CN204116284U - A kind of aircraft cellular structural composite material knocks and detects and non-destructive tests device - Google Patents
A kind of aircraft cellular structural composite material knocks and detects and non-destructive tests device Download PDFInfo
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- CN204116284U CN204116284U CN201420625434.6U CN201420625434U CN204116284U CN 204116284 U CN204116284 U CN 204116284U CN 201420625434 U CN201420625434 U CN 201420625434U CN 204116284 U CN204116284 U CN 204116284U
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Abstract
A kind of aircraft cellular structural composite material knocks and detects and non-destructive tests device.It, by knocking detection probe and monitor two parts form, knocks detection probe and is wirelessly connected with monitor; The utility model is to knock detection technique for principle of work, in conjunction with automation equipment technology, modern electronic technology, Digital Signal Analysis and Processing technology and radio network technique, adopt the structure of knocking detection probe and watch-dog and independently separating, connected by WIFI wireless network, realize the wireless transmission of measuring-signal, monitor signal and control signal.In effective WIFI wireless network range, knock detection probe and watch-dog not by Distance geometry environmental limit.Knock detection probe and adopt rechargeable battery powered mode, be easy to portable operation.In addition, this device has that equipment is simple, and cost performance is high, easy to operate, and detection speed is fast, and by features such as the impact of surrounding environment are little, is applicable to Site Detection very much.
Description
Technical field
The utility model belongs to technique for aircraft composite technical field of nondestructive testing, particularly relates to a kind of aircraft cellular structural composite material and knocks detection and non-destructive tests device.
Background technology
Along with the development of aeronautical technology and material science and technology, compound substance obtains and applies more and more widely in civil aircraft.Wherein, honeycomb compound substance is a kind of important type.The wing flap, aileron, fixed fin, horizontal stabilizer, fuselage, floor level, hatch door etc. of some civil aircraft all employ this material.Due to the design feature of honeycomb compound substance, it is easy to occur damage under the effects such as non-design load, construction environment, foreign matter shock.Wherein, panel layering, unsticking are common degree of impairments, and this will directly jeopardize the flight safety of aircraft.Delamination damage is the separation between two-layer or two-layer above material synusia; Sticky de-damage usually occurs between honeycomb core and covering, and the bonding area between covering with secondary electrode structure.Knocking detection technique is one of the most quick and effective Dynamic Non-Destruction Measurement, because equipment is simple, easy to operate, and detection speed is fast, and by features such as the impact of surrounding environment are little, is applicable to Site Detection very much.Before, in Boeing and Airbus Aircraft Structure Repair Manual, will knock detection technique and be used for the damnification recognition method of aircraft cellular structural composite material panel layering, unsticking.
At present, the instruments such as aircraft maintainers's many uses hand hammer, go to knock aircraft cellular structural composite material to be measured surface with suitable dynamics.When there is panel layering and debonding for be measured, can change its intrinsic physical characteristics, " sound " that sends also can change.Therefore, maintainer relies on service experience, manually to knock and subjective judgement, carrys out identification of damage by the sound heard, so not only easily cause erroneous judgement and fail to judge, and operational ton is huge, efficiency is low, maintenance time is long.
Detection is knocked to aircraft cellular structural composite material and the automatic technology research of non-destructive tests is still in the starting stage due to domestic, thus not yet find to meet portable on-line maintenance at present, detection signal aircraft cellular structural composite material that is visual, quantitative and qualitative breakdown diagnosis demand knocks detection and non-destructive tests device.
Summary of the invention
In order to solve the problem, the purpose of this utility model is that providing a kind of aircraft cellular structural composite material to knock detects and non-destructive tests device.
In order to achieve the above object, the aircraft cellular structural composite material that the utility model provides knocks and to detect with non-destructive tests device by knocking detection probe and monitor two parts form, and knocks detection probe and is wirelessly connected with monitor.
Described detection probe of knocking comprises: housing and be arranged on the fan of enclosure interior, printed circuit board (PCB), two charge amplifiers, the first rechargeable battery, the second rechargeable battery, dividing plate, vibrator, two pieces of fixed heads, connecting rod, sensor, tup and two screw rods, wherein: housing is the cuboid body structure be made up of framework, front panel, rear panel, two side panels and top panel, front panel is provided with reset switch, power switch and fan swicth, rear panel is provided with two battery charging inlets and a WIFI antenna, two side panels are formed with respectively a screw rod through hole, for inserting screw rod, top panel is formed with a fan providing holes, fan is arranged in the fan providing holes on top panel, printed circuit board (PCB) utilizes four pillars to be fixed on the below of fan, dividing plate is horizontally set on enclosure interior middle part, two charge amplifiers, the first rechargeable battery and the second rechargeable batteries are installed on dividing plate, two pieces of fixed heads are vertically set on the lower inside of two side panels respectively, it are formed with respectively a through hole, the upper end of vibrator is arranged on fixed head, and both sides are formed with a screw respectively, and utilizes two to run through on two side panels through hole on screw rod through hole and two pieces of fixed heads respectively successively and the front end screw rod be inserted in screw carries out both sides fixes, small end is fixed on vibrator lower end, and tup is connected to connecting rod lower end, sensor is connected with the up-down vibration termination of vibrator, and bottom is connected with tup, printed circuit board (PCB) is provided with power-switching circuit module, microcontroller circuit module, drive circuit module, wireless transmission circuit module and monitoring and protection circuit module, wherein: microcontroller circuit module respectively with charge amplifier, drive circuit module, wireless transmission circuit module is connected with protection circuit module with monitoring, charge amplifier is connected with sensor, drive circuit module is connected with vibrator, wireless transmission circuit module is connected with WIFI antenna, first rechargeable battery is connected with drive circuit module, power-switching circuit module respectively with charge amplifier, microcontroller circuit module is connected with wireless transmission circuit module, monitoring with protection circuit module respectively with the first rechargeable battery, second rechargeable battery, power-switching circuit module, drive circuit module, wireless transmission circuit module is connected with fan.
Described top panel is provided with two handles and a fan net.
Described vibrator adopts direct current dynamic formula vibrator, knocks to be measured surface for driving tup.
Described sensor adopts piezoelectric forces/acceleration dual sensor, and acceleration transducer is used for measurement and the collection of standard component or to be measured surface vibration signals, and force snesor is used for measurement and the collection of tup percussion power signal.
Described dividing plate adopts non-magnetic material, for the electromagnetic isolation between printed circuit board (PCB) and vibrator.
Described monitor comprises a touch screen integrated machine, a fan, a USB interface, a host power switch, display power supply switch, a general supply socket and a total power switch; Wherein: touch screen integrated machine is connected with USB interface by USB serial line interface, be provided with WIFI wireless network card in USB interface, touch screen integrated machine utilizes WIFI wireless network to connect with the WIFI antenna knocked in detection probe and wireless transmission circuit module by the WIFI wireless network card in USB interface.
The aircraft cellular structural composite material that the utility model provides knocks and detects and non-destructive tests device, to knock detection technique for principle of work, in conjunction with automation equipment technology, modern electronic technology, Digital Signal Analysis and Processing technology and radio network technique, adopt the structure of knocking detection probe and watch-dog and independently separating, connected by WIFI wireless network, realize the wireless transmission of measuring-signal, monitor signal and control signal.In effective WIFI wireless network range, knock detection probe and watch-dog not by Distance geometry environmental limit.Knock detection probe and adopt rechargeable battery powered mode, be easy to portable operation.In addition, this device has that equipment is simple, and cost performance is high, easy to operate, and detection speed is fast, and by features such as the impact of surrounding environment are little, is applicable to Site Detection very much.Visual, the quantitative and qualitative breakdown diagnosis demand of portable on-line maintenance, detection signal can be met.
Accompanying drawing explanation
Fig. 1 detects and non-destructive tests device schematic diagram for aircraft cellular structural composite material that the utility model provides knocks.
Fig. 2 (a) detect for aircraft cellular structural composite material that the utility model when observing from front provides knocks with non-destructive tests device in knock detection probe structural perspective.
Fig. 2 (b) detect for aircraft cellular structural composite material that the utility model when observing from the back side provides knocks with non-destructive tests device in knock detection probe structural perspective.
Fig. 2 (c) detect for aircraft cellular structural composite material that the utility model when observing from end face provides knocks with non-destructive tests device in knock detection probe structural perspective.
Fig. 3 detect for aircraft cellular structural composite material that the utility model provides knocks with non-destructive tests device in knock detection probe internal structural map.
Fig. 4 detects and monitor external structure figure in non-destructive tests device for aircraft cellular structural composite material that the utility model provides knocks.
Fig. 5 detects and non-destructive tests apparatus system block diagram for aircraft cellular structural composite material that the utility model provides knocks.
Embodiment
Below in conjunction with the drawings and specific embodiments to the aircraft cellular structural composite material that the utility model provides knock detection and non-destructive tests device be described in detail.
As shown in Figure 1, the aircraft cellular structural composite material that the utility model provides knocks and to detect with non-destructive tests device by knocking detection probe 1 and monitor 2 two parts form, and knocks detection probe 1 and is wirelessly connected with monitor 2;
Described detection probe 1 of knocking is placed on standard component or to be measured on the surface, by WIFI wireless network, receive and resolve the steering order of monitor 2, automatically knocking material surface by certain frequency, dynamics, speed and Real-time Collection and send vibration measuring signal to monitor 2.
As shown in Fig. 2, Fig. 3 and Fig. 5, described detection probe 1 of knocking comprises: housing and be arranged on the fan 16 of enclosure interior, printed circuit board (PCB) 17, two charge amplifier 19, first rechargeable battery 20a, the second rechargeable battery 20b, dividing plate 21, vibrator 22, two pieces of fixed heads 24, connecting rod 26, sensor 27, tup 28 and two screw rods 13, wherein: housing is the cuboid body structure be made up of framework 3, front panel 4, rear panel 5, two side panels 6 and top panel 7, front panel 4 is provided with reset switch 8, power switch 9 and fan swicth 10, reset switch 8 is for knocking the Program reset of detection probe 1 and reruning, and power switch 9 controls the first rechargeable battery 20a, the second rechargeable battery 20b to the power supply of knocking detection probe 1, and fan swicth 10 is the power control switch of fan 16, rear panel 5 is provided with two battery charging inlets 11 and a WIFI antenna 12, two battery charging inlets 11 for connecting external charger, for being respectively the first rechargeable battery 20a and the second rechargeable battery 20b charges, WIFI antenna 12 is connected with monitor 2 by WIFI wireless network, for realizing the wireless transmission of measuring-signal, monitor signal and control signal, two side panels 6 are formed with respectively a screw rod through hole, for inserting screw rod 13, top panel 7 is formed with a fan providing holes, fan 16 is arranged in the fan providing holes on top panel 7, printed circuit board (PCB) 17 utilizes four pillars 18 to be fixed on the below of fan 16, dividing plate 21 is horizontally set on enclosure interior middle part, two charge amplifier 19, first rechargeable battery 20a and the second rechargeable battery 20b are installed on dividing plate 21, two pieces of fixed heads 24 are vertically set on the lower inside of two side panels 6 respectively, it are formed with respectively a through hole 25, the upper end of vibrator 22 is arranged on fixed head 24, both sides are formed with a screw 23 respectively, and utilize two to run through on two side panels 6 through hole 25 on screw rod through hole and two pieces of fixed heads 24 respectively successively and the front end screw rod 13 be inserted in screw 23 carries out both sides fixes, connecting rod 26 upper end is fixed on vibrator 22 lower end, and tup 28 is connected to connecting rod 26 lower end, sensor 27 is connected with the up-down vibration termination of vibrator 22, and bottom is connected with tup 28, printed circuit board (PCB) 17 is provided with power-switching circuit module 29, microcontroller circuit module 30, drive circuit module 31, wireless transmission circuit module 32 and monitoring and protection circuit module 33, wherein: microcontroller circuit module 30 respectively with charge amplifier 19, drive circuit module 31, wireless transmission circuit module 32 is connected with protection circuit module 33 with monitoring, charge amplifier 19 is connected with sensor 27, drive circuit module 31 is connected with vibrator 22, wireless transmission circuit module 32 is connected with WIFI antenna 12, first rechargeable battery 20a is connected with drive circuit module 31, power-switching circuit module 29 respectively with charge amplifier 19, microcontroller circuit module 30 is connected with wireless transmission circuit module 32, monitoring with protection circuit module 33 respectively with the first rechargeable battery 20a, second rechargeable battery 20b, power-switching circuit module 29, drive circuit module 31, wireless transmission circuit module 32 is connected with fan 16.
Described top panel 7 is provided with two handles 14 and a fan net 15; Handle 14 is for knocking the hand-held handle of detection probe 1, and can realize portable inspectiont, fan net 15 is for the protection of fan 16.
Described vibrator 22 adopts direct current dynamic formula vibrator, knocks to be measured surface for driving tup 28; Sensor 27 adopts piezoelectric forces/acceleration dual sensor, and acceleration transducer is used for measurement and the collection of standard component or to be measured surface vibration signals, and force snesor is used for measurement and the collection of tup percussion power signal; Charge amplifier 19 is for the conversion of vibration signal and percussion power signal and amplification; Dividing plate 21 adopts non-magnetic material, for the electromagnetic isolation between printed circuit board (PCB) 17 and vibrator 22; First rechargeable battery 20a and the second rechargeable battery 20b provides positive and negative direct supply for knocking detection probe 1, wherein the first rechargeable battery 20a is that vibrator 22 is powered, and the second rechargeable battery 20b is respectively printed circuit board (PCB) 17, charge amplifier 19 and fan 16 and powers.
The direct supply that first, second rechargeable battery 20a, 20b provide is converted to the working power needed for other circuit modules by described power-switching circuit module 29; Microcontroller circuit module 30 for exporting control signal (pulse signal), pick-up transducers measuring-signal carry out A/D conversion, receive monitoring and the monitor signal of protection circuit module 33, generate and send packet and send data to wireless transmission circuit module 32, receive wireless transmission circuit module 32 data and also resolve the duty receiving packet, implement to control, judge according to monitor signal each circuit module on printed circuit board (PCB) 17 to vibrator 22 to drive circuit module 31, to monitor and protection circuit module 33 sends guard signal; Drive circuit module 31 by the control signal power amplification of microcontroller circuit module 30, and drives vibrator 22 to vibrate; Wireless transmission circuit module 32 for generating and changing wireless WIFI data, and drives WIFI antenna 12 to send and Received signal strength; Monitoring and protection circuit module 33, for gathering the monitor signal of each circuit module, battery, fan, receive guard signal and cut off general supply.
As shown in Figure 4, described monitor 2 comprises a touch screen integrated machine 34, fan 35, USB interface 36, host power switch 37, display power supply switch 38, general supply socket 39 and a total power switch 40; Wherein: touch screen integrated machine 34 is connected with USB interface 36 by USB serial line interface, be provided with WIFI wireless network card in USB interface 36, touch screen integrated machine 34 utilizes WIFI wireless network to connect with the WIFI antenna 12 knocked in detection probe 1 and wireless transmission circuit module 32 by the WIFI wireless network card in USB interface 36.
Described watch-dog 2 is connected on WIFI wireless network, knocks the transmission packet of detection probe 1 for real-time reception and parsing; Display, analysis and storage measuring-signal and monitor signal, and identify to be measured panel layering and debonding degree; The control information of knocking detection probe 1 is set, generates and receive packet and send data to wireless transmission circuit module 32;
The aircraft cellular structural composite material now provided by the utility model knocks the principle of work detected with non-destructive tests device and is described below:
Suppose that to be measured has fixing rigidity characteristics, be namely subject to after instantaneous external force knocks, material surface free vibration state depends on its quality and material character.Aircraft cellular structural composite material standard component and to be measured belong to same aircraft cellular structural composite material, and standard component is the not damaged part of to be measured, has equal in quality and material character.If to be measured exists panel layering and debonding, its rigidity characteristics can change compared with standard component.To standard component with have to be measured of damage surface to apply after identical instantaneous external force knocks, the free vibration state difference of surface both.Vibration acceleration due to material surface can reflect its free vibration state, and measuring vibrations acceleration just can detect the correlation parameter (i.e. non-destructive tests parameter) of vibrational state.By the relative quantity of standard component and to be measured surface vibration state correlation parameter, thus identify to be measured the panel layering relative to standard component and debonding degree.
Described aircraft cellular structural composite material knocks to detect has four kinds of mode of operations with non-destructive tests device:
A. monitoring mode: monitoring and voltage, the voltage of the first rechargeable battery 20a and the second rechargeable battery 20b, the voltage three kinds of monitor signals of fan power supply of each circuit module power supply on protection circuit module 33 Real-time Collection printed circuit board (PCB) 17, be converted to digital signal through voltage sensor and transfer to microcontroller circuit module 30.If any one monitor signal goes wrong, microcontroller circuit module 30 will send guard signal to monitoring and protection circuit module 33, and monitoring and protection circuit module 33 cut off the general supply of knocking detection probe 1 immediately;
B. pattern is set: staff arrange on monitor 2 knock detection probe 1 knock frequency, dynamics and speed parameter, operation " transmissions " button generates reception packet, is sent to WIFI wireless network by Wireless USB network interface card in USB interface 36.Knock detection probe 1 and receive WIFI wireless network signal by WIFI antenna 12, after being changed by wireless transmission circuit module 32, transfer to microcontroller circuit module 30.Microcontroller circuit module 30 is resolved reception packet and is also obtained knocking frequency, dynamics and speed values, distinguishes the frequency of modulator control signal (pulse signal), amplitude and pulsewidth, and to drive circuit module 31 transmission of control signals.Drive circuit module 31 is loaded on vibrator 22 by after control signal power amplification, and vibrator 22 drives tup 28 up-down vibration standard component surface;
C. measurement pattern: knock sensor 27 Real-time Collection aircraft cellular structural composite material surface vibration acceleration charge signal (time domain) in detection probe 1 and knock dynamics charge signal (time domain), convert charge signal to voltage signal through charge amplifier 19 and amplify, and transferring to microcontroller circuit module 30.Microcontroller circuit module 30 generates and sends packet, is converted to networking signal, is sent to WIFI wireless network through WIFI antenna 12 by wireless transmission circuit module 32.Staff operates " reception " button on monitor 2, receives WIFI wireless network signal by Wireless USB network interface card in USB interface 36.Monitor 2 is resolved and is received packet, calculate, store and time domain cycle of display material surface vibration acceleration signal and amplitude information, the sensitive frequency peak value of frequency domain and phase place, the sensitive frequency energy peak of power spectrum and phase place, knock percussion power angle value and the cycle of detection probe 1;
D. analytical model: monitor 2 calculates the time domain amplitude of material surface vibration acceleration signal between to be measured and standard component and cycle, the sensitive frequency peak value of frequency domain and phase place, the sensitive frequency energy peak of power spectrum and the relative variation of phase place, to judge to be measured panel layering and debonding situation and degree.
It is as follows with the workflow of non-destructive tests device that the aircraft cellular structural composite material that the utility model provides knocks detection:
A. the power switch 9 and the fan swicth 10 that knock detection probe 1 are in " stopping " position; The USB interface 36 of monitor 2 connects Wireless USB network interface card, and host power switch 37 and display power supply switch are in " connection " position;
B. hand-held two handles 14 of staff, will knock detection probe 1 and lie in a horizontal plane in standard component surface.Power switch 9 and fan swicth 10 are in " connection " position, knock detection probe 1 power-up initializing, enter monitoring mode.After 3 seconds, enter the pattern of setting and measurement pattern, obtain the vibration information on standard component surface;
C. hand-held two handles 14 of staff, will knock detection probe 1 and lie in a horizontal plane in be measured surface.Power switch 9 and fan swicth 10 are in " connection " position, knock detection probe 1 power-up initializing, enter monitoring mode.After 3 seconds, enter the pattern of setting and measurement pattern, obtain to be measured surperficial vibration information;
D. enter analytical model, show to be measured panel layering and debonding situation and degree.
Claims (7)
1. an aircraft cellular structural composite material knocks and detects and non-destructive tests device, it is characterized in that: it, by knocking detection probe (1) and monitor (2) two parts form, knocks detection probe (1) and be wirelessly connected with monitor (2).
2. aircraft cellular structural composite material according to claim 1 knocks and detects and non-destructive tests device, it is characterized in that: described detection probe (1) of knocking comprising: housing and be arranged on the fan (16) of enclosure interior, printed circuit board (PCB) (17), two charge amplifiers (19), the first rechargeable battery (20a), the second rechargeable battery (20b), dividing plate (21), vibrator (22), two pieces of fixed heads (24), connecting rod (26), sensor (27), tup (28) and two screw rods (13), wherein: housing is the cuboid body structure be made up of framework (3), front panel (4), rear panel (5), two side panels (6) and top panel (7), front panel (4) is provided with reset switch (8), power switch (9) and fan swicth (10), rear panel (5) is provided with two battery charging inlets (11) and a WIFI antenna (12), two side panels (6) are formed with a screw rod through hole respectively, for inserting screw rod (13), top panel (7) is formed with a fan providing holes, fan (16) is arranged in the fan providing holes on top panel (7), printed circuit board (PCB) (17) utilizes four pillars (18) to be fixed on the below of fan (16), dividing plate (21) is horizontally set on enclosure interior middle part, two charge amplifiers (19), the first rechargeable battery (20a) and the second rechargeable batteries (20b) are installed on dividing plate (21), two pieces of fixed heads (24) are vertically set on the lower inside of two side panels (6) respectively, it are formed with respectively a through hole (25), the upper end of vibrator (22) is arranged on fixed head (24), both sides are formed with a screw (23) respectively, and utilize two to run through the upper screw rod through hole of two side panels (6) and two pieces of upper through holes (25) of fixed heads (24) respectively successively and the front end screw rod (13) be inserted in screw (23) carries out both sides fixes, connecting rod (26) upper end is fixed on vibrator (22) lower end, and tup (28) is connected to connecting rod (26) lower end, sensor (27) is connected with the up-down vibration termination of vibrator (22), and bottom is connected with tup (28), printed circuit board (PCB) (17) is provided with power-switching circuit module (29), microcontroller circuit module (30), drive circuit module (31), wireless transmission circuit module (32) and monitoring and protection circuit module (33), wherein: microcontroller circuit module (30) respectively with charge amplifier (19), drive circuit module (31), wireless transmission circuit module (32) is connected with protection circuit module (33) with monitoring, charge amplifier (19) is connected with sensor (27), drive circuit module (31) is connected with vibrator (22), wireless transmission circuit module (32) is connected with WIFI antenna (12), first rechargeable battery (20a) is connected with drive circuit module (31), power-switching circuit module (29) respectively with charge amplifier (19), microcontroller circuit module (30) is connected with wireless transmission circuit module (32), monitoring with protection circuit module (33) respectively with the first rechargeable battery (20a), second rechargeable battery (20b), power-switching circuit module (29), drive circuit module (31), wireless transmission circuit module (32) is connected with fan (16).
3. aircraft cellular structural composite material according to claim 2 knocks and detects and non-destructive tests device, it is characterized in that: described top panel (7) is provided with two handles (14) and a fan net (15).
4. aircraft cellular structural composite material according to claim 2 knocks and detects and non-destructive tests device, it is characterized in that: described vibrator (22) adopts direct current dynamic formula vibrator, knocks to be measured surface for driving tup (28).
5. aircraft cellular structural composite material according to claim 2 knocks and detects and non-destructive tests device, it is characterized in that: described sensor (27) adopts piezoelectric forces/acceleration dual sensor, acceleration transducer is used for measurement and the collection of standard component or to be measured surface vibration signals, and force snesor is used for measurement and the collection of tup percussion power signal.
6. aircraft cellular structural composite material according to claim 2 knocks and detects and non-destructive tests device, it is characterized in that: described dividing plate (21) adopts non-magnetic material, for the electromagnetic isolation between printed circuit board (PCB) (17) and vibrator (22).
7. aircraft cellular structural composite material according to claim 1 knocks and detects and non-destructive tests device, it is characterized in that: described monitor (2) comprises a touch screen integrated machine (34), a fan (35), a USB interface (36), a host power switch (37), display power supply switch (38), a general supply socket (39) and a total power switch (40); Wherein: touch screen integrated machine (34) is connected with USB interface (36) by USB serial line interface, USB interface is provided with WIFI wireless network card in (36), and touch screen integrated machine (34) utilizes WIFI wireless network to connect with the WIFI antenna (12) knocked in detection probe (1) and wireless transmission circuit module (32) by the WIFI wireless network card in USB interface (36).
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| CN106053600A (en) * | 2016-06-29 | 2016-10-26 | 航天材料及工艺研究所 | Automatic detection system and method for multi-channel impact of composite material adhesive structure |
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| CN106053600A (en) * | 2016-06-29 | 2016-10-26 | 航天材料及工艺研究所 | Automatic detection system and method for multi-channel impact of composite material adhesive structure |
| CN106198728A (en) * | 2016-06-29 | 2016-12-07 | 航天材料及工艺研究所 | The multichannel of a kind of adhesive bonding of composites structure taps detection device |
| CN106053600B (en) * | 2016-06-29 | 2018-12-21 | 航天材料及工艺研究所 | A kind of adhesive bonding of composites structure multichannel taps automatic checkout system and method |
| CN106198728B (en) * | 2016-06-29 | 2019-01-25 | 航天材料及工艺研究所 | A kind of multichannel percussion detection device of adhesive bonding of composites structure |
| CN109342572B (en) * | 2018-11-30 | 2022-02-22 | 中国航空工业集团公司沈阳飞机设计研究所 | Nondestructive testing method and system for corrosion damage of outfield airplane airfoil honeycomb structure |
| CN109342572A (en) * | 2018-11-30 | 2019-02-15 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of outfield plane airfoil honeycomb corrosion damage lossless detection method and system |
| CN109580780A (en) * | 2018-12-14 | 2019-04-05 | 天津工业大学 | Hand-held taps detector and detection method |
| CN110068612A (en) * | 2019-04-11 | 2019-07-30 | 中国民航大学 | A kind of multiple spot percussion more points collection formula technique for aircraft composite detection system |
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