Question 1

A rocket is designed to operate in both atmospheric and vacuum conditions. During the ascent phase, the ambient pressure (Pa) decreases. Based on the thrust equation, how does this change affect thrust production, assuming all other parameters remain constant?

Accepted Answer

Thrust increases because decreasing Pa increases the pressure thrust component, enhancing total thrust.

Answer

Thrust decreases because decreasing Pa reduces pressure thrust, making the overall thrust lower.

Answer

Thrust first decreases then increases because nozzle efficiency varies with altitude.

Answer

Thrust remains constant because momentum thrust is not affected by external pressure.

Question 2

A new heavy-lift launch vehicle is being designed with a T/W ratio of 1.1 at liftoff. Engineers are considering increasing it to 1.5. What is a possible negative consequence of increasing the T/W ratio too much?

Accepted Answer

The rocket may experience excessive structural stress, potentially leading to mechanical failure.

Answer

A higher T/W ratio improves overall mission performance, with no significant drawbacks.

Answer

Increasing the T/W ratio reduces the need for multi-stage designs, making the rocket simpler.

Answer

A higher T/W ratio improves fuel efficiency, making the rocket more cost-effective.

Question 3

A mission planner is selecting a nozzle expansion ratio for a new Mars lander rocket engine. The engine will operate in the thin Martian atmosphere (~0.6% of Earth’s sea-level pressure). Which nozzle type would be most effective?

Accepted Answer

Underexpanded nozzle, to ensure maximum energy conversion from exhaust expansion.

Answer

Optimally expanded nozzle, to ensure the exhaust exits at Martian atmospheric pressure.

Answer

Overexpanded nozzle, to generate higher pressure inside the nozzle and improve efficiency.

Answer

Aerospike nozzle, to passively adjust expansion ratio at different altitudes.

Question 4

A spacecraft departing Earth orbit for Jupiter has two propulsion options: Solid rocket boosters (Isp = 275 s) Cryogenic upper stage (Isp = 450 s) Which choice is better for the interplanetary transfer, and why?

Accepted Answer

Cryogenic upper stage, because it offers higher specific impulse, making it more fuel-efficient.

Answer

Solid rocket boosters, because they generate high thrust, reducing transfer time.

Answer

Either option, since both will ultimately achieve the same orbital insertion.

Answer

Solid rocket boosters, because they work independently of fuel boil-off issues in deep space.

Question 5

A rocket is designed for deep-space missions, where reusability is not a priority and simplicity is crucial due to limited maintenance opportunities. Which cooling method would be the most suitable for this mission?

Accepted Answer

Ablative Cooling

Answer

Film Cooling

Answer

Regenerative Cooling

Answer

A combination of Regenerative and Film Cooling

Question 6

A launch vehicle’s first-stage engine must provide high thrust and reliable ignition without external infrastructure at remote launch sites. Which of the following combustion cycle variants would be the best choice?

Accepted Answer

Gas Generator Cycle with Solid Propellant Start Cartridge

Answer

Gas Generator Cycle with Flight Start Tanks

Answer

Gas Generator Cycle with Tank Head Start

Answer

Gas Generator Cycle with Ground Start Tanks

Question 7

A rocket nozzle experiences underexpanded flow at high altitudes. What is the primary cause of this phenomenon, and how can it be mitigated?

Accepted Answer

The exhaust gas pressure is higher than ambient pressure; using an extendable nozzle can mitigate this issue.

Answer

The nozzle is optimized for vacuum conditions; using a smaller expansion ratio would improve performance at high altitude.

Answer

The exhaust gas pressure is lower than ambient pressure; using a conical nozzle can mitigate this issue.

Answer

The nozzle throat is too narrow; widening the throat will solve the problem.

Question 8

A company is developing a Single-Stage-to-Orbit (SSTO) vehicle. To maintain high efficiency across varying altitudes, it is considering an aerospike nozzle. Which of the following is the greatest challenge in implementing this technology?

Accepted Answer

High complexity and manufacturing costs

Answer

Low efficiency at high altitudes

Answer

Incompatibility with staged combustion cycles

Answer

Inability to function in a vacuum

Question 9

Aerospace engineers are evaluating the RL-10 engine, which operates using the expander cycle. Given the characteristics of this cycle, for what type of mission would the RL-10 be the least suitable?

Accepted Answer

Heavy-lift first-stage launches requiring high thrust

Answer

Deep-space exploration requiring multiple restarts

Answer

Satellite deployment missions into geostationary transfer orbit (GTO)

Answer

Upper-stage launches that prioritize fuel efficiency

Question 10

The SpaceX Raptor engine operates at combustion chamber pressures exceeding 30 MPa, significantly higher than older engines like the F-1 (7 MPa). What is the primary reason for using such high chamber pressures?

Accepted Answer

To increase specific impulse and fuel efficiency

Answer

To eliminate the effects of aerodynamic drag during ascent

Answer

To simplify turbopump design and reduce mechanical stress

Answer

To reduce the need for advanced cooling systems

Question 11

Aerospace engineers are designing a new heavy-lift launch vehicle and must choose an engine cycle that balances high thrust and efficiency while maintaining reusability. Based on current technologies, which engine cycle is most appropriate for this mission?

Accepted Answer

Full-Flow Staged Combustion Cycle

Answer

Expander Cycle

Answer

Pressure-Fed Cycle

Answer

Gas Generator Cycle

Question 12

A mission to Mars requires a propulsion system that maximizes fuel efficiency while reducing crew radiation exposure through shorter transit times. Based on current technologies, which propulsion system offers the best balance for this mission?

Accepted Answer

Nuclear Thermal Propulsion (NTP)

Answer

Hall-Effect Thrusters

Answer

Gas Generator Cycle Rocket Engine

Answer

Expander Cycle Cryogenic Engine

Question 13

A satellite needs to enter a polar orbit for Earth observation. However, launching from a near-equatorial site like Kourou (5°N latitude) requires additional maneuvers. What is the primary challenge of launching a polar mission from an equatorial site?

Accepted Answer

The rocket must perform a large plane change maneuver, which requires significant fuel.

Answer

A launch from the equator provides too much initial velocity, making a polar orbit unstable.

Answer

The rocket experiences higher aerodynamic drag when launching toward the poles.

Answer

The rocket will not be able to achieve a polar orbit due to Earth's rotation.

Question 14

A mission planner is designing a three-stage rocket for an interplanetary mission. Which of the following best explains why the first stage typically has the highest mass?

Accepted Answer

The first stage needs to counteract gravity and atmospheric drag while providing the highest thrust.

Answer

The first stage needs additional shielding to protect from atmospheric heating.

Answer

The first stage requires extra mass to provide stability during takeoff.

Answer

The first stage must contain the most advanced engines for space maneuvers.

Question 15

A space agency is designing a new multistage rocket. What would be the primary drawback of using a parallel staging configuration instead of serial staging?

Accepted Answer

Parallel staging requires more structural reinforcement, increasing the overall dry mass.

Answer

Parallel staging is only useful for reusable rockets and is ineffective for disposable rockets.

Answer

Parallel staging results in a lower payload capacity compared to serial staging.

Answer

Parallel staging reduces the total thrust available at launch.

Question 16

A rocket has successfully reached Low Earth Orbit (LEO), but the mission requires a transfer to Geostationary Orbit (GEO). What must happen next?

Accepted Answer

The rocket must perform a Hohmann transfer, increasing its velocity at perigee to reach apogee at GEO altitude.

Answer

The rocket must maintain its LEO orbit until atmospheric drag naturally raises its altitude.

Answer

The rocket must reduce its velocity to enter a direct insertion path toward GEO.

Answer

The rocket must align with the Moon’s gravitational influence to slingshot into GEO.

Question 17

A space agency is planning a mission to deploy a new space telescope. The payload is large and requires manual adjustments in orbit. Based on past missions, which launch system would be the most suitable choice, and why?

Accepted Answer

Space Shuttle – It has a large cargo bay and allows astronauts to manually operate payload deployment.

Answer

Falcon 9 – It is a reusable launch vehicle with a proven track record of carrying payloads to orbit.

Answer

Delta IV Heavy – It has the highest lift capacity among currently operational launch vehicles.

Answer

Atlas V – It is a reliable ELV that has successfully launched large payloads such as interplanetary probes.

Question 18

A new upper-stage engine is being designed for deep-space missions. What is the most critical design factor to ensure efficient operation in space?

Accepted Answer

The ability to restart multiple times to make trajectory adjustments

Answer

A wide thrust range to ensure high power at launch

Answer

A small nozzle to reduce weight and fuel consumption

Answer

A dense atmosphere-compatible fuel mixture for better combustion

Question 19

A satellite launch mission has strict budget constraints. The payload is medium-sized, and launch reliability is crucial. Based on cost efficiency and sustainability, which vehicle would be the best option?

Accepted Answer

Falcon 9 – Reusable first stage, significantly reducing launch costs.

Answer

Delta IV Heavy – High payload capacity but expensive to manufacture and launch.

Answer

Ariane 5 – Used for major scientific missions but follows an expendable design.

Answer

Atlas V – Proven reliability but requires a new rocket for each launch.

Question 20

A space agency is planning a series of high-frequency cargo resupply missions to a future lunar base. Why might they avoid using Expendable Launch Vehicles (ELVs) for this purpose?

Accepted Answer

ELVs are optimized for single-use missions, making them cost-ineffective for repeated launches.

Answer

ELVs are unreliable and have a high failure rate compared to reusable rockets.

Answer

ELVs are banned from launching interplanetary missions due to environmental concerns.

Answer

ELVs cannot carry large payloads, limiting their application for lunar resupply missions.

Question 21

Which of the following missions would have been least affected if the Centaur upper stage had not been available?

Accepted Answer

Hubble Space Telescope Deployment – Placed into a low Earth orbit.

Answer

Voyager 1 & 2 – Needed multiple burns for outer planet flybys.

Answer

New Horizons – Required a high-energy boost to reach Pluto.

Answer

Mars Science Laboratory – Needed precise trajectory corrections for landing on Mars.

Question 22

During the gravity turn maneuver, a rocket experiences bending loads due to lateral forces. What design strategy is most effective for mitigating these loads without adding unnecessary mass?

Accepted Answer

Utilizing a monocoque structure with optimized material distribution and internal stiffening elements

Answer

Increasing the outer shell thickness significantly to counteract bending stresses

Answer

Designing the rocket with a completely rigid body to prevent bending altogether

Answer

Implementing additional propulsion systems to counteract gravity-induced bending forces

Question 23

A launch vehicle with multiple strap-on boosters must ensure symmetrical detachment. What is the primary structural risk if one booster detaches asymmetrically, and how can this be prevented?

Accepted Answer

Torsional instability, mitigated by synchronized detachment mechanisms and real-time thrust vectoring

Answer

Heat stress on the remaining boosters, mitigated by additional thermal shielding

Answer

Excessive aerodynamic drag, mitigated by increased fairing size

Answer

Increased axial load, mitigated by reinforcing the payload fairing

Question 24

During ascent, a rocket’s onboard systems experience significant dynamic loads, including vibrations and acoustic stress. Which of the following is the most effective method for minimizing the impact of these dynamic loads on sensitive instruments?

Accepted Answer

Using shock absorbers and damping materials to isolate instruments from high-frequency vibrations

Answer

Encasing sensitive instruments in a vacuum-sealed chamber to prevent exposure to vibrations

Answer

Increasing the overall structural mass to dampen vibrations

Answer

Rigidly mounting instruments to the rocket frame to ensure stability

Question 25

The introduction of reusable rockets, such as SpaceX’s Falcon 9 and Starship, has dramatically reduced launch costs. Which of the following factors contributes most significantly to the economic feasibility of reusable launch systems?

Accepted Answer

The ability to recover and refurbish first-stage boosters, reducing manufacturing costs

Answer

The complete automation of rocket launches, eliminating human oversight costs

Answer

The elimination of all structural reinforcements to maximize payload capacity

Answer

The use of solid propellant engines, which require less maintenance

Question 26

A satellite in a stable circular orbit around Earth suddenly experiences a minor propulsion system malfunction, causing a slight decrease in its velocity. What is the most likely outcome of this event?

Accepted Answer

The satellite will gradually shift into an elliptical orbit, with its new periapsis lower than before.

Answer

The satellite will immediately fall to Earth and burn up in the atmosphere.

Answer

The satellite will move into a higher orbit due to the conservation of angular momentum.

Answer

The satellite will maintain its circular orbit but at a slightly reduced altitude.

Question 27

A space mission planner needs to place a satellite in a geostationary orbit. Which of the following parameters must be ensured for this to happen?

Accepted Answer

The satellite’s orbital velocity must equal Earth’s rotational velocity at that altitude.

Answer

The satellite must be positioned at an altitude of exactly 500 km.

Answer

The satellite must have an eccentricity of exactly 1.

Answer

The satellite must be in a polar orbit to ensure constant visibility of the same point.

Question 28

A spacecraft on a hyperbolic trajectory around Jupiter performs a gravity assist maneuver. What happens to the spacecraft’s velocity relative to the Sun?

Accepted Answer

The velocity increases as Jupiter transfers some of its orbital momentum to the spacecraft.

Answer

The velocity remains constant due to conservation of energy.

Answer

The velocity remains unchanged relative to Jupiter but decreases relative to the Sun.

Answer

The velocity decreases because the spacecraft is moving away from Jupiter’s gravity well.

Question 29

A spacecraft is in a highly elliptical orbit around Earth. According to Kepler’s Second Law, how does its velocity change as it moves from apoapsis to periapsis?

Accepted Answer

The velocity increases as it approaches periapsis due to conservation of angular momentum.

Answer

The velocity remains constant throughout the orbit.

Answer

The velocity decreases as it approaches periapsis due to increasing gravitational pull.

Answer

The velocity remains the same at apoapsis and periapsis but varies in between.

Question 30

A spacecraft needs to transfer from a low Earth orbit (LEO) to a higher geostationary orbit (GEO) using a Hohmann transfer. Which of the following best describes the sequence of maneuvers required?

Accepted Answer

Two impulses: the first at LEO periapsis to reach an elliptical orbit, and the second at GEO apoapsis to circularize the orbit.

Answer

A single burn at the ascending node to correct inclination and raise altitude simultaneously.

Answer

A single impulse applied at perigee to achieve the new orbit.

Answer

A continuous low-thrust burn from LEO to GEO.

Question 31

A mission planner is considering a Molniya orbit for a communications satellite. What primary advantage does this orbit provide over a geostationary orbit for high-latitude coverage?

Accepted Answer

The satellite spends a prolonged time over high-latitude regions due to its high eccentricity.

Answer

The satellite conserves fuel by requiring only a single burn to maintain station-keeping.

Answer

The satellite remains stationary over a fixed point, ensuring constant coverage.

Answer

The satellite has a short orbital period, allowing for more frequent data transmission.

Question 32

A spacecraft needs to match the velocity of an asteroid for a landing mission. Which of the following maneuvers is most efficient for this task?

Accepted Answer

A series of small thruster firings over time to slowly reduce velocity mismatch.

Answer

A gravity assist from a nearby planet to adjust approach speed.

Answer

A direct burn to match the asteroid's speed upon arrival.

Answer

A bi-elliptic transfer orbit to gradually reduce velocity differences.

Question 33

A spacecraft orbiting Mars requires a plane change to align with a polar orbit for full surface coverage. What is the most fuel-efficient approach to achieving this change?

Accepted Answer

Conduct the maneuver at apoapsis, where the velocity is lowest, to minimize delta-v requirements.

Answer

Use an aerobraking maneuver to adjust inclination while reducing velocity.

Answer

Execute a radial burn to slowly shift the orbital inclination over multiple orbits.

Answer

Perform the plane change at the point in the orbit where velocity is lowest.

Question 34

An interplanetary mission requires a precise arrival at a distant planet. What primary factor must be carefully considered when executing a mid-course correction burn?

Accepted Answer

The relative motion of the target planet and any gravitational influences.

Answer

The amount of remaining fuel available for the mission.

Answer

The spacecraft's distance from Earth at the time of the burn.

Answer

The speed of the spacecraft relative to the Sun.

Question 35

A spacecraft in a low-energy transfer trajectory to Jupiter must perform an orbital insertion burn. At what point should this burn be executed for maximum efficiency?

Accepted Answer

At periapsis, to maximize the gravitational assist effect.

Answer

Before entering Jupiter’s gravitational sphere of influence.

Answer

At the point where the spacecraft has maximum velocity relative to Jupiter.

Answer

At the spacecraft’s closest approach to the target orbit.

Question 36

A mission requires placing a satellite in a sun-synchronous orbit to ensure consistent lighting conditions for Earth observations. What key parameter must be controlled to maintain this orbit?

Accepted Answer

The satellite’s inclination and nodal precession rate.

Answer

The satellite’s altitude and eccentricity.

Answer

The satellite’s inclination and perigee altitude.

Answer

The satellite’s argument of perigee and semi-major axis.

Question 37

A space probe is using a gravity assist from Venus to increase its velocity toward the outer planets. What is the primary advantage of this maneuver?

Accepted Answer

It increases the probe’s energy relative to the Sun without additional fuel consumption.

Answer

It helps the probe avoid high-radiation environments near the Sun.

Answer

It changes the probe’s inclination to align with a new orbital plane.

Answer

It allows the probe to reduce its velocity without using fuel.

Question 38

A lunar lander must perform a braking burn before touchdown. What key parameter should be optimized to minimize fuel consumption?

Accepted Answer

The velocity at which the burn begins.

Answer

The time at which the burn is initiated relative to periapsis.

Answer

The lander’s altitude at the start of the burn.

Answer

The thrust-to-weight ratio during descent.

Question 39

A spacecraft is in a highly elliptical orbit around Mars and needs to circularize at periapsis. Which maneuver achieves this?

Accepted Answer

A prograde burn at periapsis.

Answer

A retrograde burn at apoapsis.

Answer

A normal burn at ascending node.

Answer

A radial burn at periapsis.

Question 40

A mission design team is evaluating different orbit options for a planetary mapping satellite. Why would a polar orbit be preferred over an equatorial orbit?

Accepted Answer

A polar orbit allows for full planetary coverage over time.

Answer

A polar orbit minimizes exposure to radiation belts around the planet.

Answer

A polar orbit allows for faster data transmission back to Earth.

Answer

A polar orbit is more fuel-efficient to maintain than an equatorial orbit.

Question 41

A spacecraft in low Earth orbit (LEO) needs to transfer to a geostationary orbit using a Hohmann transfer. What are the two required burns for this maneuver?

Accepted Answer

A prograde burn at LEO followed by another prograde burn at geostationary altitude.

Answer

A prograde burn at perigee and a retrograde burn at apogee.

Answer

A retrograde burn at LEO followed by a radial burn at apogee.

Answer

A radial burn at perigee and a normal burn at apogee.

Question 42

A space telescope is planned for a Lagrange Point 2 (L2) orbit. What is the main advantage of this location?

Accepted Answer

It provides a stable gravitational point where minimal station-keeping is needed.

Answer

It keeps the telescope in constant shadow, preventing overheating.

Answer

It allows direct high-speed communication with ground stations on Earth.

Answer

It allows continuous observation of the Sun without interference from Earth.

Question 43

A satellite needs to avoid collisions with space debris. Which of the following strategies is most effective for long-term orbital debris mitigation?

Accepted Answer

Planning for a controlled deorbit at the end of the satellite’s operational life.

Answer

Increasing a satellite’s orbital altitude to move away from debris-heavy regions.

Answer

Designing satellites with thick shielding to withstand debris impacts.

Answer

Performing frequent collision avoidance maneuvers to dodge debris.

Question 44

A planetary rover on Mars is designed with a radioisotope thermoelectric generator (RTG) instead of solar panels. What is the primary reason for this choice?

Accepted Answer

RTGs allow continuous power generation regardless of sunlight conditions.

Answer

RTGs reduce the overall launch mass of the rover.

Answer

RTGs provide higher power output than solar panels.

Answer

RTGs require less shielding against cosmic radiation.

Question 45

A satellite in a Molniya orbit is used for communications over high latitudes. What is the main advantage of this orbit over a standard geostationary orbit?

Accepted Answer

It allows a satellite to spend more time over high latitudes.

Answer

It minimizes exposure to the Van Allen radiation belts.

Answer

It requires less fuel to maintain than a geostationary orbit.

Answer

It provides continuous coverage of the entire Earth.

Question 46

A mission planner must select an orbit for a high-resolution Earth observation satellite. Which factor is most critical in determining the optimal orbit?

Accepted Answer

The required ground resolution and revisit time.

Answer

The availability of launch windows

Answer

The launch provider’s preferred orbit

Answer

The satellite’s communication capabilities

Question 47

A team designing a lunar rover must select a power system. What is the most critical consideration?

Accepted Answer

The lunar night cycle and temperature extremes.

Answer

The ability to recharge from Earth-based transmitters

Answer

The rover’s top speed and mobility requirements

Answer

The distance from Earth to the Moon

Question 48

A deep-space probe is experiencing unexpected power fluctuations. What is the most effective response?

Accepted Answer

Analyze system telemetry to identify the root cause before taking corrective action.

Answer

Shut down the power system and restart the probe

Answer

Increase power transmission from Earth

Answer

Reduce the spacecraft’s scientific operations to conserve power

Question 49

A mission team must select a data transmission method for a Mars orbiter. What is the most important factor in this decision?

Accepted Answer

The availability of relay satellites and communication bandwidth.

Answer

The cost of building additional ground stations on Earth

Answer

The historical reliability of previous communication methods

Answer

The spacecraft’s ability to store data onboard

Question 50

An interplanetary spacecraft’s propulsion system is consuming more fuel than expected. What is the best course of action?

Accepted Answer

Investigate possible causes such as trajectory deviations, thruster inefficiencies, or unexpected external forces.

Answer

Request additional fuel from a future resupply mission

Answer

Reduce the spacecraft’s speed to conserve fuel

Answer

Disable redundant propulsion systems to prevent further fuel loss

Question 51

During the selection of a launch vehicle for a satellite mission, what is the most critical factor in ensuring compatibility?

Accepted Answer

The satellite’s mass, volume, and required orbit parameters.

Answer

The launch date flexibility

Answer

The number of previous successful launches by the provider

Answer

The reputation of the launch provider

Question 52

A systems engineer is assessing trade-offs for a deep-space probe’s power system. What is the best way to decide between solar panels and a radioisotope thermoelectric generator (RTG)?

Accepted Answer

Evaluate mission distance, power needs, and environmental constraints before deciding.

Answer

Choose RTGs because they provide power continuously

Answer

Use both power systems for redundancy

Answer

Choose solar panels because they are cheaper

Question 53

A spacecraft’s thermal protection system (TPS) is experiencing higher-than-expected degradation in testing. What is the most appropriate action?

Accepted Answer

Investigate material properties, heat loads, and re-entry conditions before modifying the design.

Answer

Immediately replace the TPS with a new material without further analysis

Answer

Reduce mission duration to minimize thermal exposure

Answer

Proceed with the current design and compensate with additional cooling

Question 54

What is the primary reason redundancy is included in critical spacecraft subsystems?

Accepted Answer

To ensure mission success even if primary components fail.

Answer

To increase costs and development time intentionally

Answer

To comply with regulations requiring extra hardware

Answer

To increase the complexity of the spacecraft design

Question 55

A mission design team is considering two spacecraft configurations: one optimized for minimal cost and another for high performance. How should the decision be made?

Accepted Answer

Conduct a trade-off analysis considering cost, performance, and mission objectives.

Answer

Choose the lower-cost design, as budget is the primary constraint

Answer

Split the mission into two separate launches, one for each design

Answer

Select the high-performance design to maximize scientific return

Question 56

A spacecraft operating in a high-radiation environment experiences intermittent computer failures. What is the most effective mitigation strategy?

Accepted Answer

Implement fault-tolerant software and radiation-hardened components.

Answer

Schedule more frequent reboots of the onboard computer

Answer

Reduce the spacecraft’s altitude to minimize exposure

Answer

Increase the power supplied to the onboard computer

Question 57

A mission designer is evaluating potential launch windows for a Mars mission. Which factor is most critical in determining the best launch date?

Accepted Answer

The relative positions of Earth and Mars in their orbits.

Answer

The expected duration of the spacecraft’s cruise phase

Answer

The availability of a backup launch vehicle

Answer

The spacecraft’s communication capabilities after launch

Question 58

A satellite in low Earth orbit (LEO) is experiencing excessive drag, leading to an accelerated decay in altitude. What is the most effective long-term solution?

Accepted Answer

Move the satellite to a higher orbit where atmospheric drag is lower.

Answer

Increase the frequency of station-keeping maneuvers to counteract drag

Answer

Increase the satellite’s mass to reduce the effects of drag

Answer

Adjust the satellite’s orientation to minimize atmospheric resistance

Question 59

A deep-space probe is designed to use a gravity assist maneuver. What is the primary benefit of this technique?

Accepted Answer

It significantly reduces the amount of propellant needed for the mission.

Answer

It enables the spacecraft to carry more scientific instruments

Answer

It stabilizes the spacecraft’s orientation in space

Answer

It allows the spacecraft to remain in constant communication with Earth

Question 60

A satellite in geostationary orbit (GEO) begins to drift from its assigned position. What is the most likely cause?

Accepted Answer

The satellite is experiencing perturbations from gravitational influences.

Answer

The satellite’s communication system is malfunctioning

Answer

The satellite’s altitude is too low for stable operation

Answer

The satellite’s solar panels are not receiving enough sunlight

Question 61

A mission planner is designing a lunar lander to operate in the Moon’s extreme temperature conditions. What is the most critical design consideration?

Accepted Answer

Using thermal insulation and radiators to manage heat transfer.

Answer

Selecting a landing site with a moderate temperature range

Answer

Designing solar panels to operate in low temperatures

Answer

Ensuring the lander has sufficient propulsion for descent

Question 62

A satellite manufacturer is considering different power systems for a spacecraft operating beyond Mars. Which option provides the most reliable long-term energy source?

Accepted Answer

A radioisotope thermoelectric generator (RTG).

Answer

Solar panels with battery storage

Answer

A high-efficiency diesel generator

Answer

Fuel cells with chemical energy storage

Question 63

A Mars rover is experiencing a dust storm that reduces its solar power generation. What is the best contingency plan to ensure mission survival?

Accepted Answer

Enter a low-power mode and limit non-essential operations.

Answer

Use the onboard drill to remove dust from the solar panels

Answer

Transmit all remaining scientific data before shutting down

Answer

Increase power draw from the rover’s battery to maintain full functionality

Question 64

A spacecraft is designed to perform a flyby of Jupiter. What is the greatest risk posed by the planet’s environment?

Accepted Answer

Intense radiation belts.

Answer

Collisions with its moons

Answer

Extreme gravitational forces

Answer

High atmospheric pressure

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