Joint test device for low-altitude flight spark ignition type optical engine

Abstract

The invention is suitable for the fields of aircraft component configuration, power device design and measuring instrument design and development, and provides a combined test device for a low-altitude flight spark-ignition optical engine, which comprises a spark-ignition optical engine suitable for low-altitude flight. The system further comprises a first Nd: YAG laser, a second Nd: YAG laser, a dye laser, a first spectrometer, a second spectrometer, a first ICCD, a second ICCD and a DG 645 digital delay generator. Real-time synchronous measurement of in-cylinder component concentration and temperature designed and developed for a low-altitude flight spark-ignition engine can be realized, and research work of in-cylinder combustion characteristics and pollutant generation performance of the low-altitude flight engine can be explored based on the test device. And an important combined test device is provided for development design and performance optimization of a low-altitude flight power device.

Description

Technical Field

[0001] The present invention relates to the fields of aircraft component configuration and power plant design and measuring instrument design and development, and in particular to a combined testing device for a low-altitude flying ignition optical engine. Background Art

[0002] The growing number of cars has led to a sharp increase in fossil fuel consumption and a widespread problem in major cities. To alleviate resource constraints and urban traffic congestion, researchers have conducted extensive research on new fuel-powered vehicles and manned flying vehicles. However, current research has largely focused on electric flying vehicles. While electric energy can alleviate the increasing consumption of petroleum energy, it is currently primarily derived from thermal power generation, which still consumes non-renewable fossil resources. Therefore, exploring new fuel engines suitable for low-altitude flight as a power plant is an effective way to address the massive consumption of fossil fuels and traffic congestion. However, current research on power plants has largely focused on traditional fuels. Therefore, developing a power plant suitable for low-altitude flight requires optical visualization of the in-cylinder combustion characteristics and overall pollutant generation characteristics of new fuel engines. Currently, commonly used optical testing techniques include high-speed photography, high-speed schlieren, laser-induced fluorescence, and laser-induced incandescence. However, these testing techniques primarily focus on macroscopic and qualitative measurements of the target area. Therefore, it is of great breakthrough significance to develop a joint test device for low-altitude flight spark-ignition optical engine Raman scattering concentration measurement and coherent Stokes Raman scattering temperature measurement for accurate quantitative measurement of the concentration and temperature of the combustion field and crankcase components of low-altitude flight power units. Summary of the Invention

[0003] The present invention provides a combined testing device for a low-altitude flying spark-ignition optical engine, which solves the technical problems mentioned in the background technology.

[0004] A combined test device for a low-altitude flight spark-ignition optical engine, comprising a spark-ignition optical engine suitable for low-altitude flight, a first Nd:YAG laser, a second Nd:YAG laser, a dye laser, a first spectrometer, a second spectrometer, a first ICCD, a second ICCD, and a DG 645 digital delay generator; Among them, the ignition optical engine suitable for low-altitude flight emits and detects real-time synchronized square wave electronic pulse signals through the electronic control unit and current clamp. In conjunction with the DG 645 digital delay generator, it connects the first Nd:YAG laser, the second Nd:YAG laser, the dye laser, the first spectrometer, the second spectrometer, the first ICCD and the second ICCD through the BNC anti-interference signal line to realize the signal timing synchronization setting of the entire system.

[0005] Preferably, the spark-ignition optical engine suitable for low-altitude flight is a spark-ignition optical engine with a small cylinder diameter, and the combustion chamber and crankcase are both designed with optical windows. The spark-ignition optical engine suitable for low-altitude flight is composed of a fuel supply system, a simulated supercharged intake system, an electronic control unit system and a signal generation synchronization system.

[0006] Preferably, the first Nd:YAG laser and the second Nd:YAG laser can emit 532nm pulsed lasers, both of which are 10Hz pulsed lasers. The first Nd:YAG laser is used to excite the spontaneous Raman scattering signal of the area to be measured, which is used to measure the concentration of the area to be measured; the second Nd:YAG laser is used to excite the dye laser to emit 607nm pulsed laser, and at the same time, synchronously emit 532nm pulsed laser through the beam splitting optical path. After the two beams of pulsed laser are synchronously incident on the area to be measured, they are used to excite the combustion field in the area to be measured to generate coherent anti-Stokes Raman scattering signals.

[0007] Preferably, the first spectrometer and the second spectrometer are 1200 transmission grating spectrometers, which cooperate with the first ICCD and the second ICCD respectively to collect spontaneous Raman scattering signals and coherent anti-Stokes Raman scattering signals of the area to be measured.

[0008] Preferably, the DG 645 digital delay generator has 8 channels, which are used to synchronize the timing of the ignition optical engine for low-altitude flight, the first Nd:YAG laser, the second Nd:YAG laser, the dye laser, the first ICCD, and the second ICCD, so as to realize real-time synchronous measurement of the concentration and temperature of the components in the cylinder at different time phases of the engine.

[0009] Preferably, the ignition optical engine suitable for low-altitude flight is fixed to the ground by anchor bolts. The flame during the combustion process can be excited by the laser through the optical window, and the combustion information in the cylinder can be transmitted to the optical test instrument through the optical glass; the first Nd:YAG laser and the dye laser are fixedly installed in parallel through the aluminum profile to ensure that the light emitted by the first Nd:YAG laser does not dissipate the incoming 532nm laser light. The dye laser emits 607nm laser light, and the position of the first Nd:YAG laser is calibrated to ensure that the 532nm laser light it emits is A 532nm laser and a 607nm laser are combined to emit into the area to be measured. The combined excitation of the 532nm laser and the 607nm laser can achieve coherent Stokes Raman scattering in the area to be measured, and then accurately measure the temperature quantitatively using the Voigt spectrum fitting algorithm. A second Nd:YAG laser is fixed through an aluminum profile and is perpendicular to the first Nd:YAG laser at a 90° angle to the area to be measured. The first spectrometer is fixedly connected in parallel to the first ICCD; the second spectrometer is fixedly connected in parallel to the second ICCD; the first spectrometer and the second spectrometer are fixed through an aluminum profile and are at a 90° angle. The DG 645 digital delay generator is fixed to the ground through the aluminum profile and is softly connected to the ignition optical engine suitable for low-altitude flight, the dye laser, and the first / second spectrometers through a BNC anti-interference signal cable.

[0010] Beneficial effects achieved by the present invention: The present invention provides a combined testing device for a low-altitude flight spark-ignition optical engine, which can realize real-time synchronous measurement of the concentration and temperature of the components in the cylinder designed and developed for the low-altitude flight spark-ignition engine. Based on this testing device, research work on the in-cylinder combustion characteristics and pollutant generation of the low-altitude flight engine can be explored, providing an important combined testing device for the development, design and performance optimization of low-altitude flight power units. BRIEF DESCRIPTION OF THE DRAWINGS

[0011] Figure 1 The present invention provides a structural schematic diagram of a combined testing device for a low-altitude flying spark-ignition optical engine.

[0012] Notes on the reference numerals: 1-ignition optical engine suitable for low-altitude flight, 2-first Nd:YAG laser, 3-second Nd:YAG laser, 4-dye laser, 5-first spectrometer, 6-second spectrometer, 7-first ICCD, 8-second ICCD, 9-DG 645 digital delay generator. DETAILED DESCRIPTION

[0013] Various exemplary embodiments of the present invention will now be described in detail. This detailed description should not be considered as limiting the present invention, but rather as a more detailed description of certain aspects, features, and embodiments of the present invention.

[0014] It should be understood that the terms described herein are intended only to describe particular embodiments and are not intended to limit the present invention. In addition, for numerical ranges herein, it should be understood that each intermediate value between the upper and lower limits of the range is also specifically disclosed. Each smaller range between any intermediate value within a stated value or stated range and any other stated value or intermediate value within the stated range is also encompassed by the present invention. The upper and lower limits of these smaller ranges may be independently included or excluded within the scope.

[0015] Unless otherwise indicated, all technical and scientific terms used herein have the same meaning as commonly understood by those skilled in the art. Although only preferred methods and materials are described herein, any methods and materials similar or equivalent to those described herein may also be used in the practice or testing of the present invention. All documents mentioned in this specification are incorporated by reference to disclose and describe the methods and / or materials associated with the documents. In the event of any conflict with any incorporated document, the contents of this specification shall prevail.

[0016] It will be apparent to those skilled in the art that various modifications and variations may be made to the specific embodiments described herein without departing from the scope or spirit of the invention. Other embodiments will be apparent to those skilled in the art from the description of the invention. The description and examples are intended to be exemplary only.

[0017] The words “include,” “including,” “have,” “contain,” etc. used in this document are open-ended terms, meaning including but not limited to.

[0018] See also Figure 1 The embodiment of the present invention provides a combined test device for a low-altitude flight spark-ignition optical engine, comprising a spark-ignition optical engine 1 suitable for low-altitude flight, a first Nd:YAG laser 2, a second Nd:YAG laser 3, a dye laser 4, a first spectrometer 5, a second spectrometer 6, a first ICCD 7, a second ICCD 8, and a DG 645 digital delay generator 9; Among them, the ignition optical engine 1 suitable for low-altitude flight sends and detects real-time synchronized square wave electronic pulse signals through the electronic control unit and current clamp, and cooperates with the DG 645 digital delay generator 9 through the BNC anti-interference signal line to connect the first Nd:YAG laser 2, the second Nd:YAG laser 3, the dye laser 4, the first spectrometer 5, the second spectrometer 6, the first ICCD 7 and the second ICCD 8 to realize the signal timing synchronization setting of the whole system.

[0019] In this embodiment, the spark-ignition optical engine 1 suitable for low-altitude flight is a spark-ignition optical engine with a small cylinder diameter, and the combustion chamber and crankcase are both designed with optical windows. The spark-ignition optical engine 1 suitable for low-altitude flight is composed of a fuel supply system, a simulated supercharged intake system, an electronic control unit system and a signal generation and synchronization system, and is used for the visualization of combustion and emission research of new fuels.

[0020] In this embodiment, the first Nd:YAG laser 2 and the second Nd:YAG laser 3 can emit 532nm pulsed lasers, both of which are 10Hz pulsed lasers. The first Nd:YAG laser 2 is used to excite the spontaneous Raman scattering signal of the area to be measured, which is used to measure the concentration of the area to be measured; the second Nd:YAG laser 3 is used to excite the dye laser 4 to emit 607nm pulsed laser, and at the same time, synchronously emit 532nm pulsed laser through the splitting optical path. After the two beams of pulsed laser are synchronously incident on the area to be measured, they are used to excite the combustion field in the area to be measured to generate coherent anti-Stokes Raman scattering signals.

[0021] In this embodiment, the first spectrometer 5 and the second spectrometer 6 are 1200 transmission grating spectrometers with high acquisition accuracy and high resolution, and are respectively used in conjunction with the first ICCD 7 and the second ICCD 8 to collect spontaneous Raman scattering signals and coherent anti-Stokes Raman scattering signals of the area to be measured.

[0022] In this embodiment, the DG 645 digital delay generator 9 has 8 channels, which can adjust the timing and amplitude of the digital signal, and is used to synchronize the timing of the ignition optical engine for low-altitude flight, the first Nd:YAG laser 2, the second Nd:YAG laser 3, the dye laser 4, the first ICCD 7, and the second ICCD 8, thereby realizing real-time synchronous measurement of the concentration and temperature of the components in the cylinder at different time phases of the engine.

[0023] In this embodiment, an ignition optical engine 1 suitable for low-altitude flight is fixed to the ground by anchor bolts. The flame during its combustion process can be excited by laser through an optical window, and the combustion information in the cylinder is transmitted to the optical test instrument through optical glass; the first Nd:YAG laser 2 and the dye laser 4 are fixedly installed in parallel by an aluminum profile, ensuring that the light emitted by the first Nd:YAG laser 2 does not dissipate the 532nm laser entering the dye laser 4 to emit 607nm laser. At the same time, the position of the first Nd:YAG laser 2 is calibrated to ensure that the 532nm laser and the 607nm laser emitted by it coincide with each other and enter the area to be measured. The combined excitation of the 532nm laser and the 607nm laser can realize coherent Stokes Raman scattering in the area to be measured, and then the accurate quantitative measurement of temperature is realized by the Voigt spectrum fitting algorithm; the second Nd:YAG laser 3 is fixed by an aluminum profile at a 90° angle to the first Nd:YAG laser 2 to capture the area to be measured, so that the two 532nm laser beams can be perpendicular to each other and enter the area to be measured. nm do not interfere with each other, and one beam is used to measure component concentration, and the other is used to measure temperature. The first spectrometer 5 and the first ICCD 7 are fixedly connected in parallel by bolts. The first spectrometer 5 scatters information from the combustion field through scattering of the transmission grating into a characteristic spectrum containing component concentration and temperature information. The first ICCD 7 collects this information and completes data acquisition and processing of the spectral signal. The second spectrometer 6 and the second ICCD 8 are also fixedly connected in parallel by bolts. The first spectrometer 5 and the second spectrometer 6 are fixed by aluminum profiles at 90 degrees. This ensures that the component concentration information and temperature information of the tube spectrum are resolved by the spectrometers and collected by the two ICCDs without interfering with each other. The DG 645 digital delay generator 9 is fixed to the ground by aluminum profiles and is softly connected to the spark-ignited optical engine 1 suitable for low-altitude flight, the dye laser 4, and the first / second spectrometers via BNC anti-interference signal cables, realizing real-time synchronous measurement of the component concentration and temperature of the test area at different time phases of the optical engine.

[0024] Working principle: First, install, start and preheat the ignition optical engine 1 suitable for low-altitude flight, check the operating status and trigger signal output stability of the ignition optical engine 1 suitable for low-altitude flight, and ensure stable operation of the engine at a specified speed, reliable and stable ignition, and stable signal output through the digital signal generator.

[0025] Then, the first Nd:YAG laser 2, the second Nd:YAG laser 3 and the dye laser 4 are started to test the energy stability between laser pulses, and then the entire excitation light path is aligned and debugged to ensure that the excitation light path accurately enters the area to be tested.

[0026] Install and debug the first spectrometer 5, the second spectrometer 6, the first ICCD 7 and the second ICCD 8, collimate and debug the entire collection optical path and perform a collimation test to ensure that the signal of the test area is accurately collected into the spectrometer and ICCD camera.

[0027] Based on the timing synchronization status of the entire optical engine system, laser excitation system, and signal collection system connected by DG 645 digital delay generator 9, after ensuring the timing synchronization, the entire optical engine and test system are powered on to study the combustion process and pollutant generation process in the cylinder of the engine suitable for low-altitude flight.

[0028] It should be noted that, in this document, the term "comprises" or any other variant thereof is intended to cover non-exclusive inclusion, so that a process, method, article, or apparatus that includes a series of elements includes not only those elements, but also includes other elements not explicitly listed, or also includes elements inherent to such process, method, article, or apparatus. In the absence of further limitations, an element defined by the phrase "comprises a ..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes the element.

[0029] The above are only preferred embodiments of the present invention and are not intended to limit the patent scope of the present invention. Any equivalent structure or equivalent process transformation made using the contents of the present invention description and drawings, or directly or indirectly applied in other related technical fields, are also included in the patent protection scope of the present invention.

Claims

1. A combined test device for a low-altitude flying spark-ignition optical engine, comprising a spark-ignition optical engine (1) suitable for low-altitude flight, characterized in that: It also includes a first Nd:YAG laser (2), a second Nd:YAG laser (3), a dye laser (4), a first spectrometer (5), a second spectrometer (6), a first ICCD (7), a second ICCD (8), and a DG 645 digital delay generator (9); The ignition optical engine (1) suitable for low-altitude flight emits and detects a real-time synchronized square wave electronic pulse signal through an electronic control unit and a current clamp, and cooperates with a DG 645 digital delay generator (9) to connect a first Nd:YAG laser (2), a second Nd:YAG laser (3), a dye laser (4), a first spectrometer (5), a second spectrometer (6), a first ICCD (7) and a second ICCD (8) through a BNC anti-interference signal line to realize the signal timing synchronization setting of the entire system.

2. The combined testing device for a low-altitude flying spark-ignition optical engine according to claim 1, characterized in that: The spark-ignition optical engine (1) suitable for low-altitude flight is a spark-ignition optical engine in which both the combustion chamber and the crankcase are designed with optical windows. The spark-ignition optical engine (1) suitable for low-altitude flight is composed of a fuel supply system, a simulated supercharged air intake system, an electronic control unit system, and a signal generation synchronization system.

3. The combined testing device for a low-altitude flying spark-ignition optical engine according to claim 1, characterized in that: The first Nd:YAG laser (2) and the second Nd:YAG laser (3) can emit 532nm pulsed lasers, both of which are 10Hz pulsed lasers. The first Nd:YAG laser (2) is used to excite the spontaneous Raman scattering signal of the area to be measured, and is used to measure the concentration of the area to be measured; the second Nd:YAG laser (3) is used to excite the dye laser (4) to emit 607nm pulsed laser, and at the same time, synchronously emit 532nm pulsed laser through the beam splitting optical path. After the two pulsed lasers are synchronously incident on the area to be measured, they are used to excite the combustion field in the area to be measured to generate a coherent anti-Stokes Raman scattering signal.

4. The combined testing device for a low-altitude flying spark-ignition optical engine according to claim 1, characterized in that: The first spectrometer (5) and the second spectrometer (6) are 1200 transmission grating spectrometers, which are respectively used in conjunction with the first ICCD (7) and the second ICCD (8) to collect spontaneous Raman scattering signals and coherent anti-Stokes Raman scattering signals of the area to be measured.

5. The combined testing device for a low-altitude flying spark-ignition optical engine according to claim 1, characterized in that: The DG 645 digital delay generator (9) has 8 channels and is used for setting the timing synchronization of an ignition optical engine for low-altitude flight, a first Nd:YAG laser (2), a second Nd:YAG laser (3), a dye laser (4), a first ICCD (7), and a second ICCD (8), thereby realizing real-time synchronous measurement of the concentration and temperature of components in the cylinder at different time phases of the engine.

6. The combined testing device for a low-altitude flying spark-ignition optical engine according to claim 1, characterized in that: The ignition optical engine (1) suitable for low-altitude flight is fixed on the ground. The flame in the combustion process can be excited by the laser through the optical window, and the combustion information in the cylinder is transmitted to the optical test instrument through the optical glass; the first Nd:YAG laser (2) and the dye laser (4) are fixedly installed in parallel to ensure that the light emitted by the first Nd:YAG laser (2) does not dissipate the 532nm laser entering the dye laser (4) to emit 607nm laser, and at the same time calibrate the position of the first Nd:YAG laser (2) to ensure that the 532nm laser and the 607nm laser emitted by it coincide with each other and enter the test area; the second Nd:YAG laser (3) is fixed by an aluminum profile and is perpendicular to the first Nd:YAG laser (2) at 90 degrees to the test area; the first spectrometer (5) is fixedly connected to the first ICCD (7) in parallel; the second spectrometer (6) is fixedly connected to the second ICCD (8) in parallel; the first spectrometer (5) and the second spectrometer (6) are fixed by an aluminum profile and are at 90 degrees, DG The 645 digital delay generator (9) is fixed to the ground through an aluminum profile and is softly connected to the ignition optical engine (1) suitable for low-altitude flight, the dye laser (4), the first spectrometer (5), and the second spectrometer (6) through a BNC anti-interference signal line.

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