How to store values from all iterations into one vector?

Question

Alison Michell 2018-7-25

0
链接

此问题的直接链接

https://ww2.mathworks.cn/matlabcentral/answers/411994-how-to-store-values-from-all-iterations-into-one-vector

评论： Alison Michell 2018-7-25

Hi, I am trying to run my code to calculate values over every iteration and them plot my V value vs time, however, I haven't been able to successfully store all of the calculated values over all the iterations. I tried to with the brackets before the for loop but I don't think I did them correctly. Any help in figuring out how to do this would be appreciated. Thank you!

function RocketLaunch
clc, clear
m_rocket = 24675.42;                    % Empty Mass / Mass of Rocket [kg]
m_fuel0= 379838.25;                     % Mass of Fuel [kg]
m_total0 = m_fuel0 + m_rocket;          % Initial Total Mass
thrust0 = 0;                            % Initial Thrust                      
thrust = 8296425.89;                    % Thrust in Newtons - Assuming to be constant 
BurnTime = 161;                         % Burn Time [s]
m_dot = m_fuel0./BurnTime;              % Mass flow rate of fuel - Assuming it is constant
t = [1:155];                            % Code only works to t = 155s
VEL = [];
EX_VEL = [];
for i = 1:length(t-1)
    if i > BurnTime
        m_fuel0 = 0;
        thrust = 0;
        m_dot = 0;
        V_e = thrust./m_dot; 
        V = V_e.*log(m_total./m_rocket);
     end
      m_fuel = m_fuel0-m_dot.*i;
      BurnRate = (m_fuel - m_rocket)./BurnTime;
      m_total = (m_fuel + m_rocket)+(BurnRate.*i);
      V_e = thrust./m_dot;
      V = V_e.*log(m_total./m_rocket);
end
VEL(i) = V
EX_VEL(i) = V_e
plot(t,VEL)

0 个评论
显示 -2更早的评论隐藏 -2更早的评论

请先登录，再进行评论。

请先登录，再回答此问题。

Answer 1

KSSV 2018-7-25

1
链接

此回答的直接链接

https://ww2.mathworks.cn/matlabcentral/answers/411994-how-to-store-values-from-all-iterations-into-one-vector#answer_330217

在 MATLAB Online 中打开

function RocketLaunch
clc, clear
m_rocket = 24675.42;                    % Empty Mass / Mass of Rocket [kg]
m_fuel0= 379838.25;                     % Mass of Fuel [kg]
m_total0 = m_fuel0 + m_rocket;          % Initial Total Mass
thrust0 = 0;                            % Initial Thrust
thrust = 8296425.89;                    % Thrust in Newtons - Assuming to be constant
BurnTime = 161;                         % Burn Time [s]
m_dot = m_fuel0./BurnTime;              % Mass flow rate of fuel - Assuming it is constant
t = [1:155];                            % Code only works to t = 155s
VEL = zeros([],1);
EX_VEL = zeros([],1);
for i = 1:length(t-1)
    if i > BurnTime
        m_fuel0 = 0;
        thrust = 0;
        m_dot = 0;
        V_e = thrust./m_dot;
        V = V_e.*log(m_total./m_rocket);
    end
    m_fuel = m_fuel0-m_dot.*i;
    BurnRate = (m_fuel - m_rocket)./BurnTime;
    m_total = (m_fuel + m_rocket)+(BurnRate.*i);
    V_e = thrust./m_dot;
    V = V_e.*log(m_total./m_rocket);
    VEL(i) = V ;
    EX_VEL(i) = V_e ;
end
plot(t,VEL)