超级军网环境1C卫星的SAR
来源：百度文库 编辑：超级军网 时间：2024/04/28 23:18:33
Chinese Long March 2C lofts Huanjing-1C into orbit
November 18th, 2012 by Rui C. Barbosa
China conducted its 16th orbital launch of the year by orbiting the third satellite on its Environmental Protection & Disaster Monitoring Constellation. The Huanjing-1C (Environment-1C) satellite was launched at 22:53 UTC on Sunday from the Taiyuan Satellite Launch Center’s LC9 Launch Platform using the Long March 2C (Chang Zheng-2C) launch vehicle.
Chinese Launch:
This was the 171st successful Chinese orbital launch, the 171st launch of a Chang Zheng launch vehicle, the 41st successful orbital launch from Taiyuan and the fifth launch from Taiyuan this year.
The HJ-1 satellites are a network of Earth observing satellites owned by the National Committee for Disaster Reduction and State Environmental Protection Administration of China, with the objective to establish an operational Earth observing system for disaster monitoring and mitigation using remote sensing technology and to improve the efficiency of disaster mitigation and relief.
The main application fields for China are environmental monitoring and prediction, solid waste monitoring, disaster monitoring and prediction (flood, drought, typhoon and wind damage, sand storm, earthquake, land creep, frost and grassland fires, coal fires, crop pest monitoring, ocean disaster monitoring). The program was ratified in 2003 by the Chinese authorities.
See Also
Chinese Forum Section
65 Launch Vehicle Manuals (L2)
Click here to Join L2
In May 2007, the China National Space Administration became the member of the International Charter ‘Space and Major Disasters’, a joint initiative that works to provide emergency response satellite data free of charge to those affected by disasters anywhere in the world.
Each member of the International Charter ‘Space and Major Disasters’ has demonstrated its commitment to use its space assets when it is most needed, when disasters of natural and human origin strike the world’s communities, or wreak havoc on the environment.
The first stage of the program is comprised of three minisatellites, usually referred to as the 2+1 constellation. The second stage of the program will consist of a total of eight spacecraft (four with optical payloads and four with SAR payloads, the 4+4 constellation). Originally, the launch of all the satellites was to be accomplished by 2012 through international cooperation.
The first stage implementation includes three small satellites (2+1 constellation). The spacecraft of the constellation are referred to as HJ-1A, HJ-1B, and HJ-1C. The HJ-1A and HJ-1B satellites were launched at 03:25UTC on September 6, 2008, by the Chang Zheng-2C/SMA (Y1) launch vehicle from the Taiyuan Satellite Launch Center.
HJ-1A is an optical satellite with a CCD camera and an infrared camera while HJ-1B is equipped with a CCD camera and a hyperspectral camera on board. Each spacecraft has a launch mass of 470 kg, with a size of 1.2 m x 1.1 m x 1.03 m, and a design life of three years.
The satellites were based on the CAST-968B bus of DFHSat (DFH Satellite Co Ltd.) of CAST (China Academy of Space Technology) and by the China Aerospace Science and Technology Corporation. Both satellites are 3-axis stabilized.
The HJ-1C satellite is a spacecraft with an S-band (ТКСА-6К collapsible mesh parabolic antenna) SAR payload based on the CAST-2000 (CAST-968B). The satellite will have a Sun-synchronous circular dawn-dusk orbit, at an altitude of 500 km, 97.3 degrees inclination and a 94 minutes orbital period, with a local time on descending node at 6:00 hours.
The satellite predicted operational life is three years. This is the first civil Synthetic Aperture Radar (SAR) system
The mass of the spacecraft is 890 kg, including 200 kg of its SAR payload. The communications of its payload data will use CCSDS standard to format compressed raw data and its auxiliary data. On board the satellite has 40 Gbit of storage capacity and the transmission is made via X-band downlink with QPSK modulation. The downlink data rate is of 2 x 160 Mbit/s.
Power supply is made by using a solar array with 7.5 m2 using GaAS/Ge solar cells capable of delivering a power of 1.1 kW (BOL) and 0.8 kW (EOL). Power is stored on two batteries (40Ah).
The S-band SAR instrument was developed with the assistance of NPO Mashinostroyenia & Vega Corp. from Russia. The SAR instrument has a 3.13 GHz (S-band) center frequency, corresponding to a wavelength of 9.6 cm, giving a spatial resolution of 20 meters, with a swath width of 100 km.
The SAR instrument will be capable of a two mode operation: Scan Mode and Strip Mode. On Scan Mode it will be able to get a 15 to 25 meter resolution with a swath of 95 to 105 km. The Strip Mode it will be able to get a 4 to 6 meter resolution with a swath of 35 to 40 km.
Other satellites were launched together with Huanjing-1C, the XY Xinyan-1 and the FN-1 Fengniao-1A/B pair.
The Xinyan-1 was build by the Aerospace DFH Development Limited of Shenzhen, the recently established spin-off of CAST’s mini-satellite department. The small satellite will test various components such as China-built microwave switches, a lighter user communication terminal and more accurate thermostats to be used of future satellites.
Also known by NewTech-1 (New Technology Demonstration Satellite), the XY-1 is the first new space technology in-orbit demonstration project developed by enterprises in China and used for in-orbit test demonstration of many new technologies.
The FN-1 Fengniao-1A/B (HummerSat-1) satellites represent the first realization of a new generic micro/minisatellite development of DFHSat (DFH Satellite Co. Ltd.).
The overall objective of the mission is to provide a technology demonstration as well as to test observation capabilities within the spacecraft class of 80-250 kg of total mass envelop (micro/minisatellite), for a number of different missions and applications, including support scenarios of constellations and formation flight (with intersatellite crosslink, relative navigation, guidance and control).
The FN-1 mission concept consists of two satellites, the FN-1A with a launch mass of about 160 kg, as the principal spacecraft of the formation, and a microsatellite, the FN-1B with a mass of 30 kg. Both satellites are launch as a uniform body.
On orbit, FN-1B will be deployed to form a two-spacecraft formation with the main spacecraft. Both spacecraft are in contact with a crosslink for information exchange and the enactment of required orbit manoeuvres. However, all ground communications with the formation is only via the mother spacecraft.
The goal of the mission is to demonstrate the newly developed CAST-mini bus and CAST-micro bus designs in space, in particular to validate their functional capabilities and technologies introduced, and to demonstrate the capability of close formation flying technologies such as relative navigation, guidance and control, intersatellite crosslink, and command.
The Fengniao-1A uses a new modular bus concept, referred to as CAST-mini, which is of CAST-968 and CAST-2000 platform heritage. The CAST-mini bus consists of a cylindrical (octagonal) body with face-mounted solar panels and two deployable T-form solar wings, oriented in the ±Y axis.
The spacecraft body has a size of 785 mm in diameter and 1032 mm in height. Thermal control is provided by passive means (radiator) and assisted by active means (heater) when needed. The satellite has a design life of three years. It is 3-axis stabilized with an Earth-pointing orientation, providing medium pointing and pointing-stability accuracies.
Fengniao-1B is a new microsatellite development of DFHSat. The objectives are to test the new modular platform capabilities in space and to use the spacecraft for formation flying demonstrations with FN-1A. The satellite bus features also an octagonal shape (as the mother spacecraft) with dimensions of 400 mm in diameter and 175 mm in height.
The surface-mounted solar cells (GaAs) provide an average power of ~ 5 W. Orbit and attitude control is provided with RCS (Reaction Control Subsystem) using 12 thrusters (each with 30 mN).
Relative orbit measurements between the two satellites are provided with a differential GPS (DGPS) receiver.
The Chang Zheng-2C launch vehicle:
The Chang Zheng-2C a low Earth orbit launch vehicle derived from DF-5 ICBM. The rocket is a two stage hypergolic launch vehicle with a total length of 35.17 meters, a diameter of 3.35 meters and a total mass of 192,000 kg.
This is a liquid launch vehicle mainly used for Low Earth Orbit (LEO) missions. The CZ-2C is most frequently used version of Long March Launch Vehicles which had 14 consecutive successful flights till October of 1994.
In order to meet the user’s need, China Academy of Launch Vehicle (CALT) developed a new smart dispenser upper stage; the CZ-2C/SD has been used commercially in the late 1990s and conducted seven consecutive successful launches for Iridium program.
The CZ-2C launch vehicle now provides two versions to customers: a basic version composed by a two-stage CZ-2C for LEO missions with typical launch capability of 3,366 kg; and a three-stage version: CZ-2C/CTS for LEO or SSO with typical launch capability of 1,456 kg.
This launcher provides a flexible mechanical and electrical interfaces and length-adjustable fairing for various satellites. The launch environment impinging on the cargo do be launched, such as vibration, shock, pressure, acoustics, acceleration and thermal environment, meets the common requirements in the commercial launch services market.
The first stage is equipped with a cluster of four YF-20A engines (YF-21), having a length of 23.72 meters, a gross mass of 151,000 kg (empty mass of 8,600 kg) and a burn time of 130 seconds.
The second stage is equipped with a cluster of one YF-22A engine with fixed nozzles and a swivelling venire motor consisting of four YF-23 chambers motors (the YF-24), and has a length of 8.71 meters, a gross mass of 38,200 kg (empty mass of 3,200 kg) with a burn time of 112 seconds (main engine) and 287 second (vernier).
In this launch the CZ-2C used an SMA upper stage (possibly using the SpaB-140C solid motor), increasing the SSO payload capability to 1,900 kg.
The Taiyuan Satellite Launch Center:
Situated in the Kelan County on the northwest part of the Shanxi Province, the Taiyuan Satellite Launch Center (TSLC) is also known by the Wuzhai designation. It is used mainly for polar launches (meteorological, Earth resources and scientific satellites).
The center is at a height of 1400-1900m above sea level, and is surrounded by mountains to the east, south and north, with the Yellow River to its west. The annual average temperature is 4-10 degrees C, with maximum of 28 degrees C in summer and minimum of -39 degrees C in winter.
TSLC is suitable for launching a range of satellites, especially for low earth and sun-synchronous orbit missions. The center has state-of-the-art facilities for launch vehicle and spacecraft testing, preparation, launch and in-flight tracking and safety control, as well as for orbit predictions.
http://www.nasaspaceflight.com/2 ... jing-1c-into-orbit/Chinese Long March 2C lofts Huanjing-1C into orbit
November 18th, 2012 by Rui C. Barbosa
China conducted its 16th orbital launch of the year by orbiting the third satellite on its Environmental Protection & Disaster Monitoring Constellation. The Huanjing-1C (Environment-1C) satellite was launched at 22:53 UTC on Sunday from the Taiyuan Satellite Launch Center’s LC9 Launch Platform using the Long March 2C (Chang Zheng-2C) launch vehicle.
Chinese Launch:
This was the 171st successful Chinese orbital launch, the 171st launch of a Chang Zheng launch vehicle, the 41st successful orbital launch from Taiyuan and the fifth launch from Taiyuan this year.
The HJ-1 satellites are a network of Earth observing satellites owned by the National Committee for Disaster Reduction and State Environmental Protection Administration of China, with the objective to establish an operational Earth observing system for disaster monitoring and mitigation using remote sensing technology and to improve the efficiency of disaster mitigation and relief.
The main application fields for China are environmental monitoring and prediction, solid waste monitoring, disaster monitoring and prediction (flood, drought, typhoon and wind damage, sand storm, earthquake, land creep, frost and grassland fires, coal fires, crop pest monitoring, ocean disaster monitoring). The program was ratified in 2003 by the Chinese authorities.
See Also
Chinese Forum Section
65 Launch Vehicle Manuals (L2)
Click here to Join L2
In May 2007, the China National Space Administration became the member of the International Charter ‘Space and Major Disasters’, a joint initiative that works to provide emergency response satellite data free of charge to those affected by disasters anywhere in the world.
Each member of the International Charter ‘Space and Major Disasters’ has demonstrated its commitment to use its space assets when it is most needed, when disasters of natural and human origin strike the world’s communities, or wreak havoc on the environment.
The first stage of the program is comprised of three minisatellites, usually referred to as the 2+1 constellation. The second stage of the program will consist of a total of eight spacecraft (four with optical payloads and four with SAR payloads, the 4+4 constellation). Originally, the launch of all the satellites was to be accomplished by 2012 through international cooperation.
The first stage implementation includes three small satellites (2+1 constellation). The spacecraft of the constellation are referred to as HJ-1A, HJ-1B, and HJ-1C. The HJ-1A and HJ-1B satellites were launched at 03:25UTC on September 6, 2008, by the Chang Zheng-2C/SMA (Y1) launch vehicle from the Taiyuan Satellite Launch Center.
HJ-1A is an optical satellite with a CCD camera and an infrared camera while HJ-1B is equipped with a CCD camera and a hyperspectral camera on board. Each spacecraft has a launch mass of 470 kg, with a size of 1.2 m x 1.1 m x 1.03 m, and a design life of three years.
The satellites were based on the CAST-968B bus of DFHSat (DFH Satellite Co Ltd.) of CAST (China Academy of Space Technology) and by the China Aerospace Science and Technology Corporation. Both satellites are 3-axis stabilized.
The HJ-1C satellite is a spacecraft with an S-band (ТКСА-6К collapsible mesh parabolic antenna) SAR payload based on the CAST-2000 (CAST-968B). The satellite will have a Sun-synchronous circular dawn-dusk orbit, at an altitude of 500 km, 97.3 degrees inclination and a 94 minutes orbital period, with a local time on descending node at 6:00 hours.
The satellite predicted operational life is three years. This is the first civil Synthetic Aperture Radar (SAR) system
The mass of the spacecraft is 890 kg, including 200 kg of its SAR payload. The communications of its payload data will use CCSDS standard to format compressed raw data and its auxiliary data. On board the satellite has 40 Gbit of storage capacity and the transmission is made via X-band downlink with QPSK modulation. The downlink data rate is of 2 x 160 Mbit/s.
Power supply is made by using a solar array with 7.5 m2 using GaAS/Ge solar cells capable of delivering a power of 1.1 kW (BOL) and 0.8 kW (EOL). Power is stored on two batteries (40Ah).
The S-band SAR instrument was developed with the assistance of NPO Mashinostroyenia & Vega Corp. from Russia. The SAR instrument has a 3.13 GHz (S-band) center frequency, corresponding to a wavelength of 9.6 cm, giving a spatial resolution of 20 meters, with a swath width of 100 km.
The SAR instrument will be capable of a two mode operation: Scan Mode and Strip Mode. On Scan Mode it will be able to get a 15 to 25 meter resolution with a swath of 95 to 105 km. The Strip Mode it will be able to get a 4 to 6 meter resolution with a swath of 35 to 40 km.
Other satellites were launched together with Huanjing-1C, the XY Xinyan-1 and the FN-1 Fengniao-1A/B pair.
The Xinyan-1 was build by the Aerospace DFH Development Limited of Shenzhen, the recently established spin-off of CAST’s mini-satellite department. The small satellite will test various components such as China-built microwave switches, a lighter user communication terminal and more accurate thermostats to be used of future satellites.
Also known by NewTech-1 (New Technology Demonstration Satellite), the XY-1 is the first new space technology in-orbit demonstration project developed by enterprises in China and used for in-orbit test demonstration of many new technologies.
The FN-1 Fengniao-1A/B (HummerSat-1) satellites represent the first realization of a new generic micro/minisatellite development of DFHSat (DFH Satellite Co. Ltd.).
The overall objective of the mission is to provide a technology demonstration as well as to test observation capabilities within the spacecraft class of 80-250 kg of total mass envelop (micro/minisatellite), for a number of different missions and applications, including support scenarios of constellations and formation flight (with intersatellite crosslink, relative navigation, guidance and control).
The FN-1 mission concept consists of two satellites, the FN-1A with a launch mass of about 160 kg, as the principal spacecraft of the formation, and a microsatellite, the FN-1B with a mass of 30 kg. Both satellites are launch as a uniform body.
On orbit, FN-1B will be deployed to form a two-spacecraft formation with the main spacecraft. Both spacecraft are in contact with a crosslink for information exchange and the enactment of required orbit manoeuvres. However, all ground communications with the formation is only via the mother spacecraft.
The goal of the mission is to demonstrate the newly developed CAST-mini bus and CAST-micro bus designs in space, in particular to validate their functional capabilities and technologies introduced, and to demonstrate the capability of close formation flying technologies such as relative navigation, guidance and control, intersatellite crosslink, and command.
The Fengniao-1A uses a new modular bus concept, referred to as CAST-mini, which is of CAST-968 and CAST-2000 platform heritage. The CAST-mini bus consists of a cylindrical (octagonal) body with face-mounted solar panels and two deployable T-form solar wings, oriented in the ±Y axis.
The spacecraft body has a size of 785 mm in diameter and 1032 mm in height. Thermal control is provided by passive means (radiator) and assisted by active means (heater) when needed. The satellite has a design life of three years. It is 3-axis stabilized with an Earth-pointing orientation, providing medium pointing and pointing-stability accuracies.
Fengniao-1B is a new microsatellite development of DFHSat. The objectives are to test the new modular platform capabilities in space and to use the spacecraft for formation flying demonstrations with FN-1A. The satellite bus features also an octagonal shape (as the mother spacecraft) with dimensions of 400 mm in diameter and 175 mm in height.
The surface-mounted solar cells (GaAs) provide an average power of ~ 5 W. Orbit and attitude control is provided with RCS (Reaction Control Subsystem) using 12 thrusters (each with 30 mN).
Relative orbit measurements between the two satellites are provided with a differential GPS (DGPS) receiver.
The Chang Zheng-2C launch vehicle:
The Chang Zheng-2C a low Earth orbit launch vehicle derived from DF-5 ICBM. The rocket is a two stage hypergolic launch vehicle with a total length of 35.17 meters, a diameter of 3.35 meters and a total mass of 192,000 kg.
This is a liquid launch vehicle mainly used for Low Earth Orbit (LEO) missions. The CZ-2C is most frequently used version of Long March Launch Vehicles which had 14 consecutive successful flights till October of 1994.
In order to meet the user’s need, China Academy of Launch Vehicle (CALT) developed a new smart dispenser upper stage; the CZ-2C/SD has been used commercially in the late 1990s and conducted seven consecutive successful launches for Iridium program.
The CZ-2C launch vehicle now provides two versions to customers: a basic version composed by a two-stage CZ-2C for LEO missions with typical launch capability of 3,366 kg; and a three-stage version: CZ-2C/CTS for LEO or SSO with typical launch capability of 1,456 kg.
This launcher provides a flexible mechanical and electrical interfaces and length-adjustable fairing for various satellites. The launch environment impinging on the cargo do be launched, such as vibration, shock, pressure, acoustics, acceleration and thermal environment, meets the common requirements in the commercial launch services market.
The first stage is equipped with a cluster of four YF-20A engines (YF-21), having a length of 23.72 meters, a gross mass of 151,000 kg (empty mass of 8,600 kg) and a burn time of 130 seconds.
The second stage is equipped with a cluster of one YF-22A engine with fixed nozzles and a swivelling venire motor consisting of four YF-23 chambers motors (the YF-24), and has a length of 8.71 meters, a gross mass of 38,200 kg (empty mass of 3,200 kg) with a burn time of 112 seconds (main engine) and 287 second (vernier).
In this launch the CZ-2C used an SMA upper stage (possibly using the SpaB-140C solid motor), increasing the SSO payload capability to 1,900 kg.
The Taiyuan Satellite Launch Center:
Situated in the Kelan County on the northwest part of the Shanxi Province, the Taiyuan Satellite Launch Center (TSLC) is also known by the Wuzhai designation. It is used mainly for polar launches (meteorological, Earth resources and scientific satellites).
The center is at a height of 1400-1900m above sea level, and is surrounded by mountains to the east, south and north, with the Yellow River to its west. The annual average temperature is 4-10 degrees C, with maximum of 28 degrees C in summer and minimum of -39 degrees C in winter.
TSLC is suitable for launching a range of satellites, especially for low earth and sun-synchronous orbit missions. The center has state-of-the-art facilities for launch vehicle and spacecraft testing, preparation, launch and in-flight tracking and safety control, as well as for orbit predictions.
http://www.nasaspaceflight.com/2 ... jing-1c-into-orbit/
November 18th, 2012 by Rui C. Barbosa
China conducted its 16th orbital launch of the year by orbiting the third satellite on its Environmental Protection & Disaster Monitoring Constellation. The Huanjing-1C (Environment-1C) satellite was launched at 22:53 UTC on Sunday from the Taiyuan Satellite Launch Center’s LC9 Launch Platform using the Long March 2C (Chang Zheng-2C) launch vehicle.
Chinese Launch:
This was the 171st successful Chinese orbital launch, the 171st launch of a Chang Zheng launch vehicle, the 41st successful orbital launch from Taiyuan and the fifth launch from Taiyuan this year.
The HJ-1 satellites are a network of Earth observing satellites owned by the National Committee for Disaster Reduction and State Environmental Protection Administration of China, with the objective to establish an operational Earth observing system for disaster monitoring and mitigation using remote sensing technology and to improve the efficiency of disaster mitigation and relief.
The main application fields for China are environmental monitoring and prediction, solid waste monitoring, disaster monitoring and prediction (flood, drought, typhoon and wind damage, sand storm, earthquake, land creep, frost and grassland fires, coal fires, crop pest monitoring, ocean disaster monitoring). The program was ratified in 2003 by the Chinese authorities.
See Also
Chinese Forum Section
65 Launch Vehicle Manuals (L2)
Click here to Join L2
In May 2007, the China National Space Administration became the member of the International Charter ‘Space and Major Disasters’, a joint initiative that works to provide emergency response satellite data free of charge to those affected by disasters anywhere in the world.
Each member of the International Charter ‘Space and Major Disasters’ has demonstrated its commitment to use its space assets when it is most needed, when disasters of natural and human origin strike the world’s communities, or wreak havoc on the environment.
The first stage of the program is comprised of three minisatellites, usually referred to as the 2+1 constellation. The second stage of the program will consist of a total of eight spacecraft (four with optical payloads and four with SAR payloads, the 4+4 constellation). Originally, the launch of all the satellites was to be accomplished by 2012 through international cooperation.
The first stage implementation includes three small satellites (2+1 constellation). The spacecraft of the constellation are referred to as HJ-1A, HJ-1B, and HJ-1C. The HJ-1A and HJ-1B satellites were launched at 03:25UTC on September 6, 2008, by the Chang Zheng-2C/SMA (Y1) launch vehicle from the Taiyuan Satellite Launch Center.
HJ-1A is an optical satellite with a CCD camera and an infrared camera while HJ-1B is equipped with a CCD camera and a hyperspectral camera on board. Each spacecraft has a launch mass of 470 kg, with a size of 1.2 m x 1.1 m x 1.03 m, and a design life of three years.
The satellites were based on the CAST-968B bus of DFHSat (DFH Satellite Co Ltd.) of CAST (China Academy of Space Technology) and by the China Aerospace Science and Technology Corporation. Both satellites are 3-axis stabilized.
The HJ-1C satellite is a spacecraft with an S-band (ТКСА-6К collapsible mesh parabolic antenna) SAR payload based on the CAST-2000 (CAST-968B). The satellite will have a Sun-synchronous circular dawn-dusk orbit, at an altitude of 500 km, 97.3 degrees inclination and a 94 minutes orbital period, with a local time on descending node at 6:00 hours.
The satellite predicted operational life is three years. This is the first civil Synthetic Aperture Radar (SAR) system
The mass of the spacecraft is 890 kg, including 200 kg of its SAR payload. The communications of its payload data will use CCSDS standard to format compressed raw data and its auxiliary data. On board the satellite has 40 Gbit of storage capacity and the transmission is made via X-band downlink with QPSK modulation. The downlink data rate is of 2 x 160 Mbit/s.
Power supply is made by using a solar array with 7.5 m2 using GaAS/Ge solar cells capable of delivering a power of 1.1 kW (BOL) and 0.8 kW (EOL). Power is stored on two batteries (40Ah).
The S-band SAR instrument was developed with the assistance of NPO Mashinostroyenia & Vega Corp. from Russia. The SAR instrument has a 3.13 GHz (S-band) center frequency, corresponding to a wavelength of 9.6 cm, giving a spatial resolution of 20 meters, with a swath width of 100 km.
The SAR instrument will be capable of a two mode operation: Scan Mode and Strip Mode. On Scan Mode it will be able to get a 15 to 25 meter resolution with a swath of 95 to 105 km. The Strip Mode it will be able to get a 4 to 6 meter resolution with a swath of 35 to 40 km.
Other satellites were launched together with Huanjing-1C, the XY Xinyan-1 and the FN-1 Fengniao-1A/B pair.
The Xinyan-1 was build by the Aerospace DFH Development Limited of Shenzhen, the recently established spin-off of CAST’s mini-satellite department. The small satellite will test various components such as China-built microwave switches, a lighter user communication terminal and more accurate thermostats to be used of future satellites.
Also known by NewTech-1 (New Technology Demonstration Satellite), the XY-1 is the first new space technology in-orbit demonstration project developed by enterprises in China and used for in-orbit test demonstration of many new technologies.
The FN-1 Fengniao-1A/B (HummerSat-1) satellites represent the first realization of a new generic micro/minisatellite development of DFHSat (DFH Satellite Co. Ltd.).
The overall objective of the mission is to provide a technology demonstration as well as to test observation capabilities within the spacecraft class of 80-250 kg of total mass envelop (micro/minisatellite), for a number of different missions and applications, including support scenarios of constellations and formation flight (with intersatellite crosslink, relative navigation, guidance and control).
The FN-1 mission concept consists of two satellites, the FN-1A with a launch mass of about 160 kg, as the principal spacecraft of the formation, and a microsatellite, the FN-1B with a mass of 30 kg. Both satellites are launch as a uniform body.
On orbit, FN-1B will be deployed to form a two-spacecraft formation with the main spacecraft. Both spacecraft are in contact with a crosslink for information exchange and the enactment of required orbit manoeuvres. However, all ground communications with the formation is only via the mother spacecraft.
The goal of the mission is to demonstrate the newly developed CAST-mini bus and CAST-micro bus designs in space, in particular to validate their functional capabilities and technologies introduced, and to demonstrate the capability of close formation flying technologies such as relative navigation, guidance and control, intersatellite crosslink, and command.
The Fengniao-1A uses a new modular bus concept, referred to as CAST-mini, which is of CAST-968 and CAST-2000 platform heritage. The CAST-mini bus consists of a cylindrical (octagonal) body with face-mounted solar panels and two deployable T-form solar wings, oriented in the ±Y axis.
The spacecraft body has a size of 785 mm in diameter and 1032 mm in height. Thermal control is provided by passive means (radiator) and assisted by active means (heater) when needed. The satellite has a design life of three years. It is 3-axis stabilized with an Earth-pointing orientation, providing medium pointing and pointing-stability accuracies.
Fengniao-1B is a new microsatellite development of DFHSat. The objectives are to test the new modular platform capabilities in space and to use the spacecraft for formation flying demonstrations with FN-1A. The satellite bus features also an octagonal shape (as the mother spacecraft) with dimensions of 400 mm in diameter and 175 mm in height.
The surface-mounted solar cells (GaAs) provide an average power of ~ 5 W. Orbit and attitude control is provided with RCS (Reaction Control Subsystem) using 12 thrusters (each with 30 mN).
Relative orbit measurements between the two satellites are provided with a differential GPS (DGPS) receiver.
The Chang Zheng-2C launch vehicle:
The Chang Zheng-2C a low Earth orbit launch vehicle derived from DF-5 ICBM. The rocket is a two stage hypergolic launch vehicle with a total length of 35.17 meters, a diameter of 3.35 meters and a total mass of 192,000 kg.
This is a liquid launch vehicle mainly used for Low Earth Orbit (LEO) missions. The CZ-2C is most frequently used version of Long March Launch Vehicles which had 14 consecutive successful flights till October of 1994.
In order to meet the user’s need, China Academy of Launch Vehicle (CALT) developed a new smart dispenser upper stage; the CZ-2C/SD has been used commercially in the late 1990s and conducted seven consecutive successful launches for Iridium program.
The CZ-2C launch vehicle now provides two versions to customers: a basic version composed by a two-stage CZ-2C for LEO missions with typical launch capability of 3,366 kg; and a three-stage version: CZ-2C/CTS for LEO or SSO with typical launch capability of 1,456 kg.
This launcher provides a flexible mechanical and electrical interfaces and length-adjustable fairing for various satellites. The launch environment impinging on the cargo do be launched, such as vibration, shock, pressure, acoustics, acceleration and thermal environment, meets the common requirements in the commercial launch services market.
The first stage is equipped with a cluster of four YF-20A engines (YF-21), having a length of 23.72 meters, a gross mass of 151,000 kg (empty mass of 8,600 kg) and a burn time of 130 seconds.
The second stage is equipped with a cluster of one YF-22A engine with fixed nozzles and a swivelling venire motor consisting of four YF-23 chambers motors (the YF-24), and has a length of 8.71 meters, a gross mass of 38,200 kg (empty mass of 3,200 kg) with a burn time of 112 seconds (main engine) and 287 second (vernier).
In this launch the CZ-2C used an SMA upper stage (possibly using the SpaB-140C solid motor), increasing the SSO payload capability to 1,900 kg.
The Taiyuan Satellite Launch Center:
Situated in the Kelan County on the northwest part of the Shanxi Province, the Taiyuan Satellite Launch Center (TSLC) is also known by the Wuzhai designation. It is used mainly for polar launches (meteorological, Earth resources and scientific satellites).
The center is at a height of 1400-1900m above sea level, and is surrounded by mountains to the east, south and north, with the Yellow River to its west. The annual average temperature is 4-10 degrees C, with maximum of 28 degrees C in summer and minimum of -39 degrees C in winter.
TSLC is suitable for launching a range of satellites, especially for low earth and sun-synchronous orbit missions. The center has state-of-the-art facilities for launch vehicle and spacecraft testing, preparation, launch and in-flight tracking and safety control, as well as for orbit predictions.
http://www.nasaspaceflight.com/2 ... jing-1c-into-orbit/Chinese Long March 2C lofts Huanjing-1C into orbit
November 18th, 2012 by Rui C. Barbosa
China conducted its 16th orbital launch of the year by orbiting the third satellite on its Environmental Protection & Disaster Monitoring Constellation. The Huanjing-1C (Environment-1C) satellite was launched at 22:53 UTC on Sunday from the Taiyuan Satellite Launch Center’s LC9 Launch Platform using the Long March 2C (Chang Zheng-2C) launch vehicle.
Chinese Launch:
This was the 171st successful Chinese orbital launch, the 171st launch of a Chang Zheng launch vehicle, the 41st successful orbital launch from Taiyuan and the fifth launch from Taiyuan this year.
The HJ-1 satellites are a network of Earth observing satellites owned by the National Committee for Disaster Reduction and State Environmental Protection Administration of China, with the objective to establish an operational Earth observing system for disaster monitoring and mitigation using remote sensing technology and to improve the efficiency of disaster mitigation and relief.
The main application fields for China are environmental monitoring and prediction, solid waste monitoring, disaster monitoring and prediction (flood, drought, typhoon and wind damage, sand storm, earthquake, land creep, frost and grassland fires, coal fires, crop pest monitoring, ocean disaster monitoring). The program was ratified in 2003 by the Chinese authorities.
See Also
Chinese Forum Section
65 Launch Vehicle Manuals (L2)
Click here to Join L2
In May 2007, the China National Space Administration became the member of the International Charter ‘Space and Major Disasters’, a joint initiative that works to provide emergency response satellite data free of charge to those affected by disasters anywhere in the world.
Each member of the International Charter ‘Space and Major Disasters’ has demonstrated its commitment to use its space assets when it is most needed, when disasters of natural and human origin strike the world’s communities, or wreak havoc on the environment.
The first stage of the program is comprised of three minisatellites, usually referred to as the 2+1 constellation. The second stage of the program will consist of a total of eight spacecraft (four with optical payloads and four with SAR payloads, the 4+4 constellation). Originally, the launch of all the satellites was to be accomplished by 2012 through international cooperation.
The first stage implementation includes three small satellites (2+1 constellation). The spacecraft of the constellation are referred to as HJ-1A, HJ-1B, and HJ-1C. The HJ-1A and HJ-1B satellites were launched at 03:25UTC on September 6, 2008, by the Chang Zheng-2C/SMA (Y1) launch vehicle from the Taiyuan Satellite Launch Center.
HJ-1A is an optical satellite with a CCD camera and an infrared camera while HJ-1B is equipped with a CCD camera and a hyperspectral camera on board. Each spacecraft has a launch mass of 470 kg, with a size of 1.2 m x 1.1 m x 1.03 m, and a design life of three years.
The satellites were based on the CAST-968B bus of DFHSat (DFH Satellite Co Ltd.) of CAST (China Academy of Space Technology) and by the China Aerospace Science and Technology Corporation. Both satellites are 3-axis stabilized.
The HJ-1C satellite is a spacecraft with an S-band (ТКСА-6К collapsible mesh parabolic antenna) SAR payload based on the CAST-2000 (CAST-968B). The satellite will have a Sun-synchronous circular dawn-dusk orbit, at an altitude of 500 km, 97.3 degrees inclination and a 94 minutes orbital period, with a local time on descending node at 6:00 hours.
The satellite predicted operational life is three years. This is the first civil Synthetic Aperture Radar (SAR) system
The mass of the spacecraft is 890 kg, including 200 kg of its SAR payload. The communications of its payload data will use CCSDS standard to format compressed raw data and its auxiliary data. On board the satellite has 40 Gbit of storage capacity and the transmission is made via X-band downlink with QPSK modulation. The downlink data rate is of 2 x 160 Mbit/s.
Power supply is made by using a solar array with 7.5 m2 using GaAS/Ge solar cells capable of delivering a power of 1.1 kW (BOL) and 0.8 kW (EOL). Power is stored on two batteries (40Ah).
The S-band SAR instrument was developed with the assistance of NPO Mashinostroyenia & Vega Corp. from Russia. The SAR instrument has a 3.13 GHz (S-band) center frequency, corresponding to a wavelength of 9.6 cm, giving a spatial resolution of 20 meters, with a swath width of 100 km.
The SAR instrument will be capable of a two mode operation: Scan Mode and Strip Mode. On Scan Mode it will be able to get a 15 to 25 meter resolution with a swath of 95 to 105 km. The Strip Mode it will be able to get a 4 to 6 meter resolution with a swath of 35 to 40 km.
Other satellites were launched together with Huanjing-1C, the XY Xinyan-1 and the FN-1 Fengniao-1A/B pair.
The Xinyan-1 was build by the Aerospace DFH Development Limited of Shenzhen, the recently established spin-off of CAST’s mini-satellite department. The small satellite will test various components such as China-built microwave switches, a lighter user communication terminal and more accurate thermostats to be used of future satellites.
Also known by NewTech-1 (New Technology Demonstration Satellite), the XY-1 is the first new space technology in-orbit demonstration project developed by enterprises in China and used for in-orbit test demonstration of many new technologies.
The FN-1 Fengniao-1A/B (HummerSat-1) satellites represent the first realization of a new generic micro/minisatellite development of DFHSat (DFH Satellite Co. Ltd.).
The overall objective of the mission is to provide a technology demonstration as well as to test observation capabilities within the spacecraft class of 80-250 kg of total mass envelop (micro/minisatellite), for a number of different missions and applications, including support scenarios of constellations and formation flight (with intersatellite crosslink, relative navigation, guidance and control).
The FN-1 mission concept consists of two satellites, the FN-1A with a launch mass of about 160 kg, as the principal spacecraft of the formation, and a microsatellite, the FN-1B with a mass of 30 kg. Both satellites are launch as a uniform body.
On orbit, FN-1B will be deployed to form a two-spacecraft formation with the main spacecraft. Both spacecraft are in contact with a crosslink for information exchange and the enactment of required orbit manoeuvres. However, all ground communications with the formation is only via the mother spacecraft.
The goal of the mission is to demonstrate the newly developed CAST-mini bus and CAST-micro bus designs in space, in particular to validate their functional capabilities and technologies introduced, and to demonstrate the capability of close formation flying technologies such as relative navigation, guidance and control, intersatellite crosslink, and command.
The Fengniao-1A uses a new modular bus concept, referred to as CAST-mini, which is of CAST-968 and CAST-2000 platform heritage. The CAST-mini bus consists of a cylindrical (octagonal) body with face-mounted solar panels and two deployable T-form solar wings, oriented in the ±Y axis.
The spacecraft body has a size of 785 mm in diameter and 1032 mm in height. Thermal control is provided by passive means (radiator) and assisted by active means (heater) when needed. The satellite has a design life of three years. It is 3-axis stabilized with an Earth-pointing orientation, providing medium pointing and pointing-stability accuracies.
Fengniao-1B is a new microsatellite development of DFHSat. The objectives are to test the new modular platform capabilities in space and to use the spacecraft for formation flying demonstrations with FN-1A. The satellite bus features also an octagonal shape (as the mother spacecraft) with dimensions of 400 mm in diameter and 175 mm in height.
The surface-mounted solar cells (GaAs) provide an average power of ~ 5 W. Orbit and attitude control is provided with RCS (Reaction Control Subsystem) using 12 thrusters (each with 30 mN).
Relative orbit measurements between the two satellites are provided with a differential GPS (DGPS) receiver.
The Chang Zheng-2C launch vehicle:
The Chang Zheng-2C a low Earth orbit launch vehicle derived from DF-5 ICBM. The rocket is a two stage hypergolic launch vehicle with a total length of 35.17 meters, a diameter of 3.35 meters and a total mass of 192,000 kg.
This is a liquid launch vehicle mainly used for Low Earth Orbit (LEO) missions. The CZ-2C is most frequently used version of Long March Launch Vehicles which had 14 consecutive successful flights till October of 1994.
In order to meet the user’s need, China Academy of Launch Vehicle (CALT) developed a new smart dispenser upper stage; the CZ-2C/SD has been used commercially in the late 1990s and conducted seven consecutive successful launches for Iridium program.
The CZ-2C launch vehicle now provides two versions to customers: a basic version composed by a two-stage CZ-2C for LEO missions with typical launch capability of 3,366 kg; and a three-stage version: CZ-2C/CTS for LEO or SSO with typical launch capability of 1,456 kg.
This launcher provides a flexible mechanical and electrical interfaces and length-adjustable fairing for various satellites. The launch environment impinging on the cargo do be launched, such as vibration, shock, pressure, acoustics, acceleration and thermal environment, meets the common requirements in the commercial launch services market.
The first stage is equipped with a cluster of four YF-20A engines (YF-21), having a length of 23.72 meters, a gross mass of 151,000 kg (empty mass of 8,600 kg) and a burn time of 130 seconds.
The second stage is equipped with a cluster of one YF-22A engine with fixed nozzles and a swivelling venire motor consisting of four YF-23 chambers motors (the YF-24), and has a length of 8.71 meters, a gross mass of 38,200 kg (empty mass of 3,200 kg) with a burn time of 112 seconds (main engine) and 287 second (vernier).
In this launch the CZ-2C used an SMA upper stage (possibly using the SpaB-140C solid motor), increasing the SSO payload capability to 1,900 kg.
The Taiyuan Satellite Launch Center:
Situated in the Kelan County on the northwest part of the Shanxi Province, the Taiyuan Satellite Launch Center (TSLC) is also known by the Wuzhai designation. It is used mainly for polar launches (meteorological, Earth resources and scientific satellites).
The center is at a height of 1400-1900m above sea level, and is surrounded by mountains to the east, south and north, with the Yellow River to its west. The annual average temperature is 4-10 degrees C, with maximum of 28 degrees C in summer and minimum of -39 degrees C in winter.
TSLC is suitable for launching a range of satellites, especially for low earth and sun-synchronous orbit missions. The center has state-of-the-art facilities for launch vehicle and spacecraft testing, preparation, launch and in-flight tracking and safety control, as well as for orbit predictions.
http://www.nasaspaceflight.com/2 ... jing-1c-into-orbit/
鸟文看不懂！
继续找爹，情报搜集能力不过如此
这个问题航空航天港早就扯过了,楼主是从火星来的
此文作者说环境1C星上搭载的S波段SAR设备是由俄罗斯NPO Mashinostroyenia（俄罗斯机械制造工艺科学生产联合体） 和 Vega Corp.协助开发的
QGP 发表于 2012-11-20 10:11 
这个问题航空航天港早就扯过了,楼主是从火星来的
您的域名因未备案禁止访问。
...航天港怎么上不去了。。
这个问题航空航天港早就扯过了,楼主是从火星来的
您的域名因未备案禁止访问。
...航天港怎么上不去了。。
9ifly忘记备案了？
毛子帮着交付的这个S波段SAR载荷重量200kg？
SAR星早期发展时，有加拿大和德国的技术支援！不过现在嘛，就不知道了
本来用毛子造的天线，迟迟不交货，后来又自己研制的。耽误好几年。航空航天港有帖子
这天线好像比较复杂（转自航空航天港）
zjl625 发表于 2012-11-21 01:32
这天线好像比较复杂（转自航空航天港）
这天线好像比较复杂（转自航空航天港）
关键是这个展开过程地面上没法完全模拟
楼主你out了;P
“逼”出来的国产化创新
2008年9月6日，环境与灾害监测预报小卫星A、B星发射成功，而相约1年后与A、B星同组星座的C星却迟迟没有踏上太空旅程。同时，型号改变了依靠国际合作获得C星星载探测仪器的原计划，而是加快了国产化自主创新的研制进程。
这是因为，立项中原来采用国际合作方式引进的SAR天线和微波功率放大器两大重要部件，由于迟迟不交付和出口许可证等因素不了了之，使得C星研制进度受到影响。
在各方面的支持下，研制团队于2008年和2010年分别启动了固态发射机国产化研制工作和SAR天线国产化正样研制工作。中国航天科技集团公司五院航天东方红卫星有限公司为加强研制力量，确保型号进度和质量，加强了型号指挥线和技术线的力量。型号队伍上下也都以昂扬斗志，铆足了劲要啃下这块硬骨头。 在“两总”带领下，型号队伍最终实现了多项关键技术的突破。环境与灾害监测预报小卫星C星成为我国首个具有全天时、全天候监测能力的民用微波遥感卫星，其成熟的CAST2000平台和集中式体制的SAR有效载荷技术相结合，在国内属于首创，在国际上也处于领先地位，同时，为我国合成孔径雷达卫星朝着轻小型化的方向发展开辟出了新的技术途径。
卫星总体和研制单位在SAR天线和发射机改为国产化后，经过一系列技术攻关，形成了具有国际先进意义的诸多技术创新点，包括星载大功率固态发射机、构架式可展开SAR天线、双母线在CAST2000平台上的首次应用、转动惯量多变的姿控自适应控制以及真空微放电问题的有效解决等等。
“鉴于SAR分系统是首次研制，集团公司宇航部还专门组织专家对载荷分系统进行独立评估，审查评估工作更加有针对性，并取得了良好效果。”工程总设计师郭宝柱欣慰地感慨道，“整星研制虽然受到国外技术问题的限制，但也迫使我们自主创新，自力更生，实现了技术突破，填补了技术空白，对我国民用航天体系建设具有重大意义。”
“逼”出来的国产化创新
2008年9月6日，环境与灾害监测预报小卫星A、B星发射成功，而相约1年后与A、B星同组星座的C星却迟迟没有踏上太空旅程。同时，型号改变了依靠国际合作获得C星星载探测仪器的原计划，而是加快了国产化自主创新的研制进程。
这是因为，立项中原来采用国际合作方式引进的SAR天线和微波功率放大器两大重要部件，由于迟迟不交付和出口许可证等因素不了了之，使得C星研制进度受到影响。
在各方面的支持下，研制团队于2008年和2010年分别启动了固态发射机国产化研制工作和SAR天线国产化正样研制工作。中国航天科技集团公司五院航天东方红卫星有限公司为加强研制力量，确保型号进度和质量，加强了型号指挥线和技术线的力量。型号队伍上下也都以昂扬斗志，铆足了劲要啃下这块硬骨头。 在“两总”带领下，型号队伍最终实现了多项关键技术的突破。环境与灾害监测预报小卫星C星成为我国首个具有全天时、全天候监测能力的民用微波遥感卫星，其成熟的CAST2000平台和集中式体制的SAR有效载荷技术相结合，在国内属于首创，在国际上也处于领先地位，同时，为我国合成孔径雷达卫星朝着轻小型化的方向发展开辟出了新的技术途径。
卫星总体和研制单位在SAR天线和发射机改为国产化后，经过一系列技术攻关，形成了具有国际先进意义的诸多技术创新点，包括星载大功率固态发射机、构架式可展开SAR天线、双母线在CAST2000平台上的首次应用、转动惯量多变的姿控自适应控制以及真空微放电问题的有效解决等等。
“鉴于SAR分系统是首次研制，集团公司宇航部还专门组织专家对载荷分系统进行独立评估，审查评估工作更加有针对性，并取得了良好效果。”工程总设计师郭宝柱欣慰地感慨道，“整星研制虽然受到国外技术问题的限制，但也迫使我们自主创新，自力更生，实现了技术突破，填补了技术空白，对我国民用航天体系建设具有重大意义。”
这种卫星对地观测能达到什么效果，能发现大气层内的较小的飞行器吗，比如战斗机，无人机等？
很科幻的赶脚关键是这个展开过程地面上没法完全模拟
钱老说过，所有上天的系统必须经过地面验证，所以必然是验证过的
钱老说过，所有上天的系统必须经过地面验证，所以必然是验证过的
楼主你out了
“逼”出来的国产化创新
研制单位是我国空间天线最牛的单位
“逼”出来的国产化创新
研制单位是我国空间天线最牛的单位
梦醉长安 发表于 2012-11-22 23:22
钱老说过，所有上天的系统必须经过地面验证，所以必然是验证过的
我说的话不要跳着看
钱老说过，所有上天的系统必须经过地面验证，所以必然是验证过的
我说的话不要跳着看
环境1c命运坎坷，过程一拖再拖。
xtal 发表于 2012-11-22 23:48
我说的话不要跳着看
展开过程是可以验证的，最主要的问题是怎么在空间中掌握天线是否展开到位，这个也没有问题
我说的话不要跳着看
展开过程是可以验证的，最主要的问题是怎么在空间中掌握天线是否展开到位，这个也没有问题
梦醉长安 发表于 2012-11-24 11:37
展开过程是可以验证的，最主要的问题是怎么在空间中掌握天线是否展开到位，这个也没有问题
把我回复的那句话一个字一个字看清楚。
别象下跳棋一样跳着看
展开过程是可以验证的，最主要的问题是怎么在空间中掌握天线是否展开到位，这个也没有问题
把我回复的那句话一个字一个字看清楚。
别象下跳棋一样跳着看
xtal 发表于 2012-11-21 13:14
关键是这个展开过程地面上没法完全模拟
超大现在跳棋党越来越多了
关键是这个展开过程地面上没法完全模拟
超大现在跳棋党越来越多了