After-test automatic temperature measuring device for solid rocket engine and use method of after-test automatic temperature measuring device

Abstract

The invention discloses a solid rocket engine after-test automatic temperature measuring device and a using method. The solid rocket engine after-test automatic temperature measuring device comprises a mechanical arm and a temperature measuring device, and the temperature measuring device is connected with the mechanical arm through a flange plate; the temperature measuring device comprises a temperature measuring rod, a temperature measuring rod heat insulating layer and a high-temperature thermocouple, the temperature measuring rod is provided with a wiring groove and a plurality of through holes, the wiring groove is used for arranging a high-temperature thermocouple wiring harness, and the through holes are used for fixing the high-temperature thermocouple; and the temperature measuring rod heat insulating layer is coated on the outer side of the temperature measuring rod. The automatic temperature measuring device provided by the invention is simple in mechanical structure, high in reliability, low in cost and easy to maintain and replace parts, realizes automatic measurement of the temperature of the combustion chamber after a solid rocket engine test, can flexibly adjust the position of a measuring point according to different engines and test requirements, is safe and rapid in measurement, wide in temperature measuring range and high in measuring precision, and is suitable for popularization and application. And the measurement error is small, and rapid and accurate temperature measurement without damaging the inner surface of a measured object is realized.

Description

Technical Field

[0001] The invention relates to the field of mechanical design and measurement technology, and in particular to a solid rocket engine post-test automatic temperature measurement device. Background Art

[0002] Many large solid rocket engines still need to glide with the missile for a long time after they finish working. During this period, the thermal protection performance of the solid rocket engine should meet the requirements. Under the influence of the residual heat inside the engine, many electronic components inside the missile body can still work normally. However, overly conservative thermal protection measures will greatly limit the tactical performance of the missile, such as range and maneuverability. In order to achieve a reasonable design of thermal protection measures, it is necessary to perform flow heat transfer simulation when designing solid rocket engines to predict the temperature change law inside the combustion chamber. This requires obtaining sufficient test data for calibrating the simulation model.

[0003] For a long time, since the only channel between the inside of the combustion chamber and the outside world is the throat, there is still no accurate, safe and effective means to measure the change of residual temperature at different positions inside the combustion chamber after the test over time. Therefore, it is necessary to design a temperature measuring device that can cooperate with the mechanical arm to reach into the engine to measure the temperature of the combustion chamber. Summary of the invention

[0004] In order to solve the above problems, the purpose of the present invention is to provide a solid rocket engine post-test automatic temperature measurement device and a method of use, so as to solve the current problem that the post-test temperature of the solid rocket engine combustion chamber cannot be automatically, quickly and accurately measured.

[0005] The present invention provides a solid rocket engine post-test automatic temperature measurement device, comprising a mechanical arm and a temperature measurement device, wherein the temperature measurement device is connected to the mechanical arm through a flange;

[0006] The temperature measuring device includes a temperature measuring rod, a temperature measuring rod insulation layer, and a high-temperature thermocouple, wherein:

[0007] The temperature measuring rod is provided with a wiring groove and a plurality of through holes, wherein the wiring groove is used for arranging a high-temperature thermocouple harness, and the through holes are used for fixing the high-temperature thermocouple;

[0008] The temperature measuring rod insulation layer is coated on the outside of the temperature measuring rod.

[0009] Preferably, the number and positions of the high-temperature thermocouples are arranged at different through holes according to engine requirements for accurate temperature measurement.

[0010] Preferably, the high temperature thermocouple is a platinum-rhodium high temperature thermocouple.

[0011] Preferably, the temperature measuring rod is made of 30CrMnSiA.

[0012] Preferably, the insulation layer of the temperature measuring rod is made of high temperature resistant material to isolate the residual temperature inside the combustion chamber and protect the temperature measuring rod and the high temperature thermocouple harness.

[0013] Preferably, a threaded hole is provided in the center of the flange, which cooperates with the thread on the temperature measuring rod to fix the temperature measuring rod; a plurality of annularly distributed bolt holes are provided on the flange, which is bolted to another flange on the robotic arm to fix the temperature measuring device on the robotic arm.

[0014] Preferably, the material of the flange is 30CrMnSiA.

[0015] The present invention also provides a method for using the above-mentioned solid rocket engine post-test automatic temperature measurement device, which specifically comprises the following steps:

[0016] S1. Calculate the initialization position of the automatic temperature measuring device of the solid rocket engine after the test on the guide rail, the engine center height, and the fixed throat distance of the front end of the temperature measuring rod along the engine axis; conduct a temperature survey of the combustion chamber after the test;

[0017] S2. Before the engine is put on the stage, the automatic temperature measuring device for the solid rocket engine after the test is hoisted onto the guide rail by a crane and fixed at the calculated initialization position. The axis of the automatic temperature measuring device for the solid rocket engine after the test is parallel to the axis of the engine. The power supply is connected, and the mechanical arm moves to the same height as the center of the engine according to the command, and then initializes and moves to the side of the engine nozzle outlet.

[0018] S3. After the engine is hoisted onto the platform, the movement process of the robot arm is demonstrated on site to solidify the engine application program; the movement process includes:

[0019] In the first stage of rotation action, the robot arm rotates 180°;

[0020] In the second stage, the axis feed action, the robot arm quickly feeds along the engine axis until the front end of the temperature measuring rod is flush with the rear end of the nozzle;

[0021] S4. After calibration, the robot arm returns to the initialization position with one key; check the high-temperature thermocouple circuit to make sure that all high-temperature thermocouples can work normally; cut off the power supply;

[0022] S5. After the engine is finished working, wait for the aftereffect slow combustion in the engine combustion chamber to end; turn on the power remotely, and start the automatic temperature measuring device of the solid rocket engine after the test with one button. After the mechanical arm runs to the same height as the center of the engine, it automatically completes the rotation and axial feeding actions according to the solidified model application program; then the automatic temperature measuring device of the solid rocket engine after the test is slowly fed along the engine axis with the mechanical arm to extend into the engine until the temperature measuring rod reaches the fixed throat distance;

[0023] S6. The high-temperature thermocouple automatically measures the internal temperature of the combustion chamber after the test until the internal temperature of the combustion chamber drops to room temperature, and the temperature measurement process ends;

[0024] S7. The robotic arm, carrying the solid rocket engine post-test automatic temperature measuring device, exits the engine along the straight line at the center of the engine throat. After reaching the designated position, it rotates 180° and returns to the initialization position.

[0025] Compared with the prior art, the present invention has the following beneficial effects:

[0026] (1) The automatic temperature measuring device provided by the present invention can cooperate with the mechanical arm to extend into the engine to measure the temperature of the combustion chamber after the test, and the measuring device has a simple and reliable mechanical structure, low cost, and is easy to maintain and replace parts;

[0027] (2) The automatic temperature measuring device provided by the present invention can flexibly adjust the position of the temperature measuring point according to different engines and test requirements by opening multiple through holes on the temperature measuring rod for fixing high-temperature thermocouples, and accurately measure the residual temperature after the test inside the engine combustion chamber;

[0028] (3) The automatic temperature measurement device provided by the present invention adopts a high-temperature thermocouple made of platinum-rhodium material, which has a wide measurement temperature range, high measurement accuracy, and small measurement error, thereby achieving fast, accurate temperature measurement without causing damage to the inner surface of the measurement object. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] In order to more clearly illustrate the technical solutions disclosed in the present invention, the following briefly introduces the drawings required to be used in some embodiments disclosed in the present invention. Obviously, the drawings described below are only drawings of some embodiments disclosed in the present invention. For ordinary technicians in this field, other drawings can also be obtained based on these drawings. In addition, the drawings described below can be regarded as schematic diagrams, and are not limitations on the actual size of the products involved in the embodiments disclosed in the present invention, the actual process of the method, etc.

[0030] Figure 1 A schematic diagram of a solid rocket engine post-test automatic temperature measurement device provided by the present invention.

[0031] The accompanying drawings are marked as follows: 1. flange; 2. temperature measuring rod; 3. insulation layer of temperature measuring rod; 4. high temperature thermocouple. DETAILED DESCRIPTION

[0032] The technical solutions in the embodiments of the present invention will be described clearly and completely below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention. Therefore, the present invention is not limited to the specific embodiments disclosed below.

[0033] like Figure 1 As shown, the automatic temperature measuring device for a solid rocket engine after a test includes a flange 1, a temperature measuring rod 2, a temperature measuring rod insulation layer 3 and a high-temperature thermocouple 4. The material of the flange is 30CrMnSiA. The temperature measuring rod 2 is fixed by a threaded connection, and is connected to another flange by multiple annular bolts to fix the temperature measuring device on the robotic arm. The length of the temperature measuring rod 2 is 1.2m, and the material is 30CrMnSiA. It has a wiring groove and 29 through holes. The wiring groove is used to arrange the high-temperature thermocouple wiring harness, and the through holes are used to fix the high-temperature thermocouple 4, so that the high-temperature thermocouple 4 can be extended into the solid rocket engine with the temperature measuring rod 2 for precise temperature measurement. Multiple through holes are helpful to arrange the high-temperature thermocouple 4 at different positions of the temperature measuring rod 2 according to different engine models. The insulation layer 3 of the temperature measuring rod is made of EPDM rubber material, which is used to isolate the residual temperature inside the combustion chamber and protect the temperature measuring rod 2 and the high-temperature thermocouple 4 wiring harness from the residual temperature of the combustion chamber after the test. The high-temperature thermocouple 4 is a platinum-rhodium high-temperature thermocouple, and the measured temperature is usually between 0-1800℃, and the error is usually less than 0.5%, which can meet the needs of precision measurement.

[0034] When the automatic temperature measurement device for solid rocket engines is used for the first time, the following steps should be followed:

[0035] S1. Calculate the initialization position of the automatic temperature measuring device of the solid rocket engine after the test on the guide rail, the engine center height, and the fixed throat distance of the front end of the temperature measuring rod 2 along the engine axis; and conduct a temperature survey of the combustion chamber after the test;

[0036] S2. Before the engine is put on the stage, the automatic temperature measuring device for the solid rocket engine after the test is hoisted onto the guide rail by a crane and fixed at the calculated initialization position. The axis of the automatic temperature measuring device for the solid rocket engine after the test is parallel to the axis of the engine. The power supply is connected, and the mechanical arm moves to the same height as the center of the engine according to the command, and then initializes and moves to the side of the engine nozzle outlet.

[0037] S3. After the engine is hoisted onto the platform, the movement process of the robot arm is demonstrated on site to solidify the engine application program; the movement process includes:

[0038] In the first stage of rotation action, the robot arm rotates 180°;

[0039] In the second stage, the axis feed action, the robot arm feeds rapidly along the engine axis until the front end surface of the temperature measuring rod 2 is flush with the rear end surface of the nozzle;

[0040] S4. After calibration, the robot arm returns to the initialization position with one key; check the high-temperature thermocouple circuit to make sure that all high-temperature thermocouples 4 can work normally; cut off the power supply;

[0041] S5. After the engine is finished working, wait for the aftereffect slow combustion in the engine combustion chamber to end; turn on the power remotely, and start the automatic temperature measuring device of the solid rocket engine after the test with one button. After the mechanical arm runs to the same height as the center of the engine, it automatically completes the rotation and axial feeding actions according to the solidified model application program; then the automatic temperature measuring device of the solid rocket engine after the test is slowly fed along the engine axis with the mechanical arm to extend into the engine until the temperature measuring rod 2 reaches the fixed throat distance;

[0042] S6, the high temperature thermocouple 4 automatically measures the internal temperature of the combustion chamber after the test, until the internal temperature of the combustion chamber drops to room temperature, and the temperature measurement process ends;

[0043] S7. The robotic arm, carrying the solid rocket engine post-test automatic temperature measuring device, exits the engine along the straight line at the center of the engine throat. After reaching the designated position, it rotates 180° and returns to the initialization position.

[0044] Although the present invention has been disclosed as above in the form of a preferred embodiment, it is not intended to limit the present invention. Any person skilled in the art may make possible changes and modifications to the technical solution of the present invention using the above disclosed contents without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and modifications made to the above embodiments based on the technical essence of the present invention without departing from the contents of the technical solution of the present invention shall fall within the protection scope of the technical solution of the present invention.

Claims

1. A solid rocket engine post-test automatic temperature measurement device, characterized in that: The automatic temperature measuring device comprises a mechanical arm and a temperature measuring device, wherein the temperature measuring device is connected to the mechanical arm via a flange (1); The temperature measuring device comprises a temperature measuring rod (2), a temperature measuring rod insulation layer (3), and a high-temperature thermocouple (4), wherein: The temperature measuring rod is provided with a wiring groove and a plurality of through holes, the wiring groove is used for arranging a high-temperature thermocouple harness, and the through holes are used for fixing the high-temperature thermocouple (4); The temperature measuring rod insulation layer (3) is coated on the outside of the temperature measuring rod (2).

2. The solid rocket engine post-test automatic temperature measurement device according to claim 1, characterized in that: The number and positions of the high-temperature thermocouples (4) are arranged at different through holes according to the needs of the engine, thereby achieving accurate temperature measurement.

3. The automatic temperature measurement device for a solid rocket engine after a test according to claim 1, characterized in that: The high temperature thermocouple (4) is a platinum-rhodium high temperature thermocouple.

4. The automatic temperature measurement device for a solid rocket engine after a test according to claim 1, characterized in that: The material of the temperature measuring rod (2) is 30CrMnSiA.

5. The automatic temperature measurement device for a solid rocket engine after a test according to claim 1, characterized in that: The temperature measuring rod insulation layer (3) is made of high temperature resistant material and is used to isolate the residual temperature inside the combustion chamber and protect the temperature measuring rod (2) and the high temperature thermocouple wiring harness.

6. The solid rocket engine post-test automatic temperature measurement device according to claim 1, characterized in that: The center of the assembly flange (1) is provided with a threaded hole, which cooperates with the thread on the temperature measuring rod (2) to fix the temperature measuring rod (2); the flange (1) is provided with a plurality of annularly distributed bolt holes, which are bolted to another flange on the mechanical arm to fix the temperature measuring device on the mechanical arm.

7. The automatic temperature measurement device for a solid rocket engine after a test according to claim 1, characterized in that: The material of the flange (1) is 30CrMnSiA.

8. A method for automatically measuring temperature of a solid rocket engine after testing, characterized in that: The automatic temperature measurement device for a solid rocket engine after a test according to any one of claims 1 to 7 is used, and the automatic temperature measurement method comprises the following steps: S1, calculating the initialization position of the automatic temperature measuring device of the solid rocket engine after the test on the guide rail, the engine center height, and the fixed throat distance of the front end surface of the temperature measuring rod (2) along the engine axis; and conducting a temperature survey of the combustion chamber after the test; S2. Before the engine is put on the stage, the automatic temperature measuring device for the solid rocket engine after the test is hoisted onto the guide rail by a crane and fixed at the calculated initialization position. The axis of the automatic temperature measuring device for the solid rocket engine after the test is parallel to the axis of the engine. The power supply is connected, and the mechanical arm moves to the same height as the center of the engine according to the command, and then initializes and moves to the side of the engine nozzle outlet. S3. After the engine is hoisted onto the platform, the movement process of the robot arm is demonstrated on site to solidify the engine application program; the movement process includes: In the first stage of rotation action, the robot arm rotates 180°; In the second stage, the axis feed action is performed, and the mechanical arm is fed rapidly along the axis of the engine until the front end surface of the temperature measuring rod (2) is flush with the rear end surface of the nozzle; S4. After calibration, the robot arm returns to the initialization position with one key; the high-temperature thermocouple circuit is checked to ensure that all high-temperature thermocouples (4) can work normally; and the power supply is cut off; S5. After the engine is finished working, wait for the aftereffect slow combustion in the engine combustion chamber to end; remotely turn on the power, and start the solid rocket engine test automatic temperature measurement device with one button. After the mechanical arm moves to the same height as the center of the engine, it automatically completes the rotation and axial feeding actions according to the solidified model application program; then the solid rocket engine test automatic temperature measurement device is slowly fed along the engine axis with the mechanical arm to extend into the engine until the temperature measuring rod (2) reaches a fixed throat distance; S6, the high temperature thermocouple (4) automatically measures the internal temperature of the combustion chamber after the test, until the internal temperature of the combustion chamber drops to room temperature, and the temperature measurement process ends; S7. The robotic arm, carrying the solid rocket engine post-test automatic temperature measuring device, exits the engine along the straight line at the center of the engine throat. After reaching the designated position, it rotates 180° and returns to the initialization position.

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