JPH031900U

JPH031900U -

Info

Publication number: JPH031900U
Application number: JP6220389U
Authority: JP
Priority date: 1989-05-29
Filing date: 1989-05-29
Publication date: 1991-01-10

Description

[Brief explanation of drawings]

第１図はこの考案の一実施例を示す図、第２図
は従来の磁気姿勢制御装置の一例を示した図であ
る。図中、１は制御器、２は磁気コイル制御信号、
３は磁気コイル、４は発生磁気、５は地磁気、６
は制御トルク、７は衛星ダイナミクス、８は外乱
トルク、９は入力トルク、１０は磁気浮上支持型
回転輪、１１は姿勢センサ、１２は姿勢信号、１
３は回転輪駆動器、１４は回転輪駆動信号、１５
は検出器、１６は回転数信号、１７は人工衛星、
１８は比較器、１９は異常時信号、２０は増幅器
、２１は補助磁気コイル制御信号、２２は補助磁
気コイル、２３は補助発生磁気である。なお、各図中同一符号は同一または相当部分を
示す。 FIG. 1 is a diagram showing an embodiment of this invention, and FIG. 2 is a diagram showing an example of a conventional magnetic attitude control device. In the figure, 1 is a controller, 2 is a magnetic coil control signal,
3 is a magnetic coil, 4 is generated magnetism, 5 is earth's magnetism, 6
is a control torque, 7 is a satellite dynamics, 8 is a disturbance torque, 9 is an input torque, 10 is a magnetic levitation supported rotating wheel, 11 is an attitude sensor, 12 is an attitude signal, 1
3 is a rotary wheel drive device, 14 is a rotary wheel drive signal, 15
is a detector, 16 is a rotation speed signal, 17 is an artificial satellite,
18 is a comparator, 19 is an abnormality signal, 20 is an amplifier, 21 is an auxiliary magnetic coil control signal, 22 is an auxiliary magnetic coil, and 23 is an auxiliary generated magnetism. Note that the same reference numerals in each figure indicate the same or corresponding parts.

Claims

[Scope of utility model registration request]

When a disturbance torque acts on an artificial satellite and the certain side of the artificial satellite changes so that it no longer faces the earth,
An attitude sensor that detects changes in the satellite's attitude and outputs an attitude signal proportional to the change in attitude, and a rotating wheel driver that transmits a rotating wheel drive signal proportional to the change in attitude signal to the magnetically supported rotating wheel. , a detector that detects the rotation speed of the magnetic levitation supported rotary wheel and transmits a rotation speed signal proportional to the rotation speed to the controller, and a magnetic coil control signal proportional to the rotation speed signal output to the magnetic coil. The control torque generated by the controller and the interference between the generated magnetism generated by the magnetic coil and the earth's magnetism in proportion to the magnetic coil control signal,
and satellite dynamics that is output as an input torque by subtracting it from the disturbance torque and transmitted to the magnetic levitation supported rotating wheel, the rotational speed corresponding to when the rotational speed of the magnetically levitation supported rotating wheel reaches saturation. A comparator that responds only to the signal and outputs an abnormality signal, and an amplifier that outputs an auxiliary magnetic coil control signal proportional to the abnormality signal to the auxiliary magnetic coil are installed inside the satellite at the same time, and the auxiliary magnetic coil is controlled. Adding the auxiliary generated magnetism generated by the auxiliary magnetic coil in proportion to the signal to the above generated magnetism,
A magnetic attitude control device for an artificial satellite, characterized in that the attitude of the artificial satellite is controlled by controlling the attitude of the artificial satellite so that a certain side of the artificial satellite always faces the earth by acting on the earth's magnetism together with the generated magnetism.