Help me put this rocket into orbit Need a jumpstart

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    Orbit Rocket
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SUMMARY

The discussion centers on calculating the necessary thrust and velocity for placing a rocket into a circular orbit using a single stage of launch. Key parameters include an exhaust velocity of 3,000 m/s and the need to account for gravitational acceleration as the rocket ascends. The relevant equations include V(escape)=sqrt(2GME/R) for escape velocity and thrust calculations based on mass flow rates. The user seeks guidance on which equations to apply and how to structure their calculations effectively.

PREREQUISITES
  • Understanding of basic physics principles, particularly gravitational forces and motion.
  • Familiarity with rocket propulsion concepts, including thrust and exhaust velocity.
  • Knowledge of orbital mechanics, specifically circular orbits and escape velocity.
  • Proficiency in using spreadsheet software for data visualization and calculations.
NEXT STEPS
  • Research the principles of rocket propulsion and thrust calculation using the thrust equation: thrust = [(m1v1)-(m2v2)]/(t2-t1).
  • Study orbital mechanics, focusing on the calculations for circular orbits and the necessary tangential velocity at altitude.
  • Learn how to model gravitational acceleration changes with altitude and its impact on rocket ascent.
  • Explore spreadsheet functions for graphing altitude vs. time and speed vs. altitude to visualize rocket performance.
USEFUL FOR

Aerospace engineering students, physics enthusiasts, and anyone involved in rocket design or orbital mechanics will benefit from this discussion.

joeblack99999
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Homework Statement


Ok so i had all of this typed up and some work typed out and then the page refreshed and i lost it all so this one is going to be shorter and more brief.

I have to create a spreadsheet and graph of altitude vs time and speed vs altitude. My goal is to place a rocket into a circular orbit assuming only 1 stage of launch/flight. Calculate thrust. Typical exhaust velocity is 3,000 m/s. Ignore air drag. Consider acceleration due to gravity and notice its decrease as the rocket ascends. Consider the altitude of orbit and calculate the speed necessary to keep the rocket in orbit. This will be final velocity (which is when mass of fuel = zero) Most likely i will calculate only vertical velocity. Rocket is launched on equator in east direction (speed of Earth in east direction is 1440 km/h) Ignore complication of ejecting the payload with initial tangential speed by assuming when the rocket reaches the desired height it magically turns around and the vertical velocity becomes the tangential velocity. Assume the mass of the rocket, fuel, and payload- and the burnout time.

Homework Equations


V(escape)=sqrt(2GME/R)
thrust= [(m1v1)-(m2v2)]/(t2-t1)
V(at equator)= 2piR/t = 463.8 m/s
v= sqrt(mew/r)

The Attempt at a Solution


I need a jumpstart to the problem because i really don't know where to start. I am not simply asking for a full solution to avoid doing my work, but maybe simply some info or tips to start me off thinking in the right direction. I am thinking that i will have (delta)v= v - (delta)force of gravity. I am just not sure which other formulas to use for this specific problem and how to start it off. I've been playing with some numbers and equations but can't piece it all together for the whole overall solution.
 
Last edited:
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bump- does nobody know what equations i would need to put something into orbit?
 

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