Abstract:

 Aiming at the trajectory characteristics of hypersonic vehicles and the navigation needs of flight control systems, a hypersonic vehicle integrated navigation algorithm in the launch centered Earth-fixed (LCEF) frame is proposed. Firstly, the strapdown inertial navigation system (SINS) algorithm in the LCEF frame is introduced, and the discrete recursive equations of attitude, velocity and position are derived. Then, how to convert the position and velocity of the BeiDou navigation satellite system (BDS) from the Earth-centered Earth-fixed (ECEF) frame to the LCEF frame is introduced, and the state equations and measurement equations in the LCEF frame of the SINS/BDS integrated navigation filter are derived. Taking the trajectory of a hypersonic boost-glide vehicle as an example, the SINS/BDS integrated navigation simulation is carried out. The position accuracy is less than 10 m and the speed precision is less than 0.2 m/s.

Key words: Hypersonic vehicle, Near space, Launch centered Earth-fixed frame, Strapdown inertial navigation algorithm, Integrated navigation system