Active Flow Vector Flight Control Using Only SJAs for a Fixed-Wing UAV

Chunzhi Li,Sheng Zhai,Chengcai Wang,Jianying Yang,Jianhua Shen

doi:10.1109/access.2018.2883067

Chunzhi Li, Sheng Zhai + Show 3 more

Open Access

https://doi.org/10.1109/access.2018.2883067

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Journal: IEEE Access	Publication Date: Jan 1, 2018
Citations: 16	License type: CC BY 3.0

Affiliation: Peking University

Abstract

A novel flight control method for a fixed-wing unmanned aerial vehicle (UAV) is provided, which uses only synthetic jet actuators (SJAs) to achieve thrust vector control of the fixed-wing UAV. Firstly, the fluid model of the engine jet (or primary jet) and the SJAs are built, and the relation between the deflection angle of the primary jet and the amplitude of vibrating membrane of the SJAs is obtained. Secondly, based on the relation, a SJAs-based thrust vector control pitching motion model of the UAV is built. Thirdly, considering parameter uncertainties, unmodeled dynamics and unknown external disturbance of the system, an adaptive back-stepping sliding mode control (ABSMC) law is proposed, and pitching motion of the UAV is achieved by using only the SJAs-based thrust vector control. Finally, some simulations are conducted to analyze and verify the effectiveness of the flight control method. The results show that the thrust vector produced by the SJAs can enable the pitch control of the UAV and the ABSMC performs well in the presence of parameter uncertainties, unmodeled dynamics and unknown external disturbance of the system.

Highlights

In the last years, the fixed-wing unmanned aerial vehicle (UAV) are widely studied for their wide applications [1]–[5]
SIMULATION RESULTS In order to show the performance and efficiency of the adaptive back-stepping sliding mode control (ABSMC) on the fixed-wing UAV using SJAs, we conducted some simulations on flight path angle control
In this paper, we present a novel flight control method for a fixed-wing UAV which is equipped with two SJAs near its nozzle

Summary

INTRODUCTION

The fixed-wing UAVs are widely studied for their wide applications [1]–[5]. Many studies have shown that SJA can achieve a larger thrust vector deflection angle than secondary fluidic injections. The results inspire us to use SJA to deflect the thrust vector to realize flight control. 2) Based on the relation, a SJAs-based thrust vector control pitching motion model of the UAV is built. 3) Considering parameter uncertainties, unmodeled dynamics and unknown external disturbance of the system, an ABSMC is proposed, and pitching motion of the UAV is achieved by using only the SJAs-based thrust vector control. C. Li et al.: Active Flow Vector Flight Control Using Only SJAs for a Fixed-Wing UAV TABLE 1. From the results in paper [16], the primary jet deflected after the SJA working for 0.05 s, this time is relatively small compared with the response time of the fastest loop (about 2 s). The sign(δ) in equation (7) will be explained later

THE MODEL OF THE FIX-WING UAV WITH SJAS

SIMULATION RESULTS

CONCLUSION