CN211374056U - A solid rocket motor plume smoke particle testing device - Google Patents

Abstract

The solid rocket motor plume smoke particle testing device according to the present invention includes a laser modulation part, which is located between the engine plume and the laser light source part, and modulates the spot size of the incident laser, the beam expansion angle, and the laser space parameters of the effective irradiation measurement area. ; The laser receiving part is located on the other side of the engine plume. The laser receiving part is used to collect and receive the transmitted laser light of different wavelengths after the plume to be measured, and split it into a first beam and a second beam through a half mirror. There are two beams of light; the laser diffraction detection part receives the first beam and is used to detect the diffracted light energy distribution of the first beam; the laser attenuation detection part receives the second beam and then irradiates the grating and then divides it into multiple sub-lasers according to the wavelength; For controlling the laser light source part, the particle testing and processing part is respectively connected in communication with the laser diffraction detection part and the laser attenuation detection part to process and display the parameters of the solid rocket motor plume smoke particles.

Description

A solid rocket motor plume smoke particle testing device

technical field

The utility model belongs to the technical field of aerospace power, and relates to a solid rocket motor plume smoke particle testing device.

Background technique

Solid rocket motors are widely used in aerospace power field due to their high reliability and good performance. With the rapid development of military and aerospace, there are more and more requirements for solid rocket motors. The development of propellant formulations is no longer a one-sided pursuit of higher energy, but has gradually transformed into a comprehensive pursuit of low characteristic signals while ensuring energy performance. gender indicators. The solid rocket motor exhaust plume is the combustion product discharged from the nozzle at supersonic speed. It will further diffuse and expand at the nozzle outlet, forming a luminous and heating plume flow field. Its interaction with the surrounding environment will form smoke and radiation. , on the detection or guidance signal attenuation and other effects, these effects are collectively referred to as the characteristic signal of the exhaust plume.

The engine exhaust plume will produce strong smoke, and the smoke contains a large amount of high-temperature liquid and solid particles, which will cause erosion and contamination of the fuselage of the carrier, interfere with the communication of the carrier, and cause signal attenuation and other problems. Engine plume particle parameters are important characterizations of these adverse effects. However, the particle size of these plume particles has multiple orders of magnitude (from nanometers to millimeters), the particle concentration also has a large range, and the temperature is higher and the radiation is stronger, which brings great challenges to the plume particle parameter testing. , At present, the collection method is mainly used to obtain the engine plume particles, but the efficiency of this method for collecting particles is limited, and the error of the cold state test after collection is larger than the real high temperature state. At present, there is no effective online test method to evaluate the solid rocket. Engine plume smoke particle parameters.

Utility model content

One of the purposes of the present utility model is to provide a solid rocket motor plume smoke particle testing device, by measuring the diffracted light energy distribution and attenuation degree of different wavelength lasers after passing through the plume to be measured, based on the established smoke particle inversion algorithm Obtain the solid rocket motor plume smoke particle parameters, and then evaluate the solid rocket motor plume smoke particle characteristic signal.

The utility model provides a solid rocket motor plume smoke particle testing device, which has the following characteristics: a laser light source part is located on one side of the engine plume and is used to generate incident lasers of different wavelengths; a laser modulation part is located on the engine plume Between the flow and the laser light source part, it is used to receive the incident laser, modulate the spot size of the incident laser, the beam expansion angle, and the laser spatial parameters of the effective irradiation measurement area; the laser receiving part, located on the other side of the engine plume, the laser receiving part It is used to collect and receive the transmitted laser light of different wavelengths after the plume to be measured, and split it into two beams of first beam and second beam through the semi-transparent mirror; the laser diffraction detection part receives the first beam and is used for Detecting the diffracted light energy distribution of the first beam; a laser attenuation detection part, which receives the second beam and then irradiates the grating and then divides it into multiple sub-lasers according to wavelength; and a particle testing processing part for controlling the laser light source part, wherein the particle testing processing part and the The laser diffraction detection part and the laser attenuation detection part are respectively connected in communication to process, save and display the parameters of the solid rocket motor plume smoke particles.

In the solid rocket motor plume smoke particle testing device provided by the utility model, it can also have the following characteristics: wherein, the laser light source part includes a laser controller, a plurality of lasers, a fiber coupler, a fiber collimator, and a laser controller. It is connected with multiple lasers respectively to control multiple lasers with different wavelengths to generate laser light. The laser light generated by the laser is output to the fiber coupler through the fiber. The fiber coupler receives the laser light generated by the laser and couples the laser light to the output fiber. The coupler is connected to the collimator through the output fiber.

In addition, the solid rocket motor plume smoke particle testing device provided by the present utility model may also have the following characteristics: wherein the laser modulation part includes a Gaussian lens and a diaphragm, and the laser modulation part receives the incident laser light emitted by the laser light source part, By setting the position parameters of the Gaussian lens and diaphragm, the spot size of the incident laser, the beam expansion angle, and the laser space parameters of the effective irradiation measurement area are modulated, and the incident laser is modulated into a beam of converging irradiation plumes in the measurement area and positioned in the Gaussian beam. The Gaussian laser beam in the Rayleigh zone, thereby controlling the position and size of the effective irradiation measurement area, so that the measurement results characterize the object can be controlled.

In addition, the solid rocket motor plume smoke particle testing device provided by the present utility model may also have the following characteristics: wherein, the laser receiving part includes a band-pass filter, a semi-transparent and semi-reflective mirror, a condenser and a Optical lens, fiber coupler, bandpass filter After filtering the solid rocket engine exhaust plume radiation signal, the laser receiving part splits the Gaussian laser into a first beam and a second beam through a half mirror, and the first beam is output. After reaching the laser diffraction detection part, the second beam is converged by the condenser lens into the fiber coupler, and output to the laser attenuation detection part to obtain the transmitted laser diffraction light energy distribution and intensity synchronously. The inversion algorithm simultaneously obtains particle size measurements for different particle ranges.

In addition, the solid rocket motor plume smoke particle testing device provided by the present utility model may also have the following characteristics: wherein, the laser diffraction detection part includes a narrow-band filter, a plane detector and a laser diffraction processor arranged in sequence, and the laser The diffraction detection part is located on one side of the laser receiving part, the narrow-band filter controls the wavelength of the first beam, and the plane detector receives the first beam and performs photoelectric conversion, which can be composed of dozens of concentric semi-circle detectors or sector-shaped rings , or a photodetector array, output to the laser diffraction processor, the laser diffraction processor is connected with the plane detector through a cable, the electrical signal is converted into a digital signal, and the transmitted laser diffraction light energy distribution is obtained.

In addition, the solid rocket motor plume smoke particle testing device provided by the present invention may also have the following characteristics: wherein the laser attenuation detection part includes a collimator, a grating, a plurality of photodetectors and a laser attenuation processor, The collimator and the fiber coupler are connected by optical fibers, and the collimated laser output by the laser receiving part after collimating the fiber laser is irradiated on the grating. After receiving multiple split laser beams, the optical signals are converted into electrical signals and output to the laser attenuation processor through the cable. The laser attenuation processor collects the electrical signals output by multiple photodetectors and converts the electrical signals into digital signals, thereby obtaining different Wavelength transmitted laser intensity.

The function and effect of the utility model

The utility model relates to the solid rocket motor plume smoke particle testing device, which has the following functions and effects:

(1) The utility model obtains the particle parameters under the real high temperature state of the engine plume based on the established smoke particle inversion algorithm by measuring the diffracted light energy distribution and attenuation degree of different wavelength lasers through the plume to be measured, and realizes the solid rocket motor On-line test of plume smoke particles to evaluate the characteristic signal of solid rocket motor plume smoke particles.

(2) In the present invention, the laser modulation part adopts a Gaussian lens and a diaphragm. By setting parameters such as the position and focal length of the Gaussian lens and the diaphragm, the laser space parameters such as the spot size, beam expansion angle, and effective irradiation measurement area of the incident laser are modulated. , modulate the incident laser into a convergent Gaussian beam to illuminate the plume measurement area, and locate the effective illumination measurement area in the Rayleigh area of the Gaussian beam, so as to realize the control and adjustment of the effective illumination measurement area, so as to achieve both the engine plume The average measurement in a larger space can also realize local measurement in a small space, so as to obtain the effect of the spatial distribution of particle parameters within the plume space.

(3) The utility model splits the transmission into two beams of light through the laser receiving part, one of which is converged by the condenser lens into the fiber coupler and outputs the fiber laser from the fiber to the laser attenuation detection part, and the other beam is a space laser , the output irradiates the laser diffraction detection part, so as to obtain the distribution and intensity of the transmitted laser diffraction light energy synchronously, so as to obtain the particle size measurement of different particle ranges based on the extinction spectrum particle inversion algorithm and the laser diffraction particle inversion algorithm synchronously, and comprehensively form the final test As a result, the measurement range of particle size is effectively widened and the measurement accuracy is improved.

(4) The selection of the laser wavelength and intensity of the multiple lasers of the laser light source part of the present invention, the wavelength range of the bandpass filter of the laser receiving part, the wavelength of the narrowband filter of the laser diffraction detection part and the grating parameters of the laser attenuation detection part need to be combined with the engine plume The parameters such as particle size parameter range, particle concentration parameter concentration and plume radiation characteristics are selected and determined, which avoids the influence of high-temperature plume radiation on photoelectric detection and effectively improves the test accuracy.

Description of drawings

1 is a schematic diagram of a solid rocket motor plume smoke particle testing device in an embodiment;

Fig. 2 is the principle schematic diagram of the solid rocket motor plume smoke particle testing method in the embodiment;

Fig. 3 is the schematic diagram of the laser diffraction detection part in the embodiment;

FIG. 4 is a schematic diagram of the laser diffraction light energy distribution obtained in the example.

Detailed ways

In order to make it easier to understand the technical means, creative features, goals and effects realized by the present invention, the following embodiments describe a solid rocket motor plume smoke particle testing device of the present invention in detail with reference to the accompanying drawings.

Example

As shown in FIG. 1 , this embodiment provides a solid rocket motor plume smoke particle testing device, which includes a laser light source part 2 , a laser modulation part 3 , a laser receiving part 4 , a laser diffraction detection part 5 , and a laser attenuation detection part part 6 , particle test processing part 7 , cables 71 , 72 , 73 and optical fibers 28 , 26 , 47 .

The solid rocket motor plume smoke particle testing device is used for testing the solid rocket motor plume smoke particles, and is arranged in the areas on both sides of the exhaust plume 12 of the engine 11 to be tested.

Among them, the laser light source part 2 is located on the side of the engine plume 12, and is used to generate incident laser light 20 of different wavelengths.

The laser modulation part 3 is located between the engine plume 12 and the laser light source part 2, and is used for receiving the incident laser light 20 emitted by the laser light source part 2, and modulating the spot size of the incident laser light 20, the beam expansion angle, the effective irradiation measurement area and other laser spaces parameter, output Gaussian laser beam 30 .

The laser receiving part 4 is located on the other side of the engine plume 12 , and is used for collecting and receiving the transmitted laser light 30 of different wavelengths after the plume to be measured, and splitting into two beams 45 and 46 .

The laser diffraction detection part 5 receives a beam of transmitted light 45 for detecting the diffracted light energy distribution of the received transmitted laser light 45 .

The laser attenuation detection part 6 receives another beam of transmitted light 46 for detecting the received transmitted laser light intensity of different wavelengths.

The particle testing processing part 7 is connected to the laser diffraction detection part 5 and the laser attenuation detection part 6 respectively, and is used to control the laser light source part 2 and process, save and display the parameters of the solid rocket motor plume smoke particles.

The laser light source unit 2 includes a laser controller 21 , lasers 22 , 23 , and 24 , a fiber coupler 27 , a fiber collimator 29 , a cable 25 , and optical fibers 26 and 28 .

The laser controller 21 and the lasers 22, 23, and 24 are connected in parallel through cables 25, respectively, and are used to control the lasers 22, 23, and 24 of different wavelengths to generate laser light. The laser controller 21 is controlled by the particle test processing unit 7 through the control signal cable. 71 control, the laser light generated by the laser 21 is output to the fiber coupler 27 through the fiber 26, and the fiber coupler 27 receives the laser light generated by the lasers 22, 23, and 24 and couples the laser light to the output fiber 28. The fiber coupler 27 passes the output fiber 28 is connected to a collimator 29, and the collimator 29 outputs the laser light 20.

The laser modulation part 3 includes a Gaussian lens 31 and a diaphragm 32. The laser modulation part 3 receives the incident laser light 20 emitted by the laser light source part 2, and modulates the spot of the incident laser light 20 by setting parameters such as the position and focal length of the Gaussian lens 31 and the diaphragm 32. The laser space parameters such as size, beam expansion angle, effective irradiation measurement area, etc., modulate the incident laser into a convergent Gaussian laser beam 30 to irradiate the plume 12, and locate the effective irradiation measurement area 13 in the Rayleigh region of the Gaussian beam, thereby controlling The location and size of the effective illumination measurement area, so that the measurement results characterizing the object can be controlled.

The effective irradiation measurement area 13 of the engine plume particle test is determined by parameters such as the position and focal length of the Gaussian lens 31 and the diaphragm 32 of the laser modulation unit 3. The effective irradiation measurement area 13 can be controlled and adjusted by adjusting the Rayleigh area of the Gaussian beam, either The average measurement of the large space of the engine plume can be realized, and the local measurement of the small space can be realized, so as to obtain the spatial distribution of particle parameters in the plume space.

The laser receiver 4 includes a bandpass filter 41 , a half mirror 42 , a condenser lens 43 , and an optical fiber coupler 44 arranged in sequence along the incident optical path.

After the Gaussian incident laser 30 generated and modulated by the laser light source part 2 and the laser modulation part 3 passes through the area to be measured by the plume, the transmitted laser light enters the laser receiving part 4 , and the radiation from the exhaust plume 12 of the solid rocket motor 11 is filtered by the bandpass filter 41 The signal is then split into two beams of light 45 and 46 by the half mirror 42. One beam of light 46 is condensed into the fiber coupler 44 through the condenser lens 43, and the fiber laser is output from the fiber 47 to the laser attenuation detection part 6, The other beam is a space laser 45, which is output to the irradiating laser diffraction detection part 5, and the transmitted laser diffraction light energy distribution and intensity are obtained synchronously, so that the particle inversion algorithm based on the extinction spectrum and the laser diffraction particle inversion algorithm can be synchronized to obtain different particle ranges. The particle size measurement can comprehensively form the final test result, which effectively widens the particle size measurement range and improves the measurement accuracy.

The laser diffraction detection part 5 includes a narrowband filter 51 , a plane detector 52 and a laser diffraction processor 53 arranged in sequence, and the laser diffraction detection part 5 is located on one side of the laser receiving part 4 .

As shown in FIG. 3 , the laser diffraction detection unit 5 receives a beam of spatial laser light 45 irradiated by the laser receiving unit 4 . This beam of spatial laser light 45 is a diffraction halo formed by the diffraction of particles in the area to be measured 13 . 45 is controlled by the wavelength at the selected wavelength, received by the plane detector 52 and photoelectrically converted, which can be composed of dozens of concentric semi-circular ring detectors, or composed of fan-shaped rings, or composed of photodetector arrays, and output to laser diffraction In the processor 53, the laser diffraction processor 53 is connected with the plane detector 52 through the cable 54, converts the electrical signal into a digital signal, obtains the transmitted laser diffraction light energy distribution, and outputs it to the particle test processing part 7 through the digital signal communication cable 72. .

The laser attenuation detection unit 6 includes a collimator 61 , a grating 63 , a plurality of photodetectors 65 , 66 , 67 and a laser attenuation processor 69 .

The collimator 61 is connected to the fiber coupler 44 of the laser receiver 4 through the optical fiber 47 , collimates a beam of fiber laser output from the laser receiver 4 to obtain laser light 62 and then irradiates the grating 63 .

After receiving the laser light 62, the grating 63 divides it into multi-beam sub-laser 64 according to the wavelength; a plurality of photodetectors 65, 66, 67 respectively receive the multi-beam sub-laser 64 and then convert the optical signal into an electrical signal and output it to the laser attenuation processor 69 through the cable 68 In the process, the laser attenuation processor 69 collects the electrical signals output by the detectors 65 , 66 and 67 and converts the electrical signals into digital signals, obtains the transmitted laser intensities of different wavelengths, and outputs them to the particle testing processing unit 7 via the digital signal communication cable 73 .

The particle testing and processing unit 7 is connected to the laser controller 21 through a control signal cable 71 to control the generation of incident laser light, and is connected to the laser diffraction processor 53 and the laser attenuation processor 69 through digital signal communication cables 72 and 73, respectively, to obtain transmission laser diffraction. The light energy distribution and the transmitted laser intensity of different wavelengths, the particle test processing unit 7 obtains the solid rocket motor plume smoke particle parameters based on the established smoke particle inversion algorithm, processes, saves and displays the solid rocket motor plume smoke particle parameters, and then evaluates Characteristic signal of solid rocket motor plume smoke particles.

Further, the laser wavelengths and intensities of the plurality of lasers 22, 23, and 24 in the laser light source unit 2, the wavelength range of the bandpass filter 41 of the laser receiving unit 4, the wavelength of the narrowband filter 51 of the laser diffraction detection unit 5, and the grating of the laser attenuation detection unit 6 The selection of 63 parameters needs to be determined in combination with parameters such as the particle size parameter range, particle concentration parameter concentration and plume radiation characteristics of the engine plume 12. Usually, in order to avoid the influence of the plume radiation, the laser light source part 2 has multiple lasers 22, 23, The laser wavelength of 24 is selected in the blue-violet wavelength range.

Further, the positions of the plurality of photodetectors 65 , 66 , and 67 in the laser attenuation detection unit 6 are set according to the light splitting of the grating 63 , so as to obtain the transmitted laser light intensity of different wavelengths correspondingly.

This embodiment also provides a method for testing solid rocket motor plume smoke particles, which is obtained by measuring the diffracted light energy distribution and attenuation degree of different wavelengths of laser light after passing through the plume to be measured, and based on the established smoke particle inversion algorithm. Solid rocket motor plume smoke particle parameters, and then evaluate the solid rocket motor plume smoke particle characteristic signal.

The solid rocket motor plume smoke particle testing method utilizes the solid rocket motor plume smoke particle testing device in the embodiment to test the solid rocket motor plume smoke particles as follows:

S1: Install the solid rocket motor plume smoke particle testing device on both sides of the plume;

S2: Turn on the laser controller, drive the laser to generate laser light, turn on the laser diffraction detection part and the laser attenuation detection part, respectively record, process and save the initial laser light energy distribution and intensity received by the detection;

S3: Start the test, open the laser diffraction detection part and the laser attenuation detection part at the same time, respectively record, process and save the transmitted laser diffraction light energy distribution and intensity received by the detection;

S4: Based on the established smoke particle inversion algorithm to obtain the solid rocket motor plume smoke particle parameters;

S5: Evaluate the characteristic signal of solid rocket motor plume smoke particles.

Further, the solid rocket motor plume smoke particle testing method uses different detection data for different particle size ranges, and obtains the solid rocket motor plume smoke particle parameters based on different smoke particle inversion algorithms:

For the particle size range of 0.06-10 μm, select the laser attenuation degree data of different wavelengths obtained by the laser attenuation detection part 6, and obtain the particle parameters based on the extinction spectrum particle inversion algorithm;

For the particle size range above 10 μm, the transmitted laser diffraction light energy distribution obtained by the laser diffraction detection part 5 is selected, and the particle parameters are obtained based on the laser diffraction particle inversion algorithm.

In this example, the characteristic signal of the solid rocket motor plume smoke particle is evaluated by combining the particle size range of 0.06-10 μm and the particle size range of 10 μm or more, using two algorithms for simultaneous testing and processing, and comprehensively forming the final test result.

Further, the above-mentioned extinction spectrum particle inversion algorithm is based on the fact that the attenuation degrees of different wavelengths of laser light after passing through the plume to be measured conform to Bill Lambert's law.

As shown in Figure 2, the relationship between the attenuation degrees of different wavelengths of laser light after passing through the plume to be measured is as follows:

The subscript λ _i represents different wavelengths; T is the transmittance, which is the ratio of the transmitted light intensity I to the initial light intensity I ₀ ; Q _ext is the proportionality constant, which is related to the laser wavelength, smoke particle parameters, etc.; L is the plume thickness; N _D is the concentration of smoke particles, and f(D) is the particle size distribution function of smoke particles. Thus, the plume transmittance T is obtained by experimentally measuring the laser transmission light intensity I and the initial light intensity I ₀ of different wavelengths. Therefore, the linear equations are obtained by experimentally measuring the attenuation of lasers of different wavelengths after passing through the plume to be measured:

E=Af

消光系数矩阵A中各个元素可表示为A_ij＝-3LN_Dc_jQ_ext(λ_i,m,D)/2D_j,(i＝1,2,…S；j＝1,2,…,N)，其中，N为粒径分档数，c_j为数值积分系数。f＝[f(D₁),f(D₂),…,f(D_j)]^T为待测颗粒系粒径分布函数。

Each element in the extinction coefficient matrix A can be expressed as A _ij =-3LN _D c _j Q _ext (λ _i ,m,D)/2D _j ,(i=1,2,...S; j=1,2,..., N), where N is the number of particle size bins, and c _j is the numerical integration coefficient. f=[f(D ₁ ), f(D ₂ ), . . . , f(D _j )] ^T is the particle size distribution function of the particle system to be measured.

Further, the above-mentioned laser diffraction particle inversion algorithm is obtained according to Fraunhofer diffraction theory and Barbinet's principle. The expression of the diffracted light intensity distribution I of spherical particles under parallel light irradiation is:

I ₀ is the incident light intensity of parallel light, f is the focal length of the Fourier lens, λ is the wavelength, D is the particle diameter, X=πDsinθ/λ, θ is the diffraction angle, and J ₁ is the first-order Bessel function. According to the characteristics of the Bessel function, when X=0, 2J ₁ (X)/X=1, in the spherical coordinate system (r, θ, φ), the scattering amplitudes S ₁ and S of spherical particles under the irradiation of Gaussian beam ₂ can be expressed as:

和

是光形系数，

和

是散射角函数，n与m是Legendre多项式级数，i为复数表达。颗粒的散射光强分布为：a _n and b _n are the m scattering coefficients,

and

is the shape coefficient,

and

is the scattering angle function, n and m are Legendre polynomial series, and i is a complex expression. The scattered light intensity distribution of the particles is:

In the particle diffraction problem under Gaussian beam irradiation, the light intensity of the incident beam is non-uniformly distributed, but the Fraunhofer diffraction theory and Barbinet's principle still hold, so the diffraction light energy of particles under Gaussian beam irradiation can also be deduced according to the above two principles The distribution is obtained by the plane detector of the laser diffraction detection section:

The subscript n represents the nth ring, S is the radius, Sn _,1 is the inner radius of the nth ring, Sn _,2 is the outer radius of the nth ring, and the corresponding diffraction angles are θ _n,1 and θ _n,2 , n=1,2,...,M, where M is the total number of rings of the multi-element photodetector.

The laser diffraction light energy distribution obtained by the typical embodiment is shown in FIG. 4 .

When the focal length f of the Fourier lens is much larger than the maximum radius of the photodetector, that is, the diffraction angle is small, the light energy distribution can be simplified;

Xn _,1 =πDθn _,1 /λ, Xn _,2 =πDθn _,2 /λ, D and λ are distributed as the particle size of the particle and the wavelength of the incident beam. After the above formula is integrated, the diffracted light energy on the nth ring can be obtained as:

The above formula is based on the case where there is only one particle in the measurement area. If there is a particle system composed of many particles of different sizes in the measurement area, or called a particle group, and assuming that the number of particles with a diameter of Di is Ni, the following table _i represents the particle size classification, _i =1, 2, …, K. At this time, the total diffracted light energy on the nth ring is:

The total diffracted light energy can be expressed in matrix form:

E=TW

E=(e ₁ ,e ₁ ,...,e _M ) ^T is the column vector of light energy distribution, W=(W ₁ ,W ₁ ,...,W _M ) ^T is the column vector of particle size distribution, and

is the light energy distribution coefficient matrix, the physical meaning of each element t _i,n in the matrix is the light energy diffracted by the particle with diameter D _i per unit weight and falling on the nth ring of the photodetector. The corresponding relationship between the laser diffraction light energy distribution and the particle size distribution is thus established. The light energy distribution column vector E can be measured by a plane detector through experiments, and the light energy distribution coefficient matrix T can be calculated by diffraction theory, and then the particle size distribution, particle number distribution, or particle volume distribution can be obtained. . On this basis, by combining the lasers of the laser light source part with different wavelengths and the narrow-band filters of the laser diffraction detection part, the particle laser diffraction light energy distribution of multiple wavelengths can be obtained. Further improve the test accuracy.

Action and effect of the embodiment

The device and method for testing solid rocket motor plume smoke particles provided in this embodiment have the following functions and effects:

(1) In this embodiment, by measuring the diffracted light energy distribution and attenuation degree of different wavelengths of laser light after passing through the plume to be measured, and based on the established smoke particle inversion algorithm, the particle parameters of the engine plume under the real high temperature state are obtained, and the solid rocket motor is realized. On-line test of plume smoke particles to evaluate the characteristic signal of solid rocket motor plume smoke particles.

(2) The laser modulation part of this embodiment adopts a Gaussian lens and a diaphragm. By setting parameters such as the position and focal length of the Gaussian lens and the diaphragm, the laser space parameters such as the spot size, beam expansion angle, and effective irradiation measurement area of the incident laser are modulated. The incident laser is modulated into a concentrated Gaussian beam to irradiate the plume measurement area, and the effective irradiation measurement area is positioned in the Rayleigh area of the Gaussian beam, so as to realize the control and adjustment of the effective irradiation measurement area, so that the engine plume comparison can be achieved. The average measurement in a large space can also realize local measurement in a small space, so as to obtain the effect of the spatial distribution of particle parameters within the plume space.

(3) In this embodiment, the transmitted beam is split into two beams of light by the laser receiving part, one of which is condensed into the fiber coupler through the condenser lens, and the fiber laser is output from the fiber to the laser attenuation detection part, and the other beam is a space laser , the output irradiates the laser diffraction detection part, so as to obtain the distribution and intensity of the transmitted laser diffraction light energy synchronously, so as to obtain the particle size measurement of different particle ranges based on the extinction spectrum particle inversion algorithm and the laser diffraction particle inversion algorithm synchronously, and comprehensively form the final test As a result, the measurement range of particle size is effectively widened and the measurement accuracy is improved.

(4) The selection of the laser wavelengths and intensities of the multiple lasers of the laser light source part, the wavelength range of the bandpass filter of the laser receiving part, the wavelength of the narrowband filter of the laser diffraction detection part, and the grating parameters of the laser attenuation detection part in this embodiment need to be combined with the engine plume The parameters such as particle size parameter range, particle concentration parameter concentration and plume radiation characteristics are selected and determined, which avoids the influence of high-temperature plume radiation on photoelectric detection and effectively improves the test accuracy.

The above-mentioned embodiments are preferred cases of the present invention, and are not intended to limit the protection scope of the present invention.

Those skilled in the art of the present invention can make various modifications or supplements to the described specific embodiments or replace them in similar ways, but will not deviate from the spirit of the present invention or go beyond the appended claims the defined range.

Claims (8)

1. a solid rocket motor plume smoke particle testing device, for measuring the attenuation degree of different wavelength lasers after the engine plume to be measured, is characterized in that, comprises: a laser light source part, located on one side of the engine plume, for generating incident laser light of different wavelengths; a laser modulation part, located between the engine plume and the laser light source part, for receiving the incident laser light, and modulating the spot size of the incident laser light, the beam expansion angle, and the laser space parameters of the effective irradiation measurement area; The laser receiving part is located on the other side of the engine plume, the laser receiving part is used to collect and receive the transmitted laser light of different wavelengths after the plume to be measured, and split it into a first beam through a half mirror , the second beam two beams; a laser diffraction detection part for receiving the first light beam and for detecting the diffracted light energy distribution of the first light beam; a laser attenuation detection part, which receives the second light beam, irradiates the grating, and then divides it into a plurality of sub-lasers according to wavelength; and a particle test processing part for controlling the laser light source part, Wherein, the particle testing processing part is connected in communication with the laser diffraction detection part and the laser attenuation detection part respectively, and is used for processing, saving and displaying the parameters of the solid rocket motor plume smoke particles. 2. solid rocket motor plume smoke particle testing device according to claim 1, is characterized in that: Wherein, the laser light source part includes a laser controller, a plurality of lasers, a fiber coupler, and a fiber collimator, The laser controller is respectively connected with a plurality of the lasers, and is used for controlling the plurality of lasers with different wavelengths to generate laser light, The laser light generated by the laser is output to the fiber coupler through the fiber, The fiber coupler receives laser light generated by the laser and couples the laser light into an output fiber, and the fiber coupler is connected to the collimator through the output fiber. 3. solid rocket motor plume smoke particle testing device according to claim 1, is characterized in that: Wherein, the laser modulation part includes a Gaussian lens and a diaphragm, The laser modulation part receives the incident laser light emitted by the laser light source part, and modulates the spot size and beam expansion angle of the incident laser light by setting the position parameters of the Gaussian lens and the diaphragm to effectively irradiate the laser light in the measurement area. The spatial parameter modulates the incident laser light into a Gaussian laser beam located in the measurement area in a converged illumination plume and positioned in the Rayleigh region of the Gaussian beam, thereby controlling the position and size of the effective illumination measurement area, and controlling the measurement result to characterize the object. 4. solid rocket motor plume smoke particle testing device according to claim 3, is characterized in that: Wherein, the laser receiving part includes a band-pass filter, a half mirror, a condenser lens, and an optical fiber coupler arranged in sequence along the incident optical path, After the bandpass filter filters the solid rocket engine exhaust plume radiation signal, the laser receiving part splits the Gaussian laser into the first beam and the second beam through the half mirror , the first light beam is output to the laser diffraction detection part, The second light beam is condensed into the optical fiber coupler through the condenser lens, and output to the laser attenuation detection part, The distribution and intensity of the transmitted laser diffraction light energy are obtained synchronously, so that the particle size measurement of different particle ranges can be obtained synchronously based on the extinction spectrum particle inversion algorithm and the laser diffraction particle inversion algorithm. 5. solid rocket motor plume smoke particle testing device according to claim 4, is characterized in that: Wherein, the laser diffraction detection part includes a narrow-band filter, a plane detector and a laser diffraction processor arranged in sequence, and the laser diffraction detection part is located on one side of the laser receiving part, The plane detector receives the first light beam, performs photoelectric conversion, and outputs it to the laser diffraction processor. The laser diffraction processor is connected to the plane detector through a cable, and converts electrical signals into digital signals. The transmitted laser diffraction light energy distribution is obtained. 6. solid rocket motor plume smoke particle testing device according to claim 4, is characterized in that: Wherein, the laser attenuation detection part includes a collimator, a grating, a plurality of photodetectors and a laser attenuation processor, The collimator is connected with the fiber coupler through an optical fiber, and the collimated laser light after the collimated fiber laser output from the laser receiving part is irradiated on the grating, After receiving the collimated laser light, the grating divides it into multiple sub-laser beams according to wavelength. 7. solid rocket motor plume smoke particle testing device according to claim 6, is characterized in that: Wherein, a plurality of photodetectors respectively receive multiple beams of the sub-lasers and convert optical signals into electrical signals and output them to the laser attenuation processor through cables, The laser attenuation processor collects electrical signals output by a plurality of the photodetectors and converts the electrical signals into digital signals, thereby obtaining transmitted laser intensities of different wavelengths. 8. solid rocket motor plume smoke particle testing device according to claim 5, is characterized in that: Wherein, the narrowband filter controls the wavelength of the first light beam.

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