資料載入中.....

請使用永久網址來引用或連結此文件:
https://tkuir.lib.tku.edu.tw/dspace/handle/987654321/65357

題名:  Optimal Trajectory for Vertical Ascent to Geosynchronous Earth Orbit 
作者:  Chern, Jengshing;Hong, Zuuchang 
貢獻者:  淡江大學機械與機電工程學系 
日期:  199307 
上傳時間:  20111020 21:43:03 (UTC+8) 
出版者:  Pergamon 
摘要:  In this paper, the optimal trajectory for vertical ascent to the geosynchronous Earth orbit is solved by using the parameter optimization technique. The performance index is to maximize the final mass. In other words, the propellant consumption is to be minimized. The time derivative of the velocity magnitude of the vehicle, called the acceleration profile, is assumed to be a polynomial function of the flight time, with the coefficients as free parameters to be selected. The required thrust vector is then derived as a function of the state variables and the acceleration profile. A first order polynomial function is adopted for the acceleration profile. The two coefficients along with the flight time are selected such that the final condition for geosynchronous Earth orbit insertion is satisfied and the final mass is maximized. When the initial mass is 430,000 kg and the initial flight path angle is 1°, and a laser propulsion system with 2500 s of specific impulse is used, the maximum final mass obtained is 110,965 kg. This best final mass is 25.81% of the initial mass. The ascending flight time is 1.923 h. For vertical ascending trajectory, the relative speed of the vehicle with respect to the atmosphere is the vertical component of the inertial vehicle velocity. Therefore, the dynamic pressure and the aerodynamic drag are reduced to lower levels. In this paper, the optimal trajectory for vertical ascent to the geosynchronous Earth orbit is solved by using the parameter optimization technique. The performance index is to maximize the final mass. In other words, the propellant consumption is to be minimized. The time derivative of the velocity magnitude of the vehicle, called the acceleration profile, is assumed to be a polynomial function of the flight time, with the coefficients as free parameters to be selected. The required thrust vector is then derived as a function of the state variables and the acceleration profile. A first order polynomial function is adopted for the acceleration profile. The two coefficients along with the flight time are selected such that the final condition for geosynchronous Earth orbit insertion is satisfied and the final mass is maximized. When the initial mass is 430,000 kg and the initial flight path angle is 1°, and a laser propulsion system with 2500 s of specific impulse is used, the maximum final mass obtained is 110,965 kg. This best final mass is 25.81% of the initial mass. The ascending flight time is 1.923 h. For vertical ascending trajectory, the relative speed of the vehicle with respect to the atmosphere is the vertical component of the inertial vehicle velocity. Therefore, the dynamic pressure and the aerodynamic drag are reduced to lower levels. 
關聯:  Acta Astronautica 29(7), pp.497502 
DOI:  10.1016/00945765(93)90054Z 
顯示於類別:  [機械與機電工程學系暨研究所] 期刊論文

文件中的檔案:
檔案 
大小  格式  瀏覽次數 
index.html  0Kb  HTML  27  檢視/開啟 

在機構典藏中所有的資料項目都受到原著作權保護.
