Intelligent solid rocket engine optical fiber sensing monitoring system and monitoring method

Abstract

The application discloses a kind of intelligent solid rocket engine optical fiber sensing monitoring system and monitoring method, optical fiber sensing monitoring system includes multivariable fiber grating sensor, small-scale reinforced fiber grating demodulation host, data recording module, power management module, control line, inert protective material, multivariable fiber grating sensor is laid along the inner wall of engine shell, small-scale reinforced fiber grating demodulation host is used to collect the optical fiber sensing data of engine internal state, data recording module is used to record the optical fiber sensing data collected by small-scale reinforced fiber grating demodulation host, power management module is used to power supply small-scale reinforced fiber grating demodulation host and data recording module, control line is connected with data recording module and power management module, inert protective material is used to provide protection to small-scale reinforced fiber grating demodulation host.The optical fiber sensing monitoring system can master the structural health state of engine in real time, improve the ability of diagnosing and early warning to engine health risk.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of solid rocket engine testing, and in particular to an intelligent solid rocket engine optical fiber sensing monitoring system and a monitoring method. BACKGROUND

[0002] The current state detection means of solid rocket engines have poor timeliness, single detection parameters, complex operation, high cost and other limitations, which hinder the development requirements of high reliability, high safety and high maintenance convenience of solid rocket engines in the long-term storage process. Therefore, it is necessary to study new intelligent solid rocket engine detection means to realize long-term online monitoring, state self-sensing and other functions of solid rocket engines, and to improve the full-life health monitoring capability of solid rocket engines. SUMMARY

[0003] In view of the above technical problems, the present application provides an intelligent solid rocket engine optical fiber sensing monitoring system and a monitoring method, which can realize real-time monitoring of the structural health state of the engine, reduce the safety hazards of the engine, and effectively improve the ability to diagnose and warn the health risks of the engine.

[0004] An intelligent solid rocket engine optical fiber sensing monitoring system, comprising a multi-parameter optical fiber grating sensor, a small-sized reinforced optical fiber grating demodulation host, a data recording module, a power management module, a control line, and an inert protective material, wherein the multi-parameter optical fiber grating sensor is laid along the inner wall of the engine shell, the small-sized reinforced optical fiber grating demodulation host is connected with the multi-parameter optical fiber grating sensor, and is used for collecting optical fiber sensing data of the internal state of the engine, the data recording module and the power management module are installed inside the small-sized reinforced optical fiber grating demodulation host, the data recording module is used for recording the optical fiber sensing data collected by the small-sized reinforced optical fiber grating demodulation host, and the power management module is used for supplying power to the small-sized reinforced optical fiber grating demodulation host and the data recording module, the control line is connected with the data recording module and the power management module, the tail end of the control line is led out from the engine nozzle plug cover, and the inert protective material completely covers the small-sized reinforced optical fiber grating demodulation host, and is used for protecting the small-sized reinforced optical fiber grating demodulation host.

[0005] As the preferred technical scheme, the multi-parameter fiber grating sensor comprises a temperature fiber sensor, a strain fiber sensor and a pressure fiber sensor, the temperature fiber sensor contains a polyimide coating high-temperature resistant fiber grating, adopts a small volume packaging mode, the fiber grating is first sleeved with a capillary steel pipe, and then is packaged with a heat-resistant rubber sleeve, the sensor has a cable shape with a uniform cross section, and the cross section diameter is not greater than 1 mm, and is used for measuring temperature change; the strain fiber sensor contains a polyimide coating high-temperature resistant fiber grating, adopts a small volume packaging mode, the sensing fiber is first packaged with a heat-resistant rubber sleeve, and the fiber grating is disconnected at the position of the fiber grating, the fiber grating is exposed, and then the exposed fiber grating is packaged by glue filling, the sensor has a cable shape with a uniform cross section, and the cross section diameter is not greater than 1 mm, and is used for measuring strain change; the pressure fiber sensor contains a polyimide coating high-temperature resistant fiber grating, the pressure sensor has a diameter not greater than 30 mm and a thickness not greater than 3 mm, the pressure sensor lead is packaged with a heat-resistant rubber sleeve, the cross section diameter is not greater than 1 mm, and is used for measuring pressure change.

[0006] As the preferred technical scheme, the multi-parameter fiber grating sensor is laid in the engine shell lining after completing the spraying of the heat insulation material and before charging, and the laying method is to use a quick-drying adhesive to bond, and the multi-parameter fiber grating sensor is installed to the target measurement point position along the inner wall of the engine.

[0007] As the preferred technical scheme, the small-sized reinforced fiber grating demodulation host is installed on the inner wall of the engine shell and is connected with the multi-parameter fiber grating sensor through a flange joint or fusion.

[0008] As the preferred technical scheme, the inert protective material uses a heat insulation material similar to the mechanical properties of the solid propellant.

[0009] A monitoring method using the above intelligent solid rocket engine fiber sensing monitoring system, the specific monitoring steps are as follows:

[0010] Step one, after the engine is completed, the initial value of the multi-parameter fiber grating sensor is recorded as the reference value of the engine state by starting the data recording module and the power management module through the control line;

[0011] Step two, during the storage of the engine, the fiber sensing monitoring system is started at any time according to the design and detection requirements, the engine state parameter data is obtained, and long-term quality tracking monitoring is performed;

[0012] Step three, when the batch-produced engine needs to be performance sampled or tested, the intelligent engine with the optical fiber sensing monitoring system is selected, the optical fiber sensing monitoring system is started through the control line before ignition, the data is automatically recorded, after the test is completed, the inert protective material is peeled off, the small reinforced optical fiber grating demodulation host is taken out, and the engine test process state data is read;

[0013] Step four, before the engine is formally used, the intelligent engine with the optical fiber sensing monitoring system in the same batch is selected, the optical fiber sensing monitoring system is started through the control line, the state data before emission is acquired, the long-term quality tracking optical fiber monitoring data during storage of the engine is comprehensively acquired, and engine state self-checking evaluation is performed.

[0014] The beneficial effects of the present application are that:

[0015] The device and method provided by the present application solve the problems that the internal state of the engine cannot be detected in real time and online and long-term health intelligent evaluation during the full-life health detection process of the solid rocket engine, have important reference value for mastering the structural health state of the engine and reducing safety hazards, and effectively improve the ability of diagnosing and warning the health risk of the engine. BRIEF DESCRIPTION OF DRAWINGS

[0016] Figure 1 It is a structural schematic diagram of the optical fiber sensing monitoring system.

[0017] Figure 2 It is a structural schematic diagram of the internal structure of the parameter optical fiber grating sensor and the small reinforced optical fiber grating demodulation host.

[0018] Figure 3 It is a working flowchart of the optical fiber sensing monitoring system.

[0019] The reference signs are as follows: 1, multi-parameter optical fiber grating sensor, 11, temperature optical fiber sensor, 12, strain optical fiber sensor, 13, pressure optical fiber sensor, 2, small reinforced optical fiber grating demodulation host, 3, data recording module, 4, power management module, 5, control line, 6, inert protective material. DETAILED DESCRIPTION

[0020] The technical solutions of the present application will be described clearly and completely in combination with the drawings of the present application. Based on the embodiments of the present application, all other embodiments obtained by those skilled in the art without creative labor belong to the protection scope of the present application.

[0021] For example, Figure 1 , Figure 2The illustrated intelligent solid rocket engine optical fiber sensing monitoring system comprises a multi-parameter optical fiber grating sensor 1, a small-sized reinforced optical fiber grating demodulation host 2, a data recording module 3, a power management module 4, a control line 5, and inert protective material 6. The multi-parameter optical fiber grating sensor 1 is laid along the inner wall of the engine shell. The small-sized reinforced optical fiber grating demodulation host 2 is connected with the multi-parameter optical fiber grating sensor 1, used for collecting optical fiber sensing data of the internal state of the engine. The data recording module 3 and the power management module 4 are installed inside the small-sized reinforced optical fiber grating demodulation host 2. The data recording module 3 is used for recording the optical fiber sensing data collected by the small-sized reinforced optical fiber grating demodulation host 2. The power management module 4 is used for supplying power to the small-sized reinforced optical fiber grating demodulation host 2 and the data recording module 3. The control line 5 is connected with the data recording module 3 and the power management module 4. The tail end of the control line 5 is led out from the engine nozzle cover. The inert protective material 6 completely covers the small-sized reinforced optical fiber grating demodulation host 2, used for providing protection for the small-sized reinforced optical fiber grating demodulation host 2.

[0022] In the embodiment, the multi-parameter optical fiber grating sensor 1 comprises a temperature optical fiber sensor 11, a strain optical fiber sensor 12, and a pressure optical fiber sensor 13. The temperature optical fiber sensor 11 contains a polyimide-coated high-temperature-resistant fiber grating, adopts a small-size packaging method, and is first wrapped with a capillary steel tube, then is wrapped with a heat-resistant rubber sleeve for packaging. The sensor has a uniform cross-section cable shape with a cross-section diameter not greater than 1 mm, and is used for measuring temperature changes. The strain optical fiber sensor 12 contains a polyimide-coated high-temperature-resistant fiber grating, adopts a small-size packaging method, and is first wrapped with a heat-resistant rubber sleeve, then is disconnected at the position of the fiber grating, and the fiber grating is exposed, and then the exposed fiber grating is packaged by glue filling. The sensor has a uniform cross-section cable shape with a cross-section diameter not greater than 1 mm, and is used for measuring strain changes. The pressure optical fiber sensor 13 contains a polyimide-coated high-temperature-resistant fiber grating. The pressure sensor has a diameter not greater than 30 mm and a thickness not greater than 3 mm. The pressure sensor lead is wrapped with a heat-resistant rubber sleeve for packaging, and has a cross-section diameter not greater than 1 mm, and is used for measuring pressure changes.

[0023] In the embodiment, the multi-parameter optical fiber grating sensor 1 is laid on the engine shell lining after completing the spraying of the heat-insulating material and before charging. The laying method is to use a quick-drying adhesive to bond the multi-parameter optical fiber grating sensor 1 to the target measuring point position along the inner wall of the engine.

[0024] In the embodiment, the small-sized reinforced optical fiber grating demodulation host 2 is installed on the inner wall of the engine shell and is connected with the multi-parameter optical fiber grating sensor 1 by a flange joint or fusion.

[0025] In the embodiment, the inert protective material 6 adopts a heat insulation material similar to the mechanical properties of the solid propellant.

[0026] The working process of the optical fiber sensing monitoring system is as shown in the figure. Figure 3

[0027] Step 1, install the multi-parameter optical fiber grating sensor 1 to the target measurement point position, and the specific operation method is as follows: after the engine shell lining is completed with the heat insulation material spraying, and before the charge is installed, the multi-parameter optical fiber grating sensor 1 is installed along the inner wall to the target measurement point position by using the quick-drying adhesive, wherein the temperature optical fiber sensor 11, the strain optical fiber sensor 12 and the pressure optical fiber sensor 13 are connected in series into the multi-parameter optical fiber grating sensor 1 for simultaneously detecting the temperature, strain and pressure changes of the engine internal state;

[0028] Step 2, fix the small-sized reinforced optical fiber grating demodulation host 2, connect the multi-parameter optical fiber grating sensor 1, and install the data recording module 3 and the power management module 4, and the specific operation method is as follows: before the engine injects the propellant, the multi-parameter optical fiber grating sensor 1 is connected with the small-sized reinforced optical fiber grating demodulation host 2 through the flange joint or the fusion method, after the connection, the small-sized reinforced optical fiber grating demodulation host 2 is fixed on the inner wall of the engine shell by using the adhesive, according to the structure size of the data recording module 3 and the power management module 4, a corresponding space structure area is reserved, and it is embedded and installed into the small-sized reinforced optical fiber grating demodulation host 2;

[0029] Step 3, the control line 5 connects the data recording module 3 and the power management module 4, and the tail end of the control line 5 is led out from the engine nozzle cover, and the specific operation method is as follows: the control line 5 is connected with the data recording module 3 and the power management module 4 through the serial port protocol, the power is started by using the control line 5 to input the instruction outside the engine, the optical fiber sensing data is automatically recorded after the data recording module 3 is powered on, and the data file stored in the data recording module 3 is read by using the control line 5 outside the engine.

[0030] Step 4, the inert protective material 6 is used to protect the small-sized reinforced optical fiber grating demodulation host 2, and the specific operation method is as follows: after the data recording module 3 and the power management module 4 are embedded in the small-sized reinforced optical fiber grating demodulation host 2, the whole small-sized reinforced optical fiber grating demodulation host is completely wrapped and covered by using the inert protective material 6, and after the inert protective material 6 is solidified, the solid propellant filling operation can be performed to the engine interior;

[0031] Step 5, long-term storage test of the optical fiber sensing intelligent engine.

[0032] A monitoring method using the above-mentioned any one intelligent solid rocket engine optical fiber sensing monitoring system, and the specific monitoring steps are as follows:​

[0033] Step 1: After the engine is manufactured, start the data recording module 3 and power management module 4 through control line 5 to record the initial value of the multi-parameter fiber optic grating sensor 1 as the reference value of the engine status.

[0034] Step 2: During engine storage, the fiber optic sensing monitoring system shall be activated at any time according to design and testing requirements to acquire engine status parameter data and conduct long-term quality tracking and monitoring.

[0035] Step 3: When mass-produced engines need to undergo performance sampling or test runs, select an intelligent engine with a fiber optic sensing and monitoring system. Before ignition, start the fiber optic sensing and monitoring system via control line 5 to automatically record data. After the test is completed, peel off the inert protective material 6, take out the small reinforced fiber optic demodulation host 2, and read the engine test run status data.

[0036] Step 4: Before the engine is put into formal use, select a smart engine from the same batch that is equipped with a fiber optic sensing and monitoring system, start the fiber optic sensing and monitoring system on the control line, obtain the status data before launch, and combine the long-term quality tracking fiber optic monitoring data during engine storage to conduct a self-inspection and evaluation of the engine status.

[0037] The apparatus and method provided by this invention solve the problems of the inability to monitor the internal state of a solid rocket engine in real time and to conduct long-term intelligent health assessment during the whole life health monitoring process. They have important reference value for understanding the structural health status of the engine and reducing safety hazards, and effectively improve the ability to diagnose and warn of engine health risks.

[0038] The above are merely preferred embodiments of the present invention and are not intended to limit the present invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. An intelligent solid rocket motor optical fiber sensing monitoring system, characterized by: The application relates to a multi-parameter optical fiber grating sensor, a small-sized reinforced optical fiber grating demodulation host, a data recording module, a power management module, control lines and inert protective material, wherein the multi-parameter optical fiber grating sensor is laid along the inner wall of an engine shell; the small-sized reinforced optical fiber grating demodulation host is connected with the multi-parameter optical fiber grating sensor and used for collecting optical fiber sensing data of the internal state of the engine; the data recording module and the power management module are installed in the small-sized reinforced optical fiber grating demodulation host; the data recording module is used for recording the optical fiber sensing data collected by the small-sized reinforced optical fiber grating demodulation host; the power management module is used for supplying power for the small-sized reinforced optical fiber grating demodulation host and the data recording module; the control lines are connected with the data recording module and the power management module; the tail end of the control lines is led out from the engine nozzle cover; the inert protective material completely covers the small-sized reinforced optical fiber grating demodulation host and is used for protecting the small-sized reinforced optical fiber grating demodulation host; the multi-parameter optical fiber grating sensor comprises a temperature optical fiber sensor, a strain optical fiber sensor and a pressure optical fiber sensor; the temperature optical fiber sensor contains a polyimide coating high-temperature-resistant fiber grating and adopts a small-size packaging mode; the fiber grating is first sleeved with a capillary steel pipe and then is packaged with a heat-resistant rubber sleeve; the sensor is in the form of a cable with a uniform cross section, and the cross section diameter is not greater than 1mm; and the sensor is used for measuring temperature change; the strain optical fiber sensor contains a polyimide coating high-temperature-resistant fiber grating and adopts a small-size packaging mode; a sensing fiber is first packaged with a heat-resistant rubber sleeve, the fiber grating is disconnected at the position of the fiber grating, the fiber grating is exposed, the exposed fiber grating is packaged by glue filling, the sensor is in the form of a cable with a uniform cross section, and the cross section diameter is not greater than 1mm; and the sensor is used for measuring strain change; and the pressure optical fiber sensor contains a polyimide coating high-temperature-resistant fiber grating, the pressure sensor has a diameter not greater than 30mm and a thickness not greater than 3mm, the pressure sensor lead is packaged with a heat-resistant rubber sleeve, the cross section diameter is not greater than 1mm, and the sensor is used for measuring pressure change.

2. The intelligent solid rocket engine optical fiber sensing monitoring system of claim 1, wherein: The multi-parameter optical fiber grating sensor is laid on the inner lining of the engine shell after the heat insulation material spraying is completed and before the charging.

3. The intelligent solid rocket engine optical fiber sensing monitoring system of claim 1, wherein: The small-sized reinforced optical fiber grating demodulation host is installed on the inner wall of the engine shell and is connected with the multi-parameter optical fiber grating sensor through flange joints or fusion.

4. The intelligent solid rocket engine optical fiber sensing monitoring system of claim 1, wherein: The inert protective material adopts a heat insulation material similar to the mechanical property of the solid propellant.

5. A monitoring method of the optical fiber sensing monitoring system for the intelligent solid rocket engine according to any one of claims 1-4, characterized in that: The specific monitoring steps are as follows: Step one: after the engine is completed, the data recording module and the power management module are started through the control lines, the initial value of the multi-parameter optical fiber grating sensor is recorded, and the initial value is used as the reference value of the engine state; Step two: during the storage of the engine, the optical fiber sensing monitoring system is started at any time according to the design and detection requirements, the engine state parameter data are acquired, and long-term quality tracking monitoring is conducted. Step three, when the mass-produced engine needs to be performance sampling or test run, the intelligent engine with fiber-optic sensing monitoring system is selected, the fiber-optic sensing monitoring system is started through the control line before ignition, the data is automatically recorded, after the test is completed, the inert protective material is stripped, the small reinforced fiber-optic grating demodulation host is taken out, and the engine test process state data is read; Step four, before the engine is formally used, the intelligent engine with fiber-optic sensing monitoring system in the same batch is selected, the fiber-optic sensing monitoring system is started through the control line, the state data before emission is obtained, the long-term quality tracking fiber-optic monitoring data during the storage of the engine is comprehensively considered, and the engine state self-checking evaluation is performed.

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