CN110440671B - Detection apparatus for aircraft engine front rectifier machine casket processing subassembly - Google Patents
Detection apparatus for aircraft engine front rectifier machine casket processing subassembly Download PDFInfo
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- CN110440671B CN110440671B CN201910805834.2A CN201910805834A CN110440671B CN 110440671 B CN110440671 B CN 110440671B CN 201910805834 A CN201910805834 A CN 201910805834A CN 110440671 B CN110440671 B CN 110440671B
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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
- G01B5/00—Measuring arrangements characterised by the use of mechanical techniques
- G01B5/003—Measuring of motor parts
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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
- G01B5/00—Measuring arrangements characterised by the use of mechanical techniques
- G01B5/08—Measuring arrangements characterised by the use of mechanical techniques for measuring diameters
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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
- G01B5/00—Measuring arrangements characterised by the use of mechanical techniques
- G01B5/08—Measuring arrangements characterised by the use of mechanical techniques for measuring diameters
- G01B5/12—Measuring arrangements characterised by the use of mechanical techniques for measuring diameters internal diameters
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- General Physics & Mathematics (AREA)
- A Measuring Device Byusing Mechanical Method (AREA)
Abstract
The invention discloses a detection device for a machining assembly of a front rectifier casing of an aircraft engine, and belongs to the technical field of aviation measuring devices. A detection device for an aircraft engine front fairing casing machining assembly comprises: a calibration device and a measurement device; the calibration device comprises a first calibration seat and a second calibration seat which are oppositely arranged, and the distance between the first calibration seat and the second calibration seat is matched with the diameter of the small groove; the measuring device comprises a connecting rod, a measuring component and a positioning component, wherein the measuring component and the positioning component are all telescopic; the measuring assembly and the positioning assembly are respectively arranged at two ends of the connecting rod, and the measuring assembly and the positioning assembly are respectively provided with a first measuring head and a second measuring head which are matched with the inverted cone deep hole large-diameter narrow annular small groove. The invention can conveniently place the measuring device into the machining component of the front fairing casing of the aircraft engine for measurement, and can accurately carry out detection by moving the positioning component to the initial position for positioning.
Description
Technical Field
The invention relates to the technical field of aerial measuring devices, in particular to a detection device for a machining assembly of a front rectifier casing of an aircraft engine.
Background
As shown in FIG. 1, the machining assembly (300) for the nose fairing casing of the aircraft engine is an important part in the aircraft engine, and whether the diameter of a back taper deep hole (with the depth of about 292mm from the outer end face of the part), a large diameter (phi 789.4mm), a narrow annular groove (with the annular width of about 3mm) and a small groove (with the groove width of about 2.5mm and the groove depth of about 4mm) meets the requirement or not relates to whether the engine can work normally or not. Regarding the detection of the diameter of the large-diameter narrow annular small groove (310) of the inverted cone deep hole, the detection is carried out by adopting conventional two-point and outer large end face positioning and lever rotation type measurement, and the problems of insufficient rigidity and large measurement error of a measuring device exist; and the measuring device is a reverse taper and narrow annular part, so that the measuring device is difficult to place and has poor positioning reliability.
Disclosure of Invention
The invention aims to provide a detection device for a machining assembly of a front fairing of an aircraft engine, which aims to solve the problems that the existing device for detecting the diameter of a large-diameter narrow annular small groove of a back taper deep hole of the machining assembly of the front fairing of the aircraft engine is difficult to place and poor in positioning reliability.
The technical scheme for solving the technical problems is as follows:
the utility model provides a detection apparatus of aircraft engine front fairing cartridge receiver processing subassembly for the narrow annular slot of back taper deep hole major diameter of detection processing subassembly, it includes: a calibration device and a measurement device; the calibration device comprises a first calibration seat and a second calibration seat which are arranged at intervals, and the distance between the first calibration seat and the second calibration seat is matched with the diameter of the large-diameter narrow annular small groove of the inverted cone deep hole; the measuring device comprises a connecting rod, a measuring component and a positioning component, wherein the measuring component and the positioning component are all telescopic; the measuring assembly and the positioning assembly are respectively arranged at two ends of the connecting rod, and the measuring assembly and the positioning assembly are respectively provided with a first measuring head and a second measuring head which are matched with the inverted cone deep hole large-diameter narrow annular small groove.
The measuring device is used for detecting the diameter of the large-diameter narrow-ring-shaped small groove of the inverted cone deep hole in the machining assembly of the front fairing of the aircraft engine. Because the locating component can stretch out and draw back, the locating component can get back to the initial position through sliding, when examining, the sliding location subassembly, make the whole length of measuring device reduce, thereby be convenient for put into aircraft engine front fairing casket processing subassembly with detection device, the locating component slides again, first measuring head and second measuring head can be put into back taper deep hole major diameter narrow ring shape slot smoothly, continue the sliding location subassembly, make the locating component get back to the initial position and fix a position, at this moment, measure the diameter of back taper deep hole major diameter narrow ring shape slot by measuring component, because the measuring component can stretch out and draw back, thereby can measure the different diameters of back taper deep hole major diameter narrow ring shape slot.
Before the measurement, the positioning assembly is slid to enable the first measuring head and the second measuring head to be in contact with the first calibrating seat and the second calibrating seat respectively, so that the distance between the first measuring head and the second measuring head is consistent with the standard size of the inverted cone deep hole large-diameter narrow annular small groove, and the measuring device is in an initial state at the moment. Through the checking of the calibration device, the initial position of the measurement device can be accurately positioned, and the measurement error is reduced.
In addition, the invention can detect the diameter of the large-diameter narrow annular small groove of the inverted cone deep hole and the diameter of the large-diameter narrow annular small groove of the forward cone deep hole.
Further, the measuring assembly comprises a first sleeve and a first movable rod; the first sleeve is connected with the connecting rod; the first movable rod penetrates through the first sleeve and is in sliding fit with the side wall of the first sleeve, and a first measuring block far away from the second measuring head and a first measuring instrument close to the second measuring head are respectively arranged at two ends of the first movable rod; the first measuring head is arranged on the first measuring block.
The first movable rod of the measuring assembly of the present invention is retractable in the sleeve to change the position of the first measuring head. After the positioning assembly is used for positioning, a first measuring head on the first measuring block can be in contact with the side wall of the inverted-cone deep-hole large-diameter narrow annular small groove, and the diameter of the inverted-cone deep-hole large-diameter narrow annular small groove is measured through a first measuring instrument connected with the first movable rod. When the measuring device is calibrated on the calibrating device, the reading of the first measuring instrument is an initial value (zero point can be manually adjusted), and when the measuring device is used for measuring, the deviation of the reading on the first measuring instrument is the deviation of the diameter of the reverse taper deep hole large-diameter narrow annular small groove, so that the diameter of the reverse taper deep hole large-diameter narrow annular small groove is detected.
Furthermore, the first movable rod is provided with a first waist-shaped hole; the first sleeve is provided with a first limiting pin penetrating through the first waist-shaped hole.
After the first limiting pin is arranged in the first waist-shaped hole, the first limiting pin has a limiting effect on the first movable rod, so that the first movable rod only can slide but cannot rotate, and the moving distance of the first movable rod can be limited.
Furthermore, a stop block is arranged at one end of the first movable rod close to the first measuring instrument; the end part of the first sleeve, which is close to the first measuring instrument, is provided with a placement cavity, a spring is arranged in the placement cavity, the spring is sleeved on the first movable rod, and the two ends of the spring are respectively contacted with the stop block and the bottom wall of the placement cavity.
The spring can enable the first measuring head to be in close contact with the side wall of the large-diameter narrow annular small groove of the inverted cone deep hole through elastic force, so that the problem of inaccurate measurement caused by incomplete contact is avoided. When the measuring device is used for calibrating on the calibrating device, the spring can be in a stretching state, when the measuring device is used for measuring, the positioning device returns to an initial position, the spring can be changed into the stretching state from a free state, and therefore the first measuring head can be in close contact with the side wall of the inverted-cone deep-hole large-diameter narrow annular small groove under the action of elastic force.
Further, the positioning assembly comprises a second sleeve and a second movable rod; the second sleeve is connected with the connecting rod; the second movable rod passes the second sleeve and with the inside wall sliding fit of second sleeve, and the one end that first measuring head was kept away from to the second movable rod is equipped with the second and measures the piece, and the second measuring head setting is on the second measures the piece.
The second movable rod can slide in the second sleeve, so that the position of the second measuring head can be changed, the integral length of the measuring device can be changed, and the measuring device can be conveniently placed in a machining assembly of a front fairing of an aircraft engine.
Furthermore, the second sleeve is provided with a second waist-shaped hole, and the second movable rod is provided with a deflector rod penetrating through the second waist-shaped hole.
The deflector rod of the invention is used for sliding the second movable rod. The second waist-shaped hole has the effect on the shifting lever fiber, so that the second movable rod can only slide but cannot rotate, and meanwhile, the second waist-shaped hole also limits the moving distance of the shifting lever.
Furthermore, a second measuring instrument is arranged on the outer side of the second sleeve, and a probe of the second measuring instrument is connected with the deflector rod; the outer side of the second sleeve is also provided with a tangential clamping piece matched with the second movable rod.
The second measuring instrument is used for marking the position of the positioning assembly, so that the positioning assembly can accurately return to the initial position. When the measuring device is used for calibrating on the calibrating device, the reading of the second measuring instrument is an initial value (zero point can be manually adjusted), and when the measuring device is used for measuring, the first movable rod can move, so that the reading of the second measuring instrument is deviated from the initial value, when the first movable rod is adjusted to return to the initial position, the first movable rod is indicated to return to the initial position when the reading of the second measuring instrument is the initial value, so that the positioning assembly can be accurately adopted for positioning, and the detection accuracy is improved.
Furthermore, a limiting part is arranged at one end of the second movable rod close to the first measuring head, and the limiting part is in contact with the end face of the second sleeve.
Furthermore, a positioning plate is arranged at one end of the connecting rod connected with the measuring assembly; the locating plate is the V type, and it includes link and two bifurcation ends, and the link is connected with the head rod, and first measuring head lies in between two bifurcation ends on vertical direction.
According to the invention, the two forked ends on the positioning plate and the second measuring block act on the end face of the large-diameter narrow annular small groove of the inverted-cone deep hole together, and the measuring assembly is positioned in a three-point positioning mode, so that the problem of inaccurate measurement caused by warping due to the fact that the measuring device cannot be well contacted with the end face of the large-diameter narrow annular small groove of the inverted-cone deep hole is solved.
Further, the connecting rod comprises a first connecting rod and a second connecting rod; the middle part of the first connecting rod is in an arch shape, one end of the first connecting rod is connected with the positioning plate, and the other end of the first connecting rod is connected with the second connecting rod through a connecting piece; the second connecting rod is also connected with the positioning component.
The middle part of the first connecting rod of the invention is in an arch shape, and is convenient for operating the instrument relative to a common O-shaped structure, thereby facilitating the whole measuring operation.
The invention has the following beneficial effects:
(1) the distance between the measuring assembly and the positioning assembly can be changed, so that the measuring device can be conveniently placed into the machining assembly of the front fairing of the aircraft engine for measurement, and the positioning assembly is moved to the initial position for positioning, so that the diameter of the large-diameter narrow annular small groove of the inverted cone deep hole can be accurately detected.
(2) The invention can calibrate the initial position of the measuring device through the calibrating device, thereby improving the positioning accuracy of the positioning assembly and improving the detection precision.
(3) The invention can detect the diameter of the large-diameter narrow annular small groove of the inverted cone deep hole and the diameter of the large-diameter narrow annular small groove of the forward cone deep hole.
(4) The invention adjusts the positioning assembly to the initial position by adopting the way of zeroing the measuring instrument, so that the positioning assembly is accurately positioned, and the detection precision can be improved.
Drawings
FIG. 1 is a schematic structural view of a forward fairing casing processing assembly of an aircraft engine of the present invention;
FIG. 2 is a schematic structural diagram of the calibration device of the present invention;
FIG. 3 is a schematic structural diagram of a measuring device according to the present invention;
FIG. 4 is a schematic top view of the measuring device of the present invention;
FIG. 5 is a schematic structural view of the connecting rod of the present invention;
FIG. 6 is a schematic view of the connection between the positioning plate and the first connecting rod according to the present invention;
FIG. 7 is a schematic structural view of a second connecting rod of the present invention;
FIG. 8 is a schematic view of the construction of the connector of the present invention;
FIG. 9 is a schematic view of a measuring assembly of the present invention;
FIG. 10 is a schematic view of the positioning assembly of the present invention;
FIG. 11 is a schematic view of a calibration device for calibrating a measuring device according to the present invention;
fig. 12 is a schematic structural view of the measuring apparatus according to the present invention during measurement.
In the figure: 100-a calibration device; 110-a first calibration seat; 120-a second calibration seat; 130-a base; 200-a measuring device; 210-a connecting rod; 211-a positioning plate; 212-first connecting rod; 213-a second connecting rod; 214-a connector; 220-a measurement component; 221-a first measuring head; 222-a first sleeve; 223-a first movable bar; 224-a first measurement block; 225-a first meter; 226-a first kidney-shaped aperture; 227-a first limit pin; 228-a stop; 229-a placement cavity; 230-a spring; 231-watch holder; 232-a watch dog nut; 260-a positioning assembly; 261-a second measuring head; 262-a second sleeve; 263-second movable rod; 264-second measurement block; 265-second kidney shaped aperture; 266-a deflector rod; 267-a second meter; 268-a tangential clamping member; 269-a limiter; 270-a watch frame; 300-machining a front fairing casing of an aircraft engine; 310-inverted cone deep hole large diameter narrow annular small groove.
Detailed Description
The principles and features of this invention are described below in conjunction with the following drawings, which are set forth by way of illustration only and are not intended to limit the scope of the invention.
Examples
The directional terms used in the present embodiment, such as "left" and "right", are based on the drawings, and are only used for describing the structure, but not for limiting the scope of the present invention.
A detection device for an aircraft engine front fairing casing machining assembly comprises: a calibration device 100 and a measurement device 200. The measuring device 200 is used for measuring the diameter of the inverted cone deep hole large-diameter narrow annular small groove 310, and before measurement, the measuring device 200 is calibrated by the calibrating device 100.
Referring to fig. 2, the calibration apparatus 100 includes a base 130, and a first calibration seat 110 and a second calibration seat 120 both disposed on the base 130. The first calibration seat 110 and the second calibration seat 120 are oppositely arranged on the base 130 from left to right, and the left side of the first calibration seat 110 and the right side of the second calibration seat 120 are consistent with the standard size of the inverted-cone deep-hole large-diameter narrow annular small groove 310.
Referring to fig. 3 and 4, the measuring apparatus 200 includes a connecting rod 210, a measuring component 220 and a positioning component 260, wherein the measuring component 220 and the positioning component 260 are respectively disposed at the left and right ends of the connecting rod 210.
Referring to fig. 5 to 8, the connecting rod 210 includes a first connecting rod 212 and a second connecting rod 213 sequentially connected end to end, the left end of the first connecting rod 212 is connected to the measuring assembly 220 and is provided with a positioning plate 211, the right end of the first connecting rod 212 is connected to the left end of the second connecting rod 213 through a connecting member 214, and the right end of the second connecting rod 213 is connected to the positioning assembly 260. In this embodiment, the positioning plate 211 is V-shaped, and includes a connecting end and two diverging ends, wherein the connecting end is connected to the left end of the first connecting rod 212.
The middle part of the first connecting rod 212 is arc-shaped, the left end and the right end of the first connecting rod are respectively provided with a through hole, and the axes of the two through holes are overlapped. The connecting end of the positioning plate 211 is connected to the left end of the first connecting rod 212, and the two bifurcated ends are located away from the first connecting rod 212.
The second connecting rod 213 is formed in a cylindrical shape, and the axis of the inner cavity of the second connecting rod is overlapped with the axis of the through holes at the left and right ends of the first connecting rod 212. The two ends of the connecting element 214 are respectively arranged in the through hole at the right end of the first connecting rod 212 and the inner cavity of the second connecting rod 213, and the two ends of the connecting element 214 are respectively connected with the first connecting rod 212 and the second connecting rod 213 through pins, so that the first connecting rod 212 and the second connecting rod 213 are connected.
The two ends of the first connecting rod 212 are cylindrical, and the second connecting rod 213 is also cylindrical, so that the weight of the whole measuring device is reduced, and the measuring operation is convenient.
Referring to fig. 9, the measuring assembly 220 includes a first sleeve 222 and a first movable rod 223. The first sleeve 222 penetrates through a through hole at the left end of the first connecting rod 212 and is fixedly connected with the first connecting rod 212 through a pin. The left end of the first sleeve 222, that is, the end far away from the positioning component 260, is provided with a first limit pin 227, and two ends of the first limit pin 227 are respectively connected with the side wall of the first sleeve 222, so that the middle part of the first limit pin 227 is located in the inner cavity of the first sleeve 222. A meter jaw 231, a meter jaw nut 232 and a first measuring instrument 225 are sequentially connected to the right end of the first sleeve 222, i.e. the end close to the positioning assembly 260, and the meter jaw 231, the meter jaw nut 232 and the first measuring instrument 225 are located in the arcuate groove of the first connecting rod 212. The inner cavity at the right end of the first sleeve 222 is provided with a placement cavity 229, the probe of the first measuring instrument 225 is placed in the placement cavity 229, and the placement cavity 229 is further provided with a spring 230.
The first movable bar 223 passes through the first sleeve 222 and is in sliding engagement with the inner sidewall of the first sleeve 222. The left end of the first movable rod 223, i.e. the end far away from the positioning assembly 260, is located outside the first sleeve 222, and is connected with a first measuring block 224 through a pin, and the first measuring block 224 is provided with a first measuring head 221 matched with the inverted-cone deep-hole large-diameter narrow annular small groove 310. The first movable rod 223 is provided with a first kidney-shaped hole 226, the extending direction of the first kidney-shaped hole 226 is consistent with the extending direction of the first movable rod 223, and the first limit pin 227 passes through the first kidney-shaped hole 226, so as to limit the first movable rod 223. The right end of the first movable bar 223, i.e., the end near the positioning assembly 260, is disposed in the seating chamber 229 and is connected to the probe of the first meter 225. The right end of the first movable bar 223 is further provided with a stopper 228, the spring 230 is sleeved on the first movable bar 223, and both ends of the spring 230 are respectively in contact with the bottom wall of the seating cavity 229 and the stopper 228.
Referring to fig. 10, the positioning assembly 260 includes a second sleeve 262 and a second movable rod 263. The left end of the second sleeve 262 is arranged in the second connecting rod 213 and is fixedly connected with the second connecting rod 213 through a pin, and the axis of the inner cavity of the second sleeve 262 is coincident with the axis of the inner cavity of the second connecting rod 213. The second sleeve 262 is provided with a second kidney aperture 265. A meter holder 270 is disposed outside the second sleeve 262, and a second measuring instrument 267 is disposed on a side surface of the meter holder 270. The sidewall of the second sleeve 262 is provided with a tangential clamp 268, the tangential clamp 268 extending through the sidewall of the second sleeve 262 and a middle portion of the tangential clamp 268 located within the inner cavity of the second sleeve 262.
The second moving rod 263 penetrates the second sleeve 262 and can slide in the second sleeve 262. The second movable rod 263 is cylindrical, and has a limiting member 269 and a second measuring block 264 at its left and right ends, respectively, and both the limiting member 269 and the second measuring block 264 are T-shaped. The T-shaped tail of the limiting member 269 is disposed in the inner cavity of the second movable rod 263 and connected to the sidewall of the second movable rod 263 via a pin, the T-shaped head of the limiting member 269 is located outside the second movable rod 263, and when the second movable rod 263 slides, the T-shaped head of the limiting member 269 may contact with the second sleeve 262, thereby limiting the over-displacement of the second movable rod 263. The T-shaped tail of the second measuring block 264 is placed in the inner cavity of the second movable rod 263 and connected with the side wall of the second movable rod 263 through a pin, and the T-shaped head of the second measuring block 264 is located outside the second movable rod 263 and provided with a second measuring head 261 matched with the inverted-cone deep-hole large-diameter narrow annular small groove 310.
The middle part of the second movable rod 263 is connected with a shift lever 266 through a pin, the shift lever 266 penetrates through the second waist-shaped hole 265, and a probe of a second measuring instrument 267 is connected with the side surface of the shift lever 266. The middle portion of the second movable rod 263 is also in contact with the middle portion of the tangential clamp 268, and the second movable rod 263 can be fixed by the tangential clamp 268.
Referring to fig. 11 and 12, the steps of detecting by using the detecting device of the machining component of the front fairing casing of the aircraft engine are as follows:
(1) the measuring device 200 is placed on the calibrating device 100, so that the two forked ends of the positioning plate 211 and the second measuring block 264 are respectively contacted with the top surfaces of the first calibrating seat 110 and the second calibrating seat 120, and the positioning accuracy is ensured in a three-point positioning manner;
(2) moving the shift lever 266 to move the second movable rod 263, so that the first measuring head 221 contacts with the left side surface of the first calibration seat 110 and the second measuring head 261 contacts with the right side surface of the second calibration seat 120, and then fixing the second movable rod 263 through the tangential clamping piece 268, wherein the spring 230 is in an extended state, and the distance between the first measuring head 221 and the second measuring head 261 is the standard size of the diameter of the inverted cone deep hole large-diameter narrow annular small groove 310;
(3) zeroing the readings in the first and second gauges 225, 267 and releasing the tangential clamp 268, removing the measuring device 200 from the calibration device 100;
(4) moving the shifter lever 266 to reduce the overall length of the measurement device 200 and placing the measurement device 200 into the aircraft engine forward fairing housing machining assembly 300;
(5) placing the first measuring head 221 into the inverted-cone deep-hole large-diameter narrow annular small groove 310, moving the shift lever 266, increasing the overall length of the measuring device 200, and placing the second measuring head 261 into the inverted-cone deep-hole large-diameter narrow annular small groove 310;
(6) the measuring device 200 is pressed tightly, so that two forked ends of the positioning plate 211 and the second measuring block 264 are respectively contacted with the end face of the inverted-cone deep-hole large-diameter narrow annular small groove 310, and the mounting accuracy of the measuring device 200 is ensured in a three-point positioning mode;
(7) moving the toggle lever 266 to zero the reading of the second meter 267 while simultaneously twisting the tangential clamp 268 to secure the second movable rod 263;
(8) when the reading of the second measuring instrument 267 is reset to zero by moving the shift lever 266, the spring 230 deforms, so that the reading of the first measuring instrument 225 changes, the reading of the first measuring instrument 225 is the deviation of the diameter of the inverted-cone deep-hole large-diameter narrow annular small groove 310, and therefore the measurement of the diameter of the inverted-cone deep-hole large-diameter narrow annular small groove 310 is completed.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents, improvements and the like that fall within the spirit and principle of the present invention are intended to be included therein.
Claims (9)
1. The utility model provides a detection apparatus for aircraft engine front fairing cartridge receiver processing subassembly which characterized in that for the back taper deep hole major diameter narrow annular slot of detection processing subassembly, it includes: a calibration device (100) and a measurement device (200); the calibration device (100) comprises a first calibration seat (110) and a second calibration seat (120) which are arranged at intervals, and the distance between the first calibration seat (110) and the second calibration seat (120) is matched with the diameter of a large-diameter narrow annular small groove of an inverted-cone deep hole; the measuring device (200) comprises a connecting rod (210), a measuring component (220) and a positioning component (260), wherein the measuring component and the positioning component are telescopic; the measuring assembly (220) and the positioning assembly (260) are respectively arranged at two ends of the connecting rod (210), and the measuring assembly (220) and the positioning assembly (260) are respectively provided with a first measuring head (221) and a second measuring head (261) which are matched with the inverted-cone deep-hole large-diameter narrow annular small groove;
the measuring assembly (220) comprises a first sleeve (222) and a first movable rod (223); the first sleeve (222) is connected with the connecting rod (210); the first movable rod (223) penetrates through the first sleeve (222) and is in sliding fit with the side wall of the first sleeve (222), and a first measuring block (224) far away from the second measuring head (261) and a first measuring instrument (225) close to the second measuring head (261) are respectively arranged at two ends of the first movable rod (223); the first measuring head (221) is arranged on the first measuring block (224).
2. The detection device of the aircraft engine forward fairing casing machining assembly as recited in claim 1, characterized in that said first movable rod (223) is provided with a first kidney-shaped hole (226); the first sleeve (222) is provided with a first limit pin (227) penetrating through the first kidney-shaped hole (226).
3. The detecting device for the machining component of the forward fairing casing of the aircraft engine as recited in claim 2, characterized in that a stop block (228) is arranged at one end of the first movable rod (223) close to the first measuring instrument (225); the end part of the first sleeve (222) close to the first measuring instrument (225) is provided with a mounting cavity (229), a spring (230) is arranged in the mounting cavity (229), the spring (230) is sleeved on the first movable rod (223), and two ends of the spring (230) are respectively contacted with the stop block (228) and the bottom wall of the mounting cavity (229).
4. The detecting device of the aircraft engine forward fairing casing machining assembly of claim 1, characterized in that the positioning assembly (260) comprises a second sleeve (262) and a second movable rod (263); the second sleeve (262) is connected with the connecting rod (210); the second movable rod (263) penetrates through the second sleeve (262) and is in sliding fit with the inner side wall of the second sleeve (262), one end, far away from the first measuring head (221), of the second movable rod (263) is provided with a second measuring block (264), and the second measuring head (261) is arranged on the second measuring block (264).
5. The detecting device of the machining assembly of the forward fairing casing of the aircraft engine as recited in claim 4, characterized in that said second sleeve (262) is provided with a second kidney-shaped hole (265), and said second movable rod (263) is provided with a deflector rod (266) passing through said second kidney-shaped hole (265).
6. The detecting device for the machining assembly of the forward rectifying casing of the aircraft engine according to claim 5, characterized in that a second measuring instrument (267) is arranged outside the second sleeve (262), and a probe of the second measuring instrument (267) is connected with the deflector rod (266); the outer side of the second sleeve (262) is also provided with a tangential clamping piece (268) matched with the second movable rod (263).
7. The detecting device of the machining assembly of the nose fairing of the aircraft engine as recited in claim 6, characterized in that an end of said second movable rod (263) close to said first measuring head (221) is provided with a limit stop (269), said limit stop (269) being in contact with an end face of said second sleeve (262).
8. The detecting device for the machining component of the forward fairing casing of the aircraft engine as recited in any one of claims 1 to 7, characterized in that a positioning plate (211) is arranged at one end of the connecting rod (210) connected with the measuring component (220); locating plate (211) is the V type, and it includes link and two bifurcation ends, the link with connecting rod (210) are connected, first measuring head (221) are located in vertical direction between two bifurcation ends.
9. The inspection device of an aircraft engine forward fairing box machining assembly as set forth in claim 8, characterized in that said connecting rod (210) comprises a first connecting rod (212) and a second connecting rod (213); the middle part of the first connecting rod (212) is in an arc shape, one end of the first connecting rod (212) is connected with the positioning plate (211), and the other end of the first connecting rod (212) is connected with the second connecting rod (213) through a connecting piece (214); the second connecting rod (213) is also connected with the positioning component (260).
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| Application Number | Priority Date | Filing Date | Title |
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| CN201910805834.2A CN110440671B (en) | 2019-08-29 | 2019-08-29 | Detection apparatus for aircraft engine front rectifier machine casket processing subassembly |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201910805834.2A CN110440671B (en) | 2019-08-29 | 2019-08-29 | Detection apparatus for aircraft engine front rectifier machine casket processing subassembly |
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| CN110440671A CN110440671A (en) | 2019-11-12 |
| CN110440671B true CN110440671B (en) | 2021-02-26 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN102967226A (en) * | 2012-11-14 | 2013-03-13 | 无锡麦铁精密机械制造有限公司 | Groove diameter checking tool |
| CN203642850U (en) * | 2013-12-30 | 2014-06-11 | 盛地五金制品（深圳）有限公司 | Inside diameter groove detector |
| CN203687834U (en) * | 2014-01-23 | 2014-07-02 | 安徽枞晨回转支承有限公司 | Device for measuring raceway groove diameter of inner steel ring of large bearing |
| CN105690041B (en) * | 2016-04-11 | 2018-02-16 | 贵州遵义驰宇精密机电制造有限公司 | A kind of processing method of aircraft engine front housing |
-
2019
- 2019-08-29 CN CN201910805834.2A patent/CN110440671B/en active Active
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