CN103472580B - Compression-optics-based light beam penetrating system - Google Patents
Compression-optics-based light beam penetrating system Download PDFInfo
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- CN103472580B CN103472580B CN201310383131.8A CN201310383131A CN103472580B CN 103472580 B CN103472580 B CN 103472580B CN 201310383131 A CN201310383131 A CN 201310383131A CN 103472580 B CN103472580 B CN 103472580B
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Abstract
The invention relates to a compression-optics-based light beam penetrating system. The system comprises a compression optics system and a penetrating channel, wherein the penetrating channel comprises a near infrared-visible-medium wave infrared window channel and a long-wave infrared window channel; when the system is in a working state, large-caliber incident parallel light is compressed into small-caliber emergent parallel light through the compression optics system, the small-caliber emergent parallel light is introduced into a sealed cabin from a non-sealed cabin through the penetrating channel, thus realizing the penetration of the small-caliber emergent parallel light; an astronaut works in the sealed cabin. The large-caliber emergent parallel light can be compressed into the small-caliber emergent parallel light to be introduced into the cabin by utilizing the light beam penetrating system, so that the risk of the astronaut in going out the cabins for operation can be greatly reduced.
Description
Technical field
The invention belongs to remote sensing overall design field, optical laboratory of country, space station, relate to a kind of light beam crossing cabin system based on compression optics.
Background technology
Along with the fast development of optical remote sensing technology, heavy caliber high sensitivity remote sensor demand gets more and more, the new technology relevant to heavy caliber continues to bring out, and the concerned countries plan coming years will be the platform validation heavy caliber piecemeal advanced optical remote sensing technology that this two class of package technique and diffraction imaging technology is relevant to heavy caliber in-orbit with international space station.Because large-aperture optical remote sensor volume is comparatively large, in order to economize on resources, these two large-scale remote optical sensing equipment will be installed in out of my cabin, utilize plug-in mode to implement observation experiment, and optics is in-orbit assembled and debug and also completed by mechanical arm.
According to China's manned space flight Iarge-scale system Top-layer Design Method, in spacefarer 1 year, deliver from vault number of times is limited, if testing equipment is all placed on out of my cabin, the kind of test number (TN) and test load will significantly be restricted, and can not give full play to the usefulness of manned space station.Owing to needing the extravehicular space suit of heavy wearing when spacefarer carries out space walking, people is in floating state, is difficult to fixing health, be slow in action, space suit only to ensure to be exposed in space several hours, and the running time is limited, not easily carry out complicated operation, deliver from vault work will to be simply operated as master.Hubble Telescope in-orbit optical system installation and timing has just paid great manpower and financial resources cost, and difficulty is very big.
Summary of the invention
The technical matters that the present invention solves is: overcome the deficiencies in the prior art, proposes a kind of light beam crossing cabin system based on compression optics, to solve in light beam crossing cabin process the problems such as picture element degeneration, energy dropoff.
Technical scheme of the present invention is: a kind of light beam crossing cabin system based on compression optics, comprises compression optical system and crossing cabin passage; Described crossing cabin passage comprises near ultraviolet-visible-medium-wave infrared window and LONG WAVE INFRARED window two passages, and two passages adopt integrated design; Compression optics system acceptance target emanation signal, and shorten heavy caliber incident parallel optical pressure into small-bore outgoing directional light; LONG WAVE INFRARED light beam in outgoing parallel beam enters in cabin by LONG WAVE INFRARED window, and the near ultraviolet in outgoing parallel beam-visible-medium-wave infrared light beam is by near ultraviolet-visible-medium-wave infrared window enters in cabin; Payload reception in cabin by near ultraviolet-visible-medium-wave infrared window and the outgoing of LONG WAVE INFRARED window small-bore directional light and carry out working in cabin.
Described near ultraviolet-visible-medium-wave infrared window comprises optical window glass and window frame, wherein optical window glass is divided into two-layer, be respectively main bearing course glass and redundancy bearing course glass, and main bearing course glass is identical with the thickness of redundancy bearing course glass, optical window glass material selects sapphire; Window assembly material selection titanium alloy.
Described LONG WAVE INFRARED optical window comprises optical window glass and window frame, wherein optical window glass is divided into two-layer, be respectively main bearing course glass and redundancy bearing course glass, and main bearing course glass is identical with the thickness of redundancy bearing course glass, optical window glass material selects germanium; Window assembly material selection titanium alloy.
The present invention's advantage is compared with prior art:
Crossing cabin passage of the present invention have employed near ultraviolet-medium-wave infrared, LONG WAVE INFRARED optics two windows, and adopt integrated design, after crossing cabin, rear end picture element is good, bigbore parallel beam is introduced imaging in cabin, realize maintenance and upgrading that spacefarer completes load in pressurized capsule, give full play to the advantage of space station, realize expansion load operation, carry out short-term, on-the-track technology test frequently.The compression optical system of the present invention's application, possesses the features such as general, compatibility is good, extended capability is strong.
Accompanying drawing explanation
Fig. 1 is directional light compression front-and rear-view rink corner change schematic diagram;
Fig. 2 is crossing cabin channels designs schematic diagram;
Fig. 3 is present system composition schematic diagram.
Embodiment
The present invention's composition as shown in Figure 3, comprises compression optical system and crossing cabin passage; Described crossing cabin passage comprises near ultraviolet-visible-medium-wave infrared window and LONG WAVE INFRARED window two passages; Compression optics system acceptance target emanation signal, and shorten heavy caliber incident parallel optical pressure into small-bore outgoing directional light; LONG WAVE INFRARED light beam in outgoing parallel beam enters in cabin by LONG WAVE INFRARED window, and the near ultraviolet in outgoing parallel beam-visible-medium-wave infrared light beam is by near ultraviolet-visible-medium-wave infrared window enters in cabin; Payload reception in cabin by near ultraviolet-visible-medium-wave infrared window and the outgoing of LONG WAVE INFRARED window small-bore directional light and carry out working in cabin.
Heavy caliber incident parallel optical pressure is condensed to small-bore outgoing directional light: light is after the primary mirror in primary optical system, secondary mirror, mirror of turning back, three mirrors, boil down to outgoing parallel beam, easily debug for payload module provides, the optical interface of standard, control and data-interface, hot interface, possesses the features such as general, compatibility is good, extended capability is strong.
Small-bore outgoing directional light crossing cabin: utilize window glass small-bore parallel beam can be introduced in cabin, realize participation work in spacefarer cabin.
Be considered to the spectral range of picture, have employed near ultraviolet-medium-wave infrared, LONG WAVE INFRARED optics two windows, and adopt integrated design, as shown in Figure 2.The window frame flange of the outside flange of infrared optical window and near ultraviolet-medium-wave infrared window is carried out OVERALL OPTIMIZA-TION DESIGN FOR, and in like manner, design makes window size minimize to inner flange like this, and window structure is attractive in appearance, succinctly.Window device entirety is connected with screw with window mounting platform.Mounting platform is connected with screw with bulkhead.
Selection analysis method based on the light beam penetrating technology ratio of compression of compression optics is as follows: the present invention compresses the incidence of optical system directional light, parallel light emergence.Select the suitable design of ratio of compression to optical system most important.The size of ratio of compression directly affects the spot size incided on windowpane.If ratio of compression is too small, then emergent light spot is oversize, and some light can be caused to be blocked by window, and formation is blocked, and reduces light utilization ratio, even loses portion of energy.If ratio of compression is excessive, the image quality of meeting influential system, and emergent light field angle is excessive, the design difficulty of rear end load increases.As shown in Figure 1, emergent ray angle and the ratio of angle of incident light equal system compresses ratio to directional light compression front-and rear-view rink corner situation of change.When table 1 calculates different ratio of compression, principal optical plane system exit light angle, emergent pupil size and optical window size.As can be seen from result of calculation, when ratio of compression is less than 10, emergent pupil bore is comparatively large, indirectly causes the oversize of glass window, and heavy caliber seal glass obtains difficulty greatly, and engineering realizability is poor; When ratio of compression is greater than 12, emergent ray angle is large, and rear end load design difficulty is large, and development cost is high, volume weight is large.Consider various factors, main optical afocal system ratio of compression should be selected between 10 ~ 12.
Glass window diameter during the different ratio of compression of table 1
| Ratio of compression | Outgoing field angle | Emergent pupil size (mm) |
| 5:1 | 8.25°×5.25° | 400.0 |
| Ratio of compression | Outgoing field angle | Emergent pupil size (mm) |
| 7:1 | 11.55°×7.35° | 285.7 |
| 10:1 | 16.5°×10.5° | 200.0 |
| 12:1 | 19.8°×12.6° | 166.7 |
| 17:1 | 28.05°×18.74° | 117.6 |
Method for designing based on the light beam penetrating technology crossing cabin passage of compression optics is as follows: crossing cabin channel selecting near ultraviolet-visible-medium-wave infrared window and LONG WAVE INFRARED window two passages.
Near ultraviolet-medium-wave infrared window glass Material selec-tion sapphire; Window assembly Material selec-tion titanium alloy.Optical window glass is divided into two-layer, and be respectively main bearing course glass and redundancy bearing course glass, wherein main pressure-bearing glass mainly bears the whole pressure reduction of optical window, an atmospheric pressure.Redundancy pressure-bearing glass is the backup of main pressure-bearing glass, under main pressure-bearing glass normal operating conditions, do not bear pressure, so be vacuum state between main pressure-bearing glass and redundancy pressure-bearing glass, namely pressure is 0.Thickness of glass is 14mm, can meet intensity and the optical stability of bearing course glass.The same bearing course of thickness of redundancy bearing course is 14mm.LONG WAVE INFRARED optical window bore 210mm.
LONG WAVE INFRARED optical window glass material selects germanium; Window assembly Material selec-tion titanium alloy.Optical window glass is divided into two-layer, and be respectively main bearing course glass and redundancy bearing course glass, wherein main pressure-bearing glass mainly bears the whole pressure reduction of optical window, an atmospheric pressure.Redundancy pressure-bearing glass is the backup of main pressure-bearing glass, under main pressure-bearing glass normal operating conditions, do not bear pressure, so be vacuum state between main pressure-bearing glass and redundancy pressure-bearing glass, namely pressure is 0.Thickness of glass is 22mm, can meet intensity and the optical stability of bearing course glass.The same bearing course of thickness of redundancy bearing course is 22mm, LONG WAVE INFRARED optical window bore 260mm.
Examine the security will considering cabin body entirety in conceptual design, window need possess the characteristics such as pressure-bearing, anti-scratch, antifog, good airproof performance, corrosion-resistant, radiation hardness, and two crossing cabin passages adopt integration.
The content be not described in detail in instructions of the present invention belongs to the known technology of those skilled in the art.
Claims (3)
1. based on a light beam crossing cabin system for compression optics, it is characterized in that: comprise compression optical system and crossing cabin passage; Described crossing cabin passage comprises near ultraviolet-visible-medium-wave infrared window and LONG WAVE INFRARED window two passages, and two passages adopt integrated design; Compression optics system acceptance target emanation signal, and shorten heavy caliber incident parallel optical pressure into small-bore outgoing directional light; LONG WAVE INFRARED light beam in outgoing parallel beam enters in cabin by LONG WAVE INFRARED window, and the near ultraviolet in outgoing parallel beam-visible-medium-wave infrared light beam is by near ultraviolet-visible-medium-wave infrared window enters in cabin; Payload reception in cabin by near ultraviolet-visible-medium-wave infrared window and the outgoing of LONG WAVE INFRARED window small-bore directional light and carry out working in cabin; Described ratio of compression when heavy caliber incident parallel optical pressure being shortened into small-bore outgoing directional light is selected between 10 ~ 12.
2. a kind of light beam crossing cabin system based on compression optics according to claim 1, it is characterized in that: described near ultraviolet-visible-medium-wave infrared window comprises optical window glass and window frame, wherein optical window glass is divided into two-layer, be respectively main bearing course glass and redundancy bearing course glass, and main bearing course glass is identical with the thickness of redundancy bearing course glass, optical window glass material selects sapphire; Window assembly material selection titanium alloy.
3. a kind of light beam crossing cabin system based on compression optics according to claim 1, it is characterized in that: described LONG WAVE INFRARED optical window comprises optical window glass and window frame, wherein optical window glass is divided into two-layer, be respectively main bearing course glass and redundancy bearing course glass, and main bearing course glass is identical with the thickness of redundancy bearing course glass, optical window glass material selects germanium; Window assembly material selection titanium alloy.
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Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101866054A (en) * | 2010-06-03 | 2010-10-20 | 中国科学院长春光学精密机械与物理研究所 | Optical system of multispectral area array CCD (Charge Coupled Device) imager |
| CN102809824A (en) * | 2012-07-04 | 2012-12-05 | 北京空间机电研究所 | Spatial light beam compression multichannel imaging optical system with large field of view |
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Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101866054A (en) * | 2010-06-03 | 2010-10-20 | 中国科学院长春光学精密机械与物理研究所 | Optical system of multispectral area array CCD (Charge Coupled Device) imager |
| CN102809824A (en) * | 2012-07-04 | 2012-12-05 | 北京空间机电研究所 | Spatial light beam compression multichannel imaging optical system with large field of view |
Non-Patent Citations (2)
| Title |
|---|
| "国外深空探测光学遥感载荷发展现状与启示";周峰等;《航天返回与遥感》;20120229;第33卷(第1期);第16－22页 * |
| 张秉隆等."紫外遥感在深空探测领域的应用".《中国宇航学会深空探测技术专业委员会第九届学术年会论文集(下册)》.2012,第1014-1020页. * |
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