dataset update

astro-mcqa.csv

@@ -153,3 +153,35 @@ Which are the most common power bus control techniques used in satellite electri
 Which of the following buck-boost derived regulator is the most complex among the following?,"['Full Bridge Regulator', 'Flyback', 'Two-switch Forward']","[1, 0, 0]","From least complex to most complex are the flyback, single switch forward, two switch forward, push-pull, and full-bridge regulators",True,ea3c5ee5-1439-4e00-9555-026fc3c8837f
 Which technique used on spacecraft power regulators (buck-boost) enables to further enhance their efficiency?,"['Resonant Mode Switching', 'Continuous Current Calibration', 'Voltage Ripple Reduction']","[1, 0, 0]",,True,dda35b83-c23f-4682-b89c-b4d217366785
 Which of the following power source in spacecraft design usually require storage in case of Eclipse?,"['Fuell cells', 'Nuclear reactor', 'Radioistope Thermoelectric Generator', 'Solar Thermal Dynamic', 'Solar Photovoltaic']","[0, 0, 0, 1, 1]",Both solar thermal dynamic and solar photovoltaic do not generate power during eclipse so storage is require to keep the satellite powered on.,True,8d14f358-de2e-46fa-8eb2-26edb2eee900
+Which of these statements are true of solid rockets?,"['They are relatively simple to build and operate', 'They provide limited ability to control thrust', 'They inherently produce more thrust than liquid rockets', 'They generate a lot of noise and vibration']","[1, 1, 0, 1]",,True,6a41ebbc-8a34-4036-a1b0-8507b0164ac1
+Which of these statements are true of liquid rockets? Tell all that apply.,"['They inherently produce less thrust than solid rockets', 'They must store the oxidizer and fuel propellant components onboard in separate compartments', 'To get high performance, they must use turbo pumps to direct the propellant into the combustion chamber', 'They encounter high temperatures and pressures during combustion']","[0, 1, 1, 1]",,True,10f3799c-63b3-4154-af37-bb371b1fee35
+"When applying the idea rocket equation, which components usually comprise the the rocket initial mass ?","['Payload', 'Propellant', 'Structure']","[1, 1, 1]","The initial mass at launch consists of payload, propellant, and rocket structure. The final mass refers to when the propellant has been consumed, and thus consists of payload and structure.",True,195bc8ba-e67d-435d-b384-7d23ecc1e3c8
+"When applying the idea rocket equation, which components usually comprise the the rocket final mass ?","['Payload', 'Propellant', 'Structure']","[1, 0, 1]","The initial mass at launch consists of payload, propellant, and rocket structure. The final mass refers to when the propellant has been consumed, and thus consists of payload and structure.",True,85b1737f-ce24-40eb-9cac-71220489ded7
+"Consider a rocket in free space having two engines with identical Isp, connected to a single propellant system. Recall that the relationship between specific impulse and exhaust velocity is  Vexhaust  = go * Isp.
+If one engine fails, what is the impact on the total  ΔV  that can be obtained from the system?","['ΔV will double', 'ΔV will be cut in half', 'ΔV will stay the same']","[0, 0, 1]","If one engine fails, there is no change in specific impulse, or in the total amount of propellant available. Therefore, the total ΔV that is obtainable from the system is the same. However, the thrust is cut in half, so it will take twice as long to achieve the same ΔV (until the propellant is consumed).",True,9c2d1b44-c462-4db4-9664-7625b8b054c6
+"Consider a rocket carrying 100,000 kg of propellant, 10,000 kg of structure and 5,000 kg of payload. What is the structure fraction of this rocket?","['0.053', '0.075', '0.087', '0.019']","[0, 0, 1, 0]","The structure fraction is given by the ration of the mass of the structure (10,000 kg) divided by the sum of the structure, payload and propellant (100,000 + 10,000 + 5,000). The result is 10,000 / 115,000 which is approximately 0.087.",True,655147dd-fc22-4c82-a964-a234ef65c2b7
+"Consider a rocket carrying 100,000 kg of propellant, 10,000 kg of structure and 5,000 kg of payload. Using the ideal rocket equation, and assuming a specific impulse of 450s, what would be value of the Delta V in m/s that this rocket would be able to produce if all the propellant is consumed in one stage?","['8991 m/s', '9991 m/s', '10991 m/s', '11991 m/s', '12991 m/s']","[1, 0, 0, 0, 0]","The ideal rocket equation gives ΔV = g0 * Isp * ln(mass_initial / mass_final).
+g0 = 9.81 m/s^2
+Isp = 450 s
+We need to compute the initial mass of the rocket and the final mass of the rocket.
+
+1. Initial mass of the rocket:
+initial_mass = payload_mass + structure_mass + propellant_mass = 5,000 + 10,000 + 100,000 = 115,000 kg.
+
+2. Final mass of the rocket (everything except the propellant that has been burnt)
+final_mass = payload_mass + structure_mass = 5,000 + 10,000 = 15,000 kg
+
+ΔV = 9.81 * 450 * ln( 115,000 / 15,000) = 8991 m/s",True,830a0d7a-0ce6-4c92-9a65-e7599ac1b700
+What would be the Delta V in m/s of the first stage of a rocket under the following conditions?,"['1519', '2519', '3519', '4519', '5519']","[0, 1, 0, 0, 0]","The ideal rocket equation gives ΔV = g0 * Isp * ln(mass_initial / mass_final).
+g0 = 9.81 m/s^2
+Isp = 450 s
+We need to compute the initial mass of the rocket and the final mass of the rocket.
+
+1. Initial mass of the rocket before the first stage has brunt (all the propellant is remaining)
+initial_mass = payload_mass + structure_mass + propellant_mass = 5,000 + 10,000 + 100,000 = 115,000 kg.
+
+2. Final mass of the rocket after first stage burnt (everything is included except the half of the propellant that has been burnt)
+final_mass = payload_mass + structure_mass = 5,000 + 10,000  + 100,000/2 = 65,000 kg
+
+ ΔV = g0 * Isp * ln(115,000 / 65,000) = 2519 m/s",True,3cd7b8d6-030b-491f-a92a-85afac24d921
+"What Delta V can be achieve by the second stage of a rocket, after first stage has been jettisoned and under the following assumptions?","['6910 m/s', '7910 m/s', '8910 m/s', '9910 m/s']","[0, 1, 0, 0]",,True,493d3084-22a2-475c-8227-aeba4bae1c27