Variable-pressure solid rocket engine ablation impact experiment platform

Abstract

The invention relates to a variable-pressure solid rocket engine ablation impact experiment platform which comprises a fuel gas generator, a pressure adjusting mechanism, a test piece clamping mechanism and an experiment platform base. The fuel gas generator, the pressure adjusting mechanism and the test piece clamping mechanism are fixed on the experiment platform base. According to the invention, the combustion and ablation process of the solid rocket engine under different pressure conditions can be simulated, so that the performance and stability of the engine material can be evaluated; by simulating a dynamic pressure environment in actual flight, the ablation behavior of the solid rocket engine is subjected to more accurate and comprehensive experimental research; the platform allows researchers to reproduce and research the extreme ablation phenomenon in hypersonic flight under a controlled laboratory condition, and provides a scientific basis for design and material selection of solid rocket engines.

Description

Technical Field

[0001] The invention relates to the field of ablation shock experiments of solid rocket engines, and in particular to an ablation shock experiment platform of variable pressure solid rocket engines. Background Art

[0002] Solid rocket engines are key propulsion technologies in the aerospace and military fields, and their performance directly affects the carrying capacity of aircraft and the success rate of missions. Under hypersonic flight conditions, rocket engines, especially the solid propellants in their combustion chambers, are subject to extreme thermal environments and mechanical shocks, leading to material ablation and performance degradation. The ablation process is complex and involves the interaction between high-temperature gases and solid surfaces, including multiple physical processes such as heat conduction, mass transfer, and chemical reactions. Accurate simulation and research of these phenomena is crucial to improving the performance and reliability of solid rocket engines.

[0003] Traditional solid rocket motor ablation experimental platforms are usually carried out under static conditions and cannot reproduce the dynamic pressure changes and thermal shocks encountered in actual flight. This limitation restricts the in-depth understanding of the ablation behavior of solid rocket motors under actual flight conditions. In addition, the lack of the ability to accurately control and measure experimental conditions has questioned the accuracy and repeatability of ablation data. Therefore, the development of an experimental platform that can simulate the ablation process of solid rocket motors under variable pressure conditions is of great significance for in-depth research on ablation mechanisms, optimizing material design, and improving engine performance.

[0004] The present invention aims to provide a variable pressure solid rocket engine ablation shock experimental platform, which can simulate the dynamic pressure environment in actual flight to conduct more accurate and comprehensive experimental research on the ablation behavior of solid rocket engines. This platform will allow researchers to reproduce and study extreme ablation phenomena in hypersonic flight under controlled laboratory conditions, and provide a scientific basis for the design and material selection of solid rocket engines. Summary of the invention

[0005] In view of the shortcomings of the prior art, the present invention aims to provide a variable pressure solid rocket engine ablation shock test platform, which can simulate the dynamic pressure changes and thermal shocks experienced by solid rocket engines in actual flight, so as to accurately test and analyze the ablation performance of engine materials. The test platform includes three main components: a gas generator, a pressure regulating mechanism and a specimen clamping mechanism.

[0006] The present invention is achieved through the following technical solutions.

[0007] A variable pressure solid rocket engine ablation impact test platform, comprising a gas generator, a pressure regulating mechanism, a specimen clamping mechanism, and a test platform base; the gas generator, the pressure regulating mechanism, and the specimen clamping mechanism are fixed on the test platform base;

[0008] The gas generator includes a gas generator shell and a rear end cover of the gas generator. The gas generator shell is cylindrical. Threaded holes are provided at both ends of the gas generator shell, which are respectively used to connect the rear end cover of the gas generator and the pressure regulating mechanism. A support is provided outside the gas generator shell. The support is used to be fixed to the base of the experimental platform. The rear end cover of the gas generator is provided with a threaded hole connected to the igniter; the support outside the combustion chamber is designed to firmly fix the combustion chamber on the experimental platform to withstand the force and pressure generated during the experiment.

[0009] The pressure regulating mechanism includes a pressure regulating valve and a valve driving mechanism. The pressure regulating valve includes a pressure regulating valve housing, a rear end cover of the pressure regulating valve, and a pressure regulating valve needle bolt. The inner cavity of the pressure regulating valve is composed of two vertical cylindrical cavities; one of the cylindrical cavities passes through the pressure regulating valve housing, one end of which is connected to the rear end cover of the pressure regulating valve, and the other end is connected to the tail nozzle of the specimen clamping mechanism; one end of the other cylindrical cavity is connected to the combustion chamber, and the other end is connected to the cylindrical cavity passing through the pressure regulating valve housing; the exterior of the pressure regulating valve housing is designed to be square, which is convenient for fixing and operation.

[0010] The rear end cover of the pressure regulating valve is designed as a plunger with a flange, and a cylindrical hole is opened in the center for positioning the needle bolt of the pressure regulating valve;

[0011] One end of the pressure regulating valve needle bolt is designed to be truncated into a cone shape, which is used to adjust the equivalent throat area of ​​the nozzle, and the other end is in the shape of a round rod, which is used to connect the valve drive mechanism. The middle part of the pressure regulating valve needle bolt is located in the cylindrical hole opened in the center of the rear end cover of the pressure regulating valve; the pressure regulating valve needle bolt is designed to adjust the equivalent throat area of ​​the tail nozzle to simulate different flight conditions.

[0012] The valve drive mechanism includes a servo motor, a transmission rod, and a pressure sensor. The servo motor is connected to one end of the pressure sensor through the transmission rod, and the other end of the pressure sensor is connected to the pressure regulating valve needle bolt. The servo motor drives the pressure regulating valve needle bolt to move left or right through the transmission rod and the pressure sensor. The pressure sensor is used to monitor the thrust and pull of the transmission rod in real time.

[0013] The specimen clamping mechanism includes a tail nozzle, which is mainly composed of a tail nozzle shell and a throat liner ablation specimen. The tail nozzle shell is detachably connected to the throat liner ablation specimen, the tail nozzle shell is connected to the pressure regulating valve shell, the tail nozzle is connected to the inner cavity of the pressure regulating valve, and one end of the pressure regulating valve pintle is coaxial with the throat liner ablation specimen. The experimental platform is used to simulate the throat liner ablation process of a solid rocket engine under different pressure conditions to evaluate the performance and stability of the engine material.

[0014] Furthermore, a step structure is provided inside the gas generator housing near the front end to limit the movement of the propellant.

[0015] Furthermore, a trapezoidal groove is opened in the central cylindrical hole of the rear end cover of the pressure regulating valve for installing a shaft sealing ring. The rear end cover of the pressure regulating valve is provided with a flange plate, and a circle of trapezoidal grooves is opened on the flange plate for installing a sealing ring to ensure that the regulating valve has good sealing performance.

[0016] Furthermore, the servo motor is fixed on the base of the experimental platform through a motor bracket.

[0017] Furthermore, a gas transition connection section is provided between the gas generator and the pressure regulating mechanism bracket.

[0018] Furthermore, the transmission rod includes a push rod and a threaded rod, the push rod and the threaded rod form a threaded transmission mechanism, the threaded rod is connected to the output end of the servo motor, and the push rod is connected to the pressure sensor.

[0019] Furthermore, it also includes an impact specimen support, which is fixed on the experimental platform base and is located at the outlet end of the tail nozzle.

[0020] Furthermore, the valve drive mechanism also includes a control system for controlling the rotation speed and direction of the servo motor to accurately adjust the position of the needle bolt and achieve precise control of the equivalent throat area of ​​the nozzle.

[0021] Furthermore, it also includes at least one data acquisition system for collecting parameters such as pressure, temperature and speed during the experiment to evaluate the experimental results and optimize the experimental conditions.

[0022] Compared with the prior art, the advantages of the present invention are: the variable pressure solid rocket engine ablation impact test platform of the present invention can provide a full range of ablation tests from static to dynamic during the ablation experiment, and can simulate the ablation environment that the solid rocket engine may encounter in different flight stages by accurately controlling the gas pressure conditions. This not only helps to deeply understand the ablation mechanism, but also provides experimental data and theoretical support for the development of new thermal protection materials and the improvement of existing materials. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 It is a schematic diagram of the three-dimensional structure of the present invention;

[0025] Figure 2 A top view of the present invention;

[0026] Figure 3 It is a cross-sectional view along section AA of the present invention;

[0027] Figure 4 It is a cross-sectional view along section BB of the present invention;

[0028] Among them: 1. Experimental platform base, 2. Motor bracket, 3. Servo motor, 4. Transmission rod, 5. Pressure sensor, 6. Pressure regulating valve, 7. Tail nozzle, 8. Gas generator, 9. Gas transition connection section, 10. Impact specimen support, 401. Push rod, 402. Threaded rod, 601. Pressure regulating valve housing, 602. Rear end cover of pressure regulating valve, 603. Pressure regulating valve needle bolt, 701. Tail nozzle housing, 702. Throat lining ablation specimen, 801. Rear end cover of gas generator, 802. Gas generator housing. DETAILED DESCRIPTION

[0029] The present invention will be further described below in conjunction with the accompanying drawings and specific embodiments, but they are not intended to limit the present invention.

[0030] like Figures 1 to 4 As shown, a variable pressure solid rocket engine ablation impact test platform includes a gas generator 8, a pressure regulating mechanism, a specimen clamping mechanism, and a test platform base 1; the gas generator 8, the pressure regulating mechanism, and the specimen clamping mechanism are fixed on the test platform base 1;

[0031] The gas generator 8 includes a gas generator shell 802 and a gas generator rear end cover 801. The gas generator shell 802 is cylindrical. Threaded holes are provided at both ends of the gas generator shell 802, which are respectively used to connect the gas generator rear end cover 801 and the pressure regulating mechanism. A support is provided outside the gas generator shell 802, and the support is used to be fixed to the experimental platform base 1. The gas generator rear end cover 801 is provided with a threaded hole connected to the igniter; the support outside the combustion chamber is designed to firmly fix the combustion chamber on the experimental platform to withstand the force and pressure generated during the experiment.

[0032] The pressure regulating mechanism includes a pressure regulating valve 6 and a valve driving mechanism. The pressure regulating valve 6 includes a pressure regulating valve housing 601, a rear end cover 602 of the pressure regulating valve, and a pressure regulating valve pintle 603. The inner cavity of the pressure regulating valve 6 is composed of two vertical cylindrical cavities; one of the cylindrical cavities passes through the pressure regulating valve housing 601, one end of which is connected to the rear end cover 602 of the pressure regulating valve, and the other end is connected to the tail nozzle 7 of the specimen clamping mechanism; one end of the other cylindrical cavity is connected to the combustion chamber, and the other end is connected to the cylindrical cavity passing through the pressure regulating valve housing 601; the exterior of the pressure regulating valve housing 601 is designed to be square, which is convenient for fixing and operation.

[0033] The rear end cover 602 of the pressure regulating valve is designed as a plunger with a flange, and a cylindrical hole is opened in the center for positioning the pressure regulating valve pin 603;

[0034] One end of the pressure regulating valve needle bolt 603 is designed to be truncated into a cone shape for adjusting the equivalent throat area of ​​the nozzle, and the other end is designed to be a round rod shape for connecting the valve drive mechanism. The middle part of the pressure regulating valve needle bolt 603 is located in the cylindrical hole opened in the center of the rear end cover 602 of the pressure regulating valve; the pressure regulating valve needle bolt 603 is designed to adjust the equivalent throat area of ​​the tail nozzle to simulate different flight conditions.

[0035] The valve driving mechanism includes a servo motor 3, a transmission rod 4, and a pressure sensor 5. The servo motor 3 is connected to one end of the pressure sensor 5 through the transmission rod 4, and the other end of the pressure sensor 5 is connected to the pressure regulating valve needle bolt 603. The servo motor 3 drives the pressure regulating valve needle bolt 603 to move left or right through the transmission rod 4 and the pressure sensor 5. The pressure sensor 5 is used to monitor the thrust and pull of the transmission rod 4 in real time.

[0036] The specimen clamping mechanism includes a tail nozzle 7, which is mainly composed of a tail nozzle shell 701 and a throat lining ablation specimen 702. The tail nozzle shell 701 and the throat lining ablation specimen 702 are detachably connected, the tail nozzle shell 701 is connected to the pressure regulating valve shell 601, the tail nozzle 7 is connected to the inner cavity of the pressure regulating valve 6, and one end of the truncated cone of the pressure regulating valve pin 603 is coaxial with the throat lining ablation specimen 702. The experimental platform is used to simulate the throat lining ablation process of a solid rocket engine under different pressure conditions to evaluate the performance and stability of the engine material.

[0037] Furthermore, a step structure is provided inside the gas generator housing 802 near the front end to limit the movement of the propellant.

[0038] Furthermore, a trapezoidal groove is provided in the central cylindrical hole of the rear end cover 602 of the pressure regulating valve for installing a shaft sealing ring. The rear end cover 602 of the pressure regulating valve is provided with a flange plate, and a circle of trapezoidal grooves is provided on the flange plate for installing a sealing ring to ensure that the regulating valve has good sealing performance.

[0039] Furthermore, the servo motor 3 is fixed on the experimental platform base 1 through the motor bracket 2.

[0040] Furthermore, a gas transition connection section 9 is provided between the gas generator 8 and the pressure regulating mechanism bracket.

[0041] Furthermore, the transmission rod 4 includes a push rod 401 and a threaded rod 402 , the push rod 401 and the threaded rod 402 form a threaded transmission mechanism, the threaded rod 402 is connected to the output end of the servo motor 3 , and the push rod 401 is connected to the pressure sensor 5 .

[0042] Furthermore, it also includes an impact specimen support 10, which is fixed on the experimental platform base 1, and is located at the outlet end of the tail nozzle 7. The impact specimen support 10 is used to install the impact specimen.

[0043] Furthermore, the valve drive mechanism also includes a control system for controlling the rotation speed and direction of the servo motor to accurately adjust the position of the needle bolt and achieve precise control of the equivalent throat area of ​​the nozzle.

[0044] Furthermore, it also includes at least one data acquisition system for collecting parameters such as pressure, temperature and speed during the experiment to evaluate the experimental results and optimize the experimental conditions.

[0045] Working principle: The control system controls the servo motor 3 to rotate forward, driving the threaded rod 402 to rotate, and then driving the push rod 401 to push the pressure sensor 5. The pressure sensor 5 pushes the pressure regulating valve needle bolt 603 to move to the left, so that the distance between the truncated cone end of the pressure regulating valve needle bolt 603 and the throat lining ablation test piece 702 is reduced, thereby reducing the equivalent throat area of ​​the nozzle. On the contrary, the servo motor 3 is controlled to rotate in the reverse direction, and then the push rod 401 pulls the pressure sensor 5. The pressure sensor 5 pulls the pressure regulating valve needle bolt 603 to move to the right, so that the distance between the truncated cone end of the pressure regulating valve needle bolt 603 and the throat lining ablation test piece 702 is increased, and the equivalent throat area of ​​the nozzle is increased. By changing the equivalent throat area of ​​the nozzle, the pressure of the gas flow inside the pressure regulating valve 6 is changed, and the variable pressure gas flow ablation impact is realized. By controlling the servo motor to push the pressure regulating valve needle bolt forward and backward, the pressure change is controlled; by the ablation state of the throat lining ablation test piece and the ablation state of the impact test piece, the experimental results are comprehensively evaluated and the experimental conditions are optimized.

[0046] The present invention is based on a variable pressure solid rocket engine ablation impact test platform and precisely controls the gas pressure conditions to simulate the ablation environment that a solid rocket engine may encounter in different flight phases, thereby achieving a full range of ablation tests from static to dynamic, and providing experimental data and theoretical support for the development of new thermal protection materials and the improvement of existing materials.

[0047] The present invention utilizes a servo motor to drive a gas pressure regulating valve to control the gas pressure, accurately simulates the gas pressure changes of a solid rocket engine during flight, realizes dynamic ablation test of the engine nozzle throat liner, and obtains more accurate material ablation data.

[0048] The above description is only a preferred embodiment of the present invention, and does not limit the implementation mode and protection scope of the present invention. For those skilled in the art, it should be aware that all solutions obtained by equivalent substitutions and obvious changes made using the description and illustrations of the present invention should be included in the protection scope of the present invention.

Claims

1. A variable pressure solid rocket engine ablation impact test platform, characterized in that: It comprises a gas generator (8), a pressure regulating mechanism, a specimen clamping mechanism, and an experimental platform base (1); the gas generator (8), the pressure regulating mechanism, and the specimen clamping mechanism are fixed on the experimental platform base (1); The gas generator (8) comprises a gas generator shell (802) and a gas generator rear end cover (801); the gas generator shell (802) is cylindrical; threaded holes are provided at both ends of the gas generator shell (802) for connecting the gas generator rear end cover (801) and the pressure regulating mechanism, respectively; a support is provided outside the gas generator shell (802) for fixing to the experimental platform base (1); and the gas generator rear end cover (801) is provided with a threaded hole for connecting to the igniter; The pressure regulating mechanism comprises a pressure regulating valve (6) and a valve driving mechanism. The pressure regulating valve (6) comprises a pressure regulating valve housing (601), a rear end cover (602) of the pressure regulating valve, and a pressure regulating valve pintle (603). The inner cavity of the pressure regulating valve (6) is composed of two vertical cylindrical cavities; one of the cylindrical cavities passes through the pressure regulating valve housing (601), one end of which is connected to the rear end cover (602) of the pressure regulating valve, and the other end is connected to the tail nozzle (7) of the specimen clamping mechanism; one end of the other cylindrical cavity is connected to the combustion chamber, and the other end is communicated with the cylindrical cavity passing through the pressure regulating valve housing (601); The rear end cover (602) of the pressure regulating valve is designed as a plunger with a flange, and a cylindrical hole is opened in the center for positioning the pressure regulating valve needle bolt (603); One end of the pressure regulating valve needle bolt (603) is designed to be truncated cone-shaped for adjusting the equivalent throat area of ​​the nozzle, and the other end is round rod-shaped for connecting the valve driving mechanism. The middle part of the pressure regulating valve needle bolt (603) is located in the cylindrical hole opened in the center of the rear end cover (602) of the pressure regulating valve; The valve driving mechanism comprises a servo motor (3), a transmission rod (4), and a pressure sensor (5); the servo motor (3) is connected to one end of the pressure sensor (5) via the transmission rod (4); the other end of the pressure sensor (5) is connected to a pressure regulating valve needle bolt (603); the servo motor (3) drives the pressure regulating valve needle bolt (603) to move leftward or rightward via the transmission rod (4) and the pressure sensor (5); the pressure sensor (5) is used to monitor the thrust and pull of the transmission rod (4) in real time; The specimen clamping mechanism comprises a tail nozzle (7), the tail nozzle (7) mainly comprising a tail nozzle shell (701) and a throat lining ablation specimen (702), the tail nozzle shell (701) and the throat lining ablation specimen (702) are detachably connected, the tail nozzle shell (701) is connected to a pressure regulating valve shell (601), the tail nozzle (7) is communicated with an inner cavity of the pressure regulating valve (6), and one truncated cone-shaped end of the pressure regulating valve pintle (603) is coaxial with the throat lining ablation specimen (702).

2. The variable pressure solid rocket engine ablation impact test platform according to claim 1, characterized in that: A step structure is provided inside the gas generator housing (802) near the front end to limit the movement of the propellant.

3. The variable pressure solid rocket engine ablation impact test platform according to claim 1, characterized in that: A trapezoidal groove is provided in the central cylindrical hole of the rear end cover (602) of the pressure regulating valve for installing a shaft sealing ring. The rear end cover (602) of the pressure regulating valve is provided with a flange plate, and a circle of trapezoidal grooves is provided on the flange plate for installing the sealing ring.

4. The variable pressure solid rocket engine ablation impact test platform according to claim 1, characterized in that: The servo motor (3) is fixed on the experimental platform base (1) via a motor bracket (2).

5. The variable pressure solid rocket engine ablation impact test platform according to claim 1, characterized in that: The gas generator (8) and the pressure regulating mechanism bracket are provided with a gas transition connection section (9).

6. The variable pressure solid rocket engine ablation impact test platform according to claim 1, characterized in that: The transmission rod (4) comprises a push rod (401) and a threaded rod (402), the push rod (401) and the threaded rod (402) forming a threaded transmission mechanism, the threaded rod (402) being connected to the output end of the servo motor (3), and the push rod (401) being connected to the pressure sensor (5).

7. The variable pressure solid rocket engine ablation impact test platform according to claim 1, characterized in that: It also comprises an impact test piece support (10), which is fixed on the experimental platform base (1), and the impact test piece support (10) is located at the outlet end of the tail nozzle (7).

8. The variable pressure solid rocket engine ablation impact test platform according to claim 1, characterized in that: The valve drive mechanism also includes a control system for controlling the speed and direction of the servo motor to accurately adjust the position of the pintle.

9. A variable pressure solid rocket engine ablation impact test platform according to any one of claims 1 to 8, characterized in that: It also includes at least one data acquisition system for collecting parameters such as pressure, temperature and speed during the experiment to evaluate the experimental results and optimize the experimental conditions.

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