Rocket Propulsion Online Test | Quiz

1. Find the altitude of a satellite in a circular orbit around earth with a velocity of 7000 m/s.

899.5 km

2134.3 km

9053.1 km

1751.6 km

Question 1 of 50

2. For the application of pure torques in three directions, it requires ______ thrusters.

Question 2 of 50

3. The complexity of the control elements of the engine systems depend mostly on _________

mission

trajectory

launching site

capital

Question 3 of 50

4. ____________ are used for preventing the propellant flow back into the tanks and avoiding inadvertent mixing of propellants in the flow passage.

Drainage valves

Check valves

Isolation valves

Filters

Question 4 of 50

5. Strap-on booster stages are an example of ______ staging.

parallel

partial

tandem

piggyback

Question 5 of 50

6. Petroleum fuels form ________ radiating flames.

yellow-white

blue-green

orange-yellow

orange-red

Question 6 of 50

7. 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.

16.73 kg/s

15.33 kg/s

12.94 kg/s

19.67 kg/s

Question 7 of 50

8. Which form of energy is most useful for propulsion?

The electrical energy of the rocket control system

The chemical energy of combustion of propellants

The potential energy of the rocket at some altitude

The kinetic energy of ejected matter

Question 8 of 50

9. Determine the velocity correction factor (ζ_v) if the energy conversion efficiency is 0.94.

0.85

0.99

0.97

0.92

Question 9 of 50

10. For increased operating chamber pressure, the length of the combustion chamber ________ and the nozzle throat area _________ if the diameter of the combustion chamber (assume the shape to be cylindrical) is fixed and the thrust remains constant.

increases; decreases

decreases; increases

decreases; decreases

increases; increases

Question 10 of 50

11. Military missiles generally use ___________ rocket engines.

solar

chemical

nuclear

ion-electric

Question 11 of 50

12. Determine the chamber pressure for a rocket engine if the thrust coefficient is 1.8, the throat area is 0.2 m² and the total thrust is 20000 N.

67.98 kPa

55.56 kPa

45.67 kPa

61.33 kPa

Question 12 of 50

13. The volume of the combustion chamber is selected on the basis of which of these factors?

Mixing, evaporation and complete combustion of the propellants

Mixing and complete combustion of the propellants, but not its evaporation

Mixing and evaporation but not the complete combustion of the propellants

Evaporation and complete combustion of the propellants, but not mixing

Question 13 of 50

14. ___________ is a commonly used liquid oxidizer.

OF₂

H₂O₂

ClF₃

ClF₅

Question 14 of 50

15. __________ is that part of a launch vehicle that carries the payload.

Spacecraft

Control and guidance system

Sustainer stage

Booster stage

Question 15 of 50

16. What will happen when the thrust line doesn’t intersect the center of mass of a flying vehicle?

The vehicle experiences a centripetal acceleration

The vehicle drops in altitude

The vehicle trajectory becomes zigzag

The vehicle tries to rotate in flight

Question 16 of 50

17. A shorter rocket length will help in _________

lighter vehicle structure

more vehicle structural mass

greater vehicle mass ratio

greater complexity of the vehicle design

Question 17 of 50

18. Find the stagnation enthalpy of a calorically perfect gas having a flow velocity of 94 m/s and static temperature of 315 K. (C_p=1005 J/kg/K)

321 kJ/kg

234 kJ/kg

543 kJ/kg

456 kJ/kg

Question 18 of 50

19. Transverse mode of high-frequency instability propagation can be broken into ___________

longitudinal and radial modes

longitudinal and tangential modes

tangential and radial modes

radial, tangential and longitudinal modes

Question 19 of 50

20. How does the divergence angle vary along a bell-shaped nozzle?

Remains constant for a while and then decreases

Remains constant for a while and then increases

Sharply increases, then decrease

Sharply decreases, then increase

Question 20 of 50

21. Which of the following variables is not useful in the determination of rocket effective exhaust velocity?

Exit area

Mass flow rate

Rocket velocity

Exhaust velocity

Question 21 of 50

22. What is ullage?

The ratio of the volume of the propellant to that of the extra gas after 50% of the propellant has been consumed

The volume of propellant stored inside a tank neglecting its empty volume

The extra volume of gas above the propellant in a tank

The ratio of the volume of extra gas to that of the propellant after 50% of the propellant has been consumed

Question 22 of 50

23. What is the typical amount of propellant (in percentage) used for a spacecraft propulsion system with a pressurized monopropellant feed system for contingency?

2-10% of the total load

70-90% of the total load

0.5-2% of the total load

5-15% of the total load

Question 23 of 50

24. If the pressure rise ΔP across a pump is half the discharge pressure, then which of the following relates the suction pressure P_s to discharge pressure p_d?

P_s = 2 x P_d

2 x P_s = P_d

P_s = p_d

P_s = 4 x P_d

Question 24 of 50

25. Use of stainless steel thruster helps in _________

elimination of reaction between propellants and thrusters

increase in specific impulse

reduction of total power consumption

providing better orbital correction

Question 25 of 50

26. The decomposition of solid propellants to reaction mixture is a(n) ______________ chemical reaction.

irreversible

stoichiometric

ideal

reversible

Question 26 of 50

27. __________ are not liquid oxidizers.

Borohydrides

Fluorinated hydrocarbons

Nitrogen-fluorine formulations

Oxygen-fluorine compounds

Question 27 of 50

28. For an asymmetric nozzle section of diameter 12 cm, determine the average value of flow velocity if the velocity distribution is of the form v₂ = (2r – 3r²) x 10⁴ m/s, where r denotes the radial location in the cross-section plane.

765.4 m/s

1104.4 m/s

404 m/s

891.4 m/s

Question 28 of 50

29. _____ largely determines the numerical heat transfer rate and __________ largely determines the value of wall temperatures.

Gas film coefficient; liquid film coefficient

Thermal conductivity; liquid film coefficient

Gas film coefficient; thermal conductivity

Liquid film coefficient; gas film coefficient

Question 29 of 50

30. Which of the following comes under the category of operational factors in a propellant budget?

Filling more propellant than needed into a tank

Variation in tank volume

Attempting a complex maneuver

Pressurizing cryogenic propellant tanks

Question 30 of 50

31. What is the way of production of energy in a chemical rocket?

Ionization of propellants

Combustion of propellants

Atomization of propellants

Expulsion of propellants

Question 31 of 50

32. The form drag depends on ___________

aeroelastic stresses

aerodynamic shape of the body

solid structures far downstream

solid structures far upstream

Question 32 of 50

33. Which of the following statements is correct?

RCS can operate both simultaneously with and separate from OMS.

Both RCS and OMS both cannot operate together when one of them is under operation

RCS operates separately from OMS

RCS operates only simultaneously with OMS

Question 33 of 50

34. Energy release efficiency is also called as ___________

isentropic efficiency

polytropic efficiency

combustion efficiency

propulsive efficiency

Question 34 of 50

35. Heat generation in the first zone of the atomization region is relatively low because of ________

vaporization causing a cooling effect

liquids and gases are relatively hot

vaporization causing fuel-rich and fuel-lean regions

low flow velocity in the injector zone

Question 35 of 50

36. What is the loss of velocity increment experienced by a rocket as a result of drag in the atmosphere?

35-40%

5-10%

25-30%

15-20%

Question 36 of 50

37. Assertion: Oxygen addition in the control flow gases of solid rocket engine will result in a higher characteristic velocity of the exit jet.
Reason: Because of secondary combustion, stagnation temperature and pressure increase. Higher stagnation temperature results in exhaust jet characteristic velocity.

Both assertion and reason are correct

The assertion is wrong but the reason is correct

Both assertion and reason are wrong

The assertion is correct but the reason is wrong

Question 37 of 50

38. If C denotes effective exhaust velocity and Isp is specific impulse, then which of them is a better performance parameter?

Both of them are equivalent

Both of them are equal

Isp

Question 38 of 50

39. low-frequency combustion instability is called ________

squealing

screaming

chugging

buzzing

Question 39 of 50

40. Which of the following is the mixing layer of a nozzle core flow?

Viscous inner core flow

Inviscid inner core flow

Inviscid outer core flow

Viscous outer core flow

Question 40 of 50

41. Which of the following is not a recommended source for arriving at a tentative decision about the engine to be made?

Customer preferences

Past experiences

Full-fledged simulations

Mission requirements

Question 41 of 50

42. In which of the following modes of analysis does the temperature, velocity or pressure at any normal cross-section of an axisymmetric nozzle remain to be the same?

Three dimensional

Two dimensional

N-dimensional, where N can be 1,2,3,...

One dimensional

Question 42 of 50

43. A gas tank discharges faster if it is thermally isolated than if it is kept isothermal.

True

False

Question 43 of 50

44. Acoustically stimulated variations in droplet mixing and/or vaporization can cause ___________

spinning wave

traveling wave

screeching

pogo

Question 44 of 50

45. Which of the following statements is correct for an ideal rocket?

All kinds of frictional effects are not present, but the boundary layer cannot be neglected

Propellant flow is steady but constant

All discontinuities are not present, but shock waves are allowable

The expansion of the working fluid is steady, but need not be uniform

Question 45 of 50

46. 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?

33 kg/s

3 kg/s

53 kg/s

48 kg/s

Question 46 of 50

47. The quantity h_gD/k, where h_g is the gas film coefficient, D is the diameter of the chamber and k denotes the gas conductivity is __________

Prandtl number

Bartz number

Nusselt number

Froude number

Question 47 of 50

48. Which of the following is not a unit of gas constant?

m³atm/(K.mol)

kcal/(K.mol)

amu.m²s²/K

J/(mol.K)

Question 48 of 50

49. Which of the following is the correct expression for energy radiated by a body (Assume ε to be emissivity, A to be surface area, T to be temperature, f to be geometric factor)

E = fεσAT²

E = fεσAT⁴

E = (1/f)εσAT⁴

E = (1/f)εσAT²

Question 49 of 50

50. For a constant thrust of 6000 N, find the total impulse for the burning time of 3s.

0 Ns

18000 Ns

36000 Ns

9000 Ns

Question 50 of 50

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Total Questions: 25, Total Time: 30 min, Correct Answer: 2 points, Wrong Answer: -1 point

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Rocket Propulsion Internship Test

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Total Questions: 50, Total Time: 1 hour, Correct Answer: 2 points, Wrong Answer: -1 point

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