CN105003358A - 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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- CN105003358A CN105003358A CN201510366868.8A CN201510366868A CN105003358A CN 105003358 A CN105003358 A CN 105003358A CN 201510366868 A CN201510366868 A CN 201510366868A CN 105003358 A CN105003358 A CN 105003358A
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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 installation method of solid propellant rocket embedded micro strain gauge.
Background technique
Stress is the important parameter characterizing the evolution of solid propellant rocket On Damage State.Along with going deep into of solid propellant rocket research, need a kind of method can realize the change of Real-Time Monitoring motor grain inside and interfacial stress, realize motor health forecast/diagnosis, and then to estimate for engine life a kind of new effective technology means are provided, improve engine life and estimate level and accuracy.
At present, the domestic existing micro-stress sensor possessing embedding ability, but there is no installation method and the operating procedure that sensors with auxiliary electrode is arranged on solid propellant rocket inside.This is mainly due to the particularity of solid propellant rocket, and high-energy propellant powder column is equipped with in its inside, if sensor Rig up error may produce certain impact to the integrity of engine structure, even causes dangerous generation.
Summary of the invention
Because the embedded micro strain gauge for solid propellant rocket health monitoring just completes development, be in the Preliminary Applications stage, not yet there is micro-stress sensor at the related installation method of solid propellant rocket inside, inventor is through theoretical research and technical Analysis, in conjunction with practical structures and the production technology of solid propellant rocket, by setting up the FEM (finite element) model of solid propellant rocket structure, analyze powder column median surface STRESS VARIATION situation, and then a kind of installation method of solid propellant rocket embedded micro strain gauge is proposed, embedded micro strain gauge is arranged on solid propellant rocket inside carries out interfacial stress measurement safety and precise, guarantee that the installation of sensor both can not affect the structural integrity of rocket motor, can also normally work simultaneously, obtain motor interfacial stress data comparatively accurately.
Technological scheme of the present invention is:
The installation method of described a kind of solid propellant rocket embedded micro strain gauge, is characterized in that: comprise the following steps:
Step 1: in in-engine mounting point, 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 agent is installed, drive micro-stress sensor at solid propellant rocket heat insulation layer internal surface and imbed hole, the perforate degree of depth that hole imbedded by micro-stress sensor meets micro-stress sensor and loads after micro-stress sensor imbeds hole, and micro-stress sensor surface flushes with solid propellant rocket heat insulation layer internal surface;
Step 3: hole is imbedded to micro-stress sensor and micro-stress sensor surface cleans, then Bond is coated in micro-stress sensor and imbeds in hole and micro-stress sensor bottom surface and outer surface; Micro-stress sensor is loaded micro-stress sensor to be imbedded in hole, makes micro-stress sensor and solid propellant rocket heat insulation layer strong bond; If hole imbedded by micro-stress sensors sides and micro-stress sensor space, pulverous solid propellant rocket heat insulation layer material is adopted to fill;
Step 4: open sensor lead at solid propellant rocket heat insulation layer internal surface and imbed groove, sensor lead is imbedded groove and micro-stress sensor is imbedded hole is communicated with solid propellant rocket pressure tap, sensor lead is imbedded groove by sensor lead to be caused outside solid propellant rocket pressure tap, and sensor lead is not higher than solid propellant rocket heat insulation layer internal surface, sensor lead and the sensor lead space imbedded between groove adopts pulverous solid propellant rocket heat insulation layer material to fill, and fixes with binder;
Step 5: after binder is completely fixed micro-stress sensor, each micro-stress sensor is exported and detects: on micro-stress sensor, load direct current intrinsic safety electric source, the active surface of pressing micro-stress sensor, detect micro-stress sensor to export, measure the relative micro-stress sensor zero point of output whether to change, if change, enter step 6, otherwise change corresponding micro-stress sensor;
Step 6: install micro-stress sensor region spraying lining to solid propellant rocket heat insulation layer internal surface, liner layer thickness is 0.8mm-1mm; After lining spraying terminates, again each micro-stress sensor is exported and detect: on micro-stress sensor, load direct current intrinsic safety electric source, the active surface of pressing micro-stress sensor, detect micro-stress sensor to export, measure the relative micro-stress sensor zero point of output whether to change, if change, the installation of micro-stress sensor, otherwise change corresponding micro-stress sensor.
Beneficial effect
When embedded micro strain gauge being imbedded solid propellant rocket and being inner, adopt this installation method, can effectively reduce because the installation of sensor is to the destruction of engine structural integrity, ensure that sensor still can normally work after imbedding simultaneously, improve the success rate that sensor is imbedded, reduce 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 frame; 3, solid propellant rocket heat insulation layer; 4, hole imbedded by micro-stress sensor; 5, sensor lead imbeds groove.
Embodiment
Below in conjunction with specific embodiment, the present invention is described:
As shown in Figure 1, micro-stress sensor boundary dimension is that diameter is less than 8mm, thickness is less than 3mm, the object of the present embodiment is exactly will propose a kind of installation method to be applied to the installation process of embedded micro strain gauge in solid propellant rocket inside, and reduce the impact imbedded engine structure and performance of sensor, guarantee that sensor can normally work after imbedding engine interior.
Concrete steps are:
Step 1: owing to needing to imbed multiple sensor in every platform solid propellant rocket, so be numbered micro-stress sensor in in-engine mounting point according to micro-stress sensor, and each micro-stress sensor zero point is detected.Detecting sensor method at zero point: by loading 5V direct current intrinsic safety electric source on a sensor, adopts the output of intrinsic safety type multimeter measuring transducer and record.
Step 2: before solid propellant rocket propellant agent is installed, drive micro-stress sensor at solid propellant rocket heat insulation layer internal surface and imbed hole, the perforate degree of depth that hole imbedded by micro-stress sensor meets micro-stress sensor and loads after micro-stress sensor imbeds hole, and micro-stress sensor surface flushes with solid propellant rocket heat insulation layer internal surface.
Step 3: imbed hole to micro-stress sensor and micro-stress sensor surface cleans, except crude removal, then is coated in micro-stress sensor and imbeds in hole and micro-stress sensor bottom surface and outer surface by Bond; Micro-stress sensor is loaded micro-stress sensor to be imbedded in hole, makes micro-stress sensor and solid propellant rocket heat insulation layer strong bond; If hole imbedded by micro-stress sensors sides and micro-stress sensor space, pulverous solid propellant rocket heat insulation layer material is adopted to fill.Bonding rear micro-stress sensor surface flushes with heat insulation layer internal surface.
Binder can adopt 502 adhesives or epoxy resin, at room temperature, adopts be about 10 minutes 502 adhesive curing times, adopts adhering with epoxy resin to need 1 hours curing time
Micro-stress sensor is arranged on heat insulation layer at engine interior, the frame and the propellant charge that do not destroy motor can be ensured, to drop to minimum on the impact of engine structural integrity, can ensure that sensor and motor grain are isolated after spraying lining, avoid the sensor electrical performance caused because of the chemical corrosion of propellant agent in long term storage unstable simultaneously.
Step 4: open sensor lead at solid propellant rocket heat insulation layer internal surface and imbed groove, sensor lead is imbedded groove and micro-stress sensor is imbedded hole is communicated with solid propellant rocket pressure tap, sensor lead is imbedded groove by sensor lead to be caused outside solid propellant rocket pressure tap, and sensor lead is not higher than solid propellant rocket heat insulation layer internal surface, sensor lead and the sensor lead space imbedded between groove adopts pulverous solid propellant rocket heat insulation layer material to fill, and fixes with binder.
Step 5: be still reliable and stable after being arranged on motor in order to ensure sensor, after binder is completely fixed micro-stress sensor, each micro-stress sensor is exported and detects: on micro-stress sensor, load 5V direct current intrinsic safety electric source, the active surface of pressing micro-stress sensor, detect micro-stress sensor to export, measure the relative micro-stress sensor zero point of output whether to change, if change, enter step 6, otherwise change corresponding micro-stress sensor.
Step 6: install micro-stress sensor region spraying lining to solid propellant rocket heat insulation layer internal surface, liner layer thickness is 0.8mm-1mm.The temperature of motor body spraying lining is 50 DEG C, lining spraying terminates, after recovering room temperature, again each micro-stress sensor is exported and detect: on micro-stress sensor, load 5V direct current intrinsic safety electric source, whether the active surface of pressing micro-stress sensor, detects micro-stress sensor and exports, measure the relative micro-stress sensor zero point of output and change, if change, the installation of micro-stress sensor, otherwise change corresponding micro-stress sensor.
After the installation of micro-stress sensor, filling motor completes propellant agent and sulfuration.
By said method embedded micro strain gauge imbedded solid propellant rocket inner time, can effectively reduce because the installation of sensor is to the destruction of engine structural integrity, ensure that sensor still can normally work after imbedding simultaneously, improve the success rate that sensor is imbedded, reduce measurement cost.
Claims (1)
1. a solid propellant rocket installation method for embedded micro strain gauge, is characterized in that: comprise the following steps:
Step 1: in in-engine mounting point, 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 agent is installed, drive micro-stress sensor at solid propellant rocket heat insulation layer internal surface and imbed hole, the perforate degree of depth that hole imbedded by micro-stress sensor meets micro-stress sensor and loads after micro-stress sensor imbeds hole, and micro-stress sensor surface flushes with solid propellant rocket heat insulation layer internal surface;
Step 3: hole is imbedded to micro-stress sensor and micro-stress sensor surface cleans, then Bond is coated in micro-stress sensor and imbeds in hole and micro-stress sensor bottom surface and outer surface; Micro-stress sensor is loaded micro-stress sensor to be imbedded in hole, makes micro-stress sensor and solid propellant rocket heat insulation layer strong bond; If hole imbedded by micro-stress sensors sides and micro-stress sensor space, pulverous solid propellant rocket heat insulation layer material is adopted to fill;
Step 4: open sensor lead at solid propellant rocket heat insulation layer internal surface and imbed groove, sensor lead is imbedded groove and micro-stress sensor is imbedded hole is communicated with solid propellant rocket pressure tap, sensor lead is imbedded groove by sensor lead to be caused outside solid propellant rocket pressure tap, and sensor lead is not higher than solid propellant rocket heat insulation layer internal surface, sensor lead and the sensor lead space imbedded between groove adopts pulverous solid propellant rocket heat insulation layer material to fill, and fixes with binder;
Step 5: after binder is completely fixed micro-stress sensor, each micro-stress sensor is exported and detects: on micro-stress sensor, load direct current intrinsic safety electric source, the active surface of pressing micro-stress sensor, detect micro-stress sensor to export, measure the relative micro-stress sensor zero point of output whether to change, if change, enter step 6, otherwise change corresponding micro-stress sensor;
Step 6: install micro-stress sensor region spraying lining to solid propellant rocket heat insulation layer internal surface, liner layer thickness is 0.8mm-1mm; After lining spraying terminates, again each micro-stress sensor is exported and detect: on micro-stress sensor, load direct current intrinsic safety electric source, the active surface of pressing micro-stress sensor, detect micro-stress sensor to export, measure the relative micro-stress sensor zero point of output whether to change, if change, the installation of micro-stress sensor, otherwise change corresponding micro-stress sensor.
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| Application Number | Priority Date | Filing Date | Title |
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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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| 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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| CN105003358B CN105003358B (en) | 2017-01-11 |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106567792A (en) * | 2016-10-27 | 2017-04-19 | 上海新力动力设备研究所 | Device for measuring axial displacement of solid rocket engine grain in launching 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 |
| CN110207860A (en) * | 2019-06-13 | 2019-09-06 | 内蒙动力机械研究所 | A kind of solid propellant rocket bonding interface just/monitoring device of shear stress |
| CN111779593A (en) * | 2020-06-09 | 2020-10-16 | 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 |
| CN113323772A (en) * | 2021-06-28 | 2021-08-31 | 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 |
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| 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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| 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 |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106567792A (en) * | 2016-10-27 | 2017-04-19 | 上海新力动力设备研究所 | Device for measuring axial displacement of solid rocket engine grain in launching process |
| WO2018076958A1 (en) * | 2016-10-27 | 2018-05-03 | 上海新力动力设备研究所 | Apparatus for measuring axial displacement of a solid rocket motor grain in launching process |
| 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 |
| CN110207860A (en) * | 2019-06-13 | 2019-09-06 | 内蒙动力机械研究所 | A kind of solid propellant rocket bonding interface just/monitoring device of shear stress |
| 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 |
| CN111779593A (en) * | 2020-06-09 | 2020-10-16 | 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 |
| 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 |
| CN113323772A (en) * | 2021-06-28 | 2021-08-31 | 中国人民解放军国防科技大学 | Mounting structure and mounting method of miniature high-frequency pressure sensor |
| 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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| CN105003358B (en) | 2017-01-11 |
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