Patent Grant
10957987
The present invention relates to the field of antennas, and more particularly, to an inflatable antenna for a spacecraft and related methods.
Deployable antennas are highly desirable in satellite and other space applications. In such applications, it is important for an antenna to be able to fit into a small space, but also be expandable to a fully operational size once orbit has been achieved.
The issue of antenna deployability is especially critical as the size of satellites get smaller. While the sensors and operating electronics of miniaturized satellites can be scaled to extremely small volumes, the wavelengths of the signals used by such miniaturized satellites to communicate do not scale accordingly. Given that the wavelength of a signal determines the size of an antenna used to communicate that signal, antennas for miniaturized satellites still have dimensions similar to those of larger satellites.
One approach for a space deployable antenna is disclosed in U.S. Pat. No. 6,791,510 where the antenna includes an inflatable structure, a plane antenna supported by the inflatable structure and a plurality of tensioning cables for supporting the plane antenna with the inflatable structure. When the antenna is initially placed in a satellite that is to be launched, the plane antenna and the inflatable structure are both stored inside a rocket fairing in their rolled or folded states. After the rocket is launched and the antenna is set on its satellite orbit, a gas or a urethane foam is filled into the inflatable structure to deploy the inflatable structure to its shape. The plane antenna, which is in the rolled or folded state, is extended and the tensioning cables pull uniformly on the membrane surface periphery of the plane antenna to extend it into a flat plane without distortions.
Yet another approach for an inflatable antenna is disclosed in U.S. published patent application no. 2014/0028532. The inflatable antenna includes an inflatable dish with a RF reflective main reflector and an opposing RF transparent dish wall. An inflatable RF transparent support member and an RF reflective subreflector extend from the dish wall. When the antenna is inflated, the main reflector and the subreflector oppose each other to reflect RF energy toward each other to form an antenna. A gas or a hardening foam may be used to fill the inflatable antenna.
Even in view of the above described inflatable antennas, there is still a need to reduce the weight of such antennas. For example, the cost/pound to launch a satellite in a low earth orbit (LEO) is about $10,000, whereas the cost/pound for a synchronous orbit is about $20,000. Consequently, any reduction in weight for a spaced based antenna may result in significant cost savings.
In view of the foregoing background, it is therefore an object of the present invention to provide a lightweight inflatable antenna for a spacecraft.
This and other objects, features, and advantages in accordance with the present invention are provided by a space deployable antenna apparatus comprising an inflatable antenna configurable between a deflated storage position and an inflated deployed position and comprising a plurality of collapsible tubular elements coupled together in fluid communication. The plurality of collapsible tubular elements in the deployed position may comprise a longitudinally extending boom tubular element, at least one driven tubular conductive element transverse to said boom tubular element, at least one reflector tubular conductive element transverse to said boom tubular element, and at least one director tubular conductive element transverse to said boom tubular element. A foam dispenser may be configured to inject a solidifiable foam into the inflatable antenna to configure to the inflated deployed position.
An advantage of the foam filled inflatable antenna is that it is light weight as well as low cost. In addition, the inflatable antenna in the inflated deployed position is not impacted by rigid dimensional requirements.
The at least one driven tubular conductive element may comprise a dielectric tube and a pair of spaced apart conductive layers thereon, with each conductive layer having an antenna feed point. The space deployable antenna apparatus may further comprise a coaxial cable having inner and outer conductors coupled to respective ones of the antenna feed points.
The at least one reflector tubular conductive element may comprise a dielectric tube and a conductive layer thereon. Similarly, the at least one director tubular conductive element may comprise a dielectric tube and a conductive layer thereon.
The at least one driven tubular conductive element, the at least one reflector tubular conductive element and the at least one director tubular conductive element may be coplanar with each other when the inflatable antenna is in the deployed position.
The foam dispenser may comprise first and second foam component supplies. The space deployable antenna apparatus may further comprise a mixing valve coupled between the first and second foam component supplies and the inflatable antenna.
The plurality of collapsible tubular elements may comprise a biaxially-oriented polyethylene terephthalate (BoPET) film or a polyimide film, for example.
Another aspect is directed to a spacecraft comprising a transceiver, and a space deployable antenna apparatus coupled to the transceiver, as described above.
Yet another aspect is directed to a method for deploying an inflatable antenna in space. The method may comprise initially storing the inflatable antenna in a deflated storage position within the spacecraft. When in space, a solidifiable foam may be injected from the foam dispenser into the inflatable antenna to configure to an inflated deployed position, with the plurality of collapsible tubular elements being coupled together in fluid communication in the deployed position. The tubular elements may comprise a longitudinally extending boom tubular element, at least one driven tubular conductive element transverse to the boom tubular element, at least one reflector tubular conductive element transverse to the boom tubular element, and at least one director tubular conductive element transverse to the boom tubular element.
The present invention will now be described more fully hereinafter with reference to the accompanying drawings, in which preferred embodiments of the invention are shown. This invention may, however, be embodied in many different forms and should not be construed as limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art. Like numbers refer to like elements throughout.
Referring initially to
In the deflated storage position, the inflatable antenna 32 is rolled or folded up as illustrated in
For the foam dispenser 40, a two-part foam may be used. In the illustrated embodiment, the foam dispenser 40 includes a first foam component supply 42 and a second foam component supply 44. A mixing valve 46 is coupled between the foam dispenser 40 and the inflatable antenna 32. The mixing valve 46 is used to mix together the contents of the first and second foam component supplies 42, 44.
The first and second foam component supplies 42, 44 may include different organic silicons, such as organopolyhydroxy siloxane and organopolyhydrogen siloxane, for example. In addition, one of the organic silicons has a catalyst mixed therein. The catalyst may be platinum, aminoxy or organic tin, for example. When the different organic silicons and the catalyst are mixed together in the mixing valve 46, a chemical reaction occurs. The chemical reaction generates hydrogen bubbles which causes the liquid silicon foam to expand.
When the foam dispenser 40 is activated, the contents of the first and second foam component supplies 42, 44 may be pushed by plungers into the mixing valve 46. Depending on the size of the inflatable antenna 32, it may take about 3 to 5 minutes to fill with the liquid foam. Depending on the temperature, it may take about 45 to 60 minutes for the liquid foam to solidify.
As the liquid foam expands, the inflatable antenna 32 begins to roll out and expand to the inflated deployed position. As illustrated in
An advantage of the foam filled inflatable antenna 32 is that it is light weight as well as low cost. In addition, the inflatable antenna 32 in the inflated deployed position is not impacted by rigid dimensional requirements.
More particularly, the inflatable antenna 32 comprises a plurality of collapsible tubular elements coupled together in fluid communication. The collapsible tubular elements in the deployed position comprise a longitudinally extending boom tubular element 50, at least one driven tubular conductive element 54 transverse to the boom tubular element, at least one reflector tubular conductive element 52 transverse to the boom tubular element, and at least one director tubular conductive element 56 transverse to the boom tubular element.
In the illustrated embodiment there are 6 director tubular conductive elements 56. As the number of conductive elements 56 increases, so does the gain of the Yagi-Uda antenna. TABLE 1 provides an approximate gain based on the number of director tubular conductive elements 56. The actual number of director tubular conductive elements 56 will vary depending on the intended application.
The inflatable antenna 32 is not limited to any particular frequency. The frequency depends on the intended application of the transceiver 20. As an example, the inflatable antenna 32 may be sized to operate at 450 MHz. At this frequency, the longitudinally extending boom tubular element 50 is about 5 feet in length and the reflector tubular conductive element 52 is about 13 inches in length. The length of the driven tubular conductive element 54 is about 12 inches, and the length of the director tubular conductive elements 56 is about 11 inches. A height and width of the boom tubular element 50 and the respective tubular conductive elements 52, 54, 56 are about 0.5 inches and 0.75 inches, respectively.
The inflatable antenna 32 may be formed out of two dielectric films or layers, where each dielectric layer has an outline corresponding to the Yagi-Uda antenna shape, as illustrated in
At least one of the dielectric layers has a plurality of conductive layers thereon. The conductive layers may be aluminum, copper or gold, for example. The conductive layers may be laminated, printed on, or applied with an adhesive onto the dielectric layer, as readily appreciated by those skilled in the art.
Referring now to
Referring now to
When the inflatable antenna 32 is in the deployed position, the driven tubular conductive element 54, the reflector tubular conductive element 52 and the director tubular conductive elements 56 are coplanar with each other.
The dielectric layers of the inflatable antenna 32 may be made out of Mylar™ or Kapton™, for example. Mylar™ is a polyester film, and more particularly, is a biaxially-oriented polyethylene terephthalate (BoPET) film. Kapton™ is a polyimide film and remains stable across a wide range of temperatures, from −269 to +400° C.
Another aspect is directed to a method for deploying an inflatable antenna 32 in space. The method comprises initially storing the inflatable antenna 32 in a deflated storage position within the spacecraft 10. When in space, a solidifiable foam is injected from the foam dispenser 40 into the inflatable antenna 32 to configure to an inflated deployed position, with the plurality of collapsible tubular elements being coupled together in fluid communication in the deployed position. The tubular elements comprise a longitudinally extending boom tubular element 50, at least one driven tubular conductive element 54 transverse to the boom tubular element, at least one reflector tubular conductive element 52 transverse to the boom tubular element, and at least one director tubular conductive element 56 transverse to the boom tubular element.
Many modifications and other embodiments of the invention will come to the mind of one skilled in the art having the benefit of the teachings presented in the foregoing descriptions and the associated drawings. Therefore, it is understood that the invention is not to be limited to the specific embodiments disclosed, and that modifications and embodiments are intended to be included within the scope of the appended claims.
| Number | Name | Date | Kind |
|---|---|---|---|
| 2853706 | Trench et al. | Sep 1958 | A |
| 3202998 | Hoffman | Aug 1965 | A |
| 3364488 | Perenic et al. | Jan 1968 | A |
| 3508270 | Cook | Apr 1970 | A |
| 3530469 | Dailey et al. | Sep 1970 | A |
| 4380013 | Slysh | Apr 1983 | A |
| 4482900 | Bilek | Nov 1984 | A |
| 4825599 | Swann, Jr. | May 1989 | A |
| 5017925 | Bertiger | May 1991 | A |
| 5040918 | Taricco | Aug 1991 | A |
| 5163262 | Adams | Nov 1992 | A |
| 5196857 | Chiappetta | Mar 1993 | A |
| 5313221 | Denton, Jr. | May 1994 | A |
| 5579609 | Sallee | Dec 1996 | A |
| 5886672 | Brune | Mar 1999 | A |
| 5927654 | Foley | Jul 1999 | A |
| 5977932 | Robinson | Nov 1999 | A |
| 5990851 | Henderson | Nov 1999 | A |
| 5992120 | Meguro | Nov 1999 | A |
| 6104358 | Parker | Aug 2000 | A |
| 6219009 | Shipley | Apr 2001 | B1 |
| 6343442 | Marks | Feb 2002 | B1 |
| 6373449 | Bokulic | Apr 2002 | B1 |
| 6512496 | Alexeff | Jan 2003 | B2 |
| 6791510 | Watanabe | Sep 2004 | B2 |
| 6963315 | Gierow | Nov 2005 | B2 |
| 7126553 | Fink | Oct 2006 | B1 |
| 7382232 | Essig, Jr. et al. | Jun 2008 | B2 |
| 7382332 | Essig, Jr. et al. | Jun 2008 | B2 |
| 7694465 | Pryor | Apr 2010 | B2 |
| 8730124 | Behrens et al. | May 2014 | B2 |
| 9214722 | Georgakopoulos et al. | Dec 2015 | B2 |
| 9973266 | Avellan | May 2018 | B1 |
| 20030160733 | Lee | Aug 2003 | A1 |
| 20040037167 | Anderson | Feb 2004 | A1 |
| 20040207566 | Essig, Jr. | Oct 2004 | A1 |
| 20050093754 | Lyons | May 2005 | A1 |
| 20090019784 | Tinker | Jan 2009 | A1 |
| 20090057492 | Harris | Mar 2009 | A1 |
| 20100101172 | Murphy | Apr 2010 | A1 |
| 20120019422 | Gemeny | Jan 2012 | A1 |
| 20140028532 | Ehrenberg | Jan 2014 | A1 |
| 20140263844 | Cook, Jr. | Sep 2014 | A1 |
| 20150086270 | Shany | Mar 2015 | A1 |
| Number | Date | Country |
|---|---|---|
| 1007071 | Oct 1965 | GB |
| H03154502 | Jul 1991 | JP |
| 101393097 | May 2014 | KR |
| Entry |
|---|
| Schnek et al. “Review of Inflatable Booms for Deployable Space Structures: Packing and Rigidization”, Journal of Spacecraft and Rockets, (2014) (Year: 2014). |
| Constantine et al. “Deployable antennas for CubeSat and space communications” 6th European Conference on Antennas and Propagation, EUCAP 2012, pp. 837-840. |
| Lichodziejewski et al. “Inflatably deployed membrane waveguide array antenna for space” American Institue of Aeronautics and Astronautics, Inc. AIAA 2003-1649: pp. 7. |
| Number | Date | Country | |
|---|---|---|---|
| 20180019520 A1 | Jan 2018 | US |
