|Publication number||US3805266 A|
|Publication date||Apr 16, 1974|
|Filing date||Sep 27, 1972|
|Priority date||Sep 27, 1972|
|Publication number||US 3805266 A, US 3805266A, US-A-3805266, US3805266 A, US3805266A|
|Inventors||Fletcher J, Munson R|
|Export Citation||BiBTeX, EndNote, RefMan|
|Patent Citations (4), Referenced by (22), Classifications (11)|
|External Links: USPTO, USPTO Assignment, Espacenet|
United States Patent [191 Fletcher et al.
[ 4] TURNSTILE SLOT ANTENNA  Inventors: James C. Fletcher, Administrator of the National Aeronautics and space Administration with respect to an invention of; Robert E. Munson, Salt Lake City, Utah 221 Filed: Sept. 27, 1972 21 Appl. No; 292,685
 US. Cl 343/708, 343/769, 343/853  Int. Cl. H0lq 1/28  Field of Search 343/DIG. 2, 705, 708, 769,
 References Cited UNITED STATES PATENTS 3,226,720 12/1965 Brunner et al 343/708 3,182,326 5/1965 Cutler 3 ,005,986 Reed Munson 343/708 [111 3,805,266 Apr. 16, 1974 Primary Examiner-Eli Lieberman Attorney, Agent, or Firm-R. F. Kempf; John R.
Manning 57 ABSTRACT A novel turnstile slot antenna is disclosed, the antenna being for and integral with a spacecraft having a substantially cylindrical body portion. The antenna comprises a circumferential slot about the periphery of the spacecraft body portion with an annular wave guide cavity defining a radial transmission line disposed Within the spacecraft body portion behind and in communication with the circumferential slot. Feed stubs and associated transmission apparatus are provided to excite the annular cavity in quadrature phase such 7 that an omnidirectional, circularly polarized, rotating radiation pattern is generated. The antenna of the instant invention has utility both as a transmitting and receiving device, and ensures continuous telemetry and command coverage with the spacecraft.
7 Claims, 3 Drawing Figures TRAN SMWTER i MTENTEDAPR 16 I57 I sum 2- or 2 TRAN SMWTER 1 TURNSTILE SLOT ANTENNA ORIGIN OF THE INVENTION The invention described herein was made in the performance of work under a NASA contract and is subject to the provisions of Section 305 of the National Aeronautics and Space Act of 1958, Public Law 85-568 (72 STAT. 435; 42 USC 2457).
BACKGROUND OF THE INVENTION This invention generally relates to antenna systems and particularly concerns an antenna system for and integral with spacecraft or missles so as to ensure telemetry and command coverage.
Difficulties are oftentimes encountered in effecting acceptable communication between ground tracking or command stations'and missles or other spacecraft during flight. In this respect, the spin rate associated with such spacecraft vehicles, as well as the trajectory or flight path, are such that the spacecraft or vehicle presents different angles of orientation at different times with respect to the ground tracking and/or command post. These constant changes in relative orientation of the vehicle in flight poses extreme demands on the spacecraft antenna system, which system must be capable of both receiving and sending radio information during all different physical orientations of the spacecraft, i.e., through all possible look angles.
Prior art spacecraft antenna structures generally have not satisfied these stringent requirements. For example, the type of radiation pattern required is omnidirectional and, from the standpoint of electromagnetic theory, the type of antenna necessary to generate this requisite omnidirectional pattern is what is termed a turnstile antenna which, in its classic physical embodiment, comprises two mutually perpendicular dipoles fed 90 out-of-phase. In addition to an omnidirectional power pattern coverage, the classic turnstile antenna, in theory, provides circular field polarization, a zero decibel roll pattern variation, and no roll polarization, all these attributes being extremely useful in spacecraft communication. Yet, the classic turnstile antenna does not live up to its promise in that it does not maintain theoretical operation when on or in close proximity to a spacecraft.
BRIEF SUMMARY OF THE INVENTION It is still another objective of the instant invention to provide an antenna structure or assembly which generates a substantially omnidirectional radiation pattern whereby continuous telemetry and command coverage can be effected.
It is still another objective of the instant invention to provide a spacecraft antenna assembly which does not exhibit rapid polarization switching due to vehicle spin.
A further objective of the instant invention concerns the provision of a novel antenna structure providing high gain at substantially all look angles."
Yet another objective of the instant invention concerns the provision of a novel spacecraft or missle turnstile antenna which generates an extremely smooth power radiation pattern.
These objectives, as well as others which will become apparent as the description proceeds, are implemented by the novel invention which, as afore-stated, comprises a turnstile slot antenna of novel construction, the antenna being for and integral with-a spacecraft having a substantially cylindrical body portion. In the preferred inventive embodiment,- the'antenna comprises a circumferential slot about the periphery of the spacecraft body portion with anannular wave guide cavity defining a radial tranmission line disposed within the spacecraft body portion behind and in communication with the circumferential slot. In the preferred inventive embodiment, the annular wave guide cavity has a shorted innermost wall and is constructed to have an electrical length of approximately one-quarter the wave length of the excitation frequency. The annular cavity of the antenna is excited in quadrature phase by cumference of the cavity and just inside the circumferential slot. With this placement of the feed stub, the
short circuit defined by the innermost wall of the cavity is electrically transformed to an open circuit whereby radiation is generated outwardly through the circumferential slot. Specifically, it will be seen that the radiation pattern generated is omnidirectional, circularly polarized, and defines a rotating field.
In the preferred inventive embodiment, the annular cavity is filled with a dielectric plastic honeycomb structure for strength, and the circumferential slot itself may be physically closed with a Teflon plug or seal. Tuning of the novel antenna of the instant invention is effected by the placement of a matching or tuning stub adjacent each of the feed stubs within the annular cavity.
BRIEF DESCRIPTION OF THE DRAWINGS The invention itself will be better understood, and features, and advantages thereof .in addition to those above-described, will become apparent from the following detailed description of the preferred inventive embodiment, such description making reference to the appended sheets of drawings, wherein:
FIG. 1 is a perspective illustration of a typical spacecraft or other vehicle employing the turnstile slot antenna of the instant invention as an integral part thereof;
FIG. 2 is an elevational view of the turnstile slot antenna of the instant invention, partially in section forillustrative clarity, taken along lines 2-2 of FIG. 1; and
FIG. 3 is a top plan view of the turnstile slot antenna of the instant invention taken along lines 3-3 of FIG. 3, and further schematically illustrating the electrical feed means utilized therewith to excite the antenna with quadrature phase.
DETAILED DESCRIPTION OF A PREFERRED INVENTIVE EMBODIMENT Referring now to the drawings, and particularly to FIG. 1 thereof, the integral construction of the turnstile slot antenna of the instant invention with a typical spacecraft having a substantially cylindrical body portion is shown. The spacecraft generally designated by reference numeral may comprise an orbiting satellite such as the so-called H-model orbiting solar observatory satellite. The spacecraft will be seen to typically include a plurality of solar cell panels 12, an instrument package 14, and a skirt sub-assembly or substantially cylindrical body portion 16. In the illustrated embodiment, body portion 16, while substantially cylindrical, is constructed as a polygon having a plurality of flat panels 18, as shown.
A circumferential slot generally designated by reference numeral is disposed about the periphery of the substantially cylindrical spacecraft body portion 16, this circumferential slot being filled, for example, with a dielectric material such as plastic and defining the radiation surface through which the radiation pattern of the novel antenna is generated.
Referring now to FIGS. 2 and 3 of the appended drawings, the detailed construction of the turnstile slot antenna of the instant invention can be seen. Specifically, an annular wave guide cavity designated by reference numeral 22 and defining a radial transmission line is disposed within the spacecraft body portion 16 behind and in comunication with the circumferential slot 20. The upper and lower walls, 24 and 26, respectively, of the annular wave guide cavity 22 are constructed of a thin sheet of metal, and it should be noted that the innermost wall or hub comprises a circular metallic disc 28 defining an electrical short circuit. As discussed above, the outermost wall of the annular cavity 22 is defined by the circumferential slot about the periphery of the spacecraft body portion 16 any may be filled with a plastic dielectric material such as is indicated at reference numeral 30.
The novel antenna of the instant invention includes a mean to excite the annular cavity 22 in quadrature phase and, to this end, four equally spaced electrical feed stubs 32 are disposed about the circumference of the annular cavity 22 just inside the circumferential slot 20, each feed stub 32 being excited in quadrature phase such as with the schematically illustrated transmitter and phase-shifting apparatus shown in FIG. 3, and designated by reference numeral 34. In the preferred inventive embodiment, a dielectric honeycomb filler designated by reference numeral 34 is disposed throughout the annular cavity 22 so as to provide strength, and the like. The preferred inventive embodiment of the novel antenna will be seen to further include a tuning stub 36 disposed in the annular cavity 22 adjacent each feed stub. The tuning stub 36 provides a capacitive coupling between the upper and lower walls 24 and 26, respectively, of the annular wave guide cavity 22. Each of the tuningstubs 36 and feed stubs 32 are preferably disposed at an equal radius from the center or hub of the annular cavity 22 and, in the preferred inventive embodiment, annular cavity 22 is contemplated to have a length or radial dimension approximating one-quarter wave length of the excitation frequency. With this construction, the electrical short circuit provided by the metal disc 28 at the innermost wall of the annular cavity 22 is electrically transformed to an open circuit,
thus ensuring outward radiation through the circumferential slot 20.
In operation of the novel turnstile slot antenna as above-described, an omnidirectional, circularly polarized, rotating radiation pattern is generated in an outward direction, the electric field E of the generated radiation pattern being oriented in a direction parallel to the cylindrical axis of the spacecraft body portion. Since the radiation pattern is omnidirectional in the form of a sphere, telecommunication between the ground station and the spacecraft can readily and continuously be effected, regardless of spacecraft orientation, and regardless of spin of the spacecraft.
From the foregoing detailed description, it should therefore be apparent that all the objectives set forth at the outset of this specification have been successfully achieved. Moreover, while there has been shown and described a present preferred embodiment of the invention, it is to be distinctly understood by those skilled in the art that the invention is not limited thereto, but may otherwise be variously embodied and practiced within the scope of the following claims. Accordingly,
What is claimed is:
l. A turnstile slot antenna for and integral with a spacecraft having a substantially cylindrical body portion, said antenna comprising a continuous circumferential slot about the periphery of said spacecraft body portion, an annular wave guide cavity defining a continuous radial transmission line disposed within said spacecraft body portion aligned radially within said circumferential slot and in communication with said circumferential slot and having a coaxial width no greater than the coaxial width of said circumferential slot, the depth of the cavity being greater than the width and means to excite said annular cavity in quadrature phase comprising four electrical feed stubs equally spaced about the circumference of said annular cavity inside said circumferential slot and projecting from a sidewall thereof, whereby an omnidirectional circularly polarized rotating radiation pattern is generated.
2. An antenna as defined in claim 1, wherein the electrical length of said annular cavity from circumferential slot to the innermost wall of the annular cavity approximates one-quarter wave length of the excitation frequency, the innermost wall of the cavity defining an electrical short circuit.
3. An antenna as defined in claim 2, further including a dielectric honeycomb filler disposed throughout said annular cavity.
4. An antenna as defined in claim 3, wherein said filler is constructed of plastic material.
5. An antenna as defined in claim 2, further including a tuning stub disposed in said annular cavity adjacent each feed stub.
6. An antenna as defined in claim 5, wherein each said tuning stub is capacitive.
7. An antenna a defined in claim 1, wherein the electric field E of the generated radiation pattern is oriented in a direction parallel to the cylindrical axis of the spacecraft body portion.
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|U.S. Classification||343/708, 343/769, 343/853|
|International Classification||H01Q21/26, H01Q1/28, H01Q1/27, H01Q21/24|
|Cooperative Classification||H01Q21/26, H01Q1/288|
|European Classification||H01Q21/26, H01Q1/28F|