US3559919A - Active communication satellite - Google Patents
Active communication satellite Download PDFInfo
- Publication number
- US3559919A US3559919A US734596A US3559919DA US3559919A US 3559919 A US3559919 A US 3559919A US 734596 A US734596 A US 734596A US 3559919D A US3559919D A US 3559919DA US 3559919 A US3559919 A US 3559919A
- Authority
- US
- United States
- Prior art keywords
- satellite
- octagonal
- symmetry
- orbit
- 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 - Lifetime
Links
- 238000004891 communication Methods 0.000 title claims abstract description 46
- 239000002828 fuel tank Substances 0.000 claims abstract description 9
- 230000000087 stabilizing effect Effects 0.000 claims description 8
- 238000012937 correction Methods 0.000 claims description 7
- 230000005484 gravity Effects 0.000 claims description 5
- 238000007599 discharging Methods 0.000 claims description 2
- 239000007789 gas Substances 0.000 claims description 2
- 230000006641 stabilisation Effects 0.000 abstract description 14
- 238000011105 stabilization Methods 0.000 abstract description 14
- 238000010276 construction Methods 0.000 description 5
- 230000004308 accommodation Effects 0.000 description 3
- 230000001276 controlling effect Effects 0.000 description 3
- 239000000446 fuel Substances 0.000 description 3
- 230000000712 assembly Effects 0.000 description 2
- 238000000429 assembly Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 230000001105 regulatory effect Effects 0.000 description 2
- 230000001133 acceleration Effects 0.000 description 1
- 230000033228 biological regulation Effects 0.000 description 1
- 230000015572 biosynthetic process Effects 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000013508 migration Methods 0.000 description 1
- 230000005012 migration Effects 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 238000009987 spinning Methods 0.000 description 1
Images
Classifications
-
- H—ELECTRICITY
- H04—ELECTRIC COMMUNICATION TECHNIQUE
- H04B—TRANSMISSION
- H04B7/00—Radio transmission systems, i.e. using radiation field
- H04B7/14—Relay systems
- H04B7/15—Active relay systems
- H04B7/185—Space-based or airborne stations; Stations for satellite systems
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
- B64G1/1007—Communications satellites
-
- 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
- B64G1/26—Guiding or controlling apparatus, e.g. for attitude control using jets
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/27—Adaptation for use in or on movable bodies
- H01Q1/28—Adaptation for use in or on aircraft, missiles, satellites, or balloons
- H01Q1/288—Satellite antennas
-
- 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
- B64G1/242—Orbits and trajectories
- B64G1/2427—Transfer orbits
-
- 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
- B64G1/42—Arrangements or adaptations of power supply systems
- B64G1/44—Arrangements or adaptations of power supply systems using radiation, e.g. deployable solar arrays
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10S136/00—Batteries: thermoelectric and photoelectric
- Y10S136/291—Applications
- Y10S136/292—Space - satellite
Definitions
- An active communications satellite which is stabilized as to attitude and to orbit includes at least one directional antenna rigidly mounted on a body portion.
- the antenna part of the generated surface of the body of the satellite in the operating condition is oriented toward earth.
- the other parts of the surface of the body are penetrated by control engines and their connecting parts which serve to control the attitude and orbit stabilization of the satellite.
- Some of the control engines are enclosed in the operative condition of the satellite by at least two unfoldable solar battery areas which are mounted on pivot arm members to permit them to be swung outwardly when the satellite is in space.
- a fly wheel is carried by the body for the attitude stabilization of the satellite and it rotates about the axis of symmetry parallel to the antenna plane.
- the satellite is advantageously constructed such that the apogee motor, the fly wheel, the electronic equipment and the fuel tanks are disposed so that they will be rotationally symmetric to the axis of symmetry of the satellite.
- This invention relates in general to the construction of satellites or orbiting devices and in particular to a new and useful active communications satellite which is stabilized'as to attitude and orbit and has at least one directional antenna rigidly secured to it.
- a main problem associated with such satellites is that a strongly beaming directional antenna is required at the satellite for beaming the greatest possible received input on or from the satellite. This requires a very accurate orientation of the satellite body with respect to the earth or with respect to another reference system such as a fixed star. It also requires a correct orientation of the electrically or mechanically pivotal directional antenna with respect to the satellite body.
- the portion of the generated surface of the satellite which is located between the two parabolic directional antennas is covered with solar batteries in order to supply the satellite with energy.
- the part which accommodates the solar batteries and possibly other components of the satellite is therefore in the shape of a cylindrical ring which can rotate around the actual core of the satellite to which the two directional antennas are rigidly attached.
- Such a rotating cylindrical ring takes care of the spin stabilization of the satellite so that the core with the antenna attached stands still in relation to the earth.
- This configuration has the disadvantages that only a small part, that is the outside surface of the cylindrical ring only, is available for accommodation of the solar batteries.
- the electrical components are housed in the cylindrical ring and they must be connected with the satellite core through slip rings.
- a further difficulty is that the bearings which permit the rotation of the cylindrical ring relative to the core must have an outlet into the vacuum of space so that the bearing design becomes very difficult and their life is considerably shortened.
- Relatively small parts of the satellite are available for accommodation of the parabolic directional antennas, that is, the parts which are adjacent to the faces or surfaces.
- a communications satellite which has an adequate area for the assembly of the directional antennas as provided with an accommodation for solar batteries of as large a size as possible and which does not have any rotatable parts and bearings for supporting such parts which require outlet to the space vacuum.
- the construction includes an active communications satellite having a body which is stabilized to attitude and orbit and which carries at least one directional antenna which is rigidly fixed in position. All parts of its generated surface which in the operating condition are oriented toward the earth are penetrated by at least one directional antenna. The other parts of the generated surface are penetrated by engine mounting elements for controlling the attitude and orbit stabilization.
- the directional antennas and part of the controlling engines are enclosed in the inactive condition of the satellite by at least two unfoldable solar battery areas which are made to conform to the configuration of the satellite and which in the unfolded condition can open up into positions located outside the range of the satellites generated surface
- the configuration of the communications satellite in ac cordance with the invention it is possible to reserve a portion of the generated surface for the assembly of the directional antennas which in relation to the total area of the satellite is very large.
- the surface is preferably in the form of a planar surface, the antenna type which is best suited for the application can be selected with a great deal of freedom.
- the antenna plane may accommodate a dipole and emitter field. a phased array antenna, several parabolic antennas or a honeycomb antenna.
- the solar battery covered area may be divided into partial areas or panels which may be oriented independently of each other so that a maximum of the solar batteries available is radiated by the sum simultaneously at any one point of the satellites orbit.
- the panels are unfolded and such a construction provides an additional advantage inasmuch as the field of the antenna plane is not disturbed by any obstructions and the control engines which are enclosed by the solar battery areas during the inoperative or starting phase become active without obstruction when the satellite reaches its orbit.
- a fly wheel for the attitude stabilization of the satellite.
- the fly wheel preferably rotates about the satellite bodys axis of symmetry parallel to the antenna plane. It has a speed which can be regulated in the upper range of its nominal speed.
- the attitude of the satellite may be stabilized because of the gyro effect and because of the rotational impulse exchange between the fly wheel rotor and the satellite body. Acceleration and deceleration of the fly wheel rotor relative to the satellite body permits change in the attitude to control the stabilization.
- the rotor with all bearings and the drive motor can be encapsulated, and this does away with any requirement for a vacuum bearing.
- the apogee motor, the fly wheel, the electronic equipment and the fuel tanks are disposed in a rotationally symmetrical plane in respect to the axis of symmetry of the satellite body. In this manner, the spin of the entire satellite body during the burning phase of the apogee motor can be controlled until the starting up of the fly wheel after orbit.
- the solar battery areas are advantageously covered with solar batteries on both sides. This arrangement is particularly advantageous when unfolding the solar battery areas so that they are spread into several partial areas. This arrangement makes the percentage of solar batteries radiated by the sun at any point of the orbit particularly great.
- the control engines required for attitude and orbit stabilization are disposed in the satellite body in a manner such that there is one engine for inclination corrections on the axis of symmetry opposite to the apogee motor and having a thrust direction opposed to the latter.
- Two orbit correction engines are located in a plane perpendicular to the axis of symmetry and contained in the plane of the center of gravity. These orbit correction engines have mutually opposing directions of thrust and are directed parallel to the antenna plane and radial to the axis of symmetry.
- Two additional pairs of engines are located in the same plane for the generation of a turning moment acting upon the axis of symmetry; and two more engines are provided for the generation of a precession moment in the proximity of the face of the satellite.
- the latter two engines are located in the proximity of the face of the satellite in a plane perpendicular to the antenna plane and in a plane which contains the axis of symmetry.
- the satellites electronic equipment is combined in functional units located directly adjacent the faces of the satellite body. Such an arrangement of the equipment has the advantage that temperature regulation is possible by means of flaps provided in the satellites face.
- the satellite is of tagonal configuration. preferably in the form of a prismatic column of octagonal cross section.
- the antenna plane is a plane established parallel to the axis of symmetry in the area that would be occupied by two panels of the octagonal configuration.
- a communications satellite which includes a body which is generated by surface parts which in the operating condition are oriented toward the earth and which carry the directional antenna or antennas; the other parts of the generated surface carrying control engines for attitude and orbit stabilization, and the outer surface being enclosed by at least two unfoldable solar battery areas or panels which in the inoperative position enclose the satellite body sides but which in the operative position may be extended outwardly from the satellite body.
- a further object of the invention is to provide a communications satellite in the fomt of an octagonal column having an apogee engine mounted on one end and at least one antenna located in a plane parallel to the axis of symmetry, the body sides being closable by a solar battery panel assembly arranged on each end of the satellite and with panel elements which are foldable to coincide with the octagonal sides of the body.
- a further object of the invention is to provide a communications satellite having a fly wheel for controlling the attitude of the satellite which includes an element rotatable about the axis of symmetry parallel to the antenna plane but which ad vantageously may be encapsulated and located within the antenna body or an appendage thereof.
- a further object of the invention is to provide a communications satellite which includes an apogee motor, a fly wheel, and electronic equipment for operating the antenna, as well as fuel tanks which are disposed in a rotational symmetrical plane in respect to the axis of symmetry of the satellite body.
- a further object of the invention is to provide a communications satellite which is simple in design, rugged in construction and economical to manufacture.
- FIG. 1 is a perspective view of a communications satellite in orbit constructed in accordance with the invention
- FIG. 2 is a schematic perspective view of the satellite indicated in FIG. 1 but on a slightly reduced scale;
- FIG. 3 is an exploded perspective view, partly schematic, of portions of the satellite indicating the assembly of the various units;
- FIG. 4a is a perspective view of the satellite similar to FIG. 1 but on a reduced scale and showing the solar batteries in an inoperative launch position;
- FIG. 4b is a view similar to FIG. 40 but showing the initial stages of the unfolding of the solar batteries
- FIG. 40 is a view similar to FIG. 40 showing the batteries in a further stage of unfolding.
- FIG. 4:1 is a view similar to FIG. 40 showing the solar batteries in the final position of unfolding comparable to that indicated in FIG. 1.
- the invention embodied therein comprises a communications satellite having a satellite body generally designated 2 of generally octagonal prismatic column formation. Two of the eight sides of the body 2 are removed and a planar surface 3 which is parallel to the plane of symmetry of the body 2 defines a mounting base for two parabolic antennas 4 and 5 which are rigidly affixed to the planar surface 3.
- the satellite body 2 carries swivel arms 8 and 9 having swivel joints (not shown) which permit the arms to be shifted from the inoperative position (FIG. 4a) in which the arms are not shown to the operative position in which the arms are swung out and support solar battery assemblies generally designated 6 and 7.
- the solar battery assemblies each include four panel areas 60. 6b, 6c and 6d and 7a, 7b. 7c and 711 which carry solar cells on each side or surface.
- the panel areas 6a to 6d and 7a to 7d are of a size such that they cover the side panels or side panel areas 2a to 2d and 2a to 2d, respectively.
- the satellite body 2 includes an end face 26 mounting an apogee motor 10 and two control engines 11 and 12 which are disposed in the plane of symmetry and are symmetrical to the bodys axis of symmetry.
- the satellite body 2 is shown schematically and without the solar battery areas in order to indicate the arrangement of the control engines associated with it.
- the apogee motor 10 and the control engines 11 and 12 are mounted in a plane which contains the axis of symmetry and which is parallel to the antenna plane.
- the control engine 13 On or below the opposite face of the axis of symmetry is the control engine 13 having a thrust direction opposite to the apogee motor 10 and provided for inclination corrections to the communications satellite.
- Two more control engines 14 and 15 are disposed on a side face of the satellite body 2 in a plane perpendicular to the axis of symmetry and containing the center of gravity. The thrust direction of the engines 14 and 15 is parallel to the antenna plane and radial to the axis of symmetry.
- Two additional pairs of control engines 16 and 17 on one side, and 18 and 19 on the opposite said; are mounted to produce a turning moment around the axis of symmetry.
- the turning moment produced by the engine pair 16 and 17 opposes the tuming moment produced by the engine pair 18 and 19.
- a fly wheel 20 is mounted within the body 2 adjacent a panel 28 at the end opposite from the panel 26.
- the fly wheel acts to stabilize the attitude of the satellite and is disposed in the axis of symmetry of the satellite body 2.
- a plurality of fuel tanks 21 containing fuel required for the control of the control engines are arranged around the axis of symmetry adjacent the apogee motor 10. Pairs of the tanks 21 are positioned symmetrical to the axis of symmetry and communicate with each otherthrough fuel lines (not shown) so that the fuel needed for the control engines is always taken uniformly from a pair of tanks and fed off so that the symmetry in respect to the center of gravity is maintained.
- Electronic components 22 and 23 are located adjacent the respective panels 28 and 26 within the interior of the satellite body 2.
- the electronic component 22 has an opening in its axis of symmetry for the control engine 13.
- the communications satellite When the communications satellite is assembled and ready for orbiting, it assumes the configuration indic ated in FIG. 4a.
- the communications satellite is then moved out into space on a carrier missile or rocket and located in its final orbit during the burning phase of the apogee motor 10.
- the solar battery areas 6 and 7 which initially form the outer surface of the satellite body 2 are pivoted and opened from the configuration shown in FIG. 4a to the configuration shown in FIGS. 1 and 4d.
- FIG. 4b During the initial stages of the unfolding of the solar batteries, they assume the position indicated in FIG. 4b in which they are oriented substantially parallel to each other from which location they are transferred upwardly and downwardly to the location 40.
- the swivel arms 8 and 9 first position the solar batteries as indicated in FIG. 40 and then the 'arm 9 is rotated to shift the solar battery 7 perpendicular to the solar battery area 6. This takes place only after the apogee motor 10 is burned out.
- the solar batteries 6 are located so that the engine 13 can function without any difficulty.
- the unfolding and the swivel operation of the solar cell areas 6 and 7 is carried out in a known manner by mechanical energy accumulators such as springs after exploding a holding or tensioning band, for example.
- the communications satellite performs a spinning motion after separation from its carrier rocket during the burning period of the apogee motor 10. Therefore, in order to steer the satellite easily into its final orbit and to compensate for the construction inaccuracies which might exist in respect to the axis of symmetry, the spin of the satellite must be controlled in orbit so that the antenna plane 3 will be constantly oriented toward the earth.
- the breaking up of the spin is accomplished by the fly wheel 20 which provides the orbital stabilization of the satellite by giving it a turning moment after the fly wheel is started.
- the reaction turning moment acting upon the satellite body 2 counteracts the spin of the satellite body.
- the fly wheel 20 is operated at a far greater number of revolutions than would be the number of revolutions of a spin stabilized satellite.
- the turning impulse produced by the fly wheel is about the same as that of the spin stabilized satellite.
- the turning impulse produced by the fly wheel is about the same as that of the spin stabilized satellite rotating at fewer revolutions so that the weight of the fly wheel 20 can be kept proportionately low.
- the speed of the fly wheel can be regulated for operation in the upper range of its nominal speed to provide compensation of the external interference momerits about the fly wheel shaft to provide stabilization of the axis and with it of the satellite by a gyro effect.
- the control engines 11 and 12 are provided to impart a precession moment to the satellite body when the fly wheel is running so that the gradual migration of the axis of rotation of the fly wheel 20 out of the orbit normal can be corrected from time to time through precession maneuvers.
- the control engine pairs l6, l7, l8 and 19 serve to impart to the satellite body a spin or despinning moment.
- Engines 14 and 15 serve the orbital velocity, that is, the orbit stabilization.
- the engine [3 permits the correction of the orbit in respect to inclination.
- a precise attitude stabilization of the satellite is achieved through a combination of these engines in order to provide for the exact orientation of the antenna plane 3 for the earth. After the unfolding of the solar battery areas 6 and 7, the antenna plane 3 is free for constant orientation to the earth and the control engines may operate without interference with the solar batteries.
- An active communications satellite stabilized as to attitude and orbit, comprising a satellite body having a planar surface with at least one directional antenna affixed to said planar surface said planar body surface with said antenna being orientable toward the earth, control engine means on said body for stabilizing said body in orbit and in attitude for orienting said antenna toward the earth, and solar battery means carried on said body and adapted to enclose at least a portion of said body and being unfoldable from covering said body for orientation at a position outside the surface of said body.
- control engine means includes a fly wheel for stabilizing the attitude of said satellite. said fly wheel being mounted on said body for rotation about an axis of symmetry parallel to the plane of said antenna.
- An active communications satellite including an apogee motor mounted on said body and oriented for discharging thrust gases from one end of said body, electronic equipment carried within said body, said control engine means including a fly wheel and fuel tanks, all of said apogee motor, said fly wheel, said electronic equipment and said fuel tanks being disposed rotationally symmetrical to the axis of symmetry of said satellite.
- said solar battery means comprises a panel having solar batteries on each side.
- An active communications satellite including an apogee motor mounted on said satellite body and having a nozzle thrust discharge extending outwardly from one end thereof, said control engine means including an engine mounted on said satellite body and having a thrust nozzle discharge oriented in an opposite direction to said apogee motor, said control engine means including at least two orbit correction engines arranged on substantially diametrically opposite sides of said satellite and having a thrust discharge extending outwardly in respective opposite directions away from said satellite in a plane perpendicular to the axis of symmetry and which contains the center of gravity of said satellite body, and at least two pairs of engines on respective diametric opposite sides of said satellite body having thrust discharges extending in a direction for obtaining a turning moment about the axis of symmetry of said satellite body, at least two additional control engines mounted at one end of said satellite body on each side of said apogee motor for the generation of precession moments in the vicinity of the end of said satellite body and in a plane parallel to the antenna plane and in a plane containing the axis of
- An active communications satellite including electronic equipment contained in said satellite body having portions located adjacent each end of said satellite body.
- An active communications satellite stabilized as to attitude and orbit comprising a satellite body having a surface with'at least one directional antenna affixed thereto for orientation toward the earth, control engine means on said body for stabilizing said body in attitude and in orbit, and solar battery means carried on said body and adapted to enclose at least a portion of said body and being unfoldable from covering said body for orientation at a position outside the surface of said body, said satellite body being of octagonal prismatic column configuration, a planar surface on a side of said body defined within two octagonal side areas, said antenna being mounted on a side of said satellite body on said planar surface, said planar surface being parallel to the axis of symmetry of said satellite body.
- An active communications satellite comprising an octagonal prismatic column body, having an octagonal first end and an octagonal second end, an apogee motor mounted adjacent said octagonal first end and having a thrust discharge extending outwardly from said octagonal first end, a control motor mounted on said octagonal second end and having a thrust discharge extending outwardly from said second octagonal end in an opposite direction to said apogee motor, said satellite body having planar side faces with one of said side faces extending over two portions of the octagonal configuration and being a planar surface in a plane parallel to the axis of symmetry of said body, first and second solar battery panels each including four foldable panel areas having solar batteries, each area being of a configuration to enclose a corresponding side face area of the octagonal prismatic column body, and means mounting said solar battery panels for orientation around the sides of said satellite body to cover said sides and for shifting to the exterior of said satellite body at a spaced location from
Landscapes
- Engineering & Computer Science (AREA)
- Remote Sensing (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Astronomy & Astrophysics (AREA)
- Aviation & Aerospace Engineering (AREA)
- Radar, Positioning & Navigation (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Computer Networks & Wireless Communication (AREA)
- Signal Processing (AREA)
- Photovoltaic Devices (AREA)
- Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE19671506648 DE1506648A1 (de) | 1967-06-22 | 1967-06-22 | Nachrichtensatellit |
Publications (1)
Publication Number | Publication Date |
---|---|
US3559919A true US3559919A (en) | 1971-02-02 |
Family
ID=5674038
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US734596A Expired - Lifetime US3559919A (en) | 1967-06-22 | 1968-06-05 | Active communication satellite |
Country Status (3)
Country | Link |
---|---|
US (1) | US3559919A (fr) |
FR (1) | FR1571029A (fr) |
GB (1) | GB1201547A (fr) |
Cited By (18)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3948468A (en) * | 1971-09-27 | 1976-04-06 | Rca Corporation | Replaceable solar array panels |
US4133501A (en) * | 1975-09-30 | 1979-01-09 | Communications Satellite Corporation | Self-deployable solar cell panel |
US5101267A (en) * | 1989-08-07 | 1992-03-31 | Tv Answer, Inc. | Wide area real-time T-V audience polling system with local area stations linked by satellite |
US5223923A (en) * | 1989-08-07 | 1993-06-29 | Tv Answer, Inc. | Cellular repeater stations in a wireless audience response system for satellite communication |
US5257099A (en) * | 1989-08-07 | 1993-10-26 | Tv Answer, Inc. | Central data processing station for satellite communication with local area audience response station |
US5666127A (en) * | 1993-02-25 | 1997-09-09 | Nissan Motor Co., Ltd. | Subarray panel for solar energy transmission |
US5833175A (en) * | 1995-12-22 | 1998-11-10 | Hughes Electronics Corporation | Spacecraft with large east-west dimensions |
US5927654A (en) * | 1997-05-16 | 1999-07-27 | Lockheed Martin Corp. | Spacecraft with active antenna array protected against temperature extremes |
US20080078885A1 (en) * | 2006-09-15 | 2008-04-03 | Stanley Canter | Canted solar array and method for using same |
CN103612774A (zh) * | 2013-11-20 | 2014-03-05 | 西北工业大学 | 一种可分离式微纳卫星构型 |
CN103935529A (zh) * | 2014-04-29 | 2014-07-23 | 上海卫星工程研究所 | 一种快速响应卫星结构 |
FR3006670A1 (fr) * | 2013-06-07 | 2014-12-12 | Thales Sa | Systeme de propulsion en deux modules pour controle d'orbite et controle d'attitude de satellite |
CN104290920A (zh) * | 2014-10-08 | 2015-01-21 | 上海微小卫星工程中心 | 一种模块化可重构的微纳卫星结构 |
CN104290918A (zh) * | 2014-09-12 | 2015-01-21 | 上海卫星工程研究所 | 小型化轨道拖船卫星构型与布局设计方法 |
EP2772441B1 (fr) | 2013-02-28 | 2018-04-11 | The Boeing Company | Structure de noyau modulaire pour lanceur à deux charges utiles |
CN110092013A (zh) * | 2019-02-21 | 2019-08-06 | 上海卫星工程研究所 | 高分相机承载结构 |
US20210091479A1 (en) * | 2019-09-25 | 2021-03-25 | Eagle Technology, Llc | Deployable reflector antenna systems |
US20210399793A1 (en) * | 2016-08-25 | 2021-12-23 | Star Mesh LLC | Radio system using nodes |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3148846A (en) * | 1963-01-07 | 1964-09-15 | Robert R Newton | System for gravity orienting a satellite |
US3188639A (en) * | 1961-09-29 | 1965-06-08 | Bell Telephone Labor Inc | Satellite stabilization and attitude control |
US3243143A (en) * | 1962-11-27 | 1966-03-29 | Gen Electric | Doubly stabilized satellite |
US3258225A (en) * | 1964-03-13 | 1966-06-28 | Fred H Esch | Satellite mounting structure |
-
1968
- 1968-06-05 US US734596A patent/US3559919A/en not_active Expired - Lifetime
- 1968-06-17 GB GB28757/68A patent/GB1201547A/en not_active Expired
- 1968-06-21 FR FR1571029D patent/FR1571029A/fr not_active Expired
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3188639A (en) * | 1961-09-29 | 1965-06-08 | Bell Telephone Labor Inc | Satellite stabilization and attitude control |
US3243143A (en) * | 1962-11-27 | 1966-03-29 | Gen Electric | Doubly stabilized satellite |
US3148846A (en) * | 1963-01-07 | 1964-09-15 | Robert R Newton | System for gravity orienting a satellite |
US3258225A (en) * | 1964-03-13 | 1966-06-28 | Fred H Esch | Satellite mounting structure |
Cited By (25)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3948468A (en) * | 1971-09-27 | 1976-04-06 | Rca Corporation | Replaceable solar array panels |
US4133501A (en) * | 1975-09-30 | 1979-01-09 | Communications Satellite Corporation | Self-deployable solar cell panel |
US5101267A (en) * | 1989-08-07 | 1992-03-31 | Tv Answer, Inc. | Wide area real-time T-V audience polling system with local area stations linked by satellite |
US5223923A (en) * | 1989-08-07 | 1993-06-29 | Tv Answer, Inc. | Cellular repeater stations in a wireless audience response system for satellite communication |
US5257099A (en) * | 1989-08-07 | 1993-10-26 | Tv Answer, Inc. | Central data processing station for satellite communication with local area audience response station |
US5666127A (en) * | 1993-02-25 | 1997-09-09 | Nissan Motor Co., Ltd. | Subarray panel for solar energy transmission |
US5833175A (en) * | 1995-12-22 | 1998-11-10 | Hughes Electronics Corporation | Spacecraft with large east-west dimensions |
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Also Published As
Publication number | Publication date |
---|---|
GB1201547A (en) | 1970-08-05 |
FR1571029A (fr) | 1969-06-13 |
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