WO2022234669A1 - 推力発生装置、宇宙機 - Google Patents

推力発生装置、宇宙機 Download PDF

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Publication number
WO2022234669A1
WO2022234669A1 PCT/JP2021/017563 JP2021017563W WO2022234669A1 WO 2022234669 A1 WO2022234669 A1 WO 2022234669A1 JP 2021017563 W JP2021017563 W JP 2021017563W WO 2022234669 A1 WO2022234669 A1 WO 2022234669A1
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WIPO (PCT)
Prior art keywords
laser
wavelength
debris
thrust
laser light
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Ceased
Application number
PCT/JP2021/017563
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English (en)
French (fr)
Japanese (ja)
Inventor
忠徳 福島
数馬 足立
智之 和田
俊一 戎崎
貴代 小川
克彦 津野
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Sky Perfect Jsat Corp
RIKEN
Original Assignee
Sky Perfect Jsat Corp
RIKEN
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Filing date
Publication date
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Priority to JP2023518597A priority Critical patent/JP7717155B2/ja
Priority to PCT/JP2021/017563 priority patent/WO2022234669A1/ja
Priority to US18/289,703 priority patent/US20240239519A1/en
Priority to EP21939860.9A priority patent/EP4335756A4/en
Publication of WO2022234669A1 publication Critical patent/WO2022234669A1/ja
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/40—Arrangements or adaptations of propulsion systems
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
    • B64G1/1078—Maintenance satellites
    • B64G1/1081—Maintenance satellites for debris removal
    • G—PHYSICS
    • G02—OPTICS
    • G02F—OPTICAL DEVICES OR ARRANGEMENTS FOR THE CONTROL OF LIGHT BY MODIFICATION OF THE OPTICAL PROPERTIES OF THE MEDIA OF THE ELEMENTS INVOLVED THEREIN; NON-LINEAR OPTICS; FREQUENCY-CHANGING OF LIGHT; OPTICAL LOGIC ELEMENTS; OPTICAL ANALOGUE/DIGITAL CONVERTERS
    • G02F1/00—Devices or arrangements for the control of the intensity, colour, phase, polarisation or direction of light arriving from an independent light source, e.g. switching, gating or modulating; Non-linear optics
    • G02F1/35—Non-linear optics
    • G02F1/353—Frequency conversion, i.e. wherein a light beam is generated with frequency components different from those of the incident light beams
    • G—PHYSICS
    • G02—OPTICS
    • G02F—OPTICAL DEVICES OR ARRANGEMENTS FOR THE CONTROL OF LIGHT BY MODIFICATION OF THE OPTICAL PROPERTIES OF THE MEDIA OF THE ELEMENTS INVOLVED THEREIN; NON-LINEAR OPTICS; FREQUENCY-CHANGING OF LIGHT; OPTICAL LOGIC ELEMENTS; OPTICAL ANALOGUE/DIGITAL CONVERTERS
    • G02F1/00—Devices or arrangements for the control of the intensity, colour, phase, polarisation or direction of light arriving from an independent light source, e.g. switching, gating or modulating; Non-linear optics
    • G02F1/35—Non-linear optics
    • G02F1/39—Non-linear optics for parametric generation or amplification of light, infrared or ultraviolet waves
    • G02F1/392—Parametric amplification
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
    • B64G1/24—Guiding or controlling apparatus, e.g. for attitude control

Definitions

  • the present invention relates to a thrust generator that generates a thrust force on an object by irradiating the object with a laser to cause ablation, and a spacecraft having the thrust generator.
  • Patent Document 1 The applicants have proposed a technique for irradiating debris with a laser and controlling the trajectory or attitude of the debris by the thrust generated by the laser irradiation.
  • Patent Literature 1 proposes attaching a thrust reinforcing member to the debris and irradiating the thrust reinforcing member with a laser to generate a stronger thrust.
  • attaching thrust enhancers to debris is costly. Also, this measure cannot be applied to existing objects.
  • an object of the present invention is to provide a technique for generating a strong thrust by a simpler method than before.
  • One aspect of the present invention is a thrust generator for irradiating an object with a laser to generate a thrust to the object, comprising: a first laser beam having a first wavelength and a second laser beam different from the first wavelength;
  • the thrust generator includes a laser device that generates a second laser beam of a wavelength, and an irradiation device that simultaneously irradiates the object with the first laser beam and the second laser beam.
  • the surface of the object is excited by one of the first laser beam and the second laser beam, and the absorptivity of the other laser beam is improved, which is more efficient than the case of using a single laser beam. more ablation, thus providing more powerful thrust.
  • the first laser beam has a higher intensity than the second laser beam
  • the second laser beam (second wavelength) has a higher absorptivity in the object than the first laser beam (first wavelength).
  • first wavelength the first laser beam
  • second wavelength the second laser beam
  • the absorptance of the first laser beam which originally has a low absorptivity, increases, and therefore only the first laser beam is used. It becomes possible to generate ablation more efficiently than in the case.
  • a laser device includes a laser light source that generates a first laser beam, and a wavelength converter that converts part of the first laser beam generated from the laser light source into a second laser beam.
  • a laser device may be configured including a first laser light source that generates a first laser beam and a second laser light source that generates a second laser beam.
  • the laser light source is not particularly limited, for example, a solid-state laser or fiber laser that oscillates in the 1 ⁇ m band can be used.
  • the wavelength converter may convert the wavelength of the first laser beam (first wavelength) into a shorter wavelength or a longer wavelength.
  • the wavelength converter may include a nonlinear optical crystal that generates harmonics of the first laser light to produce second laser light of a second wavelength shorter than the first wavelength.
  • the second laser beam may be any harmonic (second harmonic, third harmonic, fourth harmonic, etc.) of the first laser beam.
  • the wavelength converter may include an optical parametric oscillator to generate a second laser beam of a second wavelength longer than the first wavelength. Since the intensity of the second laser light need not be high, the wavelength conversion efficiency of the wavelength converter may be low.
  • the adjustment of the wavelength converter does not require precision and the device can be configured simply.
  • the wavelength conversion efficiency may be 10% or less (1/10 or less), or even 0.1% (1/1000) or less.
  • Such devices are easy to manufacture and are suitable, for example, for space applications.
  • Another aspect of the present invention is a spacecraft that irradiates an object with a laser to change the trajectory or attitude of the object in outer space, comprising the thrust generator described above, wherein the irradiation device comprises the laser
  • the spacecraft is characterized in that a laser generated from a generator irradiates the object so as to converge on the object.
  • FIG. 1 is a diagram showing an example of debris control according to this embodiment.
  • FIG. 2 is a diagram showing an example of laser irradiation according to this embodiment.
  • FIG. 3 is a diagram showing an example of a laser irradiation system according to this embodiment.
  • FIG. 4 is a diagram showing an example of a focus unit and a steering unit according to this embodiment.
  • 5A to 5C are diagrams showing configuration examples of the laser generator according to the present embodiment.
  • FIG. 6 is a diagram showing the wavelength dependence of absorptance for each substance.
  • FIG. 7 is a diagram showing another configuration example of the laser generator according to this embodiment.
  • the thrust generation device is a device that generates a thrust force on an object by irradiating the object with a laser to generate ablation.
  • the thrust generator is mounted on a spacecraft (artificial satellite) and used to control the orbit or attitude of an object existing in outer space. By controlling the trajectory or attitude of the object, unwanted objects can be removed, for example.
  • Objects in this embodiment are man-made objects including debris existing in outer space (space debris, space debris) and objects other than man-made objects (for example, meteorites, etc.).
  • Debris includes satellites that have become uncontrollable, satellites that have become unnecessary due to the termination of their operation, and parts of satellites that have been ejected due to collisions or the like.
  • debris is used as an object.
  • Orbit or attitude control refers to changing the orbit and attitude of an object (debris) in outer space.
  • Changing the trajectory means, for example, raising or lowering the altitude of the debris.
  • debris can be re-entered into the atmosphere and incinerated, moved to an orbit where it will not collide with other satellites (graveyard orbit), or the satellite can be temporarily moved to avoid collisions with debris and other objects. move as desired.
  • changing the posture means, for example, suppressing the rotation of the debris. This reduces the risk of collisions during physical access.
  • an example of using an artificial satellite as a spacecraft will be described, but the spacecraft is not limited to an unmanned spacecraft, and a manned spacecraft may be used as the spacecraft. Also, a device (slave device) mounted on an artificial satellite (master device) or the like may be used as a spacecraft. Further, the application of the thrust generator and the type of object are not limited to those exemplified above, and the thrust generator may be used for any object in the ground environment, for example.
  • FIG. 1 is a diagram showing an example of debris removal according to this embodiment.
  • FIG. 1 shows the earth 11, the atmosphere 12 covering the earth 11, and the orbit 13 which is the orbit around the earth.
  • the spacecraft 100 is an artificial satellite that irradiates an object with a laser.
  • the debris 200 is an object that moves in the orbit 13 at a speed v, and is, for example, an artificial satellite or the like that has become unnecessary due to the expiration of its operating period or the like.
  • the spacecraft 100 irradiates the debris 200 with a laser to cause the debris 200 to generate a velocity change ⁇ v. Due to the reaction force, the debris 200 is, for example, lowered in altitude and re-entered into the atmosphere to be incinerated.
  • the debris removal method is not limited to the above, and for example, the altitude of the debris 200 may be raised (or lowered) and moved to an orbit (graveyard orbit) where no other artificial satellite exists.
  • FIG. 2 is a diagram showing thrust generated by laser irradiation.
  • a laser 21 is a laser emitted by the spacecraft 100 .
  • the substance on the surface of the debris 200 evaporates, turns into plasma, and spouts out (plasma ablation).
  • the debris 200 receives the reaction force of the ejecting force (arrow 22) as a thrust, causing a speed change ⁇ v (arrow 23).
  • FIG. 3 is a diagram showing the configuration of the laser irradiation system according to this embodiment.
  • the laser irradiation system includes a spacecraft 100, a monitoring device 110, and the like.
  • a spacecraft 100 is an artificial satellite having a laser irradiation function.
  • the spacecraft 100 has an acquisition unit 101, a detection unit 102, a control unit 103, a propulsion unit 104, a communication unit 105, a laser irradiation device 109, and the like.
  • the laser irradiation device 109 has a laser generator 106 , a focus section 107 and a steering section 108 .
  • the laser irradiation device 109 irradiates the debris 200 with the laser output from the laser generation device 106 via the focus unit 107 and the steering unit 108, and generates thrust to the debris 200 by generating ablation.
  • the laser irradiation device 109 corresponds to a thrust generator.
  • the acquisition unit 101 is a functional unit that acquires an image using an imaging unit (not shown).
  • the acquisition unit 101 also acquires reflected light of a search laser output from a laser generator 106, which will be described later.
  • the acquisition unit 101 can also be regarded as various sensors.
  • the detection unit 102 is a functional unit that acquires detection information of the debris 200 based on the image or reflected light acquired by the acquisition unit 101 .
  • the detection information includes the distance between the spacecraft 100 and the debris 200, the position, size, shape, captured image, rotational state (attitude) of the debris 200, and the like.
  • the detection unit 102 acquires the distance between the spacecraft 100 and the debris 200 using Lidar (Light Detection and Ranging).
  • the control unit 103 controls the focus unit 107 based on the distance between the spacecraft 100 and the debris 200 so that the laser emitted from the laser generator 106 converges on the debris 200 .
  • the focus unit 107 is an optical system
  • the focal length of the optical system is adjusted.
  • the control unit 103 is a functional unit that determines the irradiation position of the laser on the debris 200 and the output value of the laser based on the detection information acquired by the detection unit 102 .
  • the control unit 103 determines the laser irradiation position based on the position and posture of the debris 200 detected by the detection unit 102 and the area suitable for laser irradiation.
  • the area suitable for laser irradiation is an area excluding locations where laser irradiation may pose a danger (for example, a fuel tank, etc.). Also, the control unit 103 may determine the position and timing of laser irradiation in consideration of a safe area on the ground.
  • a safe area is an area for dropping debris left after the debris 200 has not burned up when it re-enters the atmosphere. For example, the safe area is the sea several tens to several hundred nautical miles or more away from the routes of ships and aircraft, and land.
  • the control unit 103 preferably acquires information on areas suitable for laser irradiation and safe areas from the monitoring device 110 (to be described later) via the communication unit 105 .
  • the propulsion unit 104 is a functional unit that controls the attitude or trajectory of the spacecraft 100 by using thrusters (actuators) such as thrusters or wheels to adjust the attitude required for laser irradiation.
  • the attitude control method is not particularly limited, and an existing method such as a three-axis stability method, a bias momentum method, a zero momentum method, or the like can be adopted.
  • the communication unit 105 is a functional unit for communicating with the monitoring device 110 on the ground. Through the communication unit 105, the spacecraft 100 acquires information such as the rough position of the debris 200 (coarse orbital position), the area suitable for laser irradiation, and the safe area.
  • the laser generator 106 is a device that outputs a laser.
  • the laser generator 106 simultaneously irradiates a plurality of different laser beams to more efficiently generate ablation on the object. A more detailed description of laser generator 106 and ablation is provided later.
  • the focus part 107 is a member for converging the laser emitted by the laser generator 106 .
  • the spacecraft 100 can emit a laser to the debris 200 even from a remote location.
  • the focus unit 107 uses a general telescope, but is not limited to a telescope as long as it is a member for converging a laser.
  • the remote point is assumed to be a position about 20 m to 1000 m away from the debris 200, but the distance between the spacecraft 100 and the debris 200 is not particularly limited.
  • the steering section 108 is a member for changing the irradiation direction of the laser output by the focus section 107 .
  • a movable mirror can be used as the steering unit 108 .
  • the spacecraft 100 can easily direct the irradiation direction of the laser toward the debris 200 even from a remote location. Further, even if the spacecraft 100 and the debris 200 are not on the same orbit, it is possible to easily direct the irradiation direction of the laser to the debris 200 even from a remote location. are reduced.
  • the laser generator 106, the focus unit 107, and the steering unit 108 collectively correspond to a "thrust force generator” for generating a thrust force on the object. Also, the focus unit 107 and the steering unit 108 correspond to an “irradiation device” for irradiating the object with the laser light output from the laser generator 106 .
  • FIG. 4 is a diagram showing an example of the configuration of the focus unit 107 and the steering unit 108 according to this embodiment.
  • the laser output from the laser generator 106 is gradually converged through the focusing section 107 .
  • the laser is reflected by the steering unit 108 to change the irradiation direction.
  • the method of directing the laser to the target is not limited to the above.
  • the direction in which the laser is emitted may be changed by controlling the attitude of the spacecraft 100 itself without using the steering section 108 .
  • the direction in which the laser is emitted may be changed by changing the orientation of the focus unit 107 .
  • the focus unit 107 and the steering unit 108 are provided as a part of the spacecraft 100, but they may be provided separately from the spacecraft 100. FIG.
  • the monitoring device 110 is a device that detects the rough position of the debris 200 and transmits information on the detected debris 200 to the spacecraft 100 .
  • the monitoring device 110 may transmit to the spacecraft 100 information about areas suitable for laser irradiation and safe areas.
  • the debris 200 is a part of an artificial satellite released by a collision or the like from a large satellite such as an artificial satellite that has become uncontrollable or an artificial satellite that has become unnecessary due to the end of operation (for example, parts such as screws) may be included.
  • Objects of the debris 200 are not limited to the above, and include objects existing in outer space (for example, meteorites, etc.).
  • the size of the debris 200 is not particularly limited. In general, objects existing in outer space can be detected from the ground if they are 10 cm or more in size, but the spacecraft 100 according to this embodiment detects debris 200 in outer space. Therefore, even an object of 10 cm or less can be detected.
  • FIG. 5A is a block diagram showing one embodiment of the laser generator 106.
  • the laser generator 106 includes a laser light source 601 , a wavelength converter 602 and a wavelength converter 603 .
  • the laser light source 601 is, for example, a fiber laser or a solid-state laser using an Nd:YAG crystal that oscillates a laser with a wavelength of 1064 nm.
  • Nd:YAG crystal In order to oscillate a laser in the 1 ⁇ m band, Yb:YAG crystal may be used instead of Nd:YAG to oscillate laser light with a wavelength of 1030 nm.
  • a CW (continuous wave) laser is oscillated, but a pulse laser may be oscillated.
  • the wavelength converter 602 has a nonlinear optical crystal for converting part of the laser light generated from the laser light source 601 into second harmonics. The nonlinear optical crystal converts two photons of the fundamental wave into one photon with twice the frequency (half the wavelength).
  • wavelength converter 603 has a nonlinear optical crystal for converting the second harmonic output from the wavelength converter to the fourth harmonic. The nonlinear optical crystal converts two photons of the second harmonic into one photon of twice the frequency (half the wavelength). Therefore, the laser generator 106 outputs a fundamental wave (1064 nm), a second harmonic (532 nm) and a fourth harmonic (266 nm).
  • Non-Patent Documents 1 to 3 report that ablation can be enhanced by simultaneously irradiating an object with lasers of different wavelengths as described above. Briefly explaining the principle, when a laser beam with a low absorption rate and a laser beam with a high absorption rate are irradiated to an object at the same time, the surface of the target is excited by the absorption of the laser light with a high absorption rate. , the ablation is more strongly caused even by the laser beam, which originally has a low absorption rate.
  • FIG. 6 is a graph showing the wavelength dependence of absorptance for each material.
  • the material of the object is aluminum, which is generally used as a material for artificial satellites.
  • Laser light in the 1 ⁇ m band can be easily generated by Nd:YAG or Yb:YAG, but the absorptivity of aluminum is low and the intensity of ablation is weak.
  • the absorption rate of the fourth harmonic (266 nm) is high, at least by irradiating the fundamental wave and the fourth harmonic to an aluminum object at the same time, the surface is excited by the absorption of the fourth harmonic, Fundamental waves are more likely to be absorbed and ablation is more likely to occur.
  • the intensity of the fourth harmonic does not need to be so strong, and may be 10% or less, 1% or less, or 0.1% or less of the fundamental wave. Therefore, the wavelength converters 602 and 603 are not required to have high conversion efficiency. In order to achieve high wavelength conversion efficiency, it becomes necessary to strictly control the angles and temperatures of the nonlinear optical crystals in the wavelength converters 602 and 603, which increases the cost of the device. However, in this embodiment, effects can be obtained even with low wavelength conversion efficiency, so there is an advantage that the device can be easily manufactured and realized at low cost.
  • the second harmonic may be removed and only the fundamental wave and the fourth harmonic may be irradiated.
  • the second harmonic since the second harmonic also contributes to ablation, the second harmonic may be irradiated at the same time.
  • the configuration for removing the second harmonic is not required, the configuration of the device is simplified.
  • the fourth harmonic is used because the object is aluminum, but a suitable harmonic can be used according to the material of the object.
  • the absorptivity is high at a wavelength of 600 nm or less, so if the fundamental wave (1064 nm) and the second harmonic (532 nm) are irradiated simultaneously, an effect of enhancing ablation can be obtained.
  • the laser generator 106 may include a laser light source 601 and a wavelength converter 602 as shown in FIG. 5B.
  • metals generally have a high absorptivity at around 300 nm or less, if the fourth harmonic (266 nm), the fifth harmonic (213 nm), or higher harmonics are used, the 1 ⁇ m band absorption for general metals can be achieved.
  • a laser oscillator can be used to generate powerful ablation.
  • the target object is not limited to metal materials, and can be any material.
  • materials include glass, polymer, and CFRP (carbon fiber reinforced polymer composite material). Some materials have absorption at wavelengths longer than 1 ⁇ m.
  • OPO optical parametric oscillator
  • the laser generator 106 generates laser light with multiple wavelengths using one light source and wavelength converter, but the laser generator 106 may have multiple light sources.
  • the laser generator 106 may have an Nd:YAG laser light source 901 and a semiconductor laser light source 902, and couple the two laser beams by mirrors 903 and 904 for irradiation.
  • Semiconductor lasers are small, and even if the number of light sources is increased, there is no disadvantage in terms of device configuration.
  • a semiconductor laser can oscillate laser light with a wide range of wavelengths from visible light to infrared
  • a semiconductor laser made of an appropriate material may be used according to the material of the object. For example, if the object is aluminum, it absorbs in the 800 nm band, so if an infrared semiconductor laser is used as the semiconductor laser light source 902, it is possible to generate strong ablation on aluminum.
  • the laser irradiation device (thrust generator) 109 is mounted on the spacecraft, irradiates the debris 200 in outer space with a laser, and changes the position and attitude of the debris 200 by thrust due to ablation. did.
  • the laser irradiation device (thrust generator) is not limited to use in outer space, and may be used on the ground or in the atmosphere.
  • the impulse obtained by irradiating the same place with laser light of two wavelengths is 4.99 ⁇ Ns, which is larger than the sum of the impulses obtained by irradiating laser light of each wavelength.
  • the impulse obtained by irradiating different locations with the laser beams of two wavelengths is 4.73 ⁇ Ns, which is almost equal to the sum of the impulses obtained by irradiating the laser beams of each wavelength.
  • spacecraft 101 acquisition unit 102: detection unit 103: control unit 104: propulsion unit 105: communication unit 106: laser generator 107: focus unit 108: steering unit 109: laser irradiation device 110: monitoring device 200: debris

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  • Physics & Mathematics (AREA)
  • Engineering & Computer Science (AREA)
  • Remote Sensing (AREA)
  • Nonlinear Science (AREA)
  • General Physics & Mathematics (AREA)
  • Astronomy & Astrophysics (AREA)
  • Aviation & Aerospace Engineering (AREA)
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PCT/JP2021/017563 2021-05-07 2021-05-07 推力発生装置、宇宙機 Ceased WO2022234669A1 (ja)

Priority Applications (4)

Application Number Priority Date Filing Date Title
JP2023518597A JP7717155B2 (ja) 2021-05-07 2021-05-07 推力発生装置、宇宙機
PCT/JP2021/017563 WO2022234669A1 (ja) 2021-05-07 2021-05-07 推力発生装置、宇宙機
US18/289,703 US20240239519A1 (en) 2021-05-07 2021-05-07 Thrust generating device and spacecraft
EP21939860.9A EP4335756A4 (en) 2021-05-07 2021-05-07 Thrust generating device and spacecraft

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PCT/JP2021/017563 WO2022234669A1 (ja) 2021-05-07 2021-05-07 推力発生装置、宇宙機

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Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20110302906A1 (en) * 2010-06-15 2011-12-15 John Elihu Sinko Laser Tractor Beam
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 (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3943374A1 (de) * 1989-12-30 1991-07-04 Deutsche Forsch Luft Raumfahrt Verfahren und einrichtung zum entfernen von weltraumtruemmern
US5144630A (en) * 1991-07-29 1992-09-01 Jtt International, Inc. Multiwavelength solid state laser using frequency conversion techniques
US6834064B1 (en) * 1999-12-08 2004-12-21 Time-Bandwidth Products Ag Mode-locked thin-disk laser
US6530212B1 (en) * 2000-02-25 2003-03-11 Photonic Associates Laser plasma thruster
US7087914B2 (en) * 2004-03-17 2006-08-08 Cymer, Inc High repetition rate laser produced plasma EUV light source
JP2012002905A (ja) * 2010-06-15 2012-01-05 V Technology Co Ltd レーザ発生装置及びレーザ発生方法
JP5793308B2 (ja) * 2011-01-14 2015-10-14 株式会社Ｓｃｒｅｅｎホールディングス 光学デバイス、レーザ装置および露光装置
EP3800033B1 (en) * 2019-09-30 2024-08-21 Ricoh Company, Ltd. Irradiation target flying apparatus, three-dimensional modeling apparatus, and irradiation target flying method

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20110302906A1 (en) * 2010-06-15 2011-12-15 John Elihu Sinko Laser Tractor Beam
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

Non-Patent Citations (6)

* Cited by examiner, † Cited by third party
Title
"Laser Ablation", 1 January 1996, ELSEVIER, ISBN: 978-0-444-82412-7, article SUGIOKA K., WADA S., OHNUMA Y., NAKAMURA A., TASHIRO H., TOYODA K.: "Multiwavelength irradiation effect in fused quartz ablation using vacuum-ultraviolet Raman laser", pages: 347 - 351, XP093005216, DOI: 10.1016/B978-0-444-82412-7.50062-6 *
J. ZHANGK. SUGIOKAS. WADAH. TASHIROK. TOYODAK. MIDORIKAWA: "Precise microfabrication of wide band gap semiconductors (SiC and GaN) by VUV-UV multiwavelength laser ablation", APPL. SURF. SCI., 1998, pages 793 - 799
K. SUGIOKAS. WADAA. TSUNEMIT. SAKAIH. TAKAIH. MORIWAKIA. NAKAMURAH. TASHIROK. TOYODA: "Micropatterning of Quartz Substrates by Multi-wavelength Vacuum-Ultraviolet Laser Ablation", JPN. J. APPL. PHYS., vol. 32, 1993, pages 6185 - 6189, XP093005211, DOI: 10.1143/JJAP.32.6185
K. SUGIOKAS. WADAY. OHNUMAA. NAKAMURAH. TASHIROK. TOYODA: "Multiwavelength irradiation effect in fused quartz ablation using vacuum-ultraviolet Raman laser", APPL. SURF. SCI., 1996, pages 347 - 351, XP093005216, DOI: 10.1016/B978-0-444-82412-7.50062-6
SUGIOKA KOJI: "Micropatterning of Quartz Substrates by Multi-Wavelength Vacuum-Ultraviolet Laser Ablation", JAPANESE JOURNAL OF APPLIED PHYSICS, 1 January 1993 (1993-01-01), pages 6185 - 6189, XP093005211, [retrieved on 20221206], DOI: 10.1143/JJAP.32.6185 *
ZHANG J, ET AL.: "PRECISE MICROFABRICATION OF WIDE BAND GAP SEMICONDUCTORS (SIC AND GAN) BY VUV-UV MULTIWAVELENGTH LASER ABLATION", APPLIED SURFACE SCIENCE, ELSEVIER, AMSTERDAM , NL, vol. 127-129, 21 July 1997 (1997-07-21), Amsterdam , NL , pages 793 - 799, XP001086614, ISSN: 0169-4332, DOI: 10.1016/S0169-4332(97)00744-7 *

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