WO2022249430A1 - 宇宙物体軌道変更装置 - Google Patents

宇宙物体軌道変更装置 Download PDF

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Publication number
WO2022249430A1
WO2022249430A1 PCT/JP2021/020321 JP2021020321W WO2022249430A1 WO 2022249430 A1 WO2022249430 A1 WO 2022249430A1 JP 2021020321 W JP2021020321 W JP 2021020321W WO 2022249430 A1 WO2022249430 A1 WO 2022249430A1
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Prior art keywords
space object
wavelength
light source
changing device
source unit
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English (en)
French (fr)
Japanese (ja)
Inventor
仁深 尾野
貴敬 鈴木
貴雄 遠藤
俊行 安藤
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Mitsubishi Electric Corp
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Mitsubishi Electric Corp
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Priority to JP2023522954A priority Critical patent/JP7325691B2/ja
Priority to PCT/JP2021/020321 priority patent/WO2022249430A1/ja
Publication of WO2022249430A1 publication Critical patent/WO2022249430A1/ja
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G3/00—Observing or tracking cosmonautic vehicles

Definitions

  • the technology disclosed herein relates to a space object trajectory changing device.
  • Space objects such as artificial satellites and space debris that have completed their roles have become a problem because there are some that are in orbit around the earth and may destroy facilities that are in operation. Therefore, there is a demand for a system that accurately grasps the trajectory of space objects such as space debris and, if possible, changes the trajectory.
  • Patent Literature 1 discloses a technique for scanning an irradiation beam using prior observation information of a space object by another system, and measuring and observing the space object.
  • the distance measurement of space objects is so weak that the reflected light can be expressed in units of photons. That is, high-energy light rays are required for ranging of space objects.
  • Lasers commonly used for range finding of space objects include, for example, those that use flash lamps to excite high-energy pulsed lasers.
  • the flash lamp does not have a high repetition frequency. Therefore, prior art ranging of space objects suffers from the problem that it takes time to collect enough photon detection events for statistical processing. This is a big problem, especially for low-earth orbit objects with short observable times.
  • the space object trajectory changing device Since the space object trajectory changing device according to the technology disclosed herein has the above configuration, it is possible to artificially increase the repetition frequency of the high-energy pulse laser. Due to this effect, the space object trajectory changing apparatus according to the technology disclosed herein can shorten the time required to collect enough photon detection events for statistical processing.
  • FIG. 1 is a block diagram showing the configuration of a space object trajectory changing apparatus according to Embodiment 1.
  • FIG. 2 is an example of a timing chart showing events on the time axis of the space object orbit changing apparatus according to the first embodiment.
  • FIG. 3 is a schematic diagram showing an example of transmission wavelength setting of the wavelength tunable filter 12.
  • FIG. 4 is a graph showing an image of a photon detection event in the space object orbit changing apparatus according to the first embodiment.
  • FIG. 5 is a block diagram showing the configuration of a space object trajectory changing apparatus according to Embodiment 2.
  • FIG. 6 is a schematic diagram showing the irradiation range of the space object trajectory changing apparatus according to the second embodiment.
  • FIG. 7 is an example of a histogram of photon detection events by wavelength of the space object orbit changing apparatus according to the second embodiment.
  • FIG. 8 is a schematic diagram showing the action of a plurality of space object trajectory changing apparatuses according to the third embodiment.
  • FIG. 9 is a schematic diagram for explaining wavelengths adopted by a plurality of space object orbit changing apparatuses according to the third embodiment.
  • FIG. 10 is an example of a histogram of photon detection events by wavelength of the space object orbit changing device (61) according to the third embodiment.
  • FIG. 1 is a block diagram showing the configuration of a space object trajectory changing device 200 according to Embodiment 1.
  • a space object orbit changing device 200 according to Embodiment 1 includes a space object ranging device 1 and an orbit changing device 100 .
  • the space object ranging device 1 includes a light source unit 2 (first wavelength light source unit 2a, second wavelength light source unit 2b, third wavelength light source unit 2c, . . . ), a light source unit controller 3, Multiplexer 4, transmission telescope 5, reception telescope 11, wavelength tunable filter 12, photodetector 13, gate controller 14, event timer 15, filter controller 16, distance measurement information processing unit 21 , a trajectory information storage unit 51 , and a pointing direction controller 52 .
  • the trajectory changer 100 includes a high power beam generator 101 , a variable focus transmission telescope 102 and a focus controller 103 .
  • a space object orbit changing device 200 according to Embodiment 1 is such that the orbit changing device 100 irradiates a space object (31) with orbit changing light (111) based on the distance measurement result of the space object ranging device 1. .
  • the orbit of the space object (31) is changed by the light pressure of the orbit changing light (111).
  • the light source unit 2 (first wavelength light source unit 2a, second wavelength light source unit 2b, third wavelength light source unit 2c, . . . ) may be a pulse laser.
  • the high-power beam generator 101 may be specifically a high-energy pulsed laser.
  • the action of each component of the space object ranging device 1 will become clear from the following description.
  • L be the distance from the space object ranging device 1 to the space object (31).
  • the pulse repetition interval of the light source section 2 (first wavelength light source section 2a, second wavelength light source section 2b, and third wavelength light source section 2c) is T rep .
  • the wavelength of the light source unit 2a with the first wavelength is ⁇ a
  • the wavelength of the light source unit 2 b with the second wavelength is ⁇ b
  • the wavelength of the light source unit 2 c with the third wavelength is ⁇ c .
  • ⁇ a , ⁇ b , and ⁇ c may be different wavelengths within a range of, for example, approximately 1 to 10 [nm].
  • the space object ranging device 1 shown in FIG. 1 shows a first wavelength light source unit 2a, a second wavelength light source unit 2b, and a third wavelength light source unit 2c. is not limited to three.
  • the number of light source units 2 of the space object ranging device 1 according to the technology disclosed herein may be two or more.
  • the light source section 2 is controlled by the light source section controller 3 .
  • FIG. 2 is an example of a timing chart showing events on the time axis of the space object trajectory changing apparatus 200 according to the first embodiment.
  • the first wavelength light source section 2a, the second wavelength light source section 2b, and the third wavelength light source section 2c are all oscillated at the pulse repetition interval (T rep ).
  • the first wavelength light source section 2a, the second wavelength light source section 2b, and the third wavelength light source section 2c are oscillated at different timings.
  • the oscillation timing of the light source unit 2b of the second wavelength is controlled to be delayed by ⁇ from the oscillation of the light source unit 2a of the first wavelength.
  • the oscillation timing of the light source section 2c for the third wavelength is controlled to be delayed by ⁇ from the oscillation of the light source section 2b for the second wavelength.
  • the oscillation timing delay ⁇ is set shorter than the pulse repetition interval (T rep ).
  • the light source unit controller 3 controls the light source unit 2 (the first wavelength light source unit 2a, the second wavelength light source unit 2b, the third wavelength light source unit 2c, . . . ).
  • Laser light oscillated by the light source unit 2 (first wavelength light source unit 2a, second wavelength light source unit 2b, third wavelength light source unit 2c, . . . ) is output to the multiplexer 4.
  • FIG. The laser beams oscillated by the light source unit 2 are indicated by thick arrows in FIG. 1 indicating that they are optical signals.
  • the multiplexer 4 multiplexes the laser beams output from the light source units 2 (first wavelength light source unit 2a, second wavelength light source unit 2b, third wavelength light source unit 2c, . . . ).
  • the combined laser light is output to the transmission telescope 5 .
  • the transmission telescope 5 irradiates the space object (31) with the multiplexed laser light as transmission light (41).
  • the transmitted light (41) is represented by a thick arrow in FIG. 1 indicating that it is an optical signal.
  • the fourth row from the top of FIG. 2 shows the transmission light (41) emitted by the transmission telescope 5 on the time axis.
  • the transmission light (41) emitted by the space object ranging device 1 of the space object orbit changing device 200 according to the first embodiment is a conventional one using a single pulse laser. Apparent pulse repetition period is shorter than that.
  • Space objects (31) are specifically assumed to be geostationary orbit satellites, low earth orbit satellites, space debris, and the like.
  • the orbital information storage unit 51 stores orbital information about the space object (31).
  • the trajectory information may be in the form of TLE (Two-Line Elements), for example.
  • Orbital information is information of the past and present orbits of the space object (31).
  • the prediction of the future trajectory of the space object (31) is called trajectory prediction information to distinguish it from trajectory information.
  • Trajectory prediction information is used to track space objects (31).
  • the orbit prediction information of the target space object (31) is transferred from the orbit information storage unit 51 to the pointing direction controller 52.
  • the pointing direction controller 52 drives and controls the telescope drive system 53 based on the passed orbit prediction information.
  • a transmission telescope 5 and a reception telescope 11 are mounted on the telescope drive system 53 .
  • the transmitted light (41) is reflected according to the surface properties of the space object (31) resulting in reflected light (42).
  • the reflectivity of the laser may be high.
  • a corner cube retroreflector (CCR) having a mirror surface or retroreflection characteristics may be provided.
  • the space object (31) assumed by the technique of the present disclosure does not have a mirror surface or the like, and the reflectance is not high. It is estimated that when an object having a CCR with a diameter of several meters is compared with an object having a similar diameter without a CCR, the reflection characteristics differ by about five to six orders of magnitude.
  • the optical cross section is narrower than that of a satellite. Therefore, in the case of space debris, the intensity of the reflected light (42) is weaker than that of the satellite. For this reason as well, the laser beam used in the space object ranging apparatus 1 is required to have high pulse energy.
  • the receiving telescope 11 receives the reflected light (42) reflected by the space object (31).
  • the space object ranging device 1 of the space object trajectory changing device 200 measures the distance to the space object (31) by time of flight (hereinafter referred to as "TOF"), that is, based on the time of flight of light.
  • TOF time of flight
  • can measure the distance of Assuming that the flight time of light is ⁇ , the distance from the space object ranging device 1 to the space object (31) is L, and the speed of light is c, the relational expression ⁇ 2L/C holds.
  • FIG. 3 is a schematic diagram showing an example of transmission wavelength setting of the wavelength tunable filter 12.
  • the wavelength tunable filter 12 filters the optical signal received by the receiving telescope 11 .
  • the wavelength tunable filter 12 has a plurality of transmission wavelength bands dynamically switch-controlled by a filter controller 16 .
  • the plurality of transmission wavelength bands includes a wavelength band including ⁇ a , a wavelength band including ⁇ b , and a wavelength band including ⁇ c .
  • the transmission wavelength band starts to be set after T_offset from the time when the transmission light (41) is irradiated, and continues to be set for T_gate .
  • T_offset is determined based on the expected TOF.
  • T_gate is determined based on the oscillation timing delay ⁇ .
  • T_offset is called the offset time and T_gate is called the gate time. The details of the method of determining the offset time ( T_offset ) and the gate time ( T_gate ) will become clear from the description below.
  • the space object ranging device 1 of the space object trajectory changing device 200 can obtain the desired reflected light (42), noise and can be separated from the backscattered light (44) of the transmitted light (41).
  • the details of the effect of having the wavelength tunable filter 12 and the filter controller 16 will become clear from the description below.
  • the reflected light ( 42 ) that has passed through the wavelength tunable filter 12 is received by the photodetector 13 .
  • the photodetector 13 is required to receive weak light that can be expressed in units of the number of photons. Therefore, the photodetector 13 may be composed of, for example, a SPAD (Single Photon Avalanche Diode).
  • the photodetector 13 may operate only when a gate signal from the outside is ON (hereinafter referred to as "gate operation").
  • FIG. 1 shows a configuration in which the photodetector 13 is gated by a gate controller 14 .
  • the photodetector 13 outputs an event signal to the event timer 15 when it receives an optical signal during operation.
  • the event signal may have a fast rise time or fast fall time, and may be an electrical pulse signal, for example.
  • the event timer 15 receives an event signal from the photodetector 13, as well as from the light source unit 2 (first wavelength light source unit 2a, second wavelength light source unit 2b, third wavelength light source unit 2c, ). event signal (see FIG. 1).
  • the event timer 15 can accurately measure the time when the input event signal is input.
  • the event timer 15 tags the input event signal with time.
  • the information of the event signal tagged with the time is output to the distance measurement information processing section 21 .
  • the distance measurement information processing section 21 is roughly divided into two parts. One is for event accumulation and the other is for ranging information extraction. Information from the event timer 15 is accumulated in the event accumulation portion of the distance measurement information processing section 21 . The ranging information extraction part of the ranging information processing unit 21 calculates the TOF based on the accumulated information and calculates the distance to the space object (31).
  • the reflected light (42) dealt with in this technical field is a weak light of about the number of photons. Therefore, it is noted that the signal detection process in the art is probabilistic.
  • FIG. 1 not only the reflected light (42) but also the background light (43) and the backscattered light (44) are incident on the receiving telescope 11.
  • FIG. Background light (43) occurs both during the day and at night.
  • the background light (43) that occurs during the day is mainly sunlight scattered in the atmosphere.
  • the background light (43) that occurs at night is due to city lights and other celestial bodies.
  • the background light (43) has a larger amount of light during the daytime than at nighttime.
  • the background light (43) has the property that it does not fluctuate much over time.
  • the background light (43) has no bias or peak when viewed from a wavelength range of 1 to 10 [nm]. That is, the background light (43) has the property of not having much wavelength dependence.
  • the backscattered light (44) is the transmitted light (41) scattered in the atmosphere.
  • the amount of backscattered light (44) is highest immediately after the transmitted light (41) is output, and then decreases exponentially.
  • the transmitted light (41), reflected light (42), and backscattered light (44) for one light source have the same wavelength.
  • the transmitted light (41), the reflected light (42), and the backscattered light (44) for one light source are generated at different times.
  • the schematic diagram shown in the fifth row from the top of FIG. 2 shows this.
  • the wavelength tunable filter 12 according to Embodiment 1 changes the transmission wavelength band at the timing shown in the sixth row from the top in FIG. 2 by the filter controller 16 .
  • the wavelength tunable filter 12 has a transmission wavelength band that transmits only ⁇ Block such backscattered light (44).
  • the wavelength tunable filter 12 operates similarly at the timing of receiving the reflected light (42) from the second wavelength light source section 2b and the third wavelength light source section 2c. Due to this action, the space object ranging device 1 of the space object trajectory changing device 200 according to Embodiment 1 reduces the backscattered light (44) that becomes noise and receives the reflected light (42) with a high S/N ratio. can do.
  • the signal line of the photodetector 13 may be superimposed with detector noise (45) caused by dark current or the like.
  • detector noise 45
  • the space object ranging device 1 according to the technology of the present disclosure may also be appropriately designed to reduce the detector noise (45).
  • the ranging information processing unit 21 determines offset times ( T_offset ) and gate times ( T_gate ) for a plurality of transmission wavelength bands switched by the filter controller 16.
  • the offset time ( T_offset ) is determined based on the expected TOF.
  • the TOF prediction may use, for example, orbital information and orbital prediction information stored in the orbital information storage unit 51 .
  • the trajectory prediction information is indicated by dotted line arrows indicating that it is information.
  • the gate time ( T_gate ) is determined based on the oscillation timing delay ⁇ .
  • the gate time ( T_gate ) cannot be longer than the oscillation timing delay ⁇ .
  • the gate time ( T_gate ) should satisfy T rep > ⁇ + T_gate /2 in relation to the expected TOF. Note that ⁇ here represents the expected TOF.
  • FIG. 4 is a graph showing an image of a photon detection event in the space object ranging device 1 of the space object trajectory changing device 200 according to the first embodiment.
  • the horizontal axis of the graph represents event accumulation time.
  • the event accumulation time is described in units of gate time ( T_gate ).
  • the vertical axis of the graph represents event information recorded by the event timer 15 .
  • the event information is specifically the time from the pulse transmission time to the photon reception time.
  • Figure 4 shows that there is a distribution in the photon detection results. That is, the detection of photons in this technical field indicates that stochastic statistical processing is necessary. The reason why the photon detection result has a spread distribution is that the light is weak and the presence of background light (43), backscattered light (44), and detector noise (45). Conceivable.
  • the ranging information processing unit 21 of the space object ranging device 1 according to Embodiment 1 performs statistical processing on the accumulated event information. More specifically, the distance measurement information processing section 21 calculates the frequency distribution of event information and estimates the flight time ( ⁇ ) of the plausible signal light.
  • the space object ranging device 1 of the space object trajectory changing device 200 according to Embodiment 1 may be configured to change the gate time ( T_gate ) depending on the situation. As the amount of accumulated event information increases, the accuracy of time-of-flight ( ⁇ ) estimation improves. In other words, the time-of-flight ( ⁇ ) estimation error decreases as the accumulated event information increases. Therefore, the space object ranging apparatus 1 may be configured to sequentially shorten the oscillation timing delay ⁇ , the gate time ( T_gate ), and the pulse repetition interval ( Trep ). Shortening the gate time ( T_gate ) has the effect of reducing the ranging time.
  • the space object ranging device 1 of the space object trajectory changing device 200 according to Embodiment 1 includes ranging information calculated from the estimated flight time ( ⁇ ), and the pointing azimuth when tracking the space object (31). , the trajectory information stored in the trajectory information storage unit 51 may be updated. Adding the calculated ranging information is expected to improve the accuracy of the trajectory information.
  • Orbit changing device 100 of space object orbit changing device 200 emits orbit changing light (111) toward space object (31) based on the distance measurement result of space object ranging device 1. .
  • the orbit changing device 100 receives the ranging result of the space object ranging device 1 at the focus controller 103 .
  • the focus controller 103 controls the variable-focus transmission telescope 102 so that the orbit-changing light (111) to irradiate is focused on the space object (31).
  • the energy density of the orbit-changing light (111) on the surface of the space object (31) is increased.
  • FIG. 1 illustrates a configuration using a single transmit telescope 5
  • the number of transmitting telescopes 5 of the space object ranging device 1 according to the technology disclosed herein corresponds to each of the light source units 2 (the first wavelength light source unit 2a, the second wavelength light source unit 2b, . . . ).
  • the transmission telescope 5 may be composed of a first transmission telescope 5a corresponding to the light source unit 2a of the first wavelength, a second transmission telescope 5b corresponding to the light source unit 2b of the second wavelength, and the like.
  • each of the transmission telescopes 5 (first transmission telescope 5a, second transmission telescope 5b, . .
  • the configuration may be the same for any wavelength.
  • FIG. 1 shows a configuration in which the transmitting telescope 5 and the receiving telescope 11 are separated
  • the space object ranging device 1 according to the technology disclosed herein is not limited to this. Since the transmitting telescope 5 and the receiving telescope 11 only need to point to the space object (31), they may be integrated.
  • the space object ranging device 1 of the space object orbit changing device 200 according to Embodiment 1 has the above configuration, the repetition frequency of the high-energy pulse laser can be artificially increased. Due to this action, the space object ranging device 1 according to the technique of the present disclosure can shorten the time required to collect sufficient photon detection events for performing statistical processing.
  • FIG. 5 is a block diagram showing the configuration of the space object ranging device 1 of the space object trajectory changing device 200 according to the second embodiment.
  • the reference numerals used in the second embodiment are the same as those in the first embodiment unless otherwise specified. Further, in the second embodiment, explanations overlapping those of the first embodiment are omitted as appropriate.
  • the space object ranging device 1 of the space object trajectory changing device 200 according to the second embodiment includes an optical switch 6 instead of the multiplexer 4 of the first embodiment.
  • the space object ranging device 1 of the space object orbit changing device 200 according to Embodiment 2 includes a plurality of transmission telescopes 5 (first transmission telescope 5a, second transmission telescope 5b, third transmission telescope 5c). Prepare. Although the number of transmitting telescopes 5 (the first transmitting telescope 5a, the second transmitting telescope 5b, and the third transmitting telescope 5c) in FIG. 5 is three, the technology disclosed herein is not limited to this.
  • a plurality of transmission telescopes 5 (a first transmission telescope 5a, a second transmission telescope 5b, and a third transmission telescope 5c) irradiate a plurality of transmission lights (41a, 41b, 41c) toward a space object (31). do.
  • the space object ranging device 1 of the space object trajectory changing device 200 according to Embodiment 2 is configured to set the transmission telescope 5 (first transmission A telescope 5a, a second transmit telescope 5b, a third transmit telescope 5c) may be configured.
  • a plurality of optical signals are input to the optical switch 6 from the light source section 2 (the first wavelength light source section 2a, the second wavelength light source section 2b, and the third wavelength light source section 2c).
  • the optical switch 6 selectively switches paths of a plurality of input optical signals and transmits them to the transmission telescopes 5 (the first transmission telescope 5a, the second transmission telescope 5b, and the third transmission telescope 5c).
  • the space object ranging device 1 of the space object orbit changing device 200 according to the second embodiment may be configured to select a route based on the ranging information from the ranging information processing section 21 .
  • the plurality of transmission telescopes 5 (the first transmission telescope 5a, the second transmission telescope 5b, the third transmission telescope 5c), in the initial state, the irradiation range of the plurality of transmission lights (41a, 41b, 41c)
  • the directivity direction may be set so that each has a different field of view.
  • Space object (31) trajectory information and trajectory prediction information is available, for example, in TLE format, as described above. That is, the azimuth and elevation angles of the space object (31) at a specific time can be estimated to some extent. However, the actual trajectory of the space object (31) may deviate from the estimated value due to effects such as atmospheric friction of the earth. Setting the irradiation ranges of the plurality of transmission lights (41a, 41b, 41c) to different fields of view has the effect that the space object (31) can be tracked even when the actual orbit deviates from the estimated orbit.
  • FIG. 6 is a schematic diagram showing the irradiation range of the space object ranging device 1 of the space object trajectory changing device 200 according to the second embodiment.
  • the left side of FIG. 6 shows the initial irradiation range of the space object ranging device 1 of the space object orbit changing device 200 according to the second embodiment.
  • the right side of FIG. 6 shows the modified illumination range after the position of the space object (31) has been estimated based on the reflected light (42).
  • the space object ranging device 1 of the space object trajectory changing device 200 according to the second embodiment may be configured to change the aspect of the irradiation range according to the situation.
  • a space object ranging device 1 includes a tunable filter 12 and a filter controller 16 .
  • the space object ranging device 1 of the space object trajectory changing device 200 according to Embodiment 2 performs statistical processing of events, and the space object (31) is detected by a plurality of transmission telescopes 5 (first transmission telescopes). 5a, the second transmission telescope 5b, and the third transmission telescope 5c).
  • FIG. 7 is an example of a histogram of photon detection events by wavelength of the space object ranging device 1 of the space object orbit changing device 200 according to the second embodiment.
  • FIG. 7 shows an example in which a space object (31) exists within the irradiation range of the transmitted light (41a) with a wavelength of ⁇ a .
  • the histogram of wavelength ⁇ a has a peak in the center. This peak appears in the flight time ( ⁇ ) of the transmitted light (41a).
  • the signal may also be arranged to be output to the first transmit telescope 5a.
  • the optical switch 6 according to Embodiment 2 may be configured to select a route based on the route control signal from the distance measurement information processing section 21 .
  • the space object ranging device 1 of the space object orbit changing device 200 has the above configuration, in addition to the effects shown in the first embodiment, The effect is that the object (31) can be detected without fine beam scanning by the telescope driving system 53.
  • FIG. 8 is a schematic diagram showing actions of a plurality of space object trajectory changing devices (space object trajectory changing device 61, space object trajectory changing device 62) according to the third embodiment.
  • the reference numerals used in the third embodiment are the same as those in the previous embodiments unless otherwise specified. Further, in Embodiment 3, explanations that overlap those of the previous embodiments are omitted as appropriate.
  • Embodiment 3 is a mode in which a plurality of devices function in cooperation, and the space object trajectory changing device 61 and the space object trajectory changing device 62 function in cooperation.
  • Each of space object trajectory changing device 61 and space object trajectory changing device 62 may have the same configuration as space object trajectory changing device 200 according to either one of the first and second embodiments.
  • the third embodiment may have a configuration in which the space object trajectory changing device 61 and the space object trajectory changing device 62 are arranged at separate points, and the ranging device control station 63 is provided.
  • the space object trajectory changing device 61 and the space object trajectory changing device 62 may share observation information via the ranging device control station 63 .
  • the space object orbit changing device 61 and the space object orbit changing device 62 share information about which wavelength has been selected (hereinafter referred to as "wavelength selection information") via the ranging device control station 63. You can do
  • FIG. 8 shows a mode in which two units function in cooperation
  • the technology disclosed herein is not limited to this number.
  • the technology disclosed herein may be configured in such a manner that two or more devices cooperate with each other.
  • the technology disclosed herein may be in a mode in which the roles to be taken are different when a plurality of devices cooperate and function.
  • the space object trajectory changing device 61 may search a wide range, and the space object trajectory changing device 62 may measure a specific target with high accuracy.
  • FIG. 9 is a schematic diagram for explaining wavelengths adopted by a plurality of space object orbit changing devices (space object orbit changing device 61 and space object orbit changing device 62) according to the third embodiment.
  • a space object trajectory changing device 61 for searching a wide range may include a light source unit 2 with a wide wavelength range.
  • the wavelengths of the light source units 2 (the first wavelength light source unit 2a, the second wavelength light source unit 2b, and the third wavelength light source unit 2c) related to the space object trajectory changing device 61 are ⁇ a′ and ⁇ b , respectively. ' , and ⁇ c ' .
  • ⁇ a′ , ⁇ b′ , and ⁇ c′ may be determined, for example, so that the distance between them is 100 [nm] or more.
  • ⁇ a′ , ⁇ b′ and ⁇ c′ may be determined according to the properties of the range object.
  • the reflection characteristics of the surface are an especially important factor. Reflection characteristics generally have wavelength dependence.
  • the surface of the geodetic satellite is provided with a mirror surface or CCR.
  • the surface of a general satellite is provided with a heat insulating material such as MLI (Multi-Layer-Insulation) and a radiator such as OSR (Optical Solar Reflector).
  • MLI Multi-Layer-Insulation
  • OSR Optical Solar Reflector
  • the surface of a general satellite may be equipped with SAP (Solar Array Panel). Space debris has a wide variety of base materials and various surface characteristics.
  • ⁇ a' , ⁇ b' , and ⁇ c' may be determined in consideration of loss during spatial propagation.
  • the loss during spatial propagation has wavelength dependence, for example, in the atmosphere. It is known that atmospheric absorption has good transmittance in the 0.8 [ ⁇ m] band, 1.0 [ ⁇ m] band, and 1.5 [ ⁇ m] band. It is also generally known that the shorter the wavelength, the greater the loss due to atmospheric disturbances.
  • the space object trajectory changing device 62 that measures the range of a specific target with high accuracy may include a light source section 2 that can select one set from a plurality of sets consisting of narrow wavelength ranges.
  • the wavelengths in any pair may be determined such that the distance between them is, for example, 10 [nm] or less. Details of the wavelength range determined for the light source section 2 of the space object orbit modification device 62 will become apparent from the description along with FIG. 10 below.
  • FIG. 10 is an example of a histogram of photon detection events by wavelength of the space object orbit changing device 61 according to the third embodiment.
  • FIG. 10 shows that the reflected light (42a') for the transmitted light (41a') with wavelength ⁇ a' has the highest intensity. That is, FIG. 10 shows that the wavelength suitable for distance measurement is in the vicinity of ⁇ a' .
  • the information about wavelengths suitable for distance measurement is the aforementioned wavelength selection information.
  • the space object orbit changing device 62 determines the wavelength range based on the wavelength selection information shared via the rangefinder control station 63 .
  • the wavelength range may be determined by the space object trajectory changing device 62 or by the ranging device control station 63 . More specifically, the wavelength of the optical signal output from the light source unit 2 of the space object orbit changing device 62 is determined as a set of ⁇ a'a , ⁇ a'b and ⁇ a'c .
  • ⁇ a′a , ⁇ a′b , and ⁇ a′c are the wavelengths in the neighborhood of ⁇ a′ .
  • ⁇ a′a , ⁇ a′b , and ⁇ a′c may be determined so that the distance between them is 10 [nm] or less. Any one of ⁇ a'a , ⁇ a'b , and ⁇ a'c may be equal to ⁇ a' .
  • the wavelength of the optical signal output by the light source unit 2 need not be continuously variable.
  • the light source unit 2 of the space object trajectory changing device 61 may be realized, for example, by a set of pulsed lasers whose wavelengths are spaced over a wide band.
  • the light source unit 2 of the space object orbit changing device 62 may be realized by, for example, providing a plurality of sets of pulsed lasers whose wavelengths are spaced in narrow bands.
  • the space object trajectory changing device 61 and the space object trajectory changing device 62 according to Embodiment 3 have the above configuration, in addition to the effects shown in Embodiments 1 and 2, a plurality of wavelengths suitable for ranging can be obtained. An effect of being able to select from among the set is produced.
  • the space object orbit changing device (200, 61, 62) can be used as a device for changing the orbit of space objects such as space debris and artificial satellites, and has industrial applicability.
  • 1 space object ranging device 2 (2a, 2b, 2c) light source unit, 3 light source unit controller, 4 multiplexer, 5 (5a, 5b, 5c) transmitting telescope, 6 optical switch, 11 receiving telescope, 12 wavelength variable filter, 13 photodetector, 14 gate controller, 15 event timer, 16 filter controller, 21 ranging information processing unit, 51 trajectory information storage unit, 52 orientation controller, 53 telescope drive system, 61, 62 space Object trajectory changing device, 63 Ranging device control station, 100 Orbit changing device, 101 High power beam generator, 102 Focus variable transmission telescope, 103 Focus controller, 200 Space object trajectory changing device.

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  • Optical Radar Systems And Details Thereof (AREA)
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Cited By (1)

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Publication number Priority date Publication date Assignee Title
WO2024171157A1 (en) * 2023-02-17 2024-08-22 Southern Cross Outreach Observatory Project (SCOOP) Space debris detection and mitigation with a network of deployed observatories

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH09318743A (ja) * 1996-05-30 1997-12-12 Toshiba Corp 距離測定装置
WO2020152744A1 (ja) * 2019-01-21 2020-07-30 スカパーＪｓａｔ株式会社 宇宙機、制御システム

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2012032183A (ja) * 2010-07-28 2012-02-16 Olympus Corp 試料観測装置および試料観測方法

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH09318743A (ja) * 1996-05-30 1997-12-12 Toshiba Corp 距離測定装置
WO2020152744A1 (ja) * 2019-01-21 2020-07-30 スカパーＪｓａｔ株式会社 宇宙機、制御システム

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2024171157A1 (en) * 2023-02-17 2024-08-22 Southern Cross Outreach Observatory Project (SCOOP) Space debris detection and mitigation with a network of deployed observatories
US12286248B2 (en) 2023-02-17 2025-04-29 Southern Cross Outreach Observatory Project (SCOOP) Space debris detection and mitigation with a network of deployed observatories

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