Dr. Jinpei Yu Profile

Dr. Jinpei Yu

at Innovation Academy for Microsatellites of CAS

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Author

Publications (10)

Proceedings Article | 31 August 2022 Paper

Mission pointing optimisation of twin satellite system for all-sky burst monitoring

Xingbo Han, Fei Li, Liang Chang, Keke Zhang, Jinpei Yu, Hao Geng

Proceedings Volume 12181, 121815B (2022) https://doi.org/10.1117/12.2629160

KEYWORDS: Satellites, Solar energy, Error analysis, Sun, Electromagnetism, Astronomy, X-rays

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Proceedings Article | 24 November 2021 Paper

VHF coverage analysis for quasi-equatorial Earth satellites

Hu Jiang, Lei Deng, Wen Chen, Jinpei Yu, Zhiming Cai

Proceedings Volume 12061, 120610H (2021) https://doi.org/10.1117/12.2603266

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Space environment above Quasi-equatorial ground has an advantage of relative quietness and friendliness. It is preferred to deploy satellites of demanding stability and longer lifespan. For these satellites, the communication via VHF between ground stations and satellites has become one of the difficulties when it comes to the satellite engineering. To make a quantitative assessment, the satellite VHF coverage of ground stations are carried out for two typical orbits, of which the altitude are roughly 500km and 550km,and the inclination is 2.5 deg. Ground stations for VHF communication include the 88 stations, which are distributed along the belt with latitude less than +/-30deg. The cutoff angles for VHF communication are 10 deg. Two antenna for communication are fixed in the satellite body along +Z axis and –Z axis respectively, and the half beam angle of the boresight is 90 deg. Simulations of satellites based VHF coverage of 88 ground stations are carried out. During case 1, satellite orbit altitude is assumed to be 500km,and inclination is 2.5 deg. For case 2, satellite orbit altitude is assumed to be 550km,and inclination is 2.5 deg. Satellite-based VHF coverages of 88 ground stations are 63.3% for case 1,and 66.5% for case 2. For case 1, yearly VHF communication opportunities are 34594 times. Average duration is 576 seconds. Daily VHF communication opportunities are 95 times. Daily available communication interval is 912 minutes. The unavailable time interval is 28.2 minutes. For case 2, yearly VHF communication opportunities are 29161 times. Average duration is 718 seconds. Daily VHF communication opportunities are 80 times. Daily available communication interval is 957 minutes. The unavailable time interval is 26.4 minutes. Case 1 is preferred if satellite engineering demands more quiet space environment. Case 2 is preferred if satellite engineering demands longer lifespan and better coverage. It is suggested that case 2 be a good choice for space science mission devoted to observe astronomical events in remote space.

Proceedings Article | 13 December 2020 Poster + Paper

Mechanical design and analysis of the eXTP satellite

Rui Liu, Cheng Zhu, Wen Chen, Tao He, Aimei Zhang, Yupeng Xu, Jinpei Yu, Zhencai Zhu, Shuangnan Zhang, Fangjun Lu

Proceedings Volume 11444, 114448F (2020) https://doi.org/10.1117/12.2562170

KEYWORDS: Satellites, Mechanical engineering, X-ray telescopes, Sensors, Structural design, Polarimetry, Cameras, Mirrors, Integrated optics, X-ray detectors

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Proceedings Article | 13 December 2020 Paper

Mission analysis and preliminary spacecraft design of the enhanced x-ray timing and polarimetry observatory

Wen Chen, Zhencai Zhu, Yupeng Xu, Xingbo Han, Yehai Chen, Xingzi Bi, Qi Shi, Rui Liu, Xiangyu Chao, Cheng Zhu, Weiwei Zhao, Shuangnan Zhang, Fangjun Lu, Marco Feroci, Margarita Hernanz, Huili Yuan, Yingquan Yang, Junwang He, Yuan Fang, Yueting Zhang, Xingjian Shi, Kuoxiang Zhang, Jinpei Yu

Proceedings Volume 11444, 114442E (2020) https://doi.org/10.1117/12.2562138

KEYWORDS: Polarimetry, X-rays, Observatories, Space operations, Satellites, States of matter, Magnetism, Spectroscopes, Sensors, Earth observing sensors

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Proceedings Article | 10 October 2020 Poster + Paper

Simulation study of data transmission for equatorial Earth satellites

Hu Jiang, Lei Deng, Wen Chen, Jinpei Yu

Proceedings Volume 11555, 1155517 (2020) https://doi.org/10.1117/12.2573107

KEYWORDS: Data transmission, Satellites, Antennas

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Some Earth satellites are to be deployed in equatorial orbit in order to realize their particular objectives. For these satellites, the data transmission between ground stations and satellites has become one of the difficulties when the satellite engineering is to be realized. To make a quantitative assessment, simulations of data transmission are carried out for two typical orbits, of which the altitude are roughly 500km and 550km,and the inclination is 0 deg. Ground stations for data transmission include the such stations as Sanya China, Kourou France, Malindi Kenya. The longitude is 109.3 deg E., and the latitude is 18.3 deg N. for the station of Sanya. The longitude is 40.2 deg E., and the latitude is -3.0 deg S. for the station of Malindi. The longitude is -52.8 deg W., and the latitude is 5.3 deg N. for the station of Kourou. For Sanya, the cutoff angle for data transmission are 10 deg. For both Malindi and Kourou, the cutoff angles for data transmission are 5 deg. Two antenna for data transmission are fixed in the satellite body along +Z axis and –Z axis respectively, and the half beam angle of the boresight is 1 deg. Antenna for data transmission can scan +/-70deg both in X axis and in Y axis. Two cases are considered herein. Case 1 is that data transmission is only allowed when the celestial objects in question are obstructed by the Earth. Case 2 is that data transmission is allowed without considering the celestial objects obstruction by the Earth. For orbit altitude of 500km, 35 times data transmission are available, the average data transmission period is 305 sec,178 minutes are available for data transmission each day in Case 1; For orbit altitude of 550km, 36 times for data transmission are available, the average data transmission period is 322 sec,193 minutes are available for data transmission each day in Case 1. For orbit altitude of 500km, 9.5 times data transmission are available, the average data transmission period is 266 sec,42 minutes are available for data transmission each day in Case 2; For orbit altitude of 550km, 9.9 times for data transmission are available, the average data transmission period is 278 sec,46 minutes are available for data transmission each day in Case 2. The simulations of data transmission will support finalizing the data transmission planning before the satellite engineering project comes true.

Proceedings Article | 14 February 2020 Paper

Orbit optimization of spacecraft for remote sensing of Qinghai-Tibet plateau

Hu Jiang, Lei Deng, Jinpei Yu, Yuesheng Jiang

Proceedings Volume 11432, 114320W (2020) https://doi.org/10.1117/12.2537669

KEYWORDS: Space operations, Remote sensing, Meteorology, Hydrology, LIDAR, Radiometry, Radar, Space sensors, Sensors, Solar energy

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Qinghai-Tibet plateau is one of the increasingly important parts of Chinese Mainland. After military tension at the boundary between China and India appeared a few years ago, China is focusing on such tasks as remote sensing of Qinghai-Tibet plateau. Qinghai-Tibet plateau is too large to collect basic dataset of meteorology, greenery, and hydrology by manual means. Space-based technique can meet such an requirement. Such payloads onboard spacecraft as lidar, radiometer, radar can provide a good solution to effectively collect dataset for a particular area of interest. With the deployment of comprehensive survey of Qinghai-Tibet plateau by China, the feasibilities assessment of implementing space project to monitor the Qinghai-Tibet plateau are impending. How to choose the most proper orbit is one of the tasks of feasibilities assessment. Herein, three sets of orbits are simulated and assessed. In case 1, a circular orbit with 250 kilometers in altitude is analyzed, and the operation orbit is sun-synchronous. According to relative simulations, orbital altitude damping rate is 10.2 kilometers per day. In order to keep the stable orbit altitude or offset the orbit altitude damping, 558 kilograms of fuel should be needed per year; 1117 kilograms of fuel should be needed to keep a stable orbit every two years. In case 2, an elliptic orbit with perigee altitude of 250km and apogee altitude of 500km is considered. Based on relative simulations, orbital altitude damping rate is 2.461 kilometers per day. In order to keep the stable orbit altitude or offset the orbit altitude damping, 130 kilograms of fuel should be needed per year; 261 kilograms of fuel should be needed to keep a stable orbit every two years. In case 3, an elliptic orbit with perigee altitude of 250km and apogee altitude of 600km is considered. Based on relative simulations, orbital altitude damping rate is 1.67 kilometers per day. In order to keep the stable orbit altitude or offset the orbit altitude damping, 87.6 kilograms of fuel should be needed per year; 175.2 kilograms of fuel should be needed to keep a stable orbit every two years. During the simulation and assessment, the ratio of area to mass of the spacecraft in question is assumed to be 0.01 square meters per kilograms; and the mass of the spacecraft is set to be 500 kilograms. As a result of trade-off between economy and payload priority of observation advantages, the case 3 is preferred to work as the operation orbit. In such an orbit, the spacecraft will contribute more efficiently to the comprehensive surveying of Qinghai-Tibet plateau.

Proceedings Article | 18 December 2019 Paper

Effects of solar radio flux on payload pointing variation for the Earth observation spacecraft

Hu Jiang, Lei Deng, Jinpei Yu, Zhiming Cai, Yuesheng Jiang

Proceedings Volume 11338, 1133802 (2019) https://doi.org/10.1117/12.2538251

KEYWORDS: Sensors, Solar processes, Satellites, Space operations, Optical simulations, Control systems design, Reliability, Remote sensing

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For most Earth observation spacecrafts (EOS), repeating sun-synchronous orbit is a preferred working orbit for the Earth observation spacecraft. Repeating ground trace can provide an ideal observation geometry for space-crafts devoted to Earth observation missions. Sun-synchronous orbit can provide an ideal supply of solar power for the space-crafts. Payloads for EOS usually need demanding pointing stability. One of the main factors which may lead to the variation of payload pointing is the solar radio flux. In different year, the solar radio flux varies. This paper focuses on the characteristics of payload pointing stability due to the variation of the solar radio flux. As historic dataset, solar radio flux shows periodic change of 11 years. In 11 years, solar radio flux experiences the maximal and the minimal solar flux units (sfu). In the case of the payload beam boresight, the simulation results indicate that during the year of severe solar activity with 230sfu, 4 months of orbit drifting without any orbit maneuver will result in payload pointing change less than ±2 deg, and that during the year of severe solar activity with 230 sfu, 2 months of orbit drifting without any orbit maneuver will result in payload pointing change less than ±0.5 deg. And the simulations also indicate that during the year of average solar activity with 150sfu, 4 months of orbit drifting without any orbit maneuver will result in payload pointing change less than ±0.5 deg, and that during the year of average solar activity with 150sfu, 2 months of orbit drifting without any orbit maneuver will result in payload pointing change less than ±0.1 deg; In the case of the payload beam edge, the simulation results indicate that during the year of severe solar activity with 230sfu, 4 months of orbit drifting without any orbit maneuver will result in payload pointing change less than ±5 deg, and that during the year of severe solar activity with 230 sfu, 2 months of orbit drifting without any orbit maneuver will result in payload pointing change less than ± deg. And the simulations also indicate that during the year of average solar activity with 150sfu, 4 months of orbit drifting without any orbit maneuver will result in payload pointing change less than ±2 deg, and that during the year of average solar activity with 150sfu, 2 months of orbit drifting without any orbit maneuver will result in payload pointing change less than ±0.5 deg; The simulations provide an effective constraint of orbit maneuver scenario planning, and further boost the feasibility of space-crafts engineering.

Proceedings Article | 9 November 2018 Paper

Simulations of link opportunities between LEO Satellite and ground sites via modernized BDS

Hu Jiang, Wen Chen, Jinpei Yu, Zhiming Cai, Yuesheng Jiang

Proceedings Volume 10826, 108261U (2018) https://doi.org/10.1117/12.2503869

KEYWORDS: Satellites, Satellite communications, Space operations, Satellite navigation systems, Computer simulations, Navigation systems, Telecommunications

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Proceedings Article | 24 October 2017 Paper

Simulation of some vital space radiation characteristics for a magnetosphere probing mission

Hu Jiang, Jinpei Yu

Proceedings Volume 10463, 104630S (2017) https://doi.org/10.1117/12.2281175

KEYWORDS: Magnetosphere

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Proceedings Article | 24 October 2013 Paper

TDRS satellite application to LEO satellite data link

Hu Jiang, Xue-min Shen, Wenbin Gong, Jinpei Yu

Proceedings Volume 8889, 88891Y (2013) https://doi.org/10.1117/12.2026920

KEYWORDS: Satellites, Satellite communications, Data communications, Computer simulations, Aerospace engineering, Data centers, Data processing, Microsystems, Information technology, Relays

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With the development of space technologies, satellite-based data link is becoming more and more popular due to its wide coverage. However, it needs tens of LEO satellites, short for Low Earth Orbiting satellites, to cover the whole Earth in real time. Therefore it requires huge investment to fulfill such an engineering. If several TDRS satellites, short for Tracking and Data Relaying Satellites, are included, the engineering investment might as well be acceptable. Herein, simulations of coverage and some particular performances are presented in three cases, i.e., a single LEO satellite plus one TDRS satellite, a single LEO satellite plus two TDRS satellite, a single LEO satellite plus three TDRS satellite. Simulations have shown that in the case of one LEO satellite and one TDRS satellite, the revisiting period is 5726s,which will shorten the revisiting period by 57%;the encounter frequency between one LEO and one TDRS is 11 times daily; the average duration for every encounter is 2128s. The performances of one LEO satellite and two TDRS satellites are presented as followings：the revisiting period is 2819s,which will shorten the revisiting period by 79%;the encounter frequency among one LEO and two TDRS is 23 times daily;the average duration for every encounter is 2049s.The performances of one LEO satellite and two TDRS satellites are presented as followings：the revisiting period is 1780s,which will shorten the revisiting period by 87%;the encounter frequency among one LEO and two TDRS is 34 times daily;the average duration for every encounter is 2067s. The above simulations have indicated TDRS satellites can greatly improve LEO satellite coverage and related performances. For china customers, the space orbits of TDRS are limited by either geographical positions or by orbital space regulation in equator. Such limitations make sparsely-distributed LEO satellites global real-time data link difficult, especially above western hemisphere. LEO satellite data link above some of the western hemisphere has to be retarded. Delayed data link are hardly acceptable for some emergency rescues. Before the constellation of tens of LEO communication satellites is deployed in space, it might be a good choice to realize LEO satellite data link via TDRS satellites for China users.

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