CN114994890A - Dual-waveband off-axis total reflection optical system for space remote sensing satellite - Google Patents
Dual-waveband off-axis total reflection optical system for space remote sensing satellite Download PDFInfo
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- G02B17/06—Catoptric systems, e.g. image erecting and reversing system using mirrors only, i.e. having only one curved mirror
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Abstract
The invention relates to a dual-waveband off-axis total reflection optical system for a space remote sensing satellite, which sequentially comprises an aperture diaphragm, a first reflector, a second reflector, a third reflector and a fourth reflector from an object space to an image space; the light rays are reflected to the second reflector by the first reflector through the aperture diaphragm, then reflected to the third reflector by the second reflector, and finally reflected to the fourth reflector M4 by the third reflector; and the surface types of the first reflector, the second reflector, the third reflector and the fourth reflector adopt even-order aspheric surface design. The design of the invention is beneficial to improving the degree of freedom of the optimized design, better reducing and balancing various aberrations, and being capable of obtaining clearer imaging in both day and night. The system finally realizes the characteristics of no central blocking, wide working wave band, large field angle, long focal length, large caliber, compact structure, small volume, easy processing and installation and the like.
Description
Technical Field
The invention relates to the field of total reflection optical systems, in particular to a double-waveband off-axis total reflection optical system for a space remote sensing satellite.
Background
With the development of modern science and technology, the requirements of the space optical field on target detection and identification are higher and higher, and the space optical instrument gradually develops towards the directions of large field of view, high resolution, miniaturization, light weight and the like, which brings challenges to the design of an optical system in the scientific instrument. The reflection type optical system has the advantages of no chromatic aberration, no secondary spectrum problem, foldable light path, small volume, insensitivity to temperature and pressure change and the like, so that the reflection type optical system has obvious advantages in excellent image quality, light weight, large caliber and multiband design, and is widely applied to the technical field of space remote sensing. In view of the fact that most of off-axis total reflection optical systems designed at present adopt three reflectors and a traditional spherical surface as optical elements, system index parameters are difficult to improve, aberration correction is difficult, the working waveband is short, and the like. Therefore, the off-axis full-reflection optical system with large field of view, large caliber, high imaging performance and compact structure is designed to be a problem to be solved urgently in the research of the space remote sensing satellite.
Disclosure of Invention
In order to solve the problems of the existing off-axis total reflection optical system, compared with a three-mirror system, the off-axis four-mirror optical system has more design freedom and strong aberration balance and correction capability, so that the system has the characteristics of smaller system length and focal length ratio, large view field, high imaging quality, good stray light inhibition capability and the like, therefore, the invention establishes the aberration optimization function of the system based on the aberration theory of the coaxial total reflection optical system, and the coaxial total reflection optical system structure is off-axis and inclined, and the optical design software Zemax is combined to continuously correct the aberration, and finally, the dual-waveband off-axis total reflection optical system for the space remote sensing satellite is designed, in the system design, the surface types of the first reflecting mirror M1, the second reflecting mirror M2, the third reflecting mirror M3 and the fourth reflecting mirror M4 adopt even-order aspheric surface design; the system has the characteristics of no central block, wide working wave band, large field angle, long focal length, large caliber, compact structure, small volume, easy processing and installation and the like.
The invention adopts the following technical scheme: a dual-waveband off-axis total reflection optical system for a space remote sensing satellite comprises an aperture diaphragm, a first reflector, a second reflector, a third reflector and a fourth reflector in sequence from an object space to an image space; the light rays are reflected to the second reflector from the first reflector through the aperture diaphragm, then reflected to the third reflector from the second reflector, and finally reflected to the fourth reflector M4 from the third reflector; and the surface types of the first reflector, the second reflector, the third reflector and the fourth reflector adopt even-order aspheric surface design.
Preferably, the first reactionThe surface types of the reflector M1, the second reflector M2, the third reflector M3 and the fourth reflector M4 are all designed by adopting an even aspheric surface, and the surface type expression of the even aspheric surface meets the following equation:
wherein Z is aspheric sagittal height, c is aspheric paraxial curvature, y is lens caliber, k is cone coefficient, a i Is the 2 i-th aspheric coefficient.
Preferably, the aspherical surface profile coefficient k of the first mirror is-1.12, a 2 ＝-7.63×10 -10 ， a 3 ＝-7.80×10 -15 ，a 4 ＝-6.13×10 -19 ，a 5 ＝-7.19×10 -24 And the rest a i The coefficients are all 0.
Preferably, the aspheric surface profile factor k of the second mirror is-3.97, a 2 ＝1.39×10 -7 ， a 3 ＝-1.89×10 -11 ，a 4 ＝1.51×10 -15 ，a 5 ＝-2.90×10 -20 And the rest a i The coefficients are all 0.
Preferably, the third mirror has an aspheric surface profile coefficient k-235.50, a 2 ＝-1.39×10 -10 ， a 3 ＝-3.96×10 -11 ，a 4 ＝1.90×10 -14 ，a 5 ＝-1.60×10 -18 And the rest a i The coefficients are all 0.
Preferably, the aspherical surface profile coefficient k of the fourth mirror is-0.51, a 2 ＝8.53×10 -8 ， a 3 ＝-1.85×10 -12 ，a 4 ＝-4.88×10 -15 ，a 5 ＝5.58×10 -18 And the rest a i The coefficients are all 0.
Preferably, the spectral range of the optical system is 400nm to 1500 nm.
Preferably, the radius of the first mirror is-210 mm < R1< -205mm, the distance value between the center of the first mirror and the center of the second mirror is-80 mm < L1< -70 mm; the radius of the second mirror is-90 mm < R2< -80mm, and the distance value between the center of the second mirror and the center of the third mirror is 80mm < L2<90 mm; the radius of the third reflector is 330mm < R3<340mm, and the distance value between the center of the third reflector and the center of the fourth reflector is-70 mm < L3< -65 mm; the radius of the fourth mirror is 95mm < R4<100mm, and the distance value between the center of the fourth mirror and the center of the image plane is 220mm < L4<225 mm.
The invention has the following beneficial effects: the dual-waveband off-axis total reflection optical system for the space remote sensing satellite is an off-axis four-mirror optical system, so that the degree of freedom of optimization design is improved, various aberrations are reduced and balanced better, and clear imaging can be achieved in the daytime and at night. The system finally realizes the characteristics of no central blocking, wide working waveband, large field angle, long focal length, large caliber, compact structure, small volume, easy processing and installation and the like.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings that are required to be used in the embodiments will be briefly described below, it should be understood that the following drawings only illustrate some embodiments of the present invention and therefore should not be considered as limiting the scope, and for those skilled in the art, other related drawings can be obtained according to the drawings without inventive efforts.
FIG. 1 is a schematic structural diagram of a two-waveband off-axis total reflection optical system for a space remote sensing satellite according to the invention;
FIG. 2 is a graph of the Modulation Transfer Function (MTF) according to a two-band off-axis total reflection optical system for a space remote sensing satellite shown in FIG. 1;
FIG. 3 is a comparative plot of a dual band off-axis total reflection optical system for a satellite for remote space sensing according to FIG. 1;
in the figure: 1-first mirror M1; 2-second mirror M2; 3-third mirror M3; 4-fourth mirror M4; 5-aperture diaphragm.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention more apparent, the embodiments of the present invention will be described in detail and completely with reference to the accompanying drawings, and it is to be understood that the described embodiments are a part of the embodiments of the present invention, but not all of the embodiments of the present invention. All other embodiments obtained by a person of ordinary skill in the art based on the embodiments of the present invention without any creative effort belong to the protection scope of the present invention. Thus, the following detailed description of the embodiments of the present invention, presented in the figures, is not intended to limit the scope of the invention, as claimed, but is merely representative of selected embodiments of the invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", and the like, indicate orientations and positional relationships based on those shown in the drawings, and are used merely for convenience of description and for simplicity of description, and do not indicate or imply that the referenced device or element must have a particular orientation, be constructed and operated in a particular orientation, and thus are not to be considered as limiting the present invention.
Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless specifically defined otherwise.
In the present invention, unless otherwise explicitly stated or limited, the terms "mounted," "connected," "fixed," and the like are to be construed broadly, e.g., as being permanently connected, detachably connected, or integral; can be mechanically or electrically connected; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meaning of the above terms in the present invention can be understood according to specific situations by those of ordinary skill in the art.
In the present invention, unless expressly stated or limited otherwise, the recitation of a first feature "on" or "under" a second feature may include the recitation of the first and second features being in direct contact, and may also include the recitation of the first and second features not being in direct contact, but being in contact with another feature between them. Also, the first feature being "on," "above" and "over" the second feature includes the first feature being directly on and obliquely above the second feature, or merely indicating that the first feature is at a higher level than the second feature. The first feature being "under," "below," and "beneath" the second feature includes the first feature being directly under and diagonally under the second feature, or simply means that the first feature is at a lesser elevation than the second feature.
Examples
The following are only preferred embodiments of the present invention, and the scope of the present invention is not limited to the following examples, and all technical solutions belonging to the idea of the present invention belong to the scope of the present invention.
Referring to the attached figures 1-3 of the specification, the optical system comprises an aperture diaphragm, a first reflector M1, a second reflector M2, a third reflector M3 and a fourth reflector M4 from an object side to an image side. The light is reflected to the second reflector M2 by the first reflector M1, then reflected to the third reflector M3 by the second reflector M2, and finally reflected to the fourth reflector M4 by the third reflector M3; and the surface shapes of the first reflector, the second reflector M2, the third reflector M3 and the fourth reflector M4 are all designed to be even aspheric surfaces.
The clear aperture of the optical system is 80mm, the field angle is 2 degrees, the focal length is 800mm, the total length is 265.3mm, and the spectral range is 400 nm-1500 nm.
The radius of the first mirror M1 is-208.83 mm, and the distance between the center of the first mirror M1 and the center of the second mirror M2 is-75.96 mm; the second mirror M2 has a radius of-85.81 mm and the second mirror M2 has a center at a distance of 82.12mm from the center of the third mirror M3; the radius of the third reflector M3 is 332.1mm, and the distance value between the center of the third reflector M3 and the center of the fourth reflector M4 is-69.26 mm; the radius of the fourth mirror M4 is 95.92mm, and the distance value between the center of the fourth mirror M4 and the center of the image plane is 220.33 mm.
The surface types of the first reflector M1, the second reflector M2, the third reflector M3 and the fourth reflector M4 are all designed by adopting an even aspheric surface, and the surface type expression of the even aspheric surface satisfies the following equation:
wherein Z is aspheric sagittal height, c is aspheric paraxial curvature, y is lens caliber, k is cone coefficient, a i Is the 2 i-th aspheric coefficient.
In this example, the optical parameters of each mirror are shown in Table 1
TABLE 1 optical parameters of a dual-band off-axis total reflection optical system for space remote sensing satellites
Description figure 2 shows a Modulation Transfer Function (MTF) graph of a two-waveband off-axis total reflection optical system for a space remote sensing satellite under the condition that the space frequency is 40lp/mm, from figure 2, it can be obtained that MTF values in the meridian and sagittal directions are respectively greater than 0.28 and 0.33 at the maximum field of view, MTF curves in the meridian and sagittal directions are relatively smooth, and the difference between the MTF values in the two directions is small, which indicates that the optical system has high imaging quality; in addition, the attached fig. 3 in the specification is a relative illumination graph of a two-waveband off-axis total reflection optical system for a space remote sensing satellite, and it can be seen from fig. 3 that the relative illumination in the full view field range is greater than 0.95.
In summary, with the technical scheme of the invention, the dual-band off-axis total reflection optical system for the space remote sensing satellite has the characteristics of no central blocking, wide working band, large field angle, long focal length, large caliber, compact structure, small volume, easiness in processing and installation and the like.
Claims (8)
1. A dual-waveband off-axis total reflection optical system for a space remote sensing satellite is characterized by comprising an aperture diaphragm, a first reflector, a second reflector, a third reflector and a fourth reflector in sequence from an object side to an image side; the light rays are reflected to the second reflector by the first reflector through the aperture diaphragm, then reflected to the third reflector by the second reflector, and finally reflected to the fourth reflector M4 by the third reflector; and the surface types of the first reflector, the second reflector, the third reflector and the fourth reflector adopt even-order aspheric surface design.
2. The optical system of claim 1, which is used for the dual-waveband off-axis total reflection optical system of the space remote sensing satellite, and is characterized in that: the surface types of the first reflector M1, the second reflector M2, the third reflector M3 and the fourth reflector M4 are all designed by adopting an even aspheric surface, and the surface type expression of the even aspheric surface satisfies the following equation:
wherein Z is aspheric sagittal height, c is aspheric paraxial curvature, y is lens caliber, k is cone coefficient, a i Is the 2 i-th aspheric coefficient.
3. The optical system of claim 2, which is used for the dual-waveband off-axis total reflection optical system of the space remote sensing satellite, and is characterized in that: the aspheric surface type coefficient k of the first reflector is-1.12, a 2 ＝-7.63×10 -10 ，a 3 ＝-7.80×10 -15 ，a 4 ＝-6.13×10 -19 ，a 5 ＝-7.19×10 -24 And the rest a i The coefficients are all 0.
4. The optical system of claim 2, which is used for the dual-waveband off-axis total reflection optical system of the space remote sensing satellite, and is characterized in that: the aspheric surface type coefficient k of the second reflector is-3.97, a 2 ＝1.39×10 -7 ，a 3 ＝-1.89×10 -11 ，a 4 ＝1.51×10 -15 ，a 5 ＝-2.90×10 -20 And the rest a i The coefficients are all 0.
5. The optical system according to claim 2, characterized in that: the third reflector has an aspheric surface coefficient k of-235.50, a 2 ＝-1.39×10 -10 ，a 3 ＝-3.96×10 -11 ，a 4 ＝1.90×10 -14 ，a 5 ＝-1.60×10 -18 And the rest a i The coefficients are all 0.
6. The optical system of claim 2, which is used for the dual-waveband off-axis total reflection optical system of the space remote sensing satellite, and is characterized in that: the aspheric surface type coefficient k of the fourth reflecting mirror is-0.51, a 2 ＝8.53×10 -8 ，a 3 ＝-1.85×10 -12 ，a 4 ＝-4.88×10 -15 ，a 5 ＝5.58×10 -18 And the rest a i The coefficients are all 0.
7. The optical system according to claim 1 or 2, characterized in that: the spectral range of the optical system is 400 nm-1500 nm.
8. The optical system according to claim 1 or 2, characterized in that: the radius of the first mirror is-210 mm < R1< -205mm, and the distance value between the center of the first mirror and the center of the second mirror is-80 mm < L1< -70 mm; the radius of the second mirror is-90 mm < R2< -80mm, and the distance value between the center of the second mirror and the center of the third mirror is 80mm < L2<90 mm; the radius of the third reflector is 330mm < R3<340mm, and the distance value between the center of the third reflector and the center of the fourth reflector is-70 mm < L3< -65 mm; the radius of the fourth mirror is 95mm < R4<100mm, and the distance value between the center of the fourth mirror and the center of the image plane is 220mm < L4<225 mm.
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2022
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