Gaseous oxygen propulsion system with chemical oxygen generation

A method for providing oxygen for a rocket propulsion system comprising:

• providing a solid phase composition comprising a solid phase metal oxide and a solid phase compound, wherein said solid phase compound is selected from the group consisting of alkali metal chlorates, alkali metal perchlorates or alkali metal peroxides and mixtures thereof and a mole ratio of said solid phase compound to said solid phase metal oxide is in a range of 3:1 to 6:1;
• heating said solid phase composition and generating gaseous oxygen at a pressure of greater than or equal to 250 psia over a time period of 2.0 minutes or greater and introducing said gaseous oxygen to an accumulator of said rocket propulsion system.