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A tripropellant rocket is a rocket that uses three propellants, as opposed to the more common bipropellant rocket or monopropellant rocket designs, which use two or one fuels, respectively. Tripropellant rockets appear to offer fairly impressive gains for single stage to orbit designs, although to date no tripropellant rocket design has been developed to the point of testing that would prove the concept.
There are two principally different kinds of tripropellant rockets. One is a rocket engine which mixes three separate streams of propellants. In the 1960s, Rocketdyne fired an engine using a mixture of liquid lithium, gaseous hydrogen, and liquid fluorine to produce a specific impulse of 542 seconds, likely the highest measured such value for a chemical rocket motor. The other kind of tripropellant rocket is one that uses one oxidizer but two fuels, switching between the two in mid-flight. In this way the motor can combine the high thrust of a dense fuel like kerosene early in flight with the high specific impulse of a lighter fuel like liquid hydrogen (LH2) later in flight. The result is a single engine providing some of the benefits of staging.
Furthermore, injecting a small amount of liquid hydrogen into a Kerosene burning engine can yield significant specific impulse improvements without compromising propellant density. This was demonstrated by the RD-701 achieving a specific impulse of 415 seconds in vacuum(higher than the pure LH2/LOX RS-68), where a pure kerosene engine with a similar expansion ratio would achieve 330–340 seconds.
Although liquid hydrogen delivers the largest specific impulse of the plausible rocket fuels, it also requires huge structures to hold it due to its low density. These structures can weigh a lot, offsetting the light weight of the fuel itself to some degree, and also result in higher drag while in the atmosphere. While kerosene has lower specific impulse, its higher density results in smaller structures, which reduces stage mass, and furthermore reduces losses to atmospheric drag. In addition, kerosene-based engines generally provide higher thrust, which is important for takeoff, reducing gravity drag. So in general terms there is a "sweet spot" in altitude where one type of fuel becomes more practical than the other.
Traditional rocket designs use this sweet spot to their advantage via staging. For instance the Saturn Vs used a lower stage powered by RP-1 (kerosene) and upper stages powered by LH2. Some of the early Space Shuttle design efforts used similar designs, with one stage using kerosene into the upper atmosphere, where an LH2 powered upper stage would light and go on from there. The later Shuttle design is somewhat similar, although it used solid rockets for its lower stages.
Almost all of the cost of operating the Shuttle is for the payroll for the army of workers needed to refurbish the Shuttle after it has landed. The fuel used is orders of magnitude cheaper, and, if a single stage to orbit design SSTO avoided some of this refurbishment, costs would drop, although this could require more repairs. But in this case the staging solution is not available, by definition, so it becomes harder to use both fuels.
SSTO rockets could simply carry two sets of engines, but this would mean the spacecraft would be carrying one or the other set "turned off" for most of the flight. With light enough engines this might be reasonable, but an SSTO design requires a very high mass fraction and so has razor-thin margins for extra weight.
And thus the tripropellant engine. The engine is basically two engines in one, with a common engine core with the engine bell, combustion chamber and oxidizer pump, but two fuel pumps and feed lines. The engine is somewhat heavier and more complex than a single-fuel engine, but the complexity is generally a little less than 50% more than a single engine, hence less than two engines would be. Of course there are numerous practical reasons why this would be more complex.
At liftoff the engine typically burns both fuels, gradually changing the mixture over altitude in order to keep the exhaust plume "tuned" (a strategy similar in concept to the plug nozzle but using a normal bell), eventually switching entirely to LH2 once the kerosene is burned off. At that point the engine is largely a straight LH2/LOX engine, with an extra fuel pump hanging onto it.
The concept was first explored in the US by Robert Salkeld, who published the first study on the concept in Mixed-Mode Propulsion for the Space Shuttle, Astronautics & Aeronautics August 1971. He studied a number of designs using such engines, both ground based and a number that were air-launched from large jet aircraft. He concluded that tripropellant engines would produce gains of over 100% in payload fraction, reductions of over 65% in propellant volume and better than 20% in dry weight. A second design series studied the replacement of the Shuttles SRBs with tripropellant based boosters, in which case the engine almost halved the overall weight of the designs. His last full study was on the Orbital Rocket Airplane which used both tripropellant and (in some versions) a plug nozzle, resulting in a spaceship only slightly larger than a Lockheed SR-71, able to operate from traditional runways.
The only tripropellant engines built were in Russia. Kosberg and Glushko developed a number of experimental engines in the early 1990s for a SSTO spaceplane called MAKS, but both the engines and MAKS were later cancelled due to a lack of funding. Glushko's RD-701 was built and test fired, however, and although there were some problems, Energomash feels that the problems are entirely solvable and that the design does represent one way to reduce launch costs by about 10 times.
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