dangercomix07

import numpy as np
import matplotlib.pyplot as plt

m  = 4.00      # kg, chaser mass
u  = 0.01     # m/s, approach speed to brake from
F  = 0.010    # N, baseline nominal thrust
Tp = 0.100    # s, PWM time period
Tloss = 0.010  # s, time loss due to thruster ignition/termination (2*T_transient)
DeltaV_mission = 0.10  # m/s, total mission delta-V budget