# How to calculate Mars and Lunar payload if I have LEO payload? [closed]

I am working on a project and i need the payload capabilities of different rockets to LEO, mars and lunar orbit. Usually the LEO payload along with all other relevant data is given for all rockets. is there any way i can calculate the other two from that?

To calculate payloads one can use Tsiolkovsky rocket equation, whose parameters are delta-V (total necessary change of velocity, which is constant for a given trajectory; specifically its geometry in 4-D space), $$v_e$$ - the exhaust velocity for the gas exiting rocket engine (relative to the rocket), and $$m_0$$ - the mass of the rocket itself (with all the cargo, crew etc; except fuel). In this example (see image) $$m_{degvielai}$$ is the mass of fuel (sorry for the index - it's in Latvian, as I took it from one of my older papers, which is also in Latvian; "degviela" in Latvian means "fuel")