Design method for air delivery control system of folding-wing unmanned aerial vehicle

Abstract

The invention belongs to the technical field of unmanned aerial vehicle control systems, and provides a design method for the air delivery control system of a folding-wing unmanned aerial vehicle. A small PixHawk 4Mini platform is selected as control system hardware, a small folding wing is connected with a CH1 channel and a CH2 channel of a flight control system through a left horizontal tail steering engine control plane layout and a right horizontal tail steering engine control plane layout, pitching and rolling of the unmanned aerial vehicle are controlled through steering engine mixed control, and self-stabilization is achieved through double vertical tails during yawing; a tail thrust motor is connected with a CH3 channel through an electronic speed controller for accelerator control; a parachute landing switch and a folding and unfolding action mechanism are driven by being connected with a CH5 channel and a CH6 channel of the flight control system; control system software is subjected to secondary development on the basis of a PX4 flight control architecture, a folding and unfolding module and a parachute landing task module are integrated in an operating system process queue of the control system software, and attitude control parameters and steering engine mixed control parameters are adjusted. Based on secondary development of the PX4 flight control architecture, the development cost and time can be reduced to the maximum extent, and physical implementation and remodeling debugging are easy.

Description

technical field [0001] The invention belongs to the technical field of control systems for unmanned aerial vehicles, and in particular relates to a design method for a control system for aerial launch of a folding-wing unmanned aerial vehicle. Background technique [0002] Traditional fixed-wing UAV swarms usually take off by taxiing, which not only takes a long time to take off, but also relies heavily on venues and runways. In contrast, the folding-wing UAV based on the variable structure method uses a ground launch device to catapult and take off, which can meet the requirements of rapid deployment while reducing the storage space, such as the U.S. Navy LOCUST project "Coyote" UAV. [0003] However, according to empirical statistics, the range and cruising speed of small UAVs are often limited by the allowable take-off weight and maximum load constraints of UAVs. A single small UAV cluster cannot effectively achieve a balance between flight mission radius and cost-effecti...

AI Technical Summary

Problems solved by technology

[0005] The invention is a design method of a folding-wing unmanned aerial vehicle air release control system, which solves the technical problem of autonomous folding, unfolding and stable and reliable flight of the folding-wing unmanned aerial vehicle under the condition of air launch

Images