CN116793685A - Blind cavity dynamic stress test lead wire of aero-engine rotor and fixing method thereof - Google Patents
Blind cavity dynamic stress test lead wire of aero-engine rotor and fixing method thereof Download PDFInfo
- Publication number
- CN116793685A CN116793685A CN202310604698.7A CN202310604698A CN116793685A CN 116793685 A CN116793685 A CN 116793685A CN 202310604698 A CN202310604698 A CN 202310604698A CN 116793685 A CN116793685 A CN 116793685A
- Authority
- CN
- China
- Prior art keywords
- blind cavity
- dynamic stress
- test lead
- transmission line
- stress test
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 238000012360 testing method Methods 0.000 title claims abstract description 58
- 238000000034 method Methods 0.000 title claims abstract description 30
- WABPQHHGFIMREM-UHFFFAOYSA-N lead(0) Chemical compound [Pb] WABPQHHGFIMREM-UHFFFAOYSA-N 0.000 title claims description 14
- 238000003466 welding Methods 0.000 claims description 87
- 230000005540 biological transmission Effects 0.000 claims description 36
- 230000031700 light absorption Effects 0.000 claims description 6
- 230000008054 signal transmission Effects 0.000 claims description 2
- 238000009662 stress testing Methods 0.000 description 9
- 230000000149 penetrating effect Effects 0.000 description 4
- 238000012986 modification Methods 0.000 description 3
- 230000004048 modification Effects 0.000 description 3
- 238000003825 pressing Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 239000003292 glue Substances 0.000 description 2
- 238000005259 measurement Methods 0.000 description 2
- 229910001069 Ti alloy Inorganic materials 0.000 description 1
- 239000002390 adhesive tape Substances 0.000 description 1
- 238000005452 bending Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000001680 brushing effect Effects 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 238000005520 cutting process Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000003822 epoxy resin Substances 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 229910052751 metal Inorganic materials 0.000 description 1
- 239000002184 metal Substances 0.000 description 1
- 239000003973 paint Substances 0.000 description 1
- 229920000647 polyepoxide Polymers 0.000 description 1
- 238000007711 solidification Methods 0.000 description 1
- 230000008023 solidification Effects 0.000 description 1
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/02—Details or accessories of testing apparatus
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Chemical & Material Sciences (AREA)
- Engineering & Computer Science (AREA)
- Combustion & Propulsion (AREA)
- Testing Of Engines (AREA)
- Investigating Strength Of Materials By Application Of Mechanical Stress (AREA)
Abstract
The invention provides a dynamic stress test lead of a blind cavity of an aeroengine rotor and a fixing method thereof, and belongs to the technical field of dynamic stress test of aeroengines. According to the structure, the fixed point positions and the fixed quantity are designed according to the length of the leads, the fixed positions of the leads in the blind cavity are calculated, and the skin is coated on the fixed positions in advance, so that the test leads are fixed more conveniently and rapidly.
Description
Technical Field
The invention belongs to the technical field of aero-engine dynamic stress testing, and particularly relates to a blind cavity dynamic stress testing lead of an aero-engine rotor and a fixing method thereof.
Background
The contact strain gauge is arranged on the surface of the component, a strain gauge signal is transmitted to the data acquisition system through a lead wire, and dynamic stress signal acquisition is realized, so that the contact strain gauge is a key technology for grasping and solving the problem of strength reliability of the engine component in the engine development process. Because aeroengines are complex rotary mechanical structures, they exist as blind cavity structures such as compressor blisk cavities from disk to disk, turbine guide wire shafts, and the like. When the engine is used for testing dynamic stress, the strain gauge lead wire is usually required to be fixed in the blind cavity, so that effective testing of the dynamic stress of certain parts can be realized.
At present, two main methods for fixing a dynamic stress test lead are: one is to brush epoxy resin glue for fixing the dynamic stress test lead wire; and the other is to cover a metal skin on the dynamic stress test lead and then fix the lead by spot welding. Because the mode of glue brushing fixation is limited by the operation space and the pressurization solidification, the method is only suitable for fixing the lead of the test piece without the blind cavity structure, and the dynamic stress test of the blind cavity test piece cannot be completed. The conventional skin spot welding is only used for a visible test piece with a pressing plane because the skin is required to be covered on the lead and the skin is required to be pressed to realize spot welding. The problem that the dynamic stress test of the blind cavity structural member of the aeroengine is blocked because the strain gauge leads are fixed to test pieces with blind cavity structures of a press machine, a turbine and the like is solved.
Therefore, it is desirable to provide a method of fixing a dynamic stress test lead in a blind cavity structure to achieve dynamic stress testing of an aircraft engine blind cavity structure.
Disclosure of Invention
In order to solve the problems, the invention aims to provide the blind cavity dynamic stress testing lead of the aero-engine rotor and the fixing method thereof, so as to solve the problem of fixing the blind cavity dynamic stress testing lead of the aero-engine rotor, realize no fracture and no falling of the testing lead in the blind cavity of the aero-engine rotor, and improve the effective rate of dynamic stress measurement of the blind cavity structure test piece of the aero-engine.
In order to achieve the above purpose, the invention provides a technical scheme that an aeroengine rotor blind cavity dynamic stress testing lead wire comprises a transmission line and a plurality of skins, wherein the transmission line is used for penetrating through a blind cavity, the skins are fixed on the transmission line, the skins are folded in half along the length direction of the transmission line, a threading hole is formed in the center of the folding in a penetrating mode, the transmission line is used for transmitting dynamic stress signals, and the skins are used for fixing the transmission line on the inner cavity of the blind cavity.
The aeroengine rotor blind cavity dynamic stress test lead provided by the invention also has the characteristics that the length L of the transmission line is not smaller than the length of the blind cavity, and the distance h between two adjacent skins is not larger than 5cm.
The aeroengine rotor blind cavity dynamic stress test lead provided by the invention also has the characteristic that the distances among a plurality of skins are the same.
The blind cavity dynamic stress test lead of the aero-engine rotor provided by the invention also has the characteristic that the fixed positions of the adjacent two skins on the inner cavity of the blind cavity are respectively arranged at two sides of the transmission line.
The blind cavity dynamic stress test lead of the aero-engine rotor provided by the invention also has the characteristic that the inner diameter of the threading hole is matched with the outer diameter of the transmission line so that the transmission line is fixed in the threading hole.
Another object of the present invention is to provide a method for fixing a test wire of blind cavity dynamic stress of an aircraft engine rotor, for fixing the test wire of any of the preceding claims, comprising the steps of:
s1: improving a welding head of a spot welder, and setting a welding radian on the welding head to enable the welding head to directly touch a spot welding position in a blind cavity;
s2: fixing a lens of an endoscope on a welding head of a spot welding machine;
s3: and (3) observing the internal environment of the blind cavity through an endoscope, and spot-welding the skin on the test lead on the inner wall of the blind cavity by using a spot welder.
The fixing method of the aeroengine rotor blind cavity dynamic stress test lead wire provided by the invention has the characteristics that the skin is provided with a plurality of spot welding positions, the spot welding positions are uniformly distributed on the skin, and the distance between two adjacent spot welding positions is less than 0.5mm.
The fixing method of the blind cavity dynamic stress test lead of the aero-engine rotor also has the characteristic that a light absorption layer for preventing the reflection of an endoscope lens is arranged on a welding head of the spot welding machine in the S1.
The fixing method of the aeroengine rotor blind cavity dynamic stress test lead wire provided by the invention has the characteristics that the welding gun of the spot welding machine is provided with the light absorption layer for being matched with the endoscope to observe the head part of the welding head, the light absorption layer is arranged between the endoscope lens and the welding head, and the distance between the endoscope lens and the spot welding contact point is 5-20mm.
The fixing method of the aeroengine rotor blind cavity dynamic stress test lead wire provided by the invention also has the characteristics that the S3 further comprises the step of marking spot welding positions on the skin before the test lead wire is placed in the blind cavity.
The beneficial effects are that:
according to the dynamic stress test lead for the blind cavity of the aero-engine rotor, the fixed point positions and the fixed quantity are designed according to the length of the lead, calculation is carried out on the fixed positions of the lead in the blind cavity, and the skin is coated on the fixed positions in advance, so that the test lead is more convenient and faster to fix.
The fixing method of the blind cavity dynamic stress test lead of the aero-engine rotor provided by the invention adopts a method of fixing the blind cavity dynamic stress test lead of the rotor by spot welding, solves the requirement that the traditional spot welding needs to be pressed, and is simple to operate; according to the invention, a spot welder is combined with an endoscope to spot-weld the skin on the test lead, and the dynamic stress test lead is fixed by fixing the skin, so that observability of various conditions such as the position, trend, spot welding skin interval and the like of the lead in the blind cavity is realized; the invention solves the problem of fracture and falling of the dynamic stress testing lead in the blind cavity, greatly improves the effective rate of rotor dynamic stress measurement under the structure of the blind cavity of the engine, and can be applied to the fixation of other leads of the blind cavity of the engine rotor, such as the fixation of temperature testing leads.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present disclosure, the drawings that are needed in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present disclosure, and other drawings may be obtained according to these drawings without inventive effort to a person of ordinary skill in the art.
FIG. 1 is a block diagram of an aero-engine rotor blind cavity dynamic stress test lead provided by an embodiment of the invention;
FIG. 2 is a schematic view of a welding head structure of a spot welder used in an embodiment of the present invention;
FIG. 3 is an enlarged view of a spot welder's welding head used in an embodiment of the present invention;
wherein, 1: a transmission line; 11: a first fixed position; 12: a second fixed position; 13: a third fixed position; 14: a fourth fixed position; 2: a skin; 3: welding head of spot welder; 31: spot welding contacts; 32: a light absorbing layer; 33: a lens; 34: and a welding gun.
Detailed Description
The present invention will be described in further detail with reference to the drawings and examples, but it should be understood that these embodiments are not limiting, and functional, method, or structural equivalents or alternatives according to these embodiments are within the scope of protection of the present invention.
In the description of the embodiments of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. indicate orientations or positional relationships based on the drawings, are merely for convenience in describing the present invention and simplify the description, and do not indicate or imply that the devices or elements referred to must have a specific orientation, be configured and operated in a specific orientation, and thus should not be construed as limiting the invention.
Furthermore, the terms "first," "second," "third," and the like are used for descriptive purposes only and are not to be construed as indicating or implying a relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defining "a first", "a second", etc. may explicitly or implicitly include one or more such feature. In the description of the invention, unless otherwise indicated, the meaning of "a plurality" is two or more.
The terms "mounted," "connected," "coupled," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the above terms in the creation of the present invention can be understood by those of ordinary skill in the art in a specific case.
As shown in fig. 1, an aeroengine rotor blind cavity dynamic stress test lead is provided, the lead comprises a transmission line 1 and a plurality of skins 2, wherein the transmission line 1 is used for penetrating through a blind cavity, the skins 2 are fixed on the transmission line 1, the skins 2 are folded in half along the length direction of the transmission line 1, threading holes for the transmission line to penetrate through are formed in the center of the folding, the transmission line 1 is used for dynamic stress signal transmission, and the skins 2 are used for fixing the transmission line 1 on the inner cavity of the blind cavity.
In some embodiments, the length L of the transmission line 1 is not less than the length of the blind cavity, and the distance h between two adjacent skins 2 is not greater than 5cm.
In some embodiments, the spacing between the multiple skins 2 is the same.
In some embodiments, the fixed positions of two adjacent skins 2 on the inner cavity of the blind cavity are respectively arranged on two sides of the transmission line 1. As shown in fig. 1, the first fixing position 11 is a fixing point of the first skin 2, and is located above the transmission line 1, the second fixing position 12 is a fixing point of the second skin 2, and is located below the transmission line 1, the third fixing position 13 is a fixing point of the third skin 2, and is located above the transmission line 1, and the fourth fixing position 14 is a fixing point of the fourth skin 2, and is located below the transmission line 1.
In some embodiments, the inner diameter of the threading hole is matched with the outer diameter of the transmission line 1 so that the transmission line 1 is fixed in the threading hole.
In some embodiments, a method for fixing a blind cavity dynamic stress test lead of an aero-engine rotor is provided, the method for fixing the test lead according to any one of the preceding claims, the method comprising the steps of:
s1: improving a welding head 3 of a spot welder, wherein a welding radian is set on the welding head and is used for enabling the welding head to directly touch a spot welding position in a blind cavity;
s2: fixing a lens 33 of an endoscope on a welding head 3 of a spot welding machine;
s3: the inner environment of the blind cavity is observed through an endoscope, and the skin 2 on the test lead is spot welded on the inner wall of the blind cavity by a spot welder.
In some embodiments, the skin 2 is provided with a plurality of spot welding positions, the plurality of spot welding positions are uniformly distributed on the skin 2, and the distance between two adjacent spot welding positions is less than 0.5mm.
In some embodiments, the spot welder welding head 3 in the S1 is provided with a light absorbing layer 32 for preventing the endoscope lens 33 from reflecting light. Wherein the light absorbing layer 32 is a layer of black body paint applied.
In some embodiments, a light-absorbing layer 32 for matching with an endoscope to observe the head part of the welding head is arranged on a welding gun of the spot welding machine in the method, the light-absorbing layer 32 is arranged between an endoscope lens 33 and the welding head 3, and the distance between the endoscope lens 33 and a spot welding contact 31 is 5-20mm.
In some embodiments, the step S3 further includes marking spot welds on the skin 2 before the test leads are placed in the blind cavity.
In some embodiments, the technical solution provided in the foregoing embodiments is used to weld 4-7 blades of an engine compressor as a welding assembly, where blind cavities exist between 4-stage and 5-stage discs, between 5-stage and 6-stage discs, and between 6-stage and 7-stage discs, and in order to complete dynamic stress testing of 5-stage, 6-stage and 7-stage blades, dynamic stress testing lead fixing needs to be performed in the blind cavities.
Step one: measuring the lead path lengths of blind cavities of 4-stage and 5-stage discs, 5-stage and 6-stage and 7-stage discs according to a welded assembly size diagram of 4-7-stage discs of a compressor of a certain type of engine, wherein the lead lengths are respectively L1, L2, L3 and L4; the fixed points are designed to be spaced every two by every other, wherein h is equal to 5cm; the fixed point numbers are N1, N2, N3 and N4 respectively, wherein N n ＝L n And (h), n is the number of blind cavities, marking the fixed points on the test lead, and marking the lead with a mark pen with an anti-falling mark by drawing a circle on the lead, wherein the mark is not fallen;
step two: the method comprises the steps of pre-forming a titanium alloy skin, namely firstly cutting the skin 2 into a rectangular skin strip with the length of about 3-4 cm and the width of about 1-1.5 cm, then folding the skin strip in half along the length direction, reserving an aperture capable of allowing a fixed lead to pass through in the center of folding, and pre-pressing the tail part overlapped by the skin 2 by pliers to enable the overlapped part to be basically tightly attached, wherein the thickness of the skin 2 is 0.5-1 mm;
step three: threading the pre-treated spot welding skin 2 on the lead from the lead outlet direction penetrating into the blind cavity;
step four: the gun head of a welding gun 34 of the spot welding machine is modified, a welding head of the spot welding machine is designed to be a welding head with arc bending according to the structure of a blind cavity, and the radian of the welding head and the specific size of the welding head are determined according to the structural size of the blind cavity;
step five: binding and fixing the modified spot welding gun head and a lens 33 of an endoscope together by using an adhesive tape, and fixing the spot welding gun head on the welding gun head, so that the internal condition of a blind cavity can be clearly observed during spot welding;
step six: observing the lead wire and the skin 2 in the blind cavity through an endoscope, and poking the skin 2 by adopting a spot welding gun head to align the edge of the skin 2 close to the lead wire inlet end with the marking line;
step seven: according to the material property of the spot welding skin 2, setting spot welding energy 40J of a spot welder, placing a spot welding head on the skin 2, clamping a grounding clamp of the spot welder on a blind cavity piece, pressing a spot welding switch of the spot welder under the observation of an endoscope, and performing spot welding of the skin 2, wherein the two intervals are smaller than 0.5mm, the intervals of the welding spots are basically consistent, the spot welding is uniformly distributed on the skin 2 as much as possible, and each welding spot is only subjected to spot welding once.
The foregoing description of the preferred embodiments of the invention is not intended to be limiting, but rather is intended to cover all modifications, equivalents, and alternatives falling within the spirit and principles of the invention. The foregoing is merely a preferred embodiment of the present invention, and it should be noted that it will be apparent to those skilled in the art that modifications and variations can be made without departing from the technical principles of the present invention, and these modifications and variations should also be regarded as the scope of the invention.
Claims (10)
1. The utility model provides an aeroengine rotor blind cavity dynamic stress test lead wire, its characterized in that, the lead wire is including being used for the transmission line that passes in blind cavity and fixing a plurality of skins on the transmission line, the skin is for setting up along transmission line length direction fifty percent discount, and the fifty percent discount center is equipped with and is used for the through wire hole that the transmission line passed, the transmission line is used for dynamic stress signal transmission, the skin is used for with the transmission line is fixed on blind cavity inner chamber.
2. The aeroengine rotor blind cavity dynamic stress test lead according to claim 1, wherein the length L of the transmission line is not smaller than the length of the blind cavity, and the distance h between two adjacent skins is not greater than 5cm.
3. The aircraft engine rotor blind cavity dynamic stress test lead of claim 1, wherein the spacing between the plurality of skins is the same.
4. The aeroengine rotor blind cavity dynamic stress test lead according to claim 1, wherein the fixed positions of the adjacent two skins on the blind cavity inner cavity are respectively arranged on two sides of the transmission line.
5. The aircraft engine rotor blind cavity dynamic stress test lead of claim 1, wherein an inner diameter of the threading bore cooperates with an outer diameter of the transmission line such that the transmission line is secured within the threading bore.
6. A method of fixing a blind cavity dynamic stress test lead for an aircraft engine rotor, the method for fixing the test lead of any one of claims 1-5, the method comprising the steps of:
s1: improving a welding head of a spot welder, and setting a welding radian on the welding head to enable the welding head to directly touch a spot welding position in a blind cavity;
s2: fixing a lens of an endoscope on a welding head of a spot welding machine;
s3: and (3) observing the internal environment of the blind cavity through an endoscope, and spot-welding the skin on the test lead on the inner wall of the blind cavity by using a spot welder.
7. The method for fixing the blind cavity dynamic stress test lead of the aero-engine rotor according to claim 6, wherein a plurality of spot welding positions are arranged on the skin, the plurality of spot welding positions are uniformly distributed on the skin, and the distance between two adjacent spot welding positions is smaller than 0.5mm.
8. The method for fixing the blind cavity dynamic stress test lead of the aero-engine rotor according to claim 6, wherein a light absorption layer for preventing the reflection of an endoscope lens is arranged on a welding head of the spot welder in the step S1.
9. The method for fixing the blind cavity dynamic stress test lead of the aeroengine rotor according to claim 6, wherein a light absorption layer for matching with an endoscope to observe the head of the welding head is arranged on a welding gun of the spot welding machine in the method, the light absorption layer is arranged between an endoscope lens and the welding head, and the distance between the endoscope lens and a spot welding contact point is 5-20mm.
10. The method for fixing the blind cavity dynamic stress test lead of the rotor of the aeroengine according to claim 6, wherein the step S3 further comprises marking spot welding positions on the skin before the test lead is placed in the blind cavity.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310604698.7A CN116793685B (en) | 2023-05-26 | 2023-05-26 | Blind cavity dynamic stress test lead wire of aero-engine rotor and fixing method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202310604698.7A CN116793685B (en) | 2023-05-26 | 2023-05-26 | Blind cavity dynamic stress test lead wire of aero-engine rotor and fixing method thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN116793685A true CN116793685A (en) | 2023-09-22 |
| CN116793685B CN116793685B (en) | 2024-02-20 |
Family
ID=88048944
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202310604698.7A Active CN116793685B (en) | 2023-05-26 | 2023-05-26 | Blind cavity dynamic stress test lead wire of aero-engine rotor and fixing method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN116793685B (en) |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3830604A1 (en) * | 1988-09-08 | 1990-03-15 | Kokoku Rubber Tech | Pressure-measuring electrical lead and its production method |
| JPH10299386A (en) * | 1997-04-30 | 1998-11-10 | Aisawa Kogyo Kk | Skin plate jointing structure in open shield machine |
| CN104471808A (en) * | 2012-04-27 | 2015-03-25 | 雷比诺电力系统 | Current return connecting loom and method for mounting on a composite fuselage frame |
| CN107104269A (en) * | 2017-04-12 | 2017-08-29 | 成都国卫通信技术有限公司 | Airborne antenna waveguide cabin penetrating structure |
| CN111545803A (en) * | 2020-05-15 | 2020-08-18 | 沈阳飞机工业（集团）有限公司 | Blind hole positioning and drilling guide hole tool and using method |
| CN216593945U (en) * | 2021-12-31 | 2022-05-24 | 深圳市信为科技发展有限公司 | Pressure measuring probe with fine multiple leads |
| CN115384780A (en) * | 2022-09-02 | 2022-11-25 | 中航通飞华南飞机工业有限公司 | Skin temperature measurement structure and manufacturing method thereof |
| CN115950639A (en) * | 2023-03-09 | 2023-04-11 | 中国航发四川燃气涡轮研究院 | Dynamic stress test line switching method for rotor blade of disk separation fan |
-
2023
- 2023-05-26 CN CN202310604698.7A patent/CN116793685B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3830604A1 (en) * | 1988-09-08 | 1990-03-15 | Kokoku Rubber Tech | Pressure-measuring electrical lead and its production method |
| JPH10299386A (en) * | 1997-04-30 | 1998-11-10 | Aisawa Kogyo Kk | Skin plate jointing structure in open shield machine |
| CN104471808A (en) * | 2012-04-27 | 2015-03-25 | 雷比诺电力系统 | Current return connecting loom and method for mounting on a composite fuselage frame |
| CN107104269A (en) * | 2017-04-12 | 2017-08-29 | 成都国卫通信技术有限公司 | Airborne antenna waveguide cabin penetrating structure |
| CN111545803A (en) * | 2020-05-15 | 2020-08-18 | 沈阳飞机工业（集团）有限公司 | Blind hole positioning and drilling guide hole tool and using method |
| CN216593945U (en) * | 2021-12-31 | 2022-05-24 | 深圳市信为科技发展有限公司 | Pressure measuring probe with fine multiple leads |
| CN115384780A (en) * | 2022-09-02 | 2022-11-25 | 中航通飞华南飞机工业有限公司 | Skin temperature measurement structure and manufacturing method thereof |
| CN115950639A (en) * | 2023-03-09 | 2023-04-11 | 中国航发四川燃气涡轮研究院 | Dynamic stress test line switching method for rotor blade of disk separation fan |
Non-Patent Citations (3)
| Title |
|---|
| 孙久康 等: "基于无线传感网络的平流层飞艇蒙皮应变监测", 计算机仿真, no. 09, pages 82 - 85 * |
| 操卫忠 等: "柔性蒙皮分块金属桁架天线罩力学性能分析及蒙皮效应研究", 工业建筑, no. 02, pages 134 - 140 * |
| 申望 等: "用于飞机蒙皮成形的可重构多点柔性工装设计", 航空制造技术, no. 12, pages 57 - 60 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN116793685B (en) | 2024-02-20 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104359393B (en) | A kind of strain gauge and its manufacture and installation method | |
| EP1908406B1 (en) | Ultrasonic puncture needle | |
| US8511175B2 (en) | Sensor element | |
| CN101243968B (en) | Real-time optoacoustic monitoring with electrophysiologic catheters | |
| EP2305115B1 (en) | Method for simulating bend shape of catheter and magnetic induction catheter | |
| CN116793685B (en) | Blind cavity dynamic stress test lead wire of aero-engine rotor and fixing method thereof | |
| CN103185747B (en) | Ultrasonic detection probe and manufacturing method and tooling mechanical device thereof | |
| AU2004214572A1 (en) | Inserting shape detecting probe | |
| CN106943159A (en) | FPC plates, ultrasonic transducer and its manufacture craft and EUS | |
| CN107255459A (en) | A kind of workpiece calibrator | |
| CN201025458Y (en) | Thermocouple temperature measurement protection device for high-speed aerocraft high-temperature pneumatic thermal simulation test | |
| CN101879656A (en) | Method for preparing aluminum based intelligent composite material by ultrasonic welding | |
| CN106197719A (en) | A kind of film thermocouple lead-in wire clamp system for measuring transient cutting temp of cutting | |
| CN116380295B (en) | Wiring method for high-temperature strain gauge of middle-stage blisk blade of air compressor | |
| CN207356087U (en) | Ultrasonic probe | |
| CN105232141A (en) | Medical catheter head end capable of measuring contact force | |
| CN205041520U (en) | Medical catheter head end of measurable contact force | |
| CN103800072B (en) | Termination electrode and the assembly method with electrophysiologicalcatheter catheter thereof | |
| JP2002199494A (en) | Electron scanning type ultrasonic wave probe | |
| CN110787984A (en) | Fastener with ultrasonic transducer, manufacturing process and application | |
| CN108538408A (en) | The water-proof treatment technology of strain gauge on underwater fuel assembly guide pipe | |
| CN212721472U (en) | Laser sensor with high-temperature protection | |
| CN220933129U (en) | Pcb board card for pressure temperature chip detection | |
| CN106123827B (en) | A kind of engine high pressure turbine rotor blade tip outer diameter aided measurement device | |
| CN209028107U (en) | A kind of resistor testing needle |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |