Test system used for solid rocket engine inner trajectory aftereffect segment research

Abstract

The invention discloses a test system for researching a ballistic aftereffect section in a solid rocket engine, and the system comprises a test cabin which is internally provided with a simulation test engine and a rack; the vacuum tank is in a vacuum state and is communicated with the test cabin through a pipeline; the pressure control module is used for forcing air in the test cabin to flow into the vacuum tank after the loading of the simulation test engine is finished and the cabin door of the test cabin is completely closed, and enabling the test cabin to be at a preset pressure intensity, so that the test of the simulation test engine in the test cabin is carried out at the preset pressure intensity; air in the test chamber is sucked away through the vacuum tank, the pressure intensity of the test chamber is kept to be smaller than the internal pressure intensity of the engine, the engine is always in a vacuum state in the inner ballistic descending section process, test data are collected through the measurement and control system, and the research requirement of the solid rocket engine inner ballistic aftereffect section is met.

Description

Technical Field

[0001] The invention belongs to the field of solid rocket engines, and in particular relates to a test system for studying the interior ballistic aftereffect section of a solid rocket engine. Background Art

[0002] With the continuous upgrading of my country's aircraft and launch vehicle technology, higher requirements are placed on accuracy. However, there are unsteady combustion gases produced by the combustion of residual propellant in the engine during the descent phase, and the carbonization and ablation of the insulation layer will also generate gas. In this process, the engine flow parameters and engine thrust undergo rapid and complex changes. For the last-stage engine, the working altitude is relatively high, and the last stage can be approximated as a vacuum environment. When the last-stage engine is not separated from the head body, as long as there is gas in the combustion chamber, the gas can flow through the nozzle and be discharged at an accelerated rate, thereby generating after-effect thrust that affects the accuracy of the aircraft. Because the after-effect thrust is only generated in a vacuum environment and the thrust is very small, the cost of conducting air tests is relatively high.

[0003] Therefore, artificially creating this "vacuum" state and keeping the ambient pressure lower than the internal pressure of the engine is a prerequisite for analyzing and predicting the changing laws of various parameters in the engine combustion chamber during the descent phase. Studying the aftereffect impulse of solid rocket engines has very important engineering value for improving energy utilization and aircraft accuracy. At present, there is no ground test system for conducting solid rocket engine internal ballistic aftereffect phase test research. It is costly to develop a high-altitude simulation test bench, and it is difficult to conduct mechanistic research. Summary of the invention

[0004] The purpose of the present invention is to provide a test system for studying the internal ballistic aftereffect section of a solid rocket motor, which can simulate a vacuum state in a laboratory and test the internal ballistic aftereffect section of a solid rocket motor.

[0005] The present invention adopts the following technical scheme: a test system for studying the aftereffect phase of the interior ballistics of a solid rocket motor, comprising:

[0006] The test chamber contains simulated test engines and test benches;

[0007] The vacuum tank is in a vacuum state and is connected to the test chamber through a pipeline. It is used to force the air in the test chamber to flow into the vacuum tank after the simulated test engine is loaded and the door of the test chamber is completely closed, and to make the test chamber be under a predetermined pressure, so that the simulated test engine in the test chamber can be tested under the predetermined pressure.

[0008] Furthermore, it also includes:

[0009] The front pump is connected to the air outlet of the vacuum tank through the third pipeline. The front pump is used to evacuate the vacuum tank and make the pressure in the vacuum tank reach the first specified pressure. The third manual valve is installed on the third pipeline.

[0010] Furthermore, it also includes:

[0011] The main pump is connected with the air outlet of the vacuum tank through the second pipeline and is also connected with the front-stage pump through the first pipeline. The main pump is used to cooperate with the front-stage pump to evacuate the vacuum tank again on the basis of the first specified pressure, and make the pressure in the vacuum tank reach the working pressure; the first pipeline and the second pipeline are respectively installed with a first manual valve and a second manual valve.

[0012] Furthermore, it also includes:

[0013] The solenoid valve is installed on the pipe connecting the vacuum tank and the test chamber, and is used to open after receiving an opening command, so that the vacuum tank can suck away the air in the test chamber.

[0014] Furthermore, it also includes:

[0015] The processing module is used to send an opening instruction to the solenoid valve.

[0016] Further, the method of use is:

[0017] Step 1: Close the solenoid valve, the first manual valve, and the second manual valve, open the third manual valve, and use the fore pump to roughly pump the vacuum tank so that the pressure in the vacuum tank reaches the first specified pressure;

[0018] Step 2: Close the third manual valve, open the first manual valve, and after the main pump is stable, open the second manual valve, and use the fore pump and the main pump to evacuate the vacuum tank again based on the first specified pressure, and make the pressure in the vacuum tank reach the working pressure;

[0019] Step 3: Open the test chamber to ignite the engine. When the pressure in the combustion chamber of the engine reaches the specified value, close the door of the test chamber and trigger the processing module, so that the processing module sends an opening command to the solenoid valve, thereby causing the vacuum tank to suck away the air in the test chamber.

[0020] The beneficial effects of the present invention are:

[0021] The present invention uses a vacuum tank to suck away the air in the test chamber, maintaining the pressure of the test chamber lower than the internal pressure of the engine, so that the engine is always in a "vacuum" state during the inner ballistic descent phase, and uses a measurement and control system to collect test data to meet the research needs of the inner ballistic aftereffect phase of the solid rocket engine. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1It is a system schematic diagram of the present invention;

[0023] Figure 2 It is a schematic diagram of the structure of the present invention.

[0024] Among them: 1. Fore pump; 2. First manual valve; 3. Main pump; 4. Second manual valve; 5. Vacuum tank; 6. Solenoid valve; 7. Test chamber; 8. Third manual valve. DETAILED DESCRIPTION

[0025] The present invention is described in detail below with reference to the accompanying drawings and specific embodiments.

[0026] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside" and the like indicate positions or positional relationships based on the positions 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 device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the present invention. In addition, the terms "first" and "second" are only used for descriptive purposes, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Therefore, the features defined as "first" and "second" may explicitly or implicitly include one or more of the features. In the description of the present invention, unless otherwise specified, "multiple" means two or more.

[0027] The present invention discloses a test system for studying the aftereffect phase of the interior ballistics of a solid rocket motor. Figure 1 and Figure 2 As shown, it includes a test chamber 7 and a vacuum tank 5.

[0028] A simulated test engine and a test bench are placed in the test cabin 7; the vacuum tank 5 is in a vacuum state, and the vacuum tank 5 is connected to the test cabin 7 through a pipeline; the vacuum tank 5 is used to force the air in the test cabin 7 to flow into the vacuum tank 5 after the simulated test engine is loaded and the hatch of the test cabin 7 is completely closed, and the test cabin 7 is placed at a predetermined pressure, thereby allowing the simulated test engine in the test cabin 7 to be tested at the predetermined pressure.

[0029] As for the volume relationship between the vacuum tank 5 and the test chamber 7, according to the ideal gas state equation, after the volume ratio of the two containers reaches a certain ratio, the equilibrium pressure is less affected by the volume ratio of the two containers. Taking into account the cost and performance, the volume ratio of the vacuum tank 5 and the test chamber 7 is selected to be 150, and the internal pressure of the vacuum tank 5 can reach a minimum of 0.4Pa.

[0030] The present invention also includes: a front pump 1, which is connected to the air outlet of the vacuum tank 5 through a third pipe. The front pump 1 is used to evacuate the vacuum tank 5 and make the pressure in the vacuum tank 5 reach a first specified pressure. A third manual valve is installed on the third pipe.

[0031] The present invention also includes: a main pump 3, which is connected to the air outlet of the vacuum tank 5 through a second pipeline. The main pump 3 is also connected to the front-stage pump 1 through a first pipeline. The main pump 3 is used to cooperate with the front-stage pump 1 to evacuate the vacuum tank 5 again on the basis of the first specified pressure, and make the pressure in the vacuum tank 5 reach the working pressure; the first pipeline and the second pipeline are respectively installed with a first manual valve 2 and a second manual valve 4.

[0032] The present invention also includes: a solenoid valve 6, which is installed on a pipe connecting the vacuum tank 5 and the test chamber 7. The solenoid valve 6 is used to open after receiving an opening instruction, and allow the vacuum tank 5 to suck away the air in the test chamber 7.

[0033] The present invention further comprises: a processing module, which is used to send an opening instruction to the solenoid valve 6 .

[0034] The test cabin 7 is equipped with a simulated test engine and a test bench. The front end of the engine is provided with a measuring device for measuring the engine's aftereffect thrust. The middle combustion chamber is provided with a sensor interface for measuring pressure and temperature. The test cabin 7 is provided with an openable and closable door on the side close to the rear end of the engine. The door moves along the designed sliding track through a cylinder piston push rod mechanism to achieve a self-sealing effect of the door.

[0035] The present invention adopts graded air extraction to make the vacuum tank 5 and the test chamber 7 reach the specified working state, and uses the electromagnetic valve 6 to control the pipeline to communicate with the test chamber 7 to transmit real-time data to the measurement and control system. The measurement and control system is composed of sensors, acquisition boards, power supplies and computers, and is connected to the sensor connectors of other subsystems through lines to obtain test data.

[0036] The method of use of the present invention is:

[0037] Step 1: close the solenoid valve 6, the first manual valve 2, and the second manual valve 4, open the third manual valve 8, and use the fore-stage pump 1 to roughly pump the vacuum tank 5, so that the fore-stage pump 1 evacuates the vacuum tank 5 and makes the pressure in the vacuum tank 5 reach the first specified pressure;

[0038] Step 2: Close the third manual valve 8, open the first manual valve 2, and after the main pump 3 is stable, open the second manual valve 4, and use the fore pump 1 and the main pump 3 to evacuate the vacuum tank 5 again on the basis of the first specified pressure, and make the pressure in the vacuum tank 5 reach the working pressure;

[0039] Step 3: Open the test chamber 7 to ignite the engine. When the pressure in the combustion chamber of the engine reaches the specified value, which is usually 0.3Mpa, close the door of the test chamber 7 and trigger the processing module, so that the processing module sends an opening instruction to the solenoid valve 6, thereby allowing the vacuum tank 5 to suck away the air in the test chamber 7 for testing.

[0040] The above are only preferred embodiments of the present invention and are not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc. made within the spirit and principles of the present invention should be included in the protection scope of the present invention.

Claims

1. A test system for studying the aftereffect phase of the interior ballistics of a solid rocket motor, characterized in that: include: A test cabin (7) in which a simulated test engine and a test bench are placed; The vacuum tank (5) is in a vacuum state and is connected to the test chamber (7) through a pipeline. It is used to force the air in the test chamber (7) to flow into the vacuum tank (5) after the simulated test engine is loaded and the door of the test chamber (7) is completely closed, so that the test chamber (7) is at a predetermined pressure, thereby allowing the simulated test engine in the test chamber (7) to be tested at the predetermined pressure.

2. The test system for studying the aftereffect phase of the interior ballistics of a solid rocket motor according to claim 1, characterized in that: Also includes: The front pump (1) is connected to the air outlet of the vacuum tank (5) through a third pipeline. The front pump (1) is used to evacuate the vacuum tank (5) and make the pressure in the vacuum tank (5) reach a first specified pressure. A third manual valve is installed on the third pipeline.

3. The test system for studying the aftereffect phase of the interior ballistics of a solid rocket motor according to claim 2, characterized in that: Also includes: The main pump (3) is connected to the air outlet of the vacuum tank (5) through a second pipeline and is also connected to the front-stage pump (1) through a first pipeline. The main pump (3) is used to cooperate with the front-stage pump (1) to evacuate the vacuum tank (5) again on the basis of the first specified pressure, and to make the pressure in the vacuum tank (5) reach the working pressure; the first pipeline and the second pipeline are respectively installed with a first manual valve (2) and a second manual valve (4).

4. The test system for studying the aftereffect phase of the interior ballistics of a solid rocket motor according to claim 3, characterized in that: Also includes: The electromagnetic valve (6) is installed on a pipeline connecting the vacuum tank (5) and the test chamber (7), and is used to open after receiving an opening instruction, so that the vacuum tank (5) can suck away the air in the test chamber (7).

5. The test system for studying the aftereffect phase of the interior ballistics of a solid rocket motor according to claim 4, characterized in that: Also includes: The processing module is used to send an opening instruction to the solenoid valve (6).

6. The test system for studying the aftereffect phase of the interior ballistics of a solid rocket motor according to claim 4, characterized in that: The usage is: Step 1: close the solenoid valve (6), the first manual valve (2), and the second manual valve (4), open the third manual valve (8), and use the fore pump (1) to roughly pump the vacuum tank (5) so that the pressure in the vacuum tank (5) reaches a first specified pressure; Step 2: Close the third manual valve (8), open the first manual valve (2), and after the main pump (3) is stable, open the second manual valve (4), and use the fore pump (1) and the main pump (3) to evacuate the vacuum tank (5) again on the basis of the first specified pressure, so that the pressure in the vacuum tank (5) reaches the working pressure; Step 3: Open the test chamber (7) to ignite the engine. When the pressure in the combustion chamber of the engine reaches a specified value, close the door of the test chamber (7) and trigger the processing module, so that the processing module sends an opening instruction to the solenoid valve (6), thereby causing the vacuum tank (5) to suck away the air in the test chamber (7).

Images