engine.m

大气层内航天器飞行动力学matlab仿真模型

% Copyright Ashish Tewari (c) 2006
function [T,cT]=engine(alt,mach)
M=[0 0.25 0.5 0.75 1 1.25 1.5 1.75 2 2.25]; % Mach number
h=[0 10 20 30 36 40 50]*1000/3.28; % std. altitude (m)
Thrust=[30 21.5 15 10 8 6.5 4;
   29 21 14.5 9.8 7.5 6 3.8;
   32 22.5 16 10.5 8.5 7 4.5;
   33 28 19 12.5 10 8 5;
   35 29 23.5 16 12.5 10 6;
   37 31 25.5 21 16 13 8.5;
   42.5 35 28 22.5 19.5 15.5 9.2;
   43.5 38 33 25 21.5 17.5 10.5;
   46 39 34 28 24.5 19 11.5;
   48 42 35 29 26 21.5 13]*1000*9.8/2.2; %Thrust (N)
TSFC=[1.64 1.66 1.68 1.7 1.71 1.71 1.71;
      1.74 1.76 1.77 1.78 1.79 1.79 1.79;
      1.78 1.79 1.8 1.815 1.82 1.82 1.82;
      1.86 1.8 1.81 1.82 1.825 1.825 1.825;
      1.93 1.84 1.78 1.79 1.79 1.79 1.79;
      2 1.9 1.825 1.76 1.75 1.75 1.75;
      2.04 1.96 1.87 1.79 1.74 1.74 1.74;
      2.16 2.05 1.92 1.84 1.79 1.79 1.79;
      2.32 2.14 1.98 1.88 1.83 1.83 1.83;
      2.44 2.26 2.1 1.97 1.88 1.88 1.88]; % (per hour)
  [X,Y]=meshgrid(h,M);
  T=interp2(X,Y,Thrust,alt,mach);
  cT=interp2(X,Y,TSFC,alt,mach);