STEAM-POWER
Rocket propulsion engine
Using pyrolitic process it would be possible to significantly improve for security and reliability of rocket propulsion engines, just using the water as fuel. To achieve this aim we would just need some relatively small quantity of magnesium based fuel or similar to initialize the burning process, achieving the temperature higher then 800 degrees of Celsius scale.
Standard liquid rocket engine, such as these used for driving the space shuttle could be slightly rearanged to easy match this aim.
On this purpose, we would need only one tank for water, since the oxidizer the Oxygen, as well as fuel the Hydrogen are already natural compressed within the molecules of water in 1:1500 of volume ratio. Since the burning temperature of the HHO gas amounts over 1000 degree of Celsius, the process just need to be initialized at the beginning to achieve the self-sustained pyrolitic propulsion.
Furthermore, since the result of combusting is water again, thus there are no negative impacts on the environmental surrounding. Continuing these lines of thoughts, we could even develop double staged rocket engine, using the steam-power jet-propulsion bundle engine, at the lower altitudes, the far the density of the surrounding air is high enough to can contribute in propulsion process. The water used for steam-air mixture driven jet-propulsion engine could be cycled, thus the total need for fuel could be significantly reduced. The far the air density at the higher altitudes is going to became insufficient to contribute to the propulsion, the water pyrolitic process could be initialized.
In addition, the gyroscopic effect build upon very fast rotating disks of the Tesla turbine, which are rotating perpendicular to each another, could contribute to significantly stabilize the flight of the rocket. In doing this simple optimization, we could significantly improve for efficiency and lower the costs for propulsion, thus improve for the space traffic.
It could be estimated that the suggested system will reduce the quantity of fuel to one quarter in both volume and weight for the same final result compared to the actually used liquid rocket engines.
In doing so the flying teapott could be also easily implemented to significantly improve for the rocket technology.
