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TRA Advanced Study Guide - Technical Questions part 2

Authored by Dean Adalian

Science

12th Grade

NGSS covered

Used 7+ times

TRA Advanced Study Guide - Technical Questions part 2
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28 questions

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1.

MULTIPLE CHOICE QUESTION

30 sec • 1 pt

What is the oxidizer most commonly used in a commercial hybrid rocket motor?

N2O

N2O4

NO2

2.

MULTIPLE CHOICE QUESTION

30 sec • 1 pt

For a rocket with a much less than 10:1 “length to diameter” (L/D) ratio, such as spools and pyramids, what type of drag contributes significantly to stability and makes it possible to fly without much, if any, nose weight?

Nose drag

Base drag

Surface drag

Tags

NGSS.HS-PS2-1

3.

MULTIPLE CHOICE QUESTION

30 sec • 1 pt

When doing an air-start of an L class motor, which of the following would be considered the safest configuration?

A single computer driving a single initiator

Two computers each driving one initiator with a 0.5 second delay between firing the two initiators

Two computers each driving one initiator with no delay between them

Tags

NGSS.HS-ETS1-3

4.

MULTIPLE CHOICE QUESTION

30 sec • 1 pt

A rocket with a motor cluster consisting of a central composite motor and four black powder motors, using five identical igniters:

Will result in all motors starting about the same time

Will result in the composite motor starting first followed by the black powder motors

Will result in the black powder motors starting first followed by the central composite motor

5.

MULTIPLE CHOICE QUESTION

30 sec • 1 pt

What typically happens to a marginally stable rocket with a hybrid motor during the thrusting phase?

Nothing

The rocket may become more stable

The rocket may become less stable

6.

MULTIPLE CHOICE QUESTION

30 sec • 1 pt

In general terms, the specific impulse of a rocket motor is:

The total thrust force of a motor throughout its action time

The total impulse divided by a unit weight of propellant

Inversely related to the diameter and length of the propellant grain

7.

MULTIPLE CHOICE QUESTION

30 sec • 1 pt

In general terms, the total impulse of a rocket motor can be described as:

The product of the average motor thrust and burn time

The product of the propellant weight and burn time

The product of the propellant weight and the motor thrust

Tags

NGSS.HS-PS2-1

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