CA1262890A - Shading device for use in a geostatic satellite - Google Patents
Shading device for use in a geostatic satelliteInfo
- Publication number
- CA1262890A CA1262890A CA000459044A CA459044A CA1262890A CA 1262890 A CA1262890 A CA 1262890A CA 000459044 A CA000459044 A CA 000459044A CA 459044 A CA459044 A CA 459044A CA 1262890 A CA1262890 A CA 1262890A
- Authority
- CA
- Canada
- Prior art keywords
- axis
- rotation
- satellite
- shading plate
- paddle member
- 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
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
- B64G1/52—Protection, safety or emergency devices; Survival aids
- B64G1/58—Thermal protection, e.g. heat shields
-
- 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
- B64G1/46—Arrangements or adaptations of devices for control of environment or living conditions
Abstract
Abstract of the Disclosure A shading device is for use in a geostatic satellite having an axis of rotation parallel to the axis of the earth and comprising a paddle member in addition to a spinning drum rotated around the axis of rotation and furthermore to a despun platform held substantially stationary relative to the axis of the earth.
The paddle member is loaded with solar cells and rotated around the axis of rotation to direct the solar cells towards a line which is parallel to the sunbeam. The shading device comprising a shading plate for shading a part of despun platform from the sun-beam and rotated around the axis of rotation in synchronism with the paddle member.
The paddle member is loaded with solar cells and rotated around the axis of rotation to direct the solar cells towards a line which is parallel to the sunbeam. The shading device comprising a shading plate for shading a part of despun platform from the sun-beam and rotated around the axis of rotation in synchronism with the paddle member.
Description
~æ6~9~
Background of_the Invention:
This inve~tion relates to a shading device for use in combination with a geostatic satelliteO
A geostatic or geostationary satellite is usually used as a communication or a broadcasting satellite and classified into a body stabili~ed type and a spin stabilized type. The spin stabilized geostatic satellite comprises a spinning drum and a despun platEorm. The geostatic satellite to which this invention is applicable, furthermore comprises a paddle member for supporting a plurality of solar cells. The despun p~atform carries at least one antenna and is kept substantiall~ stationary relative to the axis of the earth. A part of the despun platform is therefore heated to a high temperature by sunlight in the day-time. The space in which the geostatic satellite revolves around the earth in synchronism with the rotation of the earth, is at a temperature of about 10R. A severe temperature distribution therefore appears on the surface of the despun platform and results in an objectionable temperature distribution inside the despun plat~orm.
Various electric circuits are mounted inside the despun platform. It is important that the electrical circuits are kept within a moderate temperature range so as to be normally operable.
Therefore, it is necessary to control the temperature distribution as uniformly as possible.
Summary of the Invention:
It is therefore an object of the present invention to provide a shading device which is capable of shading a despun ~262~39~
platform of a geostatic satellite from the sunlight.
It is another object of this invantion to provide a shading device by which the temperature distrlbutton is readily controlled in the despun platform.
Accord1ng to the present Lnvention, there is provided a geostatic satelllte having an axis of rotation and comprlsing: a spinning drum arranged to rotate around said axis of rotation; a despun plat~orm which is arranged to be held substantially s~ationary relative to the axls of the earth by counter rotation relative to said spinning drum; a paddla member loaded with solar cells and arranged to rotate around said axls of rotation to direct said solar cells towards a line which is parallel to light rays from the sun, said paddle member being attached to said despun platform; a shading plate for shading a part of said despun platform from the light rays from the sun, said shading plate being connected to said paddle member so that said shading plate is movable together with said paddle mamber to shade said part of the despun platform from the sunbeam; and rotating means for rotating said paddle member and said shading plate in synchronism around said axis of rotation.
Brief Description of the Drawina:
Figure l shows a perspective view oi a geostatic satellite which comprises a shading device according to an embodiment of this invention;
Figure 2 shows a top view of the geostatic satellite;
and z~9~
Flgure 3 schematically shows the geostatic satelli~e together with electrical circuits and mechanical parts mounted on the satellite~
Description of the Preferred Embodiments:
Referring to Figure 1, a geostatic satellite will be .
described at first in order to facilitate an understanding of the present invention. The satellite is a triple-spin stabilized satellite, which will later become clear. The illustrated satel~
lite has a despun platform 11, a spinning drum 12, and a paddle member 13. Each of the spinning drum 12 and the despun platform 11 is cylindrical. The paddle member 13 comprises a pair of solar cell paddles 13a and 13b stretched on both sides of the despun platform 11.
The despun platform 11 provides a first surface of the satellite directed upwards of this figure. The first surface is directed to the north. The despun platform 11 carries a pair of large parabolic reflectors 14 and 15 and a pair of primary horns 16 and 17 in one-to-one correspondence to the parabolic reflectors 14 and 15. A small parabolic reflector 18 is also carried on the despun platform 11 so as to be operable in cooperation with another primary horn 19. An omnidirectional antenna 20 is extended between the large parabolic reflectors 14 and 15. The spinning drum 12 provides a second surface of the satellite opposite to the first surface and directed downwards of this figure. The second surface is directed to the south. An apogee-motor nozzle ~not shown) is attached to the second surface.
The solar cell paddles 13a and 13b support a great number of solar cells for supplying electric power to elements of the satellite which will later be exemplified. At any rate, no superfluous space remains on the first and the second surfaces and, therefore, no additional external element can be mounted on the first and the second surfaces. The paddle member 13 is inevi-8~
tably attached to a cylindrical surface between the first and thesecond surfaces, as shown in Figure 1.
Such solar cells may be attached to a despun platform when a satellite consumes only a small amount of electric power.
However, the solar cell paddles 13a and 13b are indispensable to a satellite, such as a broadcasting satellite, a communication satellite, or the like, which consumes a large amount of electric power. Use of the solar cell paddles 13a and 13b makes it diffi-cult to attach the solar cells to the despun platform, as suggested from Figure 1.
Referring to Figure 2 in addition to Figure 1, the satellite has a pitch or spin axis 101 extended between the first and the second surfaces, a roll axis 102 orthogonal to the spin axis 101, and a yaw axis l03 orthogonal to both of the spin and the roll axes 101 and 102. The satellite is stabilized with respect to the three axes 101 to 103. The pitch axis 101 will presently be described more in detail. The roll axis 102 is defined by the geostationary orbit of the satellite. The ya~ axis 103 is an axis along which the satellite moves nearer to and farther from the earth. Incidentally, an arrow 104 shows the sunbeam.
The spinning drum 12 is rotated around the pitch axis 101. The pitch axis 101 therefore serves as an axis of rotation ~nd is stabilized so as to be parallel to the axis of the earth when the satellite is placed in the geostationary orbit. The attitude of the satellite is stably held relative to the earth by spinning the spinning drum 12.
The despun platform 11 is held substantially stationary relative to the axis of the earth by counter rotation relative to the spinning drum 12. Therefore, the despun platform 11 makes one rotation a day relative to the sun. As a result, electromagnetic beams which are radiated from the parabolic reflectors 14 and 15 and the parabolic reflector 18 are always directed towards a pre-determined point of the earth. The direction of the electromag-netic beams is towards a desired position on the earth.
The solar cell paddles 13a and 13b are synchronously rotated around the pitch axis 101. The solar cell paddles 13a and 13b are rotated around the pitch axis l01 in the direction of an arrow 105. As a result, the surfaces of the solar cells are directed to the full light from the sun represented by sunbeam 104.
As will be understood by the above description, the despun platform 11 is locally exposed to the sunbeam 104 always in the daytime. Therefore, the temperature distribution of the despun platform 11 becomes very uneven. On the other hand, the spinning drum 12 has a uniform temperature distribution because of spinning of the spinning drum 12 itself.
As shown in Figures 1 and 2, a shading device according to this invention is used in combination with the geostatic satel-lite. The shading device comprises a shading plate 21 and a rotating device therefor. The shading plate 21 comprises at least one member of a material having a high reflecting factor. The shading plate 21 is not narrower in area than a half of the despun platform 11. For example, a surface of the shading plate 21 is semi-cylindrical in shape. One end of the shading plate 21 is attached to one of the solar cell paddles 13a and 13b. The other end of the shading plate 21 is fixed to the other of the solar cell paddles l3a and 13b. Therefore, the shading plate 21 is rotated in synchronism with the rotation of the solar cell paddles 13a and 13b. As the solar cell paddles 13a and 13b are rotated so as to direct the surface of solar cells to the sunbeam 104, the shading plate 21 always shades the sunbeam 10~ incident on the surface of the despun platform 11. Therefore, the shading plate 21 is coupled to the solar cell paddles 13a and 13b through connections therebetween. The connections are operable to rotate the shading plate 21 and may therefore be called the rotating device.
Referring to Figure 3, a communication satellite will briefly be described. The despun platform 11 comprises a tele-metry transmitter 22, a command receiver 23, a repeater 24 in the manner known in the art. A despun platform dynamics 25 is for counterrotating the despun platform 11 relative to the spinning drum 12. The spinning drum 12 comprises a control system 26 as will later be described in detail. A spinning drum dynamics 27 is for rotating the spinning drum 12. The telemetry transmitter 22, the command receiver 23, and the repeater 24 are communicable with the earth in the usual manner through an antenna portion 28 comprising various antennas illustrated in Figure 1. The control system 26 is connected with the telemetry transmitter 22, the command receiver 23, the repeater 24, and the despun platform dynamics 25 to control them in the usual manner. The control 3~
system 26 is connectecl to a sensor portion 29 described later.
The control system 26 also controls a thermal control subsystem 3~, the spinning drum dynamics 27, and the paddle member 13.
The thermal control subsystem 30 comprises a part oper-able for the despun platform 11 and another part for the spinning drum 12. Anyway, the thermal control subsystem 30 lends itself to control the despun platform 11 and the spinning drum 12. Although not depicted in detail, each part of the thermal control subsystem 30 consists of passive members and an active member. The passive members may be, for e~ample, a member or members of a high reflec-tion factor material or an insulating material each of which is coated on the surfaces of the despun platform 11 and the spinning drum 12. The active member may be, for example, electrical heaters, heat pipes, and so on known in the art. The active member is controlled by the co~trol system 26. The sensor portion 29 comprises sensors for observing positions of the celestial bodies, such as the sun and the earthO
The operation will briefly be described hereinafter.
Communication signals are received from terrestrial stations at the antenna portion 28 for supply to the repeater 24 and are sent back to the terrestrial stations through the antenna portion 28 after amplification. On the other hand, commands are delivered from the terrestrial stations to the command receiver 23 through the antenna portion 28 to be sent to the control system 26. Responsive to the commands, the control system 26 controls the attitude of the satellite by driving the despun platform dynamics 25 and the spinning drum dynamics 27. The temperature of the satellite is watchecl by the control system 26. The control system 26 produces a status signal specifying status of the satel-lite. The status signal is sent from the control system 26 to the telemetry transmitter 22 to be delivered to the terrestrial stations through the antenna portion 28.
The control system 26 controls the rotation of the paddle member 13 as mentioned above. The shading device depicted at 31 in Figure 3 rotates in synchronism with the rotation of the paddle member 13. The shading device 31 can shade the despun platform 11 from the sunbeam in the daytime by the use of the shading plate 21 (Figures 1 and 2). Therefore, the shading device 31 serves a portion oE the thermal control subsystem 30.
As will be understood by the above description, the shading device shades the sunbeam always in the daytime. There-fore, the temperature distribution becomes uniform on the whole of the despun plat~orm 11. In other words, the despun platform 11 is always kept in a substantial thermal equilibrium. This means that various sorts of internal elements can be housed in the despun platform 11. Therefore, the thermal control subsystem can readily be designed with the illustrated structure.
While this invention has thus far been described in conjunction with an embodiment thereof, it will readily be possible for those skilled in the art to put this invention into practice in various other manners. This invention is applicable to rotate the shading plate in synchronism with a paddle member without the connection between the shading plate and the paddle member.
Background of_the Invention:
This inve~tion relates to a shading device for use in combination with a geostatic satelliteO
A geostatic or geostationary satellite is usually used as a communication or a broadcasting satellite and classified into a body stabili~ed type and a spin stabilized type. The spin stabilized geostatic satellite comprises a spinning drum and a despun platEorm. The geostatic satellite to which this invention is applicable, furthermore comprises a paddle member for supporting a plurality of solar cells. The despun p~atform carries at least one antenna and is kept substantiall~ stationary relative to the axis of the earth. A part of the despun platform is therefore heated to a high temperature by sunlight in the day-time. The space in which the geostatic satellite revolves around the earth in synchronism with the rotation of the earth, is at a temperature of about 10R. A severe temperature distribution therefore appears on the surface of the despun platform and results in an objectionable temperature distribution inside the despun plat~orm.
Various electric circuits are mounted inside the despun platform. It is important that the electrical circuits are kept within a moderate temperature range so as to be normally operable.
Therefore, it is necessary to control the temperature distribution as uniformly as possible.
Summary of the Invention:
It is therefore an object of the present invention to provide a shading device which is capable of shading a despun ~262~39~
platform of a geostatic satellite from the sunlight.
It is another object of this invantion to provide a shading device by which the temperature distrlbutton is readily controlled in the despun platform.
Accord1ng to the present Lnvention, there is provided a geostatic satelllte having an axis of rotation and comprlsing: a spinning drum arranged to rotate around said axis of rotation; a despun plat~orm which is arranged to be held substantially s~ationary relative to the axls of the earth by counter rotation relative to said spinning drum; a paddla member loaded with solar cells and arranged to rotate around said axls of rotation to direct said solar cells towards a line which is parallel to light rays from the sun, said paddle member being attached to said despun platform; a shading plate for shading a part of said despun platform from the light rays from the sun, said shading plate being connected to said paddle member so that said shading plate is movable together with said paddle mamber to shade said part of the despun platform from the sunbeam; and rotating means for rotating said paddle member and said shading plate in synchronism around said axis of rotation.
Brief Description of the Drawina:
Figure l shows a perspective view oi a geostatic satellite which comprises a shading device according to an embodiment of this invention;
Figure 2 shows a top view of the geostatic satellite;
and z~9~
Flgure 3 schematically shows the geostatic satelli~e together with electrical circuits and mechanical parts mounted on the satellite~
Description of the Preferred Embodiments:
Referring to Figure 1, a geostatic satellite will be .
described at first in order to facilitate an understanding of the present invention. The satellite is a triple-spin stabilized satellite, which will later become clear. The illustrated satel~
lite has a despun platform 11, a spinning drum 12, and a paddle member 13. Each of the spinning drum 12 and the despun platform 11 is cylindrical. The paddle member 13 comprises a pair of solar cell paddles 13a and 13b stretched on both sides of the despun platform 11.
The despun platform 11 provides a first surface of the satellite directed upwards of this figure. The first surface is directed to the north. The despun platform 11 carries a pair of large parabolic reflectors 14 and 15 and a pair of primary horns 16 and 17 in one-to-one correspondence to the parabolic reflectors 14 and 15. A small parabolic reflector 18 is also carried on the despun platform 11 so as to be operable in cooperation with another primary horn 19. An omnidirectional antenna 20 is extended between the large parabolic reflectors 14 and 15. The spinning drum 12 provides a second surface of the satellite opposite to the first surface and directed downwards of this figure. The second surface is directed to the south. An apogee-motor nozzle ~not shown) is attached to the second surface.
The solar cell paddles 13a and 13b support a great number of solar cells for supplying electric power to elements of the satellite which will later be exemplified. At any rate, no superfluous space remains on the first and the second surfaces and, therefore, no additional external element can be mounted on the first and the second surfaces. The paddle member 13 is inevi-8~
tably attached to a cylindrical surface between the first and thesecond surfaces, as shown in Figure 1.
Such solar cells may be attached to a despun platform when a satellite consumes only a small amount of electric power.
However, the solar cell paddles 13a and 13b are indispensable to a satellite, such as a broadcasting satellite, a communication satellite, or the like, which consumes a large amount of electric power. Use of the solar cell paddles 13a and 13b makes it diffi-cult to attach the solar cells to the despun platform, as suggested from Figure 1.
Referring to Figure 2 in addition to Figure 1, the satellite has a pitch or spin axis 101 extended between the first and the second surfaces, a roll axis 102 orthogonal to the spin axis 101, and a yaw axis l03 orthogonal to both of the spin and the roll axes 101 and 102. The satellite is stabilized with respect to the three axes 101 to 103. The pitch axis 101 will presently be described more in detail. The roll axis 102 is defined by the geostationary orbit of the satellite. The ya~ axis 103 is an axis along which the satellite moves nearer to and farther from the earth. Incidentally, an arrow 104 shows the sunbeam.
The spinning drum 12 is rotated around the pitch axis 101. The pitch axis 101 therefore serves as an axis of rotation ~nd is stabilized so as to be parallel to the axis of the earth when the satellite is placed in the geostationary orbit. The attitude of the satellite is stably held relative to the earth by spinning the spinning drum 12.
The despun platform 11 is held substantially stationary relative to the axis of the earth by counter rotation relative to the spinning drum 12. Therefore, the despun platform 11 makes one rotation a day relative to the sun. As a result, electromagnetic beams which are radiated from the parabolic reflectors 14 and 15 and the parabolic reflector 18 are always directed towards a pre-determined point of the earth. The direction of the electromag-netic beams is towards a desired position on the earth.
The solar cell paddles 13a and 13b are synchronously rotated around the pitch axis 101. The solar cell paddles 13a and 13b are rotated around the pitch axis l01 in the direction of an arrow 105. As a result, the surfaces of the solar cells are directed to the full light from the sun represented by sunbeam 104.
As will be understood by the above description, the despun platform 11 is locally exposed to the sunbeam 104 always in the daytime. Therefore, the temperature distribution of the despun platform 11 becomes very uneven. On the other hand, the spinning drum 12 has a uniform temperature distribution because of spinning of the spinning drum 12 itself.
As shown in Figures 1 and 2, a shading device according to this invention is used in combination with the geostatic satel-lite. The shading device comprises a shading plate 21 and a rotating device therefor. The shading plate 21 comprises at least one member of a material having a high reflecting factor. The shading plate 21 is not narrower in area than a half of the despun platform 11. For example, a surface of the shading plate 21 is semi-cylindrical in shape. One end of the shading plate 21 is attached to one of the solar cell paddles 13a and 13b. The other end of the shading plate 21 is fixed to the other of the solar cell paddles l3a and 13b. Therefore, the shading plate 21 is rotated in synchronism with the rotation of the solar cell paddles 13a and 13b. As the solar cell paddles 13a and 13b are rotated so as to direct the surface of solar cells to the sunbeam 104, the shading plate 21 always shades the sunbeam 10~ incident on the surface of the despun platform 11. Therefore, the shading plate 21 is coupled to the solar cell paddles 13a and 13b through connections therebetween. The connections are operable to rotate the shading plate 21 and may therefore be called the rotating device.
Referring to Figure 3, a communication satellite will briefly be described. The despun platform 11 comprises a tele-metry transmitter 22, a command receiver 23, a repeater 24 in the manner known in the art. A despun platform dynamics 25 is for counterrotating the despun platform 11 relative to the spinning drum 12. The spinning drum 12 comprises a control system 26 as will later be described in detail. A spinning drum dynamics 27 is for rotating the spinning drum 12. The telemetry transmitter 22, the command receiver 23, and the repeater 24 are communicable with the earth in the usual manner through an antenna portion 28 comprising various antennas illustrated in Figure 1. The control system 26 is connected with the telemetry transmitter 22, the command receiver 23, the repeater 24, and the despun platform dynamics 25 to control them in the usual manner. The control 3~
system 26 is connectecl to a sensor portion 29 described later.
The control system 26 also controls a thermal control subsystem 3~, the spinning drum dynamics 27, and the paddle member 13.
The thermal control subsystem 30 comprises a part oper-able for the despun platform 11 and another part for the spinning drum 12. Anyway, the thermal control subsystem 30 lends itself to control the despun platform 11 and the spinning drum 12. Although not depicted in detail, each part of the thermal control subsystem 30 consists of passive members and an active member. The passive members may be, for e~ample, a member or members of a high reflec-tion factor material or an insulating material each of which is coated on the surfaces of the despun platform 11 and the spinning drum 12. The active member may be, for example, electrical heaters, heat pipes, and so on known in the art. The active member is controlled by the co~trol system 26. The sensor portion 29 comprises sensors for observing positions of the celestial bodies, such as the sun and the earthO
The operation will briefly be described hereinafter.
Communication signals are received from terrestrial stations at the antenna portion 28 for supply to the repeater 24 and are sent back to the terrestrial stations through the antenna portion 28 after amplification. On the other hand, commands are delivered from the terrestrial stations to the command receiver 23 through the antenna portion 28 to be sent to the control system 26. Responsive to the commands, the control system 26 controls the attitude of the satellite by driving the despun platform dynamics 25 and the spinning drum dynamics 27. The temperature of the satellite is watchecl by the control system 26. The control system 26 produces a status signal specifying status of the satel-lite. The status signal is sent from the control system 26 to the telemetry transmitter 22 to be delivered to the terrestrial stations through the antenna portion 28.
The control system 26 controls the rotation of the paddle member 13 as mentioned above. The shading device depicted at 31 in Figure 3 rotates in synchronism with the rotation of the paddle member 13. The shading device 31 can shade the despun platform 11 from the sunbeam in the daytime by the use of the shading plate 21 (Figures 1 and 2). Therefore, the shading device 31 serves a portion oE the thermal control subsystem 30.
As will be understood by the above description, the shading device shades the sunbeam always in the daytime. There-fore, the temperature distribution becomes uniform on the whole of the despun plat~orm 11. In other words, the despun platform 11 is always kept in a substantial thermal equilibrium. This means that various sorts of internal elements can be housed in the despun platform 11. Therefore, the thermal control subsystem can readily be designed with the illustrated structure.
While this invention has thus far been described in conjunction with an embodiment thereof, it will readily be possible for those skilled in the art to put this invention into practice in various other manners. This invention is applicable to rotate the shading plate in synchronism with a paddle member without the connection between the shading plate and the paddle member.
Claims (4)
PROPERTY OR PRIVILEGE IS CLAIMED ARE DEFINED AS FOLLOWS:
1. A geostatic satellite having an axis of rotation and comprising: a spinning drum arranged to rotate around said axis of rotation; a despun platform which is arranged to be held substantially stationary relative to the axis of the earth by counter rotation relative to said spinning drum; a paddle member loaded with solar cells and arranged to rotate around said axis of rotation to direct said solar cells towards a line which is parallel to light rays from the sun, said paddle member being attached to said despun platform; a shading plate for shading a part of said despun platform from the light rays from the sun, said shading plate being connected to said paddle member so that said shading plate is movable together with said paddle member to shade said part of the despun platform from the sunbeam; and rotating means for rotating said paddle member and said shading plate in synchronism around said axis of rotation.
2. A geostatic satellite as claimed in claim 1, wherein said shading plate comprises at least one member of a material having a high reflection factor.
3. A geostatic satellite as claimed in claim 1, wherein said shading plate is wider in area than a half of said despun platform.
4. A geostatic satellite as claimed in claim 1, said paddle member comprising a pair of solar cell paddles, said solar cell paddles stretching symmetrical as regards said axis of rotation, wherein said shading plate has opposite ends connected to respective ones of said solar cell paddles.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| JP130680/1983 | 1983-07-18 | ||
| JP58130680A JPS6022600A (en) | 1983-07-18 | 1983-07-18 | Despun platform type spin satellite |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CA1262890A true CA1262890A (en) | 1989-11-14 |
Family
ID=15040041
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CA000459044A Expired CA1262890A (en) | 1983-07-18 | 1984-07-17 | Shading device for use in a geostatic satellite |
Country Status (5)
| Country | Link |
|---|---|
| US (1) | US4725023A (en) |
| EP (1) | EP0132768B1 (en) |
| JP (1) | JPS6022600A (en) |
| CA (1) | CA1262890A (en) |
| DE (1) | DE3461701D1 (en) |
Families Citing this family (18)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2605287A1 (en) * | 1986-10-16 | 1988-04-22 | Centre Nat Etd Spatiales | SUN VISOR FOR GEOSTATIONARY SATELLITE |
| JPH0640480Y2 (en) * | 1986-12-18 | 1994-10-19 | 日本電気株式会社 | Stepping motor drive circuit |
| DE3731755A1 (en) * | 1987-09-22 | 1989-03-30 | Teldix Gmbh | ACTUATOR FOR A ADJUSTABLE AERIAL ARRANGED ON A SATELLITE, SOLAR COLLECTOR O. AE. |
| GB9004435D0 (en) * | 1990-02-28 | 1990-04-25 | Marconi Co Ltd | Geostationary satellite |
| US6068218A (en) * | 1997-05-14 | 2000-05-30 | Hughes Electronics Corporation | Agile, spinning spacecraft with sun-steerable solar cell array and method |
| FR2765190B1 (en) * | 1997-06-26 | 1999-08-27 | Aerospatiale | IMPROVED THERMAL REJECTION SATELLITE |
| US6076773A (en) * | 1998-04-10 | 2000-06-20 | Hughes Electronics Corporation | Spin-stabilized spacecraft and methods |
| US6102339A (en) * | 1998-04-17 | 2000-08-15 | Turbosat Technology, Inc. | Sun-synchronous sun ray blocking device for use in a spacecraft having a directionally controlled main body |
| US6883588B1 (en) * | 2000-07-24 | 2005-04-26 | Space Systems/Loral, Inc. | Spacecraft radiator system using a heat pump |
| US6481671B1 (en) | 2000-08-14 | 2002-11-19 | Ball Aerospace & Technologies Corp. | Spacecraft sunshield for use in performing solar torque balancing |
| US6429368B1 (en) * | 2001-03-20 | 2002-08-06 | Trw Inc. | Shortened solar cell array |
| US7114682B1 (en) * | 2004-02-18 | 2006-10-03 | Kistler Walter P | System and method for transportation and storage of cargo in space |
| FR2919270B1 (en) * | 2007-07-24 | 2009-09-25 | Thales Sa | SOLAR PROTECTION DEVICE FOR SPATIAL INSTRUMENT |
| US8186628B2 (en) * | 2009-08-12 | 2012-05-29 | Raytheon Company | Multi-axis articulated solar light shade for space-based sensors |
| CN102944256A (en) * | 2012-11-26 | 2013-02-27 | 中国科学院长春光学精密机械与物理研究所 | Radiator suitable for space optical remote sensor in sun-synchronous orbit |
| CN104477415B (en) * | 2014-11-21 | 2017-01-11 | 上海卫星工程研究所 | Light-shading heat-insulation cover framework structure for spacecraft |
| US11926442B2 (en) | 2021-04-07 | 2024-03-12 | Ball Aerospace & Technologies Corp. | Multiple function spacecraft sunshade systems and methods |
| CN113173271A (en) * | 2021-05-28 | 2021-07-27 | 重庆协点通讯技术有限公司 | Star chain receiving arrangement convenient to adjust |
Family Cites Families (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3603530A (en) * | 1969-10-03 | 1971-09-07 | Us Navy | Passive temperature control for satellite |
| US3653942A (en) * | 1970-04-28 | 1972-04-04 | Us Air Force | Method of controlling temperature distribution of a spacecraft |
| US3768754A (en) * | 1971-01-26 | 1973-10-30 | Org Europ De Rech Spatiales | Louver system with sandwich type blades |
| US3877662A (en) * | 1971-06-09 | 1975-04-15 | Gordon S Reiter | Isolated frame on platforms stabilized by spinning body |
| BE785593A (en) * | 1972-06-29 | 1972-10-16 | Org Europeene De Rech | RADIATION BARRIER WITH ARTICULATED FLAPS |
| FR2476018A1 (en) * | 1980-02-14 | 1981-08-21 | Org Europeene De Rech | CONFIGURATION OF SATELLITES FOR GEOSTATIONARY MISSION |
| JPS5799500A (en) * | 1980-12-09 | 1982-06-21 | Fujitsu Ltd | Artificial satellite on which electronic computer is loaded |
| FR2522614A1 (en) * | 1982-03-02 | 1983-09-09 | Centre Nat Etd Spatiales | CONFIGURATION OF SATELLITE WITH EQUATORIAL ORBIT WITH PERFECTED SOLAR MEANS |
-
1983
- 1983-07-18 JP JP58130680A patent/JPS6022600A/en active Granted
-
1984
- 1984-07-17 CA CA000459044A patent/CA1262890A/en not_active Expired
- 1984-07-17 DE DE8484108439T patent/DE3461701D1/en not_active Expired
- 1984-07-17 US US06/631,644 patent/US4725023A/en not_active Expired - Fee Related
- 1984-07-17 EP EP84108439A patent/EP0132768B1/en not_active Expired
Also Published As
| Publication number | Publication date |
|---|---|
| EP0132768A1 (en) | 1985-02-13 |
| EP0132768B1 (en) | 1986-12-17 |
| US4725023A (en) | 1988-02-16 |
| JPH0239440B2 (en) | 1990-09-05 |
| DE3461701D1 (en) | 1987-01-29 |
| JPS6022600A (en) | 1985-02-05 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| MKLA | Lapsed |