When solving variable mass problems with rockets ejecting fuel/ gas, can I calculate the thrust by considering the force exerted on the exhaust since it is equal and opposite?
i.e. dp/dt=(m)dv/dt + (v)dm/dt
where dm/dt = mass of exhaust ejected at speed v (cancelling first term since speed of ejection constant) ?
many thanks, sorry I don't have my specific example atm