Nuclear pulse detonation rocket engines (NPDR) are theoretical propulsion concepts that involve the use of nuclear detonations to create high-speed shockwaves that produce thrust.
For nuclear pulse detonation rocket engines, the challenge lies in defining parameters such as burn time and mass flow rate, as their operation involves discrete nuclear detonations rather than continuous combustion.
The theoretical concept involves using nuclear explosions to create a series of shockwaves in a propellant, creating thrust. As the detonations are not continuous, defining a traditional burn time becomes complex. Additionally, the mass flow rate is influenced by the ejected material from the nuclear explosions.
It is defined as the thrust generated per unit of propellant expended and is expressed in seconds.
where,
- is the specific impulse of the rocket engine (in seconds, s)
- F is the Thrust Produced
- ṁ is the mass flow rate of propellant in KG/Sec
- g0 is the acceleration due to gravity