在易受涂层软硬程度影响、易造成涂层污染、检测步骤繁琐和无法实现随机点的检测的技术问题，提供一种固体火箭发动机涂层厚度自动检测装置及检测方法。The purpose of the present invention is to solve the technical problems that the existing solid rocket motor coating thickness detection method is easily affected by the softness and hardness of the coating, easily causes coating pollution, cumbersome detection steps and cannot realize random point detection, and provides a A solid rocket motor coating thickness automatic detection device and detection method.
为解决上述技术问题，本发明采用的技术方案为：In order to solve the problems of the technologies described above, the technical solution adopted in the present invention is:
一种固体火箭发动机涂层厚度自动检测装置，包括由测量臂底座、测量臂支架、主测量臂、辅助测量臂和组合传感器组成的测量机构、由工件支撑台、工件左顶装置、工件右顶装置、主动支撑轮、从动支撑轮、编码器和零点开关组成的测量台、五个电机及控制测量系统，在测量臂底座上设有直线导轨Ⅱ，第一电机设在测量臂底座上且与直线导轨Ⅱ连接，测量臂支架的下端与直线导轨Ⅱ的滑块连接以便于测量臂支架在测量臂底座上左右运动，在测量臂支架的右板面设有直线导轨Ⅰ，第二电机设在测量臂支架上且与直线导轨Ⅰ连接，主测量臂的左端与直线导轨Ⅰ的滑块连接以便于主测量臂在测量臂支架上上下运动，辅助测量臂的左端与主测量臂的右端通过关节Ⅰ连接，第三电机设在测量臂支架上且通过钢丝绳Ⅰ驱动辅助测量臂相对于主测量臂转动，组合传感器设在辅助测量臂的右端，第四电机设在测量臂支架上且通过钢丝绳Ⅱ驱动组合传感器在辅助测量臂的右端转动；工件支撑台设在测量臂底座的右侧且与测量臂底座位于同一水平面上，工件左顶装置和工件右顶装置分别设在工件支撑台台面的左右两端，主动支撑轮和从动支撑轮分别设在工件支撑台台面的左右两侧，第五电机设在工件支撑台上且通过皮带驱动装置与主动支撑轮连接，编码器设在从动支撑轮上，零点开关设在主动支撑轮上，控制测量系统分别与五个电机、组合传感器、零点开关和编码器电气连接，用于控制五个电机的工作，当检测到零点开关的信号时，控制组合传感器和编码器进行检测数据的采集。An automatic detection device for the coating thickness of a solid rocket motor, including a measuring mechanism composed of a measuring arm base, a measuring arm support, a main measuring arm, an auxiliary measuring arm and a combined sensor, a workpiece support table, a workpiece left top device, and a workpiece right top device, active support wheel, driven support wheel, encoder and zero switch composed of measuring platform, five motors and control measurement system, linear guide rail II is set on the base of the measuring arm, the first motor is set on the base of the measuring arm and It is connected with the linear guide rail Ⅱ, the lower end of the measuring arm bracket is connected with the slider of the linear guide rail Ⅱ so that the measuring arm bracket can move left and right on the base of the measuring arm. The linear guide rail Ⅰ is set on the right plate of the measuring arm bracket, and the second motor is set On the measuring arm support and connected with the linear guide rail Ⅰ, the left end of the main measuring arm is connected with the slider of the linear guide rail Ⅰ so that the main measuring arm moves up and down on the measuring arm support, and the left end of the auxiliary measuring arm passes through the right end of the main measuring arm The joint I is connected, the third motor is set on the measuring arm bracket and drives the auxiliary measuring arm to rotate relative to the main measuring arm through the steel wire rope I, the combined sensor is set at the right end of the auxiliary measuring arm, the fourth motor is set on the measuring arm bracket and passes through the steel wire rope Ⅱ Drive the combined sensor to rotate at the right end of the auxiliary measuring arm; the workpiece supporting platform is set on the right side of the measuring arm base and is on the same level as the measuring arm base, and the workpiece left top device and workpiece right top device are respectively set on the workpiece support platform. At the left and right ends, the driving support wheel and the driven support wheel are respectively set on the left and right sides of the workpiece support table, the fifth motor is set on the workpiece support table and connected with the drive support wheel through a belt drive device, and the encoder is set on the driven support wheel. On the support wheel, the zero point switch is set on the active support wheel, and the control measurement system is electrically connected with the five motors, the combined sensor, the zero point switch and the encoder, and is used to control the work of the five motors. When the signal of the zero point switch is detected , control the combined sensor and encoder to collect the detection data.
所述组合传感器由传感器固定装置、激光测距测头和环状涡流测头组成，环状涡流测头设在传感器固定装置的底部，激光测距测头设在传感器固定装置的中部，且使激光测距测头的中心和环状涡流测头的中心位于同一轴线。The combined sensor is composed of a sensor fixing device, a laser ranging probe and an annular eddy current measuring head. The annular eddy current measuring head is arranged at the bottom of the sensor fixing device, and the laser ranging measuring head is arranged at the middle of the sensor fixing device. The center of the laser distance measuring head and the center of the annular eddy current measuring head are located on the same axis.
一种采用所述固体火箭发动机涂层厚度自动检测装置进行固体火箭发动机涂层厚度检测的方法，包括以下步骤：A method for detecting the thickness of a solid rocket motor coating by using the automatic detection device for coating thickness of the solid rocket motor, comprising the following steps:
1)将待检固体火箭发动机放置在测量台上，通过控制测量系统控制主动支撑轮旋转，从而带动待检固体火箭发动机、从动支撑轮和编码器码盘旋转；1) Place the solid rocket motor to be inspected on the measuring platform, and control the rotation of the active support wheel by controlling the measurement system, thereby driving the solid rocket motor to be inspected, the driven support wheel and the code disc of the encoder to rotate;
2)通过控制测量系统控制主测量臂上下移动，对准待检固体火箭发动机开口；2) Control the main measuring arm to move up and down by controlling the measuring system, and align it with the opening of the solid rocket motor to be checked;
3)通过控制测量系统控制主测量臂前后移动、辅助测量臂旋转以及组合传感器旋转，使得组合传感器在量程范围内激光束垂直入射待检固体火箭发动机检测位置内表面；3) By controlling the measurement system to control the front and rear movement of the main measuring arm, the rotation of the auxiliary measuring arm and the rotation of the combined sensor, the laser beam of the combined sensor is vertically incident on the inner surface of the detection position of the solid rocket motor to be tested within the measuring range;
4)控制测量系统检测零点开关的信号，当检测到信号时，根据编码器的反馈信号进行激光和涡流数据采集，最终得出待检固体火箭发动机涂层的实际厚度。4) The control measurement system detects the signal of the zero point switch. When the signal is detected, the laser and eddy current data are collected according to the feedback signal of the encoder, and finally the actual thickness of the solid rocket motor coating to be inspected is obtained.
本发明采用以上技术方案，与背景技术相比，本发明具有以下优点：The present invention adopts the above technical scheme, compared with the background technology, the present invention has the following advantages:
1)由激光测距测头和环状涡流测头组成的组合传感器，实现了涂层厚度的一次性检测，避免涡流或超声检测带来的污染和不准确，以及二次激光检测带来的不便捷，达到方便、快捷、准确检测的目的；1) The combined sensor consisting of a laser distance measuring head and an annular eddy current measuring head realizes the one-time detection of coating thickness, avoiding the pollution and inaccuracy caused by eddy current or ultrasonic detection, as well as the secondary laser detection. Inconvenient, to achieve the purpose of convenient, fast and accurate detection;
2)通过主测量臂的上下、前后移动，辅助测量臂和组合传感器的旋转，可以实现内部结构复杂情况的检测；2) Through the up and down, back and forth movement of the main measuring arm, and the rotation of the auxiliary measuring arm and combined sensor, the detection of complex internal structures can be realized;
3)本发明的主动支撑轮、从动支撑轮、工件后顶装置可以根据需要调节，适用于多尺寸、多规格产品的检测，使用范围广。3) The active support wheel, the driven support wheel, and the workpiece rear jacking device of the present invention can be adjusted according to needs, and are suitable for the detection of multi-size and multi-standard products, and have a wide range of applications.
附图说明Description of drawings
图1是本发明的结构示意图；Fig. 1 is a structural representation of the present invention;
图2是本发明组合传感器的结构示意图；Fig. 2 is the structural representation of combined sensor of the present invention;
图3和图4是本发明检测固体火箭发动机弧面段或斜面段时传感器与测量臂示意图；Fig. 3 and Fig. 4 are the schematic diagrams of sensor and measuring arm when the present invention detects solid rocket motor arc section or slope section;
图5是本发明实施例中检测固体火箭发动机55个截面所得到的厚度扫描图像。Fig. 5 is a thickness scanning image obtained by detecting 55 sections of a solid rocket motor in an embodiment of the present invention.
图6和图7是本发明实施例中检测固体火箭发动机第30个截面和30°位置处所得到的厚度曲线。Fig. 6 and Fig. 7 are thickness curves obtained at the 30th section and 30° position of the solid rocket motor in the embodiment of the present invention.
具体实施方式detailed description
如图1所示，本实施例中的一种固体火箭发动机涂层厚度自动检测装置，包括由测量臂底座1、测量臂支架4、主测量臂11、辅助测量臂13和组合传感器15组成的测量机构、由工件支撑台25、工件左顶装置24、工件右顶装置17、主动支撑轮21、从动支撑轮19、编码器18和零点开关20组成的测量台、五个电机2、6、7、8、22及控制测量系统，在测量臂底座1上设有直线导轨Ⅱ3，第一电机2设在测量臂底座1上且与直线导轨Ⅱ3连接，测量臂支架4的下端与直线导轨Ⅱ3的滑块连接以便于测量臂支架4在测量臂底座1上左右运动，在测量臂支架4的右板面设有直线导轨Ⅰ5，第二电机8设在测量臂支架4上且与直线导轨Ⅰ5连接，主测量臂11的左端与直线导轨Ⅰ5的滑块连接以便于主测量臂11在测量臂支架4上上下运动，辅助测量臂13的左端与主测量臂11的右端通过关节Ⅰ12连接，第三电机7设在测量臂支架4上且通过钢丝绳Ⅰ9驱动辅助测量臂13相对于主测量臂11转动，组合传感器15设在辅助测量臂13的右端，第四电机6设在测量臂支架4上且通过钢丝绳Ⅱ10驱动组合传感器15在辅助测量臂13的右端转动；工件支撑台25设在测量臂底座1的右侧且与测量臂底座1位于同一水平面上，工件左顶装置24和工件右顶装置17分别设在工件支撑台25台面的左右两端，主动支撑轮21和从动支撑轮19分别设在工件支撑台25台面的左右两侧，第五电机22设在工件支撑台25上且通过皮带驱动装置23与主动支撑轮21连接，编码器18设在从动支撑轮19上，零点开关20设在主动支撑轮21上，控制测量系统分别与五个电机2、6、7、8、22、组合传感器15、零点开关20和编码器18电气连接，用于控制五个电机2、6、7、8、22的工作，当检测到零点开关20的信号时，控制组合传感器15和编码器18进行检测数据的采集。As shown in Figure 1, a kind of solid rocket motor coating thickness automatic detection device in the present embodiment, comprises and is made up of measuring arm base 1, measuring arm support 4, main measuring arm 11, auxiliary measuring arm 13 and combined sensor 15 Measuring mechanism, a measuring platform composed of a workpiece support table 25, a workpiece left top device 24, a workpiece right top device 17, a driving support wheel 21, a driven support wheel 19, an encoder 18 and a zero point switch 20, five motors 2, 6 , 7, 8, 22 and the control measurement system, a linear guide rail II3 is arranged on the base of the measuring arm 1, the first motor 2 is arranged on the base of the measuring arm 1 and connected with the linear guide rail II3, the lower end of the measuring arm support 4 is connected to the linear guide rail The slider of II3 is connected to facilitate the left and right movement of the measuring arm support 4 on the measuring arm base 1, and a linear guide rail I5 is provided on the right plate surface of the measuring arm support 4, and the second motor 8 is arranged on the measuring arm support 4 and connected with the linear guide rail I5 connection, the left end of the main measuring arm 11 is connected with the slider of the linear guide rail I5 so that the main measuring arm 11 moves up and down on the measuring arm bracket 4, the left end of the auxiliary measuring arm 13 is connected with the right end of the main measuring arm 11 through the joint I12, The third motor 7 is arranged on the measuring arm support 4 and drives the auxiliary measuring arm 13 to rotate relative to the main measuring arm 11 through the steel wire rope I9. and the combined sensor 15 is driven to rotate at the right end of the auxiliary measuring arm 13 through the steel wire rope II10; the workpiece supporting platform 25 is arranged on the right side of the measuring arm base 1 and is located on the same level as the measuring arm base 1, and the workpiece left top device 24 and the workpiece right The top device 17 is respectively arranged on the left and right ends of the workpiece supporting table 25 table tops, the driving supporting wheel 21 and the driven supporting wheel 19 are respectively arranged on the left and right sides of the workpiece supporting table 25 table tops, and the fifth motor 22 is located on the workpiece supporting table 25 And be connected with active support wheel 21 by belt drive device 23, encoder 18 is located on driven support wheel 19, and zero point switch 20 is located on active support wheel 21, and control measuring system is respectively connected with five motors 2,6,7, 8, 22, combination sensor 15, zero point switch 20 and encoder 18 are electrically connected, used to control the work of five motors 2, 6, 7, 8, 22, when the signal of zero point switch 20 is detected, the combination sensor 15 is controlled and encoder 18 to collect detection data.
如图2所示，所述组合传感器15由传感器固定装置26)激光测距测头27和环状涡流测头28组成，环状涡流测头28设在传感器固定装置26的底部，激光测距测头27设在传感器固定装置26的中部，且使激光测距测头27的中心和环状涡流测头28的中心位于同一轴线。确保激光测距测头27与环状涡流测头28的测量点为同一点，激光测距测头27的测量面与环状涡流测头28的测量面距离为d，本实施例中d＝38mm。激光测距测头27可测量测量面到涂层29交界面的距离为M1，环状涡流测头28可测量测量面到涂层29内表面的距离为M2，通过几何关系计算得出所测量位置的涂层厚度h＝M1-M2-d。As shown in Figure 2, described combination sensor 15 is made up of sensor fixture 26) laser distance measuring head 27 and annular eddy current measuring head 28, and annular eddy current measuring head 28 is located at the bottom of sensor fixture 26, and laser ranging The measuring head 27 is arranged in the middle of the sensor fixing device 26, and the center of the laser ranging measuring head 27 and the center of the annular eddy current measuring head 28 are located on the same axis. Guarantee that the measuring point of laser ranging probe 27 and annular eddy current measuring probe 28 is the same point, the measuring surface of laser ranging measuring probe 27 and the measuring surface distance of annular eddy current measuring probe 28 are d, in the present embodiment d= 38mm. The laser distance measuring head 27 can measure the distance from the measuring surface to the interface of the coating 29 as M1, and the annular eddy current measuring head 28 can measure the distance from the measuring surface to the inner surface of the coating 29 as M2, and the measured position can be obtained by calculating the geometric relationship The coating thickness h=M1-M2-d.
一种采用本实施例所述固体火箭发动机涂层厚度自动检测装置进行固体火箭发动机涂层厚度检测的方法，本实施例中的固体火箭发动机长2200mm，直径380mm，在前段弧面段检测10个截面，后端弧面段检测10个截面，中间直筒段检测35个截面，内部涂层的厚度在1.5-5mm之间。A method for detecting the coating thickness of a solid rocket motor using the automatic detection device for the coating thickness of the solid rocket motor described in this embodiment. The solid rocket motor in this embodiment is 2200mm long and 380mm in diameter, and 10 pieces are detected in the front arc section Cross-sections, 10 cross-sections are tested on the rear arc section, 35 cross-sections are tested on the middle straight section, and the thickness of the inner coating is between 1.5-5mm.
包括以下步骤：Include the following steps:
1)将待检固体火箭发动机16放置在测量台上的主动支撑轮21和从动支撑轮19上，待检固体火箭发动机16的一端顶住工件左顶装置24，移动工件右顶装置17顶住待检固体火箭发动机16的另一端，通过控制测量系统控制主动支撑轮21旋转，从而带动待检固体火箭发动机16、从动支撑轮19和编码器18码盘旋转；1) Place the solid rocket motor 16 to be inspected on the active support wheel 21 and the driven support wheel 19 on the measuring platform, one end of the solid rocket motor 16 to be inspected will withstand the workpiece left top device 24, and the workpiece right top device 17 will be moved Hold the other end of the solid rocket motor 16 to be checked, and control the rotation of the active support wheel 21 through the control measurement system, thereby driving the solid rocket motor 16 to be checked, the driven support wheel 19 and the code disc of the encoder 18 to rotate;
2)通过控制测量系统控制主测量臂11上下移动，对准待检固体火箭发动机16开口；2) Control the main measuring arm 11 to move up and down by controlling the measuring system, aiming at the opening of the solid rocket motor 16 to be checked;
3)通过控制测量系统控制主测量臂11前后移动、辅助测量臂13旋转以及组合传感器15旋转，使得组合传感器15在量程范围内激光束垂直入射待检固体火箭发动机16的第一个检测内表面；3) Control the main measuring arm 11 to move back and forth, the auxiliary measuring arm 13 to rotate, and the combination sensor 15 to rotate by controlling the measurement system, so that the laser beam of the combination sensor 15 is within the measuring range and is vertically incident on the first detection inner surface of the solid rocket motor 16 to be tested. ;
4)控制测量系统检测零点开关20的信号，当检测到信号时，根据编码器18的反馈信号进行激光和涡流数据采集，并通过式h＝M1-M2-d计算得出检测点厚度，当再次检测到零点开关时，该截面检测完毕，保存第一个检测截面涂层一周的厚度值；控制测量系统通过控制主测量臂11移动、辅助测量臂13旋转和组合传感器15旋转，调整组合传感器15的位置和方向，使得组合传感器15在量程范围内激光束垂直入射到待检固体火箭发动机16第2个检测内表面，重复上述步骤得到第二个截面的涂层厚度值；进而可以得到第3-55个截面的检测厚度值，最终得出待检固体火箭发动机16涂层的实际厚度，其数据显示见图5-7，检测结果得到的最大厚度值为4.51mm，最小值为1.51mm。55个截面检测共需要2个小时40分钟，实际检测速度依火箭发动机尺寸、检测截面数和检测横向分辨率而定。系统在弧面段和直筒段的检测精度分别为0.1mm和0.05mm。4) Control the measurement system to detect the signal of the zero point switch 20. When the signal is detected, the laser and eddy current data are collected according to the feedback signal of the encoder 18, and the thickness of the detection point is calculated by the formula h=M1-M2-d. When When the zero point switch is detected again, the detection of the section is completed, and the thickness value of the first detection section coating is saved; the control measurement system adjusts the combined sensor by controlling the movement of the main measuring arm 11, the rotation of the auxiliary measuring arm 13 and the rotation of the combined sensor 15. 15, the position and direction of the combined sensor 15 make the laser beam vertically incident on the second detection inner surface of the solid rocket motor 16 to be checked within the measuring range, and repeat the above steps to obtain the coating thickness value of the second section; and then the second section can be obtained. The detected thickness values of 3-55 sections finally get the actual thickness of the solid rocket motor 16 coating to be inspected. The data display is shown in Figure 5-7. The maximum thickness value obtained from the test results is 4.51mm, and the minimum value is 1.51mm . It takes 2 hours and 40 minutes to detect 55 cross-sections. The actual detection speed depends on the size of the rocket engine, the number of detection cross-sections and the horizontal resolution of the detection. The detection accuracy of the system on the arc section and the straight section is 0.1mm and 0.05mm respectively.
Claims (3)
- null1. a solid propellant rocket coating layer thickness automatic detection device，It is characterized in that: include by measuring arm base (1)、Measure arm support (4)、Main measurement arm (11)、The measuring mechanism that subsidiary arm (13) and combination sensor (15) form、By workpiece support platform (25)、The left ejection device of workpiece (24)、The right ejection device of workpiece (17)、Active support wheel (21)、Driven support takes turns (19)、The test desk that encoder (18) and Zero-point switch (20) form、Five motors (2、6、7、8、22) and control measurement system，Measuring, arm base (1) is provided with line slideway II (3)，First motor (2) is located at measurement arm base (1) and above and is connected with line slideway II (3)，The lower end measuring arm support (4) is connected with the slide block of line slideway II (3) so that measuring arm support (4) to measure the upper side-to-side movement of arm base (1)，It is provided with line slideway I (5) in the right panel face measuring arm support (4)，Second motor (8) is located at measurement arm support (4) and above and is connected with line slideway I (5)，The left end of main measurement arm (11) is connected with the slide block of line slideway I (5) so that main measurement arm (11) is measuring the upper up and down motion of arm support (4)，The left end of subsidiary arm (13) is connected by joint I (12) with the right-hand member of main measurement arm (11)，3rd motor (7) is located at measurement arm support (4) and above and drives subsidiary arm (13) to rotate relative to main measurement arm (11) by steel wire rope I (9)，Combination sensor (15) is located at the right-hand member of subsidiary arm (13)，4th motor (6) is located at measurement arm support (4) and above and drives combination sensor (15) to rotate at the right-hand member of subsidiary arm (13) by steel wire rope II (10)；nullWorkpiece support platform (25) is located at the right side measuring arm base (1) and is positioned in same level with measuring arm base (1)，The left ejection device of workpiece (24) and the right ejection device of workpiece (17) are respectively provided at the two ends, left and right of workpiece support platform (25) table top，Active support wheel (21) and the driven wheel (19) that supports are respectively provided at the left and right sides of workpiece support platform (25) table top，5th motor (22) is located at workpiece support platform (25) and above and is connected with Active support wheel (21) by belt drive (23)，Encoder (18) is located at driven support on wheel (19)，Zero-point switch (20) is located in Active support wheel (21)，Control measurement system respectively with five motors (2、6、7、8、22)、Combination sensor (15)、Zero-point switch (20) and encoder (18) electrical connection，For controlling five motors (2、6、7、8、22) work，When the signal of Zero-point switch (20) being detected，Control combination sensor (15) and encoder (18) carry out the collection of detection data.
- 2. a kind of solid propellant rocket coating layer thickness automatic detection device according to claim 1, it is characterized in that: described combination sensor (15) is made up of sensor fastening device (26), laser ranging gauge head (27) and toroidal vortex flow gauge head (28), toroidal vortex flow gauge head (28) is located at the bottom of sensor fastening device (26), laser ranging gauge head (27) is located at the middle part of sensor fastening device (26), and makes the center of laser ranging gauge head (27) and toroidal vortex flow gauge head (28) be centrally located at same axis.
- 3. one kind adopts the method that solid propellant rocket coating layer thickness automatic detection device described in claim 1 or 2 carries out solid propellant rocket coat thickness detection, it is characterised in that: comprise the following steps:1) solid propellant rocket to be checked (16) is placed on test desk, Active support wheel (21) rotation is controlled, thus driving solid propellant rocket to be checked (16), driven support wheel (19) and encoder (18) code-disc to rotate by controlling measurement system；2) control main measurement arm (11) by control measurement system to move up and down, be directed at solid propellant rocket to be checked (16) opening；3) by controlling, the measurement system main measurement arm (11) of control is movable, subsidiary arm (13) rotates and combination sensor (15) rotates so that combination sensor (15) detects position inner surface in range ability inner laser bundle vertical incidence solid propellant rocket to be checked (16)；4) signal of measurement system detection Zero-point switch (20) is controlled, when a signal has been detected, feedback signal according to encoder (18) carries out laser and eddy current data collection, finally draws the actual (real) thickness of solid propellant rocket to be checked (16) coating.
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| CN107961912A (en) * | 2017-10-13 | 2018-04-27 | 天津市久跃科技有限公司 | One kind is exempted to polish intelligent spray equipment |
| CN108663366A (en) * | 2018-03-29 | 2018-10-16 | 北京理工大学 | A kind of solid propellant rocket coated inside coating quality detection device |
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| CN113586887A (en) * | 2021-06-23 | 2021-11-02 | 北京航空航天大学 | Device and method for acquiring surface image of inner cavity of solid rocket engine |
| CN113776419A (en) * | 2021-08-07 | 2021-12-10 | 爱德森（厦门）电子有限公司 | Method and device for thickness measurement of eddy current coating using dual-crystal ultrasonic sensor assisted triggering |
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| CN114152183B (en) * | 2021-11-15 | 2023-05-26 | 中北大学 | Eddy current measurement correction method for coating thickness of workpiece with continuously variable curvature |
| CN114353656A (en) * | 2022-01-11 | 2022-04-15 | 中北大学 | Eddy current measurement curved surface correction method for thickness of coating of workpiece with gradually-changing curvature |
| CN114353656B (en) * | 2022-01-11 | 2024-01-30 | 中北大学 | Vortex measurement curved surface correction method for gradually-changed curvature workpiece coating thickness |
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Application publication date: 20160727 |
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