CN114046879B - Space debris spectrum detection optical system - Google Patents
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- CN114046879B CN114046879B CN202111221507.6A CN202111221507A CN114046879B CN 114046879 B CN114046879 B CN 114046879B CN 202111221507 A CN202111221507 A CN 202111221507A CN 114046879 B CN114046879 B CN 114046879B
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01J—MEASUREMENT OF INTENSITY, VELOCITY, SPECTRAL CONTENT, POLARISATION, PHASE OR PULSE CHARACTERISTICS OF INFRARED, VISIBLE OR ULTRAVIOLET LIGHT; COLORIMETRY; RADIATION PYROMETRY
- G01J3/00—Spectrometry; Spectrophotometry; Monochromators; Measuring colours
- G01J3/28—Investigating the spectrum
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01J—MEASUREMENT OF INTENSITY, VELOCITY, SPECTRAL CONTENT, POLARISATION, PHASE OR PULSE CHARACTERISTICS OF INFRARED, VISIBLE OR ULTRAVIOLET LIGHT; COLORIMETRY; RADIATION PYROMETRY
- G01J3/00—Spectrometry; Spectrophotometry; Monochromators; Measuring colours
- G01J3/02—Details
- G01J3/0205—Optical elements not provided otherwise, e.g. optical manifolds, diffusers, windows
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01J—MEASUREMENT OF INTENSITY, VELOCITY, SPECTRAL CONTENT, POLARISATION, PHASE OR PULSE CHARACTERISTICS OF INFRARED, VISIBLE OR ULTRAVIOLET LIGHT; COLORIMETRY; RADIATION PYROMETRY
- G01J3/00—Spectrometry; Spectrophotometry; Monochromators; Measuring colours
- G01J3/02—Details
- G01J3/0205—Optical elements not provided otherwise, e.g. optical manifolds, diffusers, windows
- G01J3/0208—Optical elements not provided otherwise, e.g. optical manifolds, diffusers, windows using focussing or collimating elements, e.g. lenses or mirrors; performing aberration correction
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01J—MEASUREMENT OF INTENSITY, VELOCITY, SPECTRAL CONTENT, POLARISATION, PHASE OR PULSE CHARACTERISTICS OF INFRARED, VISIBLE OR ULTRAVIOLET LIGHT; COLORIMETRY; RADIATION PYROMETRY
- G01J3/00—Spectrometry; Spectrophotometry; Monochromators; Measuring colours
- G01J3/02—Details
- G01J3/0205—Optical elements not provided otherwise, e.g. optical manifolds, diffusers, windows
- G01J3/0229—Optical elements not provided otherwise, e.g. optical manifolds, diffusers, windows using masks, aperture plates, spatial light modulators or spatial filters, e.g. reflective filters
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Abstract
The invention particularly relates to a space debris spectrum detection optical system which is used for solving the problems of large field of view, small entrance pupil diameter and narrow light spectrum range in spectrum detection in the conventional optical system. A space debris spectrum detection optical system; the device comprises an aperture diaphragm, a first reflector, a second reflector, a third reflector and a light splitting substrate which are sequentially arranged along the light propagation direction, wherein the first reflector, the second reflector and the third reflector are aspheric surfaces for the second time; the aperture diaphragm is positioned on the optical axis of the system. The optical system provided by the invention adopts a total reflection type structure, and the spectral range of the system is wide; the light splitting component is positioned in front of a focal plane in the system, and has small size and light weight; the primary image surface of the system is not in the imaging light beam, the field diaphragm can be installed, and the system has a real exit pupil and a Liao diaphragm, so that the stray light inhibition effect is excellent; the system has flexible and various light splitting forms, and can adopt light splitting elements such as a filter set, a grating, a prism grating and the like to perform spectrum light splitting.
Description
Technical Field
The invention belongs to the technical field of space optical systems, and particularly relates to a space debris spectrum detection optical system.
Background
Space debris refers to objects that orbit the earth and are in space, such as thrusters, shields, satellite debris, failed satellites, and the like. Space debris seriously threatens the safety of the on-orbit operation spacecraft, and the collision between the space debris and the spacecraft causes damage to the surface of the spacecraft, so that a spacecraft system is in failure, and more debris is generated at the same time. Meanwhile, in recent years, human space activities are more and more frequent, and the number of space fragments is more and more, so that the space environment is increasingly deteriorated. The spectrum classification and identification of the space debris can provide a technical basis for the integrated detection and identification of the space debris, provide an information basis for the avoidance of the space debris and the space safety, and ensure the on-orbit operation safety of the spacecraft.
The increase of the field of view, the aperture and the spectral range of the optical system directly affects the spherical aberration, the coma aberration, the distortion, the field curvature and the vertical axis chromatic aberration of the optical system, and the design difficulty of the system is greatly increased. When the optical system disclosed by the prior art is applied to space debris spectrum detection, the entrance pupil with a large view field is small in diameter, and the detection capability of the system is limited. Meanwhile, the spectrum range of the light is narrow, and the requirements of an optical system for spectral detection of space debris cannot be met
Disclosure of Invention
The invention aims to provide a total reflection type space debris spectrum detection optical system, which solves the problems of large field of view, small entrance pupil diameter and narrow optical spectrum range in spectrum detection in the conventional optical system.
The technical scheme of the invention is as follows:
the space debris spectrum detection optical system is characterized by comprising an aperture diaphragm, a first reflector, a second reflector, a third reflector and a light splitting substrate which are sequentially arranged along the light propagation direction, wherein the front surface and the rear surface of the first reflector, the front surface and the rear surface of the second reflector and the front surface and the rear surface of the third reflector are both secondary aspheric surfaces; a detector image surface is arranged behind the light path of the light splitting substrate;
the aperture diaphragm is positioned on the optical axis of the system;
radius R of the first reflector 1 Satisfies the following conditions with the system focal length f: -1.5f<R 1 <1.2f, distance to the aperture stop is: 312 mm-350 mm, and the translation distance of the first reflector relative to the Y axis is as follows: -230mm to-195 mm and the angle of rotation about the X axis is: -4.5 ° -3.28 °;
radius R of the second reflector 2 Satisfies the following conditions with the system focal length f: -0.5f<R 2 <-0.31f, the distance to the first mirror is: 300 mm-330 mm, and the translation distance of the second reflector relative to the Y axis is as follows: -7.22mm to 2.22mm and the angle of rotation about the X axis is: -4.68 ° to-2.68 °;
radius R of the third reflector 3 Satisfies the following conditions with the system focal length f: -0.82f<R 3 <-0.7f, distance from the second mirror: 400 mm-440 mm, and the third reflector translates along the Y-axis from-48.5 mm to-25 mm, and rotates around the X-axis by the following rotation angle: -6.5 to-4 °;
the distance from the light splitting substrate to the third reflector is as follows: 310 mm-390 mm, thickness 5mm, and the distance to the detector image surface is 41.3 mm-65 mm, and the translation distance of the light splitting substrate relative to the Y axis is: -52.1mm to-30 mm and the angle of rotation about the X axis is: -7.5 to-4.5.
Further, the front and back surfaces of the first reflector are quadratic aspheric surfaces, and the expression is as follows:
wherein K is: -0.81 to-0.61, z is aspheric surface rise under different calibers, c is aspheric surface curvature, K is quadric surface coefficient, and r is aspheric surface half caliber.
Further, the second reflecting mirror front and back surfaces are quadratic aspheric surface expressions as follows:
wherein K is: 7.7 to 5.5, z is aspheric surface rise under different calibers, c is aspheric surface curvature, K is quadric surface coefficient, and r is aspheric surface half caliber.
Further, the front surface and the rear surface of the third reflector (4) are second-order aspheric surfaces, and the expression is as follows:
wherein K is: -0.2 to-0.02, z is aspheric surface rise under different calibers, c is aspheric surface curvature, K is quadric surface coefficient, and r is aspheric surface half caliber.
Further, R in the first reflector 1 Comprises the following steps: 685.3mm, the distance from the first mirror to the aperture stop being: 333mm, the translation distance of the first mirror relative to the Y axis is: -212mm and the angle of rotation about the X axis is: -3.88 °;
r in the second reflector 2 Comprises the following steps: 211.85mm, the distance of the second mirror front surface to the first mirror rear surface being: 313.4mm, the second mirror is translated by a distance relative to the Y-axis: 5.22mm and the angle of rotation about the X axis is: -3.68 °;
r in the third reflector 3 Comprises the following steps: 390.0mm, the distance from the front surface of the third mirror to the rear surface of the second mirror being: 414.5mm, the third mirror is translated by a distance relative to the Y-axis: -38.53mm and the angle of rotation around the X-axis is: -5.43 °;
the distance from the front surface of the light splitting substrate to the rear surface of the third reflector is as follows: 352mm, the distance from the rear surface of the light splitting substrate to the image surface of the detector is as follows: 51.3mm, the translation distance of the spectroscopic substrate relative to the Y axis is as follows: 40.266mm and the angle of rotation about the X axis is: -6.65 °.
Furthermore, the light splitting substrate is made of quartz materials, and the front surface and the rear surface of the light splitting substrate are both flat surfaces.
Furthermore, the light splitting substrate is arranged on the filter wheel, and any one or a combination of a filter set, a grating or a prism grating is arranged on the light splitting substrate.
Compared with the prior art, the space debris spectrum detection optical system has the beneficial effects that:
1. the optical system provided by the invention adopts a total reflection type structure, and the spectral range of the system is wide.
2. The light splitting substrate is positioned in front of a focal plane in a system, and any one or more combinations of a filter set, a grating or a prism grating are arranged on the light splitting substrate, so that the light splitting substrate has small integral size and light weight and can realize multiple functions.
3. In the optical system provided by the invention, the primary image surface of the system is not in the imaging light beam, and a parasitic light diaphragm can be installed; the lens has a real exit pupil, a Lyot diaphragm is arranged at the exit pupil, and the stray light inhibition effect is excellent.
4. In the optical system provided by the invention, the system light splitting forms are flexible and various, and light splitting elements such as a filter set, a grating, a prism grating and the like can be adopted for spectral light splitting.
Drawings
FIG. 1 is a schematic structural diagram of a space debris spectrum detection optical system provided by the present invention;
fig. 2 is a schematic structural diagram of a spectroscopic substrate of the space debris spectrum detection optical system provided in this embodiment;
fig. 3 is a graph of energy concentration curves of the space debris spectrum detection optical system according to the present embodiment;
fig. 4 is a second graph of the energy concentration curve of the optical system for detecting spatial debris spectrum provided in this embodiment.
The reference numerals are specifically as follows:
in the figure, 1, an aperture diaphragm, 2, a first reflector, 3, a second reflector, 4, a third reflector, 5 and a light splitting substrate.
Detailed Description
The present embodiment provides a space debris spectrum detection optical system, wherein: the entrance pupil diameter is 150mm, the spectral range is 400nm-1000nm, the field angle is 2.5 degrees by 2.5 degrees, and the invention is further explained by combining the attached drawings.
As shown in fig. 1, the optical system for detecting a space debris spectrum provided by the present invention includes a system aperture diaphragm 1, a first reflector 2, a second reflector 3, a third reflector 4, and a light splitting substrate 5, which are sequentially arranged along a light propagation direction, wherein a detector image plane is further arranged behind a light path of the light splitting substrate 5, wherein the first reflector 2, the second reflector 3, and the third reflector 4 are all aspheric surfaces, and the light splitting substrate 5 is a plurality of filter sets or gratings or prisms; the aperture diaphragm 1 is located on the system optical axis, and the optical axis is along the Z-axis direction.
Radius R of the first reflector 2 1 Satisfies the following conditions with the system focal length f: -1.5f<R 1 <1.2f (preferred R in this example) 1 Is-685.3 mm, in this example f is-500), the distance to the aperture stop 1 is: 312mm to 350mm (in the present embodiment, the distance from the first reflection to the aperture stop 1 is preferably 333 mm), while the first mirror 2 is translated along the Y axis: 230mm to 195mm (in the present embodiment the preferred first mirror 2 translates-212 mm along the Y-axis) and rotates about the X-axis: -4.5 ° -3.28 ° (the preferred first mirror 2 rotates around the X-axis-3.88 ° in this embodiment); the first reflector 2 is a secondary aspheric surface and is mainly used for correcting the spherical aberration of the system and expressing the spherical aberrationThe formula is as follows:
wherein K is: the vector height of the aspheric surface under different calibers is-0.81 to-0.61, z is the vector height of the aspheric surface under different calibers, c is the curvature of the aspheric surface, K is the coefficient of a quadric surface, and r is the half-calibre of the aspheric surface.
The radius R2 of the second mirror 3 and the system focal length f satisfy: -0.5f < -R2 < -0.31f (in the present embodiment, preferably R2 is-211.85 mm), and the distance to the first reflecting mirror 2 is: 300mm to 330mm (in this embodiment the preferred distance from the front surface of the second mirror 3 to the back surface of the first mirror 2 is 313.4 mm), while the second mirror 3 is translated along the Y-axis: 7.22mm to 2.22mm (the preferred second mirror 3 in this embodiment translates-5.22 mm along the Y-axis) and rotates about the X-axis between-4.68 and-2.68 (the preferred second mirror 3 in this embodiment rotates-3.68 about the X-axis); the second reflector 3 is a secondary aspheric surface and is mainly used for correcting the primary aberrations such as spherical aberration, coma aberration and the like of the system, and the expression is as follows:
wherein K is: 7.7 to 5.5, z is aspheric surface rise under different calibers, c is aspheric surface curvature, K is quadric surface coefficient, and r is aspheric surface half caliber.
The radius R3 of the third reflector 4 and the system focal length f satisfy: -0.82f and sR3 < -0.7f (in this embodiment, the preferred R3 is-390.0 mm), and the distance from the second mirror 3 is: 400mm to 440mm (in this embodiment, the preferred distance from the front surface of the third mirror 4 to the back surface of the second mirror 3 is 414.5 mm), while the third mirror 4 is translated along the Y-axis: 48.5mm to-25 mm (in this embodiment the preferred third mirror 4 translates-38.53 mm along the Y axis) and rotates about the X axis: -6.5 ° -4 ° (the preferred third mirror 4 in this embodiment is rotated-5.43 ° around the X-axis); the third reflector 4 is a secondary aspheric surface and is mainly used for balancing the primary aberrations such as spherical aberration, coma aberration and the like of the system, and the expression is as follows:
wherein K is: -0.2 to-0.02, z is aspheric surface rise under different calibers, c is aspheric surface curvature, K is quadric surface coefficient, and r is aspheric surface half caliber.
The light splitting substrate 5 is made of quartz materials and can transmit most spectral bands, the front surface and the rear surface of the light splitting substrate 5 are both planes, and one or more of a filter set, a grating and a prism grating are selected to be combined and used according to the actual light splitting mode and the spectral detection requirement. The distance from the spectroscopic substrate 5 to the vertex of the third reflector 4 is: 310mm to 390mm (in this embodiment, the distance from the front surface of the spectroscopic substrate 5 to the vertex of the third reflector 4 is 352 mm.), the thickness is 5mm, the distance to the image plane of the detector is 41.3mm to 65mm (in this embodiment, the distance from the rear surface of the spectroscopic substrate 5 to the image plane of the detector is 51.3 mm), and simultaneously the spectroscopic substrate 5 is translated along the Y axis: -52.1mm to-30 mm (in this embodiment the preferred spectroscopic substrate 5 is translated by-40.266 mm along the Y-axis) and rotated around the X-axis: -7.5 ° -4.5 ° (the preferred spectroscopic substrate 5 in this embodiment is rotated-6.65 ° around the X axis).
The spectroscopic substrate 5 is mounted on a rotary filter wheel.
An image plane is present once in the optical path between the second mirror 3 and the third mirror 4.
An exit pupil is present at the conjugate position of the aperture stop.
The exit pupil and the primary image surface are provided with diaphragms for intercepting stray light. In this embodiment, the primary image plane is provided with a veiling glare diaphragm, and the exit pupil is provided with a rio diaphragm.
As shown in fig. 2, the spectroscopic substrate 5 is mounted on the filter wheel and is separated by a filter set, a grating, and a prism grating with different spectral wavelengths.
As shown in fig. 3 and 4, the above embodiments provide power concentration profiles of the optical system at different angles. The result is that 80% of the energy radii in the full field of view of the system are less than 20 μm.
Claims (7)
1. A space debris spectrum detection optical system, characterized in that: the optical system comprises an aperture diaphragm (1), a first reflector (2), a second reflector (3), a third reflector (4) and a light splitting substrate (5) which are sequentially arranged along the light propagation direction, wherein the front surface and the rear surface of the first reflector (2), the rear surface of the second reflector (3) and the front surface and the rear surface of the third reflector (4) are respectively a secondary aspheric surface, the first reflector (2) is used for correcting the spherical aberration of the system, the second reflector (3) is used for correcting the primary aberrations such as the spherical aberration and the coma aberration of the system, and the third reflector (4) is used for balancing the primary aberrations such as the spherical aberration and the coma aberration of the system; a detector image surface is also arranged behind the light path of the light splitting substrate (5);
the aperture diaphragm (1) is positioned on the optical axis of the system;
radius R of the first reflector (2) 1 Satisfies the following conditions with the system focal length f: -1.5f<R 1 <-1.2f, the distance to the aperture stop (1) being: 312 mm-350 mm, and the translation distance of the first reflector (2) relative to the Y axis is as follows: -230mm to-195 mm and the angle of rotation about the X axis is: -4.5 ° -3.28 °;
radius R of the second mirror (3) 2 Satisfies the following conditions with the system focal length f: -0.5f<R 2 <-0.31f, the distance to the first mirror (2) being: 300 mm-330 mm, and the translation distance of the second reflector (3) relative to the Y axis is as follows: -7.22mm to 2.22mm and the angle of rotation about the X axis is: -4.68 ° to-2.68 °;
radius R of the third reflector (4) 3 Satisfies the following conditions with the system focal length f: -0.82f<R 3 <-0.7f, the distance to the second mirror (3) being: 400mm to 440mm, while the third mirror (4) is translated along the Y-axis by-48.5 mm to-25 mm and rotated about the X-axis by a rotation angle of: -6.5 to-4 °;
the distance from the light splitting substrate (5) to the third reflector (4) is as follows: 310 mm-390 mm, thickness 5mm, and the distance to the detector image plane is 41.3 mm-65 mm, and the translation distance of the light splitting substrate (5) relative to the Y axis is as follows: -52.1mm to-30 mm, and the angle of rotation about the X axis is: -7.5 to-4.5.
2. The space debris spectrum detection optical system according to claim 1, wherein: the front surface and the rear surface of the first reflector (2) are quadratic aspheric surfaces, and the expression is as follows:
wherein K is: the vector height of the aspheric surface under different calibers is-0.81 to-0.61, z is the vector height of the aspheric surface under different calibers, c is the curvature of the aspheric surface, K is the coefficient of a quadric surface, and r is the half-calibre of the aspheric surface.
3. The space debris spectrum detection optical system according to claim 2, wherein: the expression of the second aspheric surface of the front and back surfaces of the second reflector (3) is as follows:
wherein K is: and the z is the height of the aspheric surface under different calibers, the c is the curvature of the aspheric surface, the K is the coefficient of a quadric surface, and the r is the half caliber of the aspheric surface.
4. A space debris spectrum detection optical system according to claim 3, wherein: the front surface and the rear surface of the third reflector (4) are second-order aspheric surfaces, and the expression is as follows:
wherein K is: -0.2 to-0.02, z is aspheric surface rise under different calibers, c is aspheric surface curvature, K is quadric surface coefficient, and r is aspheric surface half caliber.
5. The space debris spectrum detection optical system according to claim 1, wherein:
r in the first reflector (2) 1 Comprises the following steps: 685.3mm, the distance of the first mirror (2) from the aperture stop (1) being: 333mm, the translation distance of the first reflector (2) relative to the Y axis is as follows: 212mm and rotation about the X axisThe rotation angle of (c) is: -3.88 °;
r in the second reflector (3) 2 Comprises the following steps: -211.85mm, the distance from the front surface of the second mirror (3) to the back surface of the first mirror (2) being: 313.4mm, the second mirror (3) is translated by a distance relative to the Y axis: 5.22mm and the angle of rotation about the X axis is: -3.68 °;
r in the third reflector (4) 3 Comprises the following steps: 390.0mm, the distance from the front surface of the third mirror (4) to the rear surface of the second mirror (3) being: 414.5mm, the third mirror (4) is translated by a distance relative to the Y axis: -38.53mm and the angle of rotation around the X-axis is: -5.43 °;
the distance from the front surface of the light splitting substrate (5) to the rear surface of the third reflector (4) is as follows: 352mm, the distance from the rear surface of the light splitting substrate (5) to the image surface of the detector is as follows: 51.3mm, and the translation distance of the light splitting substrate (5) relative to the Y axis is as follows: 40.266mm and the angle of rotation about the X axis is: -6.65 °.
6. The space debris spectrum detection optical system according to claim 5, wherein: the light splitting substrate (5) is made of quartz materials, and the front surface and the rear surface of the light splitting substrate are both planes.
7. The space debris spectrum detection optical system according to claim 6, wherein: the light splitting substrate (5) is arranged on the filter wheel, and any one or more of a filter set, a grating or a prism grating is arranged on the light splitting substrate (5).
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