This invention relates generally to a stackable spacecraft and, more particularly, to a spacecraft including a central cylinder that extends through the spacecraft in an east/west direction relative to a geostationary orbit orientation of the spacecraft, where the cylinder allows the spacecraft to be coupled to other spacecraft also having central cylinders in a single launch fairing.
A vast constellation of spacecraft or satellites orbit the Earth that are employed for many purposes, such as communications purposes, detection purposes, etc., where some of these satellites communicate with each other through satellite cross-link signals and with ground stations through satellite uplink and downlink signals. Some of these satellites are placed in a geostationary orbit above the Earth, where the orbital speed of the satellite and the rotational speed of the Earth cause the satellite to remain above the same location on the Earth.
One specific type of satellite is referred to in the industry as a three-axis satellite, where the satellite body is generally square or rectangular. Solar arrays are often mounted to sides of the satellite that face the north/south direction, referred to as the X-direction, when the satellite is in a geostationary orbit so that when the solar arrays are deployed therefrom they are in a suitable position to be directed towards the sun. The north/south facing sides of the satellite often include a thermal radiator and equipment panel to which various electronics, such as power amplifiers, are mounted to and within the satellite body, where the panels operate as a heat sink and thermal radiator and contain heat pipes to conduct heat. Further, these types of three-axis satellites include a side referred to as the earth deck that faces the Earth in the Y-direction relative to the satellite orbit to which various antennas are mounted, where the opposite surface of the spacecraft is referred to as the zenith deck. In addition, the three-axis satellite includes sides that face the east/west direction, referred to as the Z-direction, relative to the Earth when the satellite is on orbit.
Satellites are constantly being replaced and additional satellites are being added to the constellation as old satellites reach the end of their design lives and new technologies become available. A satellite or spacecraft is typically put into orbit by launching the satellite in a launch fairing on a rocket, where once the rocket reaches a certain altitude, the satellite is released therefrom and on-board propulsion is used to provide the final position of the satellite and the proper orientation relative to the Earth so that the various antennas and other communications devices on the satellite are properly positioned for transmitting and receiving signals.
Launching a spacecraft or satellite in to Earth orbit is expensive, and thus the industry is always attempting to reduce that cost. One way in which the cost of launching a satellite into orbit can be reduced is by launching multiple satellites in a single launch vehicle so that the cost of launching each satellite is spread across all of the satellites. However, as the number of satellites provided in a single launch vehicle goes up, the weight of the launch vehicle also goes up, which also increases the cost.
In order to launch multiple satellites in a common launch vehicle, the satellites need to be mounted to each other or a common structure within the launch vehicle. In one design, multiple satellites are mounted to a common cylindrical dispenser within the launch vehicle that extends through the satellites when in the launch vehicle. Although successful, such a dispenser adds significant weight and volume to the launch vehicle.
It is also known in the art to design a three-axis satellite to have a central cylinder extending therethrough, where that cylinder is coupled to the cylinder of other satellite in the launch vehicle. However, known satellites employing central cylinders orient the cylinder in the Y-direction through the earth deck and the zenith deck of the spacecraft. Because the cylinder extends through the satellite in this direction, there is limited space on the earth deck that could otherwise be used for cross-link antennas, uplink phased arrays (UPA), downlink phased arrays (DPA), gimbal dish antennas (GDA), etc., all of which may be desirable in modern communications geostationary orbiting three-axis satellites. There are also central cylinder stacking-interface related obstructions, which complicate the placement of Earth deck antennas and electronic equipment and interfere with earth deck heat pipe placement and heat removal.
The following discussion of the embodiments of the invention directed to a three-axis spacecraft including a central stacking cylinder oriented in an east/west direction is merely exemplary in nature, and is in no way intended to limit the invention or its applications or uses. It is noted that the terms spacecraft and satellite are used interchangeably herein.
As will be discussed in detail below, the present invention proposes a stackable three-axis spacecraft that includes a central cylinder extending through the spacecraft in an east/west orientation relative to the orbit attitude of the spacecraft that allows the spacecraft to be coupled to the cylinder of other spacecraft to be stowed in a launch vehicle fairing for launch. The spacecraft also includes an earth deck facing the Y-direction of the spacecraft so that it faces the Earth when the spacecraft is on orbit. By providing the center cylinder in a direction other than the Y-direction of the spacecraft, the earth deck has more real-estate for allowing multiple antennas to be mounted thereto for expanded communications purposes. The spacecraft configuration of the present invention also allows a method of stacking where the earth deck and the zenith deck are free of stacking-interface related obstructions or interference. This allows the earth deck and zenith deck to contain heat pipes that are connected to the north/south thermal radiator and equipment panels. This feature of the present invention is particularly advantageous for earth deck mounted active array antennas because heat generated in the array antennas can be transferred through the earth deck into the north and south thermal radiator and equipment panels where it is radiated into space.
The spacecraft body 12 includes a side panel or wall at each of the six sides of the body 12, where one of the side walls facing the Z-direction has been removed so as to expose the cylinder 14 extending through the body 12. In the orientation shown in
The spacecraft 10 includes two opposing solar panels, specifically a first solar panel 38 mounted to the north panel 32 and a second solar panel 40 mounted to the south panel 34. In one embodiment, the solar panels 38 and 40 are folded into the stowed configuration, where they are positioned adjacent to the panels 32 and 34, as shown. When the solar panels 38 and 40 are deployed, they are able to rotate about the X-axis so they can be oriented perpendicular to the direction of the sun as the spacecraft 10 orbits and the Earth turns to provide maximum power efficiency.
Because the mounting cylinder 14 extends along the Z-axis in the east/west direction and the solar panels 38 and 40 are mounted to the north/south panels 32 and 34, the earth deck 22 is completely open for providing real-estate to which multiple antennas can be mounted, where modern satellites require many communications antennas often operating at different frequency bands. In this non-limiting example, a downlink phased array 44 and an uplink phased array 46 are configured at a central location on the earth deck 22, as shown, and can be used for beam steering downlink signals and uplink signals, respectively, as is well understood by those skilled in the art. Additional antennas on the earth deck 22 may include three cross-link dish antennas 48, 50 and 52 for transmitting and receiving signals to and from other spacecraft on orbit. The antenna dishes 48, 50 and 52 are shown in their deployed configuration facing away from the spacecraft 10 in
As mentioned above, the mounting cylinder 14 allows the spacecraft 10 to be mounted to other spacecraft in a single launch fairing to be launched for deployment in orbit around the Earth.
The discussion above of the spacecraft 10 is merely representative of one possible configuration of the elements that may be included in a modern three-axis spacecraft, where the configuration of the various components discussed herein can be varied within the scope of the present invention.
The foregoing discussion discloses and describes merely exemplary embodiments of the present invention. One skilled in the art will readily recognize from such discussion and from the accompanying drawings and claims that various changes, modifications and variations can be made therein without departing from the spirit and scope of the invention as defined in the following claims.
Number | Name | Date | Kind |
---|---|---|---|
3420470 | Meyer | Jan 1969 | A |
3532299 | Williamson et al. | Oct 1970 | A |
4009851 | Cable | Mar 1977 | A |
4664343 | Lofts et al. | May 1987 | A |
4834325 | Faget et al. | May 1989 | A |
4854526 | Rochefort | Aug 1989 | A |
4972151 | Rosen | Nov 1990 | A |
5052640 | Chang | Oct 1991 | A |
5152482 | Perkins et al. | Oct 1992 | A |
5199672 | King et al. | Apr 1993 | A |
5271582 | Perkins et al. | Dec 1993 | A |
5337980 | Homer et al. | Aug 1994 | A |
5344104 | Homer et al. | Sep 1994 | A |
5522569 | Steffy et al. | Jun 1996 | A |
5527001 | Stuart | Jun 1996 | A |
5613653 | Bombled et al. | Mar 1997 | A |
5755406 | Aston et al. | May 1998 | A |
5884866 | Steinmeyer et al. | Mar 1999 | A |
6138951 | Budris et al. | Oct 2000 | A |
6196501 | Hall et al. | Mar 2001 | B1 |
6206327 | Benedetti et al. | Mar 2001 | B1 |
6296206 | Chamness et al. | Oct 2001 | B1 |
6416018 | DiVerde et al. | Jul 2002 | B2 |
6504502 | Wu et al. | Jan 2003 | B1 |
6726151 | Hebert | Apr 2004 | B2 |
7780119 | Johnson et al. | Aug 2010 | B2 |
8511617 | Caplin et al. | Aug 2013 | B2 |
8789797 | Darooka | Jul 2014 | B2 |
8915472 | Aston | Dec 2014 | B2 |
9027889 | Aston et al. | May 2015 | B2 |
9573702 | Jacomb-Hood et al. | Feb 2017 | B1 |
9902507 | Walker | Feb 2018 | B2 |
20120068019 | Boccio | Mar 2012 | A1 |
20130299641 | Aston | Nov 2013 | A1 |
20140239124 | Aston et al. | Aug 2014 | A1 |
20140239125 | Aston | Aug 2014 | A1 |
20140266872 | Mitola, III | Sep 2014 | A1 |
20160318635 | Field | Nov 2016 | A1 |
20170361951 | Walker | Dec 2017 | A1 |
20180111707 | Poncet | Apr 2018 | A1 |
20180162561 | Estevez | Jun 2018 | A1 |
20180265227 | Cheynet De Beaupre | Sep 2018 | A1 |
Number | Date | Country |
---|---|---|
28 50 920 | Jun 1979 | DE |
30 02 551 | Jul 1981 | DE |
2 837 568 | Feb 2015 | EP |
WO-2016120547 | Aug 2016 | WO |
Entry |
---|
Surrey, Satellite Technology: Telecommunications & Navigation Platforms, Dec. 15, 2015, 4 pgs. http://www.sst-us.com/divisions/telecommunications-navigation/geo-platforms. |
Clark, Stephen, “Spaceflight Now, Photos: Satellites Readied for Tandem Launch on Falcon 9” Posted on Feb. 28, 2015, 6 pgs. http://spaceflightnow.com/2015/02/28/photos-satellites-readied-for-tandem-launch-on-falcon-9/. |
Hewitt, John Extreme Tech. “NASA Preps Launch of Four Satellites That Will Finally Suss Out the Origins of Earth's Mysterious Magnetic Field” Nov. 26, 2014, 4 pgs. http://www.extremetech.com/extreme/194922-nasa-preps-launch-of-four-satellites-that-will-finally-suss-out-the-origins-of-earths-mysterious-magnetic-field. |
Frick, Warren Shared Ride Opportunities on Orbital Launch Vehicles. Surrey Satellite Technology: Telecommunications & Navigation Platforms, Jun. 11, 2014, 18 pgs. http://www.sst-us.com/divisions/telecommunications-navigation/geo-platforms. |
Maly, Joe, “CubeSat Payload Accommodations and Propulsive Adapters” 11th Annual CubeSat Developer's Workshop, Apr. 25, 2014, 17 pgs. http://mstl.atl.calpoly.edu/˜bklofas/Presentations/DevelopersWorkshop2014/Maly_CubeSat_Payload_Accommodations.pdf. |
Colgate, Stirling, VELA Satellites. Multiwavelength Astronomy, Gamma Ray History, 1 pg. http://ecuip.lib.uchicago.edu/multiwavelength-astronomy/gamma-ray/history/07.html. |
Lo, A. et al. “Secondary Payloads Using the LCROSS Architecture” American Institute of Aeronautics and Astronautics, AIAA Space 2008, Conference & Exposition, USA Sep. 11, 2008, 8 pgs. |
Christensen, A. et al. “Ice on the Moon? Science Design of the Lunar Crater Observation and Sensing Satellite (LCROSS) Mission” AIAA Space Conference & Exposition, USA Sep. 19-21, 2006, 1 pg. |
Spaceflight, “New ICO Global Mobile Satellite System” Spaceflight Now, Jun. 17, 2001, 4 pgs. http://www.spaceflightnow.com/atlas/ac156/010617ico.html. |
Makita, Fumio, et al. “Design and Implementation of ICO System” 17th AIAA International Communications Satellite Systems Conference and Exhibit, 1998, Yokohama, Japan, 5 pgs. http://arc.aiaa.org/doi/pdf/10.2514/6.1998-1216. |
Maly, Joseph R., et al. “CASPAR: Low-Cost, Dual-Manifest Payload Adapter for Minotaur IV” Csa Engineering Inc Mountain View Ca, 2005, 11 pgs. http://oai.dtic.mil/oai/oai?verb=getRecord&metadataPrefix=html&identifier=ADA443936. |
Maly, Joseph, et al. “ESPA Satellite Dispenser for ORBCOMM Generation 2” 27th Annual AIAA/USU Conference on Small Satellites, 2013, 7 pgs. http://digitalcommons.usu.edu/smallsat/2013/all2013/77/. |
Number | Date | Country | |
---|---|---|---|
20180251238 A1 | Sep 2018 | US |