This paper briefly introduces hypersonic aircraft, and by analyzing the commonly used combined navigation methods, it proposes the use of SINS/GPS/CNS combined navigation as a mid-course guidance scheme for hypersonic cruise missiles. This paper uses the quaternion method to calculate SINS, and uses the federated filtering method to simulate the combined navigation. The simulation program is based on the flight trajectory and related parameters of the hypersonic cruise aircraft generated by the trajectory generator. The simulation results show the feasibility of using the SINS/GPS/CNS combined navigation system for mid-course guidance of hypersonic cruise aircraft. Keywords: hypersonic cruise aircraft; integrated navigation; mid-course guidance; federated filtering Abstract: This paper simply introduces hypersonic cruise aircraft and puts forward SINS/GPS/CNS navigation as midcourse navigation of it through the analysis of several universally integrated navigation models. SINS is calculated by quaternions and the integrated navigation system is simulated by federated Kalman filtering method in this paper. Track generator is used to generate a track and other correlation parameters of hypersonic cruise aircraft, then simulation can be made at the base of it. While simulation results show the feasibility of integrated SINS/GPS/CNS system as midcourse navigation of hypersonic cruise aircraft. Keywords: Hypersonic Cruise Aircraft, Integrated Navigation, Midcourse Navigation, Federated Filtering
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