- #1
MJCfromCT
- 20
- 0
Hi all,
I am having trouble numerically integrating a function using Maple 10. Here is a bit of background on the problem:
This problem is asking for two plots, one of the velocity of a sounding rocket with respect to time, and the other being the height of the sounding rocket with respect to time. Gravity and drag act on this rocket.
I have the following equations:
density as a function of altitude
drag coefficient as a function of mach number
mach number as a function of velocity
drag as a function of drag coefficient
thrust as a function of mass flowrate and exhaust velocity
mass as a function of time
This problem asks to create these plots for various values of mass flowrate that I am supposed to set myself (2 kg/s, 2.1 kg/s, 2.2...etc).
The known constants that I have are the following:
specific impulse
exhaust velocity
initial mass
initial velocity
initial height
initial density
After inputting everything into maple, I come up with this differential equation:
sys1 := [diff(v(t),t) = (thrust-drag-mass*9.81)/mass, diff(y(t),t) = v(t)];
I am not great with maple, so I am not sure if this is even the correct syntax.
In my attempt to solve the differential equation, I tried this command:
sol1 := dsolve(sys1, numeric, v(0)=0, y(0)=0);
Unfortunately, this gives me the following error:
Error, (in dsolve/numeric/type_check) insufficient initial/boundary value information for procedure defined problem
Any suggestions as to what may be causing the problem here? If necessary, I can post my entire maple file if more detail is needed. Thanks in advance.
I am having trouble numerically integrating a function using Maple 10. Here is a bit of background on the problem:
This problem is asking for two plots, one of the velocity of a sounding rocket with respect to time, and the other being the height of the sounding rocket with respect to time. Gravity and drag act on this rocket.
I have the following equations:
density as a function of altitude
drag coefficient as a function of mach number
mach number as a function of velocity
drag as a function of drag coefficient
thrust as a function of mass flowrate and exhaust velocity
mass as a function of time
This problem asks to create these plots for various values of mass flowrate that I am supposed to set myself (2 kg/s, 2.1 kg/s, 2.2...etc).
The known constants that I have are the following:
specific impulse
exhaust velocity
initial mass
initial velocity
initial height
initial density
After inputting everything into maple, I come up with this differential equation:
sys1 := [diff(v(t),t) = (thrust-drag-mass*9.81)/mass, diff(y(t),t) = v(t)];
I am not great with maple, so I am not sure if this is even the correct syntax.
In my attempt to solve the differential equation, I tried this command:
sol1 := dsolve(sys1, numeric, v(0)=0, y(0)=0);
Unfortunately, this gives me the following error:
Error, (in dsolve/numeric/type_check) insufficient initial/boundary value information for procedure defined problem
Any suggestions as to what may be causing the problem here? If necessary, I can post my entire maple file if more detail is needed. Thanks in advance.