摘要
With regard to the objective of stealthy optimization in control surface deflection, the stealth-based multi-effectors distribution scheme is presented for flying wing in this paper. The radar cross section(RCS) of each control surface is calculated and analyzed. The stealthy efficiency data curves are obtained through comparing the deflection values with the normal state. Taking the objective of optimal stealthy performance into account, the weighted pseudo-inverse is achieved by equivalence transformation. Furthermore, the sequential quadratic programming(SQP) based control allocation is applied to get rid of actuator constraints. To validate the effectiveness of the proposed approach, the simulation on the flying wing indicates that the stealthy generated by control surfaces can be minimized by reasonable deflections.
With regard to the objective of stealthy optimization in control surface deflection, the stealth-based multi-effectors distribution scheme is presented for flying wing in this paper. The radar cross section(RCS) of each control surface is calculated and analyzed. The stealthy efficiency data curves are obtained through comparing the deflection values with the normal state. Taking the objective of optimal stealthy performance into account, the weighted pseudo-inverse is achieved by equivalence transformation. Furthermore, the sequential quadratic programming(SQP) based control allocation is applied to get rid of actuator constraints. To validate the effectiveness of the proposed approach, the simulation on the flying wing indicates that the stealthy generated by control surfaces can be minimized by reasonable deflections.
引文
[1]O.H?rkeg?rd,Backstepping and control allocation with applications to flight control,Link?ping University,2003.
[2]C.Vermillion,J.Sun,K.Butts,Model predictive control allocation for overactuated systems-stability and performance,Proceedings of the 46th IEEE Conference on Decision and Control,New Orleans,USA,2007,1251-1256.
[3]J.M.Buffington,Modular control law design for the innovative control effectors(ICE)tailless fighter aircraft configuration,AFRL-VA-WP-TR-1999-3057,1999:12-42.
[4]A.F.Susan,B.R.Taylor,M.Bodson,Investigation of optimal control allocation for gust load alleviation in flight control,AIAA Atmospheric Flight Mechanics Conference,2012:13-16.
[5]H.Alwi,M.T.Hamayun,C.Edwards,An integral sliding mode fault tolerant control scheme for an octorotor using fixed control allocation,13th IEEE Workshop on Variable Structure Systems VSS’14,Nantes,France,2014:1-6.
[6]T.A.Johansen,T.I.Fossen,S.P.Berge,Constrained nonlinear control allocation with singularity avoidance using sequential quadratic programming,IEEE Transactions on Control Systems Technology,2004,12:211-216.
[7]C.Yong,D.Xin-min,X.Jian-ping,Multi-objective optimization design of weight coefficients for weighted control allocation scheme,Control and Decision,2013,28:991-996.
[8]A.Xiao-feng,Z.Xiao-hai,L.Yong-zhen,Bistatic scattering centres of cone-shaped targets and target length estimation,Science China Information Sciences,2012,55:2888-2898.
[9]C.Yong,D.Xin-min,W.Fa-wei,The design of space optimization for weighted control allocation scheme,Information and Control,2012,41:225-232.
[10]J.Nocedal,S.J.Wright,Numerical optimization,2th ed.,Springer,1999:529-562.
[11]C.Yong,Aerodynamic configuration design and control allocation research of flying wing,Air Force Engineering University,2009.