A solid rocket engine combustion chamber internal temperature sensor fixing device

Abstract

The present invention proposes a device for fixing a temperature sensor inside a solid rocket engine combustion chamber, comprising an antistatic material and an elastic support component; two pieces of antistatic material are fixedly mounted at the two ends of the elastic support component, and the outer side of the antistatic material is a contact surface with the inner wall surface of the annular grain column in the combustion chamber of the solid rocket engine, and its shape matches the inner wall surface of the annular grain column in the combustion chamber of the solid rocket engine; an inlay groove for fixing the temperature sensor is provided on the outer side of the antistatic material; the elastic support component has a compression preload, and through the compression preload, the antistatic materials at both ends can always fit with the inner wall surface of the annular grain column in the combustion chamber of the solid rocket engine. The present invention realizes the adaptive installation of the grain surface temperature sensor, and can be applied to the installation of sensors when the grain column has a large deformation under different high and low temperature conditions, to avoid the sensor falling off.

Description

Technical Field

[0001] The invention relates to the technical field of solid rocket engine test measurement and control, in particular to a temperature sensor fixing device in a large deformation state. Background Art

[0002] During the temperature environmental test of solid rocket engines, in order to accurately obtain the surface temperature value of the grain inside the engine combustion chamber, a temperature sensor needs to be installed on the surface of the engine grain to obtain the change pattern of the grain temperature value along with the ambient temperature.

[0003] When installing the solid rocket engine combustion chamber propellant, in order to ensure electrostatic safety, antistatic materials are selected when selecting the installation device material, which can ensure electrostatic safety during direct contact with the propellant surface. In the past solid rocket engine temperature environment test process, a soft and cuttable antistatic material was selected. This material can be cut into sensor installation strips of different shapes and sizes according to the engine combustion chamber cavity structure to adapt to the engine combustion chamber cavity structure of different sizes. This antistatic material has been used in the temperature environment test process of some models of engines and has completed multiple engine combustion chamber temperature measurement tasks. However, this method is mainly used in high temperature tests.

[0004] As the application environment of solid rocket engines becomes more and more complex and diverse, it is currently proposed to conduct temperature cycle tests, that is, the surface temperature of the grain inside the combustion chamber needs to be cycled under low temperature conditions (-45°C) and high temperature conditions (50°C). Along with the temperature cycle process, the whole process of grain temperature collection is completed. The applicant installed the temperature sensor using the above method. After the test, the temperature of the grain was calculated. At the same time, the engine top cover was opened to confirm whether the temperature sensor was in the installation position. It was found that the test data did not conform to the temperature change law of the grain itself, and the installed sensor also fell off. The reason for this is that, first, due to the special properties of the surface layer of the grain, it cannot be firmly pasted and there is a possibility of falling off; more importantly, due to the change in the temperature of the grain, the grain has a large deformation, and the expansion and contraction of the antistatic material used to fix the sensor cannot adapt to the expansion and contraction of the grain: under low temperature conditions, the grain and the antistatic material shrink at the same time, resulting in the distance between the grain and the antistatic material being too large, so the sensor falls off. Summary of the invention

[0005] In order to complete the measurement of the surface temperature of the grain during the engine temperature cycle test, adapt to the large deformation state of the engine under different temperature conditions, and realize the temperature measurement of the grain of engines of different models and sizes, the present invention proposes a solid rocket engine combustion chamber internal temperature sensor fixing device, which fixes the temperature sensor on the grain surface through a specific fixing device, and can adapt to the large deformation of the grain under extreme high and low temperature conditions, thereby realizing the adaptive installation of the grain surface temperature sensor and avoiding the sensor falling off phenomenon again.

[0006] The technical solution of the present invention is:

[0007] The solid rocket engine combustion chamber internal temperature sensor fixing device comprises an antistatic material and an elastic support component;

[0008] The two antistatic materials are fixedly mounted at the two ends of the elastic support component, and the outer side surfaces of the two antistatic materials are contact surfaces with the inner wall surface of the annular grain column of the solid rocket engine combustion chamber, and the shape thereof matches the inner wall surface of the annular grain column of the solid rocket engine combustion chamber; an inlay groove for fixing the temperature sensor is opened on the outer side surface of the antistatic material;

[0009] The elastic supporting component has a compressive preload, and through the compressive preload, the antistatic materials at both ends can always fit in contact with the inner wall surface of the annular grain column in the combustion chamber of the solid rocket engine.

[0010] Furthermore, the surface where the antistatic material is connected to the elastic supporting component is a plane, thereby ensuring uniform force between the antistatic material and the inner wall surface of the annular medicine column.

[0011] Furthermore, the elastic support component includes a fixed frame and a spring, one end of the fixed frame is fixedly connected to the first antistatic material, one end of the spring is fixedly connected to the second antistatic material, the fixed frame and the spring are fixedly connected, and the compression preload force is provided by the spring.

[0012] Furthermore, the elastic support component also includes a support rod; there is a cross beam in the middle of the fixed frame, one end of the support rod passes through the cross beam and is threadedly engaged with a fixing nut, and the fixing nut rests on the cross beam; the other end of the support rod passes through the fixed frame and the spring and contacts the second antistatic material; the support rod plays a guiding role for the spring, and is used to adjust the spring preload when the fixing device is installed inside the annular charge column in the combustion chamber of a solid rocket engine.

[0013] Furthermore, gaskets are fixedly installed at both ends of the spring, and the gaskets at both ends are respectively fixedly connected to the fixed frame and the second antistatic material; the elastic support component also includes a fixing bolt, and the fixing bolt can fix the gaskets at both ends of the spring to keep the spring in a compressed pre-tightened state.

[0014] Furthermore, the plane size of the embedding groove matches the installation size of the temperature sensor; the depth of the embedding groove is 0.5 mm to 1 mm smaller than the thickness of the temperature sensor.

[0015] Furthermore, the compression preload force of the spring is determined according to the maximum allowable bearing pressure of the drug column.

[0016] Furthermore, the compression preload of the spring is 0.3 to 0.5 times the maximum allowable pressure of the medicine column, which can ensure that the temperature sensor and the medicine column fit tightly under low-temperature contraction state, and ensure that the medicine surface will not be scratched under high-temperature expansion state.

[0017] Furthermore, a threading hole is opened in the antistatic material, and the temperature sensor signal line is fixed on the fixed frame after being led out from the threading hole, and is bundled into a wire harness on the fixed frame and led out uniformly.

[0018] A method for installing a temperature sensor fixture inside a solid rocket engine combustion chamber comprises the following steps:

[0019] Step 1: According to the size of the annular grain in the combustion chamber of the solid rocket motor, the deformation of the grain and the maximum allowable pressure of the grain, select a fixed frame and spring of corresponding size;

[0020] Step 2: Install the support rod on the fixed frame, and install anti-static materials on the fixed frame and the spring respectively; gradually compress the spring to a compressed pre-tightened state by rotating the fixing nut, and keep the spring in the compressed pre-tightened state by fixing the bolt;

[0021] Step 3: Fix the temperature sensor in the embedding groove of the antistatic material, and the temperature sensor signal line is led out from the threading hole of the antistatic material and fixed on the fixed frame;

[0022] Step 4: After placing the fixture into the annular grain test position of the solid rocket engine combustion chamber, loosen the fixing bolts to allow the antistatic material and the temperature sensor to fit tightly to the grain.

[0023] Beneficial Effects

[0024] The present invention is mainly used for the installation of the grain surface temperature sensor inside the solid rocket engine combustion chamber, realizing the adaptive installation of the grain surface temperature sensor, and can be applied to the installation of the sensor when the grain has a large deformation under different high and low temperature conditions, avoiding the sensor falling off. It has been successfully applied to the engine temperature test process, and the engine surface temperature value has been obtained truly and reliably.

[0025] Additional aspects and advantages of the present invention will be given in part in the following description and in part will be obvious from the following description, or will be learned through practice of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0026] The above and / or additional aspects and advantages of the present invention will become apparent and easily understood from the description of the embodiments in conjunction with the following drawings, in which:

[0027] Figure 1 : A schematic diagram of the structure of the present invention;

[0028] Among them: 1. Anti-static material; 2. Fixing nut; 3. Support rod; 4. Fixed frame; 5. Spring; 6. Gasket. DETAILED DESCRIPTION

[0029] Embodiments of the present invention are described in detail below, examples of which are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are intended to be used to explain the present invention, and should not be construed as limiting the present invention.

[0030] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise" and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the referred device or element must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as limiting the present invention.

[0031] In addition, the terms "first" and "second" are used for descriptive purposes only and should not be understood as indicating or implying relative importance or implicitly indicating the number of the indicated technical features. Therefore, a feature defined as "first" or "second" may explicitly or implicitly include one or more of the features. In the description of the present invention, the meaning of "plurality" is two or more, unless otherwise clearly and specifically defined.

[0032] This embodiment is used for a high and low temperature cycle test of a certain type of solid rocket engine. In order to ensure that the temperature sensor always stays in contact with the grain during the test, this embodiment proposes a temperature sensor fixing device inside the combustion chamber of a solid rocket engine, including antistatic material and elastic support components.

[0033] The two pieces of antistatic material are fixedly mounted at the two ends of the elastic support component respectively, and the outer side surfaces of the two pieces of antistatic material are contact surfaces with the inner wall surface of the annular grain column of the solid rocket engine combustion chamber, and their shapes match the inner wall surface of the annular grain column of the solid rocket engine combustion chamber; an inlay groove for fixing the temperature sensor is opened on the outer side surface of the antistatic material.

[0034] The antistatic material is located at the contact part between the fixing device and the engine medicine surface. The use of the antistatic material ensures electrostatic safety and avoids direct contact between the metal support component and the medicine surface. On the other hand, the antistatic material is soft and can be cut. After cutting according to the size and installation position of the sensor, the sensor can be placed in the inlay groove to fit the sensor tightly to the medicine surface. In case of damage, the antistatic material is also easy to replace. In this embodiment, the antistatic material is made of antistatic rubber material, which can be slightly deformed under pressure to avoid damaging the medicine surface, and is easy to cut and convenient for fixing the temperature sensor.

[0035] In this embodiment, the antistatic material must withstand the compressive preload of the elastic support component and transfer the force to the medicine surface. Therefore, the surface where the antistatic material is connected to the elastic support component is a plane to ensure uniform force between the antistatic material and the inner wall of the annular medicine column.

[0036] The elastic supporting component has a compressive preload, and through the compressive preload, the antistatic materials at both ends can always fit in contact with the inner wall surface of the annular grain column in the combustion chamber of the solid rocket engine.

[0037] In this embodiment, the elastic support component includes a fixed frame and a spring, one end of the fixed frame is fixedly connected to the first antistatic material, one end of the spring is fixedly connected to the second antistatic material, the fixed frame and the spring are fixedly connected, and the compression preload is provided by the spring. The elastic support component also includes a support rod; there is a crossbeam in the middle of the fixed frame, one end of the support rod passes through the crossbeam and is threadedly engaged with a fixing nut, and the fixing nut rests on the crossbeam; the other end of the support rod passes through the fixed frame and the spring and contacts the second antistatic material; the support rod guides the spring to prevent the spring from shifting or deforming, and is used to adjust the spring preload when the fixing device is installed inside the annular charge column of the solid rocket engine combustion chamber.

[0038] Gaskets are fixedly installed at both ends of the spring, and the gaskets at both ends are respectively fixedly connected to the fixed frame and the second antistatic material; the elastic support component also includes a fixing bolt, and the fixing bolt can fix the gaskets at both ends of the spring to keep the spring in a compressed pre-tightened state.

[0039] The compression preload of the spring is determined according to the maximum allowable pressure of the medicine column, which is 0.3 to 0.5 times of the maximum allowable pressure of the medicine column. The test surface shows that the use of this parameter can ensure that under low-temperature contraction state, the spring increases the stroke so that the temperature sensor and the medicine column fit closely, and can also ensure that under high-temperature expansion state, the medicine surface will not be scratched.

[0040] The plane size of the inlay groove matches the installation size of the temperature sensor; the depth of the inlay groove is 0.5mm to 1mm smaller than the thickness of the temperature sensor. The purpose of this parameter setting is to prevent the antistatic material from expanding and deforming at high temperature, causing the temperature sensor to be completely embedded in the inlay groove.

[0041] The antistatic material is provided with a threading hole, which passes through the inlay groove to the bottom plane. After the temperature sensor signal line is led out from the threading hole, it is fixed on the fixed frame and tied into a wire harness on the fixed frame for unified leading out.

[0042] The specific process steps for installing the above-mentioned fixing device inside the combustion chamber of the solid rocket engine are as follows:

[0043] Step 1: According to the size of the annular grain in the combustion chamber of the solid rocket motor, the deformation of the grain and the maximum allowable pressure of the grain, select a fixed frame and spring of corresponding size;

[0044] Step 2: Install the support rod on the fixed frame, and install anti-static materials on the fixed frame and the spring respectively; gradually compress the spring to a compressed pre-tightened state by rotating the fixing nut, and keep the spring in the compressed pre-tightened state by fixing the bolt;

[0045] Step 3: Fix the temperature sensor in the embedding groove of the antistatic material, and in order to avoid the signal line being pulled, the temperature sensor signal line is led out from the threading hole of the antistatic material and fixed on the fixed frame;

[0046] Step 4: After placing the fixture into the annular grain test position of the solid rocket engine combustion chamber, loosen the fixing bolts to allow the antistatic materials at both ends to extend outward under the action of the spring preload, so that the antistatic material and the temperature sensor fit tightly with the grain.

[0047] After placement, the signal line was connected to measure the temperature. After the test, all test data were checked and the data were completely consistent with the test rules. At the same time, the sensor position was checked and no obvious shift occurred, proving that the present invention can meet the high and low temperature test requirements of solid rocket engines.

[0048] Although the embodiments of the present invention have been shown and described above, it is to be understood that the above embodiments are exemplary and are not to be construed as limitations on the present invention. A person skilled in the art may change, modify, replace and modify the above embodiments within the scope of the present invention without departing from the principles and intent of the present invention.

Claims

1. A device for fixing a temperature sensor inside a combustion chamber of a solid rocket engine, characterized in that: including antistatic materials and elastic support components; The two antistatic materials are fixedly mounted at the two ends of the elastic support component, and the outer side surfaces of the two antistatic materials are contact surfaces with the inner wall surface of the annular grain column of the solid rocket engine combustion chamber, and the shape thereof matches the inner wall surface of the annular grain column of the solid rocket engine combustion chamber; an inlay groove for fixing the temperature sensor is opened on the outer side surface of the antistatic material; The elastic supporting component has a compressive preload, and through the compressive preload, the antistatic materials at both ends can always fit in contact with the inner wall surface of the annular grain column in the combustion chamber of the solid rocket engine.

2. A solid rocket engine combustion chamber internal temperature sensor fixing device according to claim 1, characterized in that: The surface where the antistatic material is connected to the elastic supporting component is a plane, thereby ensuring uniform force between the antistatic material and the inner wall surface of the annular medicine column.

3. A solid rocket engine combustion chamber internal temperature sensor fixing device according to claim 1, characterized in that: The elastic support component includes a fixed frame and a spring. One end of the fixed frame is fixedly connected to the first antistatic material, one end of the spring is fixedly connected to the second antistatic material, the fixed frame and the spring are fixedly connected, and the compression preload is provided by the spring.

4. A solid rocket engine combustion chamber internal temperature sensor fixing device according to claim 3, characterized in that: The elastic support component also includes a support rod; a cross beam is provided in the middle of the fixed frame, one end of the support rod passes through the cross beam and is threadedly engaged with a fixing nut, and the fixing nut rests on the cross beam; the other end of the support rod passes through the fixed frame and the spring and contacts the second antistatic material; the support rod guides the spring and is used to adjust the spring preload when the fixing device is installed inside the annular charge column in the combustion chamber of a solid rocket engine.

5. A solid rocket engine combustion chamber internal temperature sensor fixing device according to claim 3 or 4, characterized in that: Gaskets are fixedly installed at both ends of the spring, and the gaskets at both ends are respectively fixedly connected to the fixed frame and the second antistatic material; the elastic support component also includes a fixing bolt, and the fixing bolt can fix the gaskets at both ends of the spring to keep the spring in a compressed pre-tightened state.

6. A solid rocket engine combustion chamber internal temperature sensor fixing device according to claim 1, characterized in that: The plane size of the inlay groove matches the installation size of the temperature sensor; the depth of the inlay groove is 0.5 mm to 1 mm smaller than the thickness of the temperature sensor.

7. A solid rocket engine combustion chamber internal temperature sensor fixing device according to claim 3, characterized in that: The compression preload of the spring is determined according to the maximum allowable pressure of the drug column.

8. A solid rocket engine combustion chamber internal temperature sensor fixing device according to claim 7, characterized in that: The compression preload of the spring is 0.3 to 0.5 times the maximum allowable pressure of the medicine column, which can ensure that the temperature sensor fits tightly to the medicine column under low-temperature contraction state, and can also ensure that the medicine surface will not be scratched under high-temperature expansion state.

9. A solid rocket engine combustion chamber internal temperature sensor fixing device according to claim 1, characterized in that: The antistatic material is provided with a threading hole, and the temperature sensor signal wire is led out from the threading hole, fixed on the fixed frame, and bundled into a wire harness on the fixed frame and led out uniformly.

10. A method for installing a solid rocket engine combustion chamber internal temperature sensor fixing device according to any one of claims 1 to 9, comprising the following steps: Step 1: According to the size of the annular grain in the combustion chamber of the solid rocket motor, the deformation of the grain and the maximum allowable pressure of the grain, select a fixed frame and spring of corresponding size; Step 2: Install the support rod on the fixed frame, and install anti-static materials on the fixed frame and the spring respectively; gradually compress the spring to a compressed pre-tightened state by rotating the fixing nut, and keep the spring in the compressed pre-tightened state by fixing the bolt; Step 3: Fix the temperature sensor in the embedding groove of the antistatic material, and the temperature sensor signal line is led out from the threading hole of the antistatic material and fixed on the fixed frame; Step 4: After placing the fixture into the annular grain test position of the solid rocket engine combustion chamber, loosen the fixing bolts to allow the antistatic material and the temperature sensor to fit tightly to the grain.

Images