A single-stage weather sounding rocket has a takeoff mass of 1020 kg, a sea-level initial acceleration of 2.00 g0, carries 799 kg of useful propellant, has an average specific gravity of 1.20, a burn duration of 42 sec, a vehicle body shaped like a cylinder with an L/D ratio of 5.00 with a nose cone having a half angle of 12?. Assume the center of mass does not change during the flight. The vehicle tumbled (rotated in an uncontrolled manner) during the flight and failed to reach its objective. Subsequent evaluation of the design and assembly processes showed that the maximum possible thrust misalignment of the main thrust chamber was 1.05? with a maximum lateral off-set d of 1.85 mm. Assembly records show it was 0.7? and 1.1 mm for this vehicle. Since the propellant flow rate was essentially constant, the thrust at altitude cutoff was 16.0% larger than at takeoff. Determine the maximum torque applied by the main thrust chamber at start and at cutoff, without operating any auxiliary propulsion system. Then determine the approximate maximum angle through which the vehicle will rotate during powered flight, assuming no drag. Discuss the result.