WO2014115753A1 - Procédé de contrôle du plan orbital d'un satellite artificiel - Google Patents

Procédé de contrôle du plan orbital d'un satellite artificiel Download PDF

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Publication number
WO2014115753A1
WO2014115753A1 PCT/JP2014/051228 JP2014051228W WO2014115753A1 WO 2014115753 A1 WO2014115753 A1 WO 2014115753A1 JP 2014051228 W JP2014051228 W JP 2014051228W WO 2014115753 A1 WO2014115753 A1 WO 2014115753A1
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WO
WIPO (PCT)
Prior art keywords
satellite
orbital
artificial
orbit
orbital plane
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Application number
PCT/JP2014/051228
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English (en)
Japanese (ja)
Inventor
宏之 小泉
順一 青山
Original Assignee
国立大学法人 東京大学
次世代宇宙システム技術研究組合
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Application filed by 国立大学法人 東京大学, 次世代宇宙システム技術研究組合 filed Critical 国立大学法人 東京大学
Publication of WO2014115753A1 publication Critical patent/WO2014115753A1/fr

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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
    • B64G1/24—Guiding or controlling apparatus, e.g. for attitude control
    • B64G1/242—Orbits and trajectories
    • B64G1/2427—Transfer orbits
    • 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
    • B64G1/242—Orbits and trajectories
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
    • B64G1/00—Cosmonautic vehicles
    • B64G1/002—Launch systems
    • 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
    • B64G1/405—Ion or plasma engines

Definitions

  • the present invention relates to an orbital plane control method for an artificial satellite, and more particularly to an orbital plane control method for an artificial satellite using a propulsion device having low propulsive force and high propellant efficiency.
  • each artificial satellite on the parking orbit is inserted into each transition orbit, and each artificial satellite on each transition orbit is It is characterized by shifting to each orbit.
  • Patent Document 1 is to introduce a plurality of artificial satellites into a target parking orbit from the beginning.
  • a launch opportunity is provided as long as the mission of the main satellite is not impaired. Therefore, it cannot be expected to enter a parking orbit preferable for the piggyback satellite from the beginning.
  • the propulsion device for small satellites that are required to be extremely compact and lightweight, the propulsion device (thruster) for performing the necessary orbit control has high specific thrust characteristics that enable efficient propellant consumption. It is preferable that it is a propulsion device.
  • the propulsion device with high specific thrust has been considered to be unsuitable for track surface control that requires a high thrust level because the thrust level is extremely low. Therefore, the track surface control has so far been performed using a propulsion device with a high thrust level and a low specific thrust at the expense of propellant consumption.
  • the present invention has been made in view of such problems, and without sacrificing the mission of the main satellite, and further reducing the size and weight of the artificial satellite and providing the artificial satellite with a high thrust level propulsion device It is an object to provide an orbital plane control method for an artificial satellite capable of realizing orbit control substantially equivalent to the above.
  • the invention according to claim 1 is an orbital plane control method for an artificial satellite in which a plurality of small artificial satellites launched together with a main satellite are introduced into respective target orbits. Change the orbital altitude of the small satellite inserted into the target orbit of the main satellite using a propulsion device with a low thrust level, and use the transition of the orbital plane due to the flatness of the earth gravity field at the orbital altitude Then, a plurality of the artificial satellites are thrown into each target orbit.
  • the present invention according to claim 2 is the orbital plane control method for artificial satellite according to claim 1, wherein the change of the orbital height is performed by changing the propulsion device to the orbital traveling direction of the artificial satellite. And a second step of injecting the propulsion device in the direction opposite to the first step for the same amount of time.
  • the present invention according to claim 3 is the orbital plane control method for an artificial satellite according to claim 1 or 2, wherein the propulsion device is an ion engine.
  • the present invention controls the orbital altitude with a thruster with high specific thrust and high propellant efficiency but low thrust level, such as an ion engine. It is characterized in that the artificial satellite is thrown into the desired orbital plane by utilizing the transition of the orbital plane due to the flatness of the earth gravity field.
  • the orbital plane control method for an artificial satellite there is an effect that a small piggyback satellite can be put into a desired target orbit without impairing the mission of the main satellite.
  • propulsion efficiency can be greatly improved by using a propulsion device with a relatively low thrust level such as an ion engine, so that the equipment required for the piggyback satellite can be installed instead of propellant. effective.
  • the piggyback satellite can be further reduced in size, the number of piggyback satellites to be mounted can be increased.
  • FIG. 1 is a diagram showing orbital elements of an artificial satellite.
  • reference numeral 10 denotes an artificial satellite, and the artificial satellite 10 rotates around the earth 1 while drawing an elliptical orbit 11 having a major radius “a” in the opposite direction to the clock.
  • the angle formed by the orbital plane 3 and the equator plane 5 at this time is the orbital inclination angle i, and the orbit passes through the equator plane 5 from the south side (lower side in FIG. 1) to the north side (upper side in FIG. 1).
  • the longitude is the ascending intersection longitude (rising intersection red diameter) ⁇ . Further, ⁇ in FIG. 1 indicates the equinox point direction.
  • the earth is not a perfect sphere, but is shaped like a spheroid that is crushed to the north and south close to the spheroid centered on the earth axis.
  • the orbital angular momentum vector direction of the artificial satellite 10 changes. This change in the angular momentum vector direction represents the rotation of the track surface 3 at a predetermined angular velocity.
  • the rotation of the orbital plane is more easily affected by the lower orbital altitude, and the transition amount is larger. The higher the orbital altitude, the smaller the amount of transition.
  • a low thrust / high propellant efficiency propulsion device such as an ion engine mounted on an artificial satellite is continuously injected in the opposite direction (or the same direction) of the orbital speed for a predetermined time to increase (or lower) the orbital altitude. Then, the orbital altitude is increased (or lowered) by a predetermined value by continuously injecting (maneuvering) in the opposite direction for the same time, and the flatness of the earth's gravitational field due to the change in the orbital altitude at this time The artificial satellite is thrown into the target orbital plane by using the change in the amount of transition of the orbital plane.
  • the increase (or decrease) of the transition angular velocity of the raceway surface is obtained by increasing (or decelerating) the propulsion unit over the orbit N times in the orbital traveling direction (or the opposite direction).
  • the speed is increased (or decelerated)
  • the orbital speed remains increased by N ⁇ V with respect to the initial speed VI.
  • the increase (or decrease) proceeds at the transition speed corresponding to. Therefore, in order to return to the initial orbital surface angular velocity, it is necessary to inject the maneuver in the reverse direction by the same number of orbits (N rounds). Therefore, as a maneuver for controlling the raceway surface, it is necessary to perform both the first half and the second half maneuver with the injection direction reversed. This point will be further described with reference to FIGS.
  • FIG. 2 is an explanatory diagram showing the orbital plane transition when the orbital altitude is once lowered and then raised
  • FIG. 3 is a graph showing the injection of the propulsion device, changes in the orbital altitude and changes in the orbital plane transition.
  • reference numeral 11 denotes one of a plurality of piggyback satellites launched together with a main satellite (not shown) and put into the target orbit of the main satellite.
  • the piggyback satellite is a small satellite having a weight of about 50 kg, and is a satellite that can be launched together with the main satellite by utilizing the surplus capacity of the launch vehicle.
  • a piggyback satellite (hereinafter simply referred to as “satellite”) 11 is equipped with a propulsion device having a high propellant efficiency but a relatively low thrust level, such as an ion engine.
  • the satellite 11 is initially inserted into a target orbit S1 of a main satellite (not shown) and orbits the orbit S1.
  • the orbit S5 is the orbital plane where the satellite 11 is to be finally inserted.
  • the satellite 11 starts to descend its orbital altitude by injecting the propulsion device in the same direction as the orbital traveling direction of the satellite 11 orbiting the orbit S1. Since the thrust of the propulsion device of the satellite 11 is at a low level, the orbital altitude decreases slightly.
  • the amount of transition of the orbital plane due to the flatness of the earth's gravitational field at the orbital altitude of the satellite 11 also changes in a direction that gradually increases.
  • the ascending intersection longitude ⁇ of the satellite 11 changes to the orbit S2 while gradually changing. Further, by continuing the injection in the same direction as the orbital traveling direction, the first-half injection is terminated when the orbit S3 reaches the intermediate position until the satellite 11 reaches the target orbit S5.
  • the latter half of the injection is started.
  • the orbital altitude of the satellite 11 is started to rise by injecting the propulsion device in the direction opposite to the orbital traveling direction of the satellite 11 contrary to the first half. Since the thrust of the propulsion device of the satellite 11 is at a low level, the orbital altitude increases slightly.
  • the orbital altitude of the satellite 11 gradually rises due to the injection opposite to the orbital traveling direction, the amount of transition of the orbital plane due to the flatness of the earth's gravitational field at the orbital altitude of the satellite 11 also changes in a direction that gradually decreases.
  • the ascending intersection longitude ⁇ of the satellite 11 changes to the orbit S4 while gradually changing.
  • the satellite 11 reaches the target orbit S5 by continuing the injection in the direction opposite to the orbital traveling direction. And if the satellite 11 is thrown into the target orbit S5, the injection of the propulsion device is terminated and the orbit S5 is maintained.
  • FIG. 4 is an explanatory diagram showing the orbital plane transition when the orbital altitude is once raised and then lowered
  • FIG. 4 is a graph showing the injection of the propulsion device, changes in orbital altitude and changes in orbital plane transition.
  • reference numeral 12 denotes one of a plurality of piggyback satellites launched together with a main satellite (not shown) and put into the target orbit of the main satellite. Similar to the satellite 11, the satellite 12 is equipped with a propulsion device having a relatively low thrust level such as an ion engine.
  • the satellite 12 is initially put into a target orbit S6 of a main satellite (not shown) and orbits the orbit S6.
  • the orbit S10 is the orbital plane where the satellite 12 is to be finally inserted.
  • the propulsion device injecting the propulsion device in a direction opposite to the orbital traveling direction of the satellite 12 orbiting the orbit S6, the satellite 12 starts to increase the orbital altitude.
  • the thrust of the propulsion device of the satellite 12 is at a low level, the orbital altitude increases slightly.
  • the orbital plane of the satellite 12 changes in the opposite direction to that shown in FIG. Therefore, the ascending intersection longitude ⁇ of the satellite 12 changes to the orbit S7 while gradually changing. Further, by continuing the injection in the direction opposite to the orbit traveling direction, the first-half injection is terminated when the orbit S8 reaches the intermediate position until the satellite 12 reaches the target orbit S10.
  • the satellite 12 When the satellite 12 reaches orbit S8, which is the intermediate position, the latter half of the injection is started. In this case, the orbital altitude of the satellite 12 starts to be lowered by injecting the propulsion device in the same direction as the orbital traveling direction of the satellite 10 contrary to the first half. Since the thrust of the propulsion device of the satellite 12 is at a low level, the orbital altitude decreases slightly.
  • the orbital altitude of the satellite 12 gradually decreases due to the injection in the same direction as the orbital traveling direction, the transition amount of the orbital plane due to the flatness of the earth's gravitational field at the orbital altitude of the satellite 12 also changes in a direction that gradually increases.
  • the ascending intersection longitude ⁇ of the satellite 12 changes to the orbit S9 while gradually changing. Further, the satellite 12 reaches the target orbit S10 by continuing the injection in the same direction as the orbital traveling direction. And if the satellite 12 is thrown into the target orbit S10, the injection of the propulsion device is terminated and the orbit S10 is
  • the orbital plane control as described above is performed in accordance with the respective target orbits, so that they are put into the target orbit of the main satellite.
  • Each of the plurality of piggyback satellites can be introduced into the target orbital plane.
  • the orbital length radius a is expressed as a function of the orbital velocity V as shown in Equation 2.
  • Equation 3 the time change rate is expressed as Equation 3.
  • Equation 4 V, as shown in Equation 4, plus the initial velocity V increases small thrust added continuously during the circumferential track N to I (or decrease) the orbital velocity variation N ⁇ V.
  • Equation 6 the increase (or decrease) ⁇ in the transition angle of the raceway surface by injecting the propulsion device is expressed by Equation 6.
  • the increase (or decrease) in the transition angle of the raceway surface given by Equation 6 increases (or decelerates) the propulsion unit over the orbit N times in the orbital traveling direction (or the opposite direction) as described above.
  • those by obtained in this state is in the state that the track speed increases to an initial velocity V I by N ⁇ V
  • the while standing raceways transition corresponding to the orbital velocity It will increase (or decrease) thereafter at the transition speed. Therefore, in order to return to the initial orbital transition angular velocity, it is necessary to inject in the reverse direction by the same number of orbits following the maneuver. Therefore, as a maneuver for controlling the raceway surface, it is necessary to perform both the first half and the second half maneuver with the injection direction reversed.
  • Propellant Propellant mass ratio Hydrazine 1 / 7.5 Hydrogen peroxide 1 / 16.0 Nitrogen gas 1 / 30.0

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  • Engineering & Computer Science (AREA)
  • Remote Sensing (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
  • Automation & Control Theory (AREA)

Abstract

[Problème] L'invention a pour objet de réaliser un procédé de contrôle du plan orbital d'un satellite artificiel, capable de réaliser un contrôle d'orbite sensiblement équivalent à celui d'un satellite artificiel équipé d'un système de propulsion présentant un haut niveau de poussée, dans le but de réduire la taille et le poids du satellite artificiel sans nuire à la mission d'un satellite principal. [Solution] Le présent procédé de contrôle du plan orbital d'un satellite artificiel fait intervenir les étapes consistant à diriger une pluralité de petits satellites artificiels (11, 12), qui sont lancés conjointement avec un satellite principal, vers des orbites visées respectives, et est caractérisé en ce que les altitudes orbitales des petits satellites artificiels (11, 12), qui sont dirigés vers une orbite visée (S1) du satellite principal, sont modifiées en utilisant des systèmes de propulsion présentant un faible niveau de poussée, et en ce que la pluralité de satellites artificiels (11, 12) est introduite dans des orbites visées respectives (S5, S9) en utilisant des transitions dans les plans orbitaux causées par l'aplatissement du champ de gravité de la Terre auxdites altitudes orbitales.
PCT/JP2014/051228 2013-01-22 2014-01-22 Procédé de contrôle du plan orbital d'un satellite artificiel WO2014115753A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
JP2013-008935 2013-01-22
JP2013008935A JP2014141108A (ja) 2013-01-22 2013-01-22 人工衛星の軌道面制御方法

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WO2014115753A1 true WO2014115753A1 (fr) 2014-07-31

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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN111417576A (zh) * 2017-12-01 2020-07-14 帝奥瑞波特有限公司 在地球轨道中释放人造卫星的方法

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3020348B1 (fr) 2014-04-24 2016-05-13 Snecma Procede de deploiement d'une constellation de satellites
CN105512374B (zh) * 2015-11-30 2019-02-01 上海宇航系统工程研究所 一种同轨道面内自然伴飞条件下的卫星观测轨道设计方法
WO2020157802A1 (fr) * 2019-01-28 2020-08-06 三菱電機株式会社 Dispositif de commande de surveillance, satellite artificiel et système de surveillance
JP7068765B2 (ja) * 2019-05-31 2022-05-17 三菱電機株式会社 衛星コンステレーション形成システム、衛星コンステレーション形成方法、衛星コンステレーション形成プログラム、および地上装置
WO2020255310A1 (fr) * 2019-06-19 2020-12-24 三菱電機株式会社 Système de formation de constellation de satellites, procédé de formation de constellation de satellites, constellation de satellites et équipement de sol
CN110816896B (zh) * 2019-10-28 2021-06-11 中国空间技术研究院 一种卫星星上简易轨道外推方法

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH07187091A (ja) * 1993-12-28 1995-07-25 Natl Space Dev Agency Japan<Nasda> 複数の人工衛星の打ち上げ方法
JP2002308198A (ja) * 2001-04-17 2002-10-23 Nec Toshiba Space System Kk 衛星航行システム及び衛星の軌道投入方法

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH07187091A (ja) * 1993-12-28 1995-07-25 Natl Space Dev Agency Japan<Nasda> 複数の人工衛星の打ち上げ方法
JP2002308198A (ja) * 2001-04-17 2002-10-23 Nec Toshiba Space System Kk 衛星航行システム及び衛星の軌道投入方法

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN111417576A (zh) * 2017-12-01 2020-07-14 帝奥瑞波特有限公司 在地球轨道中释放人造卫星的方法
CN111417576B (zh) * 2017-12-01 2023-12-19 帝奥瑞波特有限公司 在地球轨道中释放人造卫星的方法

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