Astrodynamics MCQs Aeronautical Engineering

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What is the primary focus of astrodynamics? A) The study of atmospheric phenomena B) The dynamics of spacecraft and celestial bodies C) The design of aircraft engines D) The analysis of satellite communication Answer: B) The dynamics of spacecraft and celestial bodies Which law describes the motion of planets around the Sun? A) Newton’s First Law B) Kepler’s Laws C) Bernoulli’s Principle D) Archimedes’ Principle Answer: B) Kepler’s Laws What is the term for the path followed by a spacecraft around a celestial body? A) Trajectory B) Orbit C) Lagrange point D) Escape velocity Answer: B) Orbit What determines the shape of an orbit around a celestial body? A) The mass of the orbiting body B) The speed of the orbiting body C) The gravitational force D) The initial position and velocity Answer: D) The initial position and velocity Which of the following is a characteristic of a circular orbit? A) The distance between the orbiting body and the central body is constant B) The velocity varies throughout the orbit C) The orbit is elliptical D) The orbit has a changing eccentricity Answer: A) The distance between the orbiting body and the central body is constant What is the term for the point in an orbit where the orbiting body is closest to the central body? A) Aphelion B) Perihelion C) Apogee D) Perigee Answer: B) Perihelion What is the escape velocity from a celestial body? A) The velocity required to enter a stable orbit B) The velocity needed to escape the gravitational pull of the body C) The speed at which a body falls towards the central body D) The velocity needed to maintain a circular orbit Answer: B) The velocity needed to escape the gravitational pull of the body Which of the following equations is used to calculate the gravitational force between two masses? A) Newton’s Second Law B) Kepler’s Third Law C) Newton’s Law of Universal Gravitation D) Bernoulli’s Equation Answer: C) Newton’s Law of Universal Gravitation What does the term ‘specific orbital energy’ refer to in astrodynamics? A) The energy required to maintain a stable orbit B) The total energy of an orbiting body per unit mass C) The energy needed to escape the orbit D) The kinetic energy of the orbiting body Answer: B) The total energy of an orbiting body per unit mass Which type of orbit has the highest velocity at the closest approach to the central body? A) Circular orbit B) Elliptical orbit C) Parabolic orbit D) Hyperbolic orbit Answer: B) Elliptical orbit What is a Lagrange point? A) A point where gravitational forces are balanced B) A point where the spacecraft is moving fastest C) A point in a stable orbit around the central body D) A point where the orbiting body reaches its maximum distance from the central body Answer: A) A point where gravitational forces are balanced In astrodynamics, what is the significance of the Hohmann transfer orbit? A) It is used for launching spacecraft from the Earth’s surface. B) It provides the fastest route between two orbits. C) It describes the decay of an orbit over time. D) It represents a stable circular orbit. Answer: B) It provides the fastest route between two orbits. Which parameter is essential for determining the shape and orientation of an orbit? A) Orbital period B) Semi-major axis C) Eccentricity D) Orbital inclination Answer: C) Eccentricity What does the term ‘orbital inclination’ describe? A) The angle between the orbital plane and the equatorial plane B) The distance from the central body to the orbiting body C) The angle between the orbit and the direction of the central body’s rotation D) The velocity of the orbiting body Answer: A) The angle between the orbital plane and the equatorial plane Which type of orbit has an eccentricity of 1? A) Circular orbit B) Elliptical orbit C) Parabolic orbit D) Hyperbolic orbit Answer: C) Parabolic orbit What is the term for an orbit with an eccentricity greater than 1? A) Circular orbit B) Elliptical orbit C) Hyperbolic orbit D) Parabolic orbit Answer: C) Hyperbolic orbit In astrodynamics, what does ‘delta-v’ represent? A) The change in velocity required for orbital maneuvers B) The velocity of the spacecraft relative to the central body C) The difference in velocity between two orbits D) The total velocity of the orbiting body Answer: A) The change in velocity required for orbital maneuvers Which of the following is used to achieve a change in orbit known as a ‘burn’? A) Orbital transfer B) Gravity assist C) Rocket propulsion D) Spacewalk Answer: C) Rocket propulsion What is the primary method for changing an orbit from one circular orbit to another with a different radius? A) Gravity assist B) Hohmann transfer C) Direct thrust D) Tether system Answer: B) Hohmann transfer Which of Kepler’s laws describes that the line connecting a planet to the Sun sweeps out equal areas in equal times? A) First Law B) Second Law C) Third Law D) Fourth Law Answer: B) Second Law What is the primary factor influencing the period of a satellite in orbit? A) The satellite’s mass B) The central body’s mass C) The orbit’s shape D) The satellite’s velocity Answer: B) The central body’s mass What does ‘orbital period’ refer to? A) The time it takes for a spacecraft to complete one orbit around a celestial body B) The time between two orbital maneuvers C) The time it takes for a spacecraft to reach the escape velocity D) The time required for a celestial body to complete one rotation Answer: A) The time it takes for a spacecraft to complete one orbit around a celestial body In a two-body system, what is the relationship between the semi-major axis and the orbital period? A) The orbital period increases with the semi-major axis B) The orbital period decreases with the semi-major axis C) The orbital period is independent of the semi-major axis D) The orbital period and semi-major axis are inversely related Answer: A) The orbital period increases with the semi-major axis Which force is responsible for maintaining an object in orbit around a celestial body? A) Centrifugal force B) Gravitational force C) Electromagnetic force D) Frictional force Answer: B) Gravitational force What does the term ‘perturbation’ refer to in orbital mechanics? A) The influence of other celestial bodies on an orbit B) The initial velocity of the spacecraft C) The shape of the orbit D) The time taken to complete an orbit Answer: A) The influence of other celestial bodies on an orbit Which phenomenon can cause variations in the orbital elements of a satellite? A) Atmospheric drag B) Gravitational perturbations C) Solar radiation pressure D) All of the above Answer: D) All of the above What is the significance of the ‘specific angular momentum’ in astrodynamics? A) It describes the energy of the orbiting body B) It indicates the shape of the orbit C) It is constant for an isolated two-body system D) It determines the velocity of the spacecraft Answer: C) It is constant for an isolated two-body system Which equation relates the gravitational force to the orbital velocity of a satellite? A) Newton’s Law of Universal Gravitation B) Tsiolkovsky Rocket Equation C) Orbital Velocity Equation D) Kepler’s Third Law Answer: C) Orbital Velocity Equation What is the primary use of the patched-conic approximation in astrodynamics? A) To model complex orbital maneuvers B) To simplify calculations for multi-body systems C) To approximate the trajectories of spacecraft in the vicinity of celestial bodies D) To calculate fuel requirements for launch Answer: C) To approximate the trajectories of spacecraft in the vicinity of celestial bodies Which of the following is a method for increasing the altitude of a spacecraft in orbit? A) Retrograde burn B) Prograde burn C) Lateral burn D) Radial burn Answer: B) Prograde burn What does the term ‘gravity assist’ refer to in space missions? A) A technique for increasing spacecraft speed using gravitational fields of celestial bodies B) A method for reducing spacecraft speed using thrusters C) A system for maintaining spacecraft orientation D) A tool for measuring gravitational fields of celestial bodies Answer: A) A technique for increasing spacecraft speed using gravitational fields of celestial bodies What is the effect of increasing the altitude of a satellite’s orbit on its orbital velocity? A) The orbital velocity increases B) The orbital velocity decreases C) The orbital velocity remains constant D) The orbital velocity fluctuates Answer: B) The orbital velocity decreases Which concept explains why a spacecraft must be moving fast enough to remain in orbit? A) Newton’s First Law B) Centripetal Force C) Orbital Mechanics D) Kepler’s Laws Answer: C) Orbital Mechanics What is the purpose of orbital rendezvous in space missions? A) To achieve a docking maneuver with another spacecraft B) To change the spacecraft’s orbital inclination C) To perform a spacewalk for repairs D) To measure gravitational forces Answer: A) To achieve a docking maneuver with another spacecraft Which type of orbit is used for satellite communication due to its constant position relative to the Earth? A) Low Earth Orbit (LEO) B) Medium Earth Orbit (MEO) C) Geostationary Orbit (GEO) D) Highly Elliptical Orbit (HEO) Answer: C) Geostationary Orbit (GEO) What does the term ‘orbital decay’ refer to? A) The increase in orbital altitude over time B) The decrease in orbital altitude due to atmospheric drag or gravitational perturbations C) The change in orbital velocity D) The stability of an orbit over time Answer: B) The decrease in orbital altitude due to atmospheric drag or gravitational perturbations Which of the following equations is used to determine the change in velocity required for a spacecraft to move from one orbit to another? A) Tsiolkovsky Rocket Equation B) Hohmann Transfer Equation C) Newton’s Law of Universal Gravitation D) Kepler’s Third Law Answer: B) Hohmann Transfer Equation What is the effect of gravitational perturbations on a spacecraft’s orbit? A) They make the orbit more stable B) They cause the orbit to become more elliptical C) They cause the orbit to become circular D) They cause variations in the orbital elements Answer: D) They cause variations in the orbital elements What is the purpose of a space tethers system? A) To provide additional propulsion B) To maintain satellite orientation C) To capture debris D) To provide power to spacecraft Answer: A) To provide additional propulsion Which type of orbit is used for Earth observation satellites? A) Low Earth Orbit (LEO) B) Geostationary Orbit (GEO) C) Medium Earth Orbit (MEO) D) High Earth Orbit (HEO) Answer: A) Low Earth Orbit (LEO) What is the term for the process of using a spacecraft’s engines to change its trajectory? A) Orbital transfer B) Gravity assist C) Maneuvering D) Burn Answer: C) Maneuvering Which parameter of an orbit is constant and describes the distance between the central body and the orbiting body at periapsis and apoapsis? A) Semi-major axis B) Orbital period C) Eccentricity D) Specific angular momentum Answer: A) Semi-major axis What does the term ‘orbital insertion’ refer to? A) The process of placing a spacecraft into a stable orbit around a celestial body B) The act of launching a spacecraft from Earth’s surface C) The adjustment of a spacecraft’s orientation in space D) The docking of a spacecraft with another vehicle Answer: A) The process of placing a spacecraft into a stable orbit around a celestial body What is the function of a spacecraft’s reaction control system (RCS)? A) To control the spacecraft’s propulsion system B) To adjust the spacecraft’s orientation and maneuvering C) To maintain the spacecraft’s power supply D) To manage communication with Earth Answer: B) To adjust the spacecraft’s orientation and maneuvering Which of the following is a characteristic of a hyperbolic trajectory? A) The trajectory intersects the central body B) The trajectory is bound and closed C) The trajectory has an eccentricity less than 1 D) The trajectory is an open curve with eccentricity greater than 1 Answer: D) The trajectory is an open curve with eccentricity greater than 1 What is the main advantage of using low Earth orbit (LEO) for satellite missions? A) Longer orbital periods B) Reduced launch costs and closer proximity to Earth C) Higher communication latency D) Greater orbital stability Answer: B) Reduced launch costs and closer proximity to Earth Which force is the primary cause of orbital precession? A) Magnetic force B) Gravitational perturbations C) Centrifugal force D) Electromagnetic force Answer: B) Gravitational perturbations What is the main purpose of the Tsiolkovsky rocket equation? A) To calculate the maximum speed of a rocket B) To determine the amount of propellant required for a specific delta-v C) To analyze the effects of gravitational forces on a rocket D) To model orbital transfers Answer: B) To determine the amount of propellant required for a specific delta-v Which factor primarily affects the orbital velocity of a satellite? A) The satellite’s mass B) The altitude of the orbit C) The launch angle D) The time of launch Answer: B) The altitude of the orbit What is the main effect of atmospheric drag on low Earth orbit satellites? A) Increase in orbital velocity B) Decrease in orbital altitude over time C) Increase in orbital period D) Stabilization of orbit Answer: B) Decrease in orbital altitude over time

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