Miniaturized satellite-borne wind meter device based on DASH

Abstract

The invention discloses a DASH-based miniaturized satellite-borne anemoscope device, belongs to the technical field of optical machine structures, and aims to solve the problems of complex structure and large size of an existing satellite-borne anemoscope. The device comprises an electronic box, a front light receiving lens group, a mounting bottom plate, a rear projection lens group, a CCD (Charge Coupled Device) camera, a collimating lens group, a support frame I, a cubic prism, an interference unit, a support frame II, a krypton lamp, a prism support and a camera bracket, the front light receiving lens group comprises a lens I, a turning mirror I, a turning mirror II and a lens II which are sequentially arranged along an optical axis; the rear projection lens group comprises a third lens, a third turning lens and a fourth lens which are sequentially arranged along the optical axis; the collimating lens group comprises a fifth lens and a fourth turning lens which are sequentially arranged along the optical axis; according to the device, the folded light path is folded by repeatedly utilizing the folding mirror group, the occupied volume of the device is small, so that the utilization rate of the internal space of the load of the satellite-borne wind measurement interferometer is improved, the weight of the instrument is smaller, the carrying cost is reduced, and the instrument is more stable and reliable during working.

Description

Technical Field

[0001] The invention belongs to the technical field of optical-mechanical structures, and in particular relates to a miniaturized satellite-borne anemometer device based on DASH. Background Art

[0002] The existing wind measurement methods are balloon wind measurement and satellite wind measurement. There are two main methods of satellite wind measurement. One method is to use meteorological satellites to continuously track the movement of fixed balloons to observe wind direction and wind speed. The other method is to infer wind direction and wind speed from the movement of clouds on the cloud map of geostationary satellites. However, this wind measurement method uses clouds as tracers, so wind speed can only be measured in places with clouds.

[0003] In order to meet the global demand for all-weather wind speed detection, the optical Doppler principle is used to solve the wind speed, and the Doppler asymmetric differential interferometer technology (Doppler Asymmetri Spatial Heterodyne, DASH) is used to detect the wind speed. The DASH interferometer uses the airglow phenomenon to detect particle luminescence in the middle and upper atmosphere to measure wind speed. Airglow provides the light source required for passive wind field detection instruments, which are mainly divided into oxygen atoms and oxygen molecules, OH, N2 and other types. The DASH interferometer uses the interference principle of light to determine wind speed and direction. When air flows, it changes the relative path of light, causing the interference fringes to change. By analyzing these interference fringes, the speed and direction of air flow can be calculated to determine the wind speed.

[0004] See "Space Sci Rev.", Harlander et al. published a paper titled "Michelson Interferometer for Global High-resolution Thermospheric Imaging (MIGHTI): Monolithic Interferometer Design and Test", which includes a sunshade and a main functional part. The main functional part detects the atmospheric wind field based on Doppler asymmetric differential technology and contains a large number of optoelectronic components. The volume of the sunshade of this solution 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 the large number of components, and its implementation plan is complex. Summary of the invention

[0005] In order to solve the problems of complex structure and large size of existing satellite-borne wind interferometers, the present invention proposes a miniaturized satellite-borne wind meter device based on DASH. The device has the characteristics of compact arrangement, small size, light weight and strong portability.

[0006] The technical solution of the present invention is:

[0007] A miniaturized DASH satellite-borne wind measuring device comprises an electronic box, a front light collecting mirror group, a mounting base plate, a rear projection mirror group, a CCD camera, a collimating mirror group, a first support frame, a cubic prism, an interference unit, a second support frame, a krypton lamp, a prism support and a camera bracket;

[0008] The electronic box is installed on the installation base plate;

[0009] The front light-collecting mirror group includes lens 1, folding mirror 1, folding mirror 2 and lens 2 arranged in sequence along the optical axis; the periphery of each lens and folding mirror is wrapped and fixed by a lens barrel;

[0010] The rear projection lens group includes lens 3, folding mirror 3 and lens 4 which are arranged in sequence along the optical axis; the peripheries of each lens and folding mirror are wrapped and fixed by a lens barrel.

[0011] The interference unit includes a box and an interference prism fixed inside the box;

[0012] The interference unit is installed on the installation base plate;

[0013] A front light-collecting mirror group is installed at the light entrance of the interference unit, and a rear projection mirror group is installed at the light exit of the box; a cubic prism is arranged in front of the light entrance of the front light-collecting mirror group, and the cubic prism is installed on a prism support, and the prism support is installed on a mounting base plate; a CCD camera is arranged at the light exit of the rear projection mirror group, and the CCD camera is installed on a camera bracket, and the camera bracket is installed on the mounting base plate, and the CCD camera is connected to the FPGA in the electronic box;

[0014] The imaging surface of the CCD camera coincides with the imaging surface of the rear projection lens assembly;

[0015] The support frame 1 is installed separately from the front light-collecting mirror group; the front light-collecting mirror group passes through the lower layer of the support frame 1 to ensure that the two are not in direct contact; the upper layer of the support frame 1 has an annular structure, and the bottom is fixed on the installation base plate;

[0016] The collimating lens group includes a lens five and a folding mirror four arranged in sequence along the optical axis, and the periphery of each lens and folding mirror is wrapped and fixed by a lens barrel;

[0017] The lens barrels of the collimating lens group are connected by flanges, and the annular structure on the upper layer of the supporting frame 1 is used to fix and install the collimating lens group;

[0018] Install the second support frame at the rear projection lens assembly, and fix the krypton lamp on the upper layer of the second support frame;

[0019] The support frame 2 is installed separately from the rear projection lens group, and the rear projection lens group passes through the lower layer of the support frame 2 to ensure that the two are not in direct contact; the support frame 2 is positioned on the lens barrel of the rear projection lens group by snapping, and the bottom is fixed on the installation base plate.

[0020] Beneficial effects of the present invention:

[0021] 1. The device of the present invention adopts a combination of multiple devices for installation. This design is more flexible and easier to expand and replace. The device can change and replace the parameters of the mirror group, krypton lamp and other devices according to the requirements of different application scenarios.

[0022] 2. The folded light path in the optical system of the present invention is folded by multiple folding mirror groups. The device occupies a small volume, which improves the internal space utilization of the satellite-borne wind interferometer load, reduces the weight of the instrument, reduces the transportation cost, and can provide more space for heat dissipation, making the instrument more stable and reliable during operation. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 The present invention is a schematic diagram of a miniaturized satellite-borne anemometer device based on DASH.

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

[0025] Figure 2 This is a schematic diagram of the structure of a part of the support frame described in the present invention: 2 is a front light-collecting mirror group, 3 is a mounting base plate, 6 is a collimating mirror 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 schematic diagram of the structure of the support frame 2 of the present invention: 3 is a mounting base plate, 4 is a rear projection lens group, 4-1 is a lens 3, 4-2 is a folding mirror 3, 4-3 is a lens 4, 10 is a support frame 2, and 11 is a krypton lamp. DETAILED DESCRIPTION

[0027] The present invention will be further described and illustrated below in conjunction with the accompanying drawings.

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

[0029] The electronic box 1 has a built-in FPGA, which is responsible for data communication transmission, and has an aluminum cube structure.

[0030] The electronic box 1 is thermally insulated and mounted on the mounting base plate 3 by means of thermal insulation pads and screws.

[0031] The front light-collecting mirror group 2 includes a lens 1 2-1, a folding mirror 1 2-2, a folding mirror 2-3 and a lens 2-4 arranged in sequence along the optical axis. The peripheries of the lenses and the folding mirrors are wrapped and fixed by a lens barrel.

[0032] The rear projection lens group 4 includes a lens 3 4-1, a folding mirror 3 4-2 and a lens 4 4-3 arranged in sequence along the optical axis. The peripheries of the lenses and the folding mirrors are wrapped and fixed by a lens barrel.

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

[0034] The interference unit 9 is heat-insulated and installed on the mounting base plate 3 using heat-insulating pads and screws. The interference unit 9 can be adjusted in angle and height.

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

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

[0038] The cubic prism 8 is located in front of the light entrance of the front light-collecting lens assembly 2 and is mounted on the mounting base plate 3 via a prism support 12 .

[0039] The CCD camera 5 is positioned and mounted on the mounting base plate 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 1 7 is installed separately from the front light receiving mirror group 2. The front light receiving mirror group 2 passes through the lower layer of the support frame 1 7 to ensure that the two are not in direct contact. The upper layer of the support frame 1 7 has an annular structure, and the bottom is fixed to the mounting base plate 3 by a heat insulation pad and screws to ensure the stability and heat insulation effect of the overall device.

[0041] The collimating lens group 6 includes a lens 5 6-1 and a folding mirror 4 6-2 arranged in sequence along the optical axis. The periphery of each lens and folding mirror is wrapped and fixed by a lens barrel.

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

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

[0044] The support frame 2 10 is installed separately from the rear projection lens group 4. The rear projection lens group 4 passes through the lower layer of the support frame 2 10 to ensure that the two do not directly contact. The support frame 2 10 is fastened to place the frame of the support frame on the lens barrel of the rear projection lens group 4, and the bottom is fixed to the installation base plate 3 by a heat insulation pad and screws.

[0045] Working process of the present invention:

[0046] The external air glow enters the front light collecting mirror group 2 through the cubic prism 8. The light forms a primary image point through the lens 1 2-1 and the folding mirror 1 2-2, and then generates parallel light through the folding mirror 2-3 and the lens 2 2-4 and enters the interference unit 9. The light interferes in the interference prism 9-2. The light after interference enters the rear projection mirror 4, and after the light is reflected by the folding mirror 3 4-2, it is converged by the lens 3 4-1 and the lens 4 4-3 to form an image on the CCD camera 5.

[0047] The krypton lamp 11 is an internal calibration light source and enters the collimator lens group 6 through an optical fiber. The light passes through the lens five 6-1 to generate parallel light and is reflected by the folding mirror four 6-2 to enter the cubic prism 8. The light passes through the cubic prism 8 to enter the front light collecting lens group 2. The light passes through the lens one 2-1 and the folding mirror one 2-2 to form a primary image point, and then passes through the folding mirror two 2-3 and the lens two 2-4 to generate parallel light and enter the interference unit 9. The light interferes in the interference prism 9-2. The light after interference enters the rear projection mirror 4, and after the light is reflected by the folding mirror three 4-2, it is converged by the lens three 4-1 and the lens four 4-3 to form an image on the CCD camera 5.

[0048] The specific installation steps of the miniaturized satellite-borne anemometer device based on DASH described in the present invention are as follows.

[0049] Step 1: Install the interference unit 9 on the installation base plate 3 in a heat-insulated manner;

[0050] Step 2: Assemble the folding mirror group 1 2 - 1 and the folding mirror group 2 2 - 2 of the front light-collecting mirror group 2 together, and then install the front light-collecting mirror group 2 at the light entrance of the box 9 - 1 of the interference unit 9;

[0051] Step 3: Assemble the folding lens group 3 4-1 and the straight lens group 4-2 of the rear projection lens group 4 together, and then install the rear projection lens group 4 at the light outlet of the box 9-1 of the interference unit 9;

[0052] Step 4: Position and install the CCD camera 5 on the mounting base plate 3 through the camera bracket 13;

[0053] Step 5: Install a support frame 7 at the rear projection lens group 4 and install it on the installation base plate 3 in a heat-insulated manner;

[0054] Step 6: Install the krypton lamp 11 on the support frame 7;

[0055] Step 7: Install the support frame 2 10 at the front light receiving mirror group 2 and install it on the installation base plate 3 in a heat-insulated manner;

[0056] Step 8: Install the collimating lens assembly 6 on the second support frame 10;

[0057] Step 9: Install a cubic prism 8 at the front end of the light entrance of the front light receiving mirror assembly 2, and install the cubic prism 8 on the installation base plate 3 through a prism support 12;

[0058] Step 10: Use the snap-fit ​​method to cover the entire optical system with the housing to provide protection and ensure that the optical system is not affected by the external environment;

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

Claims

1. A miniaturized DASH satellite-borne wind measuring device, characterized in that: It comprises an electronic box (1), a front light collecting mirror group (2), a mounting base plate (3), a rear projection mirror group (4), a CCD camera (5), a collimating mirror group (6), a first support frame (7), a cubic prism (8), an interference unit (9), a second support frame (10), a krypton lamp (11), a prism support (12) and a camera bracket (13); The electronic box (1) is installed on a mounting base plate (3); The front light-collecting mirror group (2) contains lens 1 (2-1), folding mirror 1 (2-2), folding mirror 2 (2-3) and lens 2 (2-4) which are arranged in sequence along the optical axis; the peripheries of the lenses and folding mirrors are wrapped and fixed by a lens barrel; The rear projection lens group (4) contains lens three (4-1), folding mirror three (4-2) and lens four (4-3) which are arranged in sequence along the optical axis; the peripheries of the lenses and the folding mirrors are wrapped and fixed by a lens barrel. The interference unit (9) comprises a box (9-1) and an interference prism (9-2) fixed inside the box (9-1); The interference unit (9) is installed on the installation base plate (3); A front light-collecting mirror group (2) is installed at the light entrance of the box (9-1) of the interference unit (9), and a rear projection mirror group (4) is installed at the light exit of the box (9-1); a cubic prism (8) is arranged in front of the light entrance of the front light-collecting mirror group (2), the cubic prism (8) is mounted on a prism support (12), and the prism support (12) is mounted on a mounting base plate (3); a CCD camera (5) is arranged at the light exit of the rear projection mirror group (4), the CCD camera (5) is mounted on a camera bracket (13), the camera bracket (13) is mounted on the mounting base plate (3), and the CCD camera (5) is connected to an 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 1 (7) is installed separately from the front light-collecting mirror group (2); the front light-collecting mirror group (2) passes through the lower layer of the support frame 1 (7) to ensure that the two are not in direct contact; the upper layer of the support frame 1 (7) has an annular structure, and the bottom is fixed on the installation base plate (3); The collimating lens group (6) includes a fifth lens (6-1) and a fourth folding mirror (6-2) arranged in sequence along the optical axis, and the periphery of each lens and folding mirror is wrapped and fixed by a lens barrel; The lens barrels of the collimating lens group (6) are connected via flanges, and the upper annular structure of the supporting frame (7) is used to fix and install the collimating lens group (6); A second support frame (10) is installed at the rear projection lens group (4), and a krypton lamp (11) is fixed on the upper layer of the second support frame (10); The second support frame (10) is installed separately from the rear projection lens group (4), and the rear projection lens group (4) passes through the lower layer of the second support frame (10) to ensure that the two are not in direct contact; the second support frame (10) is fastened to position the frame of the support frame on the lens barrel of the rear projection lens group (4), and the bottom is fixed on the installation base plate (3).

2. A miniaturized DASH satellite-borne wind measuring device according to claim 1, characterized in that: The electronic box (1) has a built-in FPGA, performs data communication transmission functions, and has an aluminum cubic structure.

3. A miniaturized DASH satellite-borne wind measuring device according to claim 1, characterized in that: The lens barrels of the front light-collecting mirror group (2) are connected via flanges; the light outlet of the front light-collecting mirror group (2) is aligned with the interference prism (9-2) in the interference unit (9) and is connected to the light inlet of the box (9-1) of the interference unit (9) via flanges.

4. The miniaturized DASH satellite-borne wind measuring device according to claim 1, characterized in that: The lens barrels of the rear projection lens group (4) are connected via flanges; the light 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 light exit of the box (9-1) of the interference unit (9) via flanges.

5. The miniaturized DASH satellite-borne wind measuring device according to claim 1, characterized in that: External air glow light enters the front light collecting mirror group (2) through the cubic prism (8), the light passes through the lens 1 (2-1) and the folding mirror 1 (2-2) to form a primary image point, then passes through the folding mirror 2 (2-3) and the lens 2 (2-4) to generate parallel light and enter the interference unit (9), the light interferes in the interference prism (9-2), the light after interference enters the rear projection mirror (4), the light is reflected by the folding mirror 3 (4-2), and then converges through the lens 3 (4-1) and the lens 4 (4-3) to form an image on the CCD camera (5); The krypton lamp (11) is an internal calibration light source, and its emitted light enters the collimating lens group (6) through the optical fiber, and the light is generated as parallel light by the lens five (6-1) and reflected by the folding mirror four (6-2) to enter the cubic prism (8), and the light enters the front light collecting lens group (2) through the cubic prism (8), and the light forms a primary image point through the lens one (2-1) and the folding mirror one (2-2), and then generates parallel light through the folding mirror two (2-3) and the lens two (2-4) and enters the interference unit (9), and the light interferes in the interference prism (9-2), and the light after interference enters the rear projection mirror (4), and after being reflected by the folding mirror three (4-2), the light is converged by the lens three (4-1) and the lens four (4-3) to form an image on the CCD camera (5).

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