A model for helicopter guidance on spiral trajectoriesA point mass model is developed for helicopter guidance on spiral trajectories. A fully coupled set of state equations is developed and perturbation equations suitable for 3-D and 4-D guidance are derived and shown to be amenable to conventional state variable feedback methods. Control variables are chosen to be the magnitude and orientation of the net rotor thrust. Using these variables reference controls for nonlevel accelerating trajectories are easily determined. The effects of constant wind are shown to require significant feedforward correction to some of the reference controls and to the time. Although not easily measured themselves, the controls variables chosen are shown to be easily related to the physical variables available in the cockpit.
Document ID
19800061353
Acquisition Source
Legacy CDMS
Document Type
Conference Proceedings
Authors
Mendenhall, S. (General Electric Co. Cincinnati, Ohio, United States)
Slater, G. L. (Cincinnati, University Cincinnati, Ohio, United States)