CN105467570B - Deep space exploration aircraft determines appearance star sensor optical imaging system - Google Patents
Deep space exploration aircraft determines appearance star sensor optical imaging system Download PDFInfo
- Publication number
- CN105467570B CN105467570B CN201510967562.8A CN201510967562A CN105467570B CN 105467570 B CN105467570 B CN 105467570B CN 201510967562 A CN201510967562 A CN 201510967562A CN 105467570 B CN105467570 B CN 105467570B
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- Prior art keywords
- meniscus lens
- speculum
- rear surface
- positive meniscus
- centre distance
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- G—PHYSICS
- G02—OPTICS
- G02B—OPTICAL ELEMENTS, SYSTEMS OR APPARATUS
- G02B17/00—Systems with reflecting surfaces, with or without refracting elements
- G02B17/08—Catadioptric systems
- G02B17/082—Catadioptric systems using three curved mirrors
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
- G01C21/00—Navigation; Navigational instruments not provided for in groups G01C1/00 - G01C19/00
- G01C21/02—Navigation; Navigational instruments not provided for in groups G01C1/00 - G01C19/00 by astronomical means
Abstract
Deep space exploration aircraft determines appearance star sensor optical imaging system, belong to technical field of optical, it is of the existing technology to overcome the problems, such as, incident ray passes through the first speculum front surface reflection, it is incident on the second speculum rear surface, the first positive meniscus lens is incident on after its reflection, which through the first positive meniscus lens, the first diverging meniscus lens, the second diverging meniscus lens and the second positive meniscus lens, is finally received by a detector successively；First speculum front surface is d1 with the second speculum rear surface centre distance, second speculum rear surface is d2 with the first positive meniscus lens front surface centre distance, first positive meniscus lens rear surface is d3 with the first diverging meniscus lens front surface centre distance, first diverging meniscus lens rear surface is d4 with the second diverging meniscus lens front surface centre distance, second diverging meniscus lens rear surface is d5 with the second positive meniscus lens front surface centre distance, and the second positive meniscus lens rear surface is d6 with detector centre distance.
Description
Technical field
A kind of deep space exploration aircraft of the present invention determines appearance star sensor optical imaging system, can be applied to outer space deep space
Explorer vehicle determines appearance, belongs to technical field of optical.
Background technology
There are many imaging types according to the wavelength band, the detector type that use for star sensor.The star having been reported that at present
Sensor structure uses the transmission-type of total transmissivity eyeglass mostly, and the general 20mm~60mm of system focal length, effective Entry pupil diameters are general
10mm~50mm.This can be caused when the faint small magnitude target of observation deep space, and what image detector received in the unit interval enters
It is few to penetrate light energy, the dynamic motion imaging time of integration lengthens, the shortcomings of image refresh rate is slow, and satellite posture speed is slow, can not
Determine posture field suitable for following survey of deep space airship satellite.
Invention content
The present invention is of the existing technology in order to overcome the problems, such as, provides a kind of deep space exploration aircraft and determines appearance star sensor
Optical imaging system.
Deep space exploration aircraft determines appearance star sensor optical imaging system, anti-by the incident sequence coaxial arrangement first of light
Penetrate mirror, the second speculum, the first positive meniscus lens, the first diverging meniscus lens, the second diverging meniscus lens, the second positive meniscus lens and
Detector, incident ray pass through the first speculum front surface reflection, are incident on the second speculum rear surface, incident after its reflection
To the first positive meniscus lens, the incident light is successively through the first positive meniscus lens, the first diverging meniscus lens, the second diverging meniscus lens
With the second positive meniscus lens, finally it is received by a detector；
The first speculum front surface is d1,75mm with the second speculum rear surface centre distance<d1<82mm, second
Speculum rear surface is d2,83mm with the first positive meniscus lens front surface centre distance<d2<90mm, after the first positive meniscus lens
Surface is d3,3.2mm with the first diverging meniscus lens front surface centre distance<d3<6mm, the first diverging meniscus lens rear surface and the
Two diverging meniscus lens front surface centre distances are d4,7mm<d4<8mm, the second diverging meniscus lens rear surface and the second positive bent moon are saturating
Mirror front surface centre distance d5,0.1mm<d5<0.5mm, the second positive meniscus lens rear surface are with detector centre distance d6
8mm。
The focal length of each optical element, refractive index, radius of curvature and clear aperture magnitude are full respectively in optical system of the present invention
Sufficient the following conditions：
The beneficial effects of the invention are as follows：
1) by area of computer aided optical design and optimization, the distance and face type for selecting two speculums can reduce incident ray
The rise and angle of lens are incident on, the aberration correction pressure of rear group of lens element is preferably alleviated, is organized after reasonable selection former
Number of packages amount and structure ensure that higher image quality, make the mtf value of camera lens in 50lp/mm close to diffraction limit, full filed
In the range of be more than 0.80.
2) light collecting light ability is 3~4 times of traditional star sensor, and 85% blur circle energy concentrates on 8 μm~10 μ ms
Interior, encircled energy is high, is conducive to improve positioning accuracy under detector defocus, and all band self-energy barycenter deviation is less than 2 μm, hangs down
Axis colo(u)r bias is less than 1.9 μm, and single star measurement accuracy is better than 2 ".
3) conventional Aspherical-surface testing means, respectively adjustment can be used in the first speculum, the second speculum, and lens original paper is
Spherical surface type, coaxial to put, easy to process and adjustment, lens material is general commercial glass, reduces optical system material
Purchase difficulty and manufacture cost.
4) relative distortion is less than 0.08% in the range of service band full filed, and it is quick using transmission-type star to determine appearance compared to tradition
The method of sensor has smaller relative distortion.
Description of the drawings
Fig. 1 determines appearance star sensor optical imaging system structure diagram for deep space exploration aircraft of the present invention.
Fig. 2 determines appearance star sensor optical imaging system capacity distribution curve for deep space exploration aircraft of the present invention.
Fig. 3 determines appearance star sensor optical imaging system chromatic longitudiinal aberration curve for deep space exploration aircraft of the present invention.
Fig. 4 determines appearance star sensor optical imaging system MTF curve for deep space exploration aircraft of the present invention.
Specific embodiment
As shown in Figure 1, a kind of deep space exploration aircraft determines appearance star sensor optical imaging system, by the incident sequence of light
It is saturating to be coaxially disposed the first speculum 1, the second speculum 2, the first positive meniscus lens 3, the first diverging meniscus lens 4, the second negative bent moon
Mirror 5, the second positive meniscus lens 6 and detector 7, incident ray are reflected by 1 front surface 11 of the first speculum, and it is anti-to be incident on second
2 rear surface 21 of mirror is penetrated, the first positive meniscus lens 3 is incident on after its reflection, which penetrates the first positive meniscus lens successively
3rd, the first diverging meniscus lens 4, the second diverging meniscus lens 5 and the second positive meniscus lens 6, are finally received by detector 7.
First speculum, 1 front surface 11 and 2 rear surface of the second speculum, 21 centre distance d1,75mm<d1<82mm,
31 centre distance d2,83mm of second speculum, 2 rear surface 21 and 3 front surface of the first positive meniscus lens<d2<90mm, first is just curved
The moon 41 centre distance d3,3.2mm of 3 rear surface 32 of lens and 4 front surface of the first diverging meniscus lens<d3<6mm, the first negative bent moon are saturating
51 centre distance d47mm of 4 rear surface 42 of mirror and 5 front surface of the second diverging meniscus lens<d4<8mm, table after the second diverging meniscus lens 5
61 centre distance d5,0.1mm of face 52 and second positive meniscus lens, 6 front surface<d5<0.5mm, table 62 after the second positive meniscus lens 6
Face is 8mm with 2 centre distance d6 of detector.
The focal length of each optical element, refractive index (λ=632.8nm) and radius of curvature magnitude difference in optical system of the present invention
Meet the following conditions：
Optical system of the present invention reaches following optical index：
Focal length：F '=321.978mm；Relative aperture:F=2.01；Practical spectral line range：450nm~900nm；Field angle：
2W=2.2 °；Distortion：<0.08%；Energy barycenter deviation：<2μm；Colo(u)r bias：<1.9μm；MTF:>0.8(50lp/mm).
As shown in Fig. 2, obtaining optical system energy distribution curve, 80% energy is concentrated within 12 μm, each visual field energy
Concentration degree is more unified.
As shown in figure 3, the chromatic longitudiinal aberration for obtaining optical system shortwave and reference wave is less than 1.5 μm, shortwave and long wave hang down
Axis aberration is less than 1 μm.
As shown in figure 4, obtaining each visual field modulation transfer function of optical system more than 0.8, each visual field is more unified.
Claims (2)
1. survey of deep space airship determines appearance star sensor optical imaging system, it is characterized in that, it is coaxially disposed by the incident sequence of light
First speculum (1), the second speculum (2), the first positive meniscus lens (3), the first diverging meniscus lens (4), the second negative bent moon are saturating
Mirror (5), the second positive meniscus lens (6) and detector (7), incident ray are reflected by the first speculum (1) front surface (11), are entered
The second speculum (2) rear surface (21) is mapped to, is incident on the first positive meniscus lens (3) after its reflection, the incident light is saturating successively
The first positive meniscus lens (3), the first diverging meniscus lens (4), the second diverging meniscus lens (5) and the second positive meniscus lens (6) are crossed, most
It is received eventually by detector (7)；
First speculum (1) front surface (11) and the second speculum (2) rear surface (21) centre distance d1,75mm<d1<
82mm, the second speculum (2) rear surface (21) and the first positive meniscus lens (3) front surface (31) centre distance d2,83mm<d2<
90mm, the first positive meniscus lens (3) rear surface (32) and the first diverging meniscus lens (4) front surface (41) centre distance d3,3.2mm
<d3<6mm, the first diverging meniscus lens (4) rear surface (42) and the second diverging meniscus lens (5) front surface (51) centre distance d4,
7mm<d4<8mm, the second diverging meniscus lens (5) rear surface (52) and the second positive meniscus lens (6) front surface (61) centre distance
D5,0.1mm<d5<0.5mm, the second positive meniscus lens (6) rear surface (62) are 8mm with detector (2) centre distance d6.
2. survey of deep space airship according to claim 1 determines appearance star sensor optical imaging system, it is characterized in that, each light
The optical parameter magnitude for learning element meets the following conditions respectively：
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| Application Number | Priority Date | Filing Date | Title |
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| CN201510967562.8A CN105467570B (en) | 2015-12-22 | 2015-12-22 | Deep space exploration aircraft determines appearance star sensor optical imaging system |
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| CN201510967562.8A CN105467570B (en) | 2015-12-22 | 2015-12-22 | Deep space exploration aircraft determines appearance star sensor optical imaging system |
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| CN105467570A CN105467570A (en) | 2016-04-06 |
| CN105467570B true CN105467570B (en) | 2018-06-29 |
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| CN109298517B (en) * | 2018-11-05 | 2020-10-30 | 中国航空工业集团公司洛阳电光设备研究所 | Multispectral coaxial catadioptric afocal optical system |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102116926A (en) * | 2009-12-31 | 2011-07-06 | 北京控制工程研究所 | Imaging structure of fixed star sensor |
| CN102253479A (en) * | 2011-07-29 | 2011-11-23 | 中国科学院光电技术研究所 | Principal focus type refracting-reflecting optical system |
| CN203217159U (en) * | 2012-09-27 | 2013-09-25 | 中国科学院西安光学精密机械研究所 | Visible light, middle-wavelength infrared and long-wavelength infrared three-waveband optical imaging system |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2002093231A1 (en) * | 2001-05-15 | 2002-11-21 | Industrial Research Limited | Optical imaging system with aberration correcting means |
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Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102116926A (en) * | 2009-12-31 | 2011-07-06 | 北京控制工程研究所 | Imaging structure of fixed star sensor |
| CN102253479A (en) * | 2011-07-29 | 2011-11-23 | 中国科学院光电技术研究所 | Principal focus type refracting-reflecting optical system |
| CN203217159U (en) * | 2012-09-27 | 2013-09-25 | 中国科学院西安光学精密机械研究所 | Visible light, middle-wavelength infrared and long-wavelength infrared three-waveband optical imaging system |
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