GB1279098A - Improvements in orbiting spacecraft or satellite attitude control systems - Google Patents

Improvements in orbiting spacecraft or satellite attitude control systems

Info

Publication number
GB1279098A
GB1279098A GB5875968A GB5875968A GB1279098A GB 1279098 A GB1279098 A GB 1279098A GB 5875968 A GB5875968 A GB 5875968A GB 5875968 A GB5875968 A GB 5875968A GB 1279098 A GB1279098 A GB 1279098A
Authority
GB
United Kingdom
Prior art keywords
torque
attitude control
spacecraft
spin axis
electromagnets
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
GB5875968A
Inventor
James William Heaton
Ronald William Young
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.)
Hawker Siddeley Dynamics Ltd
Original Assignee
Hawker Siddeley Dynamics 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
Application filed by Hawker Siddeley Dynamics Ltd filed Critical Hawker Siddeley Dynamics Ltd
Priority to NL6914824A priority Critical patent/NL6914824A/xx
Priority to DE19691950332 priority patent/DE1950332A1/en
Priority to BE739696D priority patent/BE739696A/xx
Priority to FR696933480A priority patent/FR2023313B1/fr
Publication of GB1279098A publication Critical patent/GB1279098A/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
    • B64G1/28—Guiding or controlling apparatus, e.g. for attitude control using inertia or gyro effect

Abstract

1279098 Controlling satellites HAWKER SIDDELEY DYNAMICS Ltd 1 Oct 1969 [1 Oct 1968 10 Dec 1968] 46608/68 and 58759/68 Heading B7W An attitude control system for a spin stabilized orbiting spacecraft or satellite 11 comprises one or more coils or electromagnets 13, the excitation of which is controllably variable, mounted with their magnetic axes 14 perpendicular to the spacecraft spin axis 12. Application of an excitation current which is pulsed cyclically (15, Fig. 1b, not shown), or which has an alternating waveform (16), of which one or more complete cycles occur for each revolution of the structure 11 and the magnet 13, causes the magnetic moment of magnet 13 to react with the component of the local magnetic field 17 which is parallel to the axis 12 to produce an attitude control torque 18 which controls the precession of the spin axis. The amplitude of any associated nutation which would remain after removal of the torque 18 may be made zero merely by suitable adjustment of the operation time of the torque and of the appropriate moment for removing it. If the stabilization angular momentum is generated by a flywheel 20 (Fig. 2, not shown) within the stationary spacecraft structure (19), the controlling torque is obtained from two electromagnets (22) on the structure (19) which have their magnetic axes perpendicular to the spin axis (21) and to each other.
GB5875968A 1968-10-01 1968-10-01 Improvements in orbiting spacecraft or satellite attitude control systems Expired GB1279098A (en)

Priority Applications (4)

Application Number Priority Date Filing Date Title
NL6914824A NL6914824A (en) 1968-10-01 1969-10-01
DE19691950332 DE1950332A1 (en) 1968-10-01 1969-10-01 System for controlling the attitude of a spacecraft
BE739696D BE739696A (en) 1968-10-01 1969-10-01
FR696933480A FR2023313B1 (en) 1968-10-01 1969-10-01

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB4660868 1968-10-01

Publications (1)

Publication Number Publication Date
GB1279098A true GB1279098A (en) 1972-06-21

Family

ID=10441917

Family Applications (1)

Application Number Title Priority Date Filing Date
GB5875968A Expired GB1279098A (en) 1968-10-01 1968-10-01 Improvements in orbiting spacecraft or satellite attitude control systems

Country Status (1)

Country Link
GB (1) GB1279098A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103332301A (en) * 2013-06-08 2013-10-02 北京航空航天大学 Method for utilizing liquid filling variable inertial flywheel to control attitude of spacecraft and actuating mechanism thereof
CN113335567A (en) * 2021-05-26 2021-09-03 航天科工空间工程发展有限公司 Wheel magnetic hybrid attitude control method and system for microsatellite

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103332301A (en) * 2013-06-08 2013-10-02 北京航空航天大学 Method for utilizing liquid filling variable inertial flywheel to control attitude of spacecraft and actuating mechanism thereof
CN103332301B (en) * 2013-06-08 2015-09-23 北京航空航天大学 Topping up inertia variable fly wheel is utilized to control method and the actuating unit thereof of spacecraft attitude
CN113335567A (en) * 2021-05-26 2021-09-03 航天科工空间工程发展有限公司 Wheel magnetic hybrid attitude control method and system for microsatellite

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Legal Events

Date Code Title Description
PS Patent sealed
PLNP Patent lapsed through nonpayment of renewal fees