JPH0165799U

JPH0165799U -

Info

Publication number: JPH0165799U
Application number: JP1987160916U
Authority: JP
Priority date: 1987-10-21
Filing date: 1987-10-21
Publication date: 1989-04-27

Description

[Brief explanation of drawings]

第１図は、人工衛星の軌道上の位置と各軸方向
と制御位置を説明する為の図、第２図は、この考
案による人工衛星の軌道制御装置を説明する為の
図、第３図は、軌道傾斜角変化を示す図、第４図
は、第２図に示す構成機器間の接続及び信号の流
れを示す図である。図中の１は地球、２は人工衛星の軌道、３は赤
道面、４は人工衛星、５は軌道傾斜角、６は昇交
点、７は降交点、８は軌道傾斜角制御開始点、９
は軌道傾斜角制御終了点、１０はピツチ軸、１１
はロール軸、１２はヨー軸、１３は−ピツチ軸側
イオンエンジンスラスタ、１４は＋ピツチ軸側イ
オンエンジンスラスタ、１５はＧＰＳ受信装置、
１６は軌道要素計算データ処理装置１、１７は軌
道傾斜角制御判断装置２、１８は制御位置、制御
量計算と制御信号作成装置３、１９は使用スラス
タ選択装置４、２０は軌道傾斜角９大きさを表わ
す軸、２１は経過時間を表わす軸、２２は軌道傾
斜角許容最大値、２３は制御終了判断の為の傾斜
角最小値、２４はイオンエンジンスラスタ噴射時
間、２５は制御による傾斜角変化、２６は振動に
よる軌道傾斜角の変化である。尚、図中、同一符
号は同一又は相当部分を示す。 Fig. 1 is a diagram for explaining the position on the orbit of the artificial satellite, each axis direction, and control position, Fig. 2 is a diagram for explaining the orbit control device for the artificial satellite according to this invention, Fig. 3 is a diagram showing changes in the orbital inclination angle, and FIG. 4 is a diagram showing connections and signal flows between the component devices shown in FIG. 2. In the figure, 1 is the Earth, 2 is the orbit of the satellite, 3 is the equatorial plane, 4 is the satellite, 5 is the orbital inclination, 6 is the ascending node, 7 is the descending node, 8 is the starting point for orbital inclination angle control, 9
is the orbit inclination angle control end point, 10 is the pitch axis, 11
is the roll axis, 12 is the yaw axis, 13 is the - pitch axis side ion engine thruster, 14 is the + pitch axis side ion engine thruster, 15 is the GPS receiver,
16 is an orbit element calculation data processing device 1, 17 is an orbit inclination angle control judgment device 2, 18 is a control position, control amount calculation and control signal generation device 3, 19 is a thruster selection device 4, and 20 is an orbit inclination angle 9 large 21 is the axis representing the elapsed time, 22 is the maximum allowable orbit inclination angle, 23 is the minimum inclination angle value for determining the end of control, 24 is the ion engine thruster injection time, and 25 is the change in inclination angle due to control. , 26 is a change in the orbital inclination angle due to vibration. In addition, in the figures, the same reference numerals indicate the same or corresponding parts.

Claims

[Scope of utility model registration request]

A satellite in orbit uses the Global Positioning System (GPS).
ng System), a data processing device 1 that calculates orbital elements for data processing from GPS, and a data processing device 1 that determines whether the orbital inclination angle i is within the retention range from this orbital data. A device 2, a device 3 that calculates the control position and control amount and creates a signal instructing execution when the result i is outside the holding range and control is required, and a device 3 used for this control. The ion engine is equipped with a device 4 that determines which thruster to use, and an ion engine that generates thrust in a direction outside the orbital plane for i-control, and which has a higher specific impulse and consumes less propellant than conventional hydrazine thrusters. An orbit control device for an artificial satellite characterized by being able to perform on-board orbit inclination angle control with a small amount of propellant consumption.