Research On The Satellite Navigation Technology Of Spinning Missile

As the continuous construction and development of global navigation satellite system(GNSS) in different countries, satellite navigation systems can provide much more excellent performance. Satellite navigation receivers were widespread deployed on various types of guided missiles as their primary means of guidance. In the entire process of flight, the body of guided missile can often spin. How satellite navigation performance changes through the process of missile spinning, is a very attractive research field. We focus on the effects of the missile spinning state on the traditional technology of signal synchronization of navigation satellite and improve the tracking loop design of receiver which fixed on the spinning missile.The main contents of this thesis are divided into five parts:1. Analyzes the characteristics of spinning missile and the design patterns of existing onboard GNSS receiver of missile. Studies show that the onboard antenna phase center deviation from the axis of rotation is the main cause of satellite navigation performance change when the missile spinning.2. The effects of missile spinning on the receiving signal are systematically derived through the establishment of the onboard GNSS receiver antenna coordinate system. The satellite signal Doppler shift, the phase of the carrier signal and the variation of the local IF signal are derived. The GNSS IF signal model of receiver which spinning with the missile is established.3. The adaptability of traditional GNSS receiver satellite signal synchronization technology in the missile spinning scene is analyzed. Critical missile spin speeds of traditional receiver, when the signal acquisition and tracking is failed, were calculated. The simulation result shows that the traditional tracking loop can not track the signal when the missile is spinning in high rate.4. A new carrier tracking loop design which called rotating tracking loop is designed for the challenge of satellite signal tracking which faced by the receiver fixed on the spinning missile. Rotation loop discriminator, rotation loop filter and rotation NCO(Numerically Controlled Oscillator) of the new loop are also designed. The new loop consults the design of traditional carrier tracking loop. The loop doesn’t rely on any other sensor hardware, and can obtain accurate missile spinning speed measurements. With the aid of spinning rates, simulation results show that this new loop can achieve a signal tracking successfully in the high rate missile spinning scenarios in which traditional tracking loop is failed. The new loop can cover the missile spinning rates from 0 to 20r/s and cover the spinning rates acceleration from 0 to 5r/s2, and has smaller estimation errors of carrier phase and higher performance than the traditional loop.5. Builds a simulation software by the Matlab GUI to provide a visual software tool for the subsequent research on the performance analysis and design of spinning onboard satellite navigation receiver.