The escape velocity from Earth’s surface is approximately:
A. 11.2 km/s
B. 7.9 km/s
C. 9.8 km/s
D. 5.0 km/s
(Answer: A)
Escape velocity is defined as the:
A. Minimum velocity an object needs to escape the gravitational influence of a celestial body
B. Maximum speed at which an object can remain in orbit
C. Velocity required to achieve a stable orbit around a celestial body
D. Speed needed to enter a celestial body’s atmosphere
(Answer: A)
The escape velocity from a planet depends on:
A. The planet’s mass and radius
B. The planet’s distance from the Sun
C. The planet’s atmospheric composition
D. The planet’s rotation speed
(Answer: A)
For a given celestial body, the escape velocity increases with:
A. Increasing mass
B. Increasing temperature
C. Increasing altitude
D. Increasing atmospheric pressure
(Answer: A)
The escape velocity from the Moon is approximately:
A. 2.4 km/s
B. 11.2 km/s
C. 7.9 km/s
D. 5.0 km/s
(Answer: A)
Orbital energy is the sum of:
A. Kinetic energy and gravitational potential energy
B. Kinetic energy and thermal energy
C. Gravitational potential energy and atmospheric pressure
D. Kinetic energy and electrical energy
(Answer: A)
In a stable orbit, the total orbital energy of a satellite is:
A. Negative
B. Zero
C. Positive
D. Constant
(Answer: A)
The orbital velocity of a satellite in a circular orbit is:
A. The speed required to maintain a stable orbit around the celestial body
B. The speed needed to escape the gravitational influence
C. The velocity needed to achieve re-entry
D. The speed required to reach the surface
(Answer: A)
The gravitational potential energy of an object in orbit is:
A. Negative
B. Positive
C. Zero
D. Constant
(Answer: A)
To escape Earth’s gravitational pull, an object must reach:
A. Escape velocity
B. Orbital velocity
C. Re-entry speed
D. Maximum velocity
(Answer: A)
The escape velocity of a celestial body is influenced by:
A. Its mass and radius
B. Its distance from other celestial bodies
C. Its atmospheric density
D. Its rotation period
(Answer: A)
In a circular orbit, the orbital energy is:
A. Constant and negative
B. Constant and positive
C. Increasing with time
D. Decreasing with time
(Answer: A)
The escape velocity from a planet with twice the mass of Earth and the same radius will be:
A. 2\sqrt{2} times the escape velocity from Earth
B. Twice the escape velocity from Earth
C. Half the escape velocity from Earth
D. The same as the escape velocity from Earth
(Answer: A)
The kinetic energy of a satellite in orbit is:
A. Positive and related to its velocity
B. Negative and related to its distance from the center of the celestial body
C. Zero
D. Equal to its gravitational potential energy
(Answer: A)
The escape velocity of a celestial body with the same mass as Earth but twice the radius will be:
A. 12\frac{1}{\sqrt{2}} times the escape velocity from Earth
B. Twice the escape velocity from Earth
C. The same as the escape velocity from Earth
D. 12\frac{1}{2} times the escape velocity from Earth
(Answer: A)
An object in a stable orbit around Earth has:
A. Negative total orbital energy
B. Positive total orbital energy
C. Zero total orbital energy
D. Increasing total orbital energy
(Answer: A)
Escape velocity does not depend on:
A. The mass of the object trying to escape
B. The mass of the celestial body
C. The radius of the celestial body
D. The distance from the center of the celestial body
(Answer: A)
The orbital velocity of a satellite in a low orbit is:
A. Higher than that of a satellite in a higher orbit
B. Lower than that of a satellite in a higher orbit
C. The same as that of a satellite in a higher orbit
D. Equal to escape velocity
(Answer: A)
To achieve a stable orbit, a satellite must have:
A. A velocity that balances gravitational pull and centrifugal force
B. A velocity higher than escape velocity
C. A velocity equal to escape velocity
D. A zero velocity
(Answer: A)
The total energy of an object in orbit is:
A. The sum of its kinetic and potential energies
B. The product of its mass and velocity
C. The difference between its kinetic and potential energies
D. Constant and positive
(Answer: A)
If a satellite’s orbital energy becomes less negative, it:
A. Moves to a higher orbit
B. Moves to a lower orbit
C. Achieves escape velocity
D. Re-enters Earth’s atmosphere
(Answer: A)
Escape velocity is independent of:
A. The mass of the object
B. The mass of the celestial body
C. The radius of the celestial body
D. The gravitational constant
(Answer: A)
The relationship between escape velocity and orbital velocity in a circular orbit is:
A. Escape velocity is 2\sqrt{2} times the orbital velocity
B. Escape velocity is half the orbital velocity
C. Escape velocity is equal to the orbital velocity
D. Escape velocity is twice the orbital velocity
(Answer: A)
The gravitational potential energy of a satellite in orbit is:
A. Negative and proportional to its distance from the center of the celestial body
B. Positive and proportional to its distance from the center of the celestial body
C. Zero
D. Constant and independent of distance
(Answer: A)
To escape from a celestial body’s gravitational influence, a spacecraft must reach:
A. Escape velocity
B. Orbital velocity
C. Re-entry speed
D. Maximum speed
(Answer: A)
In orbit, the total mechanical energy of a satellite is:
A. The sum of its kinetic and gravitational potential energies
B. The difference between its kinetic and gravitational potential energies
C. The product of its mass and velocity
D. The gravitational force multiplied by its distance from the center of the celestial body
(Answer: A)
The kinetic energy of a satellite in orbit is:
A. Positive and proportional to the square of its velocity
B. Negative and proportional to its distance from the center of the celestial body
C. Zero
D. Equal to its gravitational potential energy
(Answer: A)
The orbital energy of a satellite is typically:
A. Negative and constant
B. Positive and variable
C. Zero
D. Increasing with time
(Answer: A)
For a satellite in a stable orbit, increasing altitude will:
A. Decrease orbital velocity and total orbital energy
B. Increase orbital velocity
C. Have no effect on orbital velocity
D. Increase total orbital energy
(Answer: A)
The escape velocity from a celestial body is proportional to:
A. The square root of its mass divided by its radius
B. The mass of the object
C. The radius of the object
D. The square of the gravitational constant
(Answer: A)
In space, a spacecraft must achieve:
A. Escape velocity to leave the gravitational influence of a celestial body
B. Orbital velocity to remain in a stable orbit
C. Re-entry speed to return to Earth
D. Maximum velocity to avoid other celestial bodies
(Answer: A)
The escape velocity of a celestial body decreases with:
A. Increasing radius
B. Increasing mass
C. Increasing gravitational constant
D. Decreasing radius
(Answer: A)
To increase orbital energy, a spacecraft must:
A. Perform a propulsion burn to increase velocity
B. Decrease its speed
C. Change its altitude without adjusting velocity
D. Maintain a constant velocity
(Answer: A)
The relationship between orbital velocity and escape velocity is:
A. Orbital velocity is less than escape velocity
B. Orbital velocity is equal to escape velocity
C. Orbital velocity is greater than escape velocity
D. Orbital velocity varies with escape velocity
(Answer: A)
The escape velocity for a celestial body with a smaller radius but the same mass as Earth will be:
A. Higher than the escape velocity from Earth
B. The same as the escape velocity from Earth
C. Lower than the escape velocity from Earth
D. Zero
(Answer: A)
In orbital mechanics, “specific orbital energy” is:
A. The total energy per unit mass
B. The total energy multiplied by the mass
C. The kinetic energy divided by the mass
D. The potential energy per unit volume
(Answer: A)
A satellite in a higher orbit has:
A. Lower kinetic energy and lower total energy compared to one in a lower orbit
B. Higher kinetic energy and higher total energy compared to one in a lower orbit
C. The same kinetic energy and total energy as one in a lower orbit
D. Zero kinetic energy
(Answer: A)
To escape from a celestial body with a given mass and radius, an object’s velocity must be:
A. Equal to the escape velocity
B. Less than the escape velocity
C. Greater than the orbital velocity
D. Zero
(Answer: A)
The escape velocity of a celestial body with a greater mass and greater radius is:
A. Higher than that of a smaller mass and radius celestial body
B. Lower than that of a smaller mass and radius celestial body
C. The same as that of a smaller mass and radius celestial body
D. Zero
(Answer: A)
The total mechanical energy of a satellite in a stable orbit is:
A. Negative
B. Positive
C. Zero
D. Variable
(Answer: A)
In an elliptical orbit, the total orbital energy:
A. Remains constant
B. Increases as the satellite approaches the celestial body
C. Decreases as the satellite moves away from the celestial body
D. Is variable
(Answer: A)
To achieve escape velocity from Earth’s surface, a spacecraft must overcome:
A. Earth’s gravitational pull
B. Atmospheric drag
C. Orbital velocity
D. The spacecraft’s own weight
(Answer: A)
The total energy of a satellite in a circular orbit is:
A. Negative and constant
B. Positive and variable
C. Zero
D. Constant and positive
(Answer: A)
The kinetic energy required for escape from a celestial body is:
A. Equal to the gravitational potential energy at the surface
B. Greater than the gravitational potential energy at the surface
C. Less than the gravitational potential energy at the surface
D. Independent of the gravitational potential energy
(Answer: A)
The escape velocity formula assumes that:
A. The object is launched from the surface of the celestial body
B. The object is already in orbit
C. Atmospheric drag is negligible
D. The celestial body’s rotation affects the calculation
(Answer: A)
The escape velocity from a celestial body with half the mass of Earth and the same radius is:
A. 12\frac{1}{\sqrt{2}} times the escape velocity from Earth
B. 2\sqrt{2} times the escape velocity from Earth
C. Half the escape velocity from Earth
D. Twice the escape velocity from Earth
(Answer: A)
In space missions, the term “orbital energy” refers to:
A. The total energy of a spacecraft in orbit
B. The energy needed for launch
C. The energy required to re-enter Earth’s atmosphere
D. The energy required to achieve escape velocity
(Answer: A)
A satellite in an elliptical orbit has:
A. Variable kinetic and potential energy throughout its orbit
B. Constant kinetic and potential energy
C. Constant total energy but variable kinetic and potential energy
D. Zero total energy
(Answer: A)
The escape velocity of a celestial body with the same mass as Earth but four times the radius will be:
A. 12\frac{1}{2} times the escape velocity from Earth
B. 12\frac{1}{\sqrt{2}} times the escape velocity from Earth
C. Twice the escape velocity from Earth
D. The same as the escape velocity from Earth
(Answer: A)