Timing control method for rocket engine combustion chamber and nozzle strong dynamic load test device

Abstract

The invention discloses a timing control method for a rocket engine combustion chamber and a nozzle strong dynamic load test device, which belongs to the field of rocket engines and comprises: performing simulation calculations based on the shock wave motion law in the process of generating strong dynamic loads, obtaining the shock wave motion estimated timing of different stages in the strong dynamic load test device, and constructing the action control timing of the strong dynamic load test device based on the shock wave motion estimated timing; utilizing a heat flux sensor provided in the strong dynamic load test device to monitor the running state of the shock wave and monitor the movement speed of the shock wave in real time; inverting the shock wave operation measured timing of different stages in the strong dynamic load test device according to the actual monitoring result of the heat flux sensor; automatically correcting and adjusting the shock wave motion estimated timing based on the inverted shock wave operation measured timing, and automatically adjusting the subsequent action control timing of the strong dynamic load test device; the invention can respond to various changes in the experimental process in real time and ensure the high precision of timing control.

Description

Technical Field

[0001] The invention relates to the technical field of rocket engine timing control, and in particular to a timing control method for a rocket engine combustion chamber and a nozzle strong dynamic load test device. Background Art

[0002] The performance verification of the combustion chamber and nozzle of a rocket engine is extremely important, and the strong dynamic load test is one of the key links in the process of technology research and development. The strong dynamic load environment is extremely complex and has a strong energy impact. There are usually strong energy release processes such as detonation, explosion, high-speed impact, and rapid flight, which instantly produce extremely high pressure, temperature or speed changes. It may cause strong shock waves, exert huge forces and impulses on surrounding objects, and make objects bear loads far beyond their static bearing capacity; it may also cause continuous forces and torques, causing structures or mechanisms to produce large-scale displacements and movements in space. The physical process of the strong dynamic load environment involves multiphase flow and complex chemical reactions. At the same time, the performance of the material will be significantly deformed, and the structure may even move and flip, which will have a profound impact on the mechanical response and failure mode.

[0003] However, the rocket engine combustion chamber and nozzle high dynamic load test equipment is driven by high-pressure air and energetic medium. The computational simulation of its high dynamic load environment is quite difficult. In addition, there are complex structural evolutions in the flow field, which may even cause damage to the instrument. As a result, it is difficult to accurately control the timing of system control, measurement and acquisition during the experiment, especially when it comes to the timing control of key processes such as aircraft, engine, component separation, and detonation.

[0004] There are two traditional approaches: (1) The start of the run is set as the starting point t0, and the timing is estimated to be t0+ti. The starting points of other actions are determined with a large margin; (2) A key action in the process is set to t0, and then t0-ti or t0+ti is determined. The typical problem is that it often relies on experience-based judgment and a large amount of redundancy in timing settings, resulting in insufficient accuracy of test timing and control, which seriously affects the effectiveness of the test. Summary of the invention

[0005] The purpose of the present invention is to provide a timing control method for a rocket engine combustion chamber and nozzle high dynamic load test device to solve the technical problem that the prior art relies on experience-based judgment and a large amount of redundancy in timing settings, resulting in insufficient accuracy of test timing and control, which seriously affects the effectiveness of the test.

[0006] In order to solve the above technical problems, the present invention specifically provides the following technical solutions:

[0007] The timing control method of the rocket engine combustion chamber and nozzle strong dynamic load test device comprises the following steps:

[0008] Step 100: High-pressure air and energetic medium are jointly driven to form shock waves, and simulation calculations are performed based on the shock wave motion law in the process of generating strong dynamic loads to obtain the shock wave motion estimated timing of different stages in the strong dynamic load test device, and the action control timing of the strong dynamic load test device is constructed based on the shock wave motion estimated timing;

[0009] Step 200, using a thermal flux sensor provided in the strong dynamic load test device to monitor the running state of the shock wave and monitor the movement speed of the shock wave in real time;

[0010] Step 300: invert the measured timing sequence of the shock wave operation at different stages in the strong dynamic load test device according to the actual monitoring result of the thermal flux sensor, analyze the operating state of the shock wave at different positions and at different times of the strong dynamic load test device based on the measured timing sequence of the shock wave operation, and determine the correlation between the operating state of the shock wave and the time when the shock wave arrives at different stages;

[0011] Step 400: automatically correct and adjust the shock wave motion estimated timing based on the inverted shock wave motion measured timing, and automatically adjust the subsequent action control timing of the strong dynamic load test device according to the corrected shock wave motion estimated timing.

[0012] As a preferred solution of the present invention, in step 100, different stages of shock wave formation in the strong dynamic load test device include a shock wave free motion stage, a shock wave reflection stage, a shock wave interaction stage, and a shock wave multiple reciprocating motion stage;

[0013] The shock wave free motion stage is a stage in which the energetic medium in the strong dynamic load test device releases energy and generates shock waves in the storage chamber of the strong dynamic load test device;

[0014] The shock wave reflection stage is a stage in which the shock wave meets the wall of the strong dynamic load test device to form a reflected wave when the shock wave moves toward the nozzle direction of the strong dynamic load test device;

[0015] The shock wave interaction stage is a stage in which multiple energetic media detonations in the strong dynamic load test device result in the generation of multiple shock waves, wherein the forces of the multiple shock waves influence each other;

[0016] The shock wave multiple reciprocating motion stage is a stage in which the shock wave is reflected back and forth in the strong dynamic load test device and interacts with various structures.

[0017] As a preferred solution of the present invention, the time series expression of the estimated time series of the shock wave motion at different stages in the strong dynamic load test device is:

[0018] ti=f (mass of energetic medium, device size, time interval of multi-point detonation).

[0019] As a preferred solution of the present invention, in step 200, the heat flux sensor is installed on the inner wall surface of the strong dynamic load test device, and all heat flux sensors are arranged in sequence along the impact direction of the shock wave, and the heat flux sensor is used to measure the moment when the shock wave arrives at its installation position.

[0020] As a preferred solution of the present invention, in step 300, the moments when the shock wave arrives at a plurality of different heat flux sensors in sequence are determined through statistical analysis of the monitoring data of each of the heat flux sensors, a correlation relationship between the shock wave operation state and time is established, and based on the correlation relationship, it is inferred whether the difference between the measured timing of the shock wave operation in the entire experimental process and the estimated timing of the shock wave motion is in line with expectations.

[0021] As a preferred solution of the present invention, in step 300, by setting different experimental conditions for the strong dynamic load test device, the monitoring results of each of the heat flux sensors are re-acquired, and based on the monitoring results of each of the heat flux sensors and the shock wave motion law, the inverted shock wave operation measured time sequence is corrected, so that the corrected shock wave operation measured time sequence can meet different experimental conditions;

[0022] Among them, different experimental conditions include changing the pressure of high-pressure air, the type and amount of energetic medium.

[0023] As a preferred solution of the present invention, in step 400, the control object of the action control sequence is the test device and the measurement system in the strong dynamic load test device;

[0024] According to the correlation between the running state of the shock wave and the moment when the shock wave reaches different stages, and the positional relationship between the control object of the action control sequence and the heat flux sensor, the action control sequence is constructed to trigger the test device and the measurement system to complete related actions.

[0025] As a preferred solution of the present invention, the difference between the real-time monitoring time of each of the heat flux sensors and the estimated monitoring time of the corresponding heat flux sensor in the shock wave motion estimation timing is determined according to the real-time monitoring time of each of the heat flux sensors, and the action control timing is updated based on the difference.

[0026] Compared with the prior art, the present invention has the following beneficial effects:

[0027] The present invention proposes to use the law of shock wave motion as the core basis for timing control. Traditional methods are often based on simple time estimation or the time points of key actions. This implementation starts from the physical phenomenon of shock waves and can more accurately reflect the essential characteristics of a strong dynamic load environment, providing a more scientific method for timing control.

[0028] The estimated timing of the shock wave motion with the shock wave motion law as the control core is adjusted through timing inverse calculation, and the relationship between the estimated timing of the shock wave motion and the action control timing of some mobile equipment is established. By monitoring the difference between the real-time monitoring time of the shock wave motion to a certain important position and the predicted time corresponding to the important position in the estimated timing of the shock wave motion, the automatic correction mechanism is used to realize dynamic adjustment of the action control timing, which can respond to various changes in the experimental process in real time and ensure the high precision of timing control. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] In order to more clearly illustrate the implementation methods of the present invention or the technical solutions in the prior art, the following briefly introduces the drawings required for the implementation methods or the description of the prior art. Obviously, the drawings in the following description are only exemplary, and for ordinary technicians in this field, other implementation drawings can be derived from the provided drawings without creative work.

[0030] Figure 1 Schematic diagram of a flow chart of a timing control method according to an embodiment of the present invention. DETAILED DESCRIPTION

[0031] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions 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.

[0032] like Figure 1 As shown, the present invention provides a timing control method for a rocket engine combustion chamber and nozzle strong dynamic load test device, wherein the strong dynamic load test device can use an existing test device, and the strong dynamic load test device for the rocket engine combustion chamber and nozzle is jointly driven by high-pressure air and energetic medium, with initial power provided by high-pressure air, and further energy released through combustion or explosion of energetic medium. The two devices work together to accurately simulate the strong dynamic load environment faced by the rocket engine during startup and actual operation, including extremely complex pressure, temperature, speed, etc.

[0033] The strong dynamic load test device can provide a test time of 10ms to 1s, which can simulate the millisecond-level drastic changes at the moment of rocket engine startup, and can also simulate stable working conditions. By accurately adjusting the operating conditions, the device can achieve large load changes and accurately apply them according to different test requirements, thereby meeting the performance test requirements of the combustion chamber and nozzle under various working conditions.

[0034] This embodiment extracts the main characteristics of shock wave motion according to the law of shock wave motion in the flow field evolution process in the strong dynamic load test device, and uses this as the basis for control work in the strong dynamic load test device.

[0035] The high-precision timing control method specifically includes the following steps:

[0036] Step 100, high-pressure air and energetic medium are jointly driven to form shock waves in the strong dynamic load test device, and simulation calculations are performed based on the shock wave motion law in the process of generating strong dynamic loads, and the shock wave motion estimated timing of different stages in the strong dynamic load test device is simulated, and the action control timing of the strong dynamic load test device is constructed based on the shock wave motion estimated timing.

[0037] The generation, propagation and interaction of shock waves are closely related to physical processes such as gas compression, expansion and energy release of energetic media. By changing the two parameters of high-pressure air and energetic media, a large number of numerical simulations of strong dynamic load experiments are formed. A data table can be formed according to the numerical simulation, and the estimated timing of shock wave motion at different stages in the strong dynamic load test device can be determined based on the data table.

[0038] Among them, in step 100, the shock wave movement impact process in the strong dynamic load test device forms different shock wave motion analysis stages, including the shock wave free motion stage, the shock wave reflection stage, the shock wave interaction stage, and the shock wave multiple reciprocating motion stage.

[0039] The shock wave free motion stage is the stage in which the energetic medium in the strong dynamic load test device releases energy and generates shock waves in the storage chamber of the strong dynamic load test device.

[0040] The shock wave reflection stage is the stage in which the shock wave meets the wall of the strong dynamic load test device to form a reflected wave when the shock wave moves toward the nozzle of the strong dynamic load test device.

[0041] The shock wave interaction stage is the stage in which multiple energetic medium detonations in the strong dynamic load test device lead to the generation of multiple shock waves, in which the forces of multiple shock waves influence each other.

[0042] The multiple reciprocating motion stage of the shock wave is the stage in which the shock wave reflects back and forth in the strong dynamic load test device and interacts with various structures.

[0043] Among them, the implementation method of obtaining the estimated timing of shock wave motion through simulation operation is: based on the gas dynamics theory, the expansion speed of high-pressure air under different pressures is calculated, and then the time and propagation speed of shock wave generation are predicted. For the reaction process of energetic media, the rate and time of energy release can be estimated based on the chemical reaction kinetic model, so as to determine the changes of shock wave under the influence of energetic medium reaction, and then through numerical simulation of multiple different shock wave analysis stages, the estimated timing of shock wave motion at different stages in the strong dynamic load test device is determined.

[0044] The time series expression of the shock wave motion prediction time series at different stages in the strong dynamic load test device is:

[0045] ti=f (mass of energetic medium, device size, time interval of multi-point detonation).

[0046] The high dynamic load test device for the rocket engine combustion chamber and nozzle also has some specific operation, measurement and collection equipment set during the test, such as; ignition and detonation at the 1st millisecond; engine start-up at the 3rd millisecond; second ignition and detonation at the 5th millisecond, etc.

[0047] Based on the simulation, the estimated timing of shock wave motion at different stages in the strong dynamic load test device, and the installation position of specific operation, measurement and acquisition equipment in the strong dynamic load test device, the action control timing of specific operation, measurement and acquisition equipment is estimated.

[0048] Since in step 100, the shock wave motion estimation timing and action control timing at different stages in the strong dynamic load test device are obtained based on simulation calculations and have certain errors, it is necessary to improve, correct and perfect the estimation timing, and the improvement, correction and perfection can be achieved through the following steps 200 and 300.

[0049] Step 200: monitor the running state of the shock wave using the thermal flux sensor provided in the strong dynamic load test device, and monitor the movement speed of the shock wave in real time.

[0050] In step 200, the heat flux sensors are installed on the inner wall surface of the strong dynamic load test device, and all the heat flux sensors are arranged in sequence along the impact direction of the shock wave, and the heat flux sensors are used to measure the moment when the shock wave reaches its installation position.

[0051] Step 300: According to the actual monitoring results of the thermal flux sensor, the measured timing of the shock wave operation at different stages in the strong dynamic load test device is inverted; based on the measured timing of the shock wave operation, the operating status of the shock wave at different positions and at different times of the strong dynamic load test device is analyzed, and the correlation between the operating status of the shock wave and the time when the shock wave arrives at different stages is determined.

[0052] In step 300, by statistically analyzing the monitoring data of each heat flux sensor, the time when the shock wave arrives at multiple different heat flux sensors in sequence is determined, and the correlation between the shock wave operation state and the time when the shock wave arrives at each heat flux sensor is inverted. Based on the correlation, it is inferred whether the difference between the measured timing of the shock wave operation in the entire experimental process and the estimated timing of the shock wave motion is in line with expectations.

[0053] By analyzing the state of the shock wave at different positions in the strong dynamic load test device, the correlation between the shock wave operation state and the shock wave motion moment is determined. For example, by measuring the time when the shock wave reaches the installation positions of multiple heat flux sensors, the shock wave operation measured time sequence of the shock wave propagation velocity and the shock wave propagation time can be established, and then it can be inferred whether the shock wave operation measured time sequence obtained during the entire experimental process meets expectations.

[0054] In order to ensure the accuracy of this correlation, it is also necessary to verify it through typical experiments. In typical experiments, different experimental conditions are set, such as changing the pressure of high-pressure air, the type and amount of energetic medium, etc., to observe the motion law and timing changes of shock waves, and correct and improve the measured timing of shock wave operation obtained by inversion, so that the measured timing of shock wave operation can accurately reflect various situations.

[0055] Among them, the thermal flux sensor monitors the heat flux, and the implementation principle of inverting the actual timing of shock wave operation based on the statistical analysis of the monitoring data of each thermal flux sensor is as follows: the shock wave contacts the thermal flux sensor during movement, resulting in a jump in the thermal flux curve, and the arrival time of the shock wave is extracted according to the jump on the thermal flux curve at multiple positions, that is, the timing of the shock wave is obtained, which is used to analyze the timing of shock wave arrival at different positions to determine the correlation between the shock wave operation state and the shock wave movement time, which is the inversion process. There are many ways to establish this correlation, such as table lookup, wave series diagram or polynomial fitting.

[0056] Specifically, in step 300, by setting different experimental conditions for the strong dynamic load test device, the monitoring results of each heat flux sensor are re-acquired, and the shock wave operation measured time sequence obtained by inversion is corrected based on the monitoring results of each heat flux sensor and the shock wave motion law, so that the corrected shock wave operation measured time sequence can meet different experimental conditions;

[0057] Among them, different experimental conditions include changing the pressure of high-pressure air, the type and amount of energetic medium.

[0058] Step 400: Based on the inverted measured shock wave operation timing, the correlation between the shock wave operation state and the time when the shock wave arrives at different stages is obtained, and the shock wave motion estimated timing is automatically corrected and adjusted, and the subsequent action control timing of the strong dynamic load test device is automatically adjusted according to the actual monitoring time of each heat flux sensor.

[0059] In step 400, the control object of the action control sequence is the test device and the measurement system in the strong dynamic load test device;

[0060] According to the correlation between the running state of the shock wave and the moment when the shock wave reaches different stages, as well as the positional relationship between the control object of the action control sequence and the heat flux sensor, an action control sequence is constructed to trigger the test device and the measurement system to complete related actions.

[0061] Furthermore, the difference between the real-time monitoring time of each heat flux sensor and the estimated monitoring time of the corresponding heat flux sensor in the shock wave motion estimation timing is determined according to the real-time monitoring time of each heat flux sensor, and the action control timing is updated based on the difference.

[0062] By comparing the real-time monitoring time of each heat flux sensor with the predicted monitoring time of each heat flux sensor according to the estimated timing of shock wave motion, the deviation of the shock wave motion position during the experiment can be discovered in time. For example, if the shock wave reaches the heat flux sensor at a key position earlier or later than expected, it means that there is a problem with the shock wave motion timing. At this time, according to the pre-set correction algorithm, the timing of subsequent actions in the action control timing is automatically adjusted to ensure that the entire experimental process is carried out according to the precise timing.

[0063] This automatic correction mechanism can realize timing monitoring and precise regulation throughout the entire experimental process, and can ensure high-precision control of the timing no matter in the initial, middle or final stages of the experiment. In complex high-dynamic-load experiments, such as multiple engine detonation experiments or multi-stage separation experiments of aircraft, this high-precision control method can ensure precise coordination between various actions, thereby improving the success rate of the experiment and the reliability of the results.

[0064] Therefore, this implementation method proposes to use the law of shock wave motion as the core basis for timing control. Traditional methods are often based on simple time estimates or the time points of key actions. This implementation method starts from the physical phenomenon of shock waves and can more accurately reflect the essential characteristics of the strong dynamic load environment, providing a more scientific method for timing control.

[0065] The estimated timing of the shock wave motion based on the law of shock wave motion is adjusted through timing inverse calculation, and the relationship between the estimated timing of the shock wave motion and the action control timing of some mobile equipment is established. By monitoring the difference between the real-time monitoring time of the shock wave motion to a certain important position and the predicted time corresponding to the important position in the estimated timing of the shock wave motion, the automatic correction mechanism is used to realize dynamic adjustment of the action control timing. This innovative mechanism can respond to various changes in the experimental process in real time and ensure high-precision timing control.

[0066] The above embodiments are only exemplary embodiments of the present application and are not intended to limit the present application. The protection scope of the present application is defined by the claims. Those skilled in the art may make various modifications or equivalent substitutions to the present application within the essence and protection scope of the present application, and such modifications or equivalent substitutions shall also be deemed to fall within the protection scope of the present application.

Claims

1. A timing control method for a rocket engine combustion chamber and nozzle strong dynamic load test device, characterized in that: The following steps are involved: Step 100: High-pressure air and energetic medium are jointly driven to form shock waves, and simulation calculations are performed based on the shock wave motion law in the process of generating strong dynamic loads to obtain the shock wave motion estimated timing of different stages in the strong dynamic load test device, and the action control timing of the strong dynamic load test device is constructed based on the shock wave motion estimated timing; Step 200, using a thermal flux sensor provided in the strong dynamic load test device to monitor the running state of the shock wave and monitor the movement speed of the shock wave in real time; Step 300: invert the measured timing sequence of the shock wave operation at different stages in the strong dynamic load test device according to the actual monitoring result of the thermal flux sensor, analyze the operating state of the shock wave at different positions and at different times of the strong dynamic load test device based on the measured timing sequence of the shock wave operation, and determine the correlation between the operating state of the shock wave and the time when the shock wave arrives at different stages; Step 400, automatically correcting and adjusting the shock wave motion estimated timing based on the inverted shock wave motion measured timing, and automatically adjusting the subsequent action control timing of the strong dynamic load test device according to the corrected shock wave motion estimated timing; In step 100, different stages of shock wave formation in the strong dynamic load test device include a shock wave free motion stage, a shock wave reflection stage, a shock wave interaction stage, and a shock wave multiple reciprocating motion stage; The shock wave free motion stage is a stage in which the energetic medium in the strong dynamic load test device releases energy and generates shock waves in the storage chamber of the strong dynamic load test device; The shock wave reflection stage is a stage in which the shock wave meets the wall surface of the strong dynamic load test device to form a reflected wave when the shock wave moves toward the nozzle direction of the strong dynamic load test device; The shock wave interaction stage is a stage in which multiple energetic media detonations in the strong dynamic load test device result in the generation of multiple shock waves, wherein the forces of the multiple shock waves influence each other; The shock wave multiple reciprocating motion stage is a stage in which the shock wave is reflected back and forth in the strong dynamic load test device and interacts with various structures; The time series expression of the shock wave motion prediction time series at different stages in the strong dynamic load test device is: ti=f (mass of energetic medium, device size, time interval of multi-point detonation).

2. The timing control method of the rocket engine combustion chamber and nozzle strong dynamic load test device according to claim 1 is characterized in that: In step 200, the heat flux sensor is installed on the inner wall surface of the strong dynamic load test device, and all heat flux sensors are arranged in sequence along the impact direction of the shock wave, and the heat flux sensor is used to measure the moment when the shock wave reaches its installation position.

3. The timing control method of the rocket engine combustion chamber and nozzle strong dynamic load test device according to claim 1 is characterized in that: In step 300, by statistically analyzing the monitoring data of each of the heat flux sensors, the moments when the shock wave arrives at a plurality of different heat flux sensors in sequence are determined, and a correlation between the shock wave operation state and time is established. Based on the correlation, it is inferred whether the difference between the measured timing of the shock wave operation in the entire experimental process and the estimated timing of the shock wave motion is in line with expectations.

4. The timing control method of the rocket engine combustion chamber and nozzle strong dynamic load test device according to claim 3 is characterized in that: In step 300, different experimental conditions are set for the strong dynamic load test device, the monitoring results of each of the heat flux sensors are reacquired, and the inverted measured shock wave operation time sequence is corrected based on the monitoring results of each of the heat flux sensors and the shock wave motion law, so that the corrected shock wave operation measured time sequence can meet different experimental conditions; Among them, different experimental conditions include changing the pressure of high-pressure air, the type and amount of energetic medium.

5. The timing control method of the rocket engine combustion chamber and nozzle strong dynamic load test device according to claim 4 is characterized in that: In the step 400, the control object of the action control sequence is the test device and the measurement system in the strong dynamic load test device; According to the correlation between the running state of the shock wave and the moment when the shock wave reaches different stages, and the positional relationship between the control object of the action control sequence and the heat flux sensor, the action control sequence is constructed to trigger the test device and the measurement system to complete related actions.

6. The timing control method of the rocket engine combustion chamber and nozzle strong dynamic load test device according to claim 5 is characterized in that: The difference between the real-time monitoring time of each heat flux sensor and the estimated monitoring time of the corresponding heat flux sensor in the shock wave motion estimation timing is determined according to the real-time monitoring time of each heat flux sensor, and the action control timing is updated based on the difference.

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