A Design Method of Folding Wing UAV Air Launch Control System

Abstract

The invention belongs to the technical field of UAV control systems, and provides a design method for a folding-wing UAV aerial launch control system. The hardware of the control system adopts the miniaturized PixHawk 4Mini platform. The small folding wing adopts the layout of the control surface of the left and right horizontal tail servos, which are respectively connected to the CH1 and CH2 channels of the flight control system. The dual vertical tails are used to achieve self-stabilization; the tail thruster motor is connected to the CH3 channel through the ESC for throttle control; the parachute switch and the folding and unfolding mechanism are respectively driven by connecting the flight control system CH5 channel and CH6 channel; the control system software is in the PX4 The secondary development is carried out on the basis of the flight control architecture, and the folding and unfolding module and the parachute task module are integrated in the process queue of its operating system, and the attitude control parameters and steering gear mixing control parameters are adjusted; the present invention is based on the PX4 flight control architecture secondary Development, which can minimize development costs and time, and is easy to physically realize and modify and debug.

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

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