CN101776441A - Real-time online system for measuring space vehicle shell impact degree and impact position - Google Patents

Abstract

The invention discloses a real-time online space vehicle (space station) housing impact degree and impact positioning measurement system, the system is based on distributed optical fiber sensor measuring stress and strain technology and space vehicle shell impact degree and impact positioning technology; the system The system includes an optical fiber Bragg sensor system, an optical signal demodulation system, a calculation system for the impact degree and impact location of the space vehicle shell; a distributed fiber Bragg grating sensor system is laid in the space vehicle shell, and when the space vehicle shell is subjected to an external impact, the stress and strain Finally, the surrounding deformation of the impact point causes the central wavelength of the monitoring light wave of the fiber Bragg grating sensor to change, and the optical signal demodulation system converts the change value of the central wavelength of the monitoring light wave into the stress of three sensors (or more) around the impact point The strain is input into the impact degree and impact location calculation system of the spacecraft shell to determine the impact degree and impact position of the spacecraft shell.

Description

A real-time on-line measurement system for impact degree and impact location of spacecraft shell

【Technical field】

The present invention is a real-time on-line space vehicle (space station) housing impact degree and impact positioning measurement system, the system is based on distributed optical fiber sensor measuring stress and strain technology and space vehicle (space station) shell impact degree and impact positioning technology .

【Background technique】

Researchers at the University of Southampton in the United Kingdom released a research report on November 4, 2009, saying that with the increase in human space exploration activities, the amount of space junk will increase sharply. "pass" incidents will increase by 50%; by 2059, they will increase by 250%. More and more space junk will undoubtedly greatly increase the probability of space "crash" events. In October 2009, "Wired Science" of the United States obtained a database of hypervelocity impacts, indicating that space debris and meteoroids hit the windows of the space shuttle in 54 missions from STS-50 to STS-114. times, forcing 92 windows to be replaced; the space shuttle's radiator was hit 317 times, actually causing holes in the radiator's aluminum honeycomb panel 53 times. At the House Subcommittee on Space Debris at the Conference on Space and Aviation, Nicholas Johnson, chief scientist for NASA's Orbital Debris Program Office, announced that space debris has become a growing problem, forcing aerospace engineers to find less This dangerous approach is on the agenda.

Fiber Bragg Grating (Fiber Bragg Grating, FBG) is a simple inherent sensing element, which is written into the fiber core by using the ultraviolet light-sensitive characteristics of silicon optical fiber, and the part of the refractive index changed by ultraviolet light irradiation forms a fiber grating. Because the fiber Bragg grating has many special advantages: small size, light weight, high strength, good bendability, good flexibility, free from electromagnetic wave interference, no external power supply, corrosion resistance, easy to embed in structures, and establish network monitoring , spectral coding, low cost, etc. Therefore, its sensor application fields are very extensive, including: intelligent network for health monitoring of large concrete structures (bridges, overpasses, railways); applications in the aerospace field; applications in the mining industry; applications in power plants; applications in the medical field; Chemical sensing devices; filter devices, etc.

The fiber Bragg grating sensor array can form the required sensor network in the following ways: One is wavelength division multiplexing (Wavelength Division Multiplexing, WDM), that is, multiple fiber grating strain sensors are connected in series on the same optical fiber to measure the structure at different positions. The number of series connections is determined by the bandwidth of the light source and signal acquisition module and the predicted strain range of each sensor; the second is Space Division Multiplexing (SDM), which is composed of 1×N optical switches ( The optical switch) designs the optical network as a radial type, and each channel can be connected to a wavelength division multiplexing sensor containing multiple wavelengths; the third is time division multiplexing (Time Division Multiplexing, TDM), that is, on a broadband optical carrier, The time is divided into periodic frames, and each frame is divided into several time slots (no matter whether the frames or time slots are mutually non-overlapping), each time slot is a communication channel, which is assigned to an output port.

The purpose of the patent of the present invention is to solve the problem of deformation detection after the above-mentioned space junk and meteoroid hit the space vehicle (space station) shell, and the technology adopted is distributed optical fiber sensor measuring stress and strain technology and the impact of the space vehicle (space station) shell Accuracy and impact positioning technology. In theory, the mathematical model is determined based on physical theories such as elastodynamics and stress wave fundamentals, and the model coefficients are determined by combining experiments and semi-physical experiment simulations. Finally, the physical and mathematical model of the impact degree and impact position of the actual space vehicle (space station) shell is established. And real-time online display of the impact process and effect of the space vehicle (space station) shell. It mainly realizes the following functions: 1. Determine the exact position of the shell of the space vehicle (space station) impacted in real time, and display it on the control interface in time. 2. Determining the impact degree and impact type of the spacecraft (space station) shell, so as to distinguish the deformation degree (elastic deformation or plastic deformation) of the space vehicle (space station) shell after being impacted. 3. When a space vehicle encounters impactors such as dense meteoroids, large masses, or a large amount of space junk, judge the degree of damage to the space vehicle (space station) shell, determine the avoidance plan for the space vehicle, or take further emergency measures.

【Content of invention】

The present invention is a real-time on-line space vehicle (space station) housing impact degree and impact positioning measurement system, the system is based on distributed optical fiber sensor measuring stress and strain technology and space vehicle (space station) shell impact degree and impact positioning technology . Adopt the following technical solutions:

The invention discloses a real-time on-line space vehicle (space station) housing impact degree and impact positioning measurement system, the system is based on distributed optical fiber sensor measuring stress and strain technology and space vehicle (space station) shell impact degree and impact positioning technology; the system includes an optical fiber Bragg sensor system, an optical signal demodulation system, a space vehicle (space station) shell impact degree and an impact positioning calculation system; a distributed fiber Bragg grating sensor system is laid in the space vehicle (space station) shell, and when space After the shell of the aircraft (space station) is stressed and strained by external impact, the surrounding deformation of the impact point causes the central wavelength of the monitoring light wave of the fiber Bragg grating sensor to change, and the optical signal demodulation system converts the central wavelength change value of the monitoring light wave into the impact point The stress and strain of the surrounding three sensors (or more) positions are input into the impact degree and impact location calculation system of the spacecraft (space station) shell, and then the impact degree and impact position of the space vehicle (space station) shell are determined.

Wherein, the distributed optical fiber sensor system includes a broadband light source, an adjustable filter, a Bragg grating array, an optical fiber connection device, a wavelength division multiplexing device, and a wavelength receiving and analyzing device; The connecting device is transmitted to the fiber Bragg grating array for stress and strain sensing, and the sensed optical signal is sequentially transmitted to the optical fiber connecting device, the wavelength division multiplexing device, and the wavelength receiving and analyzing device.

Wherein, the broadband light source is a broadband laser light source or a broadband light-emitting diode light source; the tunable filter is a tunable fiber grating filter or a Fabry-Perot tunable filter or an acoustic/optic tunable filter or array Waveguide grating tunable filter or liquid crystal tunable filter or electrical/optical tunable filter or fiber Bragg fiber tunable filter or tunable filter based on semiconductor or laser structure; the optical fiber connection device is an optical fiber connector Or optical fiber adapter or optical fiber docking device; the wavelength division multiplexing device is a grating wavelength division multiplexer or dense wavelength division multiplexer or optical fiber standard wavelength division multiplexer coupler or relay type wavelength division multiplexer or thin film filter Type wavelength division multiplexer or coarse wavelength division multiplexer; the wavelength receiving and analyzing device is a multi-light wavelength meter or a fiber grating sensing system or a spectrum analyzer.

Wherein, the fiber Bragg grating array is arranged inside the shell of the spacecraft (space station), and is closely attached to the measured point. Each FBG position with an intrinsic central wavelength represents a measured position on the spacecraft (space station) shell. When the measured position on the shell of the space vehicle (space station) undergoes elastic deformation or plastic deformation, the wavelength of the echo optical signal reflected by the fiber Bragg grating at this point changes. The amount of wavelength change corresponds to the deformation state of the spacecraft (space station) shell in real time.

Among them, the corresponding relationship between the wavelength change and the stress-strain value of the space vehicle (space station) shell is determined through experimental calibration. When a point outside the space vehicle (space station) shell is hit, the surrounding deformation of the impact point causes the fiber Bragg grating The sensor monitors the change of the central wavelength of the light wave, and obtains the stress and strain at three sensor (or more) positions around the impact point through the optical signal demodulation system. For example, the three fiber Bragg gratings FBG1, FBG2, and FBG3 whose intrinsic central wavelengths are λ ₁ , λ ₂ , and λ ₃ respectively, the wavelength changes in the ith measurement are Δλ(i) ₁ , Δλ(i) ₂ , Δλ(i) ₃ , we can get three weight coefficients δ(i) ₁ = Δλ(i) ₁ /λ ₁ , δ(i) ₂ = Δλ(i) ₂ /λ ₂ , δ(i) ₃ = Δλ( i) ₃ /λ ₃ . In the same impact measurement (the i-th impact), the larger the weight coefficient, the closer the impact point is to the measurement point.

Among them, by analyzing the weight coefficients δ(i) ₁ , δ(i) ₂ , δ(i) ₃ (or more), the position and impact degree of the impact point from three (or more) fiber Bragg gratings can be obtained , so as to realize the space vehicle (space station) shell impact degree and impact position positioning.

Among them, the fiber Bragg grating sensing array determines the position and intensity of the impact point, determines the theoretical model based on physical theories such as elastic dynamics and stress wave foundation, determines the model parameters or coefficients through experiments and semi-physical experiment simulations, and establishes the actual space vehicle (space station) ) The mathematical and physical model of the impact degree and impact position of the shell.

Among them, the determined mathematical and physical model is combined with the fiber Bragg grating sensor array, and the impact degree and impact position of the space vehicle (space station) shell are determined through the optical signals fed back from each measurement point. And real-time online display of the impact process and effect of the space vehicle (space station) shell. It includes the following functions: a. Determine the exact position of the shell of the space vehicle (space station) that is impacted in real time, and display it on the control interface in time. b. Determining the impact degree and impact type of the spacecraft (space station) shell, so as to distinguish the deformation degree (elastic deformation or plastic deformation) of the space vehicle (space station) shell after being impacted. c. Judging the degree of damage to the shell of the space vehicle (space station) when encountering dense meteoroids, large masses, or a large amount of space debris and other impactors, determining the avoidance plan for the space vehicle, or taking further emergency measures.

Wherein, the software processing system is a VC++ language development software system, and can be developed compatible with computer language program systems such as Matlab, labviw, VC, and VB.

Among them, the system determines the exact position of the shell of the space vehicle (space station) in real time, and displays it on the control interface in time, and displays the impact degree and position of the shell of the space vehicle (space station) online in real time. To provide astronauts with a reasonable and reliable man-machine control interface, to diagnose and analyze the degree of impact, and to effectively predict the life of key frames, structural parts and shells of space vehicles (space stations).

Beneficial effects of the present invention: the present invention can determine the exact position of the shell of the space vehicle (space station) that is impacted in real time and online, and display it on the control interface in time. At the same time, the impact degree and impact type of the space vehicle (space station) shell are determined, so as to distinguish the deformation degree (elastic deformation or plastic deformation) of the space vehicle (space station) shell after being impacted. When a space vehicle encounters impactors such as dense meteoroids, large masses, or a large amount of space junk, it is necessary to judge the degree of damage to the shell of the space vehicle (space station), determine an avoidance plan for the space vehicle, or take further emergency measures. After analyzing the response of the space vehicle (space station) shell under impact, the impact degree is diagnosed and the life of the key frame and shell of the space station is predicted. The invention patent has practical application value for the future development of the aerospace field.

【Instructions attached】

Figure 1 is a schematic diagram of the impact degree and impact positioning measurement system of the space vehicle (space station) shell

Fig. 2 is a schematic diagram of a Bragg grating structure;

Fig. 3 is a schematic diagram of a wavelength division multiplexing distributed fiber Bragg grating sensor system.

【Detailed ways】

The invention discloses a real-time online space vehicle (space station) shell impact degree and impact location measurement system, as shown in Figure 1, the system is based on distributed optical fiber sensor measuring stress and strain technology and space vehicle (space station) shell Impact degree and impact positioning technology, including optical fiber Bragg sensor system 110, optical signal demodulation system 120, space vehicle (space station) shell impact degree and impact positioning calculation system 130; distributed optical fiber is laid in the space vehicle (space station) shell For the Bragg grating sensor system (such as 111, 112, 113), when the shell of the space vehicle (space station) is subjected to stress and strain due to external impact, the deformation around the impact point 114 causes the monitoring light wave center of the fiber Bragg grating sensor (111, 112, 113) Change of wavelength; obtain the stress and strain of three sensors (111, 112, 113) (or more) positions around the impact point 114 by the optical signal demodulation system 120, and input the stress and strain values of the sensor positions into the space vehicle (space station) shell In the calculation system 130 of body impact degree and impact location, the impact degree and impact position of the spacecraft (space station) shell can be finally determined.

Fig. 2 is an optical fiber with multiple gratings, wherein each black part 200 is a grating 210, and each grating has a different central reflection wavelength λ ₀ , so that the gratings at different points can respectively measure the corresponding stress, strain and vibration In some cases, multiple gratings can be fabricated in the same fiber. 210 in the figure is an enlarged structural pattern of a grating, and each black part 211 is the core part of the optical fiber after the light wave refraction changes.

Fiber Bragg Grating (Fiber Bragg Grating, FBG) is a simple inherent sensing element, which utilizes the ultraviolet light sensitivity of silicon fiber to write into the fiber core. Figure 2 describes the basic structure of the fiber Bragg grating. Each black portion 211 of the grating in the figure is a portion where the refractive index changes after being irradiated with ultraviolet light. The fiber core grating Bragg reflection wavelength (λ _B ) condition can be expressed by formula (1):

λ _B ＝2×n×Λ (1)

In the formula, Λ is the period length of the grating; n is the effective refractive index of the fiber. When a wide-spectrum light source is incident into the fiber, the grating will reflect the narrow-spectrum component centered on the Bragg wavelength λ _B. In the transmission spectrum, this part of the component will disappear, and the drift Δλ _B of λ _B with stress and temperature is formula (2):

$\mathrm{<span\; class="notranslate">\; \&Delta;</span>}{\mathrm{<span\; class="notranslate">\; \&lambda;</span>}}_{\mathrm{<span\; class="notranslate">\; B</span>}}<span\; class="notranslate">\; =</span>\mathrm{<span\; class="notranslate">\; 2</span>}\mathrm{<span\; class="notranslate">\; n\&Lambda;</span>}<span\; class="notranslate">\; \{</span><span\; class="notranslate">\; \{</span>\mathrm{<span\; class="notranslate">\; 1</span>}<span\; class="notranslate">\; -</span><span\; class="notranslate">\; (</span>\frac{{\mathrm{<span\; class="notranslate">\; no</span>}}^{\mathrm{<span\; class="notranslate">\; 2</span>}}}{\mathrm{<span\; class="notranslate">\; 2</span>}}<span\; class="notranslate">\; )</span><span\; class="notranslate">\; [</span>{\mathrm{<span\; class="notranslate">\; P</span>}}_{\mathrm{<span\; class="notranslate">\; 12</span>}}<span\; class="notranslate">\; -</span>\mathrm{<span\; class="notranslate">\; v</span>}<span\; class="notranslate">\; (</span>{\mathrm{<span\; class="notranslate">\; P</span>}}_{\mathrm{<span\; class="notranslate">\; 11</span>}}<span\; class="notranslate">\; +</span>{\mathrm{<span\; class="notranslate">\; P</span>}}_{\mathrm{<span\; class="notranslate">\; 12</span>}}<span\; class="notranslate">\; )</span><span\; class="notranslate">\; ]</span><span\; class="notranslate">\; \}</span><span\; class="notranslate">\; \&Center\; Dot;</span>\mathrm{<span\; class="notranslate">\; \&epsiv;</span>}<span\; class="notranslate">\; [</span>\mathrm{<span\; class="notranslate">\; \&alpha;</span>}<span\; class="notranslate">\; +</span>\frac{\mathrm{<span\; class="notranslate">\; 1</span>}}{\mathrm{<span\; class="notranslate">\; no</span>}}<span\; class="notranslate">\; \&Center\; Dot;</span>\frac{\mathrm{<span\; class="notranslate">\; dn</span>}}{\mathrm{<span\; class="notranslate">\; dT</span>}}<span\; class="notranslate">\; ]</span>\mathrm{<span\; class="notranslate">\; \&Delta;T</span>}<span\; class="notranslate">\; \}</span><span\; class="notranslate">\; -</span><span\; class="notranslate">\; -</span><span\; class="notranslate">\; -</span><span\; class="notranslate">\; (</span>\mathrm{<span\; class="notranslate">\; 2</span>}<span\; class="notranslate">\; )</span>$

Among them: ε is the applied stress; P _{i, j} is the photoelastic tensor coefficient of the fiber; v is Poisson's ratio; α is the thermal expansion coefficient of the fiber material (such as quartz); ΔT is the temperature change.

In the above formula: the typical value of the factor of (n ² /2)[P ₁₂ -v(P ₁₁ +P ₁₂ )] is 0.22. Therefore, the FBG stress and temperature response conditions under normal temperature and normal stress conditions can be deduced as follows:

$\frac{\mathrm{<span\; class="notranslate">\; 1</span>}}{{\mathrm{<span\; class="notranslate">\; \&lambda;</span>}}_{\mathrm{<span\; class="notranslate">\; B</span>}}}<span\; class="notranslate">\; \&Center\; Dot;</span>\frac{\mathrm{<span\; class="notranslate">\; \&delta;</span>}{\mathrm{<span\; class="notranslate">\; \&lambda;</span>}}_{\mathrm{<span\; class="notranslate">\; B</span>}}}{\mathrm{<span\; class="notranslate">\; \&delta;\&epsiv;</span>}}<span\; class="notranslate">\; =</span>\mathrm{<span\; class="notranslate">\; 0.78</span>}<span\; class="notranslate">\; \&times;</span>{\mathrm{<span\; class="notranslate">\; 10</span>}}^{<span\; class="notranslate">\; -</span>\mathrm{<span\; class="notranslate">\; 6</span>}}\mathrm{<span\; class="notranslate">\; \&mu;</span>}<span\; class="notranslate">\; /</span>\mathrm{<span\; class="notranslate">\; \&epsiv;</span>}<span\; class="notranslate">\; -</span><span\; class="notranslate">\; -</span><span\; class="notranslate">\; -</span><span\; class="notranslate">\; (</span>\mathrm{<span\; class="notranslate">\; 3</span>}<span\; class="notranslate">\; )</span>$

When the grating measures the stress and strain, the grating is first attached to the underside or side of the force-bearing object. When the force-bearing object is subjected to force, the grating is simultaneously stressed, stretched or contracted, so that it inherently becomes larger or smaller. Through the formula: λ _B =2×n×Λ, it can be known that λ _B will also change. Then the initial Λ ₀ of the grating has the initial Bragg center wavelength λ ₀ =2×n×Λ ₀ . By comparing the intrinsic Bragg center wavelength with the stressed Bragg reflection wavelength Δλ=λ _B -λ ₀ , the system can convert the magnitude of the pressure.

Fiber Bragg sensor system 110, as shown in Figure 3, includes a broadband light source 301, a tunable filter 302, an optical fiber connection device 307, a Bragg grating fiber array sensing device 303, a wavelength division multiplexing device 304, a wavelength receiving and analyzing device 305 and Central processing device 306, these devices are connected by single-mode optical fiber or multi-mode optical fiber.

From the broadband light source 301 (broadband laser light source or broadband light emitting diode light source), a light source with a very wide bandwidth (about tens of nm, such as from 1530nm to 1560nm) is emitted, and passed to the automatically adjustable filter 302, the adjustable The filter can be a tunable fiber grating filter or a Fabry-Perot tunable filter or an acoustic/optic tunable filter or an array waveguide grating (Array Wave-guide Grating, AWG) tunable filter or a liquid crystal tunable filter. Tunable filter or electrical/optical tunable filter or fiber Bragg fiber tunable filter or tunable filter based on semiconductor or laser structure, tunable filter 302 increases rapidly from 1530nm to 1560nm by 1nm, a total increase of 30 Second-rate. If the scanning frequency of the tunable filter 302 is 300 Hz in one second, the range of 1530nm+1nm to 1560nm can be repeated 10 times in one second. It takes 0.1 second for the light source to change once, and the fiber Bragg gratings at all measurement positions can reflect their own conditions to the central processing unit 306 .

The light emitted from the tunable filter 302 is transmitted to the optical fiber connection device 307, and the optical fiber connection device is a fiber optic connector or a fiber optic adapter or a fiber optic docking device. After space division multiplexing by the device, it is transmitted to a plurality of Bragg grating optical fibers An array sensing device 303, each of which has dozens of gratings with different center frequencies (for example, there are 30 gratings, and the Bragg center frequencies from the 1st to the 30th are 1530nm, 1531nm, 1532nm, ... ...1560nm). In this way, when the wavelength of the light source of the tunable filter 302 is λi, only the Bragg reflection wavelength of the grating whose Bragg center wavelength is _λi is sensed by the subsequent device. According to this principle, the wavelength variation Δλ at different positions can be obtained. Calculated as follows:

Δλ=λ _B -λ ₀ (5)

The reflected wavelength on the optical fiber from the Bragg grating fiber array sensing device 303 is transmitted to the optical fiber connection device 307, and after space division multiplexing, it is transmitted to the wavelength division multiplexing device 304, and the wavelength division multiplexing device is a grating wavelength division multiplexing device. Use device or dense wavelength division multiplexer or optical fiber standard wavelength division multiplexing coupler or relay type wavelength division multiplexer or thin film filter type wavelength division multiplexer or coarse wavelength division multiplexer, through which Using this method, the wavelength change of a certain grating with different Bragg center wavelengths on the same fiber can be distinguished in real time.

The Bragg reflection wavelength that comes out from the wavelength division multiplexing device 304 is passed to the reflected light wavelength receiving and analyzing device 305 at the back, and the wavelength receiving and analyzing device is a multi-light wavelength meter or a fiber Bragg grating sensing system or a spectrum analyzer. The device obtains accurate reflected Bragg wavelength values. Cooperating with the reflected light wavelength receiving and analyzing device 305, the impact degree of the shell of the space vehicle (space station) can be determined on the central processing device 306, and the impact location can be displayed in real time as an image.

The fiber Bragg grating array 110 is arranged inside the shell 115 of the spacecraft (space station), and is closely attached to the measured point. Each fiber Bragg grating with its own central wavelength represents a measured position on the spacecraft (space station) shell. When the measured position on the shell of the space vehicle (space station) undergoes elastic deformation or plastic deformation, the wavelength of the echo optical signal reflected by the fiber Bragg grating at this point changes. The amount of wavelength change corresponds to the deformation state of the spacecraft (space station) shell. After calibration through experiments, it can be determined that the amount of wavelength change corresponds to the stress and strain value of the space vehicle (space station) shell.

When a point outside the shell of the space vehicle (space station) is hit, the deformation around the hit point causes the center wavelength of the optical fiber Bragg grating sensor to monitor the change of the wavelength, and the three sensors (or more) around the hit point are obtained through the optical signal demodulation system. Stress-strain at position. The three fiber Bragg gratings FBG1, FBG2, and FBG3 whose intrinsic central wavelengths are λ ₁ , λ ₂ , and λ ₃ respectively, and their wavelength changes are Δλ(i) ₁ , Δλ(i) ₂ , Δλ(i) ₃ , Three weight coefficients can be obtained: δ ₁ =Δλ(i) ₁ /λ ₁ , δ ₂ =Δλ(i) ₂ /λ ₂ , and δ ₃ =Δλ(i) ₃ /λ ₃ . In the same impact measurement, the larger the weight coefficient, the closer the impact point is to the measurement point. By analyzing the weight coefficients δ(i) ₁ , δ(i) ₂ , δ(i) ₃ (or more), the position and impact degree of the impact point from three (or more) FBGs can be obtained, so that The degree of impact and the positioning of the impact part of the shell of the space vehicle (space station) are realized.

Here, the fiber Bragg grating sensor array measures the position and intensity of the impact point, determines the theoretical model based on physical theories such as elastodynamics or stress wave foundation, determines the model parameters or coefficients through experiments and semi-physical experiment simulations, and establishes the actual space vehicle (space station ) The physical-mathematical model of the impact degree and impact position of the shell. The determined physical-mathematical model is combined with the fiber Bragg grating sensor array, and the impact degree and impact position of the space vehicle (space station) shell are determined through the optical signals fed back from each measurement point. And real-time online display of the impact process and effect of the space vehicle (space station) shell. It includes the following functions: 1. Determine the exact position of the shell of the space vehicle (space station) that is impacted in real time, and display it on the control interface in time. 2. Determining the impact degree and impact type of the spacecraft (space station) shell, so as to distinguish the deformation degree (elastic deformation or plastic deformation) of the space vehicle (space station) shell after being impacted. 3. When a space vehicle encounters impactors such as dense meteoroids, large masses, or a large amount of space junk, judge the degree of damage to the space vehicle (space station) shell, determine the avoidance plan for the space vehicle, or take further emergency measures.

The software processing system is developed in VC++ language, and can be developed compatible with computer language program systems such as Matlab, labviw, VC, and VB. The software processing system determines the exact position of the shell of the space vehicle (space station) in real time, and displays it on the control interface in time, and displays the impact degree and position of the shell of the space vehicle (space station) online in real time. Astronauts provide a reasonable and reliable man-machine control interface, diagnose and analyze the impact degree and effectively predict the life of the key frame, structural parts and shell of the space vehicle (space station).

The above is only the basic scheme of the specific implementation method of the present invention, but the protection scope of the present invention is not limited thereto, and any conceivable change or replacement within the technical scope disclosed by the present invention by anyone familiar with the technical field, All should be covered within the protection scope of the present invention. Therefore, the protection scope of the present invention should be determined by the protection scope of the claims. All changes that come within the equivalent meaning and range of the claims are intended to be included in the scope of the claims.

Claims (10)

1. The present invention discloses a real-time on-line space vehicle (space station) shell impact degree and impact location measurement system, the system is based on distributed optical fiber sensors measuring stress and strain technology and space vehicle (space station) shell impact degree and Impact positioning technology; the system includes an optical fiber Bragg sensor system, an optical signal demodulation system, a space vehicle (space station) shell impact degree and an impact positioning calculation system; a distributed fiber optic Bragg grating sensor system is laid in the space vehicle (space station) shell, When the shell of the space vehicle (space station) is stressed and strained by an external impact, the surrounding deformation of the impact point causes the central wavelength of the monitoring light wave of the fiber Bragg grating sensor to change, and the optical signal demodulation system converts the central wavelength change value of the monitoring light wave into Stress and strain at the positions of three sensors (or more) around the impact point, and input into the impact degree and impact positioning calculation system of the space vehicle (space station) shell, and then determine the impact degree and impact position of the space vehicle (space station) shell Location. 2. according to a kind of real-time online space vehicle (space station) shell impacted degree and impact location measurement system according to claim 1, it is characterized in that said distributed optical fiber sensor system comprises broadband light source, adjustable filter, Bragg Grating array, optical fiber connection device, wavelength division multiplexing device, wavelength receiving and analysis device; after the broadband light source is filtered by an adjustable filter, it is transmitted to the fiber Bragg grating array through the optical fiber connection device for stress and strain sensing, and the sensed optical signals are sequentially Transmission to fiber optic connection device, wavelength division multiplexing device, wavelength receiving and analyzing device. 3. according to claim 1 and 2 described a kind of real-time online space vehicle (space station) shell is subject to impact degree and impact positioning measurement system, it is characterized in that described broadband light source is broadband laser light source or broadband light emitting diode light source; The tunable filter is a tunable fiber grating filter or a Fabry-Perot tunable filter or an acoustic/optical tunable filter or an arrayed waveguide grating tunable filter or a liquid crystal tunable filter or an electric/optical tunable filter Tunable filter or fiber Bragg fiber tunable filter or tunable filter based on semiconductor or laser structure; the optical fiber connection device is an optical fiber connector or optical fiber adapter or optical fiber docking device; the wavelength division multiplexing device is a grating Wavelength division multiplexer or dense wavelength division multiplexer or optical fiber standard wavelength division multiplexing coupler or relay type wavelength division multiplexer or thin film filter type wavelength division multiplexer or coarse wavelength division multiplexer; the wavelength The receiving and analyzing device is a multi-light wavelength meter or a fiber grating sensing system or a spectrum analyzer. 4. according to a kind of real-time on-line space vehicle (space station) housing impact degree and impact positioning measurement system according to claim 1, it is characterized in that said fiber Bragg grating array is arranged in space vehicle (space station) housing inside, And it is closely attached to the measured point. Each FBG position with an intrinsic central wavelength represents a measured position on the spacecraft (space station) shell. When the measured position on the shell of the space vehicle (space station) undergoes elastic deformation or plastic deformation, the wavelength of the echo optical signal reflected by the fiber Bragg grating at this point changes. The amount of wavelength change corresponds to the deformation state of the spacecraft (space station) shell in real time. 5. according to a kind of real-time on-line space vehicle (space station) shell subjected to impact degree and impact positioning measurement system according to claim 1, it is characterized in that determining wavelength variation and space vehicle (space station) shell stress after calibration by experiment The corresponding relationship between the strain value, when a certain point outside the shell of the space vehicle (space station) is hit, the deformation around the hit point will cause the change of the center wavelength of the monitoring light wave of the fiber Bragg grating sensor. Stress-strain at three sensor (or more) locations. For example, the three fiber Bragg gratings FBG1, FBG2, and FBG3 whose intrinsic central wavelengths are λ ₁ , λ ₂ , and λ ₃ respectively, the wavelength changes in the i-th measurement are Δλ(i) ₁ , Δλ(i) ₂ , Δλ(i) ₃ , we can get three weight coefficients δ(i) ₁ = Δλ(i) ₁ /λ ₁ , δ(i) ₂ = Δλ(i) ₂ /λ ₂ , δ(i) ₃ = Δλ( i) ₃ /λ ₃ . In the same impact measurement (the i-th impact), the larger the weight coefficient, the closer the impact point is to the measurement point. 6. according to a kind of real-time on-line space vehicle (space station) shell impact degree and impact positioning measurement system according to claim 1, it is characterized in that by analyzing the weight coefficient δ(i) ₁ , δ(i) ₂ , δ (i) ₃ (or more), the position and impact degree of the impact point from three (or more) fiber Bragg gratings can be obtained, thereby realizing the impact degree and impact position location of the space vehicle (space station) shell. 7. According to a kind of real-time on-line space vehicle (space station) shell impact degree and impact positioning measurement system according to claim 1, it is characterized in that the fiber Bragg grating sensing array determines the impact point position and intensity, based on elastodynamics Determine the theoretical model based on physical theories such as stress wave foundation, determine the model parameters or coefficients through experiments and semi-physical experiment simulations, and establish a mathematical and physical model of the impact degree and impact position of the actual space vehicle (space station) shell. 8. according to claim 1 or 7 described a kind of real-time online space vehicle (space station) housing impact degree and impact positioning measurement system, it is characterized in that the determined mathematical physics model and fiber Bragg grating sensing array are combined mutually , determine the impact degree and impact position of the spacecraft (space station) shell through the optical signals fed back from each measurement point. And real-time online display of the impact process and effect of the space vehicle (space station) shell. It includes the following functions: a. Determine the exact position of the shell of the space vehicle (space station) that is impacted in real time, and display it on the control interface in time. b. Determining the impact degree and impact type of the spacecraft (space station) shell, so as to distinguish the deformation degree (elastic deformation or plastic deformation) of the space vehicle (space station) shell after being impacted. c. Judging the degree of damage to the shell of the space vehicle (space station) when encountering dense meteoroids, large masses, or a large amount of space debris and other impactors, determining the avoidance plan for the space vehicle, or taking further emergency measures. 9. according to a kind of real-time online space vehicle (space station) shell subjected to impact degree and impact positioning measurement system according to claim 1, it is characterized in that said software processing system is a VC++ language development software system, and can be used with Matlab, Compatible development of computer language program systems such as labviw, VC, VB. 10. according to a kind of real-time on-line space vehicle (space station) shell impact degree and impact location measurement system according to claim 1, it is characterized in that the system determines in real time the accurate position that the space vehicle (space station) shell is impacted , and displayed on the control interface in time, real-time online display of the impact degree and impact position of the space vehicle (space station) shell. To provide astronauts with a reasonable and reliable man-machine control interface, to diagnose and analyze the degree of impact, and to effectively predict the life of key frames, structural parts and shells of space vehicles (space stations).

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