Flashover Plasma Characteristics on 5m2 Solar Array Panels in a Simulated Plasma Environment of Geostationary Orbit and Low Earth Orbit

2010 ◽  
Author(s):  
Teppei Okumura ◽  
Tomonori Suzuki ◽  
Kumi Nitta ◽  
Masato Takahashi ◽  
Kazuhiro Toyoda
Keyword(s):  
Low Earth Orbit ◽  
Geostationary Orbit ◽  
Solar Array ◽  
Earth Orbit ◽  
Plasma Environment ◽  
Plasma Characteristics

Development of 400 V Solar Array Technology for Low Earth Orbit Plasma Environment

2006 ◽  
Vol 34 (5) ◽  
pp. 1986-1996 ◽  
Author(s):  
S. Hosoda ◽  
T. Okumura ◽  
J.-H. Kim ◽  
K. Toyoda ◽  
M. Cho
Keyword(s):  
Low Earth Orbit ◽  
Solar Array ◽  
Earth Orbit ◽  
Plasma Environment ◽  
Array Technology

scholarly journals Threshold for Secondary Arc Formation on Solar Array in Low Earth Orbit Plasma Environment

2005 ◽  
Vol 53 (622) ◽  
pp. 516-523 ◽  
Author(s):  
Seiji Aso ◽  
Tomoki Kitamura ◽  
Satoshi Hosoda ◽  
Jeongho Kim ◽  
Mengu Cho ◽  
...  
Keyword(s):  
Low Earth Orbit ◽  
Solar Array ◽  
Earth Orbit ◽  
Plasma Environment

Verification of solar array design for low earth orbit spacecraft under worst case scenario

2018 ◽  
Author(s):  
Ahmed Mokhtar Mohamed ◽  
Fawzy ElTohamy H. Amer ◽  
R. M. Mostafa ◽  
Walid A. Wahballah
Keyword(s):  
Low Earth Orbit ◽  
Solar Array ◽  
Earth Orbit ◽  
Case Scenario ◽  
Worst Case ◽  
Array Design ◽  
Worst Case Scenario

A Comparative Study of Satellite Orbits as Low Earth Orbit (LEO) and Geostationary Earth Orbit (GEO)

2015 ◽  
Vol 6 (2) ◽  
Author(s):  
Sandeep Vishwakarma ◽  
Aradhana S. Chauhan ◽  
Shoeba Aasma
Keyword(s):  
Satellite Orbit ◽  
Low Earth Orbit ◽  
Geostationary Orbit ◽  
Earth Orbit ◽  
Satellite Orbits ◽  
Satellite Systems ◽  
Broadcast Television ◽  
Television Use ◽  
Gps System ◽  
Orbiting Systems

It is known facts that satellites are used to receive the signal at geostationary orbit by remaining stationary above a particular point on the Earth. The orbit that is chosen for a satellite depends upon its application. Those used for direct broadcast television use geostationary orbit. Many communication satellites similarly use geostationary orbit. Other satellite systems used for satellite phones use Low Earth orbiting systems. Similarly, satellite systems used for navigation like Nav-star or Global Positioning (GPS) system occupy a relatively Low Earth Orbit. There are also many other types of satellites : Weather satellites Research satellites and many others. Each will have its own type of orbit depending upon its application. The actual satellite orbit that is chosen will depend on factors including its function, and the area of serving. At some instances, the satellite orbit may be as low as 100 miles (160 km) for a Low Earth Orbit (LEO), whereas others may be over 22 000 miles (36000 km) high as in the case of a Geostationary Orbit (GEO). The satellite may even has an elliptical rather than a circular orbit.

The characteristics of primary and secondary arcs on a solar array in low earth orbit

2017 ◽  
Vol 19 (5) ◽  
pp. 055304
Author(s):  
Liying ZHU ◽  
Linchun FU ◽  
Ming QIAO ◽  
Bo CUI ◽  
Qi CHEN ◽  
...  
Keyword(s):  
Low Earth Orbit ◽  
Solar Array ◽  
Earth Orbit

Orbital transfer vehicle (OTV) system sizing study for manned GEO satellite servicing

2016 ◽  
Vol 120 (1226) ◽  
pp. 573-599 ◽  
Author(s):  
B. Chudoba ◽  
G. Coleman ◽  
L. Gonzalez ◽  
E. Haney ◽  
A. Oza ◽  
...  
Keyword(s):  
Low Earth Orbit ◽  
Geostationary Orbit ◽  
Earth Orbit ◽  
Orbital Transfer ◽  
Geo Satellite ◽  
Satellite Servicing ◽  
Geo Satellites ◽  
Kennedy Space ◽  
Cost Factors ◽  
Concept Of Operations

ABSTRACTIn an effort to quantify the feasibility of candidate space architectures for astronauts servicing Geosynchronous Earth Orbit (GEO) satellites, a conceptual assessment of architecture-concept and operations-technology combinations has been performed. The focus has been the development of a system with the capability to transfer payload to and from geostationary orbit. Two primary concepts of operations have been selected: (a) Direct insertion/re-entry (Concept of Operations 1 – CONOP 1); (b) Launch to low-earth orbit at Kennedy Space Center inclination angle with an orbital transfer to/from geostationary orbit (Concept of Operations 2 – CONOP 2). The study concludes that a capsule and de-orbit propulsion module system sized for the geostationary satellite servicing mission is feasible for a direct insertion/re-entry concept of operation CONOP 1. Vehicles sized for CONOP 2 show overall total mass savings when utilising the aero-assisted orbital transfer vehicle de-orbit propulsion module options compared to the pure propulsive baseline cases. Overall, the consideration of technical, operational and cost factors determine if either the aero-assisted orbital transfer vehicle concepts or the re-usable/expendable ascent/de-orbit propulsion modules is the preferred option.

scholarly journals The Failure Analysis of Paralleled Solar Array Regulator for Satellite Power System in Low Earth Orbit

2011 ◽  
Vol 28 (2) ◽  
pp. 133-141
Author(s):  
Sung-Soo Jang ◽  
Sung-Hoon Kim ◽  
Sang-Ryool Lee ◽  
Jae-Ho Choi
Keyword(s):  
Power System ◽  
Failure Analysis ◽  
Low Earth Orbit ◽  
Solar Array ◽  
Earth Orbit
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