Multibody Dynamic Modeling and Simulation of a Tailless Folding Wing Morphing Aircraft

= =
d / dt d 2 / dt 2
A T
= = =
aerodynamic thrust components of respective variable in body coordinates
i =0,1,2,3,4 = fuselage, right inner and outer wing, left inner and outer wing
= = control surface deflection angle angle between thrust and ob xb
Superscripts (.) (..) Subscripts
2 American Institute of Aeronautics and Astronautics
The purpose of this paper is to model and simulate a tailless folding wing morphing aircraft in wing folding process. The wing area and other parameters of morphing aircraft largely change when morphing, which will affect the aerodynamic force acting on the aircraft and lead to a variation of movements in the morphing process. The dynamic model of tailless folding wing morphing aircraft in wing folding process was founded and the six-DOF nonlinear equation was deduced. Furthermore, the decoupled longitudinal dynamic equation of morphing process was presented by simplifying. And the result of numeric simulation of aerodynamic force in wing folding process shows that the aerodynamic force is approximate to the steady state. The longitudinal response of morphing process in different wing fold angular velocities was numerically simulated by quasi-steady aerodynamic assumption when taking no account of the unsteady aerodynamic effect in small wing fold angular velocities. And the key factors which affect the dynamical characteristics of morphing process of the tailless folding wing morphing aircraft were investigated by quantity. The research results can be as great reference for the flight control system design in morphing and evaluating the morphing flight safety at low altitude of morphing aircraft.
change. Moreover, the aerodynamic force acting on the aircraft also change, which will affect the movement of the morphing aircraft. So wing morphing is a very important process for morphing aircraft. If some kinetic parameters of the morphing aircraft change unexpectedly, the flying quality may be affected and will even threaten the flight safety of the morphing aircraft. So it is necessary to analysis the dynamic response of morphing aircraft in the morphing process. The wing morphing process of morphing aircraft is similar with the process of changing the sweep angle of variable swept wing aircraft. Ref. 3 investigated the dynamic response of a variable swept wing aircraft in the course of changing the sweep angle. But for morphing aircraft, the range of parameters changing will be wider. In the wing morphing process, the morphing aircraft should be regarded as a multibody system which is composed by the fuselage and several moving parts of wing. Thomas M Seigle4 analyzed the modeling of large-scale morphing aircraft in theory. However, few studies have been done on the modeling and simulation of a specific morphing aircraft. This paper focuses on modeling and simulation of a tailless folding wing morphing aircraft during the wing fold process, which can be based as the flight control design for morphing aircraft.
x, y , z
I. Introduction
M
orphing is that the aircraft can adapt the different flight environments and combat missions by changing the aerodynamic configuration, using advanced materials and actuators.1,2 For example, the morpdent, AIAA Student Member, School of Aeronautic Science and Engineering, email: yueting_buaa@ † Professor, School of Aeronautic Science and Engineering, email: bhu_wlx@ ‡ Researcher
Nomenclature
CD 0 CDV CDα CL 0 CLV CLq C Lα
= = = = = = =
drag coefficient at zero CL
ˆ) ∂CD / ∂ (V ∂CD / ∂α ˆ) ∂CL / ∂(V ˆ ∂CL / ∂q ∂CL / ∂α
lift coefficient at zero
Ting Yue * and Lixin Wang † School of Aeronautic Science and Engineering Beijing University of Aeronautics and Astronautics Beijing, China, 100191 Junqiang Ai ‡ The First Aircraft Institute of AVIC-I, Xi’an, China, 710089
AIAA Atmospheric Flight Mechanics Conference 10 - 13 August 2009, Chicago, Illinois
AIAA 2009-6155
Multibody Dynamic Modeling and Simulation of a Tailless Folding Wing Morphing Aircraft
1 American Institute of Aeronautics and Astronautics
Copyright © 2009 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.
C Lα C Lδ Cm 0 CmV Cmq Cmα Cmα Cmδ c D F Gw g Η I Ii L M m ob xb yb zb og x g y g z g p q S S T V
= = = = = = = = = = = = = = = = = = = = = = = = = = = = = = =