MCQOPTIONS
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MCQOPTIONS
This section includes 10 Mcqs, each offering curated multiple-choice questions to sharpen your Rocket Propulsion knowledge and support exam preparation. Choose a topic below to get started.
| 1. |
Which of the following cannot be the nature of the actuation system for thrust vector control? |
| A. | Mechanical |
| B. | Fluidic |
| C. | Either mechanical or fluidic |
| D. | Neither mechanical and fluidic |
| Answer» E. | |
| 2. |
For a conical nozzle of throat diameter 0.007 m, exit cross-section diameter 0.02 m, and divergent section length of 0.038 m, determine the nozzle semi-divergence angle. |
| A. | 10.5° |
| B. | 12.6° |
| C. | 7.3° |
| D. | 9.7° |
| Answer» E. | |
| 3. |
Which of the following thrust modulation techniques uses a normal shock to reduce total thrust? |
| A. | Throat Shifting Thrust Modulation |
| B. | Scarfed Nozzle Thrust Modulation |
| C. | Shock Thrust Modulation |
| D. | Fluidic Thrust modulation |
| Answer» D. Fluidic Thrust modulation | |
| 4. |
Which of the following thrust modulation technique makes use of symmetric injection for jet area control? |
| A. | Throat Shifting Thrust Modulation |
| B. | Shock Thrust Modulation |
| C. | Shock Vectoring Control |
| D. | Scarfed Nozzle Thrust Modulation |
| Answer» B. Shock Thrust Modulation | |
| 5. |
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. |
| A. | Both assertion and reason are correct |
| B. | The assertion is correct but the reason is wrong |
| C. | The assertion is wrong but the reason is correct |
| D. | Both assertion and reason are wrong |
| Answer» B. The assertion is correct but the reason is wrong | |
| 6. |
Which of the following is not a way for thrust modulation? |
| A. | Controlling the propellant flow rate to the injector |
| B. | Controlling injection orifices |
| C. | Varying chamber pressure |
| D. | Deploying control surfaces like fins |
| Answer» E. | |
| 7. |
Attitude and maneuvering corrections require impulses with _________ pulse width. |
| A. | extremely short |
| B. | extremely large |
| C. | moderately short |
| D. | moderately large |
| Answer» B. extremely large | |
| 8. |
Thrust can be varied by changing the throat area along with throttling the flow. |
| A. | True |
| B. | False |
| Answer» B. False | |
| 9. |
A two-to-one thrust decrease can be achieved using _________ in a liquid propellant rocket engine. |
| A. | throttle valves |
| B. | gas pressure feed system |
| C. | spark ignitor |
| D. | using BATES grain |
| Answer» B. gas pressure feed system | |
| 10. |
Thrust is a weak function of ______________ |
| A. | throat area |
| B. | chamber pressure |
| C. | mass flow rate |
| D. | thrust coefficient |
| Answer» E. | |