CAJ | 학술논문

研究了太阳帆日心移位轨道的稳定性、控制律设计及轨道拼接。将柱坐标形式的太阳帆动力学方程在参考移位轨道附近线性化，得到线性变分方程。分析线性变分方程的特征值在复数平面上的位置就可以得到移位轨道的稳定性条件。设计了太阳帆日心移位轨道的控制律，并证明了控制律满足稳定性条件。该控制律仅要求太阳帆在移位轨道飞行时姿态角a保持不变。此外，太阳帆移位轨道可以与开普勒轨道相互转化，也可以与移位轨道之间相互拼接。
연구료태양범일심이위궤도적은정성、공제률설계급궤도병접。장주좌표형식적태양범동역학방정재삼고이위궤도부근선성화，득도선성변분방정。분석선성변분방정적특정치재복수평면상적위치취가이득도이위궤도적은정성조건。설계료태양범일심이위궤도적공제률，병증명료공제률만족은정성조건。해공제률부요구태양범재이위궤도비행시자태각a보지불변。차외，태양범이위궤도가이여개보륵궤도상호전화，야가이여이위궤도지간상호병접。
The issues of solar sail spacecraft Sun-centred displaced orbit stability, control and patch are studied. By linearizing the model along the nominal orbit, the linear variational equation is deduced. The stability characteristics of the displaced orbit can be investigated by analyzing ei- genvalues in the complex plane. The control law of solar sail Sun-centred displaced orbit is de- signed and proved stable. This control law only requires attitude angle a keeping fixed. Besides, Sun-centred displaced orbits can be patched to Keplerian orbits, and also can be patched together.