GNSS/IMU laser quadrant detector hybridization techniques for artillery rocket guidance
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Enhancing precision has been the essential goal for ballistic rockets since the beginnings of this aircraft class. In the past, ballistic rockets impact point precision deteriorated at the same time as range was extended, specially for those rockets which were nonpropelled and nonguided amid the greater part of their trajectories. Once that inertial and Global Navigation Satellite System (GNSS) navigation and guidance systems were introduced, precision was unlinked from range increments. The fundamental issue for these inertial and GNSS strategies (hybridized or not) is the enormous errors on attitude and position determination during last phases of flight as the movement is governed by aerodynamic forces and moments, which feature a deeply nonlinear character. Choosing another kind of low-cost sensors, independent of accumulative errors and precise on terminal guidance, for example, quadrant photodetector semi-active laser, is crucially essential. Hybridization of nonlinear algorithms, such as extended Kalman filter, joining measurements from sensors such as GNSS, inertial measurement units and photodetectors are described in this paper to be utilized on modified proportional navigation techniques and novel control methods. The results are tested on rocket nonlinear flight simulations in order to prove the accuracy of proposed algorithms.
KeywordsGNSS/IMU Hybridization Laser Guidance Flight dynamics
The authors would like to thank to Lieutenant Colonel Jesús Sánchez (NMT) and‘Instituto Tecnológico La Marañosa’ of the National Institute for Aerospace Technology (INTA) for solid modeling of the concept and for discussions regarding modeling weapon accuracy.
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