B.E-B.E Aeronautical Engineering Rockets and Missiles(Sathyabama University, Chennai, Tamil Nadu-2010)
Friday, 23 August 2013 01:42Duraimani
(Established under section 3 of UGC Act,1956)
Course & Branch :B.E - AERO
Title of the Paper :Rockets and Missiles Max. Marks :80
Sub. Code :526702/626702 Time : 3 Hours
Date :02/03/2010 Session :AN
PART - A (10 x 2 = 20)
Answer ALL the Questions
1. State important injector design consideration in liquid propellant.
2. Define geysering effect.
3. What is propellant slosh?
4. What is boat tailing in missile?
5. Differentiate between Aero plane Vs missile - aerodynamics
6. Define culmination - altitude
7. What do you mean by SITVC?
8. Why do we need Jet control of Rocket?
9. What is Growth factor?
10. Define Multi stage Rocket.
PART – B (5 x 12 = 60)
Answer All the Questions
11. List the various basic design considerations of solid rocket igniters. With a neat sketch explain briefly any one type of Igniter.
(or)
12. Explain the major design consideration for the combustion chamber of the liquid propellant rockets.
13. State the importance of airframe components of a super sonic missile and explain their functions with a neat sketch.
(or)
14. With a neat sketch differentiate the body up Wash Vs down Wash in missile aerodynamics.
15. Derive an expression for burn out altitude and culmination altitude of a rocket motion in vertical trajectory (Homogenous Gravitational field)
(or)
16. (a) Derive an expression for burnout range at constant thrust.
(b) Calculate the culmination range and altitude reached by a rocket after burnout with the following data
Isp=278 sec. Thrust / WT = 1.48, mass ratio=5.2, pitch angle 41.2. Assume rocket is tracing an inclined trajectory with constant pitch angle [No Aerodynamic force]. Assume Thrust is constant.
17. (a) Derive an expression for optimization of multistage rocket / vehicle
(b) A two stage rocket has the following masses
I stage –Propellant mass = 1, 20,000 kg, Dry mass-9000 kg
II stage –Propellant mass = 30,000 kg, Dry mass-3000 kg
Payload mass=3,000 kg, ISP1=260 Sec, ISP2=320Sec
Find the rocket’s total increasing velocity.
(or)
18. Derive an expression for separation velocity (DV) between two stage helical compression spring.
19. Write short notes on
(a) Aerodynamics heating,
(b) Thermal shock,
(c) Ceramic materials
(d) Effect of space environment.
(or)
20. “Materials for different parts of rocket and missile” – Explain briefly with appropriate sketches.
| Earning: ₹ 3.10/- |
