A solid rocket engine rapid cooking test device

Abstract

A solid engine rapid bake-off test device, wherein the solid engine under test is placed above an oil tank via a fixing device, and the fuel in the oil tank is ignited by an ignition system to generate a flame so that the flame directly heats the outer surface of the solid engine; an ambient temperature monitoring system is used to monitor the ambient temperature around the solid engine during the test; a solid engine temperature monitoring system is used to monitor the temperature at the surface and internal measuring points of the solid engine; a video monitoring system is used to record the flame combustion conditions, solid engine reaction conditions, working conditions of each monitoring system measuring point, and working conditions of a verification plate during the rapid bake-off test; an infrared thermal imager is used to record the radiant heat during the rapid bake-off test; a ground and air shock wave overpressure monitoring system is used to monitor the shock wave overpressure generated when the solid engine reacts, and the verification plate is used to receive the impact of solid matter flying out when the solid engine reacts.

Description

Technical Field

[0001] The present invention relates to a solid motor rapid cook-off test device, which is used to test the maximum heat flux, response time and results that a solid motor can safely withstand when directly exposed to a flame environment, and ultimately evaluate the safety performance of the solid motor in a rapid cook-off environment. Background Art

[0002] A solid engine is a power device that generates high-temperature, high-pressure combustion gas through the normal combustion of solid propellant. This gas is then expanded and accelerated through a nozzle to generate thrust. It is easy to use, simple to maintain, and capable of long-term storage, making it widely used in missile weapons and space launches. The solid propellant is an energetic substance that undergoes a stable and orderly combustion reaction under normal ignition. The temperature and gas generated by the combustion meet the requirements for solid engine use. However, when a solid engine is exposed to an accident such as a fire, thermal stimulation such as flame combustion destroying the shell structure and continuous heat accumulation from the fire may cause the solid propellant to react rapidly, leading to safety accidents such as combustion and explosion in the solid engine.

[0003] The rapid bake-off test is one of the important test projects in the field of solid engine safety research. During the test, the solid engine is placed at a certain height above the ground, and the surface of the solid engine is continuously heated with fuel. Thermocouples, verification plates, overpressure sensors and video monitors are arranged around the solid engine to monitor the temperature, pressure, shell crushing and other conditions around the solid engine during the rapid bake-off test, and observe the response results of the solid engine under thermal stimulation.

[0004] The existing standard QJ20153-2012 "Solid Propellant Rapid Cook-off Test Method" provides the rapid cook-off test principle and test method for solid propellants, such as Figure 1 As shown, it can be used to determine the response of the propellant under standard rapid burn test conditions.

[0005] However, this method is only applicable to rapid propellant cook-off tests. The solid motor used for charge in the standard has a diameter of only 100 mm, with a sealed barrel and end cap made of carbon stainless steel. This method is also not applicable to current practical solid motor rapid cook-off tests due to its structural dimensions. For example, the solid motor in the standard is a cylindrical sealed structure, while actual solid motors can be spherical, ellipsoidal, cylindrical, conical, and have some protruding structures, making them non-sealed. The solid motor diameter in the standard is 100 mm, while actual solid motors developed for application have a wide range of diameters, ranging from 1000 mm to 2000 mm and above. The solid motor in the standard has a simple structure, consisting solely of carbon stainless steel and propellant, while actual solid motors have complex structures such as composite shells, metal parts, rubber layers, liners, and propellant. The propellant in the standard is a solid structure, which is significantly different from the complex propellant structure of actual solid motor propellants. Furthermore, the method in this standard lacks applicability, accuracy, and reliability.

[0006] Therefore, based on the actual development needs, a new solid engine rapid burnout test device was proposed for the rapid burnout test of solid engines. Summary of the Invention

[0007] The technical problem to be solved by the present invention is: QJ20153-2012 "Solid Propellant Rapid Cook-off Test Method" only provides a rapid cook-off test method for solid propellants. The sample made of solid propellant is significantly different from the size, structure, material, composition, etc. of the solid engine developed for actual application. The present invention solves the problem that it cannot directly reflect the rapid cook-off safety of the actual solid engine.

[0008] The purpose of the present invention is achieved through the following technical solutions:

[0009] A solid motor rapid cook-off test device includes a fixing device, a fire-cooking device, an ambient temperature monitoring system, a solid motor temperature monitoring system, a video monitoring system, an infrared thermal imager, a ground shock wave overpressure monitoring system, an air shock wave overpressure monitoring system, and a verification board; the fire-cooking device includes an oil tank, fuel, and an ignition system;

[0010] The solid motor under test is placed above the oil tank using a fixture, and the ignition system is used to ignite the fuel in the oil tank to generate a flame, so that the flame directly heats the outer surface of the solid motor;

[0011] The ambient temperature monitoring system is used to monitor the ambient temperature around the solid motor during the test. If the solid motor reacts, the impact of the solid motor on the ambient temperature can be monitored.

[0012] The solid motor temperature monitoring system is used to monitor the temperature of the solid motor surface and internal measuring points. It can reflect the changes in the solid motor surface and internal temperature during the solid motor rapid burn test. If the solid motor reacts, the changes in the solid motor surface and internal temperature can be recorded.

[0013] The video monitoring system is used to record the flame combustion conditions, solid engine reaction conditions, working conditions of each monitoring system measurement point, and working conditions of the verification board during the rapid burn-off test;

[0014] The infrared thermal imager is used to record the radiant heat during the rapid cooking test and to analyze the heating conditions of the solid rocket motor;

[0015] The ground shock wave overpressure monitoring system is used to monitor the shock wave overpressure generated in the ground direction when the solid engine reacts. The air shock wave overpressure monitoring system is used to monitor the shock wave overpressure generated in the air direction when the solid engine reacts. The verification plate is used to receive the impact of solid matter flying out when the solid engine reacts.

[0016] A test method based on the solid rocket motor rapid cook-off test device includes:

[0017] Surface temperature measuring points and internal temperature measuring points are arranged on the surface and inside of the solid motor; the surface temperature measuring points are evenly distributed in the vertical and horizontal directions along the solid motor equator, and the internal temperature measuring points are arranged on the inner surface of the combustion chamber grain at the front, middle and rear of the inner hole, the bottom of the wing slot, the front opening and the rear opening;

[0018] Place the fixture in the center of the oil tank and secure it, then slowly lift the solid engine onto the fixture and secure it;

[0019] Arrange temperature measuring points of the ambient temperature monitoring system in the horizontal direction and above the outside of the solid rocket;

[0020] 1. Validation panels shall be arranged on the sides and front of the solid rocket in the horizontal direction. The size of the validation panels shall cover the projected area of ​​the rocket in that direction.

[0021] Arrange ground and air shock wave overpressure monitoring systems, video monitoring systems, and infrared thermal imagers at the test site;

[0022] Check and confirm all monitoring systems and complete debugging;

[0023] Fill the tank with fuel and complete the ignition system layout;

[0024] After the personnel evacuate to a safe area, the ignition control system is activated;

[0025] The ignition system is unlocked, an ignition signal is sent, and the monitoring system is started at the same time. The fuel is ignited to generate a fire flame. The internal temperature of the solid engine rises due to the heat. The monitoring system starts recording data, and the rapid combustion test begins.

[0026] The video monitoring system is used to observe whether the solid engine reacts and whether flames or fireballs are generated. After confirming that the engine reaction is complete, the engine reaction level is determined through verification plate, temperature, and shock wave overpressure data.

[0027] Compared with the prior art, the present invention has the following beneficial effects:

[0028] (1) The present invention can conduct a rapid cook-off test on a solid motor without using sample characterization, so the cook-off safety of the tested solid motor can be directly obtained;

[0029] (2) The present invention proposes a universal solid rocket engine rapid burnout test method, which is generally applicable to various types of solid rocket engines, and the test results can be compared and referenced with each other;

[0030] (3) The present invention can obtain shock wave overpressure of solid motors on the ground and in the air during solid motor rapid burnout tests;

[0031] (4) The present invention can obtain the horizontal and vertical ambient temperatures of the solid motor during the solid motor rapid burn test;

[0032] (5) The present invention can obtain thermal radiation infrared imaging of a solid engine during a solid engine rapid cook-off test;

[0033] (6) The present invention adopts a combination of internal and external temperature measurement points to more accurately monitor the temperature changes in the solid engine rapid combustion test, and can determine the location of the hot spot area inside the solid engine. BRIEF DESCRIPTION OF THE DRAWINGS

[0034] Figure 1 Schematic diagram of a solid propellant rapid cook-off test system in the prior art.

[0035] Figure 2 This is a schematic diagram of the solid motor rapid cook-off test system of the present invention.

[0036] Figure 3 This is a top view schematic diagram of the solid motor rapid cook-off test system of the present invention.

[0037] Figure 4 Schematic diagram of the distribution of temperature measurement points inside the solid rocket engine in the present invention. DETAILED DESCRIPTION

[0038] To make the objectives, technical solutions and advantages of the present invention more clear, the embodiments of the present invention will be described in further detail below with reference to the accompanying drawings.

[0039] A solid engine rapid burnout test device, such as Figure 2 and Figure 3 As shown, it includes a fixing device, a fire roasting device (including an oil tank, fuel, and an ignition system), a ground shock wave overpressure monitoring system, an air shock wave overpressure monitoring system, an ambient temperature monitoring system, a solid engine temperature monitoring system, a verification board, a video monitoring system, an infrared thermal imager, etc.

[0040] Before the rapid cooking test, Figure 4 A solid rocket motor temperature monitoring system was established. Surface temperature measurement points were arranged on the solid rocket motor case surface, evenly spaced axially along the solid rocket motor case equator and circumferentially in the horizontal and vertical directions. Internal temperature measurement points were also arranged on the surface of the grain within the solid rocket motor combustion chamber. These points were located at characteristic locations, such as the front, middle, and rear of the inner bore, the bottom of the wing slots, and the front and rear openings.

[0041] When conducting a rapid bake-off test, the solid engine under test is placed above the oil tank through a fixing device, and the ignition system is used to ignite the fuel in the oil tank to generate a flame so that the flame heats the outer surface of the solid engine. At the same time as the ignition begins, each monitoring system is started and data is recorded.

[0042] The ambient temperature monitoring system monitors the ambient temperature around the solid motor during testing and, if a reaction occurs, monitors its impact on the ambient temperature. The solid motor temperature monitoring system monitors the temperature at measuring points on the solid motor surface and internally, reflecting changes in the solid motor surface and internal temperature during rapid cook-off tests and recording any changes in the solid motor surface and internal temperature. An infrared thermal imager records the radiant heat generated during the rapid cook-off test, enabling analysis of the solid motor's thermal conditions. The video monitoring system records the flame combustion, solid motor reaction, the operation of various monitoring system measuring points, and the operation of the witness plate during the rapid cook-off test. The ground shock wave overpressure monitoring system monitors the ground shock wave overpressure generated by the solid motor reaction, while the air shock wave overpressure monitoring system monitors the air shock wave overpressure generated by the solid motor reaction. The witness plate is used to withstand the impact of ejected solid material during the solid motor reaction.

[0043] Through the environmental temperature monitoring system, solid engine temperature monitoring system, infrared thermal imager and video monitoring system, the location of the hot spot area inside the solid engine during the rapid combustion test can be analyzed, as well as the internal and external temperature change patterns of the engine from heating to combustion or explosion.

[0044] Ground-based and airborne shockwave overpressure monitoring systems and witness plates are used to determine the level of solid motor reaction. If the witness plate shows perforations, pits, or plastic deformation after a reaction, and significant shockwave overpressure is detected, it indicates that the solid motor has exploded. If the solid motor reaction produces flames, the witness plate remains intact after a reaction, and no overpressure is detected, it is considered that the solid motor has burned.

[0045] A solid rocket motor rapid cook-off test method, comprising:

[0046] 1. Transport the solid motor, fixture, ignition system (including oil tank, fuel, ignition system), ground shock wave overpressure monitoring system, air shock wave overpressure monitoring system, ambient temperature monitoring system, solid motor temperature monitoring system, verification board, video monitoring system, infrared thermal imager, etc. used in the test to the test site;

[0047] 2. Arrange surface temperature measuring points and internal temperature measuring points on the surface and inside of the solid motor. Surface temperature measuring points are evenly distributed 3 to 10 in the vertical and horizontal directions along the solid motor equator. Internal temperature measuring points are arranged at characteristic locations such as the front, middle, and rear of the inner hole on the inner surface of the combustion chamber grain, the bottom of the wing slot, the front opening, and the rear opening. Two measuring points are arranged at each characteristic location (one of which is a backup), completing the solid motor temperature monitoring system setup.

[0048] 3. Place the fixture in the center of the oil tank and secure it. Slowly lift the solid engine onto the fixture and secure it.

[0049] 4. Arrange temperature measurement points of the ambient temperature monitoring system horizontally and above the solid motor, with the temperature measurement points 50 cm away from the surface of the solid motor;

[0050] 5. Place witness plates on the sides and front of the solid motor in the horizontal direction. The witness plates should be 100 cm away from the solid motor surface and should cover the projected area of ​​the motor in that direction.

[0051] 6. Arrange ground and air shock wave overpressure monitoring systems, video monitoring systems, infrared thermal imagers, etc. at the test site;

[0052] 7. Check and confirm all monitoring systems and complete debugging;

[0053] 8. Pour fuel into the oil tank and complete the ignition system layout;

[0054] 9. After personnel evacuate to a safe area, the ignition control system is activated;

[0055] 10. The ignition system is unlocked, an ignition signal is sent, and the monitoring system is started at the same time. The fuel is ignited to generate a fire flame. The internal temperature of the solid engine rises due to the heat. The monitoring system starts recording data, and the rapid combustion test begins;

[0056] 11. Use the video monitoring system to observe whether the solid rocket motor reacts and whether flames or fireballs are generated. After confirming that the engine reaction is complete, determine the engine reaction level through verification plates, temperature, shock wave overpressure data, etc.

[0057] The contents not described in detail in the specification of the present invention belong to the common knowledge of those skilled in the art.

[0058] Although the present invention has been disclosed above in terms of preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art may make possible changes and modifications to the technical solutions of the present invention by using the methods and technical contents disclosed above 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 content of the technical solutions of the present invention shall fall within the scope of protection of the technical solutions of the present invention.

Claims

1. A solid rocket engine rapid cooking test device, characterized in that: It includes a fixing device, a fire roasting device, an ambient temperature monitoring system, a solid engine temperature monitoring system, a video monitoring system, an infrared thermal imager, a ground shock wave overpressure monitoring system, an air shock wave overpressure monitoring system, and a verification board; the fire roasting device includes an oil tank, fuel, and an ignition system; The solid motor under test is placed above the oil tank using a fixture, and the ignition system is used to ignite the fuel in the oil tank to generate a flame, so that the flame directly heats the outer surface of the solid motor; The ambient temperature monitoring system is used to monitor the ambient temperature around the solid motor during the test. If the solid motor reacts, the impact of the solid motor on the ambient temperature can be monitored. The solid motor temperature monitoring system is used to monitor the temperature of the solid motor surface and internal measuring points. It can reflect the changes in the solid motor surface and internal temperature during the solid motor rapid burn test. If the solid motor reacts, the changes in the solid motor surface and internal temperature can be recorded. The video monitoring system is used to record the flame combustion conditions, solid engine reaction conditions, working conditions of each monitoring system measurement point, and working conditions of the verification board during the rapid burn-off test; The infrared thermal imager is used to record the radiant heat during the rapid cooking test and to analyze the heating conditions of the solid rocket motor; The ground shock wave overpressure monitoring system is used to monitor the shock wave overpressure generated in the ground direction when the solid engine reacts. The air shock wave overpressure monitoring system is used to monitor the shock wave overpressure generated in the air direction when the solid engine reacts. The verification plate is used to receive the impact of solid matter flying out when the solid engine reacts.

2. The solid engine rapid cooking test device according to claim 1, characterized in that: Surface temperature measuring points are arranged on the surface of the solid motor case. The surface temperature measuring points are evenly distributed axially according to the spacing length of the solid motor case equator, and are arranged circumferentially in the horizontal and vertical directions.

3. The solid rocket engine rapid cooking test device according to claim 1, characterized in that: Internal temperature measuring points are arranged on the surface of the internal grain of the solid motor combustion chamber. The internal temperature measuring points are arranged at the front, middle and rear parts of the inner hole, the bottom of the wing slot, the front opening and the rear opening.

4. The solid rocket engine rapid cooking test device according to claim 1, characterized in that: Through the environmental temperature monitoring system, solid engine temperature monitoring system, infrared thermal imager and video monitoring system, it is possible to analyze the location of hot spots inside the solid engine during the rapid burn test, as well as the internal and external temperature change patterns of the engine from heating to combustion or explosion.

5. The solid rocket engine rapid cooking test device according to claim 1, characterized in that: The ground shock wave overpressure monitoring system, the air shock wave overpressure monitoring system and the verification plate are used to determine the reaction level of the solid engine. If the verification plate shows perforations, pits, or plastic deformation after the reaction, and significant shock wave overpressure is detected, it means that the solid engine has exploded.

6. The solid rocket engine rapid cooking test device according to claim 1, characterized in that: The ground shock wave overpressure monitoring system, the air shock wave overpressure monitoring system and the verification plate are used to determine the reaction level of the solid motor. If the solid motor reaction produces flames, the verification plate is intact after the reaction, and no overpressure is detected, it is considered that the solid motor is burning.

7. A test method based on the solid rocket engine rapid cooking test device according to claim 1, characterized in that: include: Surface temperature measuring points and internal temperature measuring points are arranged on the surface and inside of the solid motor; the surface temperature measuring points are evenly distributed in the vertical and horizontal directions along the solid motor equator, and the internal temperature measuring points are arranged on the inner surface of the combustion chamber grain at the front, middle and rear of the inner hole, the bottom of the wing slot, the front opening and the rear opening; Place the fixture in the center of the oil tank and secure it, then slowly lift the solid engine onto the fixture and secure it; Arrange temperature measuring points of the ambient temperature monitoring system in the horizontal direction and above the outside of the solid rocket; 1. Validation panels shall be arranged on the sides and front of the solid rocket in the horizontal direction. The size of the validation panels shall cover the projected area of ​​the rocket in that direction. Arrange ground and air shock wave overpressure monitoring systems, video monitoring systems, and infrared thermal imagers at the test site; Check and confirm all monitoring systems and complete debugging; Fill the tank with fuel and complete the ignition system layout; After the personnel evacuate to a safe area, the ignition control system is activated; The ignition system is unlocked, an ignition signal is sent, and the monitoring system is started at the same time. The fuel is ignited to generate a fire flame. The internal temperature of the solid engine rises due to the heat. The monitoring system starts recording data, and the rapid combustion test begins. The video monitoring system is used to observe whether the solid engine reacts and whether flames or fireballs are generated. After confirming that the engine reaction is complete, the engine reaction level is determined through verification plate, temperature, and shock wave overpressure data.

8. The test method according to claim 7, characterized in that The external temperature measurement point of the solid motor shall be no less than 50 cm away from the surface of the solid motor.

9. The test method according to claim 7, characterized in that The verification plate shall be no less than 100 cm away from the surface of the solid rocket engine.

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