TY - GEN
T1 - Low inclination circular orbits for remote sensing satellites
AU - Kamalaldin, Karim
AU - Okasha, Mohamed
N1 - Publisher Copyright:
© (2014) Trans Tech Publications, Switzerland.
PY - 2014
Y1 - 2014
N2 - This paper investigates the design methodology of low Earth inclined circular orbits for remote sensing satellites to satisfy certain mission requirements and constrains such as coverage, resolution, illumination conditions and attitude maneuvers capabilities. Although sun synchronous orbit (SSO) proved to be a good candidate for most remote sensing applications due to its constant lighting conditions and global coverage, low inclined orbits are distinguished by long ground track especially if the target area of concern has horizontal rectangular border. With that respect, low inclined orbits may lead to improvement of the satellite imaging accessibility to the target area per day or reduction of satellite revisit time compared to SSO. This paper exploits these characteristics for low inclined orbits. The target area considered in simulation is between 22° and 32° N latitude lines with 2.5 m ground sample resolution. The satellite maximum rolling capability is 35° and the sun elevation angle is constrained between 30° and 70° for purpose of maximizing the quality of the obtained images. Matlab and STK software are employed to define the initial orbital parameters to meet these conditions for a low inclined orbit.
AB - This paper investigates the design methodology of low Earth inclined circular orbits for remote sensing satellites to satisfy certain mission requirements and constrains such as coverage, resolution, illumination conditions and attitude maneuvers capabilities. Although sun synchronous orbit (SSO) proved to be a good candidate for most remote sensing applications due to its constant lighting conditions and global coverage, low inclined orbits are distinguished by long ground track especially if the target area of concern has horizontal rectangular border. With that respect, low inclined orbits may lead to improvement of the satellite imaging accessibility to the target area per day or reduction of satellite revisit time compared to SSO. This paper exploits these characteristics for low inclined orbits. The target area considered in simulation is between 22° and 32° N latitude lines with 2.5 m ground sample resolution. The satellite maximum rolling capability is 35° and the sun elevation angle is constrained between 30° and 70° for purpose of maximizing the quality of the obtained images. Matlab and STK software are employed to define the initial orbital parameters to meet these conditions for a low inclined orbit.
KW - Low inclination orbits
KW - Mission analysis
KW - Orbit design
KW - Remote sensing satellites
UR - http://www.scopus.com/inward/record.url?scp=84921670881&partnerID=8YFLogxK
UR - http://www.scopus.com/inward/citedby.url?scp=84921670881&partnerID=8YFLogxK
U2 - 10.4028/www.scientific.net/AMM.629.298
DO - 10.4028/www.scientific.net/AMM.629.298
M3 - Conference contribution
AN - SCOPUS:84921670881
T3 - Applied Mechanics and Materials
SP - 298
EP - 303
BT - AEROTECH V
A2 - Romli, Fairuz I.
A2 - Majid, D.L.
A2 - Mustapha, Faizal
A2 - Romli, Fairuz I.
A2 - Majid, D.L.
A2 - Mustapha, Faizal
A2 - Varatharajoo, Renuganth
A2 - Romli, Fairuz I.
A2 - Ahmad, Kamarul Arifin
A2 - Majid, D.L.
A2 - Mustapha, Faizal
A2 - Varatharajoo, Renuganth
A2 - Romli, Fairuz I.
A2 - Ahmad, Kamarul Arifin
A2 - Majid, D.L.
A2 - Mustapha, Faizal
PB - Trans Tech Publications Ltd
T2 - 5th AEROTECH conference
Y2 - 29 October 2014 through 30 October 2014
ER -