GB1132392A - Improvements in radiation-operated attitude control of satellites - Google Patents

Improvements in radiation-operated attitude control of satellites

Info

Publication number
GB1132392A
GB1132392A GB307466A GB307466A GB1132392A GB 1132392 A GB1132392 A GB 1132392A GB 307466 A GB307466 A GB 307466A GB 307466 A GB307466 A GB 307466A GB 1132392 A GB1132392 A GB 1132392A
Authority
GB
United Kingdom
Prior art keywords
batteries
sun
satellite
earth
axis
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
GB307466A
Inventor
Robert Price Wanger
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.)
General Electric Co
Original Assignee
General Electric Co
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 by General Electric Co filed Critical General Electric Co
Priority to GB307466A priority Critical patent/GB1132392A/en
Publication of GB1132392A publication Critical patent/GB1132392A/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
    • B64G1/28—Guiding or controlling apparatus, e.g. for attitude control using inertia or gyro effect
    • B64G1/285—Guiding or controlling apparatus, e.g. for attitude control using inertia or gyro effect using momentum wheels
    • 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
    • B64G1/365—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
    • B64G1/366—Guiding or controlling apparatus, e.g. for attitude control using sensors, e.g. sun-sensors, horizon sensors using magnetometers

Landscapes

  • Engineering & Computer Science (AREA)
  • Remote Sensing (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Environmental & Geological Engineering (AREA)
  • General Life Sciences & Earth Sciences (AREA)
  • Geochemistry & Mineralogy (AREA)
  • Geology (AREA)
  • Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)

Abstract

1,132,392. Controlling satellites. GENERAL ELECTRIC CO. 24 Jan., 1966, No. 3074/66. Headings B7G and B7W. [Also in Divisions G3 and H4] An artificial satellite is stabilized in yaw by the interaction between the earth's magnetic field and electromagnets powered by solar batteries. As described, the satellite is gravitystabilized in pitch and roll by a geo-stabilizing rod (77, Fig. 4, not shown) and is in a polar orbit, the plane of which includes the sun. Solar batteries such as 2, 4 are connected to windings 34, 36 on a magnetic core 68, and are separated by a partition so that if the axis 51 of the satellite is yawed relative to the sun, one of the batteries 2, 4 is shaded, and the arms of the magnetic core are differentially magnetized, producing a restoring moment by interaction with the earth's magnetic field, since the lines of force and the sun's rays are substantially co-planar. A similar pair of solar batteries (6, 8, Fig. 3, not shown), are arranged below the pair 2, 4, shielded from them by a partition, and one pair or the other is used according to whether the axis 51 is pitched up or down relative to the sun (i.e. at different parts of the orbit). A similar set of four batteries 10, 12, (and 14, 16, Fig. 5, not shown) is provided at the other end, one set being used when the satellite is approaching the sun and the other when it is receding. When the axis 51 is approximately in line with the sun, i.e. over the poles, shades 56, 58 cover the batteries, and the system is inactive. Other shades protect the batteries from the earth reflection and from the sun when overhead. Resistors 18, 20, 26, 28 in series with the batteries heat up as current flows from the batteries, causing an increase in resistance which produces a damping effect.
GB307466A 1966-01-24 1966-01-24 Improvements in radiation-operated attitude control of satellites Expired GB1132392A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB307466A GB1132392A (en) 1966-01-24 1966-01-24 Improvements in radiation-operated attitude control of satellites

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB307466A GB1132392A (en) 1966-01-24 1966-01-24 Improvements in radiation-operated attitude control of satellites

Publications (1)

Publication Number Publication Date
GB1132392A true GB1132392A (en) 1968-10-30

Family

ID=9751501

Family Applications (1)

Application Number Title Priority Date Filing Date
GB307466A Expired GB1132392A (en) 1966-01-24 1966-01-24 Improvements in radiation-operated attitude control of satellites

Country Status (1)

Country Link
GB (1) GB1132392A (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2686858A1 (en) * 1992-02-04 1993-08-06 Europ Agence Spatiale Method for controlling the relative position between two craft moving close to each other, in particular between two satellites, and implementation system
EP0603869A1 (en) * 1992-12-22 1994-06-29 Hughes Aircraft Company Magnetic torque attitude control system
CN113654655A (en) * 2021-08-24 2021-11-16 宁波工程学院 Solar sun-tracking visible light photoresistor detection method
CN116263595A (en) * 2022-11-16 2023-06-16 长光卫星技术股份有限公司 Universal automatic test platform for satellite single machine environment test and control method thereof

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2686858A1 (en) * 1992-02-04 1993-08-06 Europ Agence Spatiale Method for controlling the relative position between two craft moving close to each other, in particular between two satellites, and implementation system
EP0603869A1 (en) * 1992-12-22 1994-06-29 Hughes Aircraft Company Magnetic torque attitude control system
CN113654655A (en) * 2021-08-24 2021-11-16 宁波工程学院 Solar sun-tracking visible light photoresistor detection method
CN116263595A (en) * 2022-11-16 2023-06-16 长光卫星技术股份有限公司 Universal automatic test platform for satellite single machine environment test and control method thereof
CN116263595B (en) * 2022-11-16 2024-05-10 长光卫星技术股份有限公司 Universal automatic test platform for satellite single machine environment test and control method thereof

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