EP2608313A1 - Antennenausrichtungssystem - Google Patents

Antennenausrichtungssystem Download PDF

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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
Application number
EP12008604.6A
Other languages
English (en)
French (fr)
Other versions
EP2608313B1 (de
Inventor
Richard O. Horth
Marc-André GODIN
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
MacDonald Dettwiler and Associates Corp
Original Assignee
MacDonald Dettwiler and Associates Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by MacDonald Dettwiler and Associates Corp filed Critical MacDonald Dettwiler and Associates Corp
Publication of EP2608313A1 publication Critical patent/EP2608313A1/de
Application granted granted Critical
Publication of EP2608313B1 publication Critical patent/EP2608313B1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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)
EP12008604.6A 2011-12-23 2012-12-23 Antennenausrichtungssystem Active EP2608313B1 (de)

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 (de) 2013-06-26
EP2608313B1 EP2608313B1 (de) 2019-02-13

Family

ID=47632672

Family Applications (1)

Application Number Title Priority Date Filing Date
EP12008604.6A Active EP2608313B1 (de) 2011-12-23 2012-12-23 Antennenausrichtungssystem

Country Status (2)

Country Link
EP (1) EP2608313B1 (de)
JP (1) JP6068129B2 (de)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109649697A (zh) * 2019-01-14 2019-04-19 上海卫星工程研究所 一种过约束条件下的卫星舱间连接方法
WO2020079290A1 (es) 2018-10-17 2020-04-23 Airbus Defence And Space, S.A. Mecanismo articulado y sistema de apuntamiento articulado que comprende ese mecanismo

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH04266203A (ja) * 1991-02-20 1992-09-22 Fujitsu General Ltd アンテナ装置の支持台
JP2004064195A (ja) * 2002-07-25 2004-02-26 Toshiba Corp 駆動装置及びアンテナ装置
DE102009030239A1 (de) * 2009-06-23 2010-12-30 Eads Deutschland Gmbh Halterung für einen bewegbaren 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)

* Cited by examiner, † Cited by third party
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

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH04266203A (ja) * 1991-02-20 1992-09-22 Fujitsu General Ltd アンテナ装置の支持台
JP2004064195A (ja) * 2002-07-25 2004-02-26 Toshiba Corp 駆動装置及びアンテナ装置
DE102009030239A1 (de) * 2009-06-23 2010-12-30 Eads Deutschland Gmbh Halterung für einen bewegbaren 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)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2020079290A1 (es) 2018-10-17 2020-04-23 Airbus Defence And Space, S.A. Mecanismo articulado y sistema de apuntamiento articulado que comprende ese mecanismo
CN113169439A (zh) * 2018-10-17 2021-07-23 空中客车防务及航天股份有限公司 铰接机构和包括所述机构的铰接指向系统
US11652269B2 (en) 2018-10-17 2023-05-16 Airbus Defence and Space S.A. Articulated mechanism and articulated aiming system comprising the mechanism
CN113169439B (zh) * 2018-10-17 2024-05-07 空中客车防务及航天股份有限公司 铰接机构和包括所述机构的铰接指向系统
CN109649697A (zh) * 2019-01-14 2019-04-19 上海卫星工程研究所 一种过约束条件下的卫星舱间连接方法
CN109649697B (zh) * 2019-01-14 2020-10-09 上海卫星工程研究所 一种过约束条件下的卫星舱间连接方法

Also Published As

Publication number Publication date
JP2013146059A (ja) 2013-07-25
EP2608313B1 (de) 2019-02-13
JP6068129B2 (ja) 2017-01-25

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