A nonlinear guidance law is presented for the im-pact time control of an interceptor against a stationary target. Exact closed form expressions for impact time and the guidance command are derived. For a given engagement geometry, a given impact time corresponds to a unique initial heading error. For interceptors launched with any other initial heading error, a term proportional to impact time ...

Autonomous soaring capability has the potential to significantly increase time aloft for fixed-wing UAVs. In this paper, we introduce ArduSoar, the first soaring controller integrated into a major autopilot software suite for small UAVs. We describe ArduSoar from the algorithmic standpoint, outline its integration with the ArduPlane autopilot, and discuss tuning procedures and parameter choices...

High-performance computing is rapidly expanding to include distributed collections of heterogeneous sequential and parallel systems and irregular applications with complex, data dependent execution behavior and time varying resource demands. To provide adaptive resource management for dynamic applications, we are developing the Autopilot toolkit. Autopilot provides a exible set of performance s...

Sliding mode control of a launch vehicle during its atmospheric flight phase is studied in the presence of unmatched disturbances. Linear time-varying dynamics of the aerospace vehicle is converted into a systematic formula and then dynamic sliding manifold as an advanced method is used in order to overcome the limited capability of conventional sliding manifolds in minimizing the undesired eff...

This paper proposes a decentralised vector field guidance algorithm for coordinated standoff tracking of a ground moving target by multiple UAVs. In particular, this study introduces additional adaptive terms in an existing sliding mode control concept for standoff tracking guidance, in order to reduce the effect of unmodelled dynamics and disturbances. Decentralised angular separation control ...

Atmospheric flight phase of a launch vehicle is utilized to evaluate the performance of an H∞ controller in the presence of disturbances. Dynamics of the vehicle is linearly modeled using time-varying parameters. An operating point was found to design a robust command tracker using H∞ control theory that guarantees a stable maneuver. At the end, the controller was employed on the launch vehicle...

High-performance computing is rapidly expanding to include distributed collections of heterogeneous sequential and parallel systems and irregular applications with complex, data dependent execution behavior and time varying resource demands. To provide adaptive resource management for dynamic applications, we are developing the Autopilot toolkit. Autopilot provides a exible set of performance s...