An aircraft control system for an unmanned aircraft comprising a forward propulsion system comprising a forward thrust engine and a vertical propulsion system comprising a vertical thrust engine. The aircraft control system may include a controller comprising an input coupled to receive a velocity signal indicating a determined amount of forward velocity and being configured to generate a pitch angle command associated with the determined amount of forward velocity; a splitting block comprising an input to receive the pitch angle command and being configured to generate a second pitch angle command and a forward thrust engine throttle command based on a bounded pitch angle for the unmanned aircraft; and an output coupled to provide the second pitch angle command to the vertical propulsion system and the forward thrust engine throttle command to the forward propulsion system.
Combined pitch and forward thrust control for unmanned aircraft systems
2021-08-17
Patent
Electronic Resource
English
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