摘要：【中文】本发明涉及一种高精度实时绝对定轨方法，在星载接收机高精度实时定轨的应用背景下，以伪距与载波相位作为滤波方程的观测量，结合高度非线性的动力学模型，用扩展卡尔曼滤波高精度稳定地输出卫星运行位置和速度等状态参数，在充分利用高精度载波相位观测量的同时，采用多种手段提高运行效率，以满足中低轨高精度实时定轨需求，定轨测速精度均大幅提高，此外还具备轨道预报和外推能力，很大程度上提高了导航设备在轨输出的可靠性，本发明在接收机平台上进行了低轨卫星场景模拟实时定轨测试，可实现实时绝对定轨位置精度优于0.5m、测速精度优于0.5mm/s的技术指标，相较于常规伪距实时单点定位方法，定轨测速精度均大幅提高。 【EN】The invention relates to a high-precision real-time absolute orbit determination method, which takes pseudo range and carrier phase as observed quantity of a filter equation under the application background of high-precision real-time orbit determination of a satellite-borne receiver, combines a highly nonlinear dynamic model, uses extended Kalman filtering to stably output state parameters such as satellite operation position, speed and the like at high precision, adopts various means to improve operation efficiency while fully utilizing the observed quantity of the high-precision carrier phase so as to meet the high-precision real-time orbit determination requirement of medium and low orbits, greatly improves the orbit determination and speed measurement precision, has the capabilities of orbit prediction and extrapolation, greatly improves the reliability of in-orbit output of navigation equipment, performs low-orbit satellite scene simulation real-time orbit determination test on a receiver platform, can realize the technical indexes that the precision of the real-time absolute orbit determination position is superior to 0.5m and the speed measurement precision is superior to 0.5mm/s, compared with the conventional pseudo-range real-time single-point positioning method, the orbit determination and speed measurement precision is greatly improved.