dataset update

astro-mcqa.csv

@@ -31,11 +31,7 @@ The International Space Station (ISS) is placed on an elliptical orbit around th
 "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.
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-The harpoon mechanism which was supposed to secure the lander failed and it bounced off the comet.
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-Assuming purely elastic impact, will the lander leave the comet or return at some point?","['For sure, the lander is lost.', ""The lander's chances are fair, but there is a significant risk."", 'All is good, not to worry, Philae will come down for sure.']","[0, 1, 0]",,True,6570bf60-a707-4f9b-ad31-d7bf390a306f
+"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. The harpoon mechanism which was supposed to secure the lander failed and it bounced off the comet. Assuming purely elastic impact, will the lander leave the comet or return at some point?","['For sure, the lander is lost.', ""The lander's chances are fair, but there is a significant risk."", 'All is good, not to worry, Philae will come down for sure.']","[0, 1, 0]",,True,6570bf60-a707-4f9b-ad31-d7bf390a306f
 Telecommunications satellites are often on geostationary orbits (GEO) at an altitude of 35786 km above the surface of the Earth. What is the Earth escape velocity from that orbit? (answer in km/s),"['4.7', '5.0', '5.3', '5.6', '5.9']","[1, 0, 0, 0, 0]",,True,cfaa1256-9ed3-460b-b6d4-2a79e2b335f2
 "Which formula gives the work to be performed in order to bring a unit mass from the Earth's surface to infinity? Assume that g0 is the standard gravitational acceleration for the surface of the Earth, R is the radius of the Earth, and p the atmospheric pressure.","['g0 * R * p^2', 'g0 * R * p', 'g0 * R', 'g0 * R^2']","[0, 0, 1, 0]",,True,bef97b27-a677-488c-9088-b835c0f3d1a8
 "What is the formula to compute the escape velocity given mu (standard gravitational parameter), and r (the distance to the center of the central body)?","['V = mu * r', 'V = sqrt( 2 * mu / r^3 )', 'V = sqrt( mu / r )', 'V = sqrt( 2 * mu / r )', 'V = sqrt( mu / 2r )']","[0, 0, 0, 1, 0]",,True,57080b4d-b331-4816-985f-c76f499662f6
@@ -67,8 +63,7 @@ What is the effect of a posigrade burn on a circular orbit?,"['There is no effec
 What is the reference point of the rendezvous profile diagram?,"['The chaser', 'The target', 'The center of the Earth', 'The control center']","[0, 1, 0, 0]",The rendezvous profile diagram is centered and relative to the target.,True,a28c168f-3f6a-4edb-b0c0-2ae974963858
 "What is the shape of a circular orbit, for the chaser, in a rendezvous profile diagram? (assuming the target is higher than the chaser).","['A point', 'A periodic wavy and pointy curve', 'A line', 'A sinusoidal', 'A cycloid']","[0, 0, 1, 0, 0]","On a circular orbit, the altitude does not change, so the value of the R axis does not change. The V axis does not stay the same as the velocity of the two spacecraft are not the same. The chaser will move along an horizontal line in the diagram.",True,e8b2cae4-92f6-48e6-9436-c5f33a5ac832
 A spacecraft on a circular orbit at 400 km does a retrograde burn of 1 m/s. What will be the change in the altitude (in km) of the perigee?,"['1.5', '2.5', '3.5', '4.5']","[0, 0, 1, 0]",This can be computed in a straightforward way using the equation Delta-r is close to 3.5 * Delta-V where Delta-r is in km and the burn value in m/s.,True,61e3c07e-fd5e-4429-aeb1-66afe0919eda
-"A chaser is on a circular orbit at the same altitude as the target and few kilometers behind.
-Where will the chaser be one orbit after a posigrade burn ?","['The chaser will be much further ahead', 'The chaser will be behind the target, further away than it was initally', 'The chaser will be higher than the target', 'The chaser will be lower than the target']","[0, 1, 0, 0]","Since there is a posigrade burn, the altitude of the semi-major axis is increased, the orbital velocity is decreased. If the change of altitude is sufficient, the chaser will drift behind the target further away than it was initially.",True,9fc96902-8398-4630-b53b-6d3049c8254e
+A chaser is on a circular orbit at the same altitude as the target and few kilometers behind. Where will the chaser be one orbit after a posigrade burn ?,"['The chaser will be much further ahead', 'The chaser will be behind the target, further away than it was initally', 'The chaser will be higher than the target', 'The chaser will be lower than the target']","[0, 1, 0, 0]","Since there is a posigrade burn, the altitude of the semi-major axis is increased, the orbital velocity is decreased. If the change of altitude is sufficient, the chaser will drift behind the target further away than it was initially.",True,9fc96902-8398-4630-b53b-6d3049c8254e
 What is the definition of the Astronomical Unit (AU)?,"['It is the average distance between the Earth and the Sun', 'It is the average radius of the solar system', 'It is the average radius of the Sun', 'It is the average distance betwteen the Moon and the Earth']","[1, 0, 0, 0]","An Astronomical Unit is the mean distance between the Earth and the Sun. In 2012, the International Astronomical Union defined the distance to be 149,597,870,700 meters.",True,3fedeb91-5ab5-45de-be70-a2ce8ad59e10
 What is the sphere of influence?,"['A region in space that can be controlled by a spacecraft', 'The region around the Sun in which only planets have a gravitational influence', 'A sphere around each planet inside which the motion of a spacecraft must be considered a three-body Keplerian problem', 'A sphere around each planet inside which the motion of a spacecraft is considered to be two-body Keplerian']","[0, 0, 0, 1]","For the Earth, the radius of the sphere of influence is about 924 000 km.",True,6a0ff5bb-46cb-4b10-a12b-4573589bb59f
 What is the hyperbolic excess velocity?,"['The velocity required to get into a LEO orbit from the surface of the Earth', 'The velocity at which we cross the sphere of influence', 'The velocity needed to reach the arriving planet', 'The velocity needed to reach the sphere of influence']","[0, 1, 0, 0]",It is the speed in excess of the minimum velocity required to reach the sphere of influence.,True,f274dd2f-9811-4424-abca-f3c6e4c61bd8
@@ -110,3 +105,6 @@ What causes the difference between the spectral irradiance at the top of the atm
 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
+"Which modulation method can have a combination of 2 bits per symbol, a code rate of 0.5 and a spectral efficiency of about 1.0","['BPSK', 'QPSK', '8-PSK', '16-PSK']","[0, 1, 0, 0]",,True,caf7a503-ce34-4d2e-a11a-a8eec2b04dbc
+Which of the following statements are true about Precipitation Losses for Communication Link Analysis?,"['precipitation losses attenuates RF signals by absorption', 'precipitation losses attenuates RF signals by scattering (depolarization)', 'Geographic databases of rainfall are needed for link analysis', 'precipitation losses are inversely proportional to the humidity in the atmosphere']","[1, 1, 1, 0]","Precipitation in the form of rain and wet snow attenuates RF signals through both absorption and scattering (depolarization). Precipitation-induced losses are dependent upon the product of a rate-dependent attenuation coefficient and the path length that the RF signals are required to traverse through rainfall regions within the atmosphere. Because losses are a function of the concentration of water in the atmosphere, precipitation-induced losses are heavily dependent upon a geographic and seasonal variation in weather. To provide a means for predicting rain precipitation effects, the ITU has created a geographic database of rainfall rates. This helps for link analysis.",True,61719260-46e9-444f-875e-8ea04e07f2bf
+Which of the following influence the total power at the receive amplifier in communication link analyses?,"['EIRP, the Equivalent Isotropic Radiated Power', 'mu, the Standard gravitational parameter', 'Ls, the Free-Space Losses', 'Lin, the input losses to the receiver', 'Ltx, the transmitter pointing losses', 'Na, the avogadro number']","[1, 0, 1, 1, 1, 0]","The total power at the receive amplifier can be expressed as C = EIRP + Gr - Ls - Latm - Lprec - Lin - Ltx - Lrx where EIRP is the Equivalent Isotropic Radiated Power, Gr is the gain of the receive antenna, Ls are the free-space losses, Latm and Lprec are the losses due to the atmosphere and precipitation, Lin the input losses to the receiver, Ltx the transmitter pointing losses, and Lrx the depointing losses of the receiver. The standard gravitational parameter has to do with orbital mechanics but not with communication link analysis and the avogadro number is used in chemistry, not in this context.",True,8a4c5031-a489-4d16-95b6-1049aa4806a3