固定翼无人驾驶飞机的性能参数分析附matlab代码.zip

function removal = uavparameter( InputHeight ) % UAVPARAMETER % First edition : 05-Apr-2015 01:37:56 % Lasted edition : 12-Apr-2015 00:57:51 % Lasted modify : Chang, Wei-Chieh % % DESCRIPTION % This file is the main file for "UAV-Performance". This is a software % which provides performance parameters analysis for fixed-wing unmanned % aerial vehicle. But everything is still in developing stage. % % COPYRIGHT % Copyright 2015 UAV Laboratory, Dept. of Aerospace Engineering, Tamkang % University. % % AUTHOR INFORMATIONS % Chang, Wei-Chieh % addischang1991@gmail.com % Huang,Kuan-Lin % breakfastho@yahoo.com.tw % Liu, Yu-Lin % lightning.539418@gmail.com % COUNTER % The counter is to declare scale or size for input parameters. It will % be helpful while you take integations. If you want to know more detail, % please check the parameter explanation in the end of this file. global SizH LenH CouF CouH SizH = size( InputHeight ); LenH = length( InputHeight ); CouH = 1; CouF = 1; % ATMOSPHERE DATA % The standard atmosphere data can be identified by the subfunction stdatm % which providing standard atmosphere data computation. global rho_inf h_inf g_inf a_inf T_inf atm = stdatm( InputHeight ); h_inf = atm( :, 1 ); g_inf = atm( :, 2 ); T_inf = atm( :, 3 ); a_inf = 331 + 0.6 .* ( 273 - T_inf ); rho_inf = atm( :, 6 ); % SPECIFICATIONS % The specification of aircraft which we want to analysis. Those data are % necessary for performance analysis. If you want to know more detail, % please check the parameter explanation in the end of this file. global W S_fw S_bw b_fw b_bw AR_fw AR_bw e_fw e_bw mass = 18.75; W = mass * g_inf( 1, 1 ); S_fw = 0.8929; S_bw = 0.8929; b_fw = 2.5; b_bw = 2.5; e_fw = 0.8; e_bw = 0.8; Cr_fw = 0.48979; Cr_bw = 0.48979; Ct_fw = 0.1959; Ct_bw = 0.1959; AR_fw = b_fw^2 / S_fw; AR_bw = b_bw^2 / S_bw; % AERODYNAMICS % The aerodynamics parameters global CD_0 CL_max CD_0 = 0.0125; CL_max = 1.5; % PROPULSION % The specification engine and propellers. Those parameters will dominate % the power aviliable, thrust aviliable. If you want to know more detail, % please check the parameter explanation in the end of this file. global P eta_p P = 1.7 * 746; eta_p = 0.8; % Just return. removal = rho_inf; % Parameter explanation % mass of aircraft : mass % angle of attack : alpha % free-stream velocity : V_inf % lift : L % drag : D % moment about the quarter chord : M_0.25c % moment about the leading edge : M_LE % density of the ambient air : rho_inf % reference area : S % moment : M % lift coefficient : CL % drag coefficient : CD % moment coefficient : CM % dynamic pressure : q_inf % geometory height : h_inf % Reynolds number : Re % chord length : c % Mach number : M_inf % speed of sound : a_inf % temperature : T_inf % zero-lift angle of attack : alpha_L0 % lift slope : a_0 % slope of the moment coefficient : m_0 % ski_friction coefficient : CF % aerodynamic center : CM_ac % distance between aerodynamic center and quarter_chord : x_ac % aspect ratio : AR % taper ratio : lambda % Mach angle : mu % weight : W % thrust : T % induced drag : D_i % induced drag coefficient : CD_i % span efficiency factor : e % zero-lift parasite drag : D_0 % zero-lift drag coefficient : CD_0 % jet velocity : V_j % power available : P_A % propulsive efficiency : eta_p % power from engine shaft : P % number of propeller revolutions per second : N % advance ratio : J % pitch angle : beta % weight of fuel burned per unit thrust per unit time : c_t % Reference area for forward wing : S_fw % Reference area for backard wing : S_bw % Span for forward wing : b_fw % Span for backard wing : b_bw % Wing root chord for forward wing : Cr_fw % Wing root chord for backard wing : Cr_bw % Wing tip chord for forward wing : Ct_fw % Wing tip chord for backard wing : Ct_bw % Aspect ratio for forward wing : AR_fw % Aspect ratio for backard wing : AR_bw % Efficiency for forward wing : e_fw % Efficiency for backard wing : e_bw % Size of input height : SizH % Length of input height : LenH % Counter of height : CouH % Counter of figure : CouF