Antennas for Small Satellites

Gao, Steven; Clark, Keith; Zackrisson, J.; Maynard, Kevin; Boccia, Luigi; Jia-dong, XU

doi:10.1002/9781119945147.ch15

Cited by 7 publications

(15 citation statements)

References 6 publications

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“…These functions often require several different antennas. Basic radiator configurations used are normally helices, monopoles, patches, and patch-excited cups, depending on frequency range, coverage requirements, and application (Gao et al, 2008;. Before moving on to the objectives of the Chapter, a few comments on frequency allocations are in order.…”

Section: Inter-satellite Cross Linksmentioning

confidence: 99%

“…These antennas are simple, cheap, easily fabricated, and have nearly omnidirectional or broad-beam radiation patterns, thus the satellite does not need accurate control of its attitude. One such antenna is the microstrip patch described in (Gao et al, 2008). It uses a circular patch fed by a coaxial probe at the bottom.…”

Section: Planar Antennas For Modern Small Satellitesmentioning

confidence: 99%

“…At the other end of the design spectrum, the work by (Muchalski et al, 2004) is a typical example of how suspended, electrically large patches can exhibit quite significant bandwidths. Furthermore, resonant-size patches can produce gains in the range 4-6.5 dBi and bandwidths of a few percent (Gao et al, 2008;Hamrouni et al, 2009;Maqsood et al, 2010). On the other hand, 3-D structures consisting of folded and stacked radiating parts offer moderate bandwidths and gains combined, and can even become electrically small (Lee & Woo, 2008).…”

Section: Comparison With Existing Studiesmentioning

confidence: 99%

“…1.575 n/a 8.5 2.82 (Zackrisson, 2007) X-band RX 8.000 n/a 8.9 2.63 (Zackrisson, 2007) X-band TX 8.000 n/a 7.5 2.24 (Gao et al, 2008) 2.250 22.2 6.5 1.99 (Lee & Woo, 2008) (Hamrouni et al, 2009) 1 2.400 2.9 n/a 1.62 (Hamrouni et al, 2009) Table 2. Comparison of electrical performance among GPS/GNSS/TTC antennas missions since it is 3.7-4.8 times larger than the size of the CSPP, which fits marginally on the wall of the spacecraft.…”

Section: Antenna Attributementioning

confidence: 99%

“…Only compound field antennas threaten to alter this otherwise fundamental relationship, however that topic is outside the scope of and space available in this Chapter.5 The FBW cited for(Gao et al, 2008) is aggregate, not instantaneous.309Electrically Small Microstrip Antennas Targeting Miniaturized Satellites: the CubeSat Paradigm…”

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confidence: 99%

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Electrically Small Microstrip Antennas Targeting Miniaturized Satellites: the CubeSat Paradigm

Kakoyiannis¹,

Constantinou²

2011

Microstrip Antennas

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Mini-satellite (100-500 kg) 2. Micro-satellite (10-100 kg) 3. Nano-satellite (1-10 kg) 4. Pico-satellite (0.1-1 kg) 5. Femto-satellite (0.01-0.1 kg) CubeSats belong to the genre of pico-satellites; their maximum weight lies on the borderline between pico-and nano-satellites. The main reason for miniaturizing satellites is to reduce the cost of deployment: heavier satellites require larger rockets of greater cost to finance; smaller and lighter satellites require smaller and cheaper launch vehicles, and are often suitable for launch in multiples. They can also be launched "piggyback", using the excess capacity of larger launch vehicles (Wikipedia, 2010b). But small satellites are not short of technical challenges; they usually require innovative propulsion, attitude control, communication and computation systems. For instance, micro-/nano-satellites have to use electric propulsion, compressed gas, vaporizable liquids, such as butane or carbon dioxide, or other innovative propulsion systems that are simple, cheap and scalable. Micro-satellites can use radio-communication systems in the VHF, UHF, L-, S-, C-and X-band. On-board communication systems must be much smaller, and thus more up-to-date than what is used 12 in conventional satellites, due to space constraints. Furthermore, miniature satellites usually lack the power supply and size required for conventional bulky radio transponders. Various compact innovative communication solutions have been proposed for small satellites, such as optical (laser) transceivers, antenna arrays and satellite-to-satellite data relay. Electronics need to be rigorously tested and modified to be "space hardened", that is, resistant to the outer space environment (vacuum, microgravity, thermal extremes and radiation exposure) (Wikipedia, 2010b). The CubeSat programme was developed through the joint efforts of research laboratories from California Polytechnic State University (Cal Poly) and Stanford University, beginning in 1999. The concept was introduced to the scientific community as an opportunity for all universities to enter the field of space science and exploration. A large group of universities, along with certain companies and organizations, participate actively in the CubeSat programme; it is estimated that 40 to 50 universities were developing CubeSats in 2004. Featuring both small size and weight, a CubeSat can be built and launched for an estimated total of $65,000-80,000 (per fiscal year 2004 values). The standard 10 × 10 × 10 cm 3 basic CubeSat is often called a "1U" CubeSat, meaning one unit. CubeSats are roughly scalable in 1U increments and larger. The four basic sizes are 0.5U, 1U, 2U and 3U. The number corresponds to the length of the CubeSat in decimetres; width and depth are always 10 cm, or 1 dm. Orbiters such as a "2U" CubeSat (20 × 10 × 10 cm 3) and a "3U" CubeSat (30 × 10 × 10 cm 3) have been both built and launched. Since CubeSats are all 10 × 10 cm 2 (regardless of length) they can all be launched and deployed using a common deployment system. CubeSats ar...

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Section: Inter-satellite Cross Linksmentioning

confidence: 99%

Section: Planar Antennas For Modern Small Satellitesmentioning

confidence: 99%

Section: Comparison With Existing Studiesmentioning

confidence: 99%

Section: Antenna Attributementioning

confidence: 99%

mentioning

confidence: 99%

See 3 more Smart Citations

Electrically Small Microstrip Antennas Targeting Miniaturized Satellites: the CubeSat Paradigm

Kakoyiannis¹,

Constantinou²

2011

Microstrip Antennas

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Circularly Polarized Antennas

Laheurte¹

2011

Compact Antennas for Wireless Communications and Terminals

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Circularly polarized (CP) antennas are a type of antenna with circular polarization. Due to the features of circular polarization, CP antennas have several important advantages compared to antennas using linear polarizations, and are becoming a key technology for various wireless systems including satellite communications, mobile communications, global navigation satellite systems (GNSS), wireless sensors, radio frequency identification (RFID), wireless power transmission, wireless local area networks (WLAN), wireless personal area networks (WPAN), Worldwide Interoperability for Microwave Access (WiMAX) and Direct Broadcasting Service (DBS) television reception systems. Lots of progress in research and development has been made during recent years.The CP antenna is very effective in combating multi-path interferences or fading [1,2]. The reflected radio signal from the ground or other objects will result in a reversal of polarization, that is, right-hand circular polarization (RHCP) reflections show left-hand circular polarization (LHCP). A RHCP antenna will have a rejection of a reflected signal which is LHCP, thus reducing the multi-path interferences from the reflected signals.The second advantage is that CP antenna is able to reduce the 'Faraday rotation' effect due to the ionosphere [3,4]. The Faraday rotation effect causes a significant signal loss (about 3 dB or more) if linearly polarized signals are employed. The CP antenna is immune to this problem, thus the CP antenna is widely used for space telemetry applications of satellites, space probes and ballistic missiles to transmit or receive signals that have undergone Faraday rotation by travelling through the ionosphere.Another advantage of using CP antennas is that no strict orientation between transmitting and receiving antennas is required. This is different from linearly polarized antennas which are subject to polarization mismatch losses if arbitrary polarization misalignment occurs between transmitting and receiving antennas. This is useful for mobile satellite communications where it is difficult to maintain a constant antenna orientation. With CP, the strength of the received signals is fairly constant regardless of the antenna orientation. These advantages make CP antennas very attractive for many wireless systems.

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