CN108982038A - A kind of resonance point detecting method of aviation igniter - Google Patents
A kind of resonance point detecting method of aviation igniter Download PDFInfo
- Publication number
- CN108982038A CN108982038A CN201810810302.3A CN201810810302A CN108982038A CN 108982038 A CN108982038 A CN 108982038A CN 201810810302 A CN201810810302 A CN 201810810302A CN 108982038 A CN108982038 A CN 108982038A
- Authority
- CN
- China
- Prior art keywords
- vibration
- tong
- igniter
- vibration tong
- aviation
- 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.)
- Pending
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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
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/02—Vibration-testing by means of a shake table
- G01M7/025—Measuring arrangements
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M7/00—Vibration-testing of structures; Shock-testing of structures
- G01M7/02—Vibration-testing by means of a shake table
- G01M7/027—Specimen mounting arrangements, e.g. table head adapters
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Measurement Of Mechanical Vibrations Or Ultrasonic Waves (AREA)
Abstract
The present invention relates to a kind of aviation igniter resonance point detecting methods, by designing and manufacturing vibration tong, testpieces is mounted on vibration mechine, then four Acceleration Control sensors are separately fixed on vibration tong, an acceleration monitoring sensor is fixed in aviation igniter；Vibration tong is connect by the present invention with shaking table, and sensor is connected on vibration tong, vibration tong is considered as to a part of shaking table, control sensor is accelerated no longer to directly drive vibration mechine, but driving vibration tong, the method can eliminate the resonance point of vibration tong itself and resonance point, to remove interference of the vibration tong to resonance point testing result, realization is accurately positioned aviation igniter resonance point.
Description
Technical field
The present invention relates to a kind of detection method, especially a kind of resonance point detecting method of aviation igniter.
Background technique
Existing aviation igniter resonance point inspection method is fixed on testpieces on electromagnetic vibration test platform, and prison is passed through
Acceleration pick-up sensor oscillating curve produced analyzes the resonance dot frequency of testpieces.But for aviation igniter this
Class can not the direct directly fixed product with vibration mechine, need to be transferred by vibration tong, vibrated clamp material and
Influence vibration tong of structure itself can carry resonance point, then the resonance point detected by the method can be very much, can not differentiate
It is the resonance point of vibration tong or the resonance point of testpieces out.
Summary of the invention
The object of the present invention is to provide a kind of aviation igniter resonance point detecting methods, can effectively exclude vibration tong
Interference to resonance point testing result, realization are accurately positioned aviation igniter resonance point.
The technical scheme is that detection method includes the following steps for aviation igniter resonance point:
(1) vibration tong is designed and manufactured, the material of the vibration tong is cast aluminium, it is fixed on vibration mechine,
The threaded hole of installation aviation igniter is provided on the vibration tong；
(2) vibration tong is fixedly mounted on vibration mechine, by aviation igniter to be measured and is fixed on vibration
Vibration tong on testing stand is fixed；
(3) four Acceleration Control sensors are separately fixed on vibration tong by wiring, and an acceleration monitoring is passed
Sensor is fixed in aviation igniter；
(4) it scans, the vibration acceleration curve of aviation igniter is obtained using the frequency sweep function of vibration mechine；
(5) atlas analysis analyzes the accelerating curve of aviation igniter, determines the resonance of aviation igniter
Point.
The installation site of four sensors for being mounted on vibration tong is close to vibration tong and vibration mechine
Fixed point position.
Effect of the invention:
The material that vibration tong of the invention uses alleviates the weight of fixture, that is, reduces vibration mechine for cast aluminium
Load, but since casting aluminium material itself has certain flexibility, when vibration, is also easy to produce resonance and resonance, to finding out igniter
Resonance point interference it is larger, for exclude fixture itself resonance point, four Acceleration Control sensors are separately fixed at vibration
On fixture, distributing position is the fixed point position of vibration tong and vibration mechine, multiple Acceleration Control sensors and diagonal
Line placement location can efficiently control the acceleration of entire vibration tong.Vibration tong is connect by the present invention with shaking table,
And sensor is connected on vibration tong, and vibration tong is considered as to a part of shaking table, accelerates control sensor no longer
Vibration mechine is directly driven, but drives vibration tong, the method can disappear the resonance point of vibration tong itself and resonance point
It removes, to remove interference of the vibration tong to resonance point testing result, realizes and aviation igniter resonance point is carried out accurately
Positioning.
Detailed description of the invention
Fig. 1 is attachment structure schematic diagram of the invention；
Fig. 2 is the top view of Fig. 1.
Specific embodiment
As shown, detection method includes the following steps for a kind of aviation igniter resonance point:
(1) vibration tong 1 is designed and manufactured, the material of the vibration tong 1 is cast aluminium, is fixed on vibration mechine 2
On, the threaded hole of installation aviation igniter 3 is provided on the vibration tong 1；
(2) vibration tong 1 is fixedly mounted on vibration mechine 2, by aviation igniter 3 to be measured and is fixed on vibration
Vibration tong 1 on dynamic test platform 2 is fixed；
(3) four Acceleration Control sensors 4 are separately fixed on vibration tong 1 by wiring, by an acceleration monitoring
Sensor 5 is fixed in aviation igniter 3；
(4) it scans, the vibration acceleration curve of aviation igniter 3 is obtained using the frequency sweep function of vibration mechine 2；
(5) atlas analysis analyzes the accelerating curve of aviation igniter 3, determines being total to for aviation igniter
Vibration point.
The installation site of four speed control sensors 4 for being mounted on vibration tong 2 is close to vibration tong 1 and vibration
The fixed point position of dynamic test platform 2.
Claims (2)
- The point detecting method 1. a kind of aviation igniter resonates, which is characterized in that the method the following steps are included:1) it designs and manufactures vibration tong (1), the material of the vibration tong (1) is cast aluminium, is fixed on vibration mechine (2) On, the threaded hole of installation aviation igniter (3) is provided on the vibration tong (1)；2) vibration tong (1) is fixedly mounted on vibration mechine (2), by aviation igniter (3) to be measured be fixed on Vibration tong (1) on vibration mechine (2) is fixed；3) four Acceleration Control sensors (4) are separately fixed on vibration tong (1) by wiring, by an acceleration monitoring Sensor (5) is fixed on aviation igniter (3)；4) it scans, the vibration acceleration curve of aviation igniter (3) is obtained using the frequency sweep function of vibration mechine (2)；5) atlas analysis analyzes the accelerating curve of aviation igniter (3), determines the resonance of aviation igniter Point.
- The point detecting method 2. a kind of aviation igniter as described in claim 1 resonates, which is characterized in that described is mounted on The installation site of four speed control sensors (4) of vibration tong (2) is close to vibration tong (1) and vibration mechine (2) Fixed point position.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810810302.3A CN108982038A (en) | 2018-07-20 | 2018-07-20 | A kind of resonance point detecting method of aviation igniter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810810302.3A CN108982038A (en) | 2018-07-20 | 2018-07-20 | A kind of resonance point detecting method of aviation igniter |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108982038A true CN108982038A (en) | 2018-12-11 |
Family
ID=64550629
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810810302.3A Pending CN108982038A (en) | 2018-07-20 | 2018-07-20 | A kind of resonance point detecting method of aviation igniter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108982038A (en) |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN203432803U (en) * | 2013-09-11 | 2014-02-12 | 中国航天科技集团公司第四研究院四〇一所 | Multipurpose testing tool for safety mechanism |
| CN103575493A (en) * | 2013-11-04 | 2014-02-12 | 株洲南车时代电气股份有限公司 | Device and method for appraising vibration test clamp |
| CN104729816A (en) * | 2013-12-23 | 2015-06-24 | 北京有色金属研究总院 | Solid hydrogen storage system vibration test device and method |
| CN108168819A (en) * | 2017-12-21 | 2018-06-15 | 广州广电计量检测股份有限公司 | Vibration test fixture and method, vibration test fixture debugging system and method |
| CN108387355A (en) * | 2018-01-31 | 2018-08-10 | 中国航发动力股份有限公司 | A kind of aero-engine detector probe vibration fatigue test device |
-
2018
- 2018-07-20 CN CN201810810302.3A patent/CN108982038A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN203432803U (en) * | 2013-09-11 | 2014-02-12 | 中国航天科技集团公司第四研究院四〇一所 | Multipurpose testing tool for safety mechanism |
| CN103575493A (en) * | 2013-11-04 | 2014-02-12 | 株洲南车时代电气股份有限公司 | Device and method for appraising vibration test clamp |
| CN104729816A (en) * | 2013-12-23 | 2015-06-24 | 北京有色金属研究总院 | Solid hydrogen storage system vibration test device and method |
| CN108168819A (en) * | 2017-12-21 | 2018-06-15 | 广州广电计量检测股份有限公司 | Vibration test fixture and method, vibration test fixture debugging system and method |
| CN108387355A (en) * | 2018-01-31 | 2018-08-10 | 中国航发动力股份有限公司 | A kind of aero-engine detector probe vibration fatigue test device |
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| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20181211 |