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A new missile midcourse guidance algorithm is proposed in this paper. It is a combination of sampling based path planning, Dubins' curves and classical guidance laws. Moreover, a realistic interceptor missile model is used. It allows to anticipate the future changes of flight conditions along the trajectory, especially the loss of maneuverability a...
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... US Standard Atmosphere, 1976 (US-76) is used in this paper. In the lower earth atmosphere (altitude < 35 km), density of air and atmospheric pressure decrease exponentially with altitude and approach zero at about 35 km (Fig. 2). As we consider a missile with only aerodynamic flight controls, the maneuvering ...
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Citations
... The RRT algorithms using the previously mentioned configurations are simulated in certain scenarios. The one using NP as the control input selection will be referred as RRT PN published in [PHPB13] and the one using kappa guidance will be referred as RRT kappa published in [PPHB13]. In this section, the results obtained by the RRT algorithms are compared with the ones obtained by the classical missile guidance law, the kappa guidance with optimal gains. ...
... The The RRT algorithm using the original Dubins' paths [PHPB13,PPHB13] as the metric to determine the distance between two vehicle states in the exploration space is studied in the previous chapter. The results show that an admissible trajectory between x init and X goal can be found. ...
The focus of this PhD thesis is on the trajectory planning module as a part of autonomous aircraft system. Feasible trajectories for aircraft flying in environment cluttered by obstacles are studied. Since aircraft dynamics are complex, nonlinear and nonholonomic; trajectory planning for such systems is very difficult and challenging.Rapidly-exploring Random Tree or RRT path planner is used as a basis to find a feasible trajectory. The advantage of this algorithm is that it does not consider only the complete vehicle model but also the environment. Two algorithms are developed to find a feasible and optimal solution. The RRT algorithm, combined with a preprocessing of the exploration space, is used for a complete realistic model of the system. However, this approach does not consider any optimal criteria. In order to consider performance criteria, the RRT* algorithm is used based on a simplified model with the help of the artificial potential field as a heuristic to improve the convergence rate to the solution.The algorithms are simulated in an application of hypersonic aerial vehicles, for example, interceptor missiles flying in high altitude. This makes the aerodynamically controlled aircraft have less maneuverability since the air density decreases exponentially with altitude. 3D shortest paths are developed and used as a metric. Therefore, a feasible and optimal trajectory is obtained efficiently. With these results, real-time constraints will be easier to verify if the algorithm is implemented on board the vehicle. In future work, replanning will be considered to improve the performance of the algorithm in case of dynamic environment or changes in the mission.
