JPS6180200U - - Google Patents

Info

Publication number
JPS6180200U
JPS6180200U JP16140985U JP16140985U JPS6180200U JP S6180200 U JPS6180200 U JP S6180200U JP 16140985 U JP16140985 U JP 16140985U JP 16140985 U JP16140985 U JP 16140985U JP S6180200 U JPS6180200 U JP S6180200U
Authority
JP
Japan
Prior art keywords
output
supplied
magnetic
circuit
artificial satellite
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.)
Granted
Application number
JP16140985U
Other languages
Japanese (ja)
Other versions
JPS6131920Y2 (en
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed filed Critical
Priority to JP16140985U priority Critical patent/JPS6131920Y2/ja
Publication of JPS6180200U publication Critical patent/JPS6180200U/ja
Application granted granted Critical
Publication of JPS6131920Y2 publication Critical patent/JPS6131920Y2/ja
Expired legal-status Critical Current

Links

Landscapes

  • Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)

Description

【図面の簡単な説明】[Brief explanation of the drawing]

図はこの考案の一実施例を示すブロツク構成図
であり、1は磁気トルカ、2はアンローデイング
回路、3は地磁気センサ、4はバイアス発生回路
、5は加算器である。
The figure is a block diagram showing an embodiment of this invention, in which 1 is a magnetic torquer, 2 is an unloading circuit, 3 is a geomagnetic sensor, 4 is a bias generation circuit, and 5 is an adder.

Claims (1)

【実用新案登録請求の範囲】[Scope of utility model registration request] 人工衛星のアンローデイング等の目的に使用す
る磁気姿勢制御装置において、ホイールの速度信
号および地磁気センサ3の出力を供給されるアン
ローデイング回路2と、このアンローデイング回
路2の出力およびバイアス発生回路4の出力を供
給される加算器5と、この加算器5の出力を供給
される磁気トルカ1とからなり、上記バイアス回
路の出力信号を磁気トルカに供給して上記外乱ト
ルクにより発生する人工衛星の姿勢の乱れを除去
するように構成したことを特徴とする人工衛星の
磁気姿勢制御装置。
In a magnetic attitude control device used for the purpose of unloading an artificial satellite, an unloading circuit 2 is supplied with a wheel speed signal and the output of a geomagnetic sensor 3, and an output of the unloading circuit 2 and a bias generating circuit 4 are provided. It consists of an adder 5 supplied with an output, and a magnetic torquer 1 supplied with the output of this adder 5, and the output signal of the bias circuit is supplied to the magnetic torquer to adjust the attitude of the artificial satellite caused by the disturbance torque. 1. A magnetic attitude control device for an artificial satellite, characterized in that it is configured to remove disturbances in the magnetic field.
JP16140985U 1985-10-22 1985-10-22 Expired JPS6131920Y2 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
JP16140985U JPS6131920Y2 (en) 1985-10-22 1985-10-22

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP16140985U JPS6131920Y2 (en) 1985-10-22 1985-10-22

Publications (2)

Publication Number Publication Date
JPS6180200U true JPS6180200U (en) 1986-05-28
JPS6131920Y2 JPS6131920Y2 (en) 1986-09-17

Family

ID=30719319

Family Applications (1)

Application Number Title Priority Date Filing Date
JP16140985U Expired JPS6131920Y2 (en) 1985-10-22 1985-10-22

Country Status (1)

Country Link
JP (1) JPS6131920Y2 (en)

Also Published As

Publication number Publication date
JPS6131920Y2 (en) 1986-09-17

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