A miniaturized space-borne wind lidar device based on DASH

Abstract

The application discloses a miniaturized spaceborne wind measuring interferometer device based on DASH and belongs to the technical field of optical mechanical structures. In order to solve the problems of complex structure and large volume of the existing spaceborne wind measuring interferometer, the device comprises an electronic box, a front light collecting lens group, a mounting bottom plate, a rear projection lens group, a CCD camera, a collimating lens group, a support frame one, a cubic prism, an interference unit, a support frame two, a krypton lamp, a prism support and a camera support. The front light collecting lens group comprises a lens one, a folding mirror one, a folding mirror two and a lens two which are sequentially arranged along an optical axis. The rear projection lens group comprises a lens three, a folding mirror three and a lens four which are sequentially arranged along the optical axis. The collimating lens group comprises a lens five and a folding mirror four which are sequentially arranged along the optical axis. In the device, the folded light path is folded through the folding mirror group for multiple times. The device occupies a small volume, the internal space utilization rate of the spaceborne wind measuring interferometer load is improved, the weight of the instrument is smaller, the carrying cost is reduced, and the instrument is more stable and reliable during work.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of optical mechanical structures, and particularly relates to a miniaturized spaceborne wind measuring instrument device based on DASH. BACKGROUND

[0002] Existing wind measuring methods include balloon wind measurement and satellite wind measurement, wherein satellite wind measurement mainly includes two methods, one of which is to use a meteorological satellite to continuously track the movement of a fixed balloon to observe wind direction and wind speed, and the other of which is to calculate wind direction and wind speed from the movement of clouds on a cloud image of a stationary satellite. However, this wind measuring method uses clouds as tracers, so it can only measure wind speed in places where there are clouds.

[0003] In order to meet the global all-weather wind speed detection requirement, wind speed is solved by using the optical Doppler principle, and wind speed is detected by using a Doppler asymmetric difference interference technology (DASH). The DASH interferometer uses airglow to detect particle light in the middle and upper atmosphere, thereby measuring wind speed. Airglow provides a light source required by passive wind field detection instruments, and is mainly divided into oxygen atom and oxygen molecule, OH, N2 and the like. The DASH interferometer uses the principle of light interference to determine wind speed and direction. When air flows, it changes the relative path of light, causing the interference fringes to change, and by analyzing these interference fringes, the speed and direction of air flow can be calculated, so as to determine the wind speed.

[0004] Referring to the device disclosed in the article entitled "Michelson Interferometer for Global High-resolution Thermospheric Imaging (MIGHTI): Monolithic Interferometer Design and Test" published by Harlander et al., the device comprises a light shield and a main functional part. The main functional part detects the atmospheric wind field based on the Doppler asymmetric difference technology, and comprises a large number of photoelectric components. The volume of the light shield is similar to that of the main functional part of the instrument, and the mechanical structure assembly is relatively complex. The device has a large volume due to a large number of components, and the implementation scheme is complex. SUMMARY

[0005] The application discloses a miniaturized spaceborne wind measuring instrument device based on DASH, which solves the problems of complex structure and large volume of the existing spaceborne wind measuring interferometer.

[0006] The technical solution of the application is as follows:

[0007] A miniaturized DASH spaceborne wind measuring device, comprising an electronic box, a front light collecting lens group, a mounting base plate, a rear projection lens group, a CCD camera, a collimating lens group, a support frame one, a cubic prism, an interference unit, a support frame two, a krypton lamp, a prism support and a camera support;

[0008] The electronic box is mounted on the mounting base plate;

[0009] The front light collecting lens group comprises, in sequence along an optical axis, a lens one, a turning mirror one, a turning mirror two and a lens two; each lens and turning mirror is fixed by a lens barrel;

[0010] The rear projection lens group comprises, in sequence along an optical axis, a lens three, a turning mirror three and a lens four; each lens and turning mirror is fixed by a lens barrel.

[0011] The interference unit comprises a box body and an interference prism fixed in the box body;

[0012] The interference unit is mounted on the mounting base plate;

[0013] The front light collecting lens group is mounted at an entrance of the box body of the interference unit, and the rear projection lens group is mounted at an exit of the box body; the cubic prism is arranged in front of the entrance of the front light collecting lens group, the cubic prism is mounted on the prism support, and the prism support is mounted on the mounting base plate; the CCD camera is arranged at the exit of the rear projection lens group, the CCD camera is mounted on the camera support, the camera support is mounted on the mounting base plate, and the CCD camera is connected with an FPGA in the electronic box;

[0014] An imaging surface of the CCD camera coincides with an imaging surface of the rear projection lens group;

[0015] The support frame one is mounted separately from the front light collecting lens group; the front light collecting lens group passes through a lower layer of the support frame one to ensure that the two are not in direct contact; an upper layer of the support frame one has an annular structure, and the bottom is fixed on the mounting base plate;

[0016] The collimating lens group comprises, in sequence along an optical axis, a lens five and a turning mirror four; each lens and turning mirror is fixed by a lens barrel;

[0017] The lens barrels of the collimating lens group are connected through flanges, and the annular structure of the upper layer of the support frame one is used to fix and mount the collimating lens group;

[0018] The support frame two is mounted at the rear projection lens group, and the krypton lamp is fixed on the upper layer of the support frame two;

[0019] The support frame two is installed separately from the rear projection lens group, the rear projection lens group passes through the lower layer of the support frame two to ensure that the two are not in direct contact, the support frame two is located above the rear projection lens group lens barrel through buckling of the frame of the support frame, and the bottom is fixed on the mounting bottom plate.

[0020] The beneficial effects of the present application are:

[0021] 1. The device adopts a multi-device combined installation, which is more flexible and easier to expand and replace.

[0022] 2. The folding light path in the optical system in the present application is folded through multiple use of the folding mirror group, the device occupies a small volume, the utilization rate of the internal space of the satellite-borne wind interferometer load is improved, the instrument weight is smaller, the carrying cost is reduced, and more space can be provided for heat dissipation, so that the instrument is more stable and reliable during operation. BRIEF DESCRIPTION OF DRAWINGS

[0023] Figure 1 It is a schematic diagram of a miniaturized satellite-borne wind instrument device based on DASH.

[0024] Wherein: 1 is an electronic box, 2 is a front light collecting lens group, 2-1 is a lens one, 2-2 is a folding mirror one, 2-3 is a folding mirror two, 2-4 is a lens two, 3 is a mounting bottom plate, 4 is a rear projection lens group, 4-1 is a lens three, 4-2 is a folding mirror three, 4-3 is a lens four, 5 is a CCD camera, 6 is a collimating lens group, 7 is a support frame one, 8 is a cubic prism, 9 is an interference unit, 9-1 is a box body, 9-2 is an interference prism, 10 is a support frame two, 11 is a krypton lamp, 12 is a prism support, and 13 is a camera support.

[0025] Figure 2 It is a structure schematic view of the support frame one in the present application: 2 is a front light collecting lens group, 3 is a mounting bottom plate, 6 is a collimating lens group, 6-1 is a lens five, 6-2 is a folding mirror four, 7 is a support frame one, and 8 is a cubic prism.

[0026] Figure 3 It is a structure schematic view of the support frame two in the present application: 3 is a mounting bottom plate, 4 is a rear projection lens group, 4-1 is a lens three, 4-2 is a folding mirror three, 4-3 is a lens four, 10 is a support frame two, and 11 is a krypton lamp. DETAILED DESCRIPTION

[0027] The present application will be further described and explained in conjunction with the accompanying drawings.

[0028] As Figure 1As shown, a miniaturized DASH spaceborne wind measurement device includes an electronic box 1, a front light receiving lens group 2, a mounting base plate 3, a rear projection lens group 4, a CCD camera 5, a collimating lens group 6, a support frame 7, a cubic prism 8, an interference unit 9, a support frame 10, a krypton lamp 11, a prism support 12, and a camera support 13.

[0029] The electronic box 1 is internally provided with an FPGA, and has an aluminum cubic structure.

[0030] The electronic box 1 is installed on the mounting base plate 3 by means of a heat insulation pad and screws.

[0031] The front light receiving lens group 2 comprises, in sequence along an optical axis, a lens 2-1, a folding mirror 2-2, a folding mirror 2-3, and a lens 2-4. Each lens and folding mirror is fixed by a lens barrel.

[0032] The rear projection lens group 4 comprises, in sequence along an optical axis, a lens 4-1, a folding mirror 4-2, and a lens 4-3. Each lens and folding mirror is fixed by a lens barrel.

[0033] The interference unit 9 comprises a box 9-1 and an interference prism 9-2 fixed inside the box.

[0034] The interference unit 9 is installed on the mounting base plate 3 by means of a heat insulation pad and screws. The interference unit 9 can be adjusted in angle and height.

[0035] The front light receiving lens group 2 is installed at an entrance of the box 9-1 of the interference unit 9, and the rear projection lens group 4 is installed at an exit of the box 9-1 of the interference unit 9. The cubic prism 8 is arranged in front of the entrance of the front light receiving lens group 2, and is installed in the prism support 12. The CCD camera 5 is arranged at the exit of the rear projection lens group 4, and is installed on the camera support 13. The CCD camera 5 is connected to the FPGA in the electronic box 1.

[0036] The lens barrels of the front light receiving lens group 2 are connected by flanges. The exit of the front light receiving lens group 2 is aligned with the interference prism 9-2 in the interference unit 9, and is connected to the entrance of the box 9-1 of the interference unit 9 by flanges.

[0037] The lens barrels of the rear projection lens group 4 are connected by flanges. The entrance of the rear projection lens group 4 is aligned with the interference prism 9-2 in the interference unit 9, and is connected to the exit of the box 9-1 of the interference unit 9 by flanges.

[0038] The cubic prism 8 is arranged in front of the entrance of the front light receiving lens group 2, and is installed on the mounting base plate 3 by the prism support 12.

[0039] The CCD camera 5 is positioned and mounted on the mounting base 3 via the camera bracket 13, so that the imaging surface of the CCD camera 5 coincides with the imaging surface of the rear projection lens group 4.

[0040] like Figure 2 As shown, the support frame 7 is installed separately from the front focusing lens assembly 2. The front focusing lens assembly 2 passes through the lower layer of the support frame 7 to ensure that the two do not come into direct contact. The upper layer of the support frame 7 has a ring structure, and the bottom is fixed to the mounting base plate 3 by heat insulation pads and screws to ensure the stability and heat insulation effect of the overall device.

[0041] The collimating lens group 6 contains a lens 6-1 and a folding mirror 6-2 arranged sequentially along the optical axis. Each lens and folding mirror is surrounded and fixed by a lens tube.

[0042] The collimating lens group 6 is connected by flanges, and the collimating lens group 6 is fixedly installed by the annular structure on the upper layer of the support frame 7.

[0043] like Figure 3 As shown, a support frame 2 10 is installed at the rear projection lens group 4, and the krypton lamp 11 is fixed above the support frame 2 10.

[0044] The support frame 2 10 is installed separately from the rear projection lens assembly 4. The rear projection lens assembly 4 passes through the lower layer of the support frame 2 10 to ensure that the two do not come into direct contact. The support frame 2 10 is positioned on top of the lens barrel of the rear projection lens assembly 4 by a snap-fit ​​method, and the bottom is fixed to the mounting base plate 3 by heat insulation pads and screws.

[0045] The working process of this invention:

[0046] External gas glow enters the front receiving mirror group 2 through the cubic prism 8. The light rays pass through lens 1 2-1 and folding mirror 1 2-2 to form a primary image point, and then pass through folding mirror 2-3 and lens 2-4 to produce parallel light that enters the interference unit 9. The light rays interfere at the interference prism 9-2. The light rays after interference enter the rear projection mirror 4, and after being reflected by folding mirror 3 4-2, they converge through lens 3 4-1 and lens 4-3 to form an image on the CCD camera 5.

[0047] Krypton lamp 11 serves as the internal calibration light source, entering collimating lens group 6 via optical fiber. The light is parallelized by lens 5 6-1 and reflected by folding mirror 4 6-2 before entering cubic prism 8. The light then enters front receiving lens group 2 via cubic prism 8. A primary image point is formed by lens 1 2-1 and folding mirror 1 2-2, and then parallelized by folding mirror 2-3 and lens 2-4 before entering interference unit 9. Interference occurs at interference prism 9-2. The interfered light enters rear projection mirror 4, is reflected by folding mirror 3 4-2, and then converges through lens 3 4-1 and lens 4-3 to form an image on CCD camera 5.

[0048] The specific installation steps of the miniaturized spaceborne wind measuring instrument device based on DASH are as follows.

[0049] Step 1: thermally insulating installation of the interference unit 9 on the installation base plate 3;

[0050] Step 2: assembly of the turning mirror group one 2-1 and the turning mirror group two 2-2 of the front light collecting lens group 2 together, and then installation of the front light collecting lens group 2 on the light inlet of the box body 9-1 of the interference unit 9;

[0051] Step 3: assembly of the turning mirror group three 4-1 and the straight mirror group 4-2 of the rear projection lens group 4 together, and then installation of the rear projection lens group 4 on the light outlet of the box body 9-1 of the interference unit 9;

[0052] Step 4: positioning and installation of the CCD camera 5 on the installation base plate 3 through the camera support 13;

[0053] Step 5: installation of the support frame one 7 at the rear projection lens group 4 and thermally insulating installation on the installation base plate 3;

[0054] Step 6: installation of the krypton lamp 11 on the support frame one 7;

[0055] Step 7: installation of the support frame two 10 at the front light collecting lens group 2 and thermally insulating installation on the installation base plate 3;

[0056] Step 8: installation of the collimating lens group 6 on the support frame two 10;

[0057] Step 9: installation of the cubic prism 8 at the front end of the light inlet of the front light collecting lens group 2, and installation of the cubic prism 8 on the installation base plate 3 through the prism support 12;

[0058] Step 10: use of the snap-fit mode to cover the entire optical system with the shell to provide a protection function and ensure that the optical system is not affected by the external environment;

[0059] Step 11: installation of the electronic box 1 on the installation base plate 3.

Claims

1. A miniaturized DASH space-borne wind measuring device, characterized in that, It includes electronic box (1), pre light collection lens group (2), mounting base plate (3), rear projection lens group (4), CCD camera (5), collimating lens group (6), support frame one (7), cubic prism (8), interference unit (9), support frame two (10), krypton lamp (11), prism support (12) and camera support (13); The electronic box (1) is mounted on the mounting base plate (3); The pre light collection lens group (2) contains lens one (2-1), turning mirror one (2-2), turning mirror two (2-3) and lens two (2-4) arranged in sequence along the optical axis, and the periphery of each lens and turning mirror is fixed by a lens barrel; The rear projection lens group (4) contains lens three (4-1), turning mirror three (4-2) and lens four (4-3) arranged in sequence along the optical axis, and the periphery of each lens and turning mirror is fixed by a lens barrel; The interference unit (9) includes a box body (9-1) and an interference prism (9-2) fixed inside the box body (9-1); The interference unit (9) is mounted on the mounting base plate (3); The pre light collection lens group (2) is mounted at the light inlet of the box body (9-1) of the interference unit (9), and the rear projection lens group (4) is mounted at the light outlet of the box body (9-1); The cubic prism (8) is arranged in front of the light inlet of the pre light collection lens group (2), the cubic prism (8) is mounted on the prism support (12), and the prism support (12) is mounted on the mounting base plate (3); The CCD camera (5) is arranged at the light outlet of the rear projection lens group (4), the CCD camera (5) is mounted on the camera support (13), the camera support (13) is mounted on the mounting base plate (3), and the CCD camera (5) is connected with the FPGA in the electronic box (1); The imaging surface of the CCD camera (5) coincides with the imaging surface of the rear projection lens group (4); The support frame one (7) is separately mounted with the pre light collection lens group (2); The pre light collection lens group (2) passes through the lower layer of the support frame one (7) to ensure that the two are not in direct contact; The upper layer of the support frame one (7) has an annular structure, and the bottom is fixed on the mounting base plate (3); The collimating lens group (6) contains lens five (6-1) and turning mirror four (6-2) arranged in sequence along the optical axis, and the periphery of each lens and turning mirror is fixed by a lens barrel; The lens barrels of the collimating lens group (6) are connected through flanges, and the annular structure of the upper layer of the support frame one (7) is used to fix and mount the collimating lens group (6); The support frame two (10) is mounted at the rear projection lens group (4), and the krypton lamp (11) is fixed on the upper layer of the support frame two (10); The support frame two (10) is separately mounted with the rear projection lens group (4), the rear projection lens group (4) passes through the lower layer of the support frame two (10) to ensure that the two are not in direct contact; The support frame two (10) is fixed on the mounting base plate (3) by buckling the frame of the support frame above the lens barrel of the rear projection lens group (4).

2. The miniaturized DASH space-borne wind measuring device according to claim 1, characterized in that The electronic box (1) is internally provided with FPGA, which undertakes data communication transmission function, and the outer surface is an aluminum cubic structure.

3. The miniaturized DASH space-borne wind measuring device according to claim 1, characterized in that, The front light collection lens group (2) is connected by flange between each lens barrel, and the light outlet of the front light collection lens group (2) is aligned with the interference prism (9-2) in the interference unit (9), which is connected by flange at the light inlet of the box (9-1) of the interference unit (9).

4. The miniaturized DASH space-borne wind measuring device according to claim 1, characterized in that, The rear projection lens group (4) is connected by flange between each lens barrel, and the light inlet of the rear projection lens group (4) is aligned with the interference prism (9-2) in the interference unit (9), which is connected by flange at the light outlet of the box (9-1) of the interference unit (9).

5. The miniaturized DASH space-borne wind measuring device according to claim 1, characterized in that, The external air glow enters the front light collection lens group (2) through the cubic prism (8), and the light forms a primary image point through the lens one (2-1) and the turning mirror one (2-2), and then generates parallel light through the turning mirror two (2-3) and the lens two (2-4) to enter the interference unit (9), the light is interfered in the interference prism (9-2), and the light after interference enters the rear projection lens group (4), the light is reflected through the turning mirror three (4-2), and then converges to form an image on the CCD camera (5) through the lens three (4-1) and the lens four (4-3); The internal calibration light source krypton lamp (11) emits light through the optical fiber into the collimating lens group (6), the light generates parallel light through the lens five (6-1) and is reflected into the cubic prism (8) through the turning mirror four (6-2), the light enters the front light collection lens group (2) through the cubic prism (8), the light forms a primary image point through the lens one (2-1) and the turning mirror one (2-2), and then generates parallel light through the turning mirror two (2-3) and the lens two (2-4) to enter the interference unit (9), the light is interfered in the interference prism (9-2), and the light after interference enters the rear projection lens (4), the light is reflected through the turning mirror three (4-2), and then converges to form an image on the CCD camera (5) through the lens three (4-1) and the lens four (4-3).

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