Final answer:
The maximum thrust of the A/THR system is determined by the exhaust velocity, rate of mass ejection, and the mass of the rocket.
Step-by-step explanation:
The maximum thrust that the A/THR system can command is determined by three major factors. The first factor is the exhaust velocity of the gases relative to the rocket, Ve. The greater the Ve, the greater the acceleration. The practical limit for Ve is about 2.5 × 10³ m/s for conventional hot-gas propulsion systems.
The second factor is the rate at which mass is ejected from the rocket, which is represented by the factor Am/At in the equation. The faster the rocket burns its fuel, the greater its thrust, and therefore, the greater its acceleration.
The third factor is the mass of the rocket, m. The smaller the mass, the greater the acceleration. As the rocket's mass decreases during flight due to burning fuel, the acceleration increases continuously, reaching a maximum just before the fuel is exhausted.