Satellite launch vehicles are designed to:
A. Propel satellites into their desired orbits around Earth
B. Provide a stable orbit for satellites
C. Maintain satellite velocity in orbit
D. Re-enter and land satellites on Earth
(Answer: A)
The primary purpose of a satellite launch vehicle is to:
A. Overcome Earth’s gravity and place a satellite into orbit
B. Ensure the satellite remains in geostationary orbit
C. Slow down the satellite to maintain orbit
D. Adjust the satellite’s orientation in space
(Answer: A)
Orbital decay occurs due to:
A. The gradual loss of altitude due to atmospheric drag and gravitational perturbations
B. The increase in satellite velocity
C. The stability of the satellite’s orbit
D. The constant speed of the satellite
(Answer: A)
To counteract orbital decay, satellites use:
A. Station-keeping maneuvers to adjust their position and altitude
B. Additional fuel to maintain their initial velocity
C. Gravity assists to change their trajectory
D. Magnetic fields to stabilize their orbit
(Answer: A)
Station-keeping involves:
A. Periodic adjustments to a satellite’s position to maintain its desired orbit
B. Increasing the satellite’s speed to escape Earth’s gravity
C. Re-entering the satellite into Earth’s atmosphere
D. Achieving a stable orbit around a central body
(Answer: A)
The primary force causing orbital decay in low Earth orbit is:
A. Atmospheric drag
B. Gravitational attraction from the central body
C. Solar radiation pressure
D. Magnetic fields
(Answer: A)
Satellites in geostationary orbit are:
A. Positioned directly above the equator, rotating with Earth’s rotation
B. Constantly moving relative to Earth’s surface
C. Orbiting Earth in a polar trajectory
D. Placed in low Earth orbit
(Answer: A)
The main advantage of a geostationary orbit is:
A. The satellite remains fixed relative to a point on Earth’s surface
B. The satellite experiences no atmospheric drag
C. The orbit is highly elliptical
D. The satellite can easily change its orbital inclination
(Answer: A)
Orbital decay is accelerated by:
A. Increased atmospheric density at lower altitudes
B. Reduced gravitational forces
C. High orbital velocities
D. Stable satellite speeds
(Answer: A)
Station-keeping thrusters are used to:
A. Perform small adjustments to a satellite’s orbit and position
B. Increase the satellite’s speed
C. Decrease the satellite’s altitude
D. Stabilize the satellite’s orientation
(Answer: A)
The altitude of a satellite affects:
A. The rate of orbital decay due to atmospheric drag
B. The satellite’s velocity in orbit
C. The satellite’s fuel consumption
D. The satellite’s ability to perform gravity assists
(Answer: A)
Geostationary satellites are commonly used for:
A. Communication, weather monitoring, and broadcasting
B. Scientific research in polar regions
C. High-speed interplanetary travel
D. Low-altitude Earth observation
(Answer: A)
The key challenge in maintaining a satellite’s orbit is:
A. Compensating for orbital decay and perturbations
B. Increasing the satellite’s speed continuously
C. Reducing atmospheric drag
D. Achieving escape velocity
(Answer: A)
Station-keeping maneuvers are typically performed:
A. Using small thrusters to correct orbital position
B. By increasing the satellite’s mass
C. Through gravitational assists
D. By reducing the satellite’s velocity
(Answer: A)
Orbital decay in low Earth orbit is primarily due to:
A. Drag from the Earth’s atmosphere
B. Solar radiation pressure
C. Gravitational perturbations from other celestial bodies
D. Magnetic field interactions
(Answer: A)
The lifespan of a satellite in low Earth orbit is often limited by:
A. The rate of orbital decay due to atmospheric drag
B. The satellite’s fuel capacity
C. The satellite’s communication capabilities
D. The rate of gravitational pull from Earth
(Answer: A)
In a geostationary orbit, the satellite’s period is:
A. Equal to the rotational period of Earth
B. Half of Earth’s rotational period
C. Twice Earth’s rotational period
D. Independent of Earth’s rotation
(Answer: A)
To adjust for orbital decay, satellites use:
A. Propellant from onboard thrusters
B. Additional gravitational forces
C. Changes in atmospheric density
D. High-speed propulsion systems
(Answer: A)
The concept of “orbital maintenance” refers to:
A. Regular adjustments made to a satellite’s orbit to counteract decay and perturbations
B. Continuous propulsion to increase speed
C. Re-entering the satellite into Earth’s atmosphere
D. Stabilizing the satellite’s altitude without propulsion
(Answer: A)
The primary purpose of using station-keeping thrusters is to:
A. Maintain a satellite’s position and orbit accuracy
B. Increase the satellite’s velocity
C. Achieve a new orbital path
D. Decrease the satellite’s altitude
(Answer: A)
Orbital decay can be mitigated by:
A. Performing periodic station-keeping maneuvers
B. Increasing the satellite’s altitude continuously
C. Reducing the satellite’s speed in orbit
D. Avoiding atmospheric drag
(Answer: A)
Satellites in higher orbits experience:
A. Slower rates of orbital decay compared to those in low Earth orbit
B. Faster rates of decay due to increased atmospheric density
C. No atmospheric drag
D. Higher gravitational forces
(Answer: A)
The “life expectancy” of a satellite in geostationary orbit is:
A. Often limited by fuel for station-keeping
B. Determined by atmospheric drag
C. Dependent on the satellite’s speed
D. Influenced by gravitational perturbations
(Answer: A)
A satellite’s altitude affects:
A. The amount of atmospheric drag it experiences
B. The satellite’s communication range
C. The satellite’s fuel efficiency
D. The rate of gravitational pull
(Answer: A)
The primary reason for periodic station-keeping is:
A. To compensate for perturbations and maintain the satellite’s desired position
B. To increase the satellite’s speed
C. To reduce the satellite’s altitude
D. To adjust the satellite’s orientation
(Answer: A)
Orbital decay in satellites is primarily caused by:
A. Atmospheric drag and gravitational perturbations
B. The satellite’s propulsion system
C. Solar radiation pressure
D. Magnetic field interactions
(Answer: A)
Satellites in low Earth orbit (LEO) typically require:
A. More frequent station-keeping maneuvers due to higher atmospheric drag
B. Fewer maneuvers compared to geostationary satellites
C. Constant propulsion to maintain orbit
D. No station-keeping maneuvers
(Answer: A)
The “delta-v” budget for a satellite mission includes:
A. The total amount of velocity change available for maneuvers and orbit adjustments
B. The amount of fuel required for launch
C. The velocity needed for achieving geostationary orbit
D. The speed at which the satellite leaves Earth’s atmosphere
(Answer: A)
In orbital mechanics, “orbital perturbations” refer to:
A. Small changes in a satellite’s orbit due to gravitational influences and other forces
B. The constant velocity of the satellite in orbit
C. The satellite’s atmospheric drag
D. The propulsion system’s efficiency
(Answer: A)
Geostationary satellites are typically placed:
A. At an altitude of approximately 35,786 km above the equator
B. In low Earth orbit at altitudes below 2,000 km
C. In a polar orbit with varying altitudes
D. At random altitudes for diverse mission needs
(Answer: A)
The process of “de-orbiting” a satellite involves:
A. Reducing its altitude to eventually re-enter Earth’s atmosphere
B. Increasing its altitude to escape gravitational pull
C. Stabilizing its position in orbit
D. Maintaining its geostationary orbit
(Answer: A)
A satellite’s “orbital lifetime” is affected by:
A. The balance between atmospheric drag and propulsion systems
B. The satellite’s communication range
C. The altitude of the satellite’s orbit
D. The satellite’s fuel efficiency
(Answer: A)
The primary function of the onboard propulsion system in a satellite is:
A. To perform maneuvers for station-keeping and orbit adjustments
B. To increase the satellite’s speed continuously
C. To stabilize the satellite’s orientation
D. To achieve escape velocity
(Answer: A)
The concept of “orbital insertion” refers to:
A. Placing a satellite into its intended orbit after launch
B. Adjusting the satellite’s position within its existing orbit
C. Increasing the satellite’s speed for interplanetary travel
D. Stabilizing the satellite’s orientation in space
(Answer: A)
The “re-entry” of a satellite is:
A. The process of returning a satellite from orbit to Earth’s atmosphere
B. The maneuver to enter a stable orbit
C. The adjustment to maintain a geostationary orbit
D. The stabilization of the satellite’s altitude
(Answer: A)
The use of “station-keeping” maneuvers is crucial for satellites to:
A. Maintain their precise positions and compensate for orbital decay
B. Increase their speed for interplanetary travel
C. Reduce atmospheric drag
D. Stabilize their orientation in space
(Answer: A)
The effect of “solar radiation pressure” on a satellite is:
A. A small perturbation that can influence the satellite’s orbit over time
B. A significant force that causes rapid orbital decay
C. A factor that stabilizes the satellite’s orbit
D. A method to increase the satellite’s velocity
(Answer: A)
“Orbital precession” refers to:
A. The gradual change in the orientation of a satellite’s orbit over time
B. The adjustment of satellite velocity for station-keeping
C. The decrease in satellite altitude due to atmospheric drag
D. The increase in satellite speed due to propulsion
(Answer: A)
The primary use of “thrusters” in satellite operations is to:
A. Perform precise adjustments to the satellite’s orbit and position
B. Increase the satellite’s speed for escape velocity
C. Decrease atmospheric drag
D. Stabilize the satellite’s orientation without affecting its orbit
(Answer: A)
A satellite’s “ground track” is:
A. The path that the satellite traces on Earth’s surface as it orbits
B. The satellite’s trajectory through space
C. The path of atmospheric drag around the satellite
D. The satellite’s speed in orbit
(Answer: A)
“Attitude control” in satellite operations refers to:
A. Adjusting the satellite’s orientation to maintain its desired position and function
B. Increasing the satellite’s speed in orbit
C. Performing maneuvers for orbital decay
D. Stabilizing the satellite’s ground track
(Answer: A)
The “altitude” of a satellite determines:
A. The level of atmospheric drag and the need for station-keeping
B. The satellite’s speed and orbital period
C. The satellite’s fuel consumption
D. The satellite’s communication capabilities
(Answer: A)
The primary factor affecting a satellite’s “orbital period” is:
A. The altitude of the satellite’s orbit
B. The satellite’s propulsion system
C. The rate of atmospheric drag
D. The satellite’s orientation in space
(Answer: A)
To prolong a satellite’s operational life, mission planners must:
A. Regularly perform station-keeping maneuvers and manage fuel efficiently
B. Continuously increase the satellite’s velocity
C. Avoid atmospheric drag at all costs
D. Maintain a low-altitude orbit
(Answer: A)
Satellite “orbit circularization” is:
A. The process of adjusting the satellite’s orbit to become more circular from an elliptical shape
B. Increasing the satellite’s speed for a higher orbit
C. Reducing atmospheric drag to maintain a stable orbit
D. Decreasing the satellite’s altitude for better performance
(Answer: A)
The effect of “orbital perturbations” is:
A. Small variations in the satellite’s orbit due to external forces such as gravity
B. A constant speed in orbit
C. A stable satellite position
D. A reduction in atmospheric drag
(Answer: A)