Part B: LRE Rocket DesignYou have been inspired to create your own rocket to resupply space stations in orbit. Consider a payload of $2000$ kg of stable cargo. Design a pressure$-$fed liquid rocket engine to achieve this mission.You will need to consider several aspects and possibly iterations. Go through the design process, report your design, and discuss the thought process used along the way. Submit a write up $($an actual report, not bullet points$)$ with all numbers, equations, calculations, figures$/$tables$,$ etc. Treat this submission as a final design to a client$/$boss$\mathrm{.}1.$ Choose a mission $($not necessarily to ISS in LEO, but maybe other space stations$)$ and calculate your V$.$ This is open ended, please state your assumptions$\mathrm{.}2.$ Choose a propellant. You will need to calculate various quantities from chemical equilibrium $($e$.$g$.,$ combustion temperature, c$*,$ MW$,$ etc.$).$ You will also need to decide the propellant mass ratio $($i$.$e$.,$ stoichiometry$)\mathrm{.}3.$ Figure out chamber pressure for your design$\mathrm{.}4.$ Calculate a nozzle area ratio based upon your target expansion conditions. Which geometry will you use?$5.$ Find your overall mass flow rate and the mass flow rates of each propellant. The mass flow rates may be steady, or you may choose to throttle the rocket if youd like$\mathrm{.}6.$ Finish sizing the nozzle $($e$.$g$.,$ throat area$),$ choose an L$*$ to find a chamber length$\mathrm{.}7.$ Size your tanks appropriately$\mathrm{.}8.$ Discuss aspects of the injectors and heat transfer in the rocket. Include any relevant calculations$\mathrm{.}9.$ Estimate the weight and size of the propulsion system. The rest of the mass will be the car and passenger$($s$)\mathrm{.}10.$ Justify all choices$/$decisions made$11.$ Include any code you write in an appendix.