You are an expert in writing code in many different languages. Your goal is to perform code completion for the following code, keeping in mind the rest of the code and the file meta data.
    Metadata details:
    filename: hohmann.m
    path of file: ./repos/Orbital_Mechanics
    
    the code of the file until where you have to start completion: function hohmann(Ria,Rip,Rfa,Rfp,m, isp)
    %% Calculates the delta-v to Hohmann transfer from orbit 1 to 2

    
function hohmann(Ria,Rip,Rfa,Rfp,m, isp)
    %% Calculates the delta-v to Hohmann transfer from orbit 1 to 2
    %
    % Jeremy Penn
    % 23/10/2017
    %
    % Revision: 23/10/2017
    %
    % function hohmann(Ria,Rip,Rfa,Rfp)
    %
    % Purpose: This function calculates the delta-v necessary to Hohmann
    %          transfer from orbit 1 to 2. Additionally, it calculates the fuel
    %          usage.
    %
    % Input:  o Ria   - The altitude of the apoapis of the initial orbit [km]
    %         o Rip   - The altitude of the periapis of the initial orbit [km]
    %         o Rfa   - The altitude of the apoapis of the final orbit [km]
    %         o Rfp   - The altitude of the perigee of the final orbit [km]
    %         o m     - The mass of the spacecraft before 1st manuveur [kg]
    %         o isp   - The specific impulse of the engine [s]
    %
    
    clc;
    mu = 398600; %[km^3/s^2]
    g  = 9.807;  %[m/s^2]
    
    %% Cacluate altitude from center of the Earth
    Ria = Ria + 6378;
    Rip = Rip + 6378;
    Rfa = Rfa + 6378;
    Rfp = Rfp + 6378;
    
    %% Calculate the angular momenta
    h1 = sqrt(2*mu)*sqrt((Ria*Rip)/(Ria + Rip));
    h2 = sqrt(2*mu)*sqrt((Rfa*Rip)/(Rfa + Rip));
    h3 = sqrt(2*mu)*sqrt((Rfa*Rfp)/(Rfa + Rfp));
    
    %% Calculate the speed at each point
    va1 = h1 / Rip;
    va2 = h2 / Rip;
    va  = va2 - va1;
    va  = va*1000;   %convert to [m/s]
    
    vb2 = h2 / Rfa;
    vb3 = h3 / Rfa;
    vb  = vb3 - vb2;
    vb  = vb*1000;   %convert to [m/s]
    
    deltav = abs(va) + abs(vb);
    
    %% Calculate mass of propellant expend