1. Explain in detail the safety criteria of a missile launch for parent aircraft.

2. Derive an expression for the time of climb of a missile. Explain the assumptions in detail.

3. Discuss the basic inputs for design of a solid propellant rocket.

4. A turbo jet engine travels at 216 m/s in air at 0·78 bar and -7.2°C. Air first enters the diffuser (of 0.78 bar) in which it is brought to rest relative to the unit and it is then compressed in a compressor through a pressure ratio of 5·8 and fed to a turbine at 110°C. The gases expand through the turbine and then through the nozzle to atmospheric pressure (0.78 bar). The efficiencies of diffuser, nozzle and compressor are each 90%. The efficiency of turbine is 80%. Pressure drop in combustion chamber is 0.168 bar.

Determine:

Air fuel ratio, and

Total thrust, if the inlet cross-section of diffuser is 0.12 m^2.

Assume calorific value of fuel as 44150 kJ/kg of fuel.

5. Describe the working of a Ram-Jet engine. Depict the various processes occurring in it on the h-s diagram.

6. Explain with a neat sketch all forces and moments acting on the two separating stages in a multi-stage rocket.

7. What is thermal protection system? Describe a thermal protection system based on heat dissipation.

8. Differentiate between any two of the following:

Mass loading and Volume loading concepts

Missile and Rocket

Homing command guidance and Beam rider guidance

9. Write short notes on any two of the following:

Flight Dispersion

Geysering

Solid Propellants