I have long been following SpaceX and I really like their KISS (Keep it simple, stupid) approach, especially if (as planned) they can make their first stages reusable. Now that I have heard of their BFR (Big F***ing rocket) I’m gone take a guess at what they have planned.<br /><br />There are two SpaceX rockets in development, the Falcon I and the Falcon V, both are LOX (liquid oxygen) and RP-1 (kerosene) propelled, helium pressurised, two stage rockets. There are also two SpaceX rocket engines the pressure fed second stage Kestrel and the turbo-pump Merlin.<br /><br /><b>Kestrel specification</b><br />Vacuum Thrust:7,500 lb<br />Vacuum Isp:325s<br /><br /><b>Merlin specification</b><br />Sea Level Thrust:71,500 lb<br />Vacuum Thrust:85,000 lb<br />Sea Level Isp:261<br />Vacuum Isp:310<br /><br />The Falcon I uses one Kestrel engine and one Merlin engine to put a payload into orbit while the Falcon V uses five Merlins as a first stage and another as a second stage to reach orbit.<br /><br />Now SpaceX has a large amount of reasoning as to why this architecture was decided upon and I am not about to disagree. However if the Falcon I can be made so cost effective and the architecture has the minimum risks from engine, stage separation and, to a much lesser degree, avionics failures then why not offer a single engine version of the Falcon V? <br /><br />Carrying on with the nomenclature of SpaceX I’ll call this engine Peregrine. So what is required of the Peregrine engine?<br /><br />To allow for an engine out capability on the Falcon V the Merlin has to be throttled back to 80% thrust, therefore, a single engine capable of replacing all five Merlins would have to have specifications roughly as below, in keeping with the SpaceX nomenclature I’ll call this the peregrine:<br /><br /><b>Peregrine specification</b><br />Sea Level Thrust: 286,000 lb<br />Vacuum Thrust: 340000 lb<br />Sea Level Isp:261<br />Vacuum Isp:310<br /><br />These two versions of the Falcon V should be able to service two marke