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Rocket Propulsion Practice Test: Liquid Propellant Rocket Engine
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Liquid Propellant Rocket Engine topics include: Liquid propellants, gas pressure feed systems, propellant tanks, tank pressurization, turbopump feed systems and engine cycles, flow and pressure balance, rocket engines for manueuvering, orbit adjustments or attitude control, liquid propellant rocket engine feed systems and engine support structure. A liquid propellant rocket engine (LRE) is a rocket propulsion system that uses liquid propellants to burn. LREs are used in space vehicles and expandable and reusable launchers worldwide.  LREs use a bipropellant configuration, where the fuel and... Show more
Rocket Propulsion Practice Test: Liquid Propellant Rocket Engine
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25 Questions

1. In a turbopump, what are are the gear ratios for ao and af (for oxidizer pump and fuel pump respectively) if no gears are used?
2. Which component of the external tank of Space Shuttle served the main purpose of distributing thrust loads from SRBs?
3. If the total propellant flow rate is 24 kg/s and the mixture ratio is 2.3, determine the mass flow rate of the oxidizer.
4. Propellant tanks containing oxygen and nitrogen tetroxide can be pressurized using _________
5. Which of the following is not true about the pressurizing gas?
6. Which of the following materials of the propellant tank requires a thin inner liner of metal to avoid leakage?
7. Pump feed systems don’t require positive pressure in the tank.
8. Reaction control systems produce larger thrust than auxiliary propulsion systems.
9. Which of the following ways of thrust chamber cooling may use niobium metal?
10. _____ is used for separating liquids from the pressurizing gas.
11. Open cycles perform better than closed cycle in a turbopump feed type rocket engine.
12. Pressurizing gas cannot perform ___________
13. Which of the following statements is correct?
14. In turbopump feed systems, the pressurization of the propellants is done by ____________ and they are driven by ____________
15. In gas generator cycles, the turbine inlet gas is obtained from a portion of exhaust gases about to pass through the rocket nozzle.
16. If L represents torque, and the subscripts T, o, f, b denotes the turbopump, oxidizer pump, fuel pump and bearings respectively, then which of the following expressions is true when there are no gears in a particular turbopump?
17. If the gear ratio for fuel pump is thrice that of the oxidizer pump, the shaft speed of fuel pump is ____________ the oxidizer pump.
18. What is the total mass flow rate through the gas generator if the oxidizer flow through it is 15 kg/s and fuel flow is 18 kg/s?
19. Which of the following pressurization techniques involves combustion inside the propellant tank?
20. Determine the amount of propellant trapped in pipe, fittings, and valve corners and lost by other means, if the initial mass of the propellant was M and it had an expulsion efficiency of 97%.
21. For the application of pure torques in three directions, it requires ______ thrusters.
22. If the pressure rise ΔP across a pump is half the discharge pressure, then which of the following relates the suction pressure Ps to discharge pressure pd?
23. At what temperature are the liquid oxygen and the liquid hydrogen kept in their storage tanks of the cryogenic rocket engine?
24. What is range of side force required by a ballistic missile during its final closing maneuver just before nearing in on the target?
25. Tank pressure for the pressure feed system is between ___________ and __________

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