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The PGA engine consists of a combustion chamber, a main
April 3, 2018 by Kenneth Newton 
The PGA engine consists of a combustion chamber, a main chamber and a main control chamber. Each chamber is filled with a special chamber that releases pressure from the main chamber to the combustion chamber. An oil pressure chamber is also used for the main chamber, with a different amount of pressure for different parts of the combustion chamber. This process is called "pump-in," and while it's not exactly a new invention, it's still a cool idea, said Brad Smith, director of the Center for Advanced Dynamics at Johns Hopkins University.
The PGA engine is a solid-state (SS) system that uses a mix of propellant and a solid-state (SSO) mixture to cool the combustion chamber. The SSO mixture contains a mixture of propellants and a liquid oxygen mixture, and the liquid oxygen mixture is a mixture of hydrogen and oxygen. According to the PGA website , the SSO mixture, called the liquid oxygen tank, is an SSO system that has a lower mass and lower pressure than a conventional SSO system that has a mass of just over 10 times more propellant.
According to the PGA website , the SSO system would have a mass of 0.04 grams.
According to the PGA website , the rocket would have a range of about 70 kilometers (40 miles), and would carry a payload of about 2,000 kilograms of payload, which is about the weight of a human hair.
The company has set its initial launch target of July 14, 2016, and it has yet to confirm if this is the intended goal.
A few more details about the launch are provided in the accompanying story.