CN211374056U - Solid rocket engine plume smoke particle testing device - Google Patents
Solid rocket engine plume smoke particle testing device Download PDFInfo
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- CN211374056U CN211374056U CN202020323625.2U CN202020323625U CN211374056U CN 211374056 U CN211374056 U CN 211374056U CN 202020323625 U CN202020323625 U CN 202020323625U CN 211374056 U CN211374056 U CN 211374056U
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Abstract
According to the utility model discloses a solid rocket engine plume smoke particle testing device, including laser modulation portion, be located between engine plume and the laser light source portion, the laser space parameter of modulation incident laser's facula size, the angle of expanding the beam, effective irradiation measuring area; the laser-receiving part is positioned at the other side of the engine plume and is used for converging and receiving the transmission laser with different wavelengths after passing through the plume to be detected and splitting the transmission laser into a first light beam and a second light beam through the semi-transparent and semi-reflective mirror; the laser diffraction detection part receives the first light beam and is used for detecting the light energy distribution of the first light beam diffraction; the laser attenuation detection part receives the second light beam, irradiates the grating and then divides the second light beam into a plurality of laser beams according to the wavelength; the particle testing and processing part is used for controlling the laser light source part, is respectively in communication connection with the laser diffraction detection part and the laser attenuation detection part and is used for processing and displaying plume smoke particle parameters of the solid rocket engine.
Description
Technical Field
The utility model belongs to the technical field of space flight power, a solid rocket engine plume smoke particle testing arrangement is related to.
Background
The solid rocket engine is widely applied to the field of aerospace power with high reliability and good performance. With the rapid development of military and aerospace, the requirements on solid rocket engines are more and more, the development of the propellant formula is not to seek higher energy on one side, but gradually turns into the pursuit of comprehensive indexes such as low characteristic signals and the like while the energy performance is ensured. The exhaust plume of the solid rocket engine is a combustion product discharged from the spray pipe at a supersonic speed, and the combustion product can be further diffused and expanded at the outlet of the spray pipe to form a luminous and heating plume flow field, and the interaction of the luminous and heating plume flow field and the surrounding environment can form various effects such as smoke, radiation, detection or guidance signal attenuation and the like, and the effects are collectively called as characteristic signals of the exhaust plume.
The engine exhaust plume can generate strong smoke, and the smoke contains a large amount of high-temperature liquid and solid particles, so that the problems of corrosion and contamination to the body of the carrier, interference to carrier communication, signal attenuation and the like can be caused. Engine plume particle parameters are important indicators of these adverse effects. However, the parameter particle diameters of the plume particles are in multiple orders (from nanometer to millimeter orders), the particle concentration is also in a large range, the temperature is high, the radiation is strong, and great challenges are brought to the parameter test of the plume particles.
SUMMERY OF THE UTILITY MODEL
One of the purposes of the utility model is to provide a solid rocket engine plume smoke particle testing arrangement, through measuring diffraction light energy distribution and the decay degree of different wavelength lasers behind the plume that awaits measuring, obtain solid rocket engine plume smoke particle parameter based on the flue gas particle inversion algorithm of establishing, and then aassessment solid rocket engine plume smoke particle characteristic signal.
The utility model provides a solid rocket engine plume smoke particle testing device, which is characterized in that the device comprises a laser light source part, a laser emission part and a smoke particle testing part, wherein the laser light source part is positioned at one side of the engine plume and is used for generating incident laser with different wavelengths; the laser modulation part is positioned between the engine plume and the laser light source part and is used for receiving incident laser and modulating the spot size, the beam expansion angle and the laser space parameters of the effective irradiation measuring area of the incident laser; the laser-receiving part is positioned at the other side of the engine plume and is used for converging and receiving the transmission laser with different wavelengths after passing through the plume to be detected and splitting the transmission laser into a first light beam and a second light beam through the semi-transparent and semi-reflective mirror; the laser diffraction detection part receives the first light beam and is used for detecting the light energy distribution diffracted by the first light beam; the laser attenuation detection part receives the second light beam, irradiates the grating and then divides the second light beam into a plurality of laser beams according to the wavelength; and the particle testing processing part is used for controlling the laser light source part, wherein the particle testing processing part is respectively in communication connection with the laser diffraction detection part and the laser attenuation detection part and is used for processing, storing and displaying parameters of plume smoke particles of the solid rocket engine.
The utility model provides an in the solid rocket engine plume smoke particle testing arrangement, can also have such characteristic: the laser light source part comprises a laser controller, a plurality of lasers, an optical fiber coupler and an optical fiber collimator, wherein the laser controller is respectively connected with the lasers and used for controlling the lasers with different wavelengths to generate laser, the laser generated by the lasers is output to the optical fiber coupler through the optical fiber, the optical fiber coupler receives the laser generated by the lasers and couples the laser to an output optical fiber, and the optical fiber coupler is connected with the collimator through the output optical fiber.
In addition, in the utility model provides a solid rocket engine plume smoke particle testing arrangement, can also have such characteristic: the laser modulation part comprises a Gaussian lens and a diaphragm, receives incident laser emitted by the laser light source part, modulates the spot size, the beam expansion angle and the laser space parameter of the incident laser by setting the position parameters of the Gaussian lens and the diaphragm, modulates the incident laser into a converged Gaussian laser beam which irradiates a measuring area in a plume and is positioned in a Gaussian beam Rayleigh area, thereby controlling the position and the size of the effective irradiation measuring area and controlling a measuring result representation object.
In addition, in the utility model provides a solid rocket engine plume smoke particle testing arrangement, can also have such characteristic: the laser receiving part comprises a band-pass filter, a semi-transparent semi-reflecting mirror, a condensing lens and an optical fiber coupler which are sequentially arranged along an incident light path, after the band-pass filter filters exhaust plume radiation signals of the solid rocket engine, the laser receiving part splits Gaussian laser into a first light beam and a second light beam through the semi-transparent semi-reflecting mirror, the first light beam is output to the laser diffraction detection part, the second light beam is converged by the condensing lens to enter the optical fiber coupler and is output to the laser attenuation detection part, and the distribution and the intensity of transmitted laser diffraction light energy are synchronously obtained, so that particle size measurement in different particle ranges is synchronously obtained based on an extinction spectrum particle inversion algorithm and a laser diffraction particle inversion algorithm.
In addition, in the utility model provides a solid rocket engine plume smoke particle testing arrangement, can also have such characteristic: wherein, laser diffraction detection portion is including the narrowband filter that sets gradually, plane detector and laser diffraction treater, laser diffraction detection position is located the one side of laser diffraction portion, the wavelength of the first light beam of narrowband filter control, plane detector receives first light beam and carries out photoelectric conversion, can be tens of concentric semicircle ring detector component, perhaps fan-shaped ring is constituteed, perhaps the photoelectric detector array is constituteed, export to the laser diffraction treater in, the laser diffraction treater passes through cable junction with plane detector, change the signal of telecommunication into digital signal, it can distribute to obtain transmission laser diffraction luminous energy.
In addition, in the utility model provides a solid rocket engine plume smoke particle testing arrangement, can also have such characteristic: the laser attenuation detection part comprises a collimator, a grating, a plurality of photoelectric detectors and a laser attenuation processor, the collimator is connected with the optical fiber coupler through an optical fiber, collimated laser output by the laser receiving part after being collimated by the optical fiber laser irradiates the grating, the grating receives the collimated laser and then divides the collimated laser into a plurality of beams according to the wavelength, the photoelectric detectors respectively receive the beams of the collimated laser and then convert optical signals into electric signals, the electric signals are output to the laser attenuation processor through cables, the laser attenuation processor collects the electric signals output by the photoelectric detectors and converts the electric signals into digital signals, and therefore the transmission laser intensity of different wavelengths is obtained.
Action and effect of the utility model
The utility model relates to a solid rocket engine plume smoke particle testing arrangement, the effect that has and the effect have:
(1) the utility model discloses a measure diffraction light energy distribution and attenuation degree of different wavelength laser behind the plume that awaits measuring, obtain particle parameter under the real high temperature state of engine plume based on the cigarette granule inversion algorithm of establishing, realize solid rocket engine plume cigarette granule on-line measuring, and then aassessment solid rocket engine plume cigarette granule characteristic signal.
(2) The utility model discloses well laser modulation portion adopts gauss lens and diaphragm, through the position that sets up gauss lens and diaphragm, the isoparametric of focus, the facula size of modulation incident laser, the beam expanding angle, effectively shine laser space parameters such as measurement area, modulate incident laser into a branch of gauss light beam that assembles and shine plume measurement area, and will effectively shine measurement area location at the rayleigh district of gauss light beam, thereby realize effectively shining measurement area's control and adjustment, reach the average measurement that both can realize the great space of engine plume, can realize little space local measurement again, thereby obtain the effect of the spatial distribution condition of particle parameter in plume space range.
(3) The utility model discloses a laser receiver will transmit the beam splitting and become two bundles of light, one of them beam light assembles the entering fiber coupler and exports optic fibre laser to laser attenuation detection portion by optic fibre through condensing lens, another branch is space laser, laser diffraction detection portion is shone in the output, thereby obtain transmission laser diffraction light energy distribution and intensity in step, thereby obtain the particle diameter measurement of different granule scopes in step based on extinction spectrum granule inversion algorithm and laser diffraction granule inversion algorithm, synthesize and form final test result, the effectual granule particle diameter measurement scope of having widened, the measurement accuracy has been improved.
(4) The utility model discloses the selection of laser wavelength and intensity, laser receiving portion band-pass filter wavelength range, laser diffraction detection portion narrowband filter wavelength and laser attenuation detection portion grating parameter of a plurality of lasers of laser light source portion need combine engine plume particle diameter parameter scope, particle concentration parameter concentration and plume radiation characteristic isoparametric to select the affirmation, has avoided the influence of high temperature plume radiation to photoelectric detection, the effectual measuring accuracy that has improved.
Drawings
FIG. 1 is a schematic view of a solid rocket engine plume particle testing device in an embodiment;
FIG. 2 is a schematic diagram of a solid rocket engine plume particle testing method in accordance with an embodiment;
FIG. 3 is a schematic view of a laser diffraction detecting portion in the embodiment;
fig. 4 is a schematic diagram of laser diffraction light energy distribution obtained in the example.
Detailed Description
In order to make the technical means, creation features, achievement purpose and efficacy of the utility model easy to understand, the following embodiments are combined with the accompanying drawings to specifically illustrate the solid rocket engine plume particle testing device of the utility model.
Examples
As shown in fig. 1, the present embodiment provides a solid rocket engine plume particle testing device, which includes a laser light source unit 2, a laser modulation unit 3, a laser light receiving unit 4, a laser diffraction detection unit 5, a laser attenuation detection unit 6, a particle testing processing unit 7, cables 71, 72, 73, and optical fibers 28, 26, 47.
The solid rocket engine plume smoke particle testing device is used for testing solid rocket engine plume smoke particles and is arranged in the two side areas of the exhaust plume 12 of the engine 11 to be tested.
The laser light source 2 is located on the engine plume 12 side and generates incident laser light 20 with different wavelengths.
The laser modulation part 3 is positioned between the engine plume 12 and the laser light source part 2, and is used for receiving the incident laser 20 emitted by the laser light source part 2, modulating laser space parameters of the incident laser 20, such as spot size, beam expansion angle, effective irradiation measurement area, and the like, and outputting a gaussian laser beam 30.
The laser receiving part 4 is located at the other side of the engine plume 12, and is used for converging and receiving the transmission laser 30 with different wavelengths after passing through the plume to be measured, and splitting the beam into two beams of light 45 and 46.
The laser diffraction detecting unit 5 receives a beam of the transmitted light 45 and detects the distribution of the diffracted light energy of the received transmitted laser 45.
And the laser attenuation detection part 6 receives another beam of transmission light 46 and is used for detecting the intensity of the received transmission laser with different wavelengths.
The particle testing processing part 7 is respectively connected with the laser diffraction detection part 5 and the laser attenuation detection part 6 and is used for controlling the laser light source part 2 and processing, storing and displaying the parameters of the plume smoke of the solid rocket engine.
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 a cable 25, respectively, and are used for controlling the lasers 22, 23, and 24 with different wavelengths to generate laser light, the laser controller 21 is controlled by the particle testing processing unit 7 through a control signal cable 71, the laser light generated by the laser 21 is output to the optical fiber coupler 27 through the optical fiber 26, the optical fiber coupler 27 receives the laser light generated by the lasers 22, 23, and 24 and couples the laser light to the output optical fiber 28, the optical fiber coupler 27 is connected with the collimator 29 through the output optical fiber 28, and the collimator 29 outputs the laser light 20.
The laser modulation part 3 comprises a Gaussian lens 31 and a diaphragm 32, the laser modulation part 3 receives incident laser 20 emitted by the laser light source part 2, laser space parameters such as the spot size, the beam expansion angle and the effective irradiation measurement area of the incident laser 20 are modulated by setting parameters such as the positions and the focal lengths of the Gaussian lens 31 and the diaphragm 32, the incident laser is modulated into a converged Gaussian laser beam 30 to irradiate the plume 12, and the effective irradiation measurement area 13 is positioned in the Rayleigh area of the Gaussian beam, so that the position and the size of the effective irradiation measurement area are controlled, and the measurement result representation object can be controlled.
The effective irradiation measuring area 13 for the engine plume particle test is determined by parameters such as the positions, focal lengths and the like of the Gaussian lens 31 and the diaphragm 32 of the laser modulation part, and the effective irradiation measuring area 13 can be controlled and adjusted through the adjustment of the Rayleigh area of the Gaussian beam, so that the average measurement of a larger space of the engine plume can be realized, the local measurement of a small space can be realized, and the space distribution condition of particle parameters in the plume space range can be obtained.
The laser receiving section 4 includes a band pass filter 41, a half mirror 42, a condenser lens 43, and an optical fiber coupler 44, which are sequentially provided along an incident light path.
After the gaussian incident laser 30 generated and modulated by the laser source part 2 and the laser modulation part 3 passes through the region to be measured of the plume, the transmitted laser light enters the laser receiving part 4, the band-pass filter 41 filters the signal radiated by the exhaust plume 12 of the solid rocket engine 11, and then the beam is split into two beams of light 45 and 46 by the half mirror 42, one beam of light 46 is converged by the condenser lens 43 and enters the fiber coupler 44, and the fiber 47 outputs the fiber laser to the laser attenuation detecting part 6, the other beam is space laser 45, which is output to the irradiation laser diffraction detector 5 to synchronously obtain the energy distribution and intensity of the transmitted laser diffraction light, therefore, particle size measurement in different particle ranges is synchronously obtained based on the extinction spectrum particle inversion algorithm and the laser diffraction particle inversion algorithm, a final test result is comprehensively formed, the particle size measurement range is effectively widened, and the measurement precision is improved.
The laser diffraction detecting unit 5 includes a narrow band filter 51, a plane detector 52, and a laser diffraction processor 53, which are arranged in this order, and the laser diffraction detecting unit 5 is located on the side of the laser receiving unit 4.
As shown in fig. 3, the laser diffraction detection unit 5 receives a beam of spatial laser 45 irradiated by the laser reception unit 4, the beam of spatial laser 45 is a diffraction light ring formed by diffraction of particles in the region 13 to be measured, the spatial laser 45 is controlled at a selected wavelength by the narrow band filter 51, and is received by the plane detector 52 and is subjected to photoelectric conversion, and may be composed of tens of concentric semicircular detectors, or a sector ring, or a photodetector array, and is output to the laser diffraction processor 53, and the laser diffraction processor 53 is connected to the plane detector 52 by the cable 54, converts an electrical signal into a digital signal, obtains distribution of transmitted laser diffraction light energy, and outputs the distribution to the particle test processing unit 7 through the digital signal communication cable 72.
The laser attenuation detecting section 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/light receiving unit 4 via the optical fiber 47, and collimates one of the fiber lasers output from the laser/light receiving unit 4 to obtain a laser beam 62, which is then irradiated onto the grating 63.
The grating 63 receives the laser 62 and then divides the laser into a plurality of beams 64 according to the wavelength; the plurality of photodetectors 65, 66, 67 respectively receive the plurality of beams of laser light 64 and then convert the optical signals into electrical signals, and output the electrical signals to the laser attenuation processor 69 through the cable 68, and the laser attenuation processor 69 collects the electrical signals output by the detectors 65, 66, 67 and converts the electrical signals into digital signals, obtains the intensities of the transmitted laser light with different wavelengths, and outputs the digital signals to the particle testing processing part 7 through the digital signal communication cable 73.
The particle testing and processing part 7 is connected with the laser controller 21 through a control signal cable 71 to control the generation of incident laser, and is respectively connected with the laser diffraction processor 53 and the laser attenuation processor 69 through digital signal communication cables 72 and 73 to respectively obtain the distribution of transmitted laser diffraction light energy and the intensities of transmitted laser with different wavelengths, the particle testing and processing part 7 obtains the parameters of the plume particles of the solid rocket engine based on the established smoke particle inversion algorithm, processes, stores and displays the parameters of the plume particles of the solid rocket engine, and further evaluates the characteristic signals of the plume particles of the solid rocket engine.
Further, the selection of the laser wavelengths and intensities of the plurality of lasers 22, 23, 24 in the laser source section 2, the wavelength range of the band pass filter 41 in the laser receiving section 4, the wavelength of the narrow band filter 51 in the laser diffraction detecting section 5, and the grating 63 parameter in the laser attenuation detecting section 6 needs to be selected and determined in combination with the parameters such as the particle diameter parameter range, the particle concentration parameter concentration, and the plume radiation characteristic of the engine plume 12, and usually, the laser wavelengths of the plurality of lasers 22, 23, 24 in the laser source section 2 are selected within the wavelength range of the blue-violet light in order to avoid the influence of the plume radiation.
Furthermore, the positions of the photodetectors 65, 66, and 67 in the laser attenuation detecting portion 6 are set according to the light splitting of the grating 63, so as to obtain the intensities of the transmitted laser light with different wavelengths correspondingly.
The embodiment also provides a solid rocket engine plume smoke particle testing method, which includes measuring the diffraction light energy distribution and attenuation degree of laser with different wavelengths after passing through a plume to be tested, obtaining a solid rocket engine plume smoke particle parameter based on an established smoke particle inversion algorithm, and further evaluating a solid rocket engine plume smoke particle characteristic signal.
The solid rocket engine plume smoke particle testing method utilizes the solid rocket engine plume smoke particle testing device in the embodiment to test the solid rocket engine plume smoke particles, and comprises the following steps:
s1: installing the solid rocket engine plume smoke particle testing device on two sides of the plume;
s2: opening a laser controller, driving a laser to generate laser, opening a laser diffraction detection part and a laser attenuation detection part, and respectively recording, processing and storing the initial laser light energy distribution and intensity received by detection;
s3: starting a test, simultaneously opening a laser diffraction detection part and a laser attenuation detection part, and respectively recording, processing and storing the distribution and the intensity of the transmitted laser diffraction light energy received by detection;
s4: obtaining plume smoke particle parameters of the solid rocket engine based on the established smoke particle inversion algorithm;
s5: evaluating a signature of the plume smoke particles of the solid rocket engine.
Further, the solid rocket engine plume smoke particle testing method adopts different detection data for different particle size ranges, and obtains the parameters of the solid rocket engine plume smoke particles based on different smoke particle inversion algorithms:
for the particle size range of 0.06-10 μm, selecting the laser attenuation degree data with different wavelengths obtained by the laser attenuation detection part 6, and obtaining particle parameters based on an extinction spectrum particle inversion algorithm;
for the particle size range of more than 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 the embodiment, the evaluation of the characteristic signals of the plume smoke particles of the solid rocket engine is realized by combining the particle size range of the particles of 0.06-10 mu m and the particle size range of the particles of more than 10 mu m, and two algorithms are adopted for synchronous testing and processing to comprehensively form the final test result.
Further, the extinction spectrum particle inversion algorithm is obtained by establishing that the attenuation degree of the laser with different wavelengths after passing through the plume to be measured accords with the Bellambert law.
As shown in fig. 2, the attenuation degree of the laser with different wavelengths after passing through the plume to be measured is as follows:
subscript λiRepresenting different wavelengths; t is the transmittance, which is the transmitted light intensity I and the initial light intensity I0The ratio of (A) to (B); qextIs a proportionality constant related to laser wavelength, smoke particle parameters, etc.; l is plume thickness; n is a radical ofD(d) is the smoke particle concentration, f (d) is a function of the smoke particle size distribution. Therefore, the transmitted light intensity I and the initial light intensity I of the laser with different wavelengths are measured through experiments0The plume transmittance T is obtained. Therefore, a linear equation set is obtained by experimentally measuring the attenuation of the lasers with different wavelengths after passing through the plume to be measured:
E＝Af
Further, the laser diffraction particle inversion algorithm is obtained according to Fraunhofer diffraction theory and Babinet's principle. The expression of the diffraction light intensity distribution I of the spherical particles under parallel light irradiation is as follows:
I0is the incident light intensity of parallel light, f is the focal length of the Fourier lens, lambda is the wavelength, D is the particle diameter, X ═ pi Dsin theta/lambda, theta is the diffraction angle, J1Is a first order Bessel function. From the characteristics of the Bessel function, 2J can be obtained when X is 01(X)/X ═ 1, and in a spherical coordinate system (r, θ, Φ), the scattering amplitude S of the spherical particles under the irradiation of a gaussian beam1And S2Can be expressed as:
anand bnIs the coefficient of scattering in the meter of,
and
is the form factor of the light, and,
and
is a function of the scattering angle, 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 the irradiation of the Gaussian beam, the light intensity of the incident beam is non-uniformly distributed, but the Fraunhofer diffraction theory and the Babinet theory are still established, so the particle diffraction light energy distribution under the irradiation of the Gaussian beam can be derived according to the two principles, and the particle diffraction light energy distribution is obtained by a laser diffraction detection part plane detector:
the subscript n represents the nth ring, S is the radius, Sn,1Is the inner radius of the n-th ring, Sn,2Is the outer radius of the nth ring and corresponds to a diffraction angle of thetan,1And thetan,2And n is 1,2, …, and M, wherein M is the total ring number of the multiple photodetectors.
The laser diffraction light energy distribution obtained by the exemplary embodiment is shown in fig. 4.
When the focal length f of the Fourier lens is far larger than the maximum radius of the photoelectric detector, namely the diffraction angle is small, the light energy distribution can be simplified;
Xn,1＝πDθn,1/λ，Xn,2＝πDθn,2the/λ, D and λ distributions are the particle size of the particles and the wavelength of the incident beam. The diffraction light energy on the nth ring obtained by integrating the above formula is as follows:
the above equation is based on the case where the measurement zone has only one particle. If there are a plurality of particle systems, or clusters, of different sizes in the measurement area, and the diameter is assumed to be DiThe number of particles of (A) is NiTable i below shows the particle size classification, i ═ 1,2, …, K. The total diffracted light energy on the nth ring at this time is:
the total diffracted light energy can be expressed in matrix form:
E＝TW
E＝(e1,e1,…,eM)Tis the light energy distribution column vector, W ═ W1,W1,…,WM)TThe particle size distribution is arranged in the column vector, and
for the matrix of light energy distribution coefficients, each element t in the matrixi,nThe physical meaning of (A) is a diameter per unit weight of DiThe light energy that is diffracted to fall on the nth ring of the photodetector. Thereby establishing a correspondence between the laser diffraction light energy distribution and the particle size distribution. The optical energy distribution column vector E can be measured by a plane detector through an experiment, the optical energy distribution coefficient matrix T can be obtained by calculation through a diffraction theory, and then the particle size distribution, the number distribution of particles, or the volume distribution of particles can be obtained. On the basis, the lasers of the laser light source parts with different wavelengths are combined with the narrow-band filter of the laser diffraction detection part, so that the particle laser diffraction light energy distribution with multiple wavelengths can be obtained, and the test precision can be further improved through the inversion of the multi-wavelength light energy distribution.
Effects and effects of the embodiments
The solid rocket engine plume smoke particle testing device and the method provided by the embodiment have the following effects:
(1) in the embodiment, the distribution and attenuation degree of diffracted light energy of lasers with different wavelengths after passing through the plume to be detected are measured, particle parameters of the engine plume in a real high-temperature state are obtained based on an established smoke particle inversion algorithm, the on-line test of the smoke particles of the solid rocket engine plume is realized, and further the characteristic signals of the smoke particles of the solid rocket engine plume are evaluated.
(2) The laser modulation part of the embodiment adopts the Gaussian lens and the diaphragm, and modulates laser space parameters such as the spot size, the beam expansion angle and the effective irradiation measurement area of incident laser by setting the positions, the focal length and the like of the Gaussian lens and the diaphragm, modulates the incident laser into a converged Gaussian beam to irradiate the plume measurement area, and positions the effective irradiation measurement area in the Rayleigh area of the Gaussian beam, thereby realizing the control and adjustment of the effective irradiation measurement area, achieving the purposes of realizing the average measurement of a larger space of the engine plume and realizing the local measurement of a small space, and further obtaining the effect of the space distribution condition of particle parameters in the plume space range.
(3) In the embodiment, the transmission beam is split into two beams of light by the laser receiving part, one beam of light is converged by the condensing lens, enters the optical fiber coupler and is output by the optical fiber to the laser attenuation detection part, the other beam of light is space laser, and is output to irradiate the laser diffraction detection part, so that the energy distribution and the intensity of the transmission laser diffraction light are synchronously obtained, particle size measurement in different particle ranges is synchronously obtained based on an extinction spectrum particle inversion algorithm and a laser diffraction particle inversion algorithm, a final test result is comprehensively formed, the particle size measurement range is effectively widened, and the measurement precision is improved.
(4) The selection of the laser wavelengths and the intensities of the lasers of the laser light source part, the wavelength range of the band-pass filter of the laser receiving part, the wavelength of the narrow-band filter of the laser diffraction detection part and the grating parameters of the laser attenuation detection part needs to be selected and determined by combining parameters such as particle size parameter range, particle concentration parameter concentration, plume radiation characteristics and the like of the engine plume, so that the influence of high-temperature plume radiation on photoelectric detection is avoided, and the test precision is effectively improved.
The above embodiments are preferred examples of the present invention, and are not intended to limit the scope of the present invention.
Various modifications, additions and substitutions for the specific embodiments described herein may be made by those skilled in the art without departing from the spirit of the invention or exceeding the scope of the invention as defined in the accompanying claims.
Claims (8)
1. A solid rocket engine plume smoke particle testing device is used for measuring the attenuation degree of different wavelength laser after passing through an engine plume to be tested, and is characterized by comprising the following components:
a laser light source unit located on the engine plume side for generating incident laser light of different wavelengths;
the laser modulation part is positioned between the engine plume and the laser light source part and is used for receiving the incident laser and modulating the spot size, the beam expanding angle and the laser space parameters of the effective irradiation measuring area of the incident laser;
the laser receiving part is positioned at the other side of the engine plume and is used for converging and receiving the transmission laser with different wavelengths after passing through the plume to be detected and splitting the transmission laser into a first light beam and a second light beam through a half-transmitting and half-reflecting mirror;
the laser diffraction detection part receives the first light beam and is used for detecting the light energy distribution diffracted by the first light beam;
the laser attenuation detection part receives the second light beam, irradiates the grating and then divides the second light beam into a plurality of laser beams according to the wavelength; and
a particle test processing part for controlling the laser light source part,
the particle testing and processing part is in communication connection with the laser diffraction detection part and the laser attenuation detection part respectively and is used for processing, storing and displaying parameters of plume smoke particles of the solid rocket engine.
2. The solid rocket engine plume smoke particle testing device of claim 1, wherein:
wherein the laser light source part comprises a laser controller, a plurality of lasers, an optical fiber coupler and an optical fiber collimator,
the laser controller is respectively connected with the plurality of lasers and is used for controlling the plurality of lasers with different wavelengths to generate laser,
the laser light generated by the laser is output to the optical fiber coupler through an optical fiber,
the optical fiber coupler receives the laser generated by the laser and couples the laser into an output optical fiber, and the optical fiber coupler is connected with the collimator through the output optical fiber.
3. The solid rocket engine plume smoke particle testing device of claim 1, wherein:
wherein the laser modulation part comprises a Gaussian lens and a diaphragm,
the laser modulation part receives incident laser emitted by the laser light source part, modulates the spot size, the beam expansion angle and the laser space parameters of an effective irradiation measurement area of the incident laser by setting the position parameters of the Gaussian lens and the diaphragm, and modulates the incident laser into a converged Gaussian laser beam which irradiates the measurement area in the plume and is positioned in a Gaussian beam Rayleigh area, so that the position and the size of the effective irradiation measurement area are controlled, and a measurement result is controlled to represent an object.
4. The solid rocket engine plume smoke particle testing device of claim 3, wherein:
wherein the laser receiving part comprises a band-pass filter, a semi-transparent and semi-reflective mirror, a condensing lens and an optical fiber coupler which are arranged along an incident light path in sequence,
after the band-pass filter plate filters the exhaust plume radiation signal of the solid rocket engine, the laser receiving part splits the Gaussian laser into the first light beam and the second light beam through the semi-transparent semi-reflecting mirror,
the first beam is output to the laser diffraction detecting section,
the second light beam is converged by the condenser lens, enters the optical fiber coupler and is output to the laser attenuation detection part,
and synchronously obtaining the distribution and the intensity of the transmitted laser diffraction light energy, thereby synchronously obtaining particle size measurement in different particle ranges based on an extinction spectrum particle inversion algorithm and a laser diffraction particle inversion algorithm.
5. The solid rocket engine plume smoke particle testing device of claim 4, wherein:
wherein the laser diffraction detection part comprises a narrow-band filter, a plane detector and a laser diffraction processor which are arranged in sequence, the laser diffraction detection part is positioned at one side of the laser receiving part,
the plane detector receives the first light beam, performs photoelectric conversion, and outputs the first light beam to the laser diffraction processor, and the laser diffraction processor is connected with the plane detector through a cable to convert an electric signal into a digital signal and obtain transmitted laser diffraction light energy distribution.
6. The solid rocket engine plume smoke particle testing device of claim 4, wherein:
wherein the laser attenuation detection part comprises a collimator, a grating, a plurality of photoelectric detectors and a laser attenuation processor,
the collimator is connected with the optical fiber coupler through an optical fiber, collimated laser light output by the laser receiving part after being collimated is irradiated on the grating,
and the grating receives the collimated laser and then divides the collimated laser into a plurality of beams of laser according to the wavelength.
7. The solid rocket engine plume smoke particle testing device of claim 6, wherein:
wherein, the plurality of photodetectors respectively receive the plurality of laser beams and convert the optical signals into electric signals to be output to the laser attenuation processor through cables,
the laser attenuation processor collects the electric signals output by the photoelectric detectors and converts the electric signals into digital signals, so that the intensities of the transmission laser with different wavelengths are obtained.
8. The solid rocket engine plume smoke particle testing device of claim 5, wherein:
wherein the narrow band filter controls a wavelength of the first light beam.
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