Optimal direct ascent to GEO using laser propulsion system
碩士 === 國立中央大學 === 機械工程研究所 === 82 === The optimal trajectory for direct ascent to the geosynchronous earth orbit (GEO) with prescribed longitudinal displacement will be solved by using parameter optimization method. The time derivative of th...
| Main Authors: | , |
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| Other Authors: | |
| Format: | Others |
| Language: | zh-TW |
| Published: |
1994
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| Online Access: | http://ndltd.ncl.edu.tw/handle/47327631886770076419 |
| Summary: | 碩士 === 國立中央大學 === 機械工程研究所 === 82 === The optimal trajectory for direct ascent to the geosynchronous
earth orbit (GEO) with prescribed longitudinal displacement
will be solved by using parameter optimization method. The time
derivative of the velocity mangitude of the vehicle is assumed
to be a polynomial function of the flight time, with the
coefficients as free parameters to be selected. The required
thrust magnitude and angle are then derived as functions of the
state variables and the polynomial. For the thrust acceleration
and dynamic pressure constrained, we can fined seven
trajectories. Finally there are three equally located launching
stations along the Earth's equator.
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