EP0286716A2 - An antenna system for exoatmospheric missiles - Google Patents
An antenna system for exoatmospheric missiles Download PDFInfo
- Publication number
- EP0286716A2 EP0286716A2 EP87113224A EP87113224A EP0286716A2 EP 0286716 A2 EP0286716 A2 EP 0286716A2 EP 87113224 A EP87113224 A EP 87113224A EP 87113224 A EP87113224 A EP 87113224A EP 0286716 A2 EP0286716 A2 EP 0286716A2
- Authority
- EP
- European Patent Office
- Prior art keywords
- antenna system
- antenna
- base member
- shield
- feeder
- 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- Withdrawn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
- 229940020445 flector Drugs 0.000 claims abstract description 4
- 239000002184 metal Substances 0.000 claims description 5
- 229920000271 Kevlar® Polymers 0.000 claims description 2
- 230000009975 flexible effect Effects 0.000 claims description 2
- 239000004761 kevlar Substances 0.000 claims description 2
- 239000000463 material Substances 0.000 claims description 2
- 229920002994 synthetic fiber Polymers 0.000 claims 2
- 206010009192 Circulatory collapse Diseases 0.000 abstract 1
- 230000002411 adverse Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000009987 spinning Methods 0.000 description 1
Images
Classifications
-
- 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
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q1/00—Details of, or arrangements associated with, antennas
- H01Q1/08—Means for collapsing antennas or parts thereof
-
- 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
- H01Q1/281—Nose antennas
Definitions
- This invention relates to an antenna system for exoatmospheric seekers, for use in exoatmospheric missiles.
- the seeker is provided with an antenna for receiving and possibly transmitting electromagnetic waves. Since a high tracking accuracy and a high angular discrimination are required, the antenna should be as large as possible, since the accuracy increases with the antenna surface.
- the physical size, and more particularly the diameter, of the missile body has placed a limit on the effective size, or diameter,of the antenna, and therefore on its performance (beam width, side lobes, gain, etc.), because, as well known, the antenna specifications depend to a large extent on such parameter (for instance, the beam width, for a given tapering and operating frequency, is inversely proportional to the antenna diameter).
- a main object of the invention is to provide an antenna system for seekers for exoatmospheric missiles which overcomes the problem of size limitation and has an improved performance over prior antennas installed on missiles.
- an antenna system for seekers for exoatmospheric missiles comprising:
- a substantially cylindrical seeker missile 10 is propelled by a rocket engine 12.
- seeker 10 is provided with a ring-shaped base member 14, rotatably mounted on a fixed member 16 that is rigidly attached at the forward tip of the missile body.
- Base member 14 is provided with a set of peripherally distributed nozzles 18, inclined with respect to the radial direction, and adapted to be supplied with compressed air by means not shown, when it is desired to activate the antenna to its operative condition, as explained below.
- an antenna feeder extends axially and forwardly to the missile, and comprises a waveguide 20 terminating in a conventional inverted horn 22 for radiating electromagnetic waves generally in the direction of the arrows in Fig. 2.
- the waveguide is connected to radio receiving and or transmitting means (not shown) located within the missile body.
- the reflector is folded down, or packed to a furled, unoperative condition around the axial feeder 20, 22.
- a rigid shield preferably comprising two sections or cheeks 26, 28 extends around and encloses the furled reflector and is adapted to be released and discarded when the missile has exited the atmosphere and is flying in exoatmospheric space.
- the reflector can spread to a diameter several times as large as the diameter of the mis sile body, without any adverse effect either on the behaviour of the missile or on the integrity of the antenna system.
- Fig. 4 shows an alternative embodiment of an extendable antenna system according to the invention.
- the reflector is a conical metal sheet 30 that is normally coiled up in a furled, unoperative condition, as shown in full lines on the Figure. When the reflector is required to become operative, metal sheet 30 is released to spread out to its extended condition, as shown in dotted lines.
- the feeder in this case is a slotted waveguide 32.
Landscapes
- Physics & Mathematics (AREA)
- Electromagnetism (AREA)
- Engineering & Computer Science (AREA)
- Astronomy & Astrophysics (AREA)
- Aviation & Aerospace Engineering (AREA)
- General Physics & Mathematics (AREA)
- Remote Sensing (AREA)
- Details Of Aerials (AREA)
- Support Of Aerials (AREA)
- Aerials With Secondary Devices (AREA)
Abstract
Description
- This invention relates to an antenna system for exoatmospheric seekers, for use in exoatmospheric missiles.
- It is known to use seeker missiles for seeking and tracking objects in exoatmospheric environment. To such purpose, the seeker is provided with an antenna for receiving and possibly transmitting electromagnetic waves. Since a high tracking accuracy and a high angular discrimination are required, the antenna should be as large as possible, since the accuracy increases with the antenna surface. However, the physical size, and more particularly the diameter, of the missile body has placed a limit on the effective size, or diameter,of the antenna, and therefore on its performance (beam width, side lobes, gain, etc.), because, as well known, the antenna specifications depend to a large extent on such parameter (for instance, the beam width, for a given tapering and operating frequency, is inversely proportional to the antenna diameter).
- On the other hand, in an exoatmospheric environment there are no stringent aerodynamic requirements for moving objects, so that non-aerodynamic shapes, such as antennas without a radome or other protection, are permissible.
-
- Therefore, a main object of the invention is to provide an antenna system for seekers for exoatmospheric missiles which overcomes the problem of size limitation and has an improved performance over prior antennas installed on missiles.
- The invention achieves the above and other objects, such as they will appear from a consideration of the following disclosure, by means of an antenna system for seekers for exoatmospheric missiles, comprising:
- a) an antenna base member bearing an axially oriented antenna feeder;
- b) a rigid, removable shield enclosing the base member and the feeder;
- c) a collapsible antenna reflector connected to the base member, normally enclosed in a collapsed condition within the shield and around the feeder, and adapted to be extended to an operative condition after removal of the shield.
- Preferred embodiment of the invention will now be described with reference to the attached drawings, in which:
- Fig. 1 is a prospective view of a seeker missile incorporating a first embodiment of an antenna system according to the invention, the antenna being in a collapsed unoperative condition;
- Fig. 2 is an axial cross-section of the missile of Fig. 1, with the antenna in an extended, operative condition;
- Fig. 3 is a more detailed, partly diagrammatical, perspective view of the antenna system according to the first embodiment; and
- Fig. 4 is a perspective, partly diagrammatical view of a second embodiment of antenna system according to the invention.
- In Figs. 1 and 2, a substantially
cylindrical seeker missile 10, known per se, is propelled by arocket engine 12. At its forward tip,seeker 10 is provided with a ring-shaped base member 14, rotatably mounted on a fixedmember 16 that is rigidly attached at the forward tip of the missile body.Base member 14 is provided with a set of peripherally distributednozzles 18, inclined with respect to the radial direction, and adapted to be supplied with compressed air by means not shown, when it is desired to activate the antenna to its operative condition, as explained below. - From the center of
base member 14, an antenna feeder (see Fig. 2) extends axially and forwardly to the missile, and comprises awaveguide 20 terminating in a conventional invertedhorn 22 for radiating electromagnetic waves generally in the direction of the arrows in Fig. 2. The waveguide is connected to radio receiving and or transmitting means (not shown) located within the missile body. - From the periphery of
base member 14 extends an umbrella-shaped reflector 24 of a flexible, electromagnetically reflective material such as metal-coated kevlar. In Fig. 1 the reflector is folded down, or packed to a furled, unoperative condition around theaxial feeder - A rigid shield preferably comprising two sections or
cheeks - When the shield is released, compressed air is also fed to
nozzles 18, in order to setbase member 14 spinning around its axis, which coincides with the axis of the missile. The centrifugal force thus generated will then spread out the reflector to its extended, operative condition, as shown in Fig. 2 and, with dot-and-dash, on Fig. 3. - Since no aerodynamic requirements are any longer placed on the geometry of the missile now that it is flying in exoatmospheric space, the reflector can spread to a diameter several times as large as the diameter of the mis sile body, without any adverse effect either on the behaviour of the missile or on the integrity of the antenna system.
- The release of the shield and the ejection of compressed air from the nozzles in the base member of the antenna reflector are started by a command that is part of the control system of the missile, and is beyond the scope of the invention.
- Fig. 4 shows an alternative embodiment of an extendable antenna system according to the invention. The reflector is a
conical metal sheet 30 that is normally coiled up in a furled, unoperative condition, as shown in full lines on the Figure. When the reflector is required to become operative,metal sheet 30 is released to spread out to its extended condition, as shown in dotted lines. The feeder in this case is aslotted waveguide 32. - Preferred embodiments of the invention have been described, but obviously equivalent changes may be made to them by a person skilled in the art, within the scope of the attached claims.
Claims (6)
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
IT2014787 | 1987-04-16 | ||
IT20147/87A IT1203912B (en) | 1987-04-16 | 1987-04-16 | ANTENNA SYSTEM FOR EXOATMOSPHERIC MISSILES |
Publications (2)
Publication Number | Publication Date |
---|---|
EP0286716A2 true EP0286716A2 (en) | 1988-10-19 |
EP0286716A3 EP0286716A3 (en) | 1988-11-30 |
Family
ID=11164185
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP87113224A Withdrawn EP0286716A3 (en) | 1987-04-16 | 1987-09-10 | An antenna system for exoatmospheric missiles |
Country Status (3)
Country | Link |
---|---|
EP (1) | EP0286716A3 (en) |
CA (1) | CA1285649C (en) |
IT (1) | IT1203912B (en) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2867616A1 (en) * | 2004-03-11 | 2005-09-16 | Commissariat Energie Atomique | Radio-electric illuminating system for e.g. terrestrial application, has electromagnetic waves reflector including flexible and deployable support structure e.g. canopy system of parachute, to which reflecting units are integrated |
US10353064B2 (en) | 2016-05-26 | 2019-07-16 | Decisive Analytics Corporation | Method and apparatus for detecting airborne objects |
CN112086726A (en) * | 2020-08-26 | 2020-12-15 | 扬州船用电子仪器研究所(中国船舶重工集团公司第七二三研究所) | Antenna structure adopting worm and gear transmission for expansion |
Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2750321A (en) * | 1951-09-04 | 1956-06-12 | Raymond De Icer And Engineerin | Antennas and material for fabrication thereof |
US3176303A (en) * | 1962-02-21 | 1965-03-30 | Whittaker Corp | Collapsible antenna with plurality of flexible reflector petals releasably retained |
US3286259A (en) * | 1964-04-30 | 1966-11-15 | Goodyear Aerospace Corp | Unfurlable reflector |
GB1544815A (en) * | 1974-12-21 | 1979-04-25 | Messerschmitt Boelkow Blohm | Carbon-fibre-reinforced plastics laminate |
-
1987
- 1987-04-16 IT IT20147/87A patent/IT1203912B/en active
- 1987-08-05 CA CA000543805A patent/CA1285649C/en not_active Expired - Lifetime
- 1987-09-10 EP EP87113224A patent/EP0286716A3/en not_active Withdrawn
Patent Citations (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2750321A (en) * | 1951-09-04 | 1956-06-12 | Raymond De Icer And Engineerin | Antennas and material for fabrication thereof |
US3176303A (en) * | 1962-02-21 | 1965-03-30 | Whittaker Corp | Collapsible antenna with plurality of flexible reflector petals releasably retained |
US3286259A (en) * | 1964-04-30 | 1966-11-15 | Goodyear Aerospace Corp | Unfurlable reflector |
GB1544815A (en) * | 1974-12-21 | 1979-04-25 | Messerschmitt Boelkow Blohm | Carbon-fibre-reinforced plastics laminate |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2867616A1 (en) * | 2004-03-11 | 2005-09-16 | Commissariat Energie Atomique | Radio-electric illuminating system for e.g. terrestrial application, has electromagnetic waves reflector including flexible and deployable support structure e.g. canopy system of parachute, to which reflecting units are integrated |
US10353064B2 (en) | 2016-05-26 | 2019-07-16 | Decisive Analytics Corporation | Method and apparatus for detecting airborne objects |
CN112086726A (en) * | 2020-08-26 | 2020-12-15 | 扬州船用电子仪器研究所(中国船舶重工集团公司第七二三研究所) | Antenna structure adopting worm and gear transmission for expansion |
Also Published As
Publication number | Publication date |
---|---|
IT1203912B (en) | 1989-02-23 |
EP0286716A3 (en) | 1988-11-30 |
CA1285649C (en) | 1991-07-02 |
IT8720147A0 (en) | 1987-04-16 |
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17P | Request for examination filed |
Effective date: 19890421 |
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17Q | First examination report despatched |
Effective date: 19910506 |
|
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: 19910917 |
|
RIN1 | Information on inventor provided before grant (corrected) |
Inventor name: RIOLI, QUINIRO |