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序號 學年期 教師動態
1 81/1 航太系 馬德明 教授 會議論文 發佈 Variations of Orbital Elements of Optimal Plane Change by Low Aerodynamic Forces , [81-1] :Variations of Orbital Elements of Optimal Plane Change by Low Aerodynamic Forces會議論文Variations of Orbital Elements of Optimal Plane Change by Low Aerodynamic ForcesMa, Der-Ming淡江大學航空太空工程學系Made available in DSpace on 2014-12-23T05:36:54Z (GMT). No. of bitstreams: 0;Submitted by 雯婷 何 (144370@mail.tku.edu.tw) on 2014-12-23T05:36:54Z&#x0D; No. of bitstreams: 0;tku_id: 000086418;2014-12-23 待補正 by 何雯婷en國內199212TWN第三十四屆航太學會年會<links><record><name>機構典藏連結</name><url>http://tkuir.lib.tku.edu.tw:8080/dspace/handle/987654321/99807</url></record></links>
2 88/2 航太系 馬德明 教授 會議論文 發佈 低地太陽同步衛星軌道之模擬計算 , [88-2] :低地太陽同步衛星軌道之模擬計算會議論文低地太陽同步衛星軌道之模擬計算Orbit Simulation of Low Altitude Sun-Synchronous Satellite馬德明淡江大學航空太空工程學系軌道衛星;太陽同步衛星;軌道力學Orbital Satellite;Sun Synchronous Satellite;Orbital Mechanics第四屆海內外華人航天科技研討會論文集,頁381-386中國航空太空學會; 中國宇航學會; 美華航太工程師協會本研究主要的目的在探討重力場之J/sub 2/、J/sub 3/、J/sub 4/對太陽同步衛星軌道的影響並推導其擾動線性方程式以作為星載軌道定位使用之方程式。由模擬計算可以知道J/sub 2/、J/sub 3/、J/sub 4/的影響對瞬時的運動而言是很小的,最大的是J/sub 2/對Ω的影響約在10/sup -7/左右,其它的都在 10/sup -10/以下,甚至更小,所以在太陽同步衛星軌道的動力模型上我們只考慮J/sub 2/對Ω的影響。tku_id: 000086418;Made available in DSpace on 2013-03-22T07:32:30Z (GMT). No. of bitstreams: 0 Previous issue date: 2010-01-11T07:19:59Z;2014/04/17補正by映潔zh_TW國內20000411~20000414中國航空太空學會; 中國宇航學會; 美華航太工程師協會TWN4th Global Chinese aerospace science and technology conference=第四屆海內外華人航天科技研討會屏東縣, 臺灣<links><record><name>機構典藏連結</name><url>http://tkuir.lib.tku.edu.tw:8080/dspace/handle/987654321/38473</url></record></links>
3 81/2 航太系 馬德明 教授 會議論文 發佈 Analytic Theory Of Optimal Plane Change By Low Aerodynamic Forces , [81-2] :Analytic Theory Of Optimal Plane Change By Low Aerodynamic Forces會議論文Analytic Theory Of Optimal Plane Change By Low Aerodynamic Forces受微小氣動力的最佳軌變分析解Ma, Der-Ming; Wu, Chi-Hang; Nguyen X. Vinh淡江大學航空太空工程學系Advances in the Astronautical Sciences Series 82, pp.1139-1154The properties of the optimal and sub-optimal solutions to multiple-pass aeroassisted plane change are studied in terms of the trajectory variables in Refs. [3] and [4]. The solutions show the strong orbital nature. Then, it is proposed to obtain the variational equations of the orbital elements. We shall use these equations and the approximate control derived in Ref. [4] to calculate the trajectories. In this respect, the approximate control law and the transversality condition are transformed in terms of the orbital elements. Folllowing the above results, we can reduce the computational task by further simplification. with W and Q being small and returning to the value of zero after each revolution, we neglect the equations
4 82/1 航太系 馬德明 教授 會議論文 發佈 Optimal entry angle of aeroassisted orbital plane change , [82-1] :Optimal entry angle of aeroassisted orbital plane change會議論文Optimal entry angle of aeroassisted orbital plane changeMa, Der-Ming; Tseng, Ching-Yeh淡江大學航空太空工程學系美國航太學會大氣飛行力學學術研討會,頁525-531Made available in DSpace on 2013-03-22T07:50:59Z (GMT). No. of bitstreams: 0&#x0D; Previous issue date: 2011-10-18T13:36:52Z;tku_id: 000086418;20130320格式已修正by陸桂英en國際19930809~199308111993 Guidance, Navigation, and Control and Co-located Conferences - Flight Simulation and TechnologiesMonterey, CA, U.S.A.<links><record><name>機構典藏連結</name><url>http://tkuir.lib.tku.edu.tw:8080/dspace/handle/987654321/62484</url></record></links>
5 81/1 航太系 馬德明 教授 會議論文 發佈 The Variations of the Elements of the Orbit of Multiple-Pass Aeroassisted Plane Change , [81-1] :The Variations of the Elements of the Orbit of Multiple-Pass Aeroassisted Plane Change會議論文The Variations of the Elements of the Orbit of Multiple-Pass Aeroassisted Plane Change多次進出之大氣輔助軌道平面轉變的軌道參數 特性馬德明; Ma, Der-ming淡江大學航空太空工程學系軌道力學;軌道轉換;最佳軌跡; 氣輔助轉換;狀態方程式;Orbit Mechanics;Orbital Transfer;Optimal Trajectory;Aeroassisted Transfer;State Equation成功大學中國航空太空學會第三十四屆學術研討會論文集(二)=Proceedings of the AASRC 34th Aeronautics and Astronautics Conference (I I), pp.554-563多次進出大氣層所產生最大軌道平面轉變 之最佳軌跡及次佳軌跡具備了軌道之特性。因 此,引發了吾人探討此解之軌道參數變化特性 。 首先,利用適當之關係將最佳軌跡之軌跡 參數(.phi.,.psi.,.theta.,h,u,.gamma.)轉換為軌道參數(.alpha.,.OMEGA.,I,a,e,.omega.)。接著,引用Lagrange's軌 道方程式直接推導軌道參數變化之方程式。並 且利用上述之方程式及次佳控制法則來計算軌 跡。當然,在引用次佳控制法則及橫斷條件時 已經將它們以軌道參數來表示了。 依據上述之結果,吾人發覺.omega.及.OMEGA.之 變化很小,因而使得.alpha..apprxeq.f。所以,忽略 .omega.,.OMEGA.及.alpha.三個式子,僅考慮I,a,及e,三 式即可,而使得計算大氣輔助軌道平面轉變更 為簡單。;The properties of the optimal and sub-optimal solutions to multiple-pass aeroassisted plane change are studied in terms of the trajectory variables in Ref
6 85/1 機電系 洪祖昌 教授 會議論文 發佈 Aerodynamic and Stabilization Gravity Gradient Stabilization for Micro-Satellite , [85-1] :Aerodynamic and Stabilization Gravity Gradient Stabilization for Micro-Satellite會議論文Aerodynamic and Stabilization Gravity Gradient Stabilization for Micro-SatelliteChen, Y. H.; Hong, Z. C.; Chern, J. S.淡江大學機械與機電工程學系第三屆海內外華人航天科技學術研討會, 頁491~499When the orbital altitude of a satellite is relatively low, for example, less than 500 km, the method of aerodynamic stabilization can be considered. In particular, this method is very effective when the satellite is small. The aerodynamic restoring torque can be provided by a very light tail stabilizer which is several meters downstream from the main body of the small satellite. An aerodynamic stabilization system has been installed in the Cosmos-149 and another one in the Cosmos-320. One of the disadvantages in using the aerodynamic stabilization is that no rolling stabilization can be achieved. The gravity gradient stabilization method has been used in many satellites. One of the examples is the Eole satellite. In the recent years, many small sa
7 92/1 物理系 杜昭宏 教授 會議論文 發佈 Charge, Orbital, and Spin Ordering in the Strongly Correlated Electron System , [92-1] :Charge, Orbital, and Spin Ordering in the Strongly Correlated Electron System會議論文Charge, Orbital, and Spin Ordering in the Strongly Correlated Electron System杜昭宏淡江大學物理學系淡江大學尖端材料科學研討會,臺北tku_id: 000119219;Submitted by 曉芬 游 (139570@mail.tku.edu.tw) on 2011-10-23T10:33:14Z No. of bitstreams: 0;Made available in DSpace on 2011-10-23T10:33:15Z (GMT). No. of bitstreams: 0校內淡水校園20031120~20031121<links><record><name>機構典藏連結</name><url>http://tkuir.lib.tku.edu.tw:8080/dspace/handle/987654321/69564</url></record></links>
8 93/2 化學系 王伯昌 教授 會議論文 發佈 Electronic Sturcture and Molecular Orbital Study of the Red OLED Material DCM From Ab Initio and TD-B3LYP , [93-2] :Electronic Sturcture and Molecular Orbital Study of the Red OLED Material DCM From Ab Initio and TD-B3LYP會議論文Electronic Sturcture and Molecular Orbital Study of the Red OLED Material DCM From Ab Initio and TD-B3LYP王伯昌淡江大學化學學系泰國第2屆亞太理論與計算化學研討會tku_id: 000077214;Submitted by 曉芬 游 (139570@mail.tku.edu.tw) on 2011-10-23T09:25:58Z No. of bitstreams: 0;Made available in DSpace on 2011-10-23T09:25:58Z (GMT). No. of bitstreams: 020050502~20041222<links><record><name>機構典藏連結</name><url>http://tkuir.lib.tku.edu.tw:8080/dspace/handle/987654321/69532</url></record></links>
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