CN106199955A - A kind of face battle array static state infrared earth sensor optical system - Google Patents
A kind of face battle array static state infrared earth sensor optical system Download PDFInfo
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- CN106199955A CN106199955A CN201610781335.0A CN201610781335A CN106199955A CN 106199955 A CN106199955 A CN 106199955A CN 201610781335 A CN201610781335 A CN 201610781335A CN 106199955 A CN106199955 A CN 106199955A
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- face
- meniscus lens
- optical system
- static state
- battle array
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- G—PHYSICS
- G02—OPTICS
- G02B—OPTICAL ELEMENTS, SYSTEMS OR APPARATUS
- G02B27/00—Optical systems or apparatus not provided for by any of the groups G02B1/00 - G02B26/00, G02B30/00
- G02B27/0025—Optical systems or apparatus not provided for by any of the groups G02B1/00 - G02B26/00, G02B30/00 for optical correction, e.g. distorsion, aberration
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- G—PHYSICS
- G02—OPTICS
- G02B—OPTICAL ELEMENTS, SYSTEMS OR APPARATUS
- G02B27/00—Optical systems or apparatus not provided for by any of the groups G02B1/00 - G02B26/00, G02B30/00
- G02B27/0081—Optical systems or apparatus not provided for by any of the groups G02B1/00 - G02B26/00, G02B30/00 with means for altering, e.g. enlarging, the entrance or exit pupil
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- General Physics & Mathematics (AREA)
- Optics & Photonics (AREA)
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Abstract
A kind of face battle array static state infrared earth sensor characteristic far infrared optical system, refractive optical structure, use 3 meniscus lens and 1 tablet filter to realize, the angle of visual field 50 °, meet satellite attitude measurement area requirement.For correction off-axis aberration, use 4 aspheric surfaces.Back work distance is easily installed optical filter and detector and heat control system from more than 10mm.Native system simple in construction, quality is little, and F# is not more than 1.5, meets product signal to noise ratio requirement, and in full filed, distortion is less than 0.5%, is particularly well-suited to the use of the spacecraft Attitude and orbit control system mid-infrared earth sensors such as satellite airship.
Description
Technical field
The invention belongs to the spacecraft rail control subsystem infrared earth sensor technology neck fields such as satellite airship, relate to
And a kind of face battle array static state infrared earth sensor optical system, to the earth 14～16 microns of far infrared radiation optical imageries.
Background technology
Spacecraft face battle array static state infrared earth sensor (infrared earth sensor is once called as infrared horizon)
Infrared optical system effect is the far infrared radiation optical imagery to earth atmosphere, and wavelength is generally 14～16 microns.Due to spoke
Penetrate energy faint, this optical system need to possess big relative aperture (little F#), less and thin eyeglass passes through to improve energy
Rate；Need the bigger angle of visual field to improve measurement scope；Need suppression distortion, facilitate satellite to use.The most domestic there is no face
License in terms of the static infrared earth sensor optical system of battle array, domestic disclosed document is as follows:
(1) " optical design of Radix Rumicis f-θ static state infrared horizon camera lens " Liu Ying, optical precision engineering, volume 18 the 6th
Phase, in June, 2010
(2) " optimized design of static state infrared horizon " Lv Yinhuan, infrared and laser engineering, volume 35 the 5th
Phase, the l0 month in 2006
(3) " design of Optical System without transconversion into heat of LONG WAVE INFRARED horizon sensor and realization " Lv Yinhuan, infrared technique, volume 33
11 phases, in November, 2011
Document 1, utilizes f-θ lens design principle, selects aspheric design wide-angle optics, and full filed angle is 136 degree,
F number is 0.61, back work distance 15mm；This camera lens is made up of 4 mirrors, solves wide-angle lens off-axis aberration equilibrium problem.Document 1
Design has a disadvantage in that
(1) although the F# of optical system is 0.61, but after the aperture diaphragm of system is positioned at the 3rd lens, rather than the
Before one lens, the true energy utilization rate of system is too low, and effective F# is only 2.4, causes product signal to noise ratio too low, it is impossible to full
Foot requirement；
(2) camera lens is made up of 4 mirrors, causes optical transmittance low；
(3) although product design is f-θ optical texture, but the target of imaging is face object and non-dots object, causes
Pattern distortion is excessive, it is impossible to provide satellite to use；
In document 2, optical system selects 2 lens arrangements of transmission-type, and system focal is 27.98mm, and optics bore is
30mm, F#=0.9, aberration meets requirement, but in order to improve the energy that detector accepts, sensitive band is loosened to 13.5～16.5
Micron.The shortcoming that document 2 design exists is as follows
(1) 21 degree of optical field of view angle, cause optical measurement scope little, and satellite uses limited；
(2) back work distance is from too small (about 7mm), and the installation causing optical filter and detector is limited, the thermal control system of detector
System is installed limited；
(3) this optical system resolution is low, is only capable of for linear array state infrared earth sensor, it is impossible to red for face battle array static state
Outer earth sensor uses.
In document 3, optical system selects 3 lens arrangements of transmission-type, uses 3 aspheric surfaces, and system focal is
13.75mm, optics bore is 15.28mm, and F#=0.9, aberration meets requirement.The shortcoming that document 3 design exists is as follows
(1) before the aperture diaphragm of system is positioned at the 2nd lens, rather than before first lens, the true energy profit of system
Too low by rate, effective F# is 1.6；
(2) systematical distortion 8.8%, needs individually to carry out image rectification；
Summary of the invention
The technology of the present invention solves problem: overcome the deficiencies in the prior art, it is provided that a kind of face battle array static state infrared earth
Sensor optical system, design of Optical System ensures that effective F# is not more than 1.5, meets product signal to noise ratio requirement；Use 3 mirrors real
Existing；Suppression distortion, in full filed, distortion is less than 0.5%, meets satellite and uses requirement；The system angle of visual field is more than 50 degree, conveniently defends
Star uses；Optical system back work distance is from more than 10mm, it is simple to install optical filter and detector and heat control system.
The technical solution of the present invention is: a kind of face battle array static state infrared earth sensor optical system, including first just
Focal power meniscus lens, the second negative power meniscus lens, the 3rd positive light coke meniscus lens and optical filter；Aperture diaphragm is positioned at meniscus lens
Effectively logical light edge, be used for controlling visual field and veiling glare；Earth far infrared radiation sequentially pass through the first positive light coke meniscus lens,
Second negative power meniscus lens, the 3rd positive light coke meniscus lens converge, then after optical filter filters, at the image planes of detector
Imaging.
First positive light coke meniscus lens, the second negative power meniscus lens, the 3rd positive light coke meniscus lens, optical filter are germanium
Monocrystal material, the first positive light coke meniscus lens, the second negative power meniscus lens, the 3rd positive light coke meniscus lens surface are coated with the reddest
Outer anti-reflection film.
The face r1 of the first positive light coke meniscus lens, face r2 are aspheric surface, and meet relation:
15mm < | R1 | < 22mm,
15mm < | R2 | < 22mm,
0.8 < | R1/R2 | < 1.2,
Wherein, | R1 | for face r1 at the absolute value of the radius of apex, | R2 | for face r2 at radius absolute of apex
Value, and the thickness d 1 of the first positive light coke meniscus lens is satisfied:
3mm<d1<5mm。
The face r3 of the second negative power meniscus lens is aspheric surface, and face r4 is convex spherical, and meets relation:
25mm < | R3 | < 35mm,
25mm < | R4 | < 35mm,
0.8 < | R3/R4 | < 1.2,
Wherein, | R3 | for face r3 at the absolute value of the radius of apex, | R4 | for face r4 at radius absolute of apex
Value, and the thickness d 3 of the second negative power meniscus lens is satisfied:
4mm<d3<6mm。
The face r5 of the 3rd positive light coke meniscus lens is aspheric surface, and face r6 is convex spherical, and meets relation:
40mm < | R5 | < 50mm,
24mm < | R6 | < 32mm,
Wherein, | R5 | for face r5 at the absolute value of the radius of apex, | R6 | for face r6 at radius absolute of apex
Value, and the thickness d 5 of the 3rd positive light coke meniscus lens is satisfied:
4mm<d5<6mm。
The face r7 of optical filter, face r8 are plane, and face r7, face r8 are all coated with multilayer dielectric film, constitute bandpass filter.
Spacing d2 between first positive light coke meniscus lens and the second negative power meniscus lens, the second negative power meniscus lens with
Spacing d4 between 3rd positive light coke meniscus lens, and meet:
Back work distance meets from d6:
d6>10mm。
System focal f, Entry pupil diameters D, optical system F#=f/D, and F# < 1.5.
Present invention advantage compared with prior art is:
(1) optical system F# is not more than 1.5, meets product signal to noise ratio requirement；
(2) optical system uses 3 mirrors to realize, and the optical power losses in eyeglass is low；
(3) by the way of controlling different visual fields chief ray image height, suppression distortion, in full filed, distortion is less than 0.5%, full
Foot satellite uses requirement；
(4) the system angle of visual field 50 degree, facilitate satellite to use；
(5) optical system back work distance is from more than 10mm, it is simple to install optical filter and detector and heat control system.
Accompanying drawing explanation
Fig. 1 is optical system configuration composition of the present invention；
Fig. 2 is parameter label figure in the present invention.
Detailed description of the invention
As it is shown in figure 1, optical system of the present invention includes installing the first positive light coke meniscus lens 1, the second negative power bent moon
Mirror 2, the 3rd positive light coke meniscus lens 3, optical filter 4.Aperture diaphragm is positioned at the most logical plain edge of the first positive light coke meniscus lens 1
Edge, is mainly used in controlling visual field and veiling glare.Earth infra-red radiation is through the first positive light coke meniscus lens 1, and the second negative power is curved
Month mirror 2, after the 3rd positive light coke meniscus lens 3 converges, more filtered 4 is filtered, is incident to detector 5 imaging.
The face r1 of the first positive light coke meniscus lens 1, face r2 are aspheric surface, and the face r3 of the second negative power meniscus lens 2 is non-
Sphere, the face r6 of the 3rd positive light coke meniscus lens 3 is aspheric surface, is used for correcting off-axis aberration.
Embodiment
In this example, the face r1 of the first positive light coke meniscus lens 1 is aspheric surface, | R1 |=18, conic coefficient-0.7, four times
Term coefficient 4.6E-6, six term coefficient 2E-8, face r2 is aspheric surface, | R2 |=18.5, conic coefficient 0.7, four term coefficient
2.5E-5, six term coefficient 2E-8, meet relation:
15<|R1|<22
15<|R2|<22
0.8<|R1/R2|<1.2
Wherein, | R1 | for face r1 at the absolute value of the radius of apex, | R2 | for face r2 at radius absolute of apex
Value.
Thickness d 1=4 of the first positive light coke meniscus lens 1, meets relation:
3<d1<5
In this example, the face r3 of the second negative power meniscus lens 2 is aspheric surface, | R3 |=28, conic coefficient 6, four term systems
Number 5E-6, face r4 are convex spherical, and | R4 |=30 meet relation:
25<|R3|<35
25<|R4|<35
0.8<|R3/R4|<1.2
Wherein, | R3 | is for face r3 at the absolute value of the radius of apex, and | R4 | is the absolute value of face r4 radius.
Thickness d 3=5 of the second negative power meniscus lens 2, meets relation:
4<d3<6
In this example, the face r5 of the 3rd positive light coke meniscus lens 3 is sphere, | R5 |=30, and r6 is aspheric surface, | R6 |=45,
Conic coefficient 5, four term coefficient 6E-6, face r6 is convex spherical, | R6 |=28, and is required to meet relation:
40<|R5|<50
24<|R6|<32
Wherein, | R5 | is for face r5 at the absolute value of the radius of apex, and | R6 | is the absolute value of face r6 radius.
Thickness d 5=5 of the 3rd positive light coke meniscus lens 3, meets relation:
4<d5<6
Spacing d2=7 between first positive light coke meniscus lens 1 and the second negative power meniscus lens 2, the second negative power is curved
Spacing d4=4.8 between month mirror 2 and the 3rd positive light coke meniscus lens 3, meets relation:
9<d2+d4<15
Back work distance, from d6=12, meets relation:
d6>10
System focal f=19.2, Entry pupil diameters D=2h=19.2, optical system F#=f/D=1, meet relation:
F#<1.5
This csr optical system overall length 48mm, light path maximum gauge 46mm, in full filed, distortion is less than 0.3%, system visual field
50 degree.
The content not being described in detail in description of the invention belongs to the known technology of those skilled in the art.
Claims (9)
1. a face battle array static state infrared earth sensor optical system, it is characterised in that: include the first positive light coke meniscus lens
(1), the second negative power meniscus lens (2), the 3rd positive light coke meniscus lens (3) and optical filter (4)；Aperture diaphragm is positioned at meniscus lens
(1) the most logical light edge, is used for controlling visual field and veiling glare；Earth far infrared radiation sequentially passes through the first positive light coke bent moon
Mirror (1), the second negative power meniscus lens (2), the 3rd positive light coke meniscus lens (3) converge, then after optical filter (4) filters,
Imaging at the image planes of detector (5).
A kind of face the most according to claim 1 battle array static state infrared earth sensor optical system, it is characterised in that: first just
Focal power meniscus lens (1), the second negative power meniscus lens (2), the 3rd positive light coke meniscus lens (3), optical filter (4) are germanium list
Brilliant material, the first positive light coke meniscus lens (1), the second negative power meniscus lens (2), the 3rd positive light coke meniscus lens (3) surface
It is coated with far infrared anti-reflection film.
A kind of face the most according to claim 1 battle array static state infrared earth sensor optical system, it is characterised in that: first just
The face r1 of focal power meniscus lens (1), face r2 are aspheric surface, and meet relation:
15mm < | R1 | < 22mm,
15mm < | R2 | < 22mm,
0.8 < | R1/R2 | < 1.2,
Wherein, | R1 | for face r1 at the absolute value of the radius of apex, | R2 | for face r2 at the absolute value of the radius of apex, and
The thickness d 1 of the first positive light coke meniscus lens (1) meets:
3mm<d1<5mm。
A kind of face the most according to claim 1 battle array static state infrared earth sensor optical system, it is characterised in that: second is negative
The face r3 of focal power meniscus lens (2) is aspheric surface, and face r4 is convex spherical, and meets relation:
25mm < | R3 | < 35mm,
25mm < | R4 | < 35mm,
0.8 < | R3/R4 | < 1.2,
Wherein, | R3 | for face r3 at the absolute value of the radius of apex, | R4 | for face r4 at the absolute value of the radius of apex, and
The thickness d 3 of the second negative power meniscus lens (2) meets:
4mm<d3<6mm。
A kind of face the most according to claim 1 battle array static state infrared earth sensor optical system, it is characterised in that: the 3rd just
The face r5 of focal power meniscus lens (3) is aspheric surface, and face r6 is convex spherical, and meets relation:
40mm < | R5 | < 50mm,
24mm < | R6 | < 32mm,
Wherein, | R5 | for face r5 at the absolute value of the radius of apex, | R6 | for face r6 at the absolute value of the radius of apex, and
The thickness d 5 of the 3rd positive light coke meniscus lens (3) meets:
4mm<d5<6mm。
A kind of face the most according to claim 1 battle array static state infrared earth sensor optical system, it is characterised in that: optical filter
(4) face r7, face r8 are plane, and face r7, face r8 are all coated with multilayer dielectric film, constitute bandpass filter.
A kind of face the most according to claim 1 battle array static state infrared earth sensor optical system, it is characterised in that: first just
Spacing d2 between focal power meniscus lens (1) and the second negative power meniscus lens (2), the second negative power meniscus lens (2) and the 3rd
Spacing d4 between positive light coke meniscus lens (3), and meet:
9mm<d2+d4<15mm。
A kind of face the most according to claim 1 battle array static state infrared earth sensor optical system, it is characterised in that: work afterwards
Distance d6 meets:
d6>10mm。
A kind of face the most according to claim 1 battle array static state infrared earth sensor optical system, it is characterised in that: system is burnt
Away from f, Entry pupil diameters D, optical system F#=f/D, and F# < 1.5.
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| CN201610781335.0A CN106199955B (en) | 2016-08-30 | 2016-08-30 | A kind of static infrared earth sensor optical system of face battle array |
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| CN201610781335.0A CN106199955B (en) | 2016-08-30 | 2016-08-30 | A kind of static infrared earth sensor optical system of face battle array |
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| CN106199955A true CN106199955A (en) | 2016-12-07 |
| CN106199955B CN106199955B (en) | 2018-08-31 |
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Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2006119262A (en) * | 2004-10-20 | 2006-05-11 | Matsushita Electric Ind Co Ltd | Imaging lens |
| CN101276038A (en) * | 2007-03-27 | 2008-10-01 | 富士能株式会社 | Imaging lens, camera module, and portable terminal apparatus |
| CN201945744U (en) * | 2010-09-20 | 2011-08-24 | 哈尔滨工业大学 | Refraction type infrared optical system for supersonic guidance |
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2016
- 2016-08-30 CN CN201610781335.0A patent/CN106199955B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2006119262A (en) * | 2004-10-20 | 2006-05-11 | Matsushita Electric Ind Co Ltd | Imaging lens |
| CN101276038A (en) * | 2007-03-27 | 2008-10-01 | 富士能株式会社 | Imaging lens, camera module, and portable terminal apparatus |
| CN201945744U (en) * | 2010-09-20 | 2011-08-24 | 哈尔滨工业大学 | Refraction type infrared optical system for supersonic guidance |
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| CN106199955B (en) | 2018-08-31 |
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