Virtual flight test of pitch and roll attitude control based on circulation control of tailless flying wing aircraft without rudders

Zhang, Liu; HUANG, Yong; ZHU, Zhenglong; GAO, Lihua; CHEN, Fuzheng; WU, Fuzhang; He, Meng

doi:10.1016/j.cja.2023.03.017

Cited by 9 publications

(1 citation statement)

References 17 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…For example, Lockheed proposed the "Innovative Control Effectors (ICE)" plan [11], NATO AVT-239 task group [12], and successfully performed flight verification at low speeds, for example using DEMON UAV [13] and MAGMA UAV Demonstrator [14]. Through a powered virtual flight test in a wind tunnel [15], the China Aerodynamics Research and Development Center verified the rudderless flight control of a tailless flying wing in pitch and roll attitudes based on CC, and responded rapidly. The studies above preliminarily show the application prospect of CC for improving the stealth and maneuver control characteristics of flying wing aircraft.…”

Section: Introductionmentioning

confidence: 99%

Flow Characteristics and Parameter Influence of the Under-Expansion Jet on Circulation Control Airfoil

Zhang

et al. 2023

Energies

Self Cite

View full text Add to dashboard Cite

The enhancement in the jet pressure ratio and jet velocity contributes to expanding the control efficiency and control boundary of circulation control airfoil under high subsonic incoming flow. However, because of an excessive jet pressure ratio, the jet separates prematurely on the Coanda surface, resulting in control failure. In a bid to improve the adhesion capability of the jet under a high pressure ratio, a circulation control airfoil with a converging nozzle and back-facing step structure at the trailing edge was numerically simulated based on the Reynolds averaged Navier−Stokes equation (RANS), and a study was conducted on the complex flow structure of the under-expansion jet on the Coanda surface and the impact of design parameters such as jet pressure ratio, ellipticity, and nozzle height on the jet separation. The results show that the back-facing step provides an expansion space for the under-expansion jet and changes the shock-boundary layer interaction form. As the jet pressure ratio and nozzle height increase, the size of the shock cell increases, the strength of the intercepting shocks on both sides increases, and Mach reflection occurs, resulting in jet stratification and in a decline in the adhesion capability of the jet. The combination design of proper ellipticity and the back-facing step contributes to forming a closed low-pressure vortex area behind the step and promote jet attachment. Reducing the nozzle height can improve the adhesion capability of the jet under a high pressure ratio.

show abstract