thermeq.m

航天工程工具箱

function [abem,TC,TK]=thermeq(abem,A,Tp,a,d,R,r,Q)
%[aeo TC TK] = thermeq(ae,[Atot Amin Amax],Tp,a,d,R,r,[Qmin Qmax])
%
%   ae   []     : [alpha epsilon]  (Nx2)
%   Atot [m^2]  : total spacecraft surface area
%   Amin [m^2]  : minimum spacecraft surface area
%   Amax [m^2]  : maximum spacecraft surface area
%   Tp   [K]    : planet surface brightness temperature
%   a    []     : planet albedo
%   d    [AU]   : planet orbital radius
%   R    [Mm]   : planet radius
%   r    [Mm]   : spacecraft orbital radius
%   Qmin [W]    : spacecraft minimum internal thermal power
%   Qmax [W]    : spacecraft maximum internal thermal power
%
%   aeo  []     : [alpha epsilon alpha/epsilon]  (Nx3)
%   TC   [degC] : [Tmin Tmax DeltaT]
%   TK   [K]    : [Tmin Tmax DeltaT]

ab=abem(:,1);
em=abem(:,2);
abem(:,3)=ab./em;
s=constant('sigma');
T0=constant('T0');
d=convert(d,'AU','m');
R=R*1e6;
r=r*1e6;
Jp=s*Tp^4;
disp(['Jp = ' num2sci(Jp) 'W/m^2'])
S=3.92e26/(4*pi*d^2);
disp(['S = ' num2sci(S) 'W/m^2'])
H=(r-R)/R;
F12=.5*[1-sqrt(H^2+2*H)/(1+H)];
Tmin=sqrt(sqrt((A(2)*em*F12*Jp+Q(1))./(A(1)*em*s)));
Tmax=sqrt(sqrt((A(3)*ab*S+A(3)*ab*a*F12*Jp+A(3)*em*F12*Jp+Q(1))./(A(1)*em*s)));
TK=[Tmin Tmax Tmax-Tmin];
TC=[Tmin-T0 Tmax-T0 Tmax-Tmin];