Particle Image Velocimetry System Based on the Vacuum Chamber of Weightless Aircraft

Abstract

The invention relates to a particle image velocity measurement system based on a vacuum chamber of a weightless aircraft, comprising: a high-speed image acquisition subsystem, a panoramic image acquisition subsystem, an illumination subsystem, and a control subsystem. The high-speed image acquisition subsystem comprises a high-speed camera collector and a plurality of high-speed cameras arranged in sequence along the side wall of the vacuum chamber of the weightless aircraft. The panoramic image acquisition subsystem comprises at least two groups of panoramic cameras, which are respectively arranged at the upper part and the lower part of the vacuum chamber of the weightless aircraft. The control subsystem comprises a portable industrial computer, a camera synchronization trigger, camera setting and control software, image data analysis software, and a synchronization trigger cable. The portable industrial computer controls the synchronous triggering of the high-speed camera and the panoramic camera through the camera synchronization trigger, so that multiple high-speed cameras can relay and high-speed shoot particle motion images, and can realize the whole process tracking shooting of key moments of particles with different particle sizes, thereby improving the measurement accuracy of the velocity measurement system, reducing system errors, and expanding the application scope of the velocity measurement system.

Description

Technical Field

[0001] The invention relates to the field of aerospace technology, and in particular to a particle image velocimetry system based on a vacuum cabin of a weightless aircraft. Background Art

[0002] With the development of aerospace technology, planetary sampling has gradually become one of the key development directions of the aerospace industry. Therefore, the deep space exploration planetary sampling environment simulation equipment and the ground weightlessness aircraft test have become the key ground test equipment for verifying the design compliance and equipment reliability, safety, and environmental adaptability of the planetary sampling device. The star soil sampling particle motion parameter measurement system and the planetary sampling device mechanism motion parameter measurement system that are equipped with the test equipment will be widely used as important supporting test equipment.

[0003] The original particle speed measurement system in the vacuum chamber of the weightless aircraft uses a measurement system composed of multiple independent schlieren instruments and conventional cameras. The system records the schlieren change process formed by the movement of particles through video recording, and then manually selects the movement position of particles in the sequence images to obtain the movement speed of particles within a certain time within a certain camera field of view.

[0004] However, the above system uses a schlieren instrument for measurement. The schlieren optical path is relatively complex and requires high operator skills. At the same time, the measurement accuracy of the schlieren instrument is limited. It cannot perform high-precision quantitative measurement, nor can it classify and track particles of different sizes and perform classification data analysis. At the same time, the frame rate of a conventional camera is only 30fps, and the minimum exposure time can only reach milliseconds. The high-speed moving particles captured have serious shadow removal, which in turn produces large measurement errors. Summary of the invention

[0005] In order to solve the technical problems existing in the above-mentioned prior art, the purpose of the present invention is to provide a particle image velocimetry system based on a vacuum chamber of a weightless aircraft, so as to improve the measurement accuracy of the system, reduce the system error, and expand the scope of use of the velocimetry system.

[0006] To achieve the above-mentioned purpose, the present invention provides a particle image velocimetry system based on a vacuum chamber of a weightless aircraft, comprising:

[0007] A high-speed image acquisition subsystem, comprising a high-speed camera collector and a plurality of high-speed cameras arranged in sequence along the side wall of the vacuum chamber of the weightless aircraft, wherein the high-speed cameras are electrically connected to the high-speed camera collector;

[0008] A panoramic image acquisition subsystem includes at least two sets of panoramic cameras, which are respectively arranged at the upper and lower parts of the vacuum cabin of the weightless aircraft;

[0009] The lighting subsystem includes a lighting controller, a plurality of sets of high-brightness background lighting and at least two sets of panoramic lighting, wherein the lighting controller is electrically connected to the high-brightness background lighting and the panoramic lighting; the high-brightness background lighting and the panoramic lighting are respectively arranged in one-to-one correspondence with the high-speed camera and the panoramic camera;

[0010] The control subsystem includes a portable industrial computer, a camera synchronization trigger, a camera setting and control software, an image data analysis software and a synchronization trigger cable. The portable industrial computer is electrically connected to the high-speed camera collector, the camera synchronization trigger and the lighting controller. The camera synchronization trigger is electrically connected to the high-speed camera and the panoramic camera through the synchronization trigger cable for synchronously triggering the high-speed camera and the panoramic camera. The camera setting and control software is built in the portable industrial computer, and the high-speed camera collector is electrically connected to the portable industrial computer.

[0011] According to a technical solution of the present invention, it also includes a mechanical structure subsystem, which is arranged on the outer side of the vacuum chamber of the weightless aircraft, and the mechanical structure subsystem includes:

[0012] A high-speed camera mounting bracket and a panoramic camera mounting bracket, used for mounting the high-speed camera and the panoramic camera;

[0013] An observation window assembly is arranged on the side of the vacuum cabin of the weightless aircraft, comprising an observation window and a fixed flange portion arranged on the periphery of the observation window, and the high-speed camera mounting bracket and the panoramic camera mounting bracket are mounted on the observation window through the fixed flange portion;

[0014] The integrated operating platform is fixed on the outer side of the vacuum chamber of the weightless aircraft and is used for installing the high-speed camera collector, the lighting controller, the portable industrial computer and the camera synchronization trigger.

[0015] According to a technical solution of the present invention, the high-speed camera mounting bracket and the panoramic camera mounting bracket both include:

[0016] Two supporting arms arranged opposite to each other include a supporting arm body arranged perpendicular to the side wall of the vacuum chamber of the weightless aircraft and a fixing plate protruding along the side of the supporting arm body, wherein the fixing plate is provided with a first fixing through groove arranged along the length direction of the vacuum chamber of the weightless aircraft; and the supporting arm body is provided with a second fixing through groove arranged along the length direction of the supporting arm body;

[0017] The support plate is arranged between the two support arm bodies, and its two ends are fixed to the support arm bodies through coaxially arranged bolts, and the bolts are arranged in the second fixing through grooves.

[0018] According to a technical solution of the present invention, the high-brightness background lighting lamp is arranged on the inner wall of the vacuum chamber of the weightless aircraft, at a position relative to the axis of the high-speed camera;

[0019] The two groups of panoramic lighting lamps are respectively arranged on the top and bottom of the vacuum cabin of the weightless aircraft;

[0020] The highlight background lighting and the panoramic lighting are connected to the lighting controller via lighting power supply cables. The lighting power supply cables include an in-cabin lighting power supply cable arranged in the vacuum cabin of the weightless aircraft and an out-cabin lighting power supply cable arranged outside the vacuum cabin of the weightless aircraft. The in-cabin lighting power supply cable and the out-cabin lighting power supply cable are connected via a through-cabin electrical connector.

[0021] According to a technical solution of the present invention, the control subsystem further comprises a power supply filter, and the power supply filter is arranged between the control subsystem and the onboard power supply of the weightless aircraft;

[0022] A decoupling capacitor is connected in series to the ground line connected between the integrated operating platform and the body of the weightless aircraft.

[0023] According to a technical solution of the present invention, the high-speed camera is a large-array grayscale high-speed camera, an impact-resistant lens is provided on the high-speed camera, and the large-array grayscale high-speed camera is electrically connected to the high-speed camera collector via a high-speed camera composite cable.

[0024] According to a technical solution of the present invention, the panoramic camera is electrically connected to the portable industrial computer via a panoramic camera USB data cable and a panoramic camera power cable.

[0025] According to a technical solution of the present invention, the cable used in the system is a cable with a shielding layer, and the exterior of the synchronous trigger cable is coated with a shielding protective tape.

[0026] According to a technical solution of the present invention, the control modes of the lighting controller include a normal lighting mode and a strong light lighting mode.

[0027] According to a technical solution of the present invention, the high-speed image acquisition subsystem further includes a camera calibration device for calibrating a plurality of the high-speed cameras.

[0028] Compared with the prior art, the present invention has the following beneficial effects:

[0029] The present invention provides a particle image velocity measurement system based on a vacuum chamber of a weightless aircraft, which uses multiple high-speed cameras that are triggered synchronously to relay and shoot particle motion images at high speed, and can achieve full-process tracking and shooting of key moments of particles of different particle sizes, which can not only ensure full-process tracking and shooting of key links of particles of different particle sizes, but also reduce the field of view of each high-speed camera to a certain range, thereby improving the spatial size resolution represented by each pixel, improving the measurement accuracy, meeting the needs of classification tracking and classification data analysis of particles of different particle sizes, and can be applied to particle motion velocity measurement of star soil particle sampling of planetary probes of different specifications. At the same time, through high-brightness backlighting, the exposure time can be reduced to microseconds, avoiding the problem of image separation in high-speed motion particle imaging, and thereby reducing system measurement errors.

[0030] The present invention controls the high-speed camera acquisition subsystem, the panoramic image acquisition subsystem and the lighting subsystem through a control subsystem, sets the camera and analyzes the acquired data through a portable industrial computer, and synchronously controls the high-speed camera and the panoramic camera through a camera synchronization trigger and a synchronization trigger cable, thereby achieving the unification of the time zero point of each device in the system and ensuring the timing accuracy of multi-camera relay shooting.

[0031] In the present invention, the control subsystem is installed on the outer side of the vacuum cabin of the weightless aircraft through the mechanical structure subsystem. The system is simple to operate and easy to install, which effectively reduces the number of operators and avoids the problem of poor communication among the onboard system operators due to the noise in the cabin. At the same time, the operation process is simplified and easier to master.

[0032] In the present invention, each component adopts a modular design, and each control subsystem can be installed separately and then connected by cables or the like, which is convenient for quickly replacing front-end acquisition equipment such as high-speed cameras and panoramic cameras that may be damaged during use, greatly shortening the repair and maintenance time and improving the maintainability of the system. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments are briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention, and for ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work.

[0034] Figure 1 A schematic diagram of the structure of a particle image velocimetry system based on a vacuum chamber of a weightless aircraft provided in accordance with one embodiment of the present invention is shown;

[0035] Figure 2 A schematic diagram of the installation position of the observation window assembly according to an embodiment of the present invention is schematically shown;

[0036] Figure 3 A schematic diagram schematically shows the installation position of a mechanical structure subsystem according to an embodiment of the present invention;

[0037] Figure 4 A schematic diagram schematically shows an installation position diagram of a control subsystem according to an embodiment of the present invention;

[0038] Figure 5 A schematic diagram schematically showing the installation position of a lighting lamp according to an embodiment of the present invention;

[0039] Figure 6 A schematic diagram showing a cable arrangement according to another embodiment of the present invention;

[0040] Figure 7 A schematic diagram schematically shows the structure of a high-speed camera mounting bracket and a panoramic camera mounting bracket according to another embodiment of the present invention;

[0041] Figure 8 The following schematically shows a working flow chart of a particle image velocimetry system based on a vacuum chamber of a weightless aircraft according to another embodiment of the present invention.

[0042] The corresponding relationship between the reference numerals and component names is as follows:

[0043] 1. High-speed image acquisition subsystem; 2. Panoramic image acquisition subsystem; 3. Lighting subsystem; 4. Control subsystem; 5. Mechanical structure subsystem; 6. Weightless aircraft vacuum chamber;

[0044] 11. High-speed camera collector; 12. High-speed camera; 13. Camera calibration device; 14. Impact-resistant lens; 15. High-speed camera composite cable;

[0045] 21. Panoramic camera; 22. USB data cable for panoramic camera; 23. Power cable for panoramic camera;

[0046] 31. Lighting controller; 32. High-brightness background lighting; 33. Panoramic lighting; 34. Lighting power supply cable; 35. Through-cabin electrical connector;

[0047] 341. Cabin lighting power supply cable; 342. Cabin lighting power supply cable;

[0048] 41. Portable industrial computer; 42. Camera synchronization trigger; 43. Camera setting and control software; 44. Image data analysis software; 45. Synchronous trigger cable; 46. Power filter;

[0049] 51. High-speed camera mounting bracket; 52. Panoramic camera mounting bracket; 53. Integrated operating platform; 54. Observation window assembly;

[0050] 501, support arm; 502, first fixed through slot; 503, second fixed through slot; 504, support plate;

[0051] 61. Observation window; 62. Fixed flange; 63. Hatch door. DETAILED DESCRIPTION

[0052] The description of the embodiments of this specification should be combined with the corresponding drawings, which should be considered as part of the complete specification. In the drawings, the shape or thickness of the embodiments may be enlarged and indicated for simplification or convenience. Furthermore, the parts of each structure in the drawings will be described separately. It is worth noting that the elements not shown in the drawings or not described in words are in a form known to ordinary technicians in the relevant technical field.

[0053] The description of the embodiments herein and any reference to directions and orientations are only for the convenience of description and are not to be construed as any limitation on the scope of protection of the present invention. The following description of the preferred embodiments may involve combinations of features, which may exist independently or in combination, and the present invention is not particularly limited to the preferred embodiments. The scope of the present invention is defined by the claims.

[0054] like Figure 1 As shown, a particle image velocimetry system based on a vacuum cabin of a weightless aircraft of the present invention comprises a high-speed image acquisition subsystem 1, a panoramic image acquisition subsystem 2, an illumination subsystem 3, a control subsystem 4 and a mechanical structure subsystem 5, and the velocimetry system is installed on a vacuum cabin 6 of a weightless aircraft.

[0055] The high-speed image acquisition subsystem 1 includes a high-speed camera collector 11 and a plurality of high-speed cameras 12 arranged in sequence along the side wall of the vacuum chamber 6 of the weightless aircraft. The high-speed cameras 12 are electrically connected to the high-speed camera collector 11 .

[0056] According to a technical solution of the present invention, the high-speed camera 12 is a large-array grayscale high-speed camera. An impact-resistant lens 14 is provided on the high-speed camera 12. The large-array grayscale high-speed camera is electrically connected to the high-speed camera collector 11 via a high-speed camera composite cable.

[0057] The large-array grayscale high-speed camera adopts a miniaturized impact-resistant high-speed camera, and is equipped with an impact-resistant lens 14, with a total pixel of 2 million and a full-frame maximum working rate of 200fps. It can withstand a three-axis impact response of 20g and 11ms, and is more suitable for the vibration impact environment on the weightless aircraft. The high-speed camera acquisition controller has the ability to connect multiple large-array grayscale high-speed cameras at the same time, and can receive control instructions such as camera working parameter settings and camera triggers from the host computer, as well as the data transmission function of transmitting the image signals collected by multiple large-array grayscale high-speed cameras at the front end to the host computer. At the same time, it can respond to external trigger instructions and transmit the front-end 4 large-array grayscale high-speed cameras in real time for synchronous work. The number of high-speed cameras 12 can be set according to the size of the vacuum chamber 6 of the weightless aircraft, and is generally set to 3-8.

[0058] In order to solve the problem that traditional velocity measurement systems cannot track particle velocity throughout the entire process, this method uses multiple high-speed cameras to take relay shots, which can not only ensure the full-process tracking and shooting of key links of particles of different particle sizes, but also reduce the field of view of each high-speed camera to a certain range, thereby improving the spatial size resolution represented by each pixel and improving the measurement accuracy.

[0059] According to a technical solution of the present invention, the high-speed image acquisition subsystem 1 further includes a camera calibration device 13 for calibrating a plurality of high-speed cameras 12. The camera calibration device 13 may be a ceramic checkerboard.

[0060] The panoramic image acquisition subsystem 2 includes at least two sets of panoramic cameras 21, which are respectively arranged at the upper and lower parts of the vacuum chamber 6 of the weightless aircraft, and are used to obtain panoramic images in the chamber from upper and lower directions.

[0061] According to a technical solution of the present invention, the panoramic camera 21 can be electrically connected to the control subsystem connection 4 via the panoramic camera USB data cable 22 and the panoramic camera power cable 23 to improve the integration and unification of the system without the need for an additional panoramic camera recorder, thereby reducing the number of system devices and the complexity of the system.

[0062] The lighting subsystem 3 includes a lighting controller 31, a plurality of sets of high-brightness background lightings 32 and at least two sets of panoramic lightings 33. The lighting controller 31 is electrically connected to the high-brightness background lightings 32 and the panoramic lightings 33. The high-brightness background lightings 32 and the panoramic lightings 33 are respectively arranged in one-to-one correspondence with the high-speed camera 12 and the panoramic camera 21;

[0063] According to a technical solution of the present invention, a high-brightness background lighting lamp 32 is arranged on the inner wall of the vacuum chamber 6 of the weightless aircraft, at a position opposite to the axis of the high-speed camera 12;

[0064] Two sets of panoramic lighting lamps 33 are respectively arranged on the top and bottom of the vacuum chamber 6 of the weightless aircraft;

[0065] The highlight background lighting 32 and the panoramic lighting 33 are connected to the lighting controller 31 through the lighting power supply cable 34. The lighting power supply cable 34 includes an in-cabin lighting power supply cable 341 arranged in the vacuum cabin 6 of the weightless aircraft and an out-cabin lighting power supply cable 342 arranged outside the vacuum cabin 6 of the weightless aircraft. The in-cabin lighting power supply cable 341 and the out-cabin lighting power supply cable 342 are connected via a through-cabin electrical connector 35.

[0066] According to a technical solution of the present invention, the control mode of the lighting controller 31 includes a normal lighting mode and a strong light lighting mode.

[0067] The control subsystem 4 includes a portable industrial computer 41, a camera synchronization trigger 42, a camera setting and control software 43, an image data analysis software 44 and a synchronization trigger cable 45. The portable industrial computer 41 is electrically connected to the high-speed camera collector 11, the camera synchronization trigger 42, and the lighting controller 31. The camera synchronization trigger 42 is electrically connected to the high-speed camera 12 and the panoramic camera 21 through the synchronization trigger cable 45, and is used to synchronously trigger the high-speed camera 12 and the panoramic camera 21; the camera setting and control software 43 and the image data analysis software 44 are built in the portable industrial computer 41, and the high-speed camera collector 11 is electrically connected to the portable industrial computer 41.

[0068] The control subsystem 4 adopts an integrated and integrated design. A portable industrial computer 41 can complete the control of all acquisition devices. At the same time, the portable industrial computer 41 can directly control the panoramic camera and collect and store the image data of the panoramic camera through its own USB3.0 interface and USB cable, without the need for an additional acquisition recorder for the panoramic camera. This integrated design, on the basis of further reducing the complexity of the system equipment, is more convenient for the on-board operator to operate, and can also directly reduce the number of original test system operators from 3 to 1, thereby avoiding the problem of poor communication between on-board system operators due to the noise in the cabin. At the same time, the simplified operation process is easier to master, reducing the professional requirements for operators.

[0069] According to a technical solution of the present invention, the control subsystem 4 further includes a power filter 46, and the power filter 46 is arranged between the control subsystem 4 and the onboard power supply of the weightless aircraft;

[0070] A decoupling capacitor is connected in series to the ground line connecting the integrated operating platform 53 and the body of the weightless aircraft.

[0071] According to a technical solution of the present invention, the cable used in the system is a cable with a shielding layer, and the exterior of the synchronous trigger cable 45 is coated with a shielding protective tape.

[0072] The control subsystem 4 forms an electromagnetic interference filtering device through a power filter 46, a decoupling capacitor, a cable with a shielding layer, and a shielding protective tape, which can effectively avoid the influence of electromagnetic interference on the speed measurement system equipment and the accuracy of the measurement results, and improve the speed measurement system's ability to resist electromagnetic interference.

[0073] The mechanical structure subsystem 5 is used to install the control subsystem 4 on the outer side of the vacuum chamber 6 of the weightlessness aircraft. The mechanical structure subsystem 5 includes a high-speed camera mounting bracket 51 and a panoramic camera mounting bracket 52 , an observation window assembly 54 and an integrated operating platform 53 .

[0074] The high-speed camera mounting bracket 51 and the panoramic camera mounting bracket 52 are used to mount the high-speed camera 12 and the panoramic camera 21. The observation window assembly 54 is arranged on the side of the weightless aircraft vacuum chamber 6, and includes an observation window 61 and a fixing flange portion 62 arranged on the periphery of the observation window 61. The high-speed camera mounting bracket 51 and the panoramic camera mounting bracket 52 are mounted on the observation window 61 through the fixing flange portion 62.

[0075] The integrated operating platform 53 is fixed on the outer side of the vacuum chamber 6 of the weightless aircraft and is used to install the high-speed camera collector 11 , the lighting controller 31 , the portable industrial computer 41 and the camera synchronization trigger 42 .

[0076] According to a technical solution of the present invention, Figure 7 As shown, the high-speed camera mounting bracket 51 and the panoramic camera mounting bracket 52 include two support arms 501 and a support plate 504. The two support arms 501 arranged opposite to each other include a support arm body arranged perpendicular to the side wall of the weightless aircraft vacuum chamber 6 and a fixing plate protruding along the side of the support arm body, and the fixing plate is provided with a first fixing through groove 502 arranged along the length direction of the weightless aircraft vacuum chamber 6, and the bolt passes through the first fixing through groove 502 and is fixed to the fixing flange part 62. By adjusting the position of the bolt in the first fixing through groove 502, the position adjustment of the high-speed camera 12 and the panoramic camera 21 arranged on the high-speed camera mounting bracket 51 and the panoramic camera mounting bracket 52 in the up and down direction can be achieved.

[0077] A second fixed through slot 503 is provided on the support arm body along the length direction of the support arm body, and a support plate 504 is provided between the two support arm bodies. Both ends of the support plate 504 are fixed to the support arm body by coaxially arranged bolts, and the bolts are arranged in the second fixed through slot 503. By adjusting the position of the bolts in the second fixed through slot 503, the position of the high-speed camera 12 and the panoramic camera 21 arranged on the high-speed camera mounting bracket 51 and the panoramic camera mounting bracket 52 in the front-to-back direction can be adjusted; at the same time, the bolts at both ends of the support plate 504 are coaxially arranged, and the pitch angle of the support plate 504 can be adjusted after loosening the bolts, and then the pitch angle can be fixed by tightening the bolts, thereby realizing the adjustment of the pitch angle of the high-speed camera 12 and the panoramic camera 21.

[0078] The working process of the present invention is as follows:

[0079] Installation of speed measurement system:

[0080] A window is opened on the vacuum cabin 6 of the weightless aircraft, and an observation window assembly 54 is installed. The observation window 61 is composed of high-transmittance fused quartz glass and a sealing ring. The fixed flange part 62 is installed on the periphery of the observation window 61. The installation position is as follows: Figure 2 shown.

[0081] A high-speed camera mounting bracket 51 and a panoramic camera mounting bracket 52 are mounted on the observation window assembly, and a comprehensive operating platform 53 is mounted on the outer wall of the vacuum chamber 6 of the weightless aircraft. The mounting positions are as follows: Figure 3 shown.

[0082] The high-speed camera 12 and the panoramic camera 21 are installed on the high-speed camera mounting bracket 51 and the panoramic camera mounting bracket 52. The high-speed camera collector 11, the lighting controller 31, the camera synchronization trigger 42 and the portable industrial computer 41 are installed on the integrated operation platform 53.

[0083] High-brightness background lighting lamps 32 are respectively installed at positions opposite to the axis of the high-speed camera 12 on the inner wall of the vacuum chamber 6 of the weightless aircraft, and two sets of panoramic lighting lamps 33 are respectively installed on the top and bottom of the vacuum chamber 6 of the weightless aircraft. Figure 5 shown.

[0084] The cables of the system are laid, wherein the in-cabin lighting supply cable 34 and the out-cabin lighting supply cable are connected through the through-cabin electrical connector 35 on the vacuum cabin 6 of the weightless aircraft. The cable layout diagram is shown in FIG. Figure 6 shown.

[0085] The camera setting and control software 43 and the image data analysis software 44 are installed on the operating system of the portable industrial computer 41 .

[0086] After installation, the pitch angle, lens aperture and focus of the high-speed camera 12 and the panoramic camera 21 are adjusted according to the installation position of the planetary probe sampler installed in the vacuum cabin 6 of the weightless aircraft.

[0087] Install electromagnetic interference filtering device: install power filter 46 between this system and the onboard power supply of the weightless aircraft; connect decoupling capacitor in series in the connecting ground wire between the system housing and the aircraft body, and after installation, start the power supply to start working.

[0088] The working process of the speed measurement system is as follows:

[0089] like Figure 7 As shown, firstly, the main power switch on the weightless aircraft is powered on to power up the portable industrial computer 41, and the high-speed camera acquisition controller 11 and the lighting controller 31 are powered on by the portable industrial computer 41 to control the high-speed camera 12 and the panoramic camera 21 to turn on, and the lighting controller 31 controls the lighting to switch to the normal lighting mode. The internal and external parameters of the high-speed camera 12 are calibrated by the camera calibration device 13, and the parameters of the high-speed camera 12 and the panoramic camera 21 are set by the camera setting and control software 43, so that the high-speed camera 12 and the panoramic camera 21 enter the waiting state.

[0090] According to the test needs, choose whether to switch the lighting mode to the strong light lighting mode. According to the test trigger instruction, control the camera synchronization trigger 42 to synchronously trigger the high-speed camera 12 and the panoramic camera 21. The high-speed camera 12 and the panoramic camera 21 record the test data and transmit them to the portable industrial computer 41. The portable industrial computer 41 turns off the high-speed camera 12, the lighting, the panoramic camera 21 and the system power supply, and analyzes and processes the test data through the image data analysis software 44.

[0091] It should be noted that, in this article, the terms "include", "comprises" or any other variations thereof are intended to cover non-exclusive inclusion, so that a process, method, article or terminal device including a series of elements includes not only those elements, but also other elements not explicitly listed, or also includes elements inherent to such process, method, article or terminal device. In the absence of further restrictions, the elements defined by the sentence "comprises a ..." do not exclude the existence of other identical elements in the process, method, article or terminal device including the elements.

[0092] Finally, it should be noted that the above is a preferred embodiment of the present invention. It should be pointed out that although the preferred embodiment of the present invention has been described, for those skilled in the art, once the basic creative concept of the present invention is known, several improvements and modifications can be made without departing from the principles of the present invention, and these improvements and modifications should also be regarded as the protection scope of the present invention. Therefore, the attached claims are intended to be interpreted as including the preferred embodiment and all changes and modifications that fall within the scope of the embodiments of the present invention.

Claims

1. A particle image velocimetry system based on a vacuum chamber of a weightless aircraft, characterized in that: include: A high-speed image acquisition subsystem (1) comprises a high-speed camera collector (11) and a plurality of high-speed cameras (12) arranged in sequence along the side wall of a vacuum chamber (6) of a weightless aircraft, wherein the high-speed cameras (12) are electrically connected to the high-speed camera collector (11); A panoramic image acquisition subsystem (2) includes at least two sets of panoramic cameras (21), which are respectively arranged at the upper part and the lower part of the vacuum chamber (6) of the weightless aircraft; The lighting subsystem (3) comprises a lighting controller (31), a plurality of sets of high-brightness background lightings (32) and at least two sets of panoramic lightings (33); the lighting controller (31) is electrically connected to the high-brightness background lightings (32) and the panoramic lightings (33); the high-brightness background lightings (32) and the panoramic lightings (33) are respectively arranged in a one-to-one correspondence with the high-speed camera (12) and the panoramic camera (21); The control subsystem (4) comprises a portable industrial computer (41), a camera synchronization trigger (42), a camera setting and control software (43), an image data analysis software (44) and a synchronization trigger cable (45); the portable industrial computer (41) is electrically connected to the high-speed camera collector (11), the camera synchronization trigger (42) and the lighting controller (31); the camera synchronization trigger (42) is electrically connected to the high-speed camera (12) and the panoramic camera (21) through the synchronization trigger cable (45) for synchronously triggering the high-speed camera (12) and the panoramic camera (21); the camera setting and control software (43) is built in the portable industrial computer (41); the high-speed camera collector (11) is electrically connected to the portable industrial computer (41); It also includes a mechanical structure subsystem (5) which is arranged on the outer side of the vacuum chamber (6) of the weightless aircraft. The mechanical structure subsystem (5) includes: A high-speed camera mounting bracket (51) and a panoramic camera mounting bracket (52), used for mounting the high-speed camera (12) and the panoramic camera (21); An observation window assembly (54) is arranged on the side of the vacuum chamber (6) of the weightless aircraft, comprising an observation window (61) and a fixing flange portion (62) arranged on the periphery of the observation window (61), wherein the high-speed camera mounting bracket (51) and the panoramic camera mounting bracket (52) are mounted on the observation window (61) via the fixing flange portion (62); The integrated operating platform (53) is fixed on the outer side of the vacuum chamber (6) of the weightless aircraft and is used to install the high-speed camera collector (11), the lighting controller (31), the portable industrial computer (41) and the camera synchronization trigger (42).

2. The particle image velocimetry system based on the vacuum chamber of a weightless aircraft according to claim 1, characterized in that: The high-speed camera mounting bracket (51) and the panoramic camera mounting bracket (52) both include: Two supporting arms (501) arranged opposite to each other comprise a supporting arm body arranged perpendicular to the side wall of the weightless aircraft vacuum chamber (6) and a fixing plate protruding from the side of the supporting arm body, wherein the fixing plate is provided with a first fixing through groove (502) arranged along the length direction of the weightless aircraft vacuum chamber (6); and the supporting arm body is provided with a second fixing through groove (503) arranged along the length direction of the supporting arm body; The support plate (504) is arranged between the two support arm bodies, and its two ends are fixed to the support arm bodies by coaxially arranged bolts, and the bolts are arranged in the second fixing through groove (503).

3. The particle image velocimetry system based on the vacuum chamber of a weightless aircraft according to claim 1, characterized in that: The high-brightness background lighting lamp (32) is arranged on the inner wall of the vacuum chamber (6) of the weightless aircraft, at a position opposite to the axis of the high-speed camera (12); The two groups of panoramic lighting lamps (33) are respectively arranged on the top and bottom of the vacuum cabin (6) of the weightless aircraft; The highlight background lighting (32) and the panoramic lighting (33) are connected to the lighting controller (31) via a lighting power supply cable (34); the lighting power supply cable (34) comprises an in-cabin lighting power supply cable (341) arranged in a vacuum cabin (6) of the weightless aircraft and an out-cabin lighting power supply cable (342) arranged outside the vacuum cabin (6) of the weightless aircraft; the in-cabin lighting power supply cable (341) and the out-cabin lighting power supply cable (342) are butt-jointed via a through-cabin electrical connector (35).

4. The particle image velocimetry system based on the vacuum chamber of a weightless aircraft according to claim 1, characterized in that: The control subsystem (4) further comprises a power filter (46), wherein the power filter (46) is arranged between the control subsystem (4) and an onboard power supply of the weightless aircraft; A decoupling capacitor is connected in series to the ground line connected between the integrated operating platform (53) and the body of the weightless aircraft.

5. The particle image velocimetry system based on the vacuum chamber of a weightless aircraft according to claim 1, characterized in that: The high-speed camera (12) is a large-area grayscale high-speed camera. An impact-resistant lens (14) is provided on the high-speed camera (12). The large-area grayscale high-speed camera is electrically connected to the high-speed camera collector (11) via a high-speed camera composite cable (15).

6. The particle image velocimetry system based on the vacuum chamber of a weightless aircraft according to claim 1, characterized in that: The panoramic camera (21) is electrically connected to the portable industrial computer (41) via a panoramic camera USB data cable (22) and a panoramic camera power cable (23).

7. The particle image velocimetry system based on a weightless aircraft vacuum chamber according to claim 1, characterized in that: The cable used in the system is a cable with a shielding layer, and the exterior of the synchronous trigger cable (45) is coated with a shielding protective tape.

8. The particle image velocimetry system based on the vacuum chamber of a weightless aircraft according to claim 1, characterized in that: The control modes of the lighting lamp controller (31) include a normal lighting mode and a strong light lighting mode.

9. The particle image velocimetry system based on a weightless aircraft vacuum chamber according to claim 1, characterized in that: The high-speed image acquisition subsystem (1) further comprises a camera calibration device (13) for calibrating a plurality of the high-speed cameras (12).

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