1. The problem statement, all variables and given/known data A 20,000 kg rocket exhausts gasses at a constant 700 kg/sec at 300 ms^-1 Deduce the thrust applied to the rocket by its engines 2. Relevant equations The only equation I know is a= T- mg/m Where T= thrust a=acceleration m=mass 3. The attempt at a solution I don't know any other formulas and I can't use the one above because I don't have the acceleration Please help??