Research on Morphing Scheme and Forward-Swept Wing Parameters Based on a Forward-Swept Wing Morphing Aircraft

2019 ◽  
pp. 1353-1364
Author(s):  
Xuefei Li ◽  
Zhansen Qian ◽  
Chunpeng Li ◽  
Xianhong Xiang ◽  
Pengbo Xu
Keyword(s):  
Swept Wing ◽  
Morphing Aircraft ◽  
Wing Morphing

Research on Longitudinal Static Stability for VFSW Tailless Configuration UAV

2014 ◽  
Vol 543-547 ◽  
pp. 348-353
Author(s):  
Xin Bing Su ◽  
Zhou Zhou ◽  
Jing Cheng Shi ◽  
Xu Wang
Keyword(s):  
Flight Control ◽  
Stability Margin ◽  
Static Stability ◽  
Flight Control System ◽  
Swept Wing ◽  
Mechanical Environment ◽  
Morphing Aircraft ◽  
Variation Curve ◽  
Dynamic Shape ◽  
Longitudinal Static Stability

The Variable Forward-Swept Wing (VFSW) Tailless configuration UAV can well satisfy multipurpose demands. However, this kind of unconventional morphing aircraft lacks tail, which brings great challenge to stability analysis. The connatural aero-elasticity divergence and the strong aerodynamic coupling as well as many uncertain factors in mechanical environment, give the VFSW Tailless configuration UAV complicated dynamic characteristics. During the process of transformation, the variation of dynamic shape will inevitably lead to the variation about aerodynamic center and barycentre positions of airplane, then make the angle of attack static stability margin variable, and directly influence stability of aircraft. On the basis of introduction of the VFSW Tailless configuration UAV, according to its geometric shape, positions of aerodynamic center and barycentre, in different states with different forward-swept angle, were calculated, so as to obtain variation curve of longitudinal static stability margin, which provided preferences for dynamics analysis, position of barycentre adjustment and design of flight control system (FCS).

The Analysis of Motion Characteristics of Variable Forward-Swept Wing Mechanism with a Double Slideways

2013 ◽  
Vol 456 ◽  
pp. 137-141
Author(s):  
Xin Bing Su ◽  
Zhou Zhou ◽  
Xu Wang ◽  
Jing Cheng Shi ◽  
Peng Chen
Keyword(s):  
Delta Wing ◽  
Three Dimensional ◽  
Linear Motion ◽  
Dimensional Model ◽  
Swept Wing ◽  
Three Dimensional Model ◽  
Morphing Aircraft ◽  
Motion Characteristics ◽  
General Configuration ◽  
Analysis Of Motion

Based on the variable forward-swept wing configuration, this paper utilized a variable forward-swept wing mechanism with a double slideways, which make it possible for the aircraft to switch among orthogonal wing, forward-swept wing and delta wing freely. The general configuration of the variable forward-swept wing mechanism with a double slideways was elucidated by means of a three-dimensional model plot and then the mathematic simulation model was also established. The motion characteristics of linear motion were simulated, analyzed and optimized. The results indicated that the variable forward-swept wing mechanism with a double slideways can meet the aerodynamic requirements better. Moreover, there exists great linear relationship between the position of nut and the wing forward-swept angle. Therefore, this mechanism may serve as a useful reference when developing a morphing aircraft.

Longitudinal Dynamics Response of M-Wing Morphing Aircraft

2012 ◽  
Vol 538-541 ◽  
pp. 2627-2630
Author(s):  
Lai Bin Xu
Keyword(s):  
Vortex Lattice ◽  
Equations Of Motion ◽  
Lattice Method ◽  
Morphing Aircraft ◽  
Simulation Methodology ◽  
Vortex Lattice Method ◽  
Longitudinal Dynamic ◽  
Aerodynamic Properties ◽  
Dynamics Response ◽  
Wing Morphing

A simulation methodology suitable for morphing wing aircraft is presented, accounting for the changes in both inertial and aerodynamic properties. The aerodynamics was generated with vortex lattice method and solved concurrently with 6DOF nonlinear extended equations of motion. Due to the wing morphing, there are 4 additional forces and moments exhibiting in the extended equations of motion. The simulation mythology was applied to M-wing morphing aircraft, and the longitudinal dynamic response was analyzed with the wing morphing symmetrically. The results show that the additional forces and moments influence the flight dynamic considerably

scholarly journals Adaptive Wing Morphing Strategy and Flight Control Method of a Morphing Aircraft Based on Reinforcement Learning

2019 ◽  
Vol 37 (4) ◽  
pp. 656-663
Author(s):  
Binbin Yan ◽  
Yong Li ◽  
Pei Dai ◽  
Muzeng Xing
Keyword(s):  
Reinforcement Learning ◽  
Flight Control ◽  
Control Method ◽  
Sliding Mode ◽  
Normal Load ◽  
Aerodynamic Characteristics ◽  
Morphing Aircraft ◽  
Adaptive Wing ◽  
Aerodynamic Parameters ◽  
Wing Morphing

The morphing aircraft can change different wing shapes or geometries to achieve the optimal flight performance according to various mission scenarios. In this paper, DATCOM is used to calculate aerodynamic parameters based on Firebee UAV morphing aircraft with different wing configurations and analyze aerodynamic characteristics. A novel adaptive wing morphing strategy for morphing aircraft based on reinforcement learning method is proposed. This method can highly meet the demand of keeping optimal performance in multiple flight conditions, and the adaptive wing morphing strategy, three-loop normal load altitude controller and sliding mode velocity controller can together make sure stability of morphing aircraft during morphing process with good tracking performance.

Sign in / Sign up

Export Citation Format

Share Document