Sub-millisecond combustion mode discrimination system and method based on pressure and photoelectric sensing multi-source heterogeneous data fusion

Abstract

The invention discloses a sub-millisecond combustion mode discrimination system and method based on pressure and photoelectric sensing multi-source heterogeneous data fusion. The system comprises a pressure detection module, a photoelectric signal detection module, a data fusion analysis module and a discrimination result output module. The pressure detection module and the photoelectric signal detection module are arranged at the characteristic point positions in the combustion chamber of the dual-mode scramjet engine respectively, data fusion analysis is carried out on synchronous measurement signals of the pressure detection module and the photoelectric signal detection module, the combustion mode discrimination method with remarkable characteristics is formed, and only a few continuous measurement values are needed. The purpose of fast-response and high-reliability combustion mode discrimination can be achieved, and the theoretical discrimination speed can reach the sub-millisecond magnitude under the support of the high-frequency data acquisition speed (greater than or equal to 10kHz).

Description

Technical Field

[0001] The present invention belongs to the field of energy power device sensing technology, and relates to a scramjet engine combustion mode judgment device and method, and specifically to a scramjet engine combustion mode judgment device and method using pressure and photoelectric sensor multi-source heterogeneous data fusion to achieve sub-millisecond level. Background Art

[0002] Scramjet (Supersonic Combustion Ramjet) is a high-speed air-breathing propulsion system. Compared with traditional turbofan engines, scramjet engines have no complex rotating parts, relatively simple structure, and can generate greater thrust. They are especially suitable for high-speed flight and have broad application prospects and development potential in the fields of aerospace planes, hypersonic weapons, and wide-range aircraft.

[0003] At present, the technology of dual-mode scramjet engine is still in the stage of continuous development and improvement, and its working state can be divided into two combustion modes, namely, scramjet mode and subcombustion mode. In the scramjet mode, the thermal throat in the combustion chamber does not reach the critical state, and the airflow velocity of the entire flow field remains in the supersonic state, which helps to achieve higher combustion efficiency and thrust performance; in the subcombustion mode, the thermal throat in the combustion chamber remains in the sonic state, the airflow upstream of the sonic section is subsonic flow, and the airflow downstream of the sonic section is supersonic flow. This mode is suitable for the case of low incoming flow velocity. In order to ensure that the dual-mode scramjet engine has a high performance in the entire wide Mach number range, it is necessary to choose the appropriate time to convert the combustion mode during the flight. When the incoming flow conditions change, the control system needs to perform a smooth combustion mode conversion through fuel regulation; the mutation and hysteresis characteristics in the conversion process will cause nonlinear changes in thrust, affecting the stability of the aircraft, and in severe cases, it will cause dangerous accidents such as engine overheating and inlet failure to start. When controlling the combustion mode transition, it is necessary to seek a combustion mode characterization method with high precision, high reliability and fast response.

[0004] The characterization method of the combustion mode of a dual-mode scramjet engine is usually to arrange several pressure measuring points at specific locations based on the basic characteristics of the engine, and to characterize the engine combustion mode through the pressure values ​​or the relationship between the pressures of these measuring points. However, this method requires the arrangement of multiple measuring points, which is very easy to cause misjudgment of the results when there is a small amount of data; only by increasing the data accumulation for a period of time can sufficient accuracy be ensured, which in turn leads to a time lag in mode discrimination; as an input parameter for engine control, the discrimination lag of the combustion mode is very unfavorable to the engine stability control. Therefore, it is urgent to develop a method for convenient and rapid judgment of the engine combustion mode. Summary of the invention

[0005] In order to achieve easy-to-operate, highly reliable, and fast-response combustion mode discrimination of a dual-mode scramjet engine, the present invention provides a sub-millisecond combustion mode discrimination system and method using multi-source heterogeneous data fusion of pressure and photoelectric sensors. The present invention arranges pressure detection modules and photoelectric signal detection modules at characteristic points inside the combustion chamber of the dual-mode scramjet engine, performs data fusion analysis on the synchronous measurement signals of the two, and forms a combustion mode discrimination method with significant characteristics. Only a few consecutive measurement values ​​are required to achieve the purpose of fast response and high reliability of combustion mode discrimination. With the support of high-frequency data acquisition speed (≥10kHz), the theoretical discrimination speed can reach the sub-millisecond level.

[0006] The objective of the present invention is achieved through the following technical solutions:

[0007] A sub-millisecond combustion mode discrimination system using pressure and photoelectric sensor multi-source heterogeneous data fusion includes a pressure detection module, a photoelectric signal detection module, a data fusion analysis module and a discrimination result output module, wherein:

[0008] The pressure detection module is used to obtain the pressure values ​​of the characteristic points of the dual-mode scramjet engine combustion chamber and transmit them to the data fusion analysis module;

[0009] The photoelectric signal detection module is used to obtain the photoelectric signal representing the combustion intensity of the dual-mode scramjet engine combustion chamber and transmit it to the data fusion analysis module;

[0010] The data fusion analysis module is used to process the synchronous data obtained by the pressure detection module and the photoelectric signal detection module in real time, and to quickly distinguish the combustion mode of the dual-mode scramjet engine through the synchronous data fusion analysis algorithm;

[0011] The discrimination result output module is used to display the discrimination result in real time and provide corresponding signals to a potential control system.

[0012] A sub-millisecond combustion mode discrimination method using pressure and photoelectric sensor multi-source heterogeneous data fusion includes the following steps:

[0013] Step 1: obtain characteristic points in the combustion chamber of the dual-mode scramjet engine through experiments or simulations, and arrange pressure detection modules and photoelectric information detection modules to collect pressure values ​​and photoelectric signals of the characteristic points in real time during the test;

[0014] Step 2: The data fusion analysis module uses a synchronous data fusion analysis algorithm to process the synchronous pressure value and the photoelectric signal to achieve sub-millisecond discrimination of the combustion mode of the dual-mode scramjet engine;

[0015] Step 3: Transmit the judgment result of step 2 to the judgment result output module, display the combustion mode of the current dual-mode scramjet engine in real time, and transmit the signal to the control system according to relevant requirements.

[0016] Compared with the prior art, the present invention has the following advantages:

[0017] 1. The present invention combines the pressure information and the combustion intensity information represented by the photoelectric signal, and a small amount of continuously measured data can realize the rapid judgment of the combustion model. Compared with the general method, it has a faster response and higher accuracy.

[0018] 2. The present invention has fewer measuring points arranged on the engine, has a simple structure, is easy to operate, and is suitable for integrated application in flight tests; at the same time, parameters can be adjusted in time according to the test conditions to achieve more efficient modal discrimination results, and has great room for optimization. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] Figure 1 It is a schematic diagram of the principle of the combustion mode rapid discrimination system of the present invention;

[0020] Figure 2 It is a flow chart of the data fusion analysis algorithm of the present invention;

[0021] Figure 3 The typical pressure data and photoelectric signal changes over time obtained in the real ground model engine test of the present invention;

[0022] Figure 4 For the present invention Figure 3 The average value S of N consecutive data calculated in the data;

[0023] Figure 5 For the present invention Figure 4 The judgment basis R calculated from the data. DETAILED DESCRIPTION

[0024] The technical solution of the present invention is further described below in conjunction with the accompanying drawings, but is not limited thereto. Any modification or equivalent replacement of the technical solution of the present invention without departing from the spirit and scope of the technical solution of the present invention should be included in the protection scope of the present invention.

[0025] The present invention provides a sub-millisecond combustion mode discrimination system using pressure and photoelectric sensor multi-source heterogeneous data fusion, such as Figure 1 As shown, the system includes a pressure detection module, a photoelectric signal detection module, a data fusion analysis module and a discrimination result output module, wherein:

[0026] The pressure detection module is used to obtain the pressure values ​​of the characteristic points of the dual-mode scramjet engine combustion chamber and transmit them to the data fusion analysis module;

[0027] The photoelectric signal detection module is used to obtain the photoelectric signal representing the combustion intensity of the dual-mode scramjet engine combustion chamber and transmit it to the data fusion analysis module;

[0028] The data fusion analysis module is used to process the synchronous data obtained by the pressure detection module and the photoelectric signal detection module in real time, and to quickly distinguish the combustion mode of the dual-mode scramjet engine through the synchronous data fusion analysis algorithm;

[0029] The discrimination result output module is used to display the discrimination result in real time and provide corresponding signals to a potential control system.

[0030] In the present invention, the pressure detection module is a detection device capable of obtaining the static pressure inside the dual-mode scramjet engine, including but not limited to a static pressure sensor, etc., and its data sampling rate is ≥1kHz.

[0031] In the present invention, the photoelectric signal detection module is a detection device capable of obtaining the flame luminous intensity in the combustion chamber of a dual-mode scramjet engine, including but not limited to a photomultiplier tube, a photodetector, etc., and its data sampling rate is ≥1kHz; when detecting the flame luminous intensity in real time and obtaining the radiation information of a specific component, filters of different bands can be selectively used at the front end of the photoelectric signal detection module to achieve higher accuracy and faster judgment speed.

[0032] In the present invention, the data fusion analysis module is a hardware device that can quickly implement a synchronous data fusion analysis algorithm and output a discrimination result.

[0033] A sub-millisecond combustion mode discrimination method using pressure and photoelectric sensor multi-source heterogeneous data fusion, obtains the basic characteristics of the engine combustion chamber through experiments or simulations, and arranges pressure detection modules and photoelectric signal detection modules at characteristic points to characterize the pressure value and combustion intensity of the point. Finally, through the synchronous data fusion analysis algorithm of the two, the sub-millisecond discrimination of the combustion mode of the dual-mode scramjet engine is realized. The method specifically includes the following steps:

[0034] Step 1: obtain characteristic points in the combustion chamber of the dual-mode scramjet engine through experiments or simulations, and arrange pressure detection modules and optoelectronic information detection modules to collect pressure values ​​and optoelectronic signals of the characteristic points in real time during the test.

[0035] In this step, the characteristic points in the combustion chamber of the dual-mode scramjet engine are obtained based on experiments or simulation calculations, and are generally the anchoring positions of the flames.

[0036] Step 2: The data fusion analysis module uses a synchronous data fusion analysis algorithm to process the synchronous pressure value and the photoelectric signal to achieve sub-millisecond discrimination of the combustion mode of the dual-mode scramjet engine. The specific steps are as follows:

[0037] Step 21: Obtain time series data of pressure and photoelectric signals, such as Figure 3 As shown, set the parameters K, N, T1 and T2 according to Z k =P k I k The Z value is obtained, where K is the average value of M S values ​​calculated for the scramjet mode and the subsmoker mode under standard test conditions, M>100, N is the number of selected continuous measurement values, T1 and T2 are preset thresholds, and P k represents the kth pressure value collected in chronological order, I k represents the kth photoelectric signal collected in time sequence, Z k It represents the product of the kth pressure value collected in time sequence and the photoelectric signal.

[0038] In this step, the parameter K needs to be calculated based on the S value of the scramjet mode and the subsmolar mode under the standard test; the parameter N needs to be set based on the allowable error in the judgment. Generally, the larger the N, the greater the accuracy, but the response time of the mode conversion will decrease accordingly; the parameter thresholds T1 and T2 can be adjusted according to the accuracy of the test and the required confidence interval.

[0039] Step 2: Calculate the S value according to formula (1):

[0040]

[0041] Among them, S k is the average of the Z values ​​from k-N+1 to k collected continuously. The result is as follows Figure 4 As shown, which includes the S values ​​when N=1, N=5 and N=10 respectively.

[0042] Step 2: Calculate the R value according to formula (2) and make judgment based on the R value:

[0043] R k =arctan(lnS k -K) (2)

[0044] Among them, R k As the judgment standard, the judgment result is given by comparing with the preset thresholds T1 and T2; the judgment standard is: when R k ≥T1, it is subcombustion mode; when T1>R k >T2, it is a transition mode; when R kWhen ≤T2, it is the scramjet mode, T1 and T2 need to be set according to the confidence interval, and their values ​​are generally between -1 and 1. Figure 5 As shown, the parameters T1 and T2 are set to 0.95 and -0.95 respectively. When the N value is set to 10, the result judgment accuracy is >99%. When the acquisition speed is 10kHz, the judgment speed of the combustion mode is less than 1ms.

[0045] Step 3: Transmit the judgment result of step 2 to the judgment result output module, display the combustion mode of the current dual-mode scramjet engine in real time, and transmit the signal to the control system according to relevant requirements.

Claims

1. A sub-millisecond combustion mode discrimination system using pressure and photoelectric sensor multi-source heterogeneous data fusion, characterized by The system includes a pressure detection module, a photoelectric signal detection module, a data fusion analysis module and a discrimination result output module, wherein: The pressure detection module is used to obtain the pressure values ​​of the characteristic points of the dual-mode scramjet engine combustion chamber and transmit them to the data fusion analysis module; The photoelectric signal detection module is used to obtain the photoelectric signal representing the combustion intensity of the dual-mode scramjet engine combustion chamber and transmit it to the data fusion analysis module; The data fusion analysis module is used to process the synchronous data obtained by the pressure detection module and the photoelectric signal detection module in real time, and to quickly distinguish the combustion mode of the dual-mode scramjet engine through the synchronous data fusion analysis algorithm; The discrimination result output module is used to display the discrimination result in real time and provide corresponding signals to a potential control system.

2. The sub-millisecond combustion mode discrimination system using pressure and photoelectric sensor multi-source heterogeneous data fusion according to claim 1 is characterized in that The pressure detection module includes but is not limited to a static pressure sensor.

3. The sub-millisecond combustion mode discrimination system using pressure and photoelectric sensor multi-source heterogeneous data fusion according to claim 1 or 2 is characterized in that The data sampling rate of the pressure detection module is ≥1kHz.

4. The sub-millisecond combustion mode discrimination system using pressure and photoelectric sensor multi-source heterogeneous data fusion according to claim 1 is characterized in that The photoelectric signal detection module includes but is not limited to a photomultiplier tube and a photodetector.

5. The sub-millisecond combustion mode discrimination system using pressure and photoelectric sensor multi-source heterogeneous data fusion according to claim 1 or 4 is characterized in that The data sampling rate of the photoelectric signal detection module is ≥1kHz.

6. The sub-millisecond combustion mode discrimination system using pressure and photoelectric sensor multi-source heterogeneous data fusion according to claim 1 is characterized in that When the system detects the flame luminous intensity in real time and obtains the radiation information of specific components, filters of different bands are selectively used at the front end of the photoelectric signal detection module.

7. A method for distinguishing combustion modes at sub-millisecond level by using the system described in any one of claims 1 to 6 and fusing heterogeneous data from pressure and photoelectric sensors, characterized in that The method comprises the following steps: Step 1: obtain characteristic points in the combustion chamber of the dual-mode scramjet engine through experiments or simulations, and arrange pressure detection modules and photoelectric information detection modules to collect pressure values ​​and photoelectric signals of the characteristic points in real time during the test; Step 2: The data fusion analysis module uses a synchronous data fusion analysis algorithm to process the synchronous pressure value and the photoelectric signal to achieve sub-millisecond discrimination of the combustion mode of the dual-mode scramjet engine; Step 3: Transmit the judgment result of step 2 to the judgment result output module, display the combustion mode of the current dual-mode scramjet engine in real time, and transmit the signal to the control system according to relevant requirements.

8. The sub-millisecond combustion mode discrimination method using pressure and photoelectric sensor multi-source heterogeneous data fusion according to claim 7 is characterized in that The characteristic point in the combustion chamber of the dual-mode scramjet engine is the anchoring position of the flame.

9. The sub-millisecond combustion mode discrimination method using pressure and photoelectric sensor multi-source heterogeneous data fusion according to claim 7 is characterized in that The specific steps of step 2 are as follows: Step 21: Obtain the time series data of pressure and photoelectric signals, and set the parameters K, N, T1 and T2 according to Z k =P k I k The Z value is obtained, where K is the average value of M S values ​​calculated for the scram mode and substeam mode under standard test conditions, N is the number of selected continuous measurement values, T1 and T2 are preset thresholds, and P k represents the kth pressure value collected in chronological order, I k represents the kth photoelectric signal collected in time sequence, Z k It represents the product of the kth pressure value collected in time sequence and the photoelectric signal; Step 2: Calculate the S value according to formula (1): Among them, S k is the average of the Z values ​​from k-N+1 to k collected continuously; Step 2: Calculate the R value according to formula (2) and make judgment based on the R value: R k =arctan(lnS k -K) (2) Among them, R k As the judgment standard, when R k ≥T1, it is subcombustion mode; when T1>R k >T2, it is a transition mode; when R k When ≤T2, it is the scramjc mode.

10. The sub-millisecond combustion mode discrimination method using pressure and photoelectric sensor multi-source heterogeneous data fusion according to claim 9 is characterized in that When M>100, T1 and T2 are set according to the confidence interval, and their values ​​are between -1 and 1.

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