US3460148A - Antenna for space vehicle - Google Patents

Antenna for space vehicle Download PDF

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Publication number
US3460148A
US3460148A US512394A US3460148DA US3460148A US 3460148 A US3460148 A US 3460148A US 512394 A US512394 A US 512394A US 3460148D A US3460148D A US 3460148DA US 3460148 A US3460148 A US 3460148A
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US
United States
Prior art keywords
antenna
satellite
despun
platform
spin
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
Application number
US512394A
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English (en)
Inventor
Emeric I Podraczky
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.)
International Telecommunications Satellite Organization
Original Assignee
Comsat 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 Comsat Corp filed Critical Comsat Corp
Application granted granted Critical
Publication of US3460148A publication Critical patent/US3460148A/en
Assigned to INTERNATIONAL TELECOMMUNICATIONS SATELLITE ORGANIZATION, reassignment INTERNATIONAL TELECOMMUNICATIONS SATELLITE ORGANIZATION, ASSIGNMENT OF ASSIGNORS INTEREST. Assignors: COMMUNICATION SATELLITE CORPORATION
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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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
    • H01Q1/08—Means for collapsing antennas or parts thereof
    • H01Q1/084—Pivotable 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
    • 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
    • H01Q25/00—Antennas or antenna systems providing at least two radiating patterns
    • H01Q25/002—Antennas or antenna systems providing at least two radiating patterns providing at least two patterns of different beamwidth; Variable beamwidth antennas

Definitions

  • a spin-stabilized space satellite may be defined as one which is spun about its axis to prevent change in its attitude with relation to the earth axis. Such attitude change would, in the absence of such a spinning arrangement, take place as a result of tumbling of the satellite.
  • a spin-stabilized space satellite is the synchronous satellite Syncom. Such a satellite is controllably positioned in inertial space at a fixed point with relation to the earth. Its radial velocity is the same as that of the earth. In order to prevent tumbling or change in its attitude, a spin is imparted to the satellite.
  • the spin imparting means does not form a part of this invention but for background information this spinning is imparted by the launch vehicle whereby when the satellite is injected into its orbit, it is spinning or rotating about its axis at a speed which may be between 100 and 150 revolutions.
  • This spin rate is of course defined with relation to inertial space.
  • Mechanically associated with the spin-stabilized space satellite is an antenna platform on which an antenna is mounted. This platform may be mounted to the satellite by means such as low-friction bearings.
  • a suitable despinning motor mounted in the satellite and mechanically connected to the antenna may be provided. This motor functions to prevent the antenna platform and therefore the antenna from spinning at the spin rate of the satellite.
  • the platform is identified as despun and the antenna identified as operating in its despun mode.
  • the radio frequency energy pattern of the antenna is fixed with relation to the earth and has its major axis fixed with relation to a point on the earth during the orbit of the satellite.
  • the motor rotates the antenna platform in a direction opposite to the direction of rotation of the satellite at a speed equal to the rotational speed of the satellite less one revolution per orbit.
  • the present invention provides means by which the energy pattern of the antenna switches from the despun mode (pencil beam) to an omni mode (toroidal beam).
  • the energy pattern is a conventional lobe having its major axis directed toward the earth.
  • the pattern may be substantially doughnut shaped, that is, radiating substantially equally in the directions perpendicular to the spin axis.
  • the present invention relates to a fail safe antenna device for spin-stabilized space satellites in which the omni mode antenna energy pattern is automatically achieved upon failure of the despinning motor by direction or by accident. This is done by taking advantage of the centrifugal forces which are produced when the antenna rotates at the spin rate of the satellite due to despinning motor failure. These forces, acting upon the antenna device, change its physical arrangement and more particularly its reflector orientation to achieve the omni mode type of operation. Of course, de-energizing of the despinning motor will result in the antenna platform and consequently the antenna with associated reflectors rotating at the same speed as the satellite.
  • the active first position referred to in which the antenna array normally finds itself is of course the despun mode and the passive second position is of course the omni mode.
  • FIGURE 1 is a perspective view of a spin-stabilized satellite showing the normally despun section including the antenna with reflector and associated RF transparent cylinder, during a despun type of operation;
  • FIGURE 2 is similar to FIGURE 1, but representing the omni mode type of operation;
  • FIGURE 3 is similar to FIGURE 2, but illustrating a different type of antenna reflector and transparent means
  • FIGURE 4 is similar to FIGURE 3, but representing a despun mode type of operation
  • FIGURE 5 is a perspective view of an antenna device but illustrating a diiferent type of reflector and transparent means operating in the despun mode;
  • FIGURE 6 is similar to FIGURE 5, but representing an omni mode type of operation.
  • FIGURE 1 represents a spin-stabilized satellite 10 with antenna platform 11 mounted by bearing means 12 to the satellite. Mounted by spring-loaded hinges 16 to the platform 11 are the metallic parabolic reflector 14 and the RF transparent parabolic cylinder 15. The antenna is identified at 13. The platform 11 is mounted by some conventional means to a despinning motor (not shown) carried by the satellite.
  • FIGURE 1 is illustrative of the despun mode type of operation in which the members 14 and 15 are biased by the springs 16 toward their active first position (the despun mode) and away from a passive second position (omni mode). Since the despinning motor substantially prevents spinning of the platform with relation to inertial space, the antenna device does not generate a significant amount of centrifugal force.
  • springs are illustrative only. Any mechanical means performing a similar function may be employed. In fact, arrangements such as shown in FIGURES 3 through 6 may be employed.
  • FIGURE 3 there is shown a satellite 10 operating in the omni state.
  • the antenna 13 is in this figure associated with flexible metallic wire reflectors 17 and flexible RF transparent wires 18.
  • the de-energizing of the despinning motor causes the antenna platform and device to rotate with the satellite and to generate centrifugal force whereby these Wires move from the despun mode as shown in FIGURE 4 to the omni mode shown in FIGURE 3.
  • FIGURES 5 and 6 illustrate respectively despun mode and omni mode types of operation in which the reflectors are constituted of a plurality of flexible metallic petals :19 and the RF transparent means is in the form of a parabolic supporting cylinder 20.
  • the specific type of antenna array, reflector or RF transparent means is not critical to the invention.
  • the metallic reflector may be of any suitable type commonly used in the art and the RF transparent means may be made of Fiberglas.
  • the flexible metallic wires referred to in FIGURES 3 and 4 may be of conventional beryllium-copper type. This is also true in connection with the flexible metallic petals shown in FIGURES 5 and 6.
  • the bearing means by which the antenna platform is mounted to the satellite may be conventional. These bearings should be as frictionless as possible.
  • the despinning motor mounted within the satellite and connected to the antenna platform may also be conventional and forms no part of this invention.
  • the functioning of the RF transparent member is only for dynamic balancing purposes.
  • a fail safe antenna device for a spin-stabilized space satellite having a normally despun section comprising: a radiator/collector member mounted on the despun section and wave reflector means mounted on the despun section adjacent the radiator-collector member and biased toward an active first position and away from a passive second position whereby centrifugal force overcomes the biasing to move the reflector means to the passive second position whenever the normal despun section rotates with the satellite.
  • a fail safe antenna device as claimed in claim 1 wherein said normally despun section comprises a platform means for carrying said radiator/ collector member, and substantially frictionless bearing means mounting said platform to said satellite.
  • a fail safe antenna device as claimed in claim 3 further including hinge means connecting said platform and said wave reflector means.
  • a fail safe antenna device as claimed in claim 1 further including an RF transparent means mounted to said despun section adjacent said radiator/collector oriented opposite to said wave reflector means.

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  • Engineering & Computer Science (AREA)
  • Remote Sensing (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Details Of Aerials (AREA)
  • Aerials With Secondary Devices (AREA)
US512394A 1965-12-08 1965-12-08 Antenna for space vehicle Expired - Lifetime US3460148A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US51239465A 1965-12-08 1965-12-08

Publications (1)

Publication Number Publication Date
US3460148A true US3460148A (en) 1969-08-05

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Family Applications (1)

Application Number Title Priority Date Filing Date
US512394A Expired - Lifetime US3460148A (en) 1965-12-08 1965-12-08 Antenna for space vehicle

Country Status (3)

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US (1) US3460148A (fr)
FR (1) FR1502296A (fr)
GB (1) GB1094424A (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2417220A1 (fr) * 1978-02-09 1979-09-07 Thomson Csf Poste emetteur et/ou recepteur a deux diagrammes de rayonnement et reseau equipe de tels postes
US20110175604A1 (en) * 2010-01-15 2011-07-21 Vale S.A. Stabilization system for sensors on moving platforms

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3303547A1 (de) * 1983-02-03 1984-08-09 Karl 3340 Wolfenbüttel Grölich Windkraftaggregat
GB2202090A (en) * 1987-01-21 1988-09-14 Laurence Robert Wilson Tennant Directionally-stabilised reflector

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3341151A (en) * 1965-07-23 1967-09-12 Kampinsky Abe Apparatus providing a directive field pattern and attitude sensing of a spin stabilized satellite

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3341151A (en) * 1965-07-23 1967-09-12 Kampinsky Abe Apparatus providing a directive field pattern and attitude sensing of a spin stabilized satellite

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2417220A1 (fr) * 1978-02-09 1979-09-07 Thomson Csf Poste emetteur et/ou recepteur a deux diagrammes de rayonnement et reseau equipe de tels postes
US20110175604A1 (en) * 2010-01-15 2011-07-21 Vale S.A. Stabilization system for sensors on moving platforms
US8456159B2 (en) * 2010-01-15 2013-06-04 Vale S.A. Stabilization system for sensors on moving platforms

Also Published As

Publication number Publication date
FR1502296A (fr) 1967-11-18
GB1094424A (en) 1967-12-13
DE1541471B2 (de) 1975-09-18
DE1541471A1 (de) 1969-07-17

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Legal Events

Date Code Title Description
AS Assignment

Owner name: INTERNATIONAL TELECOMMUNICATIONS SATELLITE ORGANIZ

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST.;ASSIGNOR:COMMUNICATION SATELLITE CORPORATION;REEL/FRAME:004114/0753

Effective date: 19820929