dataset update

astro-mcqa.csv

@@ -1,13 +1,13 @@
 question,propositions,labels,justification,answerable,uid
-True or False? An object that is not accelerating or decelerating has no forces acting on it.,"['True', 'False', 'Impossible to say without more information']","[0, 1, 0]",,True,ff0e8305-73e0-404a-a775-4e7be538d99b
+True or False? An object that is not accelerating or decelerating has no forces acting on it.,"['True', 'False', 'Impossible to say without more information']","[0, 1, 0]","According to Newton's first law: ""In the absence of a force, a body either is at rest or moves in a straight line with constant speed"". However, the opposit is not true. A body can have forces acting on it and not accelerate if the resulting force is zero.",True,ff0e8305-73e0-404a-a775-4e7be538d99b
 "Complete the following: During its orbital period, as a planet moves farther away from the sun, the orbital velocity of the planet ...","['remains the same', 'increases', 'decreases']","[0, 0, 1]",,True,40a73e51-5eb4-46d3-baab-8acd624f2287
-Which affirmation is true when talking about Earth’s potential energy?,"['The potential energy is positive', 'The potential energy is constant', 'The potential energy is negative', 'None of the above answers']","[0, 0, 1, 0]",,True,883f8ed7-8b2a-4671-80d3-f68791fa4118
+Which affirmation is true when talking about Earth’s potential energy?,"['The potential energy is positive', 'The potential energy is constant', 'The potential energy is negative', 'None of the above answers']","[0, 0, 1, 0]",This is because the Earth potential energy is expressed as Epot = - mu / r,True,883f8ed7-8b2a-4671-80d3-f68791fa4118
 Why do we talk about microgravity in LEO?,"['All the external forces are not cancelling exactly', 'In LEO orbits, the Earth’s gravity is not exactly zero', 'The free-fall trajectory gets perturbed', 'None of the above answers']","[0, 0, 1, 0]",,True,7667b6ef-31e5-4ff3-87e2-65f9a4467551
 To what wavelength is the atmosphere the most transparent?,"['X-rays', 'Visible light', 'Infra Red', 'Radio Waves']","[0, 0, 0, 1]",,True,b855830d-0498-4c21-8aca-ac69c917178c
 "In the atmosphere and space environment, what best describes the so-called airglow?","['Photo ionization of oxygen', 'Northern lights', 'Diffraction of the Sun light in the upper layers of the atmosphere', 'Photo Ionization of Hydrogen']","[1, 0, 0, 0]",,True,e8663499-3be2-4284-88b1-6bada5682f75
 "A rocket is launched from ESA spaceport in Kourou, French Guyana. Through which layers of the atmosphere and in what order the rocket will pass through?","['thermosphere, troposphere, stratosphere, mesosphere', 'troposphere, mesosphere, thermosphere, stratosphere', 'troposphere, stratosphere, mesosphere, thermosphere', 'troposphere, mesosphere, stratosphere, thermosphere']","[0, 0, 1, 0]",,True,1b6dbef8-074c-47b0-aba9-5b291196850d
-What are the Van Allen belts?,"['The region between 90 and 100 km altitude', 'Low radiation regions', 'Much used orbits for telecommunication', 'Radiation belts']","[0, 0, 0, 1]",,True,9d24c8a3-5a62-4b10-a5c6-82a9a7173042
-"Why is the inner radiation belt harmful for satellites, and more so than the outer belt ?","['Inner radiation modify the magnetic field and will damage optical system of satellites.', 'Inner radiation traps space debris which damage the structure of satellites.', 'Inner radiation traps protons which are more likely to damage on-board electronics.', 'the question is not correct, the outer belt is more harmful for satellites.']","[0, 0, 1, 0]",,True,45402b06-b7b3-46b0-ae5c-1d3ad697d8b4
+What are the Van Allen belts?,"['The region between 90 and 100 km altitude', 'Low radiation regions', 'Much used orbits for telecommunication', 'Radiation belts']","[0, 0, 0, 1]","These are regions in which you have an increased density of charged particles, mainly protons and electrons, and they are moving to the North and to the South. They are trapped in these regions of increased flux of protons and electrons. Electrons are not too harmful, but protons could be.",True,9d24c8a3-5a62-4b10-a5c6-82a9a7173042
+"Why is the inner radiation belt harmful for satellites, and more so than the outer belt ?","['Inner radiation modify the magnetic field and will damage optical system of satellites.', 'Inner radiation traps space debris which damage the structure of satellites.', 'Inner radiation traps protons which are more likely to damage on-board electronics.', 'the question is not correct, the outer belt is more harmful for satellites.']","[0, 0, 1, 0]","On top of electrons the inner radiation traps a significant amount of protons whose mass is much higher than the electrons. Because those protons carry more energy, they are also more likely to cause critical damage to the on-board electronics. One way to mitigate this problem is to harden the circuitry by applying redundancy as needed or by shielding the components.",True,45402b06-b7b3-46b0-ae5c-1d3ad697d8b4
 "The sunspot number is a value that changes with time, with a period of approximately...","['7 years', '9 years', '11 years', '13 years']","[0, 0, 1, 0]",,True,920728e6-584b-46bd-b596-80aaab4ccfad
 "True or False: the latitude of sunpots during a solar cycle stays uniform and constant, regardless of the sun activity","['True', 'False']","[0, 1]",,True,32387be2-0b71-47c8-abbf-b06d60781657
 Which of the following statement(s) is or are correct(s) with respect to the solar cycle effect on satellite lifetime at a given altitude?,"['At solar maximum, you have higher atmosphere density, which means more drag, and reduced satellite lifetime', 'At solar maximum, you have lower atmosphere density, which means less drag, and and increased satellite lifetime', 'At solar minimum, you have higher atmosphere density, which means more radiation, and reduced satellite lifetime', 'At solar minimum, you have lower atmosphere density, when means less lift for the satellite, and reduced lifetime']","[1, 0, 0, 0]",,True,433d3c7b-4f56-4934-ac4b-d513d975c33b
@@ -24,12 +24,12 @@ Coronal Mass Ejections (CMEs) are huge ejections of plasma from the Sun. What is
 What is the magnetosphere?,"['A spherical object composed solely of magnetic material', 'A region that surrounds an object that has a magnetic field, usually a dipole which is distored by charged particles', 'A region in Indonesia', 'A region that surrounds an object that has a magnetic field, which tunnels neutral particles away from the object']","[0, 1, 0, 0]",,True,a279f385-4896-4877-8c32-c265ae0f6b31
 "Some of the solar flux is reflected off the surface of the Earth. The fraction of sunlight reflected is given by the albedo. If the albedo increases, how will the amount of reflected light change?","['It increases', 'It descreases', 'It stays the same', 'Impossible to say, we need more information to answer']","[1, 0, 0, 0]",,True,dea1ba45-fcb4-454c-ab94-8a06a4d4f2f4
 Crossing the South Atlantic Anomaly (SAA) with a satellite can greatly restrict its performance. Why?,"['The SAA is a region of permanent shadow over the South Atlantic, thus there is no power generated by the solar panels.', 'The SAA is a region of extremely high radiation. Radiations create errors in the onboard electronics which can potentially be permanent.', 'The SAA is a region of extremely low radiation. This induces large currents in the onboard electronics which degrades the performance.', 'The SAA is a region which is not covered by any array of antenna, which renders any communication between the ground and the satellite impossible.']","[0, 1, 0, 0]",,True,8b9f71e4-c6db-45d7-8199-a83a58c31074
-An object X and an object Y are in orbit (at the same altitude). X has a Drag Coefficient of 2 while Y has a drag Coefficient of 2.2. Which object will first fall back to Earth?,"['Object X', 'Object Y', 'Both at the same time', 'Impossible to say']","[0, 0, 0, 1]",,True,274915a7-1ad4-49f5-979e-c38c3994eba4
+An object X and an object Y are in orbit (at the same altitude). X has a Drag Coefficient of 2 while Y has a drag Coefficient of 2.2. Which object will first fall back to Earth?,"['Object X', 'Object Y', 'Both at the same time', 'Impossible to say']","[0, 0, 0, 1]",The masses and cross-sections have to be given to be able to estimate which will fall back first.,True,274915a7-1ad4-49f5-979e-c38c3994eba4
 "Space debris mitigation rule states that after end of nominal operations, a satellite has to fall back to Earth or to be put on a graveyard orbit within","['23 years', '24 years', '25 years', '42 years']","[0, 0, 1, 0]",,True,20566fe9-5314-4bb3-a0b7-4e9f01f8c396
 Hubble's solar arrays were damaged because of collisions with:,"['Orbital debris', 'Meteorites with a 10e-5 cm diameter', 'Meteorites with a 10e-2 cm diameter', 'Meteroites with a 10 cm diameter', 'The famous cosmos-irridium breakup that destroyed the primary mirror of the telescope']","[1, 1, 1, 0, 0]",,True,80824e85-50b6-4981-9056-5f91e3bd6326
 The International Space Station (ISS) is placed on an elliptical orbit around the Earth. The orbital apogee is 417 km and orbital perigee is 401 km. What is the gravitational acceleration created by the Earth at the orbit perigee?,"['1.72 m/s^2', '8.68 m/s^2', '0 m/s^2', '7.78 m/s^2']","[0, 1, 0, 0]",,True,2772845a-52cb-4686-8cfe-b19647b0ad18
-"What is the escape velocity from the surface of the moon Europa (mass M = 4.8e22 kg, radius 1560 km)? (answer in km/s)","['1.072', '2.026', '3.48', '6.01', '9.96']","[0, 1, 0, 0, 0]",,True,90c76998-7060-491c-a0fb-3ae580a72a22
-The escape velocity out of the solar system from Jupiter's orbit is 18.5 km/s while the average orbital velocity is 13.1 km/s. What is the transfer velocity in km/s?,"['0.2', '1.4', '2.7', '3.6', '5.4']","[0, 0, 0, 0, 1]",,True,6df3d9f1-800e-4b7d-b9ca-ce2ef8090718
+"What is the escape velocity from the surface of the moon Europa (mass M = 4.8e22 kg, radius 1560 km)? (answer in km/s)","['Approximately 1', 'Approximately 2', 'Approximately 3', 'Approximately 4', 'Approximately 5']","[0, 1, 0, 0, 0]",The escape velocity of Europa is simply computed from Vesc = sqrt( 2*mu / R) which is approximately 2 km/s,True,90c76998-7060-491c-a0fb-3ae580a72a22
+The escape velocity out of the solar system from Jupiter's orbit is 18.5 km/s while the average orbital velocity is 13.1 km/s. What is the transfer velocity in km/s?,"['0.2', '1.4', '2.7', '3.6', '5.4']","[0, 0, 0, 0, 1]","The transfer velocity, for a given planet, is the velocity that has to be added to the planet's circular velocity for a transfer to infinity from this location in the Sun's gravitational well. Therefore, the transfer velocity out of the solar system is 18.5 - 13.1 = 5.4 km/s.",True,6df3d9f1-800e-4b7d-b9ca-ce2ef8090718
 The comet 67P/Churyumov-Gerasimenko has an escape velocity close to 1 m/s. What would be sufficient in the following to escape its surface and never come back ?,"['You, by jumping the equivalent of 50 cm on Earth.', 'A tennis ball hit by Roger Federer.', 'A bullet shot by a pistol.', 'None of the above.']","[1, 1, 1, 0]",,True,dcd48a6f-2c96-42e6-b75e-b5cb28b2c1fa
 "The Rosetta spacecraft launched by the European Space Agency successfully entered the orbit of the comet 67P/Churyumov-Gerasimenko in August 2014. November 12 2014, the Philae lander was released and touched down 7 hours later at a speed of 0.98m/s.
 
@@ -48,8 +48,8 @@ Which of the following proportionnality relation with the orbital period T with
 An artificial Earth satellite is in an elliptical orbit with a perigee altitude of hp = 250 km and an apogee altitude of ha = 800 km. What is the correct expression of the orbital period?,"['T = 2*pi * sqrt( a^3 / mu )', 'T = 2*pi * sqrt( a^2 / mu )', 'T = 2*pi * sqrt( a^(1/2) / mu )', 'T = 2*pi * a^3 / mu']","[1, 0, 0, 0]",,True,176ce268-f5ed-4c3e-bf98-b53c8c63fed0
 "An artificial Earth satellite is in an elliptical orbit with a perigee altitude of hp and an apogee altitude of ha. How do you express the semi major of the axis of the satellite orbit ""a""  in function of hp, ha, and R where R is the Earth's radius?","['a = R ( hp + ha ) / 2', 'a = R ( ha - hp ) / 2', 'a = 2R + (ha + hp) / 2', 'a = R - (hp + ha) / 2', 'a = R + (ha + hp) / 2']","[0, 0, 0, 0, 1]",,True,874c48df-381b-4887-a2b8-fa09963fbb2f
 An artificial Earth satellite is in an elliptical orbit with a perigee altitude of hp = 250 km and an apogee altitude of ha = 800 km. What is its orbital period expressed in minutes?,"['18.0', '89.5', '95.0', '100.9']","[0, 0, 1, 0]",,True,6ef8b7da-7aea-4809-95ce-c17f64866bee
-A geostationary orbit is defined as an orbit were the satellite is always pointing towards the same point on the Earth's surface. What is its eccentricity?,"['0', '1', '1.3', '0.5']","[1, 0, 0, 0]",,True,5064e3a3-16e9-431c-816e-3d8cd10c9331
-A geostationary orbit is defined as an orbit were the satellite is always pointing towards the same point on the Earth's surface. What is its inclination?,"['7.01°', '0°', '3.2°', '45°']","[0, 1, 0, 0]",,True,6192c62d-489d-45e4-acf6-23083a809273
+A geostationary orbit is defined as an orbit were the satellite is always pointing towards the same point on the Earth's surface. What is its eccentricity?,"['0', '1', '1.3', '0.5']","[1, 0, 0, 0]","Since the Earth's rotation is constant, the eccentricity of the orbit is zero, otherwise its orbital velocity would not be constant.",True,5064e3a3-16e9-431c-816e-3d8cd10c9331
+A geostationary orbit is defined as an orbit were the satellite is always pointing towards the same point on the Earth's surface. What is its inclination?,"['7.01°', '0°', '3.2°', '45°']","[0, 1, 0, 0]",The inclination is also zero otherwise the satellite's pointing would oscillate across the equator.,True,6192c62d-489d-45e4-acf6-23083a809273
 "In orbital mechanics, what is the meaning of the mean motion n = sqrt( mu / a^3 )?","['It is the average angular rate over one full orbit, in rad/s', 'It can be defined only for parabolic orbits.', 'It corresponds to the instantaneous angular rate for a non-circular orbit.', 'In the specific case where the eccentricity e tends to zero, the mean motion and the true anomaly tend to be equal.', 'The mean motion relates to the true position of a body moving along a Keplerian orbit.']","[1, 0, 0, 0, 0]",,True,bc2f3517-6e5a-4b39-89c6-fb11c2209392
 What reference frame is the best suited for an interplanetary probe?,"['Geographic coordinate system', 'Geo-centric coordinate system', 'Heliocentric-inertial coordinate system']","[0, 0, 1]","The center of the heliocentric-inertial coordinate system is the Sun. The two other coordinate systems use the Earth as center, and are not appropriate to for an interplanetary probe.",True,8d7cc580-c7b9-4875-9ba6-bf468df0a61d
 The complete precessional cycle of the Earth lasts about 26000 years. What is the precession rate? (in degrees per year),"['0.00384', '0.01384', '0.02384', '0.03384', '0.04384', '0.05384']","[0, 1, 0, 0, 0, 0]",The precession rate per year is 360°/26000 years = 0.0138°/years.,True,e4fda0e7-b147-48fd-bcea-fbc007d2ee9b
@@ -77,3 +77,36 @@ What is the hyperbolic excess velocity?,"['The velocity required to get into a L
 "An interplanetary probe is in transit towards an inner planet, very close to the arrival planet. How is the velocity of the planet with respect to the velocity of the probe?","['faster', 'identifical', 'slower']","[0, 0, 1]","The transfer ellipse ressemble a Hohmann transfer to go from a high to a lower orbit, thus the velocity of the probe is higher than the arrival planet. When leaving the Earth, the probe should also reduce its heliocentric speed. This can be done by crossing the sphere of influence with the velocity vector of the spacecraft in the opposite direction of Earth's velocity vector.",True,e344b8fb-a2cc-42b2-979c-544644a2a5b0
 There is no burn during the slingshot maneuvers and yet the speed in the heliocentric reference frame increases. How is that possible?,"['At the periapsis of the slingshot, some massive object is jettisoned', 'An ion thruster is systematically switched on and this type of propulsion is only efficient in planetary neighborhood', 'The velocity vector of the probe is not changed in norm, but in direction in the planetocentric reference frame']","[0, 0, 1]","The norm of the velocity vector stays constant, there is no acceleration in the direction of the velocity vector. However, the direction of the trajectory of the spacecraft in the sphere of influence of the planet is a hyperbola. The direction of the velocity vector changes when the spacecraft is inside the sphere of influence.",True,6012cf0f-5cb3-440a-a35b-91c61539f393
 What can Gravity-assist be used for? (more than one answer possible),"['Increase the heliocentric velocity', 'Decrease the heliocentric velocity', 'Make communications between the probe and Earth easier', 'Explorations of ""worlds"" during the transit flight to the destination']","[1, 1, 0, 1]","The most common application of gravity assist is to increase the heliocentric velocity. However, it can be reduced if the direction of the spacecraft velocity vector is well chosen when entering the sphere of influence. Voyager and Pioneer probes took advantage of their multiple gravity assist maneuvers to explore and take close-up images of all the planets in our solar system. This was made possible due to a particularly favorable alignement of the planets.",True,bb3def0d-b962-4777-84f9-bdd55055516a
+"In space propulsion, what is true about the specific Impulse (Isp)?","['It is expressed in seconds', 'it changes with the gravity value g', 'it is an expression of the propulsion system efficiency', 'It is related to the exhaust velocity', 'It expresses the impact of the local gravity on the launcher capability to reach orbit.']","[1, 0, 1, 1, 0]",The Isp is related to the exhaust velocity by multiplying its value always by g=9.81. This relation is not dependant on the local value of the gravitational acceleration.,True,63bea71f-58f0-4e0a-a5c1-1ba58f8c927c
+There are various combinations of fuel and oxidizer which exist. Which combination gives the biggest Isp among the following?,"['LOX/LH2', 'N2H4/LOX', 'N2H4/N2O4', 'Kerosene/N2O4', 'MMH/N2O4']","[1, 0, 0, 0, 0]",The LH2/LOX mixture provides an Isp of ~450s in vacuum. It was used for the Space Shuttle main engine and for the Ariane 5 vulcain engine for instance.,True,19654539-bab9-49dc-96ce-3bf60d2aa5be
+Why is electric propulsion system more efficent than chemical propulsion?,"['It does not generate heat.', 'It produces a higher exhaust velocity.', 'Because of the recombination of ions and electrons to form neutral atoms.', 'Because of the production of electrodynamics shock waves at the exhaust.']","[0, 1, 0, 0]",,True,1397b4df-ea27-4305-9089-6292f6408abc
+In the process of Orbit insertion what does MECO refer to?,"['Micro-Elliptic Catapult Orbit', 'Main Engine Cut-Off', 'It does not mean anything relevant']","[0, 1, 0]",,True,9f48dd27-ffa4-4042-8bbd-b9ff30e365c4
+Which of the following statements are true?,"['LVLH is a coordinate system', 'LVLH is a french luxury clothing brand', 'LVLH is an inertial coordinate system', 'In the LVLH system, the z-axis points towards the center of the Earth', 'LVLH stands for Local Vertical, Local Horizontal.']","[1, 0, 0, 1, 1]","The LVLH, Local Vertical, Local Horizontal, is a local reference frame which is linked to the Earth's ground. x is in the direction of travel and z towards the center of the Earth.",True,bde40118-169c-4667-b624-b4742c2e3348
+"In orbital manoeuvres, is the order of the Euler sequence commutative? (i.e. can you inverse two or more rotations)","['Yes', 'No']","[0, 1]",,True,2c39dc9e-9e69-4c79-b23f-2c28cce8dd83
+How does a magnetic torquer work ?,"['The needle of a compass presses on the thruster button to correctly orient the spacecraft', ""A coil is wrapped around an elongated rod. An electrical current runs through the the coil generating a magnetic field which has the tendency to align itself with Earth's magnetic field"", 'Permanent magnets are placed at strategic places in the spacecraft, keeping it correctly oriented']","[0, 1, 0]",,True,b9b75cd4-9c1f-4195-b471-25be0cd57a14
+"Solar arrays should be oriented towards the Sun with a very low accuracy. The angle Theta from the normal of the solar array to the Sun, however, is directly linked to the power generated. Why is the requirement the pointing of the solar arrays to the Sun so loose?","['The power generated is proportional to sine of Theta', 'The power generated is proportional to the cosine of Theta', 'The individual solar cells can points each towards the exact direction of the sun', 'We cannot point a higher precision']","[0, 1, 0, 0]","cos(10°) ~ 0.985, still very close to 1, the supplementary computational, electrical and even consumable needed to increase the power generated by 1 point is not always worth the effort. This lessen also the constraints on the attitude of the spacecraft to give more possibilities to the payload.",True,554f161d-df31-425b-aaa6-c95ef48d9b48
+Select all propositons that applies to attitude maneuvers with thrusters,"['It is the most precise technique', 'It can be used to desaturate other attitude maneuver systems', '6 thrusters are needed to have pure rotations', 'A minimum of 12 thrusters are needed to have pure rotations', 'All thrusters systems need to have a ignition system']","[0, 1, 0, 1, 0]","Thruster is a very simple and quite crude method.
+Thrusters are used to desaturate reaction wheels.
+12 thrusters (4 per axis) are needed to be able to rotate and brake without translation.
+All thrusters systems don't need to have a ignition system:  for example MMH/N2O4 is a hypergolic reaction and does not need an ignition system. For mono-propellant thrusters, the Hydrazine is catalysed on a berilium substrat.",True,fc1295d7-07f9-4a04-b7d7-f0d9a27720df
+What is the fundamental principle that is used when working with rotation wheels?,"['Conservation of momentum', 'Conservation of angular momentum', 'Conservation of electric charge', 'Freedom']","[0, 1, 0, 0]","When the rotation wheel starts to rotate, the spacecraft will counter-rotate in order to conserve its total angular momentum, thanks to this, the attitude of a spacecraft can be modified",True,a4854768-4cb1-4483-a41e-e2565d01ebbc
+What was the main power source of the Space Shuttle?,"['Solar arrays', 'Fuel cells', 'Radioisotope Thermoelectric Generators (RTG)', 'Hamsters running in a wheel', 'Astronaut bicycle ergometer with a generator']","[0, 1, 0, 0, 0]",,True,d9a55108-1a19-48eb-9069-a847b7a02f0b
+A tether deployed from the Space Shuttle with a passive satellite at the end can be used as ...,"['Electrical Generator', 'Space elevator', 'Electrical motor', 'Dipole antenna']","[1, 0, 1, 0]",,True,b13d3f2d-ed82-43fc-a442-7276c41661d2
+Which effect dominates the forces on a tethered systems?,"['Drag disturbances', 'Radiation pressure', 'Gravity gradient', 'Collision with other spacecraft']","[0, 0, 1, 0]",A collision with another spacecraft is very unlikely. The dominant effect is the gravity gradient which tends to align the system along the orbital radius.,True,84b8c9af-0b86-4e27-b1c9-eeff18b5dcd5
+What elements were part of selected configuration of the Space Shuttle? (Select all that applies),"['An orbiter', 'A capsule', '3 main engines', 'Two solid rocket boosters', 'An external tank', 'A third stage']","[1, 0, 1, 1, 1, 0]",,True,102c8ce4-14c0-4b6b-a584-cdc889e6f12b
+During which year the Shuttle approach and landing tests took place?,"['1974', '1975', '1976', '1977', '1978']","[0, 0, 0, 1, 0]",,True,f16dafd8-ba8c-4f1f-992b-f5c46867e858
+Up to how many crew-members could participate in Space Shuttle Missions?,"['2', '5', '7', '10', '11']","[0, 0, 1, 0, 0]",,True,7809da4f-3612-4c97-b146-440b5425bca2
+Which abbreviations correspond to real Space Shuttle Missions? (Select all that applies),"['STS-1', 'STS-432', 'STS-75', 'STS-51L', 'STS-137', 'STS-118']","[1, 0, 1, 1, 0, 1]","STS-1 was the first Shuttle flight in 1981, STS-51L corresponds to the Challenger accident in 1986, STS-75 was Claude Nicollier's third flight in 1996 with a tethered satellite. The last Shuttle flight was STS-135 so STS-137 and STS-432 do not make sense.",True,6167effd-5661-488b-a91b-01856dc8a560
+What changes did occur after the Challenger accident? (Select all that applies),"['The design of some components of the Space Shuttle Transportation System was modified', 'Crew to the ISS were sent only with Soyuz spacecraft', 'The Launch and Entry Suit was introduced', 'The Shuttle was not used by the Department of Defense or for commercial flights', 'Nothing']","[1, 0, 1, 1, 0]",,True,e26b1a0e-e633-43a7-9191-84614aaaa4ee
+When did the ISS start to be assembled?,"['2001', '1995', '1998', '2011']","[0, 0, 1, 0]",,True,e5d95638-231a-474a-912a-c7880d3db90d
+"Which of the following vehicles were able to bring crews to the ISS, until 2011? (Select all that applies)","['Soyuz', 'Progress', 'Dragon', 'Space Shuttle', 'Shenzhou']","[1, 0, 0, 1, 0]","Only Soyuz spacecraft and the Space Shuttle were able to bring crews to the ISS. Shenzhou is the Chinese manned spacecraft which have been able to bring Chinese crews onboard the Chinese Space Station. Progress and Dragon are supply vehicles, not manned.",True,79d76e22-fdf1-4988-a33d-4eb00f028fb7
+What year did the first spacewalk take place?,"['1962', '1963', '1964', '1965']","[0, 0, 0, 1]","The first spacewalk, realized by Alexei Leonov, took place on March 18, 1965 during the Voskhod 2 mission and lasted for 12 minutes.",True,3f36e2d1-f565-4e93-a265-d47774d48919
+What new item was introduced in Apollo 15 to explore the Moon?,"['A second, scientific, deck to the LEM', 'A Lunar Roving Vehicle', 'A tent-like structure to analyze boulders', 'The spacesuits featured cold gas thrusters to fly small distances']","[0, 1, 0, 0]","The A Lunar Roving Vehicle called ""buggy"" was electrically powered and was driven on Apollo 15, 16 and 17, the last three flights. During Apollo 17, it was driven on the surface for more than 20 km!",True,df3bd299-9a98-41e0-910c-2bc81b057023
+Which of the following is NOT a branch within the European Cooperation for Space Standardization (ECSS) system?,"['Policy branch (P-branch)', 'System description branch (S-branch)', 'Environmental Sustainability branch (E-branch)', 'Configuration and information management branch (D-branch)']","[0, 0, 1, 0]","The ECSS system includes several branches that cover a wide range of standardization disciplines, but an Environmental Sustainability branch (E-branch) as described is not one of them. The actual E-branch within ECSS refers to the Engineering branch, which defines standard engineering processes and technical requirements for space systems. The ECSS space sustainability branch (U-branch), was initiated in 2012, and defines two disciplines: space debris mitigation and planetary protection.",True,e1cb1e26-e334-478b-9cdb-2a4786585402
+Which ECSS standard series focuses specifically on the product assurance aspects of space projects?,"['E-branch', 'S-branch', 'Q-branch', 'P-branch']","[0, 0, 1, 0]",The ECSS product assurance branch (Q-branch) defines the methods and requirements relevant to assure the safety and reliability of space products.,True,53550861-e6fe-46fb-ab3d-a059fda50de8
+The South Atlantic Anomaly (SAA) is an area where the Earth's inner Van Allen radiation belt comes closest to the Earth's surface. What does it lead to?,"['A screening from sun light.', 'A decreased flux of energetic particles.', 'An increased flux of energetic particles.', 'A high number of auroras.']","[0, 0, 1, 0]",It leads to an increased flux of energetic particles in this region and exposes orbiting satellites to higher than usual levels of radiation. The effect is caused by the non-concentricity of the Earth and its magnetic dipole.,True,d1daaa31-090c-450f-a947-5fbe99bdcf52
+What might be the effect of the impact of a cosmic ray with the onboard electronics? (More than one answer possible),"['Change the position of the satellite.', 'Create single event upsets.', 'Create single event latchups.', 'Cause the loss of performance of the system.']","[0, 1, 1, 1]","Single-event effects (SEE), mostly affecting only digital devices. When a high-energy particle travels through a semiconductor, it leaves an ionized track behind. This ionization may cause a highly localized effect. Single event upsets can be fixed by rebooting the system while single event latchups create a permanent localised failure, which in turn can result in loss of performance (that's why all electronic component are redundant on satellites).",True,96aee273-ea94-47ef-bb24-2748f7d7efae
+What causes the difference between the spectral irradiance at the top of the atmosphere and at sea level?,"['The passage of airplanes', 'The presence of water in the atmosphere', 'The presence of CO2', 'The high albedo (about 0.9) at the poles']","[0, 1, 1, 0]",A lot of the solar flux is absorbed by different molecules present in the atmosphere. Certain regions of the atmosphere (in the UV for example) are opaque as the water molecule absorb all the available energy at that wavelength.,True,5cbdcce5-5cb1-489e-8750-cf2778362dfa
+A probe is leaving the vicinity of Earth to fly to Mercury. Where will the solar panels generate the most power?,"['In the vicinity of Earth.', 'Mid-flight from the Earth to Mercury.', 'In the vicinity of Mercury.', 'The distance to the Sun does not matter.']","[0, 0, 1, 0]","The solar irradiance decreases with the square of the distance to the Sun. Closer objects will receive more solar flux, thus more power is generated in the vicinity of Mercury than in the vicinity of Earth.",True,04ac75a0-ba3b-4c49-bf33-8105794ad710
+The Earth receives an almost constant flux from the Sun of S = 1361 W/m^2. Which of the following is correct?,"['All the energy received is funnelled to the core of the Earth to keep it at a constant temperature.', 'The Earth reflects most of the energy received and is kept in its thermal equilibrium by the heat source in its core.', 'The Earth is in constant shadow due to the multitude of satellites that orbit, such that it is in thermal equilibrium.', 'The Earth is in thermal equilibrium because some of the heat received is reflected back to space and the Earth radiates away energy, mostly in the IR.']","[0, 0, 0, 1]",There is an Earth energy budget. The input of energy are the Sun irradiance and the internal energy provided by the molten core. Some of the energy of the Sun is immediately reflected off the surface (via the albedo coefficient) and another output is the black body radiation of the Earth that peaks in the IR.,True,a59daf71-d948-4d60-b7a4-ace8e86205b3
+The exterior of a satellite must be covered with a coating. What would be the best choice such that the temperature of the satellite is the lowest possible?,"['Gold (alpha = 0.299, epsilon = 0.023)', 'White Epoxy (alpha = 0.248, epsilon = 0.924)', 'Titanium (alpha = 0.448, epsilon = 0.129)', 'Aluminum (alpha = 0.379, epsilon = 0.0346)']","[0, 1, 0, 0]","The best coating is the one that has the lowest alpha/epsilon ratio, because alpha describes the ability of the material to absorb heat while epsilon describes the capacity to radiate heat away. Among the proposed materials white epoxy is the best choice here. It has an alpha/epsilon ratio of about 0.27.",True,2afb1154-4608-47bd-9176-2b3503a1e8a6