Space debris detection optical system with active and passive composite

Abstract

The application discloses a kind of space debris detection optical systems with active and passive composite, belong to space debris detection field in aerospace.The application includes the front fixed group of first piece of lens, second piece of lens, third piece of lens composition, and is divided into two detection channels by fourth piece of parallel glass mirror, and fifth piece of lens, sixth piece of lens, seventh piece of lens, eighth piece of lens, ninth piece of lens composition visible light channel lens group;Tenth piece of lens, eleventh piece of lens;Twelfth piece of lens, thirteenth piece of lens composition laser group;In the image space of laser radar receiving system, join fourteenth piece of prism and laser radar transmitting system to form the transmitting channel lens group of laser radar.The application uses visible light channel to capture wide-area space debris, and small field of view is used to accurately position space debris in laser channel, and space debris can be searched and identified in space environment using laser channel and visible light channel two channels.

Description

Technical Field

[0001] This invention relates to a combined active and passive space detection optical system, belonging to the field of space debris detection. Background Technology

[0002] Space exploration optics is an optical detection technology that effectively acquires information about space debris in a short time. Space debris mainly arises from the disintegration of satellites in their orbits after failure, and from debris generated when rockets propel satellites into orbit and then break away. Currently, there are tens of thousands of pieces of space debris in space. Even though many pieces re-enter the atmosphere each year, the number of millimeter-sized and centimeter-sized pieces still poses a significant threat to spacecraft operations. Centimeter-sized debris can cause complete damage to a spacecraft, while continuous impacts from millimeter-sized or micrometer-sized debris can lead to performance degradation or functional failure.

[0003] Currently, the main space exploration methods used worldwide are space-based and ground-based. Ground-based telescopes employ traditional space debris monitoring, but lack the ability to detect new space debris and are easily limited by lighting and weather conditions, allowing monitoring only during dawn and dusk. In traditional space-based detection methods, passive optical imaging systems have limitations such as weak perception of various aspects of the target and single-channel imaging. A hybrid active-passive space exploration optical system is proposed. This system can complete the task of detecting and identifying space debris through multi-channel, active laser detection and passive visible light detection. Furthermore, because it is a hybrid system, its overall weight and size are smaller than two separate systems, making it more convenient, faster, and more accurate. Summary of the Invention

[0004] The purpose of this invention is to provide a combined active and passive optical system for space debris detection. This system employs a visible light channel to capture space debris over a wide area, and after determining the specific location of the debris, uses a laser channel with a small field of view to precisely locate it. This method enables the detection of space debris across different spectral bands and the search and precise location of space debris in a wide area of ​​space. This invention allows for the search and identification of space debris using both laser and visible light channels in a space environment.

[0005] The objective of this invention is achieved through the following technical solution.

[0006] This invention discloses a space debris detection optical system with active and passive composite capabilities. It includes a front fixed group consisting of a first lens, a second lens, and a third lens. These three lenses are eighth-order even-order aspherical surfaces. The incident visible light beam and laser beam undergo preliminary spherical aberration correction through six refractions within the front fixed group. Subsequently, the incident beam is transmitted through a coated fourth plate glass element, allowing the laser beam to be transmitted and the visible light beam to be reflected. After reflection at the plate glass, the visible light beam enters the subsequent visible light channel lens group, where spherical aberration is corrected by the sixth and seventh lenses, and other remaining aberrations are corrected by the eighth and ninth lenses. The laser beam is transmitted through the fourth plate glass element into the subsequent laser channel lens group, where new asymmetric aberrations are introduced after transmission through the plate glass. The laser beam undergoes spherical aberration correction through four refractions by the tenth and eleventh lenses, and the twelfth and thirteenth lenses complete the correction of asymmetric aberrations and other aberrations. A fourteenth prism is added to the image space of the lidar receiving system, forming the lidar's transmitting channel lens group along with the lidar transmitting system.

[0007] The first lens has a thickness of 14.87mm to 15.31mm, a front surface radius of curvature of 334.26mm to 334.94mm, and a rear surface radius of curvature of 156mm to 156.81mm, and is made of heavy flint glass; preferably, the first lens has a thickness of 15mm, a front surface radius of curvature of 334.485mm, a rear surface radius of curvature of 156.1065mm, and is made of H-ZF52A.

[0008] The second lens has a thickness of 14.5mm to 15.5mm, a front surface radius of curvature of 138.88mm to 139.235mm, and a rear surface radius of curvature of 213.96mm to 214.53mm, and is made of lanthanum crown glass; preferably, the second lens has a thickness of 15mm, a front surface radius of curvature of 139.035mm, a rear surface radius of curvature of 214.202mm, and is made of H-LAK3.

[0009] The third lens has a thickness of 15.52mm to 16.52mm, a front surface radius of curvature of 453.011mm to 453.988mm, and a rear surface radius of curvature of -1088.11mm to -1089.11mm, and is made of lanthanum flint glass; preferably, the third lens has a thickness of 16mm, a front surface radius of curvature of 453.501mm, a rear surface radius of curvature of -1088.400mm, and is made of LAF5.

[0010] The fifth lens has a thickness of 8.00mm to 9.05mm, a front surface radius of curvature of -69.45mm to -70.87mm, and a rear surface radius of curvature of -51.26mm to -52.23mm, and is made of lanthanum crown glass; preferably, the fifth lens has a thickness of 8.5mm, a front surface radius of curvature of -70.26mm, a rear surface radius of curvature of -51.705mm, and is made of H-LAK3.

[0011] The sixth lens has a thickness of 24.5mm to 25.5mm, a front surface radius of curvature of -55.13mm to -55.98mm, and a rear surface radius of curvature of 427.11mm to 427.68mm, and is made of fluorine crown glass; preferably, the sixth lens has a thickness of 25.00mm, a front surface radius of curvature of 55.705mm, a rear surface radius of curvature of 427.580mm, and is made of H-FK61.

[0012] The seventh lens has a thickness of 5.50mm to 6.50mm, a front surface radius of curvature of 79.26mm to 80.11mm, and a rear surface radius of curvature of -48.78mm to -49.43mm, and is made of flint glass; preferably, the seventh lens has a thickness of 6mm, a front surface radius of curvature of -79.840mm, a rear surface radius of curvature of -49.073mm, and is made of H-F1.

[0013] The eighth lens has a thickness of 9.50mm to 10.50mm, a front surface radius of curvature of -65.26mm to -66.11mm, and a rear surface radius of curvature of -163.78mm to -164.43mm, and is made of fluorine crown glass; preferably, the eighth lens has a thickness of 10mm, a front surface radius of curvature of -65.956mm, a rear surface radius of curvature of -164.294mm, and is made of H-FK61.

[0014] The ninth lens has a thickness of 3.86mm to 4.21mm, a front surface radius of curvature of 217.11mm to 217.89mm, and a rear surface radius of curvature of -115.215mm to -115.945mm, and is made of flint glass; preferably, the ninth lens has a thickness of 4.00mm, a front surface radius of curvature of 217.386mm, a rear surface radius of curvature of -115.515mm, and is made of H-F1.

[0015] The tenth lens has a thickness of 29.5mm to 30.5mm, a front surface radius of curvature of 161.80mm to 162.42mm, and a rear surface radius of curvature of 1100.42mm to 1101.12mm, and is made of lanthanum crown glass; preferably, the tenth lens has a thickness of 30mm, a front surface radius of curvature of 161.945mm, a rear surface radius of curvature of 1100.908mm, and is made of H-LAK3.

[0016] The eleventh lens has a thickness of 16.5mm to 17.5mm, a front surface radius of curvature of -205.12mm to -205.98mm, and a rear surface radius of curvature of -206.32mm to -207.25mm, and is made of heavy flint glass; preferably, the eleventh lens has a thickness of 17mm, a front surface radius of curvature of -205.823mm, a rear surface radius of curvature of -115.90mm, and is made of H-ZF52A.

[0017] The twelfth lens has a thickness of 14.5mm to 15.5mm, a front surface radius of curvature of -3865.12mm to -3865.98mm, and a rear surface radius of curvature of 65.32mm to 66.25mm, and is made of crown glass; preferably, the twelfth lens has a thickness of 15mm, a front surface radius of curvature of -3865.89mm, a rear surface radius of curvature of 65.48mm, and is made of K9.

[0018] The visible light detection spectrum of the active-passive composite space detection optical system is: 0.48 ~0.70 The aperture is 100-120mm, the field of view is 7-8°×7-8°, the F-number is 1.5-2, the system pixel size is 6.5μm×6.5μm, and the detector size is 4k×4k. The laser optical receiving system operates in the 1062-1066nm range, has an aperture of 140-160mm, a focal length of 490-510mm, and a field of view of 2ω=±0.5°; the overall system volume is less than 480×330×300mm. 3 .

[0019] The working method of a space debris detection optical system with active and passive combined features disclosed in this invention is as follows:

[0020] The active-passive hybrid optical system for space debris detection first detects reflected sunlight from space debris using a visible light receiving system. The incident visible light beam undergoes initial spherical aberration correction through six refractions between the first fixed lens elements. Then, the incident beam is reflected by a coating at the fourth flat glass element. After reflection at the flat glass, the visible light beam enters the subsequent visible light channel lens group. Spherical aberration is then corrected by the sixth and seventh lenses, and remaining aberrations are corrected by the eighth and ninth lenses, thus ensuring good image quality and enabling wide-area space debris detection.

[0021] After detecting a space debris target, further detection is conducted to confirm its information across different spectral bands. A laser emission system emits a laser beam, which is then emitted through the same optical path as the laser receiving system. The emitted laser beam passes through an optical system and is incident on the space debris, before being reflected back into the optical system. Once inside the optical system, the laser beam is transmitted through the fourth flat glass pane into the subsequent laser channel lens group. This transmission through the flat glass introduces new asymmetric aberrations. The laser beam undergoes four refractions through the tenth and eleventh lenses to correct spherical aberration, and the twelfth and thirteenth lenses correct for asymmetric and other aberrations, ensuring good optical imaging quality and obtaining more accurate space debris information. By sequentially detecting space debris across different spectral bands using both visible light and laser optical systems, specific information about the space debris is obtained, thus achieving the goal of searching for and identifying space debris.

[0022] Beneficial effects:

[0023] For on-orbit detection payloads, the size and weight of the instrument must be as small as possible. Therefore, the innovation or uniqueness of this invention lies in:

[0024] 1. This invention discloses a combined active and passive optical system for space debris detection. In space debris detection, it employs dual-channel detection using visible light (0.48μm–0.72μm) and laser (1.064μm) to replace traditional single-channel detection. Compared to traditional single-spectrum detection, this invention obtains more comprehensive and accurate information about space debris across different spectral bands.

[0025] 2. In the field of space debris detection, existing space debris detection systems are significantly limited by the wide area of ​​space. Conventional visible light passive detection can only passively receive reflected light from space debris, while conventional active laser detection is limited by the field of view, resulting in a narrow detection range. This invention discloses a combined active and passive space debris detection optical system, employing a dual-channel system combining visible light (passive) and laser (active) detection. This solves the problem in conventional space-based multi-channel space debris detection where only reflected light from space debris can be passively received, thus fulfilling the requirement for combined active and passive detection of space debris.

[0026] 3. This invention discloses a combined active and passive space debris detection optical system. While incorporating multiple channels and both active and passive detection methods, it employs parallel glass to couple the active and passive multi-channel approaches. Furthermore, it utilizes a prism for beam splitting to couple the optical paths of the transmitting and receiving systems during active detection. This achieves the requirement of minimizing the size and weight of the instrument while maintaining the effective payload for on-orbit detection. In the combined active and passive configuration, the overall system volume of the combined active and passive space detection optical system is stably maintained at 480×330×300mm. 3 It has a compact structure.

[0027] 4. The present invention discloses a combined active and passive space debris detection optical system, which, while possessing multiple channels and active and passive detection modes, achieves large field-of-view detection in the visible spectrum by using an eighth-order even-order aspherical lens, and corrects asymmetric aberrations in the laser spectrum to ensure good imaging quality and more accurately acquire information about space debris. The MTF curve of the optical system shows that the MTF value is greater than 0.4 at a Nyquist frequency of 76.9 lp / mm. Attached Figure Description

[0028] Figure 1 A structural diagram of the optical system for a combined active and passive space exploration system.

[0029] Figure 2 A point diagram of the active-passive composite space detection optical system in the visible light receiving system;

[0030] Figure 3 A point diagram of the active-passive composite space detection optical system within the laser receiving system;

[0031] Figure 4 MTF curve of active-passive composite space detection optical system in visible light receiving system;

[0032] Figure 5 MTF curve of active-passive composite space detection optical system in laser receiving system;

[0033] Figure 6Energy curve of the encircling circle of the visible light receiving system in a combined active and passive space detection optical system;

[0034] Figure 7 Energy curve of the encircling circle of the laser receiving system in a combined active and passive space detection optical system;

[0035] Wherein: 1—first lens, 2—second lens, 3—third lens, 4—fourth parallel glass, 5—fifth lens, 6—sixth lens, 7—seventh lens, 8—eighth lens, 9—ninth lens, 10—tenth lens, 11—eleventh lens, 12—twelfth lens, 13—thirteenth lens, 14—fourteenth prism, 15—laser emission system. Detailed Implementation

[0036] The present invention will be further explained below with reference to the accompanying drawings and embodiments.

[0037] Example 1

[0038] like Figure 1 As shown, this embodiment discloses a combined active and passive space debris detection optical system, comprising a first lens 1, a second lens 2, a third lens 3, a fourth parallel glass mirror 4, a fifth lens 5, a sixth lens 6, a seventh lens 7, an eighth lens 8, a ninth lens 9, a tenth lens 10, an eleventh lens 11, a twelfth lens 12, a thirteenth lens 13, a fourteenth prism 14, and a fifteenth laser emitting system. The first lens 1, second lens 2, and third lens 3 form a front fixed group; the fourth parallel glass mirror 4 separates the laser beam from the visible light beam; the fifth lens 5, sixth lens 6, seventh lens 7, eighth lens 8, and ninth lens 9 form a rear mirror group for the visible light receiving system; and the tenth lens 10, eleventh lens 11, twelfth lens 12, and thirteenth lens 13 form a rear fixed group for the laser receiving system. The fourteenth prism couples the laser emitting system and the laser receiving system, and the fifteenth prism constitutes the laser emitting system.

[0039] The first lens is 15mm thick, with a front surface radius of curvature of 334.485mm and a rear surface radius of curvature of 156.1065mm, and is made of H-ZF52A material.

[0040] The second lens is 15mm thick, with a front surface radius of curvature of 139.035mm and a rear surface radius of curvature of 214.202mm, and is made of H-LAK3 material.

[0041] The preferred third lens has a thickness of 16mm, a front surface radius of curvature of 453.501mm, a rear surface radius of curvature of -1088.400mm, and is made of LAF5 material.

[0042] The fifth lens is preferably 8.5mm thick, with a front surface radius of curvature of -70.26mm and a rear surface radius of curvature of -51.705mm, and is made of H-LAK3 material.

[0043] The sixth lens is preferably 25.00 mm thick, with a front surface radius of curvature of 55.705 mm and a rear surface radius of curvature of 427.580 mm, and is made of H-FK61 material.

[0044] The seventh lens is preferably 6mm thick, with a front surface radius of curvature of -79.840mm and a rear surface radius of curvature of -49.073mm, and is made of H-F1 material.

[0045] The seventh lens is preferably 10mm thick, with a front surface radius of curvature of -65.956mm and a rear surface radius of curvature of -164.294mm, and is made of H-FK61 material.

[0046] The ninth lens is preferably 4.00 mm thick, with a front surface radius of curvature of 217.386 mm and a rear surface radius of curvature of -115.515 mm, and is made of H-F1 material.

[0047] The preferred tenth lens has a thickness of 30mm, a front surface radius of curvature of 161.945mm, a rear surface radius of curvature of 1100.908mm, and is made of H-LAK3 material.

[0048] The preferred eleventh lens has a thickness of 17mm, a front surface radius of curvature of -205.823mm, a rear surface radius of curvature of -115.90mm, and is made of H-ZF52A material.

[0049] The preferred eleventh lens has a thickness of 15mm, a front surface radius of curvature of -3865.89mm, a rear surface radius of curvature of 65.48mm, and is made of K9 material;

[0050] Technical specifications: 0.48~0.70 The aperture is 110mm, the field of view is 7.5°×7.5°, the F-number is 1.85, the system pixel size is 6.5μm×6.5μm, and the detector size is 4k×4k. The laser optical receiving system operates in the 1064nm spectral band, has an aperture of 150mm, a focal length of 500mm, and a field of view of 2ω=±0.5°; the overall system volume is less than 480×330×300mm. 3 .

[0051] The working method of a space debris detection optical system with active and passive combined features disclosed in this embodiment is as follows:

[0052] Active-passive combined optical system for space debris detection, such as Figure 1 First, a visible light receiving system detects reflected sunlight from space debris. The incident visible light beam undergoes preliminary correction of spherical aberration through six refractions between the first fixed group (lens 1, 2, and 3). Then, the incident beam is reflected by a coating at the fourth flat glass plate (4). After reflection at the flat glass, the visible light beam enters the subsequent visible light channel lens group, where it undergoes spherical aberration correction by the fifth, sixth, and seventh lenses (lens 5, 6, and 7). Finally, the remaining aberrations are corrected by the eighth and ninth lenses (lens 8 and 9), thus ensuring good imaging quality and enabling wide-area space debris detection.

[0053] After detecting a space debris target, further detection is conducted to confirm its information across different spectral bands. A laser emission system emits a laser beam, which is then emitted through the same optical path as the laser receiving system. The emitted laser beam passes through the optical system and is incident on the space debris, before being reflected back into the optical system by the debris. When the laser beam enters the optical system, it is transmitted through the fourth flat glass plate (4) into the subsequent laser channel lens group. At this point, a new asymmetric aberration is introduced after passing through the flat glass. The laser beam undergoes four refractions through the tenth lens (10) and eleventh lens (11) to correct spherical aberration. The twelfth lens (12) and thirteenth lens (13) then correct for the asymmetric aberration and other aberrations, ensuring good optical imaging quality and obtaining more accurate space debris information. By sequentially detecting space debris across different spectral bands using both the visible light optical system and the laser optical system, specific information about the space debris is obtained, thus achieving the goal of searching for and identifying space debris.

[0054] Figure 2 , Figure 3 Spot plots are presented for the visible light and laser bands of the active-passive composite space optical detection system. The plots show that the system's maximum RMS value in the visible light band is 5.623. At the center field of view, the RMS is only 4.577. When the system is in the laser band, the maximum RMS value is 32.052. The central field of view is 22.265. It can be concluded that the imaging quality of the active-passive composite space optical detection system is good.

[0055] Figure 4 , Figure 5MTF curves of the active-passive composite space optical detection system in two different spectral bands, visible light and laser, are presented respectively. It can be seen from the figure that the MTF value of the system in the visible light band is greater than 0.4, and the MTF value is above 0.5 except for the 3.71 field of view; the MTF value of the system in the laser band is greater than 0.5, and the MTF value can reach 0.6 or above in most fields of view.

[0056] The above detailed description further illustrates the purpose, technical solution, and beneficial effects of the invention. It should be understood that the above description is only a specific embodiment of the present invention and is not intended to limit the scope of protection of the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.

Claims

1. An optical system for detecting space debris with a combination of active and passive modes, characterized in that: The system comprises a front fixed group consisting of a first, second, and third lens. These three lenses are eighth-order even-order aspherical surfaces. The incident visible light beam and laser beam undergo initial spherical aberration correction through six refractions within the front fixed group. Subsequently, the incident beam is transmitted through a coating at the fourth flat glass panel, allowing the laser beam to be transmitted and the visible light beam to be reflected. After reflection at the flat glass, the visible light beam enters the subsequent visible light channel lens group, where spherical aberration is corrected by the fifth, sixth, and seventh lenses. The remaining aberrations are corrected by the eighth and ninth lenses. The laser beam is transmitted through the fourth flat glass panel into the subsequent laser channel lens group, where new asymmetric aberrations are introduced. The laser beam undergoes four refractions through the tenth and eleventh lenses, correcting spherical aberration. The twelfth and thirteenth lenses then complete the correction of asymmetric aberrations and other aberrations. Finally, a fourteenth prism is added to the image space of the laser radar receiving system, forming the laser radar's transmitting channel lens group. The first lens has a thickness of 14.87mm to 15.31mm, a front surface radius of curvature of 334.26mm to 334.94mm, a rear surface radius of curvature of 156mm to 156.81mm, and is made of heavy flint glass. The second lens has a thickness of 14.5mm to 15.5mm, a front surface radius of curvature of 138.88mm to 139.235mm, a rear surface radius of curvature of 213.96mm to 214.53mm, and is made of lanthanum crown glass. The third lens has a thickness of 15.52mm to 16.52mm, a front surface radius of curvature of 453.011mm to 453.988mm, a rear surface radius of curvature of -1088.11mm to -1089.11mm, and is made of lanthanum flint glass. The fifth lens has a thickness of 8.00mm to 9.05mm, a front surface radius of curvature of -69.45mm to -70.87mm, a rear surface radius of curvature of -51.26mm to -52.23mm, and is made of lanthanum crown glass. The sixth lens has a thickness of 24.5mm to 25.5mm, a front surface radius of curvature of -55.13mm to -55.98mm, a rear surface radius of curvature of 427.11mm to 427.68mm, and is made of fluorine crown glass. The seventh lens has a thickness of 5.50mm to 6.50mm, a front surface radius of curvature of 79.26mm to 80.11mm, a rear surface radius of curvature of -48.78mm to -49.43mm, and is made of flint glass. The eighth lens has a thickness of 9.50mm to 10.50mm, a front surface radius of curvature of -65.26mm to -66.11mm, a rear surface radius of curvature of -163.78mm to -164.43mm, and is made of fluorine crown glass. The ninth lens has a thickness of 3.86mm to 4.21mm, a front surface radius of curvature of 217.11mm to 217.89mm, a rear surface radius of curvature of -115.215mm to -115.945mm, and is made of flint glass. The tenth lens has a thickness of 29.5mm to 30.5mm, a front surface radius of curvature of 161.80mm to 162.42mm, a rear surface radius of curvature of 1100.42mm to 1101.12mm, and is made of lanthanum crown glass. The eleventh lens has a thickness of 16.5mm to 17.5mm, a front surface radius of curvature of -205.12mm to -205.98mm, a rear surface radius of curvature of -206.32mm to -207.25mm, and is made of heavy flint glass. The twelfth lens has a thickness of 14.5mm to 15.5mm, a front surface radius of curvature of -3865.12mm to -3865.98mm, a rear surface radius of curvature of 65.32mm to 66.25mm, and is made of crown glass. The visible light detection spectrum of the active-passive composite space detection optical system is: 0.48 ~0.70 The aperture size is 100~120mm; the field of view is 7~8°×7~8°; the F-number is 1.5~2; the system pixel size is 6.5μm×6.5μm; the detector size is 4k×4k; the operating spectrum of the laser optical receiving system is 1062~1066nm, the aperture is 140~160mm, the focal length is 490~510mm, and the field of view is 2ω=±0.5°; the total system volume is less than 480×330×300mm. 3 .

2. The space debris detection optical system with active and passive composite characteristics as described in claim 1, characterized in that: The first lens is 15mm thick, with a front surface radius of curvature of 334.485mm and a rear surface radius of curvature of 156.1065mm, and is made of H-ZF52A material. The second lens is 15mm thick, with a front surface radius of curvature of 139.035mm and a rear surface radius of curvature of 214.202mm, and is made of H-LAK3 material. The third lens is 16mm thick, with a front surface radius of curvature of 453.501mm and a rear surface radius of curvature of -1088.400mm, and is made of LAF5 material. The fifth lens is 8.5mm thick, with a front surface radius of curvature of -70.26mm and a rear surface radius of curvature of -51.705mm, and is made of H-LAK3 material. The sixth lens has a thickness of 25.00 mm, a front surface radius of curvature of -55.705 mm, a rear surface radius of curvature of 427.580 mm, and is made of H-FK61 material. The seventh lens is 6mm thick, with a front surface radius of curvature of 79.840mm and a rear surface radius of curvature of -49.073mm, and is made of H-F1 material. The eighth lens is 10mm thick, with a front surface radius of curvature of -65.956mm and a rear surface radius of curvature of -164.294mm, and is made of H-FK61 material. The ninth lens has a thickness of 4.00 mm, a front surface radius of curvature of 217.386 mm, a rear surface radius of curvature of -115.515 mm, and is made of H-F1 material. The tenth lens is 30mm thick, with a front surface radius of curvature of 161.945mm and a rear surface radius of curvature of 1100.908mm, and is made of H-LAK3 material; The twelfth lens is 15mm thick, with a front surface radius of curvature of -3865.89mm and a rear surface radius of curvature of 65.48mm, and is made of K9 material.

3. A space debris detection optical system with active and passive composite characteristics as described in claim 1 or 2, characterized in that: The active-passive composite optical system for space debris detection first detects reflected sunlight from space debris using a visible light receiving system. The incident visible light beam undergoes initial spherical aberration correction through six refractions between the first fixed groups. Subsequently, the incident beam is reflected by a coating at the fourth flat glass plate. After reflection at the flat glass plate, the visible light beam enters the subsequent visible light channel lens group, where spherical aberration is corrected by the fifth, sixth, and seventh lenses. Finally, the remaining aberrations are corrected by the eighth and ninth lenses, achieving wide-area space debris detection. After detecting a space debris target, further detection is conducted to confirm its information from different spectral bands. A laser emission system emits a laser beam, which is then emitted through the same optical path as the laser receiving system. The emitted laser beam passes through the optical system and is incident on the space debris, then reflected back to the optical system by the space debris. When the laser beam enters the optical system, it is transmitted through the fourth flat glass plate into the subsequent laser channel lens group. At this point, a new asymmetric aberration is added after passing through the flat glass plate. The laser beam is refracted four times by the tenth and eleventh lenses to correct spherical aberration, and the twelfth and thirteenth lenses complete the correction of asymmetric aberration and other aberrations, ensuring optical imaging quality and thus obtaining space debris information. By using the visible light optical system and the laser optical system to detect different spectral bands sequentially, specific information about the space debris is obtained, thereby achieving the purpose of searching for and identifying space debris.

Images