CN105003358B - Mounting method of embedded miniature stress sensor for solid rocket engine - Google Patents
Mounting method of embedded miniature stress sensor for solid rocket engine Download PDFInfo
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- CN105003358B CN105003358B CN201510366868.8A CN201510366868A CN105003358B CN 105003358 B CN105003358 B CN 105003358B CN 201510366868 A CN201510366868 A CN 201510366868A CN 105003358 B CN105003358 B CN 105003358B
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Abstract
The invention provides a mounting method of an embedded miniature stress sensor for a solid rocket engine. The mounting method comprises the following steps: mounting the miniature stress sensor on a heat insulating layer at the inner part of the engine, so that the outer casing and a propellant grain of the engine are not damaged, and influence on the structural integrity of the engine is reduced to the lowest level; and besides, segregating the embedded miniature stress sensor from the propellant grain of the engine through spraying a lining layer, and the situation that the electrical property of the sensor is unstable because of the chemical corrosion of a propellant in a long-term storing process is avoided.
Description
Technical field
The present invention relates to the installation method of micro-stress sensor, be specially a kind of solid propellant rocket embedding and decline
The installation method of type strain gauge.
Background technology
Stress is to characterize the important parameter that solid propellant rocket On Damage State develops.Along with solid propellant rocket
Going deep into of research, needs a kind of method to be capable of in real time and monitors the internal change with interfacial stress of motor grain, real
Existing electromotor health forecast/diagnosis, and then estimate a kind of new effective technology means of offer for engine life, improve and send out
Motivation life prediction level and accuracy.
At present, the domestic micro-stress sensor having possessed embedding ability, but there is no sensors with auxiliary electrode and be arranged on solid
Installation method within rocket engine and operating procedure.This is mainly due to the particularity of solid propellant rocket, its
It is internal equipped with high-energy propellant powder column, if sensor Rig up error may produce one to the integrity of engine structure
Fixed impact, even causes dangerous generation.
Summary of the invention
Owing to just completing to develop, at the beginning of being in for the embedded micro strain gauge of solid propellant rocket health monitoring
The step application stage, not yet there is micro-stress sensor the related installation method within solid propellant rocket, inventor
Through theoretical research and technical Analysis, in conjunction with practical structures and the production technology of solid propellant rocket, solid by setting up
The FEM (finite element) model of body rocket motor structure, analyzes powder column median surface STRESS VARIATION situation, and then proposes a kind of solid
The rocket engine installation method of embedded micro strain gauge, safety and precise ground is by embedded micro stress sensing
Device is arranged on inside solid propellant rocket and carries out interfacial stress measurement, it is ensured that the installation of sensor had not both interfered with rocket
The structural intergrity of electromotor, can also normally work simultaneously, it is thus achieved that accurately electromotor interfacial stress data.
The technical scheme is that
The installation method of described a kind of solid propellant rocket embedded micro strain gauge, it is characterised in that: bag
Include following steps:
Step 1: in in-engine installation site, micro-stress sensor is numbered according to micro-stress sensor,
And each micro-stress sensor zero point is detected；
Step 2: before solid propellant rocket propellant is installed, open at solid propellant rocket heat insulation layer inner surface
Micro-stress sensor embedment hole, the perforate degree of depth in micro-stress sensor embedment hole meets micro-stress sensor and loads
Behind micro-stress sensor embedment hole, micro-stress sensor surface flushes with solid propellant rocket heat insulation layer inner surface；
Step 3: micro-stress sensor embedment hole and micro-stress sensor surface are cleaned, then by binding agent
In being coated in micro-stress sensor embedment hole and micro-stress sensor bottom surface and outer surface；Micro-stress sensor is filled
Enter in miniature strain gauge embedment hole, make micro-stress sensor and solid propellant rocket heat insulation layer strong bond；
If micro-stress sensors sides has space with micro-stress sensor embedment hole, the solid-rocket of powder is used to start
Machine heat insulation layer material is filled；
Step 4: opening sensor lead embedment groove at solid propellant rocket heat insulation layer inner surface, sensor lead is imbedded
Micro-stress sensor embedment hole is connected by groove with solid propellant rocket pressure tap, and sensor lead is passed through sensor
Lead-in wire embedment groove causes outside solid propellant rocket pressure tap, and sensor lead is not higher than solid propellant rocket thermal insulation
Layer inner surface, the space between sensor lead and sensor lead embedment groove uses the solid propellant rocket of powder
Heat insulation layer material is filled, and fixes with bonding agent；
Step 5: after bonding agent is completely fixed micro-stress sensor, is carried out the output of each micro-stress sensor
Detection: load direct current intrinsic safety electric source, the active surface of pressing micro-stress sensor, detection on micro-stress sensor
Micro-stress sensor exports, and measuring and exports whether relative micro-stress sensor zero point changes, if changing, entering
Enter step 6, otherwise change corresponding micro-stress sensor；
Step 6: solid propellant rocket heat insulation layer inner surface is installed micro-stress sensor region spraying lining, lining
Layer thickness is 0.8mm-1mm；After lining spraying terminates, then the output of each micro-stress sensor is detected:
Load direct current intrinsic safety electric source, the active surface of pressing micro-stress sensor on micro-stress sensor, detect micro-stress
Sensor exports, and measures and exports whether relative micro-stress sensor zero point changes, if changing, micro-stress passes
Sensor installation, otherwise changes corresponding micro-stress sensor.
Beneficial effect
By time internal for embedded micro strain gauge embedment solid propellant rocket, use this installation method, can have
Effect ground reduces the destruction to engine structural integrity of installing because of sensor, still can be just after ensureing sensor embedment simultaneously
Often work, improves the success rate of sensor embedment, reduces measurement cost.
Accompanying drawing explanation
Fig. 1: micro-stress sensor schematic diagram；
Fig. 2: micro-stress sensor mounting location schematic diagram；
Wherein: 1, solid propellant rocket pressure tap；2, solid propellant rocket shell body；3, solid-rocket starts
Machine heat insulation layer；4, micro-stress sensor embedment hole；5, sensor lead embedment groove.
Detailed description of the invention
Below in conjunction with specific embodiment the present invention described:
As it is shown in figure 1, micro-stress sensor overall dimensions is diameter is less than 8mm, thickness is less than 3mm, this reality
Execute the purpose of example to seek to propose a kind of installation method and start at solid-rocket to be applied to embedded micro strain gauge
Installation process within machine, and reduce the embedment of sensor to engine structure and the impact of performance, it is ensured that sensor exists
Can normally work after embedment engine interior.
Concretely comprise the following steps:
Step 1: owing to needing to imbed multiple sensor in every solid propellant rocket, so passing according to micro-stress
Micro-stress sensor is numbered by sensor in in-engine installation site, and to each micro-stress sensor zero
Point detects.Detection sensor zero point method: by loading 5V direct current intrinsic safety electric source on a sensor, uses intrinsic safety
Output the record of sensor measured by type circuit tester.
Step 2: before solid propellant rocket propellant is installed, open at solid propellant rocket heat insulation layer inner surface
Micro-stress sensor embedment hole, the perforate degree of depth in micro-stress sensor embedment hole meets micro-stress sensor and loads
Behind micro-stress sensor embedment hole, micro-stress sensor surface flushes with solid propellant rocket heat insulation layer inner surface.
Step 3: micro-stress sensor embedment hole and micro-stress sensor surface are cleaned, remove dirt,
In binding agent is coated in micro-stress sensor embedment hole again and micro-stress sensor bottom surface and outer surface；Answer miniature
Force transducer loads in micro-stress sensor embedment hole, makes micro-stress sensor and solid propellant rocket heat insulation layer
Strong bond；If micro-stress sensors sides has space with micro-stress sensor embedment hole, use consolidating of powder
Body rocket engine insulation material is filled.Bonding rear micro-stress sensor surface flushes with heat insulation layer inner surface.
Bonding agent can use 502 adhesives or epoxy resin, at room temperature, used for 502 adhesive hardening times
It is about 10 minutes, uses adhering with epoxy resin to need about 1 hour hardening time
Micro-stress sensor is arranged on heat insulation layer at engine interior, it is ensured that do not destroy the shell body of electromotor
And propellant charge, the impact of engine structural integrity will be minimized, can ensure to pass after spraying lining simultaneously
Sensor and motor grain isolate, it is to avoid the sensor caused because of the chemical attack of propellant in long term storage
Electrical property is unstable.
Step 4: opening sensor lead embedment groove at solid propellant rocket heat insulation layer inner surface, sensor lead is imbedded
Micro-stress sensor embedment hole is connected by groove with solid propellant rocket pressure tap, and sensor lead is passed through sensor
Lead-in wire embedment groove causes outside solid propellant rocket pressure tap, and sensor lead is not higher than solid propellant rocket thermal insulation
Layer inner surface, the space between sensor lead and sensor lead embedment groove uses the solid propellant rocket of powder
Heat insulation layer material is filled, and fixes with bonding agent.
Step 5: be still reliable and stable after being arranged on electromotor in order to ensure sensor, is completely fixed miniature answering at bonding agent
After force transducer, the output of each micro-stress sensor is detected: on micro-stress sensor, load 5V straight
Stream intrinsic safety electric source, the active surface of pressing micro-stress sensor, detection micro-stress sensor output, measure output phase
Whether micro-stress sensor zero point is changed, if changing, entering step 6, otherwise changing corresponding micro-stress
Sensor.
Step 6: solid propellant rocket heat insulation layer inner surface is installed micro-stress sensor region spraying lining, lining
Layer thickness is 0.8mm-1mm.The temperature of motor body spraying lining is 50 DEG C, and lining spraying terminates, recovery room
Wen Hou, then the output of each micro-stress sensor is detected: on micro-stress sensor, load 5V direct current originally
Peace power supply, the active surface of pressing micro-stress sensor, detection micro-stress sensor output, measure output the most micro-
Whether type strain gauge zero point changes, if changing, and micro-stress sensor installation, otherwise change correspondence
Micro-stress sensor.
After micro-stress sensor installation, filling electromotor completes propellant and vulcanizes.
By said method by time internal for embedded micro strain gauge embedment solid propellant rocket, can effectively drop
Low because of the destruction to engine structural integrity of installing of sensor, ensure that sensor still can normally work after imbedding simultaneously,
Improve the success rate of sensor embedment, reduce measurement cost.
Claims (1)
1. the solid propellant rocket installation method of embedded micro strain gauge, it is characterised in that: include with
Lower step:
Step 1: in in-engine installation site, micro-stress sensor is numbered according to micro-stress sensor,
And each micro-stress sensor zero point is detected；
Step 2: before solid propellant rocket propellant is installed, open at solid propellant rocket heat insulation layer inner surface
Micro-stress sensor embedment hole, the perforate degree of depth in micro-stress sensor embedment hole meets micro-stress sensor and loads
Behind micro-stress sensor embedment hole, micro-stress sensor surface flushes with solid propellant rocket heat insulation layer inner surface；
Step 3: micro-stress sensor embedment hole and micro-stress sensor surface are cleaned, then by binding agent
In being coated in micro-stress sensor embedment hole and micro-stress sensor bottom surface and outer surface；Micro-stress sensor is filled
Enter in miniature strain gauge embedment hole, make micro-stress sensor and solid propellant rocket heat insulation layer strong bond；
If micro-stress sensors sides has space with micro-stress sensor embedment hole, the solid-rocket of powder is used to start
Machine heat insulation layer material is filled；
Step 4: opening sensor lead embedment groove at solid propellant rocket heat insulation layer inner surface, sensor lead is imbedded
Micro-stress sensor embedment hole is connected by groove with solid propellant rocket pressure tap, and sensor lead is passed through sensor
Lead-in wire embedment groove causes outside solid propellant rocket pressure tap, and sensor lead is not higher than solid propellant rocket thermal insulation
Layer inner surface, the space between sensor lead and sensor lead embedment groove uses the solid propellant rocket of powder
Heat insulation layer material is filled, and fixes with bonding agent；
Step 5: after bonding agent is completely fixed micro-stress sensor, is carried out the output of each micro-stress sensor
Detection: load direct current intrinsic safety electric source, the active surface of pressing micro-stress sensor, detection on micro-stress sensor
Micro-stress sensor exports, and measuring and exports whether relative micro-stress sensor zero point changes, if changing, entering
Enter step 6, otherwise change corresponding micro-stress sensor；
Step 6: to solid propellant rocket heat insulation layer inner surface, installation micro-stress sensor region spraying lining
Layer, liner layer thickness is 0.8mm-1mm；After lining spraying terminates, then the output of each micro-stress sensor is examined
Survey: on micro-stress sensor, load direct current intrinsic safety electric source, the active surface of pressing micro-stress sensor, detect micro-
Type strain gauge exports, and measures and exports whether relative micro-stress sensor zero point changes, if changing, miniature
Strain gauge installation, otherwise changes corresponding micro-stress sensor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510366868.8A CN105003358B (en) | 2015-06-29 | 2015-06-29 | Mounting method of embedded miniature stress sensor for solid rocket engine |
Applications Claiming Priority (1)
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| CN201510366868.8A CN105003358B (en) | 2015-06-29 | 2015-06-29 | Mounting method of embedded miniature stress sensor for solid rocket engine |
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| CN105003358A CN105003358A (en) | 2015-10-28 |
| CN105003358B true CN105003358B (en) | 2017-01-11 |
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Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106567792B (en) * | 2016-10-27 | 2018-09-07 | 上海新力动力设备研究所 | The device of solid rocket motor grain axial displacement in a kind of measurement ejection process |
| CN107044914A (en) * | 2017-03-16 | 2017-08-15 | 中国人民解放军海军航空工程学院 | Solid engines bonding interface loaded state supervises detection means |
| CN108387330A (en) * | 2018-01-29 | 2018-08-10 | 华南理工大学 | Cable intermediate joint interfacial pressure measurement method based on MEMS pressure sensor |
| CN110207860B (en) * | 2019-06-13 | 2022-05-03 | 内蒙动力机械研究所 | Monitoring device for normal/shear stress of bonding interface of solid rocket engine |
| CN111779593B (en) * | 2020-06-09 | 2021-09-07 | 湖北航天技术研究院总体设计所 | Solid rocket engine shell, solid rocket engine and manufacturing method thereof |
| CN113323772B (en) * | 2021-06-28 | 2022-05-10 | 中国人民解放军国防科技大学 | Mounting structure and mounting method of miniature high-frequency pressure sensor |
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|---|---|---|---|---|
| US7535158B2 (en) * | 2007-02-15 | 2009-05-19 | Epson Toyocom Corporation | Stress sensitive element |
| CN101813537A (en) * | 2010-03-18 | 2010-08-25 | 北京理工大学 | Micro-thruster array testing table |
| CN202216713U (en) * | 2011-09-07 | 2012-05-09 | 齐齐哈尔北方机器有限责任公司 | Sensor support |
| CN103674085A (en) * | 2013-12-16 | 2014-03-26 | 西安电子科技大学 | U-shaped structure sapphire fiber grating temperature and stress sensor and manufacturing method thereof |
-
2015
- 2015-06-29 CN CN201510366868.8A patent/CN105003358B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7535158B2 (en) * | 2007-02-15 | 2009-05-19 | Epson Toyocom Corporation | Stress sensitive element |
| CN101813537A (en) * | 2010-03-18 | 2010-08-25 | 北京理工大学 | Micro-thruster array testing table |
| CN202216713U (en) * | 2011-09-07 | 2012-05-09 | 齐齐哈尔北方机器有限责任公司 | Sensor support |
| CN103674085A (en) * | 2013-12-16 | 2014-03-26 | 西安电子科技大学 | U-shaped structure sapphire fiber grating temperature and stress sensor and manufacturing method thereof |
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| CN105003358A (en) | 2015-10-28 |
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