EP2608313A1 - Antenna pointing system - Google Patents
Antenna pointing system Download PDFInfo
- Publication number
- EP2608313A1 EP2608313A1 EP12008604.6A EP12008604A EP2608313A1 EP 2608313 A1 EP2608313 A1 EP 2608313A1 EP 12008604 A EP12008604 A EP 12008604A EP 2608313 A1 EP2608313 A1 EP 2608313A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- payload
- pointing system
- antenna pointing
- mounting structure
- movably
- 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
- 230000007246 mechanism Effects 0.000 description 4
- 238000006073 displacement reaction Methods 0.000 description 3
- 238000009429 electrical wiring Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
Images
Classifications
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/12—Supports; Mounting means
- H01Q1/125—Means for positioning
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q3/00—Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system
- H01Q3/02—Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system using mechanical movement of antenna or antenna system as a whole
- H01Q3/08—Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system using mechanical movement of antenna or antenna system as a whole for varying two co-ordinates of the orientation
Definitions
- the present invention relates to the field of antenna systems, and is more particularly concerned with pointing systems for steerable antennas.
- steerable antennas it is well known in the art to use steerable (or tracking) antennas to communicate with a relatively moving target over a scan angle.
- steerable RF (Radio Frequency signal) antennas preferably need to have precise pointing, high gain, low mass, and high reliability.
- Satellites often contain two (2) degree of freedom pointing devices to communicate, sense, etc. with other satellites or bodies. Since the distances are large, the pointing accuracy and resolution is critical.
- the payload of these pointing devices is variable. Some payloads are full antennas, portions of an antenna, sensors, etc.
- the above first three (3) points are main advantages when using rotary actuators.
- an antenna pointing system for selectively moving a payload relative to a mounting surface, said system comprising:
- the flexible mounting structure is a universal joint, including bearings, flexures or the like, preferably located near a geometric center of the payload.
- first and second rotary actuators connecting to respective said connecting rod with said second ends of said connecting rods movably connecting to corresponding first and second attachment points of the payload.
- first and second attachment points are angularly spaced from one another relative to a rotation center of the flexible mounting structure, and the first and second attachment points are substantially adjacent a perimeter of the payload.
- first and second attachment points are substantially 90 degrees apart from one another relative to the rotation center of the flexible mounting structure.
- Figures 1a and 1b are side and rear elevation views, respectively, of an antenna reflector mounted with a prior art two-axis gimbal pointing system
- Figure 2 is a top perspective view of an embodiment of an antenna pointing system in accordance with the present invention movably supporting an antenna reflector payload;
- Figure 3 is an enlarged top perspective view of a rotary actuator of the embodiment of Figure 2 ;
- Figure 4 is a partially broken enlarged top perspective view of a universal joint of the embodiment of Figure 2 ;
- Figure 5 is a partially broken top plan view of the embodiment of Figure 2 .
- FIG. 2 there is shown a schematic diagram of an embodiment of the low profile high resolution and torque antenna pointing system 10.
- the pointing system 10 points a reflector, part of an RF (Radio Frequency signal) antenna 12 mounted on board of a spacecraft, represented by the mounting surface 14 situated in orbit.
- the pointing system 10 consists of using rotary actuators 20 in conjunction with cranks 22 and connecting rods 24 to impart rotations to a payload structure 26, such as an antenna reflector assembly, which is movably held in place by a flexible mounting structure 28 as a universal joint structure or the like.
- An example of the complete system 10 is shown in Figure 2 .
- the RF performance is improved because the generally orthogonal first 30 and second 31 rotation axes of the universal joint 28 intersects a point proximate the geometric center of the reflector 26, to define the rotation center R thereof.
- the system 10 uses two rotary actuators 20 to drive two degrees of freedom. Both rotary actuators 20 have their fixed part secured to the base plate 14 eliminating any mobile harnessing, such as RF rotary joint, electrical wiring, etc.
- a crank 22 is assembled on the output of the moving part of both rotary actuators 20.
- a rotary actuator 20 with its crank 22 is shown in Figure 3 .
- An elongated connecting rod 24 has a first proximal end 32 movably connected to the shaft 23 of the crank 22 and the opposite second distal end 34 movably connected to the payload 26, at an attachment point 27 typically adjacent a perimeter thereof.
- both ends 32, 34 are connected through spherical bearings 35, flexures or the like in order to allow angular displacements thereof between respective connecting elements.
- the payload 26 is movably mounted on the surface 14 using the universal joint 28 typically consisting of one to two (1-2) static brackets 36 securable to the surface 14 and movably supporting a cross 38 about the first rotation axis 30 via at least one first bearing 40, flexure or the like, and one to two (1-2) moving brackets 42 extending from or secured to the payload 26 and movably supported by the cross 38 about the second rotation axis 31 via at least one second bearing 44, flexure or the like, as shown in Figure 4 .
- the universal joint 28 typically consisting of one to two (1-2) static brackets 36 securable to the surface 14 and movably supporting a cross 38 about the first rotation axis 30 via at least one first bearing 40, flexure or the like, and one to two (1-2) moving brackets 42 extending from or secured to the payload 26 and movably supported by the cross 38 about the second rotation axis 31 via at least one second bearing 44, flexure or the like, as shown in Figure 4 .
- the two attachment points 27 connecting to the two second distal ends 34 of the respective connecting rods 24 are typically angularly spaced from one another relative to the rotation center R of the flexible mounting structure 28, as illustrated by angle A.
- Angle A is typically sufficient to make use of the full angular displacement range of the payload 26 about the flexible mounting structure 28. To this end, angle A is preferably around 90 degrees.
Landscapes
- Variable-Direction Aerials And Aerial Arrays (AREA)
- Aerials With Secondary Devices (AREA)
Abstract
Description
- The present invention relates to the field of antenna systems, and is more particularly concerned with pointing systems for steerable antennas.
- It is well known in the art to use steerable (or tracking) antennas to communicate with a relatively moving target over a scan angle. Especially in the aerospace industry when the antenna is on board of a spacecraft, such steerable RF (Radio Frequency signal) antennas preferably need to have precise pointing, high gain, low mass, and high reliability.
- Satellites often contain two (2) degree of freedom pointing devices to communicate, sense, etc. with other satellites or bodies. Since the distances are large, the pointing accuracy and resolution is critical.
- The payload of these pointing devices is variable. Some payloads are full antennas, portions of an antenna, sensors, etc.
- Many different pointing devices have been devised in the past. The simplest one being two rotary actuators (RA) assembled in a sequential chain and holding the payload, such as a reflector, as shown in
Figures 1a and 1b . Especially when relatively small scan angles are required, such as below +/- 30 degrees for example, these types of pointing devices have many disadvantages, or at least a few, among the following list: - high profile;
- heavy mass, structurally inefficient;
- high cost;
- low accuracy;
- low resolution;
- low reliability;
- need for Hold down and Release Mechanisms (HRM);
- requires fixed predetermined stowed position for launch;
- need for moving harness (RF rotary joint, electrical wiring, etc.); and/or
- reduced RF performance in the case of a reflector pointing mechanism.
- Accordingly, there is a need for an improved antenna pointing system.
- It is therefore a general object of the present invention to provide an improved antenna pointing system that solves the above-mentioned problems.
- Advantages of the antenna pointing system of the present invention are:
- 1. lower profile;
- 2. lower mass, structurally efficient;
- 3. lower cost;
- 4. higher accuracy;
- 5. higher resolution;
- 6. higher reliability;
- 7. eliminates need for Hold down and Release Mechanisms (HRM);
- 8. allows for last minute selection of stowed position for launch;
- 9. eliminated need for moving harness (RF rotary joint, electrical wiring, etc.): and/or
- 10. improved RF performance in the case of a reflector pointing mechanism.
- The above first three (3) points are main advantages when using rotary actuators.
- According to an aspect of the present invention there is provided an antenna pointing system for selectively moving a payload relative to a mounting surface, said system comprising:
- at least one rotary actuator having a moving part being movable relative to a fixed part adapted for mounting on the surface;
- a connecting rod movably connecting to the moving part at a first end thereof and adapted for movably connecting to the payload at a second end thereof; and
- a flexible mounting structure for movably attaching the payload to the mounting surface.
- Conveniently, the flexible mounting structure is a universal joint, including bearings, flexures or the like, preferably located near a geometric center of the payload.
- In one embodiment, there are two rotary actuators with essentially the two second ends of the connecting rods connecting adjacent a perimeter of the payload, the two actuators being angularly spaced from one another relative to a rotation center of the flexible mounting structure, typically by an angle sufficient to make use of the full angular displacement range of the payload about the flexible mounting structure.
- In one embodiment, there are first and second rotary actuators connecting to respective said connecting rod with said second ends of said connecting rods movably connecting to corresponding first and second attachment points of the payload.
- Typically, the first and second attachment points are angularly spaced from one another relative to a rotation center of the flexible mounting structure, and the first and second attachment points are substantially adjacent a perimeter of the payload.
- Conveniently, the first and second attachment points are substantially 90 degrees apart from one another relative to the rotation center of the flexible mounting structure.
- Other objects and advantages of the present invention will become apparent from a careful reading of the detailed description provided herein, within appropriate reference to the accompanying drawings.
- In the annexed drawings, like reference characters indicate like elements throughout.
-
Figures 1a and 1b are side and rear elevation views, respectively, of an antenna reflector mounted with a prior art two-axis gimbal pointing system; -
Figure 2 is a top perspective view of an embodiment of an antenna pointing system in accordance with the present invention movably supporting an antenna reflector payload; -
Figure 3 is an enlarged top perspective view of a rotary actuator of the embodiment ofFigure 2 ; -
Figure 4 is a partially broken enlarged top perspective view of a universal joint of the embodiment ofFigure 2 ; and -
Figure 5 is a partially broken top plan view of the embodiment ofFigure 2 . - With reference to the annexed drawings the preferred embodiments of the present invention will be herein described for indicative purpose and by no means as of limitation.
- Referring to
Figures 2 and3 , there is shown a schematic diagram of an embodiment of the low profile high resolution and torqueantenna pointing system 10. In the case presented, thepointing system 10 points a reflector, part of an RF (Radio Frequency signal)antenna 12 mounted on board of a spacecraft, represented by the mountingsurface 14 situated in orbit. Thepointing system 10 consists of usingrotary actuators 20 in conjunction withcranks 22 and connectingrods 24 to impart rotations to apayload structure 26, such as an antenna reflector assembly, which is movably held in place by aflexible mounting structure 28 as a universal joint structure or the like. An example of thecomplete system 10 is shown inFigure 2 . - In the
embodiment 10, the RF performance is improved because the generally orthogonal first 30 and second 31 rotation axes of theuniversal joint 28 intersects a point proximate the geometric center of thereflector 26, to define the rotation center R thereof. Thesystem 10 uses tworotary actuators 20 to drive two degrees of freedom. Bothrotary actuators 20 have their fixed part secured to thebase plate 14 eliminating any mobile harnessing, such as RF rotary joint, electrical wiring, etc. Acrank 22 is assembled on the output of the moving part of bothrotary actuators 20. Arotary actuator 20 with itscrank 22 is shown inFigure 3 . - An elongated connecting
rod 24 has a firstproximal end 32 movably connected to theshaft 23 of thecrank 22 and the opposite seconddistal end 34 movably connected to thepayload 26, at anattachment point 27 typically adjacent a perimeter thereof. Typically, both ends 32, 34 are connected throughspherical bearings 35, flexures or the like in order to allow angular displacements thereof between respective connecting elements. Thepayload 26 is movably mounted on thesurface 14 using the universal joint 28 typically consisting of one to two (1-2)static brackets 36 securable to thesurface 14 and movably supporting across 38 about thefirst rotation axis 30 via at least onefirst bearing 40, flexure or the like, and one to two (1-2) movingbrackets 42 extending from or secured to thepayload 26 and movably supported by thecross 38 about thesecond rotation axis 31 via at least onesecond bearing 44, flexure or the like, as shown inFigure 4 . - As best seen in
Figure 5 , the two attachment points 27 connecting to the two second distal ends 34 of the respective connectingrods 24 are typically angularly spaced from one another relative to the rotation center R of theflexible mounting structure 28, as illustrated by angle A. Angle A is typically sufficient to make use of the full angular displacement range of thepayload 26 about theflexible mounting structure 28. To this end, angle A is preferably around 90 degrees.
Claims (7)
- An antenna pointing system (10) for selectively moving a payload (26) relative to a mounting surface (14), said system (10) comprising:- at least one rotary actuator (20) having a moving part (22) being movable relative to a fixed part adapted for mounting on the surface (14);- a connecting rod (24) movably connecting to the moving part (22) at a first end (32) thereof and adapted for movably connecting to the payload (26) at a second end (34) thereof; and- a flexible mounting structure (28) for movably attaching the payload (26) to the mounting surface (14).
- The antenna pointing system (10) of claim 1. wherein the at least one rotary actuator includes first and second rotary actuators (20) connecting to respective said connecting rod (24) with said second ends (34) of said connecting rods (24) movably connecting to corresponding first and second attachment points (27) of the payload (26).
- The antenna pointing system (10) of claim 2, wherein the first and second attachment points (27) are angularly spaced (A) from one another relative to a rotation center (R) of the flexible mounting structure (28).
- The antenna pointing system (10) of claim 3, wherein the first and second attachment points (27) are substantially adjacent a perimeter of the payload (26).
- The antenna pointing system (10) of claim 2, wherein the first and second attachment points (27) are substantially 90 degrees apart (A) from one another relative to the rotation center (R) of the flexible mounting structure (28).
- The antenna pointing system (10) of claim 1, wherein the flexible mounting structure (28) is located adjacent a geometric center of the payload (26).
- The antenna pointing system (10) of claim 1, wherein the flexible mounting structure is a universal joint structure (28).
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US201161630985P | 2011-12-23 | 2011-12-23 |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2608313A1 true EP2608313A1 (en) | 2013-06-26 |
EP2608313B1 EP2608313B1 (en) | 2019-02-13 |
Family
ID=47632672
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP12008604.6A Active EP2608313B1 (en) | 2011-12-23 | 2012-12-23 | Antenna pointing system |
Country Status (2)
Country | Link |
---|---|
EP (1) | EP2608313B1 (en) |
JP (1) | JP6068129B2 (en) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN109649697A (en) * | 2019-01-14 | 2019-04-19 | 上海卫星工程研究所 | Connection method between a kind of satellite capsule under overconstrained condition |
WO2020079290A1 (en) | 2018-10-17 | 2020-04-23 | Airbus Defence And Space, S.A. | Articulated mechanism and articulated aiming system comprising the mechanism |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPH04266203A (en) * | 1991-02-20 | 1992-09-22 | Fujitsu General Ltd | Mount for antenna system |
JP2004064195A (en) * | 2002-07-25 | 2004-02-26 | Toshiba Corp | Driver and antenna assembly |
DE102009030239A1 (en) * | 2009-06-23 | 2010-12-30 | Eads Deutschland Gmbh | Holder for a movable sensor |
US20110043433A1 (en) * | 2009-08-24 | 2011-02-24 | Jurgen Zimmermann | Positioning equipment for aligning a device |
US20110234464A1 (en) * | 2010-03-23 | 2011-09-29 | Lockheed Martin Corporation | Pivot radar |
Family Cites Families (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3262321A (en) * | 1963-09-16 | 1966-07-26 | Jr George E Moul | Two-rod seeker head |
US4251819A (en) * | 1978-07-24 | 1981-02-17 | Ford Aerospace & Communications Corp. | Variable support apparatus |
-
2012
- 2012-12-23 EP EP12008604.6A patent/EP2608313B1/en active Active
- 2012-12-25 JP JP2012281094A patent/JP6068129B2/en active Active
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JPH04266203A (en) * | 1991-02-20 | 1992-09-22 | Fujitsu General Ltd | Mount for antenna system |
JP2004064195A (en) * | 2002-07-25 | 2004-02-26 | Toshiba Corp | Driver and antenna assembly |
DE102009030239A1 (en) * | 2009-06-23 | 2010-12-30 | Eads Deutschland Gmbh | Holder for a movable sensor |
US20110043433A1 (en) * | 2009-08-24 | 2011-02-24 | Jurgen Zimmermann | Positioning equipment for aligning a device |
US20110234464A1 (en) * | 2010-03-23 | 2011-09-29 | Lockheed Martin Corporation | Pivot radar |
Cited By (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2020079290A1 (en) | 2018-10-17 | 2020-04-23 | Airbus Defence And Space, S.A. | Articulated mechanism and articulated aiming system comprising the mechanism |
CN113169439A (en) * | 2018-10-17 | 2021-07-23 | 空中客车防务及航天股份有限公司 | Articulated mechanism and articulated pointing system comprising said mechanism |
US11652269B2 (en) | 2018-10-17 | 2023-05-16 | Airbus Defence and Space S.A. | Articulated mechanism and articulated aiming system comprising the mechanism |
CN113169439B (en) * | 2018-10-17 | 2024-05-07 | 空中客车防务及航天股份有限公司 | Hinge mechanism and hinge pointing system comprising said mechanism |
CN109649697A (en) * | 2019-01-14 | 2019-04-19 | 上海卫星工程研究所 | Connection method between a kind of satellite capsule under overconstrained condition |
CN109649697B (en) * | 2019-01-14 | 2020-10-09 | 上海卫星工程研究所 | Satellite cabin connection method under over-constrained condition |
Also Published As
Publication number | Publication date |
---|---|
EP2608313B1 (en) | 2019-02-13 |
JP6068129B2 (en) | 2017-01-25 |
JP2013146059A (en) | 2013-07-25 |
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