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GB1483467A - Orientation system for a spin stabilized spacecraft - Google Patents

Orientation system for a spin stabilized spacecraft

Info

Publication number
GB1483467A
GB1483467A GB4759374A GB4759374A GB1483467A GB 1483467 A GB1483467 A GB 1483467A GB 4759374 A GB4759374 A GB 4759374A GB 4759374 A GB4759374 A GB 4759374A GB 1483467 A GB1483467 A GB 1483467A
Authority
GB
United Kingdom
Prior art keywords
thrust
sensor
craft
spin
spin 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
GB4759374A
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.)
RCA Corp
Original Assignee
RCA Corp
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 RCA Corp filed Critical RCA Corp
Publication of GB1483467A publication Critical patent/GB1483467A/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
    • B64G1/281—Spin-stabilised spacecraft
    • 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

Landscapes

  • Engineering & Computer Science (AREA)
  • Remote Sensing (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)

Abstract

1483467 Attitude control R C A CORPORATION 4 Nov 1974 [16 Nov 1973] 47593/74 Heading G3N The attitude of a spin-stabilized space-craft body is adjusted without changing the craft velocity by a system in which equal and opposite thrusts F 1 , F 2 create a pure couple about an axis T 1 perpendicular to the spin axis 13. The system requires a sensor 17 which establishes the direction of an inertial reference point, e.g. the sun. The sensor, in moving round the spin axis, is aligned with that point once per rotation and this establishes a time-reference relative to which the correct instant to apply a predetermined reactive-thrust couple in order to effect a desired attitude change. The thrusts are pulsed - that is, a predetermined single-shot thrust of given duration and magnitude is repeated, at appropriate time intervals, until the desired attitude change has been effected. The control system Fig. 2 (not shown) consists of a delay circuit with two inputs: one receiving a command signal from the ground to determine whether, and by how much, an attitude change is required; and the other from the sun sensor to determine the time of thrust-firing in relation to the rotation of the craft about the spin axis. The delay circuit output operates a fire command circuit for the thrustors, subject to an enabling input from the earth station.
GB4759374A 1973-11-16 1974-11-04 Orientation system for a spin stabilized spacecraft Expired GB1483467A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US41657973A 1973-11-16 1973-11-16

Publications (1)

Publication Number Publication Date
GB1483467A true GB1483467A (en) 1977-08-17

Family

ID=23650521

Family Applications (1)

Application Number Title Priority Date Filing Date
GB4759374A Expired GB1483467A (en) 1973-11-16 1974-11-04 Orientation system for a spin stabilized spacecraft

Country Status (5)

Country Link
JP (1) JPS5317240B2 (en)
CA (1) CA1004205A (en)
DE (1) DE2454071C3 (en)
FR (1) FR2251472B1 (en)
GB (1) GB1483467A (en)

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3072363A (en) * 1959-04-30 1963-01-08 Robert C Baumann Spin adjusting mechanism
US3169729A (en) * 1963-03-26 1965-02-16 Godo Einar Attitude control system
US3532297A (en) * 1967-01-23 1970-10-06 Rocket Research Corp Space vehicle attitude control by microrockets utilizing subliming solid propellants

Also Published As

Publication number Publication date
JPS5317240B2 (en) 1978-06-07
DE2454071A1 (en) 1975-06-26
DE2454071B2 (en) 1981-07-02
JPS5082799A (en) 1975-07-04
FR2251472B1 (en) 1980-11-14
DE2454071C3 (en) 1982-03-18
FR2251472A1 (en) 1975-06-13
CA1004205A (en) 1977-01-25

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Legal Events

Date Code Title Description
PS Patent sealed
PE20 Patent expired after termination of 20 years

Effective date: 19941103