![\"\"](\"https:\/\/www.nasaspaceflight.com\/wp-content\/uploads\/2018\/02\/2018-02-01-234218-473x350.jpg\")
<\/p>\nA Long March 2D has conducted the sixth Chinese launch of 2018, with the lofting of the Zhangheng-1 spacecraft, a new research satellite for the observation of ionospheric precursors of earthquakes. The launch took place at 07:51 UTC on Friday from the 94 Launch Platform at the LC43 Launch Complex from the Jiuquan Satellite Launch Center (JSLC). An additional six small satellites rode along with the primary payload.<\/p>\n<\/p>\n
The Zhangheng-1 (ZH-1) \u2013 also known as China Seismo-Electromagnetic Satellite (CSES) \u2013 was developed by the Chinese Academy of Space Technology (CAST) and is based on the CAST2000 bus.<\/p>\n
The satellite will be operated by China National Space Administration (CNSA) together with the China Earthquake Administration and the China National Space Administration in cooperation with the Italian Space Agency (ASI).<\/p>\n
ZH-1 carries six instruments to measure the electromagnetic effects of earthquakes above 6 magnitude in China and quakes above magnitude seven all over the world.<\/p>\n
<\/p>\n
Zhangheng-1<\/p>\n
On board the satellite is the High-Energy Particle Detector (HEPD) to detects protons and electrons, measuring the flow of protons and electrons in short-term disturbances in the radiation belt whether caused by terrestrial, solar or anthropic phenomena; the Search-coil magnetometer (SCM) that will measure fluctuations in the magnetic field of the ionosphere and the Electric Field Detector (EFD) to measure the variation of the ionosphere electric field due to disturbances from solar, seismic and anthropic phenomena.<\/p>\n
Also included is the High-Energy Particle Package (HEPP), composed of three instruments designed to measure high energy particles (a solar x-ray detector, a high-energy detector and a low-energy detector); a Langmuir Probe to examine the parameters of the ionosphere in real time and on site together to the coupling of the ionosphere and the lithosphere before, during and after an earthquake occurs; the High-Precision Magnetometer (HPM) to take measures based on the spectroscopy of two photons of free alkaline atoms; and a plasma analyser to measure the density, composition, temperature and drift velocity of the ions of which the plasma is composed to check the coupling between ionosphere and seismic.<\/p>\n
Also onboard is a GNSS Occultation Receiver to measure the total electron content and obtain the vertical density of electrons, and a beacon that will operate in three bands that will allow transmission in VHF \/ UHF \/ L-band, also measuring ionospheric irregularities in the three bands for transmission from space to the ground.
\n![\"\"](\"https:\/\/www.nasaspaceflight.com\/wp-content\/uploads\/2018\/02\/2018-02-01-234408-400x350.jpg\")
The lithosphere-atmosphere-ionosphere coupling is a complex subject involving many physical effects and interactions that occur from the Earth surface up to the magnetosphere. The investigation of such coupling mechanisms \u2013 and in particular of the, partially unknown, behavior of the iono-magnetosphere transition region \u2013 is of fundamental importance for Earth remote sensing, monitoring of the near-Earth electromagnetic environment and studying of natural hazards.<\/p>\n
SpaceX (adsbygoogle = window.adsbygoogle || []).push({});<\/p>\n A great part of these effects is caused by natural non-seismic and anthropogenic electromagnetic emissions, but of particular relevance are the electromagnetic disturbances associated with the seismic activity that can produce ionospheric perturbations as well as the precipitation of particles from the Van Allen belts, observed before, during and after earthquakes of medium and strong magnitude.<\/p>\n All of these phenomena must be distinguished from those induced by sources external to the geomagnetic cavity and by atmospheric events. In fact, an important role in controlling the dynamic of the topside ionosphere is played by the Sun \u2013 that generates (regular and irregular) variations of the lithosphere-ionosphere-magnetosphere parameters by impulsive events as solar Coronal Mass Ejections and Solar Flares \u2013 as well as by tropospheric activity (lightning, TLE, etc.)<\/p>\n The CAST 2000 is a compact satellite platform characterized by its high performance, expandability and flexibility.<\/p>\n It is fitted with an S-band TT&C sub-system, X-band data transmission sub-system and 3-axis attitude stabilization, and is able to offer highly precise control, large-range sway and flexible orbit control, highly integrated housekeeping and a highly efficient power supply.<\/p>\n This platform has already been successfully applied in several Chinese small satellites, including the Huanjing-A, B satellites, and its performance and reliability have proven to be excellent.<\/p>\n This platform is also capable of operating in low, medium and high orbits, and has a life span of more than three years. The CAST 2000 bus mass is between 200 \u2013 400 kg and the payload capability is between 300 \u2013 600 kg. The satellite has a 3-axis stabilization and a sway attitude control capability.<\/p>\n In general, the platform can be used for Earth observation, technology demonstration, scientific exploration, Earth environmental exploration, meteorological research and application, communications and navigation.<\/p>\n Riding along Zhangheng-1 were six small satellites: GomX-4A (Ulloriaq) and GomX-4B, Fengmaniu-1, Shaonian Xing, and the \u00d1uSat-4 \u2018Ada\u2019 (Aleph-1 4) and \u00d1uSat-5 \u2018Maryam\u2019 (Aleph-1 5).<\/p>\n GomX-4A (Ulloriaq) and GomX-4B will test intersatellite communication links and propulsion while orbiting up to 4500 km apart. The two satellites are based on the CubeSat models that are nanosatellites based on standardized 10\u00d710 cm units. GomX-4B is a \u20186-unit\u2019 CubeSat, double the size of its predecessor GomX-3, which was released from the International Space Station in 2015.<\/p>\n GomX-4 satellites<\/p>\n The two small satellites will test intersatellite link technology, routing data from one satellite to the other, then down to the ground station. Part of the ground testing ensured they could indeed talk to each other and the actual ground station on an end-to-end basis.<\/p>\n After separation from the second stage of the Long March-2D rocket, the two satellites will first orient themselves to align their antennas. Then GomX-4B will gradually fly away from its counterpart, pausing at around 100 km intervals with their intersatellite links activated to see how well they work. Their separation will be controlled by new cold-gas propulsion on GomX-4B contributed by Sweden\u2019s NanoSpace company, using highly miniaturized thrusters.<\/p>\n The satellites will maintain their links through flat, patch antennas and software-controlled radios at a maximum distance of some 4500 km \u2013 a limit being set by the operating concept of a minimum of 10 satellites equally spaced around the same orbital plane to form a future constellation.<\/p>\n Apart from operating together, the two satellites have separate payloads. GomX-4B is the first CubeSat to fly the new HyperScout hyperspectral imager, developed by cosine Research in the Netherlands through ESA\u2019s General Support Technology Programme. Hyperscout images Earth in 45 different spectral bands, gathering a wealth of environmental data. The amount of data will be immense, that the camera must perform its own processing to drastically reduce the amount needing to be sent back to the ground.<\/p>\n GomX-4B also carries a new small startracker for precise attitude determination developed by Innovative Solutions in Space in the Netherlands, an ESA test payload checking components\u2019 susceptibility to space radiation, and a dedicated radio receiver to detect signals from worldwide air traffic.<\/p>\n GOMX-4A was built by GOMSpace for the Danish Ministry of Defence and also build GOMX-4B for ESA, but under another contract.<\/p>\n Fengmaniu-1 (FMN-1) is a three-unit CubeSat developed by Link Space Aerospace Technology for scientific education and technology demonstration. FMN-1 main mission will be to test new components like two cameras in space serving also as a repeater for amateurs worldwide via the onboard transponder system with a FM repeater uplink 145.945 MHz and a FM repeater downlink and telemetry 435.350 MHz, 9k6 BPSK AX25. Launch mass is 3 kg. The Shaonian Xing resulted from an initiative organized by China Soong Ching-ling Foundation, by the China Association for Science and Technology, and by the Chinese Education Society.<\/p>\n The Argentinian \u00d1uSat-4 \u2018Ada\u2019 (Aleph-1 4) and \u00d1uSat-5 \u2018Maryam\u2019 (Aleph-1 5) satellites are part of the Aleph-1 constellation that is being developed and operated by Satellogic S.A..<\/p>\n The Aleph-1 constellation will consist of up to 25 satellites.<\/p>\n The two satellites are almost identical to each other and have a mass of 37 kg, with dimensions 450mm x 450mm x 800mm. The primary objective of the mission is to commercially provide earth observation images to the general public in the visible and infrared parts of the spectrum.<\/p>\n Both satellites are equipped with cameras operating in visible light and infrared and will operate in 500 km SSO orbit with inclination at 97.5 degrees.<\/p>\n \u00d1uSat-4 is designated \u2018Ada\u2019 in honor of Ada Lovelace, an English mathematician and writer, chiefly known for her work on Charles Babbage\u2019s proposed mechanical general-purpose computer. \u00d1uSat-5 is designated \u2018Maryam\u2019 in honor of Maryam Mirzakhani, an Iranian mathematician and a professor of mathematics at Stanford University. Her research topics included Teichm\u00fcller theory, hyperbolic geometry, ergodic theory, and symplectic geometry.<\/p>\n The Long March-2D (LM-2D) launch vehicle is a two-stage rocket developed by the Shanghai Academy of Spaceflight Technology. With storable propellants is mainly used to launch a variety of low earth orbit satellites.<\/p>\n The development of LM-2D was started in February 1990. From 2002, to meet the demand of SSO satellites, the payload fairing of 3350mm in diameter and attitude control engine for the second stage have been successfully developed; and the discharge of remaining propellant and de-orbit of the second stage have been realized. This launcher is mainly used for launching LEO and SSO satellites.<\/p>\n Long March 2D<\/p>\n It is characterized by high reliability, wide application and mature technology.<\/p>\n The LM-2D can launch a 1,300 kg cargo in a 645 km SSO. The rocket is 41.056 meters long and the first, second stages and payload fairing are all 3.35 meters in diameter.<\/p>\n The first stage is the same of the Long March-4.<\/p>\n The second stage is based on LM-4 second stage with an improved equipment bay. Lift-off mass is 232,250 kg, total length 41,056 meters, diameter 3.35 meters and fairing length 6.983 meters. At launch, it develops 2961.6 kN engine thrust.<\/p>\n The first stage has a 27.910 meter length with a 3.35 meter diameter, consuming 183,200 kg of N2O4 \/ UDMH (launch mass of the first stage is 192,700 kg). Equipped with a YF-21C engine capable of a ground thrust of 2,961.6 kN and a ground specific impulse of 2,550 m\/s. Burn time is 170 seconds.<\/p>\n The second stage has a 10.9 meter length with a 3.35 meter diameter, launch mass of 39,550 kg and consuming 45,550 kg of N2O4 \/ UDMH. Equipped with a YF-24C cluster engine with a main engine vacuum thrust of 742.04 kN and a vernier engine with a vacuum thrust of 47.1 kN (specific impulses of 2,942 m\/s and 2,834 m\/s, respectively).<\/p>\n The LM-2D can use two types of fairings depending on the cargo. Type A fairing has a 2.90 meters diameter (total launch vehicle length is 37.728 meters) and Type B fairing with a diameter of 3.35 meters \u2013 total launch vehicle length is 41.056 meters. Second stage main engine cut-off takes place at 4 minutes 21 seconds and second stage Vernier engines cut-off takes place at 9 minutes and 10 seconds. Nominally payload separation takes place three seconds later.<\/p>\n The first launch of the LM-2D was on August 9th, 1992 from the Jiuquan Satellite Launch Center orbiting the Fanhui Shei Weixing FSW-2-1 (22072 1992-051A) recoverable satellite.<\/p>\n The Jiuquan Satellite Launch Center, in Ejin-Banner \u2013 a county in Alashan League of the Inner Mongolia Autonomous Region \u2013 was the first Chinese satellite launch center and is also known as the Shuang Cheng Tze launch center.<\/p>\n The site includes a Technical Centre, two Launch Complexes, Mission Command and Control Centre, Launch Control Centre, propellant fuelling systems, tracking and communication systems, gas supply systems, weather forecast systems, and logistic support systems.<\/p>\n The launch site<\/p>\n Jiuquan was originally used to launch scientific and recoverable satellites into medium or low earth orbits at high inclinations. It is also the place from where all the Chinese manned missions are launched.<\/p>\n The LC-43 launch complex, also known as South Launch Site (SLS) is equipped with two launch pads: 91 and 94. Launch pad 91 is used for the manned program for the launch of the Long March-2F launch vehicle (Shenzhou and Tiangong). Launch pad 94 is used for unmanned orbital launches by the Long March-2C, Long March-2D and Long March-4C launch vehicles.<\/p>\n Other launch zones at the launch site are used for launching the Kuaizhou, Kaituo and the Long March-11 solid propellant launch vehicles.<\/p>\n The first orbital launch took place on April 24, 1970 when the Long March-1 rocket launched the first Chinese satellite, the Dongfanghong-1 (04382 1970-034A).<\/p>\n","protected":false},"excerpt":{"rendered":" A Long March 2D has conducted the sixth Chinese launch of 2018, with the lofting of the Zhangheng-1 spacecraft, a new research satellite for the observation of ionospheric precursors of earthquakes. The launch took place at 07:51 UTC on Friday from the 94 Launch Platform at the LC43 Launch Complex from the Jiuquan Satellite Launch […]<\/p>\n","protected":false},"author":1,"featured_media":0,"comment_status":"","ping_status":"","sticky":false,"template":"","format":"standard","meta":{"_acf_changed":false,"inline_featured_image":false,"footnotes":"","_links_to":"","_links_to_target":""},"categories":[2],"tags":[135,205],"class_list":["post-38558","post","type-post","status-publish","format-standard","hentry","category-news","tag-china","tag-long-march"],"acf":[],"_links":{"self":[{"href":"https:\/\/starpath.global\/blog\/wp-json\/wp\/v2\/posts\/38558"}],"collection":[{"href":"https:\/\/starpath.global\/blog\/wp-json\/wp\/v2\/posts"}],"about":[{"href":"https:\/\/starpath.global\/blog\/wp-json\/wp\/v2\/types\/post"}],"author":[{"embeddable":true,"href":"https:\/\/starpath.global\/blog\/wp-json\/wp\/v2\/users\/1"}],"replies":[{"embeddable":true,"href":"https:\/\/starpath.global\/blog\/wp-json\/wp\/v2\/comments?post=38558"}],"version-history":[{"count":0,"href":"https:\/\/starpath.global\/blog\/wp-json\/wp\/v2\/posts\/38558\/revisions"}],"wp:attachment":[{"href":"https:\/\/starpath.global\/blog\/wp-json\/wp\/v2\/media?parent=38558"}],"wp:term":[{"taxonomy":"category","embeddable":true,"href":"https:\/\/starpath.global\/blog\/wp-json\/wp\/v2\/categories?post=38558"},{"taxonomy":"post_tag","embeddable":true,"href":"https:\/\/starpath.global\/blog\/wp-json\/wp\/v2\/tags?post=38558"}],"curies":[{"name":"wp","href":"https:\/\/api.w.org\/{rel}","templated":true}]}}See Also<\/h4>\n
\n
![\"\"](\"https:\/\/www.nasaspaceflight.com\/wp-content\/uploads\/2018\/02\/2018-02-01-234528-528x350.jpg\")
<\/p>\n
\n![\"\"](\"https:\/\/www.nasaspaceflight.com\/wp-content\/uploads\/2018\/02\/2018-02-01-234643-374x350.jpg\")
Shaonian Xing (also known as Youth Star) is a three-unit CubeSat developed by Chinese students as part of the Sat-China outreach project to engage youth in thinking about space, STEAM education, and even satellite development. Launch mass is 2 kg.<\/p>\n![\"\"](\"https:\/\/www.nasaspaceflight.com\/wp-content\/uploads\/2018\/02\/2018-02-01-234800-622x350.jpg\")
<\/p>\n
\nLaunch profile of the Long March-2D starts with engine ignition at 1.2 seconds before lift-off. Pitch over maneuver happens at 12 seconds into the flight and the end of the first stage ignition occurs at two minutes 33 seconds. Stage separation and second stage ignition occur one second latter. At 3 minutes 34 seconds the two parts of the fairing separate from the second stage.<\/p>\n![\"\"](\"https:\/\/www.nasaspaceflight.com\/wp-content\/uploads\/2018\/02\/2018-02-01-234923-538x350.jpg\")
<\/p>\n