You are a spacecraft integrator seeking to visually communicate the trade-space between delta-V capability and payload mass provision. For an ESPA class satellite with a total wet mass of 180.0 kg, create a plot that compares the amount of conferred Total AV vs. Payload Mass allocation (zero to max), as a function of the following prevailing propulsion types (specified Isp): cold Igas (75s), monoprop (220s), bi-prop (316s), and Hall Effect Thruster (1380s). The total space vehicle mass is defined as follows: MTotal = MSpacecraft + MPropellant + MPayload where the combined payload-propellant mass-fraction ([MPayload + MPropellant] / MSpacecraft) is 50.0%.