A photonic laser thruster, also known as a laser propulsion system, is a theoretical concept that involves using directed laser energy to propel a spacecraft. In such a system, a laser beam is used to transfer momentum to a spacecraft by reflecting off a reflective surface on the spacecraft.
For a photonic laser thruster, the thrust is generated by the transfer of momentum from the laser photons to the reflective surface on the spacecraft. The specific impulse depends on factors such as the power of the laser, the reflectivity of the spacecraft surface, and the efficiency of momentum transfer.
Accurate calculations for specific impulse in the context of a photonic laser thruster would require detailed knowledge of the laser system characteristics, reflective surface properties, and the resulting momentum transfer. These values are typically obtained through theoretical modeling, simulations, and potentially experimental tests.
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