Propellant delivery ratio for altitude change

In Figure 5.9 the ratio of the total mass units of propellant (launcher and OMV) required per unit mass of the satellite is presented for the four space propulsion systems and the four launcher propulsion systems, namely those in Table 5.9.

Figure 5.9 shows the dramatic reduction in the total propellant mass (launcher and OMV) required per unit mass of the satellite, for all of the OMV propulsion systems, by advancing the performance of the launcher propulsion system. By incorporating a LACE system into an existing hydrogen/oxygen rocket the propel-lant required to deliver 1 mass unit of propellant to LEO is reduced by 56%. Proceeding to a Mach 12 ram/scramjet produces another 50% reduction in the required propellant to deliver 1 mass unit of propellant to LEO. So instead of the 190.5 mass units of propellant required, LACE reduces that number to 83.1 and a Mach 12 ram/scramjet reduces that to 41.8 propellant mass units required to deliver

0 0

Post a comment