CN112596095B - Satellite-borne multi-probe ionosphere imager device - Google Patents
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Abstract
The invention belongs to the technical field of space optical detection and satellite-borne detection devices, and particularly relates to a satellite-borne multi-probe ionosphere imager device, which comprises: the device comprises a first camera, a second camera, a third camera, a photometer and a main frame. The first camera, the second camera and the third camera work in different wave bands to form images of different channels on an ionized layer; the photometer measures the illumination intensity in a field of view and judges day and night alternation; the main frame is used for fixing the three cameras and the photometer and providing a heat dissipation function. The device solves the problems of poor reliability caused by the need of switching the filter wheel in ionosphere detection and inconsistent detection time of different channels.
Description
Technical Field
The invention belongs to the technical field of space optical detection and satellite-borne detection devices, and particularly relates to a satellite-borne multi-probe ionosphere imager device.
Background
The ionosphere, one of the most important areas of human spatial activity, is the area formed by partial ionization of the neutral atmosphere of the earth at a height of about 60-1000km from the ground under the action of radiation such as solar X-rays, EUV and the like. In this region, in addition to the neutral atmosphere, there are a large number of free electrons and ions that can significantly affect the propagation of radio waves.
With the increasing maturity of remote sensing technology, the space activity of human is more and more, and the ionosphere is more and more closely related with human life. Radio communication, broadcasting, satellite navigation, radar positioning and the like are mainly concentrated in the area, and ionosphere storm (solar black particle activity, strong charged particle flow released by a broken zone before and after an earthquake and the like) and ionosphere artificial sudden disturbance (such as nuclear explosion, heating of a high-power transmitter to the ionosphere and the like) can cause serious influence on ionosphere communication and broadcasting and even interrupt signals; the characteristics of ion distribution in the ionized layer can reflect the change of the earth magnetic field, and the occurrence of meteorological geological disasters such as earthquakes and the like can be indirectly predicted; the ionosphere is also the main operating site of remote missiles, low orbit satellites and space stations, and the condition of the environment directly influences the service life of an aircraft operating in the ionosphere, the functional realization and the life health and safety of astronauts. Therefore, the ionosphere state monitoring and forecasting method and the ionosphere change law research are beneficial to promoting the ionosphere theory development related to the field of earth science, analyzing factors causing ionosphere abnormity and predicting disasters possibly caused by ionosphere disturbance, and have irreplaceable practical significance and strategic purposes in the daily life fields of national defense safety, disaster monitoring, power supply, radio communication and the like.
Ionospheric imagers are common probing devices. In order to obtain information of different wave bands, a common detection mode is to embed a filter wheel device in an imager and switch channels in a detection process. Due to the introduction of the movable mechanism, the reliability of the on-track operation is lower than that of the non-movable structure. In addition, due to the switching of the optical filters, the time continuity of different channels cannot be guaranteed, so that the time resolution of the corresponding same channel is reduced.
Disclosure of Invention
The invention aims to solve the problems of ionospheric exploration reliability and multichannel exploration time continuity, and provides a satellite-borne multi-probe ionospheric imager device which has the characteristics of large field of view, multiple channels and high resolution.
In order to achieve the purpose, the invention provides a satellite-borne multi-probe ionosphere imager device. The device comprises: a first camera 1, a second camera 2, a third camera 3, a photometer 4, a main frame 6;
the first camera 1, the second camera 2 and the third camera 3 are arranged on the main frame 6 in a triangular distribution mode, and the photometer 4 is arranged in the triangular center formed by the first camera 1, the second camera 2 and the third camera 3;
the first camera 1, the second camera 2 and the third camera 3 have the same structure but different wave band work, and form images of different channels on the ionized layer; the photometer measures the illumination intensity in a field of view and judges day and night alternation; the main frame 6 is used for fixing the three cameras and the photometer 4 and providing a heat dissipation function.
As a modification of the above technical solution, the main frame 6 further includes a heat dissipation plate 5 located at one side of the second camera 2 and the third camera 3.
As an improvement of the above technical solution, the first camera 1, the second camera 2, and the third camera 3 each further include: the lens is sequentially connected with a camera lens hood 10, a first spacer 11, a first pressing ring 12, a second reflector 14, a lens barrel 17, a first reflector 13, a front lens hood 18, a fourth reflector 16, a first spacer 19, a rear lens hood 20, a second pressing ring 21, a second spacer 22, a third reflector 15 and a detector assembly 23.
As one improvement of the above technical solution, the operating band of the first camera 1 is 135.6 ± 5 nm; the working band of the second camera 2 is 140-160 nm; the working band of the third phase machine 3 is 160-180 nm.
As an improvement of the above technical solution, the optical system of the camera 1, the camera 2, and the camera 3 is a coaxial four-lens reflex optical system.
As one improvement of the above technical solution, the photometer 4 further includes a photometer shade 24, a photometer mirror frame 25, a fifth reflector 26, a sixth reflector 27, a seventh reflector 28, an eighth reflector 29, a first pressing piece 30, a second pressing piece 31, a third pressing piece 32, a fourth pressing piece 33, a tube seat 34, a photomultiplier 35, and a third pressing ring 36; wherein,
the photometer shade 24 is fixed on the main frame 6, and the photometer lens frame 25 is used for installing a fifth reflector 26, a sixth reflector 27, a seventh reflector 28 and an eighth reflector 29;
the first pressing piece 30, the second pressing piece 31, the third pressing piece 32 and the fourth pressing piece 33 press the fifth reflecting mirror 26, the sixth reflecting mirror 27, the seventh reflecting mirror 28 and the eighth reflecting mirror 29;
the first pressing piece 30 is connected with the tube seat 34;
the photomultiplier 35 is supported in the tube seat 34 through a third pressing ring 36;
the photomultiplier 35 adopts an end window type structure;
the working waveband of the photometer 4 is 135.6 +/-5 nm.
As a modification of the above technical solution, the main frame 6 further includes a heat dissipation plate 5, an installation opening 7, and an installation leg 9.
As an improvement of the above technical solution, the surfaces of the camera shade 10, the front shade tube 18 and the rear shade tube 20 are all sprayed with extinction materials, and the absorption coefficient is greater than 0.98.
The matting material is a material known in the art.
As one improvement of the above technical solution, the surfaces of the first reflector 13, the second reflector 14, the third reflector 15 and the fourth reflector 16 are all plated with a multilayer dielectric film, the in-band reflectivity is greater than 0.8, and the out-of-band reflectivity is less than 0.1
As an improvement of the above technical solution, in the coaxial four-mirror optical system, at least one of the first reflector 13, the second reflector 14 and the third reflector 15 is an aspherical mirror, and the others are spherical mirrors; the fourth mirror 16 is a flat mirror.
As a modification of the above technical solution, at least one of the fifth mirror 26, the sixth mirror 27, the seventh mirror 28, and the eighth mirror 29 is a spherical mirror, and the others are plane mirrors;
the surfaces of the fifth reflector 26, the sixth reflector 27, the seventh reflector 28 and the eighth reflector 29 are all plated with multilayer dielectric films, the in-band reflectivity is greater than 0.8, and the out-of-band reflectivity is less than 0.1.
As one improvement of the technical scheme, the surface of the heat dissipation plate 5 is sprayed with the thermal control white paint, the absorptivity is less than 0.1, and the emissivity is greater than 0.85.
As one improvement of the technical scheme, the mounting ports 7 are 4 in total, the mounting ports 7 for mounting the cameras are distributed in a triangular mode, and the mounting ports 7 for mounting the photometer 4 are positioned in the triangular center.
Compared with the prior art, the invention has the beneficial effects that:
compared with the existing ultraviolet optical system, the satellite-borne multi-probe ionosphere imager provided by the invention has the characteristics of large view field, multiple channels and high resolution. Through detection of a plurality of channels, the use of a filter wheel with low reliability for converting a spectrum channel is avoided, simultaneous measurement can be realized, time deviation caused by switching of the filter wheel is not introduced, and the time resolution for observing the same target is improved. Compared with a common coaxial two-reflector optical system, the field of view is increased, and the imaging quality of the edge field of view is better. Compared with a general imaging spectrometer, the high-sensitivity optical spectrometer has higher sensitivity.
Drawings
FIG. 1 is a schematic structural diagram of a satellite-borne multi-probe ionosphere imager in accordance with the present invention;
FIG. 2 is a schematic structural diagram of a main frame in a satellite-borne multi-probe ionosphere imager in accordance with the present invention;
FIG. 3 is an assembly view of a camera structure in a satellite-borne multi-probe ionosphere imager in accordance with the present invention;
FIG. 4 is an exploded view of a camera structure in a satellite-borne multi-probe ionosphere imager in accordance with the present invention;
FIG. 5 is a cross-sectional view of a camera structure in a satellite-borne multi-probe ionosphere imager in accordance with the present invention;
FIG. 6 is an optical path diagram of a satellite-borne multi-probe ionosphere imager of the present invention;
FIG. 7 is an assembly view of a photometer structure in a satellite-borne multi-probe ionosphere imager of the present invention;
FIG. 8 is a cross-sectional view of a photometer structure in a satellite-borne multi-probe ionosphere imager of the present invention;
FIG. 9 is an exploded view of a photometer structure in a satellite-borne multi-probe ionosphere imager of the present invention;
reference numerals:
1. the camera comprises a first camera, a second camera, a third camera, a photometer, a third camera, a fourth camera lens, a fourth lens, a fifth lens, a sixth lens, a fifth lens, a sixth lens, a fourth lens, a fifth lens, a sixth lens, a fifth lens, a sixth lens, a third lens, a.
Detailed Description
The invention is further illustrated by the following examples and figures.
As shown in figure 1, the invention provides a satellite-borne multi-probe ionosphere imager device, which solves the problems of small instantaneous field of view, low multi-channel detection time resolution and poor reliability of movable parts of the satellite-borne imager.
The satellite-borne multi-probe ionosphere imager device comprises: a first camera 1, a second camera 2, a third camera 3, a photometer 4, and a main frame 6. The three cameras and the photometer 4 are all fixed on the main frame 6.
The first camera 1, the second camera 2 and the third camera 3 have the same structure but different wave band work, and form images of different channels on the ionized layer; the working waveband of the first camera 1 is 135.6 +/-5 nm; the working band of the second camera 2 is 140-160 nm; the working band of the third phase machine 3 is 160-180 nm.
The photometer 4 measures the illumination intensity in the field of view and judges day and night alternation;
the main frame 6 is used for fixing the three cameras and the photometer 4 and providing a heat dissipation function.
As shown in fig. 2, the main frame 6 further includes a heat dissipation plate 5, a mounting opening 7, and mounting legs 9. The main frame 6 is an integral truss structure, so that the weight can be reduced and the strength can be ensured. The heat radiating plate 5 is integrated with the main frame 6, increasing heat conduction efficiency. The mounting feet 9 are used to secure the instrument to the satellite platform.
The surface of the heat dissipation plate 5 is sprayed with the thermal control white paint, the absorptivity is less than 0.1, and the emissivity is greater than 0.85. The lower the absorption rate of the heat dissipation plate, the lower the temperature thereof. The greater the emissivity of the heat sink, the faster the rate at which heat is radiated to the outside.
As shown in fig. 2, the number of the mounting ports 7 is 4, and the mounting ports 7 for mounting the cameras are distributed in a triangular manner; the mounting opening 7 for mounting the photometer is located in the center of the triangle. The reinforcing ribs 8 are used for reinforcing the heat dissipation plate, the heat dissipation plate is prevented from being broken or deformed in mechanical vibration, and the reinforcing ribs are in triangular structures and are connected with the heat dissipation plate and the frame.
As shown in fig. 3, 4 and 5, the first camera 1, the second camera 2 and the third camera 3 have the same structure, and include a camera hood 10, a first spacer 11, a first pressing ring 112, a first reflector, a second reflector, a third reflector, a fourth reflector, a lens barrel 17, a front light-shielding barrel 18, a first spacer 19, a rear light-shielding barrel 20, a second pressing ring 21, a second spacer 22 and a detector assembly 23. The camera hood 10 is fixed to the foremost end and is fixed to the lens barrel 17 by screws. The first spacer 11 is a heat insulation part, made of glass fiber reinforced plastic or polyimide, and is located between the camera hood 10 and the lens barrel 17. The first reflector 13 and the fourth reflector 16 are fixed to the front light shielding cylinder 18 by using an adhesive. The second reflector 14 and the third reflector 15 are respectively installed at the front end and the rear end of the lens barrel 17 and fixed by adhesive. The first pressing ring 12 and the second pressing ring 21 are fastened on the lens barrel 17 through threads, and only limit the second reflector 14 and the third reflector 15, but do not play a fastening role. The camera hood 10 and the camera module are fixed to the lens barrel 17 together by screws. The camera module is separated from the camera hood 17 by a second spacer 22.
The camera shade 10, the front shade tube 18 and the rear shade tube 20 are used for suppressing stray light, so that the surface is sprayed with extinction materials, and the absorption coefficient is larger than 0.98. The larger the absorption coefficient, the better the matting effect.
As shown in fig. 6, the optical systems of the first camera 1, the second camera 2, and the third camera 3 are all coaxial four-lens reflex optical systems. The coaxial four-reflection optical system can realize larger field of view and imaging quality than a common two-reflection optical system.
At least one of the coaxial four-reflection optical system, the first reflector 13, the second reflector 14 and the third reflector 15 is an aspherical mirror, and the others are spherical mirrors; the fourth reflector 16 is a plane mirror.
The surfaces of the first reflector 13, the second reflector 14, the third reflector 15 and the fourth reflector 16 are all plated with multilayer dielectric films, the in-band reflectivity is greater than 0.8, and the out-of-band reflectivity is less than 0.1
The photometer 4 shown in fig. 7, 8 and 9 includes a photometer shade 24, a photometer lens holder 25, a fifth reflector 26, a sixth reflector 27, a seventh reflector 28, an eighth reflector 29, a first pressing piece 30, a second pressing piece 31, a third pressing piece 32, a fourth pressing piece 33, a stem 34, a photomultiplier 35 and a third pressing ring 36. The photometer light shield 24 is fixed to the main frame 6 and is not connected to the photometer frame 25. The photometer lens frame 25 is used for mounting a fifth reflector 26, a sixth reflector 27, a seventh reflector 28 and an eighth reflector 29; the first pressing piece 30, the second pressing piece 31, the third pressing piece 32 and the fourth pressing piece 33 press the reflecting mirror and are fixed on the photometer lens frame 25 through screws. The photomultiplier 35 is in an end window type structure, is supported in the tube seat 34 through a third pressing ring 36, and is bonded through silicon rubber. Silica gel is filled between the photomultiplier 35 and the tube seat 34, which can play a role in shock absorption.
The working waveband of the photometer is 140-180nm, and the waveband exists only at night, so that when the photometer has no response, the photometer can judge that the photometer has the daytime. And when the camera is judged to be in the daytime state, all the cameras are switched to the daytime mode at night. In the daytime mode, only the first camera 1 is operated, and the second camera 2 and the third camera 3 are turned off.
The third reflector 26, the fourth reflector 27, the seventh reflector 28 and the eighth reflector are arranged in parallel, and at least one of the reflectors is a spherical reflector and the others are plane mirrors. The surface of the reflector is plated with a plurality of dielectric films, the reflectivity in the band is more than 0.8, and the reflectivity out of the band is less than 0.1.
The imager is arranged on a satellite platform and points to the earth center generally and the polar region in special cases. Ionospheric airglow and aurora are observed objects, and the observed objects are imaged to a phase plane through an imager. At the opposite side, a detector assembly 23 is mounted for collecting signals, the detector assembly 23 typically being an enhanced detector.
Finally, it should be noted that the above embodiments are only used for illustrating the technical solutions of the present invention and are not limited. Although the present invention has been described in detail with reference to the embodiments, it will be understood by those skilled in the art that various changes may be made and equivalents may be substituted without departing from the spirit and scope of the invention as defined in the appended claims.
Claims (6)
1. A satellite-borne multi-probe ionospheric imager apparatus, said apparatus comprising: a first camera (1), a second camera (2), a third camera (3), a photometer (4) and a main frame (6);
the first camera (1), the second camera (2) and the third camera (3) are arranged on the main frame (6) in a triangular distribution mode, and the photometer (4) is arranged in a triangular center formed by the first camera (1), the second camera (2) and the third camera (3);
the working waveband of the first camera (1) is 135.6 +/-5 nm; the working band of the second camera (2) is 140-160 nm; the working waveband of the third camera (3) is 160-180 nm;
the structures of the first camera (1), the second camera (2) and the third camera (3) all comprise: the lens is characterized in that a camera lens hood (10), a first spacer (11), a first pressing ring (12), a second reflector (14), a lens barrel (17), a first reflector (13), a front lens hood (18), a fourth reflector (16), a first spacer ring (19), a rear lens hood (20), a second pressing ring (21), a second spacer (22), a third reflector (15) and a detector assembly (23) are sequentially connected;
at least one of the first reflector (13), the second reflector (14) and the third reflector (15) is an aspherical mirror, and the others are spherical mirrors; the fourth reflector (16) is a plane mirror;
the reflectivity of the first reflector (13), the second reflector (14), the third reflector (15) and the fourth reflector (16) is larger than 0.8 in a band, and the reflectivity of the outside of the band is smaller than 0.1.
2. The apparatus according to claim 1, wherein the main frame (6) further comprises a heat dissipation plate (5) located at one side of the second camera (2) and the third camera (3);
the surface of the heat dissipation plate (5) is sprayed with thermal control white paint, the absorptivity is less than 0.1, and the emissivity is greater than 0.85.
3. The device according to claim 1, wherein the surfaces of the first reflector (13), the second reflector (14), the third reflector (15) and the fourth reflector (16) are coated with a multilayer dielectric film.
4. The apparatus of claim 1, wherein the surfaces of the camera hood (10), front shade cylinder (18) and rear shade cylinder (20) are coated with a matting material having an absorption coefficient greater than 0.98.
5. The device according to claim 1, characterized in that the photometer (4) comprises a photometer light shield (24), a photometer lens frame (25), a fifth mirror (26), a sixth mirror (27), a seventh mirror (28), an eighth mirror (29), a first press plate (30), a second press plate (31), a third press plate (32), a fourth press plate (33), a tube holder (34), a photomultiplier (35), a third press ring (36); wherein,
the photometer light shield (24) is fixed on the main frame (6), and the photometer lens frame (25) is used for mounting a fifth reflector (26), a sixth reflector (27), a seventh reflector (28) and an eighth reflector (29);
the first pressing piece (30), the second pressing piece (31), the third pressing piece (32) and the fourth pressing piece (33) press the fifth reflector (26), the sixth reflector (27), the seventh reflector (28) and the eighth reflector (29);
the first pressing sheet (30) is connected with the tube seat (34);
the photomultiplier (35) is supported in the tube seat (34) through a third pressing ring (36);
the photomultiplier (35) adopts an end window type structure;
the working waveband of the photometer (4) is 135.6 +/-5 nm.
6. The apparatus according to claim 5, characterized in that at least one of the fifth (26), sixth (27), seventh (28) and eighth (29) mirrors is a spherical mirror, the others are flat mirrors;
the surfaces of the fifth reflector (26), the sixth reflector (27), the seventh reflector (28) and the eighth reflector (29) are all plated with multilayer dielectric films, the in-band reflectivity is greater than 0.8, and the out-of-band reflectivity is less than 0.1.
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Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5212588A (en) * | 1991-04-09 | 1993-05-18 | The United States Of America As Represented By The United States Department Of Energy | Reflective optical imaging system for extreme ultraviolet wavelengths |
| CN102866487A (en) * | 2012-09-12 | 2013-01-09 | 北京空间机电研究所 | Coaxial four-reflector ultra-low distortion optical system |
| CN103308166A (en) * | 2013-06-24 | 2013-09-18 | 中国科学院长春光学精密机械与物理研究所 | Multi-direction multi-band atmospheric remote sensing ultraviolet imager |
| CN103344580A (en) * | 2013-06-24 | 2013-10-09 | 中国科学院长春光学精密机械与物理研究所 | Imaging method for three-waveband multi-azimuth simultaneous limb nadir atmospheric remote sensing |
| CN105301626A (en) * | 2015-08-19 | 2016-02-03 | 西北核技术研究所 | Strong-current pulse electron beam incident angle two-dimensional measurement probe, device and method |
| CN106229249A (en) * | 2016-07-25 | 2016-12-14 | 中国科学院国家空间科学中心 | A kind of vibration absorber for installing photomultiplier tube |
| CN110262024A (en) * | 2019-06-21 | 2019-09-20 | 中国科学院长春光学精密机械与物理研究所 | A kind of novel coaxial four surpasses in reverse compact optical system |
| CN111175781A (en) * | 2020-01-16 | 2020-05-19 | 中国科学院国家空间科学中心 | Multi-angle multispectral spaceborne ionosphere detection device |
| CN111238637A (en) * | 2020-01-16 | 2020-06-05 | 中国科学院国家空间科学中心 | Satellite-borne ionosphere photometer |
| CN111323122A (en) * | 2020-03-11 | 2020-06-23 | 中国科学院国家空间科学中心 | Satellite-borne multi-channel aurora spectral imaging device |
-
2020
- 2020-11-04 CN CN202011217211.2A patent/CN112596095B/en active Active
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5212588A (en) * | 1991-04-09 | 1993-05-18 | The United States Of America As Represented By The United States Department Of Energy | Reflective optical imaging system for extreme ultraviolet wavelengths |
| CN102866487A (en) * | 2012-09-12 | 2013-01-09 | 北京空间机电研究所 | Coaxial four-reflector ultra-low distortion optical system |
| CN103308166A (en) * | 2013-06-24 | 2013-09-18 | 中国科学院长春光学精密机械与物理研究所 | Multi-direction multi-band atmospheric remote sensing ultraviolet imager |
| CN103344580A (en) * | 2013-06-24 | 2013-10-09 | 中国科学院长春光学精密机械与物理研究所 | Imaging method for three-waveband multi-azimuth simultaneous limb nadir atmospheric remote sensing |
| CN105301626A (en) * | 2015-08-19 | 2016-02-03 | 西北核技术研究所 | Strong-current pulse electron beam incident angle two-dimensional measurement probe, device and method |
| CN106229249A (en) * | 2016-07-25 | 2016-12-14 | 中国科学院国家空间科学中心 | A kind of vibration absorber for installing photomultiplier tube |
| CN110262024A (en) * | 2019-06-21 | 2019-09-20 | 中国科学院长春光学精密机械与物理研究所 | A kind of novel coaxial four surpasses in reverse compact optical system |
| CN111175781A (en) * | 2020-01-16 | 2020-05-19 | 中国科学院国家空间科学中心 | Multi-angle multispectral spaceborne ionosphere detection device |
| CN111238637A (en) * | 2020-01-16 | 2020-06-05 | 中国科学院国家空间科学中心 | Satellite-borne ionosphere photometer |
| CN111323122A (en) * | 2020-03-11 | 2020-06-23 | 中国科学院国家空间科学中心 | Satellite-borne multi-channel aurora spectral imaging device |
Non-Patent Citations (1)
| Title |
|---|
| COSMIC电离层光度计观测数据反演峰值电子密度的算法与结果;江芳 等;《科技导报》;20181231;第36卷(第5期);第85-91页 * |
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