The invention discloses a premixed
carbon dioxide pneumatic
laser driven by the
combustion of a continuous rotary
detonation rocket. The premixed
carbon dioxide pneumatic
laser comprises a continuousrotary
detonation combustion device, a transition section, a CO2 pneumatic
laser generation device and an exhaust section. The continuous rotary
detonation combustion device is used for generating a high-temperature and high-pressure
fuel gas heat source as a
total energy source of downstream output laser and comprises a shell, a central cone, a rotary detonation
combustion chamber and an injection panel, the transition section enables the
fuel gas behind the combustion device to adapt to configuration changes, and enables the
fuel gas to stably flow to the front of an array spray
pipe with the total pressure loss as small as possible, the CO2 pneumatic laser generating device comprises the array spray
pipe and an
optical cavity, and the exhaust section enables a
product gas after light emitting to be rapidly exhausted to the outside. The continuous rotary detonation
rocket combustion device is adopted as a pumping source, so that the produced laser is high in efficiency, and the energy is saved. The premixed
carbon dioxide pneumatic laser can be used on a
rocket or an aircraft boosted by a rocket, and not only can generate thrust, but also can generate laser without increasing theload, and can also be used as a high-power continuous intense
laser light source on the ground.