一种基于太阳震荡时间延迟量测的自主天文导航方法

太阳震荡可以在短时间内引起太阳光强度和光谱线心波长的剧烈变化，通过探测太阳光强度和光谱线心波长并记录时间，可以获得直接接收的太阳光到达时间和经天体反射的太阳光到达时间之间的时间延迟，可以利用时间延迟作为量测量提供航天器的位置信息。提出了一种基于太阳震荡时间延迟量测的自主天文导航方法；建立了基于时间延迟的隐式量测模型，并应用了IUKF方法。仿真结果表明：本文所提出的导航方法，应用在转移轨道上的位置误差和速度误差分别约为3.55 km和0.077 m/s，环绕轨道分别为1.76 km和1.57 m/s。同时也研究了3种因素对导航性能的影响。

A Novel Autonomous Celestial Navigation Method Using Solar Oscillation Time Delay Measurement

Solar oscillation,causing a dramatic variation of the sunlight spectral central wavelengths and intensity during a short time,has been studied in detail over the years,both observationally and theoretically. Through detecting the sunlight spectral central wavelengths and intensity and recording the moment when solar oscillation occurs,the time delay between the sunlight coming from the Sun directly and the sunlight reflected by a celestial body such as the satellite of planet or asteroid can be obtained. Because the solar oscillation time delay is determined by the relative positions of the spacecraft,reflective celestial body and the Sun,it can be adopted as the navigation measurement to provide the spacecraft''s position information. In this paper,a novel celestial navigation method using solar oscillation time delay measurement is proposed. The implicit measurement model of time delay is built,and the Implicit Unscented Kalman Filter (IUKF) is applied. Simulation results indicate that the position error and velocity error of the proposed method for the transfer orbit are about 3.55 km and 0.077 m/s respectively,and for the surrounding orbit are about 1.76 km and 1.57 m/s respectively. The impact of the three factors on the navigation performance is also investigated.