EP0290969A2 - Unfoldable antenna with two reflecting surfaces - Google Patents
Unfoldable antenna with two reflecting surfaces Download PDFInfo
- Publication number
- EP0290969A2 EP0290969A2 EP88107264A EP88107264A EP0290969A2 EP 0290969 A2 EP0290969 A2 EP 0290969A2 EP 88107264 A EP88107264 A EP 88107264A EP 88107264 A EP88107264 A EP 88107264A EP 0290969 A2 EP0290969 A2 EP 0290969A2
- Authority
- EP
- European Patent Office
- Prior art keywords
- reflector
- antenna
- sub
- reflecting surfaces
- telescopic rod
- 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.)
- Withdrawn
Links
- 239000012530 fluid Substances 0.000 description 1
- 238000003475 lamination Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 239000013585 weight reducing agent Substances 0.000 description 1
Images
Classifications
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q19/00—Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic
- H01Q19/10—Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic using reflecting surfaces
- H01Q19/18—Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic using reflecting surfaces having two or more spaced reflecting surfaces
- H01Q19/19—Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic using reflecting surfaces having two or more spaced reflecting surfaces comprising one main concave reflecting surface associated with an auxiliary reflecting surface
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q15/00—Devices for reflection, refraction, diffraction or polarisation of waves radiated from an antenna, e.g. quasi-optical devices
- H01Q15/14—Reflecting surfaces; Equivalent structures
- H01Q15/16—Reflecting surfaces; Equivalent structures curved in two dimensions, e.g. paraboloidal
- H01Q15/161—Collapsible reflectors
Definitions
- This invention regards an antenna with two generic reflecting surfaces, of which one is unfoldable.
- the purpose of this invention is to provide a system which, with regard to antennae for on board satellites applications, reduces the space occupied during launch phase and which, during transportation, with regard to ground antennae, when fitted to self propelled or trailed vehicles, also requires minimum accomodation space.
- Positioning of the operating configuration may be activated by remote control, for on board systems, or manually for groundbased systems.
- the invention presented here belongs to the telecommunications field, more precisely to that of remote sensing as it may be utilized both as on board equipment and as transportable ground station equipment.
- the present invention solves the problem concerning experienced personnel and suitable and expensive equipments to verify the alignment of the parts.
- Figure 1 shows that the antenna consists of a reflector 1 fixed to a bearing structure which in turn is connected to an interface structure 8. Connection of elements 7 and 8 varies according to the type of system to be implemented.
- Structure 7 carries hinge 6 and motor 3 interfaces, set to unfold and to lock the system in minimum dimensions situation 10.
- motor 3 moves the unfolding structure 4 to which the sub reflector is connected.
- the unfolding speed reduction depends on the type of system application; for on board equipment, motor 3 is connected to a break (such as eddy current, spring type, etc); on the contrary for self propelled ground equipment, opening speed reduction may be achieved by means of lamination of fluids within the telescopic rod 5 itself or by means of a suitable device connected to motors 3; furthermore, for self propelled ground systems, the motor applied may reverse direction of progress so as to restore the minimum dimension configuration of the antenna.
- a break such as eddy current, spring type, etc
- opening speed reduction may be achieved by means of lamination of fluids within the telescopic rod 5 itself or by means of a suitable device connected to motors 3; furthermore, for self propelled ground systems, the motor applied may reverse direction of progress so as to restore the minimum dimension configuration of the antenna.
- the motor may be of the spring type.
Landscapes
- Physics & Mathematics (AREA)
- Electromagnetism (AREA)
- Aerials With Secondary Devices (AREA)
- Variable-Direction Aerials And Aerial Arrays (AREA)
- Details Of Aerials (AREA)
Abstract
Description
- This invention regards an antenna with two generic reflecting surfaces, of which one is unfoldable.
- The purpose of this invention is to provide a system which, with regard to antennae for on board satellites applications, reduces the space occupied during launch phase and which, during transportation, with regard to ground antennae, when fitted to self propelled or trailed vehicles, also requires minimum accomodation space.
- Reduced dimensions, achieved by folding, imply consequent weight reduction, and therefore also less stress on the supporting structure and on the folding surface either for on board or ground based applications.
- Positioning of the operating configuration may be activated by remote control, for on board systems, or manually for groundbased systems.
- The invention presented here belongs to the telecommunications field, more precisely to that of remote sensing as it may be utilized both as on board equipment and as transportable ground station equipment.
- At the present state of groundbased application techniques for transportable antennae, dismantling of the assembly on the field by experienced personnel equipped with suitable tools for realignment is also made possible.
- The present invention solves the problem concerning experienced personnel and suitable and expensive equipments to verify the alignment of the parts.
- As far as on board satellite applications are concerned, to the authors' notice there is no solution known may be checked during launch and may be made operative once in orbit by means of remote controls.
- The invention will now be described with reference to one of its presently preferred forms of implementation, and is reported as an illustration without being limited to it and with reference to the tables of drawings enclosed.
- Figure 1 shows the schematic configuration of the antenna:
a) side view
b) cutaway view
c) top view
The following parts are visible:
1) reflector
2) sub-reflector
3) hinge actuator motor
4) unfolding structure
5) telescopic rod
6) hinges
7) supporting structure
8) interface structure
9) settable end of run
10) fixing area of the foldable structure. - Figure 2 shows the schematic configuration of the antenna in the minimum dimensions situation.
- Figure 3 shows the schematic configuration of a symmetrical two reflector antenna.
- Figure 4 shows the schematic configuration of the antenna fitted to a self propelled vehicle.
- Once again, with reference to the tables of drawings enclosed, operation of the antenna presented herein will be described.
- Figure 1 shows that the antenna consists of a
reflector 1 fixed to a bearing structure which in turn is connected to aninterface structure 8. Connection ofelements -
Structure 7 carrieshinge 6 andmotor 3 interfaces, set to unfold and to lock the system inminimum dimensions situation 10. When thelocking mechanism 10 is unlocked,motor 3 moves theunfolding structure 4 to which the sub reflector is connected. - Movement of
structure 4 aroundhinges 3, throughhinges 6, shortenstelescopic rod 5 which carries a settable end race 9 which determines the system operating position together with the motors which remain powered. - To minimize impact of the end race, the unfolding speed reduction depends on the type of system application; for on board equipment,
motor 3 is connected to a break (such as eddy current, spring type, etc); on the contrary for self propelled ground equipment, opening speed reduction may be achieved by means of lamination of fluids within thetelescopic rod 5 itself or by means of a suitable device connected tomotors 3; furthermore, for self propelled ground systems, the motor applied may reverse direction of progress so as to restore the minimum dimension configuration of the antenna. - For on board systems which must be opened once only, the motor may be of the spring type.
Claims (4)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
IT4794687 | 1987-05-15 | ||
IT47946/87A IT1205964B (en) | 1987-05-15 | 1987-05-15 | ANTENNA WITH TWO REFLECTIVE SURFACES AND SUB-REFLECTOR AVAILABLE |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0290969A2 true EP0290969A2 (en) | 1988-11-17 |
EP0290969A3 EP0290969A3 (en) | 1990-03-28 |
Family
ID=11263532
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP88107264A Withdrawn EP0290969A3 (en) | 1987-05-15 | 1988-05-06 | Unfoldable antenna with two reflecting surfaces |
Country Status (2)
Country | Link |
---|---|
EP (1) | EP0290969A3 (en) |
IT (1) | IT1205964B (en) |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3646564A (en) * | 1969-03-03 | 1972-02-29 | Raytheon Co | Antenna slew system |
FR2517626A1 (en) * | 1981-12-04 | 1983-06-10 | Europ Agence Spatiale | ORBITAL SPACE ENGINE, IN PARTICULAR SATELLITE, WITH MULTIPLE MISSIONS |
JPS6051004A (en) * | 1983-08-30 | 1985-03-22 | Nec Corp | Parabolic antenna for loading on artificial satellite |
EP0152221A2 (en) * | 1984-02-09 | 1985-08-21 | THE GENERAL ELECTRIC COMPANY, p.l.c. | An earth terminal for satellite communication systems |
EP0181221A2 (en) * | 1984-11-07 | 1986-05-14 | THE GENERAL ELECTRIC COMPANY, p.l.c. | Reflector Arrangement |
-
1987
- 1987-05-15 IT IT47946/87A patent/IT1205964B/en active
-
1988
- 1988-05-06 EP EP88107264A patent/EP0290969A3/en not_active Withdrawn
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3646564A (en) * | 1969-03-03 | 1972-02-29 | Raytheon Co | Antenna slew system |
FR2517626A1 (en) * | 1981-12-04 | 1983-06-10 | Europ Agence Spatiale | ORBITAL SPACE ENGINE, IN PARTICULAR SATELLITE, WITH MULTIPLE MISSIONS |
JPS6051004A (en) * | 1983-08-30 | 1985-03-22 | Nec Corp | Parabolic antenna for loading on artificial satellite |
EP0152221A2 (en) * | 1984-02-09 | 1985-08-21 | THE GENERAL ELECTRIC COMPANY, p.l.c. | An earth terminal for satellite communication systems |
EP0181221A2 (en) * | 1984-11-07 | 1986-05-14 | THE GENERAL ELECTRIC COMPANY, p.l.c. | Reflector Arrangement |
Non-Patent Citations (1)
Title |
---|
PATENT ABSTRACTS OF JAPAN, vol. 9, no. 178 (E-330)[1901], 23rd July 1985; & JP-A-60 051 004 (NIPPON DENKI K.K.) 22-03-1985 * |
Also Published As
Publication number | Publication date |
---|---|
EP0290969A3 (en) | 1990-03-28 |
IT1205964B (en) | 1989-04-05 |
IT8747946A0 (en) | 1987-05-15 |
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Legal Events
Date | Code | Title | Description |
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17P | Request for examination filed |
Effective date: 19900926 |
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17Q | First examination report despatched |
Effective date: 19921002 |
|
STAA | Information on the status of an ep patent application or granted ep patent |
Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN |
|
18D | Application deemed to be withdrawn |
Effective date: 19930213 |