GB1285919A - A device for automatically controlling the attitude of a space satellite utilizing geomagnetic field - Google Patents

A device for automatically controlling the attitude of a space satellite utilizing geomagnetic field

Info

Publication number
GB1285919A
GB1285919A GB47227/69A GB4722769A GB1285919A GB 1285919 A GB1285919 A GB 1285919A GB 47227/69 A GB47227/69 A GB 47227/69A GB 4722769 A GB4722769 A GB 4722769A GB 1285919 A GB1285919 A GB 1285919A
Authority
GB
United Kingdom
Prior art keywords
satellite
attitude
computer
sensor
geomagnetic field
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.)
Expired
Application number
GB47227/69A
Inventor
Moritada Kubo
Masamichi Shigehara
Shozo Yasui
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.)
Toshiba Corp
Original Assignee
Tokyo Shibaura Electric Co Ltd
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
Priority claimed from JP43069504A external-priority patent/JPS491439B1/ja
Priority claimed from JP43069505A external-priority patent/JPS4913759B1/ja
Application filed by Tokyo Shibaura Electric Co Ltd filed Critical Tokyo Shibaura Electric Co Ltd
Publication of GB1285919A publication Critical patent/GB1285919A/en
Expired legal-status Critical Current

Links

Classifications

    • 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
    • B64G1/32—Guiding or controlling apparatus, e.g. for attitude control using earth's magnetic field
    • 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
    • B64G1/36—Guiding or controlling apparatus, e.g. for attitude control using sensors, e.g. sun-sensors, horizon sensors
    • 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
    • B64G1/36—Guiding or controlling apparatus, e.g. for attitude control using sensors, e.g. sun-sensors, horizon sensors
    • B64G1/366—Guiding or controlling apparatus, e.g. for attitude control using sensors, e.g. sun-sensors, horizon sensors using magnetometers
    • 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
    • B64G1/36—Guiding or controlling apparatus, e.g. for attitude control using sensors, e.g. sun-sensors, horizon sensors
    • B64G1/361—Guiding or controlling apparatus, e.g. for attitude control using sensors, e.g. sun-sensors, horizon sensors using star sensors
    • 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
    • B64G1/36—Guiding or controlling apparatus, e.g. for attitude control using sensors, e.g. sun-sensors, horizon sensors
    • B64G1/363—Guiding or controlling apparatus, e.g. for attitude control using sensors, e.g. sun-sensors, horizon sensors using sun sensors
    • 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
    • B64G1/36—Guiding or controlling apparatus, e.g. for attitude control using sensors, e.g. sun-sensors, horizon sensors
    • B64G1/365—Guiding or controlling apparatus, e.g. for attitude control using sensors, e.g. sun-sensors, horizon sensors using horizon or Earth sensors
    • 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
    • B64G1/36—Guiding or controlling apparatus, e.g. for attitude control using sensors, e.g. sun-sensors, horizon sensors
    • B64G1/369—Guiding or controlling apparatus, e.g. for attitude control using sensors, e.g. sun-sensors, horizon sensors using gyroscopes as attitude sensors

Abstract

1285919 Automatic control of satellites TOKYO SHIBAURA ELECTRIC CO Ltd 25 Sept 1969 [27 Sept 1968 (2)] 47227/69 Heading G3R The vector senses of attitude, attitude error and ambient geomagnetic field are combined to determine the necessary sense of operation of a reversing switch controlling the energization of a coil fixed to the satellite so that it corrects the error by interaction with the geomagnetic field. In Fig. 3, a sensor 303, such as a gyroscope, horizon sensor, sun sensor or star tracker carried by an earth orbiting satellite produces a signal dependent on the attitude of the spin axis of the satellite. A reference signal is produced by a gyroscopic or a sun, star or earth seeking device 302 which is set to correspond with a desired attitude of the satellite. A signal representing the difference between moments of inertia of the satellite relative to the actual and desired attitudes is derived from the above signals at 307 and applied to a computer 304 together with a signal representing the direction of the ambient geomagnetic field derived from a magnetometer 301 and the signal representing the attitude of the satellite from sensor 303. Computer 304 calculates from its inputs a function the sign of which determines the position of a reversing relay 308 controlling the energization of a coil 310 having an axis coincident with the spin axis of the satellite. As a result a current is applied alternately in one sense and the other to maintain the satellite in a desired attitude. In a modification, the coil current variations during orbit are controlled by a digital programmer which is periodically updated, e.g. once per orbit, by signals transmitted to the satellite from a computer on the ground. At the same frequency, e.g. once per orbit, signals from an attitude sensor transmitted from the satellite, and data on the orbit, location and speed of the satellite derived from a tracking radar, are applied to update simulators in the computer on the ground. Immediately after each updating of the programmer in the satellite, the computer predicts from that programme, which is stored, and the latest orbital and attitude data, the programme of coil current variations which will be transmitted at the next updating of the programmer in the satellite.
GB47227/69A 1968-09-27 1969-09-25 A device for automatically controlling the attitude of a space satellite utilizing geomagnetic field Expired GB1285919A (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
JP43069504A JPS491439B1 (en) 1968-09-27 1968-09-27
JP43069505A JPS4913759B1 (en) 1968-09-27 1968-09-27

Publications (1)

Publication Number Publication Date
GB1285919A true GB1285919A (en) 1972-08-16

Family

ID=26410690

Family Applications (1)

Application Number Title Priority Date Filing Date
GB47227/69A Expired GB1285919A (en) 1968-09-27 1969-09-25 A device for automatically controlling the attitude of a space satellite utilizing geomagnetic field

Country Status (3)

Country Link
DE (1) DE1948760A1 (en)
FR (1) FR2019068A1 (en)
GB (1) GB1285919A (en)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2129969A (en) * 1982-04-20 1984-05-23 Messerschmitt Boelkow Blohm Method of and apparatus for magnetically adjusting the position of a satellite
CN100441483C (en) * 2006-12-14 2008-12-10 北京航空航天大学 Integrated magnetically suspended control moment gyroscope control platform
CN105173120A (en) * 2015-09-21 2015-12-23 上海卫星工程研究所 Control method for in-orbit automatic job task implementation of satellite
CN105487402A (en) * 2014-09-17 2016-04-13 上海新跃仪表厂 Attitude determination full-physical simulation test method by combination of star sensor and gyro
CN107054702A (en) * 2017-02-15 2017-08-18 上海航天控制技术研究所 Earth's magnetic field analogy method in a kind of semi-physical simulation test
CN111060111A (en) * 2019-12-23 2020-04-24 北京国电高科科技有限公司 Low-orbit satellite orbit-entering initial orbit determination method
CN117040608A (en) * 2023-10-10 2023-11-10 四川轻化工大学 Vehicle-mounted satellite relay

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3606636C1 (en) * 1986-02-28 1987-11-05 Messerschmitt Boelkow Blohm Method for determining geomagnetic field components with reference to a satellite-fixed coordinate system
CN113581492B (en) * 2021-07-23 2023-07-21 上海卫星工程研究所 Self-adaptive configuration method applied to double-star combined orbit entering roles
CN115817856B (en) * 2022-11-21 2023-06-20 清华大学 Method and device for controlling stable attitude of satellite to solar spin based on pure magnetic control mode

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2129969A (en) * 1982-04-20 1984-05-23 Messerschmitt Boelkow Blohm Method of and apparatus for magnetically adjusting the position of a satellite
CN100441483C (en) * 2006-12-14 2008-12-10 北京航空航天大学 Integrated magnetically suspended control moment gyroscope control platform
CN105487402A (en) * 2014-09-17 2016-04-13 上海新跃仪表厂 Attitude determination full-physical simulation test method by combination of star sensor and gyro
CN105487402B (en) * 2014-09-17 2018-07-20 上海新跃仪表厂 A kind of star is quick to determine appearance full physical simulation test method with Gyro
CN105173120A (en) * 2015-09-21 2015-12-23 上海卫星工程研究所 Control method for in-orbit automatic job task implementation of satellite
CN105173120B (en) * 2015-09-21 2017-03-22 上海卫星工程研究所 Control method for in-orbit automatic job task implementation of satellite
CN107054702A (en) * 2017-02-15 2017-08-18 上海航天控制技术研究所 Earth's magnetic field analogy method in a kind of semi-physical simulation test
CN107054702B (en) * 2017-02-15 2019-07-26 上海航天控制技术研究所 Earth's magnetic field analogy method in a kind of semi-physical simulation test
CN111060111A (en) * 2019-12-23 2020-04-24 北京国电高科科技有限公司 Low-orbit satellite orbit-entering initial orbit determination method
CN117040608A (en) * 2023-10-10 2023-11-10 四川轻化工大学 Vehicle-mounted satellite relay
CN117040608B (en) * 2023-10-10 2023-12-08 四川轻化工大学 Vehicle-mounted satellite relay

Also Published As

Publication number Publication date
FR2019068A1 (en) 1970-06-26
DE1948760A1 (en) 1970-05-06

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Legal Events

Date Code Title Description
PS Patent sealed [section 19, patents act 1949]
435 Patent endorsed 'licences of right' on the date specified (sect. 35/1949)
PE20 Patent expired after termination of 20 years