CN109398753B - Device and method for detecting flick amount and flick direction of aircraft joint hole - Google Patents
Device and method for detecting flick amount and flick direction of aircraft joint hole Download PDFInfo
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- CN109398753B CN109398753B CN201811464802.2A CN201811464802A CN109398753B CN 109398753 B CN109398753 B CN 109398753B CN 201811464802 A CN201811464802 A CN 201811464802A CN 109398753 B CN109398753 B CN 109398753B
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- 238000000034 method Methods 0.000 title claims description 9
- 238000001514 detection method Methods 0.000 claims abstract description 12
- 239000003550 marker Substances 0.000 claims description 6
- 238000003825 pressing Methods 0.000 claims description 5
- 238000004519 manufacturing process Methods 0.000 claims description 4
- 238000003780 insertion Methods 0.000 claims description 2
- 230000037431 insertion Effects 0.000 claims description 2
- 238000005259 measurement Methods 0.000 abstract description 3
- 210000001503 joint Anatomy 0.000 description 2
- 239000000853 adhesive Substances 0.000 description 1
- 230000001070 adhesive effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 229920003023 plastic Polymers 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/60—Testing or inspecting aircraft components or systems
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
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- Engineering & Computer Science (AREA)
- Manufacturing & Machinery (AREA)
- Transportation (AREA)
- Aviation & Aerospace Engineering (AREA)
- Force Measurement Appropriate To Specific Purposes (AREA)
Abstract
The invention discloses a detection device capable of accurately measuring the flicking amount and flicking direction of an aircraft joint hole, which comprises a dial indicator and a shell consisting of an upper shell and a lower shell, wherein a guide hole for inserting a dial indicator rod is arranged in the middle of the top of the shell, a mandril is arranged below the dial indicator rod in a sliding manner, the lower end of the mandril is provided with a flicking device, the flicking device comprises a left connecting rod, a right connecting rod, a spring, a left flicking rod and a right flicking rod, the upper ends of the left connecting rod and the right connecting rod are respectively hinged with the lower end of the mandril, the lower ends of the left flicking rod and the right flicking rod are rotatably arranged in the shell through bolts, the lower ends of the left connecting rod and the right connecting rod are respectively hinged with the middle parts of the left flicking rod and the right flicking rod, the spring is arranged between the left connecting rod and the connecting rod, and flicking grooves corresponding to the left flicking rod and the right flicking rod are respectively arranged on two sides of the lower part of the shell. The invention realizes the accurate measurement of the spring-open quantity value and the direction of the joint hole, and avoids the situation that the subsequent parts cannot be butted when the subsequent parts are butted due to the out-of-tolerance of the spring-open quantity of the joint hole.
Description
Technical Field
The invention relates to a device and a method for detecting the flick amount and flick direction of an aircraft joint hole.
Background
Along with improvement of airplane manufacturing and assembly requirements, joint coaxiality requirements during butt joint between components are continuously improved, the traditional method for checking the joint hole flick amount by checking a bolt is adopted, because the limit of the diameter of the bolt is checked, the joint hole flick amount can only be checked within a certain control range, the accurate numerical value of the flick amount can not be accurately detected, the flick direction of the joint hole can not be checked, and when the requirement on the butt joint coaxiality of the components is higher, or the direction requirement on the crossing point flick amount exists, the traditional bolt checking method can not meet the measurement requirement.
Disclosure of Invention
The invention aims to overcome the defects of the prior art and provides a device for detecting the flick amount and flick direction of an aircraft joint hole.
The technical problems solved by the invention are realized by adopting the following technical scheme:
the utility model provides a detection device of aircraft joint hole bullet volume of opening and bullet direction, includes the amesdial and comprises last casing and lower casing the casing, and the casing is big-end-up's ladder cylindricality structure, is equipped with the guiding hole that supplies amesdial gauge rod male in the middle of the casing top, and the below slip of amesdial gauge rod is equipped with the ejector pin, and the lower extreme of ejector pin is equipped with the bullet device, and the bullet device of opening includes left connecting rod, right connecting rod, spring, left bullet open rod and right bullet open rod, the upper end of left connecting rod and right connecting rod is articulated with the lower extreme of ejector pin respectively, and the lower extreme of left bullet open rod and right bullet open rod passes through the rotatable installation of bolt inside the casing, and the lower extreme of left connecting rod and right connecting rod is articulated with the middle part of left bullet open rod and right bullet open rod respectively, and the spring mounting is equipped with the bullet fluting that corresponds left bullet open rod and right bullet open rod respectively in casing lower part both sides.
Further, the ejecting ends of the left ejecting rod and the right ejecting rod are of ball structures.
Further, a light-emitting diode is arranged at the inner upper part of the shell, a groove corresponding to the light-emitting diode is arranged on the lower shell, a lampshade is embedded in the groove, a contact switch is arranged at the inner lower part of the shell, a contact of the contact switch protrudes out of the upper shell, a battery box is arranged in the shell, and the battery box connects the light-emitting diode and the contact switch into a closed loop through a wire; the light emitting diode works in a normal state; when the contact of the contact switch is pressed, the light-emitting diode is extinguished.
Further, the body cover of casing is equipped with the pointer ring, and the outside of pointer ring is equipped with two angle pointers and a direction pointer, and wherein, two angle pointers symmetry set up, and the direction pointer sets up perpendicularly with the angle pointer, and the direction of direction pointer is unanimous with the bulge direction of contact switch.
Further, a pointer ring positioning hole is formed in the shell, and the pointer ring is fixed to the shell through a set screw.
Further, the inside of lower casing is equipped with the wiring groove, and the wire passes through the preforming pressure equipment and is in the wiring groove.
Further, a locking hole is formed in one side of the upper portion of the shell, and a locking screw used for being matched and locked with the shaft portion of the dial indicator is arranged in the locking hole.
Further, the upper shell and the lower shell are fixedly connected through a connecting screw.
The method for detecting the flick amount and the flick direction by adopting the detection device for the flick amount and the flick direction of the aircraft joint hole comprises the following steps:
a first step of; the dial indicator is zeroed, a marker post part of the dial indicator is inserted into a guide hole of the shell, so that the bottom of the thimble is zeroed after being contacted with the upper part of the ejector rod, and the marker post of the dial indicator is fixed through a locking screw;
a second step; manufacturing a set of positioning device, wherein the positioning device comprises a positioning device body and a bushing with a dial on the surface, a notch corresponding to the zero graduation on the dial is arranged on the bushing, and a bolt hole corresponding to the notch of the dial is arranged on the positioning device body;
thirdly, inserting a bushing with a dial into the positioner body, rotating the bushing to align a zero notch on the bushing with a bolt hole of the positioner body, and press-fitting the bushing on the positioner body through the zero bolt;
fourthly, inserting the detection device of the flick amount and flick direction of the aircraft joint hole into the inner holes of the bushing and the part joint, rotating the shell to enable the flick ends of the left flick rod and the right flick rod to be respectively in contact with the hole wall of the part joint, observing the reading change condition of the dial indicator, namely the flick amount value of the joint hole relative to the positioner body when the reading change is maximum, simultaneously observing scale values pointed by two angle pointers on the pointer ring in a positive value area and a negative value area, and recording angle values (two positive values and negative values) corresponding to the angle pointers at the moment;
the shell is rotated again, the rotation at the moment rotates 90 degrees clockwise or anticlockwise towards the angle pointed by the angle pointer respectively, whether the light-emitting diode is extinguished is observed, when the light-emitting diode is extinguished, the area pointed by the direction pointer is observed, when the direction pointer is positive, the flick amount direction is positive, and the reading is the reading pointed by the angle pointer in a positive area; when the direction pointer is negative, the flick amount direction is negative, and the reading is that indicated by the angle pointer in a negative area, so that the magnitude and the direction of the flick amount of the joint hole can be accurately read.
The invention realizes the accurate measurement of the spring-open quantity value and the direction of the joint hole, can effectively judge whether the spring-open quantity of the joint hole meets the assembly requirement when the assembly of the parts is completed, and avoids the situation that the subsequent parts cannot be butted when the subsequent parts are butted due to the out-of-tolerance spring-open quantity of the joint hole.
Drawings
FIG. 1 is a schematic view of the structure of the upper housing in the preferred embodiment of the present invention;
FIG. 2 is a schematic view of the structure of the lower housing according to the preferred embodiment of the present invention;
FIG. 3 is a schematic view of the structure of the pointer ring in the preferred embodiment of the present invention;
FIG. 4 is a front cross-sectional view of a preferred embodiment of the present invention;
FIG. 5 is a rear cross-sectional view of a preferred embodiment of the present invention;
FIG. 6 is a schematic representation of the invention in operation;
in the drawing, dial indicator 1, housing 2, connecting screw 3, locking screw 4, bolt 5, contact switch 6, pointer ring 7, set screw 8, lamp shade 9, light emitting diode 10, battery case 11, wire 12, pressing piece 13, ejector rod 14, left link 15, right link 16, spring 17, left pop-up lever 18, right pop-up lever 19, part joint 20, positioner body 21, bushing 22, dial 23, zero bolt 24, angle pointer 71, direction pointer 72, upper housing 201, and lower housing 202.
Description of the embodiments
The invention is further described with reference to the following detailed drawings in order to make the technical means, the creation characteristics, the achievement of the purpose and the effect of the implementation of the invention easy to understand.
Referring to fig. 1, the detection device for the flicking amount and flicking direction of the aircraft joint hole shown in fig. 5 comprises a dial gauge 1 and a shell 2 consisting of an upper shell 201 and a lower shell 202, wherein the shell 2 is of a stepped cylindrical structure with a large upper part and a small lower part, a guide hole for the insertion of the dial gauge 1 is arranged in the middle of the top of the shell 2, a mandril 14 is slidably arranged below the dial gauge 1, the lower end of the mandril 14 is provided with a flicking device, the flicking device comprises a left connecting rod 15, a right connecting rod 16, a spring 17, a left flicking rod 18 and a right flicking rod 19, the upper ends of the left connecting rod 15 and the right connecting rod 16 are respectively hinged with the lower ends of the mandril 14, the lower ends of the left connecting rod 15 and the right flicking rod 19 are respectively hinged with the middle parts of the left flicking rod 18 and the right flicking rod 19, the spring 17 is arranged between the left connecting rod 15 and the connecting rod 24, and grooves corresponding to the left flicking rod 18 and the right flicking rod 19 are respectively arranged on two sides of the lower part of the shell 2.
Further, the ejecting ends of the left ejecting rod 18 and the right ejecting rod 19 are ball structures.
Further, the upper inner part of the shell 2 is provided with a light emitting diode 10, the lower shell 202 is provided with a groove corresponding to the light emitting diode 10, the groove is embedded with a lampshade 9, and more preferably, the lampshade 9 is made of red transparent plastic, the lower inner part of the shell 2 is provided with a contact switch 6, a contact of the contact switch 6 protrudes out of the upper shell 201, a battery box 11 is arranged in the shell 2, and the battery box 11 connects the light emitting diode 10 and the contact switch 6 into a closed loop through a lead 12; the light emitting diode 10 operates in a normal state, and when the contact of the contact switch 6 is pressed, the light emitting diode 10 is extinguished.
Further, the body of the housing 2 is sleeved with a pointer ring 7, two angle pointers 71 and a direction pointer 72 are arranged outside the pointer ring 7, wherein the two angle pointers 71 are symmetrically arranged, the direction pointer 72 is perpendicular to the angle pointer 71, and the pointing direction of the direction pointer 72 is consistent with the protruding direction of the contact switch 6.
Further, a pointer ring positioning hole is formed in the shell, and the pointer ring 7 is fixed to the shell through a set screw 8.
Further, a wiring groove is formed in the lower shell, and the wire 12 is pressed into the wiring groove through the pressing piece 13.
Further, a locking hole is formed in one side of the upper portion of the shell, and a locking screw 4 used for being matched and locked with the shaft portion of the dial gauge 1 is arranged in the locking hole.
Further, the upper shell and the lower shell are fixedly connected through a connecting screw 3.
When the detection device is manufactured, the battery box 11 is adhered to the lower shell 202, the contact switch 6 is placed in the switch groove of the lower shell 202, the contact switch 611 is adhered to the lower shell 202 through an adhesive, the eight pressing sheets are screwed with the lower shell through connecting screws, the wires are ensured not to be ejected from the wire grooves,
referring to a method for detecting the flick amount and the flick direction of an aircraft joint hole in fig. 6, the method comprises the following steps:
a first step of; the dial indicator 1 is zeroed, the marker post part of the dial indicator 1 is inserted into the guide hole of the shell 2, the bottom of the thimble is zeroed after contacting with the upper part of the ejector rod 14, and the marker post of the dial indicator is fixed through the locking screw 4;
a second step; manufacturing a set of positioning device, wherein the positioning device comprises a positioning device body 21 and a bushing 22 with a dial 23 on the surface, a notch corresponding to the zero graduation on the dial 23 is arranged on the bushing 22, and a bolt hole corresponding to the notch of the dial 23 is arranged on the positioning device body 21;
thirdly, inserting a bush 22 with a dial 23 into the positioner body 21, rotating the bush 22 to a position that zero notches on the bush 22 are aligned with bolt holes of the positioner body 21, and pressing the bush 22 on the positioner body 21 through zero bolts 24;
fourthly, inserting a detection device of the flick amount and the flick direction of the aircraft joint hole into inner holes of the bushing 22 and the part joint 204, rotating the shell 2 to enable the flick ends of the left flick rod 18 and the right flick rod 19 to be respectively contacted with the hole wall of the part joint, observing the reading change condition of the dial indicator, namely the flick amount value of the joint hole relative to the positioner body 21 when the reading change is maximum, simultaneously observing scale values pointed by two angle pointers on the pointer ring 7 in a positive value area and a negative value area, and recording angle values (two positive values and negative values) corresponding to the angle pointers at the moment;
the shell 2 is rotated again, the rotation at the moment rotates 90 degrees clockwise or anticlockwise towards the angle pointed by the angle pointer respectively, whether the light-emitting diode is extinguished is observed, when the light-emitting diode is extinguished, the area pointed by the direction pointer is observed, when the direction pointer is positive, the flick amount direction is positive, and the reading is the reading pointed by the angle pointer in a positive area; when the direction pointer is negative, the flick amount direction is negative, and the reading is that indicated by the angle pointer in a negative area, so that the magnitude and the direction of the flick amount of the joint hole can be accurately read.
The working principle of the invention is as follows: the diameter of the upper half part of the shell of the detection device is consistent with the inner diameter of the lining 22, so that the shell can be inserted into the lining 22, an accurate hole position can be found, the lower half part of the shell stretches into a hole of a part joint 20 to be detected, the left spring opening rod 18 and the right spring opening rod 19 of the spring are respectively opened in a free state, the inner diameters of the spring ends of the two ball head structures are the same as the inner diameters of theoretical joint holes, when the part joint holes deviate relative to the lining 22 of the locator body, the hole wall at one side of the part joint holes can press the spring opening rod to enable the spring opening rod to shrink inwards, then the connecting rod is driven to move upwards, so that the ejector rod 14 moves upwards in a cavity formed by the upper shell and the lower shell, the ejector rod 14 moves upwards to press the ejector pin of the dial gauge, the dial gauge is changed, the reading of the hole spring opening quantity is read, the angle pointer 71 on the detection device indicates the angle value of the joint spring opening quantity in a positive value area and a negative value area, and the contact switch 6 preassembled on the lower half part of the shell of the detection device is in contact with the inner wall of the hole of the part joint 20 at the moment, so that the switch is opened, the light-emitting diode is turned off, and the direction of the light emitting diode is turned off, and the direction of the contact point on the contact switch 6 is in the positive value area or negative value area.
The foregoing has shown and described the basic principles and main features of the present invention and the advantages of the present invention. It will be understood by those skilled in the art that the present invention is not limited to the embodiments described above, and that the above embodiments and descriptions are merely illustrative of the principles of the present invention, and various changes and modifications may be made without departing from the spirit and scope of the invention, which is defined in the appended claims. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (8)
1. The device for detecting the flicking amount and flicking direction of the aircraft joint hole comprises a dial indicator (1) and a shell (2) consisting of an upper shell (201) and a lower shell (202), and is characterized in that the shell (2) is of a stepped cylindrical structure with a big top and a small bottom, a guide hole for the insertion of the dial indicator (1) is formed in the middle of the top of the shell (2), a mandril (14) is slidably arranged below the dial indicator (1) and below the dial indicator, the lower end of the mandril (14) is provided with a flicking device, the flicking device comprises a left connecting rod (15), a right connecting rod (16), a spring (17), a left flicking rod (18) and a right flicking rod (19), the upper ends of the left connecting rod (15) and the right connecting rod (16) are hinged with the lower end of the mandril (14) respectively, the lower ends of the left connecting rod (15) and the right flicking rod (19) are rotatably arranged in the shell through bolts (5), the lower ends of the left connecting rod (15) and the right connecting rod (16) are hinged with the middle parts of the left flicking rod (18) and the right flicking rod (19) respectively, and the left connecting rod (18) and the left connecting rod (24) are arranged between the left connecting rod (18) and the right flicking rod (19) and the left connecting rod (24) and the left flicking rod (2) respectively; the ejecting ends of the left ejecting rod (18) and the right ejecting rod (19) are all ball structures; the detection device further comprises a positioning device, the positioning device comprises a positioning device body (21) and a bushing (22) with a dial (23) on the surface, a notch corresponding to the zero scale on the dial (23) is arranged on the bushing (22), and a bolt hole corresponding to the notch of the dial (23) is arranged on the positioning device body (21).
2. The device for detecting the flick amount and the flick direction of the aircraft joint hole according to claim 1, wherein the upper inner part of the shell (2) is provided with a light emitting diode (10), the lower shell (202) is provided with a groove corresponding to the light emitting diode (10), the groove is embedded with a lampshade (9), the lower inner part of the shell (2) is provided with a contact switch (6), a contact of the contact switch (6) protrudes out of the upper shell (201), a battery box (11) is arranged in the shell (2), and the battery box (11) connects the light emitting diode (10) and the contact switch (6) into a closed loop through a lead (12); the light emitting diode (10) works in a normal state; when the contact of the contact switch (6) is pressed, the light-emitting diode (10) is extinguished.
3. The device for detecting the flick amount and the flick direction of the aircraft joint hole according to claim 2, wherein the body of the housing (2) is sleeved with a pointer ring (7), two angle pointers (71) and one direction pointer (72) are arranged outside the pointer ring (7), the two angle pointers (71) are symmetrically arranged, the direction pointer (72) is perpendicular to the angle pointer (71), and the pointing direction of the direction pointer (72) is consistent with the protruding direction of the contact switch (6).
4. The device for detecting the flick amount and the flick direction of the joint hole of the airplane according to claim 2, wherein the shell is provided with a pointer ring positioning hole, and the pointer ring (7) is fixed on the shell through a set screw (8).
5. The device for detecting the flick amount and the flick direction of the aircraft joint hole according to claim 2, wherein the lower housing is internally provided with a wiring groove, and the wire (12) is pressed into the wiring groove by a pressing sheet (13).
6. The device for detecting the flick amount and the flick direction of the aircraft joint hole according to claim 1, wherein a locking hole is formed in one side of the upper part of the shell, and a locking screw (4) for being matched and locked with the shaft part of the dial indicator (1) is arranged in the locking hole.
7. The device for detecting the flick amount and the flick direction of the joint hole of the airplane according to claim 1, wherein the upper shell and the lower shell are fixedly connected through a connecting screw (3).
8. A method for detecting the flick amount and the flick direction by using the device for detecting the flick amount and the flick direction of the joint hole of an aircraft according to claim 3, comprising the steps of:
a first step of; the dial indicator (1) is zeroed, a marker post part of the dial indicator (1) is inserted into a guide hole of the shell (2), the bottom of the thimble is zeroed after being contacted with the upper part of the ejector rod (14), and the marker post of the dial indicator is fixed through the locking screw (4);
a second step; manufacturing a set of positioning devices;
thirdly, inserting a bushing (22) with a dial (23) into the positioner body (21), rotating the bushing (22) to align zero notches on the bushing (22) with bolt holes of the positioner body (21), and press-fitting the bushing (22) on the positioner body (21) through zero bolts (24);
fourthly, inserting a detection device of the flick amount and flick direction of an aircraft joint hole into inner holes of a bushing (22) and a part joint (204), rotating a shell (2) to enable the flick ends of a left flick rod (18) and a right flick rod (19) to be respectively in contact with the hole wall of the part joint, observing the reading change condition of a dial indicator, namely the flick amount value of the joint hole relative to a positioner body (21) when the reading change is maximum, observing scale values pointed by two angle pointers on a pointer ring (7) in a positive value area and a negative value area, and recording angle values (positive value and negative value) corresponding to the angle pointers at the moment;
the shell (2) is rotated again, the rotation at the moment rotates 90 degrees clockwise or anticlockwise towards the angle pointed by the angle pointer respectively, whether the light-emitting diode is extinguished is observed, when the light-emitting diode is extinguished, the area pointed by the direction pointer is observed, when the direction pointer is positive, the flick amount direction is positive, and the reading is the reading pointed by the angle pointer in a positive area; when the direction pointer is negative, the flick amount direction is negative, and the reading is that indicated by the angle pointer in a negative area, so that the magnitude and the direction of the flick amount of the joint hole can be accurately read.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811464802.2A CN109398753B (en) | 2018-12-03 | 2018-12-03 | Device and method for detecting flick amount and flick direction of aircraft joint hole |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811464802.2A CN109398753B (en) | 2018-12-03 | 2018-12-03 | Device and method for detecting flick amount and flick direction of aircraft joint hole |
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| Publication Number | Publication Date |
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| CN109398753A CN109398753A (en) | 2019-03-01 |
| CN109398753B true CN109398753B (en) | 2023-06-02 |
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| CN201811464802.2A Active CN109398753B (en) | 2018-12-03 | 2018-12-03 | Device and method for detecting flick amount and flick direction of aircraft joint hole |
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| CN112417584B (en) * | 2020-10-10 | 2022-11-18 | 江西洪都航空工业股份有限公司 | Integrated resistance reduction design method for guided missile wire groove and sliding block separation socket |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR100962885B1 (en) * | 2007-06-13 | 2010-06-09 | 현대자동차주식회사 | Starter Brushes Abrasion Meter |
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|---|---|---|---|---|
| CN201716072U (en) * | 2010-05-20 | 2011-01-19 | 江苏宜川仪表有限公司 | Operated liquid level meter with adjustable zero position |
| CN102207427A (en) * | 2010-11-23 | 2011-10-05 | 浙江豪情汽车制造有限公司 | Detection device for thermoatat |
| JP2015079221A (en) * | 2013-10-18 | 2015-04-23 | 三菱電機株式会社 | Optical element support device and adjustment method of optical element support device |
| KR101478711B1 (en) * | 2014-07-28 | 2015-01-02 | 현원재 | Ultrasonic inspection device for detecting micro-scale cracks |
| CN205279920U (en) * | 2015-12-08 | 2016-06-01 | 山西北方机械制造有限责任公司 | Deep hole internal diameter alignment detection device |
| CN209467348U (en) * | 2018-12-03 | 2019-10-08 | 江西洪都航空工业集团有限责任公司 | A kind of survey aircraft nipple orifice amount of flicking and the detection device for flicking direction |
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| CN109398753A (en) | 2019-03-01 |
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