- It is Geosynchronous transfer orbit. Geosynchronous transfer orbit listed as GTO Geosynchronous transfer orbit - How is Geosynchronous transfer orbit abbreviated?
- The invention is directed to a method for transferring a spacecraft from a quasi-GTO to a geosynchronous orbit by using the gravity provided by the moon to.
- To demonstrate the proposed method, a geosynchronous transfer orbit (GTO), inclined at a specified inclination (here, 28.5 degrees) to the Earth's equatorial plane is connected to a lunar orbit.
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- What Is Geosynchronous Transfer Orbit (gto)
- Geostationary Transfer Orbit
- Geosynchronous Transfer Orbit Vs Geostationary
TAMPERE, Finland — A Chinese telecommunications satellite has suffered unspecified anomalies following an apparently successful launch into geosynchronous transfer orbit.
Technique for Escape from Geosynchronous Transfer Orbit Using a Solar Sail Victoria L. Coverstone¤and John E. Prussing† University of Illinois at Urbana– Champaign, Urbana, Illinois 61801 A technique for escaping the Earth using a solar sail is developed and numerically simulated. The spacecraft is initially in a geosynchronous transfer.
Zhongxing-18 (ChinaSat-18), a civilian telecommunications satellite to provide broadcasting and communications services to China, lifted off atop of an enhanced Long March 3B launch vehicle from the Xichang Satellite Launch Center, southwest China, at 8:03 a.m. Eastern Monday, with amateur footage from the vicinity confirming liftoff. The first official confirmation of many Chinese launches come around one hour after launch from the China Aerospace Science and Technology Corporation (CASC), the main space contractor for the space program, or the media arm of the People’s Liberation Army.
Speculation grew among Chinese space watchers and enthusiasts online as the hours passed with no official statement on the mission.
Early Tuesday, Chinese state news agency Xinhua reported that the satellite separated from the rocket stage as normal, but ChinaSat 18, “has experienced abnormalities, and space engineers are investigating the cause.”
No indication of the source or nature of the issue was offered. Data published by the U.S. Space Surveillance Network following the launch indicates two objects in geosynchronous transfer orbit, suggesting successful separation of the rocket stage and satellite as per the Xinhua statement.
New satellite platform
Zhongxing-18 is equipped with 30 Ku-band transponders, 9 Ka-band transponders and 2 Ka BSS-band transponders to provide a range of broadcasting, communications services and internet applications across a lifetime of 15 years or more.
The satellite is based on a DFH-4E satellite platform and is the first of its type launched. It is a variant of the established large DFH-4 platform. Two of 21 DFH-4-based satellites launched have suffered solar array issues, leading to the failure in orbit of Nigerian communication satellite NigComSat-1 in 2008 and the loss Xinnuo 2 (SinoSat-2) in 2006 when the solar arrays failed to deploy.
Zhongxing-18 is to be operated by China Satcom, a CASC subsidiary specialized in satellite communications & broadcasting services. China Satcom planned an IPO for this year and entered the Shanghai Stock Exchange on June 28.
Debris downrange
Spent stages from the Long March 3B, a three-stage 55-meter-tall (180-foot) hypergolic launcher with four side boosters, fell to Earth downrange of Xichang, with two cows apparently losing their lives as a result.
China’s previous launch from Xichang saw a first test of grid fins on the two-stage Long March 2C launch vehicle, with apparent resemblance to those used to guide SpaceX Falcon boosters back to landing areas. The test was stated to both decrease downrange dangers of launches and pave the way for future reusable launchers.
Three of China’s four national launch centers were established during the Cold War, with tensions with the United States and Soviet Union prompting the decision for the sites to be located far inland for security reasons. Despite careful rocket flight path design and safety measures on the ground, spent boosters have frequently fallen among towns and villages downrange from Xichang, sometimes damaging property.
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We propose a 4-year 6-U CubeSat mission with the primary science goal of advancing our quantitative understanding of acceleration and loss of relativistic electrons in the Earth's outer radiation belt. From a low inclination geosynchronous transfer orbit (GTO), GTOSat will measure electron spectra and pitch angles of both the seed and the energized electron populations simultaneously, using a compact, high-heritage Relativistic Electron Magnetic Spectrometer (REMS), a customized version of the MagEIS-Medium instruments from NASA's Van Allen Probes mission. A boom-mounted fluxgate magnetometer will provide 3-axis knowledge of the ambient local magnetic field. These high quality particle and field measurements enable direct measurement of spectral and pitch angle evolution of the outer radiation belt. and calculation of physically significant quantities, such as phase space density (PSD) and its radial gradients, which are necessary to discriminate between radial transport and in-situ modes of electron energization. GTOSat will fly in a highly elliptical GTO, with nominal apogee near 6.6 Earth Radii (RE). A likely off- equatorial inclination means GTOSat will sample the particle dynamics of the outer radiation belt beyond 6.6 RE, well beyond the Van Allen Probes, providing two radial profiles of the radiation belts every orbit (~11 hours).
The GTOSat bus consists of a 6U structure designed for Planetary System Corporation's (PSC) 6U deployer. It is spin-stabilized with a Sun-pointing spin-axis and deployable solar arrays. Mitigation of radiation effects is accomplished through a multi-pronged systems approach consisting of spot shielding, parts selection, and a 'vault' that reduces the total dose for 1 year on orbit to less than 10 krad. The attitude determination and control system (ADCS) consists of a reaction wheel system with magneto-torquers for stability and momentum dumping, multiple fine and coarse sun sensors for pointing, and an inertial measurement unit. Communication is achieved via an S-band transceiver, enabling high data throughput through the Near-Earth Network (NEN) and real-time radiation belt monitoring via the Tracking and Data Relay Satellite System (TDRSS). Significant systems engineering analyses have been performed already, including 'Day in the Life' studies for thermal, communications, ACS, and power.
In addition to the compelling science objective, which has never been attempted on a CubeSat, GTOSat will fly a new scalable radiation tolerant command and data handling (C&DH) and electrical power system (EPS) systems that could be used for future SmallSat missions, and pave the way for highly reliable, capable cubesat constellations and missions beyond low earth orbit (LEO). The NASA 2014 Science Plan notes that Heliophysics science relies on maintaining the Heliophysics System Observatory (HSO), and that this is difficult in the current constrained fiscal environment. By demonstrating that a cubesat can reliably obtain high quality scientific measurements in the Van Allen radiation belts, at a time after the Van Allen Probes will end, GTOSat serves as a timely HSO replacement spacecraft for the radiation belts, and also as a pathfinder for other reliable, low-cost, small inner magnetospheric spacecraft, in line with the NASA Science Plan and the Heliophysics Roadmap. GTOSat directly addresses the objectives of the Low-Cost Access to Space (LCAS) program by providing scientifically valuable measurements to the radiation belt community while advancing technologies to support future missions and scientific investigations and training early career scientists in instrument and mission development.
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Dates
| Metadata Created Date | November 12, 2020 |
|---|---|
| Metadata Updated Date | November 12, 2020 |
What Is Geosynchronous Transfer Orbit (gto)
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- Data.json Data.json Metadata
Harvested from NASA Data.json
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Geostationary Transfer Orbit
| Resource Type | Dataset |
|---|---|
| Metadata Created Date | November 12, 2020 |
| Metadata Updated Date | November 12, 2020 |
| Publisher | Space Technology Mission Directorate |
| Unique Identifier | Unknown |
| Maintainer | |
| Identifier | TECHPORT_94406 |
| Data First Published | 2022-01-01 |
| Data Last Modified | 2020-01-29 |
| Public Access Level | public |
| Bureau Code | 026:00 |
| Metadata Context | https://project-open-data.cio.gov/v1.1/schema/catalog.jsonld |
| Metadata Catalog ID | https://data.nasa.gov/data.json |
| Schema Version | https://project-open-data.cio.gov/v1.1/schema |
| Catalog Describedby | https://project-open-data.cio.gov/v1.1/schema/catalog.json |
| Homepage URL | https://techport.nasa.gov/view/94406 |
| Program Code | 026:027 |
| Source Datajson Identifier | True |
| Source Hash | 433ff2534c884ff1188d4476636bdd16cab05b76 |
| Source Schema Version | 1.1 |
Geosynchronous Transfer Orbit Vs Geostationary
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