Conceptual Study Of Navigation System For Suborbital Launch Vehicle

In recent years, with the development of aerospace technology, man began to look into new areas, nearspace, with its potentially huge economic and military value, each country with advanced aerospace technology focus on researching the nearspace vehicles. The Suborbital Launch Vehicle as one of them has its unique worth. Navigation system is the base of the Suborbital Launch Vehicle GNC System, In Paper, the scheme, model and algorithm of navigation for Suborbital Launch Vehicle have been studied.The fllowing shows the main contents:1. On the analysis of the advantages and disadvantages of all single navigation system Presented, gave the combination navigation system adaptable the Suborbital Launch Vehicle. When flighting in the aerosphere adopt the inertial navigation system(INS) aided by the Globle Position System(GPS),When flighting out the aerosphere adopt the inertial navigation system(INS) aided by the Globle Position System(GPS) and Celestial Navigation System(CNS).2. Introduce the theory of the INS, algoritlhm of SNIS; The principle of determining Position and attitude of CNS and the theory of GPS; The error state of INS, inertial sensor,Star sensor, receiver of GPS, have been analyzed and modeled.3. On the use of positon and velocity information given by GPS, attitude information given by CNS, estibalished the INS/GPS, INS/CNS model and the Federal Kalman filter.4. The Performrnace of various combination sehemes was simulated by Matlab/Simulink. The simulation in single SNIS, SNIS/GPS, SNIS/CNS, SNIS/GPS/CNS showed that the SNIS/GPS have better position and velocity accuracy, the SNIS/CNS have better attitude accuracy, the SNIS/GPS/CNS combination navigation system have good position ,velocity and attitude accuracy.