Abstract
To solve the issues of directional control and aerodynamic moment coupling for a low-aspect tailless configuration with a diamond-shaped wing, we herein propose the concept of a flow coupling rudder (FCR). The FCR was composed of two basic control surfaces: a spoiler slot deflector (SSD) on the upper surface of the wing and the corresponding elevon. With the constraints of the fixed area and spanwise position of the SSD, the effects of the leading-edge sweep angle, chord position of the SSD, and collocating deflection angles of the SSD and elevon on the control characteristics of the configuration were analyzed using a numerical method. Based on the analysis, the selection principle of the key parameters for designing the FCR for the configuration was proposed. This proves that the leading edge of the selected SSD should be swept back instead of being parallel to the trailing edge of the wing to design an FCR with favorable aerodynamic performance for such a configuration. By accurately adjusting the parameters of the SSD and elevon, the FCR on the one-side wing could supply an effective yawing moment while simultaneously weakening or even eliminating the coupling pitching and rolling moments of traditional drag-type control surfaces. In this study, we provide a method for the directional control surface design of a low-aspect tailless configuration with a diamond-shaped wing.
Highlights
Academic Editor: Hirotaka SakaueLow-aspect tailless configurations with diamond-shaped wings have become the focus of advanced fighter research owing to their superior aerodynamic performance, good stealth performance, and easy integration arrangement [1,2,3,4]
When adopting the elevon or spoiler slot deflector (SSD) alone, it provides yawing and couples the rolling and pitching moments. It requires the cooperation of other control surfaces to reduce or even eliminate coupled moments; For the configuration with a diamond-shaped wing, the SSD with an appropriate sweptback leading edge is more conducive to improving the directional control and providing more stable control than the SSD with the leading edge parallel to the trailing edge of the wing; In terms of the configuration studied adjust collocating deflection angles of flow coupling rudder (FCR) reasonably, the directional stability of maneuvering flight state can be increased and the coupled rolling and pitching moments can be weakened or even be eliminated at small and medium angles of attack; The concept of FCR for the tailless configuration could provide a satisfactory yaw moment and weaken or even eliminate the coupling pitching and rolling moments
The FCR can improve the directional control and aerodynamic moment coupling issues by only one group of control surfaces, providing more options for the other side of the control surface to participate in other controls
Summary
Low-aspect tailless configurations with diamond-shaped wings have become the focus of advanced fighter research owing to their superior aerodynamic performance, good stealth performance, and easy integration arrangement [1,2,3,4]. The Royal Institute of Technology (KTH) proposed the concept of 2yaw of 18 control by differential flaps on a tailless configuration based on a wind tunnel test [15]. Concept of yaw control by differential flaps on a tailless configuration based on moment, a wind tunnel test rolling [15]. Related research has studies mainly focused on wings with a sweptback trailing edge and lacked related parameter demonstrated that CCS can offer a satisfactory yawing moment and decrease the coupling investigations. Aiming at the yawing control issue of low-aspect tailless configurations with a and the corresponding elevon based on flow coupling is proposed .
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