GB2241480A - Apparatus and method for controlling attitude of a spacecraft orbiting Earth or other celestial body - Google Patents
Apparatus and method for controlling attitude of a spacecraft orbiting Earth or other celestial body Download PDFInfo
- Publication number
- GB2241480A GB2241480A GB9004472A GB9004472A GB2241480A GB 2241480 A GB2241480 A GB 2241480A GB 9004472 A GB9004472 A GB 9004472A GB 9004472 A GB9004472 A GB 9004472A GB 2241480 A GB2241480 A GB 2241480A
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- GB
- United Kingdom
- Prior art keywords
- spacecraft
- magnet means
- primary magnet
- attitude
- magnet
- 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
Links
- 238000000034 method Methods 0.000 title claims description 9
- 239000007788 liquid Substances 0.000 claims description 8
- 239000012530 fluid Substances 0.000 claims description 7
- 230000003993 interaction Effects 0.000 claims description 6
- 238000004891 communication Methods 0.000 claims description 5
- 239000007787 solid Substances 0.000 claims description 4
- 229910000975 Carbon steel Inorganic materials 0.000 claims description 3
- 239000010962 carbon steel Substances 0.000 claims description 3
- KPLQYGBQNPPQGA-UHFFFAOYSA-N cobalt samarium Chemical compound [Co].[Sm] KPLQYGBQNPPQGA-UHFFFAOYSA-N 0.000 claims description 2
- 235000013870 dimethyl polysiloxane Nutrition 0.000 claims description 2
- 239000004205 dimethyl polysiloxane Substances 0.000 claims description 2
- 239000000463 material Substances 0.000 claims description 2
- 230000003534 oscillatory effect Effects 0.000 claims description 2
- 238000013021 overheating Methods 0.000 claims description 2
- 229920000435 poly(dimethylsiloxane) Polymers 0.000 claims description 2
- 230000005855 radiation Effects 0.000 claims description 2
- 229910000938 samarium–cobalt magnet Inorganic materials 0.000 claims description 2
- 230000005484 gravity Effects 0.000 description 8
- 230000000694 effects Effects 0.000 description 3
- BGPVFRJUHWVFKM-UHFFFAOYSA-N N1=C2C=CC=CC2=[N+]([O-])C1(CC1)CCC21N=C1C=CC=CC1=[N+]2[O-] Chemical group N1=C2C=CC=CC2=[N+]([O-])C1(CC1)CCC21N=C1C=CC=CC1=[N+]2[O-] BGPVFRJUHWVFKM-UHFFFAOYSA-N 0.000 description 1
- 229910000831 Steel Inorganic materials 0.000 description 1
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 1
- 229910052782 aluminium Inorganic materials 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000013016 damping Methods 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000010355 oscillation Effects 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
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
- B64G1/244—Spacecraft control systems
-
- 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
- B64G1/34—Guiding or controlling apparatus, e.g. for attitude control using gravity gradient
Abstract
Apparatus for controlling attitude of a spacecraft (1) orbiting Earth or other Celestial body, includes primary magnet means (2) mountable on the spacecraft (1) for motion relative thereto under the influence of the magnetic field (A) of the Earth or other Celestial body, energy dissipating means (3, 4) locatable on the spacecraft (1) and operable to bring motion of the spacecraft (1) substantially into equality with that of the primary magnet means (2), thereby to damp down rotation of the spacecraft (1), and means (5) for biasing the primary magnet means (2) towards a desired orientation with respect to the spacecraft (1) thereby to control attitude of the spacecraft (1). <IMAGE>
Description
APPARATUS AND METHOD FOR CONTROLLING ATTITUDE OF
A SPACECRAFT ORBITING EARTH OR OTHER
CELESTIAL BODY
This invention relates to an apparatus and method for controlling attitude of a spacecraft orbiting Earth or other celestial body and is particularly, but not exclusively, suitable for use with a satellite operating within the Earth's magnetosphere. Such a satellite may be a gravity gradient stabilised spacecraft, a spacecraft with attitude control provided solely by the control apparatus or a spacecraft in which magnetic torques are used as an adjunct of attitude control.
One of the problems encountered with gravity gradient stabilised satellites is that of initial attitude acquisition. The main difficulty encountered in initial attitude acquisition with such a satellite is the problem of preventing "upside down" acquisition relative to the Earth due to the fact that a gravity gradient stabilised satellite has two eqltilibrium orientations.
Additionally with spacecraft not controlled by gravity gradient means, and orbiting Earth or other Celestial body, there can be the problem of how to control the attitude of the spacecraft to permit the use of directional communications equipment carried on the spacecraft. Use of omnidirectional communications equipment, which would be required without attitude control, is wasteful of electric power.
Also, with a spacecraft in orbit around Earth or other
Celestial body, if it is desired to use magnetic torques as an adjunct of the control apparatus, there may be a need to reduce the power consumption of on board electromagnets.
There is thus a need for a generally improved apparatus and method for controlling a spacecraft orbiting Earth or other
Celestial attitude body which at least minimises the above noted difficulties and problems and which preferably does so in a simple, cheap and reliable manner.
According to a first aspect of the present invention there is provided apparatus for controlling attitude of a spacecraft orbiting Earth or other Celestial body, including primary magnet means mountable on the spacecraft for motion relative thereto under the influence of the magnetic field of the Earth or other celestial body, energy dissipating means locatable on the spacecraft and operable to bring motion of the spacecraft substantially into equality with that of the primary magnet means, thereby to damp down rotation of the spacecraft, and means for biasing the primary magnet means towards a desired orientation with respect to the spacecraft, thereby to control the attitude of the spacecraft.
Preferably the primary magnet means is substantially rod-like in shape, substantially spherical in shape or substantially angular in shape so as to have salient edges andlor salient vertices.
Conveniently the primary magnet means is a substantially spherical magnet, or a magnet in a substantially spherical casing, mounted for rotation about any axis, relative to the spacecraft.
Advantageously the energy dissipating means is operable by solid state friction, fluid viscosity or electromagnetically induceable eddy currents.
Preferably the apparatus includes a housing surrounding the primary magnet means at a spacing therefrom, with the viscous fluid being contained in the housing at least partially around the primary magnet means, which housing is fixedly securable to the spacecraft.
Conveniently the means for biasing the primary magnet means is variably operable to vary the desired orientation of the primary magnet means and thereby exert a control torque on the spacecraft by interaction between the primary magnet means and the magnetic field.
Advantageously the biasing means includes least one secondary magnet means fixedly attachable to the spacecraft and operable to bias the primary magnet means orientation.
According to a second aspect of the present invention there is provided a spacecraft including an apparatus as aforesaid, operable such that the desired orientation is substantially constant relative to the spacecraft and with the attitude of the spacecraft being controlled by interaction of the apparatus with the magnetic field of the Earth or other Celestial body.
Preferably the spacecraft includes a deployable boom member which is extensible or retractable along an axis which is substantially parallel or antiparallel to the desired orientation.
Conveniently, the spacecraft is placed in the desired initial attitude by the primary magnet means following the magnetic field of the Earth or other Celestial body and the energy dissipating means dragging the spacecraft to follow the primary magnet means, the biasing means operates on the primary magnet means to ensure that the primary magnet means and the spacecraft come to relative rest in a desired attitude, and whereafter the boom member is deployed at a time when its orientation is calculable to be approximately vertical.
For a better understanding of the present invention, and to show how the same may be carried into effect, reference will now be made, by way of example, to the accompanying drawings, in which Figure 1 is a diagrammatic view of a spacecraft incorporating apparatus according to a first embodiment of the invention, with an optional modification being shown in dotted lines,
Figure 2 is a diagrammatic plan view of an alternative form of secondary magnet means in the form of a solenoid for use with the apparatus of the invention shown in Figure 1, and
Figure 3 is an end view of the solenoid and primary magnet means of Figure 2.
Basically, the present invention provides apparatus for controlling attitude of a spacecraft orbiting Earth or other
Celestial body such as a gravity gradient stabilised satellite orbiting Earth. The apparatus includes, as shown in the embodiment of Figure 1, primary magnet means mountable on a spacecraft 1 for motion relative thereto under the influence of the magnetic field of the Earth or other Celestial body, whose direction is shown by the arrow A in Figure 1, into line with the magnetic field. Also forming part of the apparatus is energy dissipating means locatable on the spacecraft 1 and operable to bring motion of the spacecraft substantially into equality with that of the primary magnet means so as to damp down rotation of the spacecraft.Means are provided, as will be later described in detail, for biasing the primary magnet means towards a desired orientation with respect to the spacecraft 1 thereby to control the attitude of the spacecraft 1.
The primary magnet means may be mountable so as to be capable of adopting any orientation relative to the spacecraft 1, or so as to be constrained for rotation about an axis fixed in relation to the spacecraft 1. The primary magnet means may be made of carbon steel or samarium cobalt material and may be substantially rod-like in shape, substantially spherical in shape or substantially angular in shape so as to have salient edges and I or salient vertices. According to the embodiment of Figure 1 the primary magnet means is a substantially spherical permanent magnet 2 in the form of a carbon steel ball mounted for rotation about any axis, relative to the spacecraft 1.
Alternatively, but not shown, the magnet 2 could be of any shape housed in a substantially spherical casing. A preferred primary magnet 2 is a fully magnetised (10000 Gauss) steel ball having a radius of 10mum and a mass of 30g. This is suitable for a spacecraft whose inertias are not more that 5kgm2 and whose assumed release condition is 0.5 revsXmin The maximum torque
To on the magnet 2 will occur if it is placed at a right angle to the Earth's magnetic field. Thus, when the magnet 2 is misaligned from the Earth's field by an angle e, the restoring torque is
To Sin e - - - - - (1)
Conveniently Sin e is approximately equal to 0.5, when the spacecraft 1 has its maximum rotation rate.This allows the magnet 2 to retain Earth locked orientation throughout the process of damping out the rotation imparted to the spacecraft on release from a launch vehicle. Rotation of the spacecraft is not intentional, but can stem from unintentional rotation imparted on release from the launch vehicle.
The apparatus of the invention also includes energy dissipating means operable by solid state friction, fluid viscosity or electro magnetimlly induceable eddy currents. The primary permanent magnet 2 is in effect driven by the Earth's magnetic field and gradually drags the spacecraft 1 with it into line with the Earth's magnetic field direction A, via the energy dissipating means. In the embodiment of Figure 1, the energy dissipating means is operable by fluid viscosity of a liquid at least partially surrounding the magnet 2. To this end a housing 3 is provided, which surrounds the primary magnet 2 at a spacing 4 therefrom, with the viscous fluid being contained in the housing 3 at least partially around the magnet 2. The housing 3 is fixedly secured to the spacecraft 1 to move therewith.The housing 3 can have any convenient shape, but in the embodiment of Figure 1, the housing 3 is substantially spherical in shape to define a substantially spherical internal cavity 3a for housing the magnet 2 and viscous liquid. Assuming a spacing 4 of 1 millimetre, a suitable viscosity value is about 70 poise and the preferred viscous liquid is a polydimethyl siloxane having this value of viscosity.
Means may be provided for preventing the creation of excessive viscous drag or solid state friction between the freely moveable magnet 2 and its housing 3 via the viscous liquid in the spacing 4.
Thus, the substantially spherically shaped magnet 2 may be provided with a plurality of substantially rigid or elastic projections extending from the outer surface of the magnet 2 to ensure that a desired spacing between the magnet 2 and the housing 3 is maintained and thereby prevent the creation of excessive viscous drag between the magnet 2 and the housing 3.
As an alternative, the plurality of substantially rigid or elastic projections may be provided on the inner surface of the substantially spherical inner cavity 3a, to extend inwardly therefrom, again to ensure that a desired spacing 4 between the magnet 2 and the housing 3 is maintained, to prevent the creation of excessive viscous drag. Preferably the magnet 2 or the housing 3 has six such projections, located where desired, although any other number of such projections could be used if desired. The projection ensure concentricity of the magnet 2 and the housing 3 when the spacecraft 1 is on station and these should be, sufficiently flexible or elastic not to break during the launch of the spacecraft into orbit. Preferably, the projections should have a low friction surface.
As aforesaid, means are provided for biasing the primary permanent magnet 2 towards a desired orientation with respect to the spacecraft 1. Consequently, such means operate so that when the magnet 2 and spacecraft 1 come to relative rest, the attitude of the spacecraft is determined by the biasing means.
The preferred desired orientation is substantially constant relative to the spacecraft.
The biasing means may include a spring housed in a shaped container and engaging the primary permanent magnet 2.
Alternatively, the biasing means may include at least one secondary magnet means fixedly attachable to the spacecraft 1 and operable to bias the primary permanent magnet 2 orientation.
Conveniently, the at least one secondary magnet means is a permanent magnet or an electro-magnet.
In the embodiment of Figure 1, the at least one secondary magnet means is a pair of secondary permanent magnets 5. In the Figure 1 embodiment, these secondary magnets 5 are substantially disc or rod-like in shape and are located diametrically opposite one another with their poles opposed, one on either side of the housing 3 so as to create a magnetic field which is substantially parallel to the direction B which is fixed in relation to the spacecraft. After successful operation of the apparatus of the invention, the direction B is approximately coincident with the direction A of the Earth's magnetic field.
The strength of the magnets 5 should be less than that of the magnet 2, for example such as to generate a field about one tenth the Earths magnetic field at the north and south poles, so as to bias the magnet 2 towards a preferred orientation. Whilst generally the secondary magnets 5 are fixed in position relative to the spacecraft 1, at least one of the magnets 5 could alternatively be made rotatable through 1800 with respect to the other secondary magnet 5 so as to vary the net field of the secondary magnets 5 between a maximum value and a zero value in the vicinity of the primary magnet 2.This is intended to reduce or eliminate the biasing effect torque on the permanent magnet 2 when the spacecraft 1 is on station and thereby minimise production of any disturbances, such as pitch librations which would otherwise produce oscillations both along-track and across the track of the spacecraft 1.
Alternatively, the secondary magnets 5 may be mounted in gimbals which are lockable in position when desired, such as in the acquisition phase. A further alternative, as illustrated in
Figures 2 and 3, is to make the at least one secondary magnet means in the form of an electromagnet conveniently in the shape of at least one solenoid 6 suppliable with electric current controllable to produce a magnetic field substantially constant in strength and direction. The solenoid 6 is an open ended cylinder located around the primary magnet housing 3, as shown in Figures 2 and 3. The electromagnetic solenoid 6 can be rendered inactive, by switching off its driving electric current, when the satellite 1 is on station. Conveniently the solenoid 6 may be wound with turns 7 of aluminum wire.
Also shown in the embodiment of Figure 1 in dotted lines is a retractable and extensible boom member 8. With a gravity-gradient spacecraft 1, the spacecraft 1 is placed in the desired initial attitude by the primary magnet means following the magnetic field of the Earth and the energy dissipating means dragging the spacecraft to follow the primary magnet means.
The secondary magnet means may be used to acquire the right-way-up attitude for the spacecraft and the boom 8 then extended, at a time when its orientation is calculable to be approximately vertical, to ensure that the gravity gradient maintains the right-way-up attitude. This boom member 8 is extensible or retractable approximately parallel or antiparallel to the axis B. Thus the orientation of the magnetic moment of the secondary magnets 5 is towards the face thereof which will be
Earth pointing in the gravity-gradient mode.
The boom member 8 may be of any convenient form such as having telescopic portions, having portions hingedly connected to one another or preferably in the form of a flexible tape stiffened by preformation of its cross-section and capable of being wound from or onto a rotatable reel. Whatever its construction the member 8 is capable of moving between a collapsed or retracted position and an extended elongated position. The boom member 8 may be extended in response to a telecommand such as when the spacecraft 1 passes close to the geographic North Pole of the
Earth, so as to extend away from Earth.
It is necessary during acquisition, when gravity-gradient torques are small, before extension of the boom member 8, that the torques arising from the secondary magnets 5 should exceed the gravity gradient torque so that the upside down oonfiguration is unstable when the gravity gradient torques are included.
The apparatus of the present invention, can be used in a configuration such that the desired or preferred orientation of the primary magnet 2 in relation to the principal axes of the spacecraft or satellite 1, is selected so as to cause nutational motion or oscillatory rotation, of the spacem9ft 1 as it travels, on station, around its orbit, and thereby avoid localised overheating of the spacecraft by solar radiation.
It is also possible that the apparatus of the invention may be used as the sole means of attitude control of a spacecraft, thus allowing economies of design with respect to attitude control while at the same time permitting the use of directional communications equipment on the spacecraft for communication with the Earth.
Alternatively, the apparatus of the invention may be used as part of a more elaborate attitude control system in which the said apparatus serves to provide control torques which are controllably variable by the interaction of the primary magnet with the Earth's magnetic field. With this aspect of the invention, the means of biasing the primary magnet would be operable to vary the desired orientation of the primary magnet from time to time, thereby controllably to vary the torque arising from the interaction. In this instance, the biasing means may be such as to create a magnet field which is controllably variable in direction the field strength of which may exceed that of the Earth. The spacecraft may carry other torque actuators and for example it may be possible to use the apparatus also to desaturate one or more momentum wheels.
Claims (31)
1. Apparatus for controlling attitude of a spacecraft orbiting
Earth or other celestial body, including primary magnet means mountable on the spacecraft for motion relative thereto under the influence of the magnetic field of the Earth or other celestial body, energy dissipating means locatable on the spacecraft and operable to bring motion of the spacecraft substantially into equality with that of the primary magnet means, thereby to damp down rotation of the spacecraft, and means for biasing the primary magnet means towards a desired orientation with respect to the spacecraft thereby to control the attitude of the spacecraft.
2. Apparatus according to Claim 1, wherein the primary magnet means is mountable so as to be capable of adopting any orientation relative to the spacecraft or so as to be constrained for rotation about an axis fixed in relation to the spacecraft.
3. Apparatus according to Claim 2, wherein the primary magnet means is made of carbon steel or samarium cobalt material.
4. Apparatus according to any one of Claims 1 to 3, wherein the primary magnet means is substantially rod-like in shape, substantially spherical in shape or substantially angular in shape so as to have salient edges andlor salient vertices.
5. Apparatus according to Claim 4, wherein the primary magnet means is a substantially spherical magnet, or magnet in a substantially spherical casing, mounted for rotation about any axis, relative to the spacecraft.
6. Apparatus according to any one of Claims 1 to 5, wherein the energy dissipating means is operable by solid state friction, fluid viscosity or electromagnetically induceable eddy currents.
7. Apparatus according to Claim 6, wherein the energy dissipating means is operable by fluid viscosity of a liquid at least partially surrounding the substantially spherical magnet or casing.
8. Apparatus according to Claim 7, including a housing surrounding the primary magnet means at a spacing therefrom, with the viscous liquid being contained in the housing at least partially around the primary magnet means, which housing is fixedly securable to the spacecraft.
9. Apparatus according to Claim 8, wherein the housing is shaped to define a substantially spherical internal cavity for housing the primary magnet means and viscous liquid.
10. Apparatus according to Claim 9, wherein the viscous liquid is a polydimethyl siloxane.
11. Apparatus according to Claim 9 or Claim 10, wherein the primary magnet means substantially spherical magnet or casing is provided with a plurality of substantially rigid or elastic projections extending from the outer surface of the magnet or casing to ensure that a desired spacing between the magnet or casing and housing is maintained to prevent the creation of excessive viscous drag.
12. Apparatus according to Claim 9 or Claim 10, wherein the substantially spherical inner cavity of the housing is provided with a plurality of substantially rigid or elastic projections extending inwardly therefrom to ensure that a desired spacing between the substantially spherical magnet and housing is maintained to prevent the creation of excessive viscous drag.
13. Apparatus according to Claim 11 or Claim 12, including six said projections.
14. Apparatus according to Claim 1, wherein the means for biasing the primary magnet means is variably operable to vary the desired orientation of the primary magnet means and thereby exert a control torque on the spacecraft by interaction between the primary magnet means and the magnetic field.
15. Apparatus according to Claim 1, wherein the means for biasing the primary magnet means includes a spring housed in a shaped container and engaging the primary magnet means.
16. Apparatus according to Claim 1 or Claim 14, wherein the biasing means includes at least one secondary magnet means fixedly attachable to the spacecraft and operable to bias the primary magnet means orientation.
17. Apparatus according to Claim 16, wherein the at least one secondary magnet means is a permanent magnet or an electromagnet.
18. Apparatus according to Claim 17, wherein the at least one secondary magnet means is an electromagnet in the form of at least one solenoid suppliable with electric current controllable to produce a magnetic field substantially constant in strength and direction.
19. Apparatus according to claim 18, wherein the or each solenoid is an open ended cylinder fitted around the substantially spherical housing, with the electrical current to the solenoid being switchable on or off as desired.
20. Apparatus according to Claim 17, wherein the at least one secondary magnet means is a pair of secondary permanent magnets.
21. Apparatus according to Claim 20, wherein at least one of the secondary magnets is rotatable through substantially 1800 to the other secondary magnet so as to vary the net field of the secondary magnets between a maximum value and a zero value in the vicinity of the primary magnet.
22. Apparatus according to Claim 20, wherein both secondary magnets are mounted in gimbals which are lockable in position when desired.
23. Apparatus for controlling attitude of a spacecraft orbiting
Earth or other celestial body, substantially as hereinbefore described and as illustrated in Figure 1 or Figures 2 and 3 of the accompanying drawings.
24. A spacecraft including an apparatus according to any one of
Claims 1 to 13, 15 to 18, and 20 to 23, operable such that the desired orientation is substantially constant relative to the spacecraft and with the attitude of the spacecraft being controlled by interaction of the apparatus with the magnetic field of the Earth or other Celestial body.
25. A spacecraft according to Claim 24, including directional communications equipment.
26. A spacecraft according to Claim 24 or Claim 25, including a deployable boom member which is extensible or retractable along an axis which is substantially parallel or antiparallel to the desired orientation.
27. A spacecraft substantially as hereinbefore described and as illustrated in Figure 1 of the accompanying drawings.
28. A method of controlling attitude of a spacecraft according to
Claim 26, in which the spacecraft. is placed in the desired initial attitude by the primary magnet means following the magnetic field of the Earth or other Celestial body and the energy dissipating means dragging the spacecraft to follow the primary magnet means, the biasing means operates on the primary magnet means to ensure that the primary magnet means and the spacecraft come to relative rest in a desired attitude, and whereafter the boom member is deployed at a time when its orientation is calculated to be approximately vertical.
29. A method according to Claim 28, in which the biasing means is deactivated when the spacecraft attitude is as desired on station, to avoid on station attitude disturbances.
30. A method of controlling attitude of a spacecraft according to any one of Claims 24 to 27, in which the desired orientation is chosen in relation to the principal axes of inertia of the spacecraft so as to cause oscillatory rotation or nutation of the spacecraft, as it travels around its orbit, to avoid localised overheating of the spacecraft by solar radiation.
31. A method of controlling attitude of a spacecraft orbiting
Earth or other Celestial body, substantially as hereinbefore described.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB9004472A GB2241480B (en) | 1990-02-28 | 1990-02-28 | Apparatus and method for controlling attitude of a spacecraft orbiting earth or other celestial body |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB9004472A GB2241480B (en) | 1990-02-28 | 1990-02-28 | Apparatus and method for controlling attitude of a spacecraft orbiting earth or other celestial body |
Publications (3)
| Publication Number | Publication Date |
|---|---|
| GB9004472D0 GB9004472D0 (en) | 1990-04-25 |
| GB2241480A true GB2241480A (en) | 1991-09-04 |
| GB2241480B GB2241480B (en) | 1993-05-26 |
Family
ID=10671741
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB9004472A Expired - Fee Related GB2241480B (en) | 1990-02-28 | 1990-02-28 | Apparatus and method for controlling attitude of a spacecraft orbiting earth or other celestial body |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB2241480B (en) |
Cited By (3)
| 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 |
| WO2011061729A1 (en) | 2009-11-17 | 2011-05-26 | Stenenko, Maria | Method of overcoming gravity and a flight vehicle for the implementation thereof |
| FR3058393A1 (en) * | 2016-11-10 | 2018-05-11 | Airbus Defence And Space Sas | SPACE ENGINE COMPRISING MEANS OF ATTITUDE ACTIVE MONITORING AND PASSIVE ATTITUDE CONTROL MEANS |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3765621A (en) * | 1970-07-29 | 1973-10-16 | Tokyo Shibaura Electric Co | System of controlling the attitude of a spinning satellite in earth orbits |
| US3834653A (en) * | 1972-03-27 | 1974-09-10 | Rca Corp | Closed loop roll and yaw control for satellites |
| US4034941A (en) * | 1975-12-23 | 1977-07-12 | International Telephone And Telegraph Corporation | Magnetic orientation and damping device for space vehicles |
| US4084773A (en) * | 1975-09-15 | 1978-04-18 | Rca Corporation | Magnetic control of spacecraft roll disturbance torques |
| GB2121984A (en) * | 1982-04-20 | 1984-01-04 | Messerschmitt Boelkow Blohm | Method of and equipment for adjusting the position of an earth satellite |
-
1990
- 1990-02-28 GB GB9004472A patent/GB2241480B/en not_active Expired - Fee Related
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3765621A (en) * | 1970-07-29 | 1973-10-16 | Tokyo Shibaura Electric Co | System of controlling the attitude of a spinning satellite in earth orbits |
| US3834653A (en) * | 1972-03-27 | 1974-09-10 | Rca Corp | Closed loop roll and yaw control for satellites |
| US4084773A (en) * | 1975-09-15 | 1978-04-18 | Rca Corporation | Magnetic control of spacecraft roll disturbance torques |
| US4034941A (en) * | 1975-12-23 | 1977-07-12 | International Telephone And Telegraph Corporation | Magnetic orientation and damping device for space vehicles |
| GB2121984A (en) * | 1982-04-20 | 1984-01-04 | Messerschmitt Boelkow Blohm | Method of and equipment for adjusting the position of an earth satellite |
Cited By (6)
| 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 |
| WO2011061729A1 (en) | 2009-11-17 | 2011-05-26 | Stenenko, Maria | Method of overcoming gravity and a flight vehicle for the implementation thereof |
| FR3058393A1 (en) * | 2016-11-10 | 2018-05-11 | Airbus Defence And Space Sas | SPACE ENGINE COMPRISING MEANS OF ATTITUDE ACTIVE MONITORING AND PASSIVE ATTITUDE CONTROL MEANS |
| WO2018087273A1 (en) * | 2016-11-10 | 2018-05-17 | Airbus Defence And Space Sas | Spacecraft comprising active attitude control means and passive attitude control means |
| EP3696096A1 (en) * | 2016-11-10 | 2020-08-19 | Airbus Defence and Space SAS | Spacecraft comprising active attitude control means and passive attitude control means |
| US10773832B2 (en) | 2016-11-10 | 2020-09-15 | Airbus Defence And Space Sas | Projectile intended for damping a spacecraft and corresponding space delivery vehicle |
Also Published As
| Publication number | Publication date |
|---|---|
| GB2241480B (en) | 1993-05-26 |
| GB9004472D0 (en) | 1990-04-25 |
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Effective date: 19940228 |