The one thing that VBA has going for it is the incredibly large user base. I would love to take a look at how much data there is. It also holds true for rocket-like reaction vehicles whenever the effective exhaust velocity is constant, and can be summed or integrated when the effective exhaust velocity varies. Tsiolkovsky's Rocket Equation. Thank you again!
The Tsiolkovsky rocket equation, classical rocket equation, or ideal rocket equation is a mathematical equation that describes the motion of vehicles that follow the basic principle of a rocket: a device that can apply acceleration to itself using thrust by expelling part of its mass with high velocity can thereby move due to the conservation of momentum. : Method to calculate the altitude that your rocket should reach with a given motor.
One has to approach it much more like hardware design (for integrated circuits or FPGAs) , i.e. @dmckee: I agree, debugging a poorly designed spreadsheet is hard to impossible. V E: Velocity of the rocket's exhaust in meters per second or feet per second.
The values in the report are given as 'inertial acceleration' but I haven't learnt this yet (still in high school). You say the report lists the takeoff acceleration as $10$ m/sec$^2$, which is over $1$ g. This would be very high for a liquid rocket. For any such maneuver (or journey involving a sequence of such maneuvers): This spreadsheet does not include a weight column, so I'm wondering if I even need to subtract the force of weight from the thrust. Imagine a rocket at rest in space with no forces exerted on it (The effective exhaust velocity is often specified as a The rocket equation captures the essentials of rocket flight physics in a single short equation. Understanding NASA's terminology and frame of reference will be essential to getting this question right… unfortunately that is not my area of expertise, but that's the information I would look for.Without seeing your calculations and a link to the report I can't be sure, but I suspect you are reading the report incorrectly. Realising that impulse over the change in mass is equivalent to force over propellant mass flow rate (p), which is itself equivalent to exhaust velocity,
By representing the delta-v equation as the following: However, I can't seem to get the right acceleration.
Thanks!
I'll appreciate any and all helpful feedback and I can provide more information if needed.
At one level, you could consider the fuel flow and thrust constant and just model the acceleration as thrust/mass less gravity. I'll look into that now!
Description The Tsiolkovsky rocket equation, or ideal rocket equation describes the motion of vehicles that follow the basic principle of a rocket: a device that can apply acceleration to itself (a thrust) by expelling part of its mass with high speed and move due to the conservation of momentum. From the ideal rocket equation, 90% of the weight of a rocket going to orbit is propellant weight. So instead of saying$$x_{new} = x_{old} + 0.5*(v_{old}+v_{new}) * dt $$There are also many tricks you can use in Excel to minimize the chance of errors - I hope you know how to use named ranges (after assigning the name "gravity" to cell A6 and putting the value 9.81 in it, you can type Some other things to consider (it sounds like you already know this):Coriolis forces are always at right angles to the instantaneous velocity, and they appear because an object flying in a straight line will "feel the earth rotate underneath it".
Spreadsheets can often be forced to do programming tasks but above a certain level of complexity they are not the right tool for the job. With three similar, subsequently smaller stages with the same and the payload is 10% × 10% × 10% = 0.1% of the initial mass.
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