id
int64 0
199
| uid
stringlengths 36
36
| question
stringlengths 17
437
| permutation_idx
int64 0
2
| choices
listlengths 3
6
| labels
listlengths 3
6
| prompt
stringlengths 72
709
| expected_output
stringlengths 4
285
|
|---|---|---|---|---|---|---|---|
139
|
c2bd96c1-08db-4bb3-bdc0-67097d6f174c
|
How it is possible to maintain a certain orientation by spinning a spacecraft?
| 1
|
[
"Due to the electron spin",
"Due to the rotational speed being waved",
"Due to the gyroscopic effect"
] |
[
0,
0,
1
] |
How it is possible to maintain a certain orientation by spinning a spacecraft?
A. Due to the electron spin
B. Due to the rotational speed being waved
C. Due to the gyroscopic effect
|
C. Due to the gyroscopic effect
|
139
|
c2bd96c1-08db-4bb3-bdc0-67097d6f174c
|
How it is possible to maintain a certain orientation by spinning a spacecraft?
| 2
|
[
"Due to the gyroscopic effect",
"Due to the rotational speed being waved",
"Due to the electron spin"
] |
[
1,
0,
0
] |
How it is possible to maintain a certain orientation by spinning a spacecraft?
A. Due to the gyroscopic effect
B. Due to the rotational speed being waved
C. Due to the electron spin
|
A. Due to the gyroscopic effect
|
140
|
b185c125-a603-4e68-97bf-796ee0dd929a
|
How is it possible to use gravity gradient for attitude control?
| 0
|
[
"For an elongated object, the gravity force at the bottom of the object is greater than the force at the top",
"For a spherical rotating object, the gravity at the bottom of the sphere is greater than the gravity at the top",
"For an elongated object, the gravity force at the top of the object is greater than the force at the bottom",
"For a spherical rotating object, the gravity gradient originates from the fluid forces momentum in the intern structure."
] |
[
1,
0,
0,
0
] |
How is it possible to use gravity gradient for attitude control?
A. For an elongated object, the gravity force at the bottom of the object is greater than the force at the top
B. For a spherical rotating object, the gravity at the bottom of the sphere is greater than the gravity at the top
C. For an elongated object, the gravity force at the top of the object is greater than the force at the bottom
D. For a spherical rotating object, the gravity gradient originates from the fluid forces momentum in the intern structure.
|
A. For an elongated object, the gravity force at the bottom of the object is greater than the force at the top
|
140
|
b185c125-a603-4e68-97bf-796ee0dd929a
|
How is it possible to use gravity gradient for attitude control?
| 1
|
[
"For a spherical rotating object, the gravity gradient originates from the fluid forces momentum in the intern structure.",
"For an elongated object, the gravity force at the bottom of the object is greater than the force at the top",
"For a spherical rotating object, the gravity at the bottom of the sphere is greater than the gravity at the top",
"For an elongated object, the gravity force at the top of the object is greater than the force at the bottom"
] |
[
0,
1,
0,
0
] |
How is it possible to use gravity gradient for attitude control?
A. For a spherical rotating object, the gravity gradient originates from the fluid forces momentum in the intern structure.
B. For an elongated object, the gravity force at the bottom of the object is greater than the force at the top
C. For a spherical rotating object, the gravity at the bottom of the sphere is greater than the gravity at the top
D. For an elongated object, the gravity force at the top of the object is greater than the force at the bottom
|
B. For an elongated object, the gravity force at the bottom of the object is greater than the force at the top
|
140
|
b185c125-a603-4e68-97bf-796ee0dd929a
|
How is it possible to use gravity gradient for attitude control?
| 2
|
[
"For an elongated object, the gravity force at the top of the object is greater than the force at the bottom",
"For a spherical rotating object, the gravity at the bottom of the sphere is greater than the gravity at the top",
"For an elongated object, the gravity force at the bottom of the object is greater than the force at the top",
"For a spherical rotating object, the gravity gradient originates from the fluid forces momentum in the intern structure."
] |
[
0,
0,
1,
0
] |
How is it possible to use gravity gradient for attitude control?
A. For an elongated object, the gravity force at the top of the object is greater than the force at the bottom
B. For a spherical rotating object, the gravity at the bottom of the sphere is greater than the gravity at the top
C. For an elongated object, the gravity force at the bottom of the object is greater than the force at the top
D. For a spherical rotating object, the gravity gradient originates from the fluid forces momentum in the intern structure.
|
C. For an elongated object, the gravity force at the bottom of the object is greater than the force at the top
|
141
|
57f57993-5f84-46b7-82ab-37aba7f12d70
|
Which of the following is the primary factor determine the voltage of a solar array?
| 0
|
[
"The number of cells connected in series to form a string",
"The mounting structure of the solar cell",
"The temperature of the environment where the solar array is in",
"The solar cell thickness"
] |
[
1,
0,
0,
0
] |
Which of the following is the primary factor determine the voltage of a solar array?
A. The number of cells connected in series to form a string
B. The mounting structure of the solar cell
C. The temperature of the environment where the solar array is in
D. The solar cell thickness
|
A. The number of cells connected in series to form a string
|
141
|
57f57993-5f84-46b7-82ab-37aba7f12d70
|
Which of the following is the primary factor determine the voltage of a solar array?
| 1
|
[
"The solar cell thickness",
"The number of cells connected in series to form a string",
"The mounting structure of the solar cell",
"The temperature of the environment where the solar array is in"
] |
[
0,
1,
0,
0
] |
Which of the following is the primary factor determine the voltage of a solar array?
A. The solar cell thickness
B. The number of cells connected in series to form a string
C. The mounting structure of the solar cell
D. The temperature of the environment where the solar array is in
|
B. The number of cells connected in series to form a string
|
141
|
57f57993-5f84-46b7-82ab-37aba7f12d70
|
Which of the following is the primary factor determine the voltage of a solar array?
| 2
|
[
"The number of cells connected in series to form a string",
"The solar cell thickness",
"The temperature of the environment where the solar array is in",
"The mounting structure of the solar cell"
] |
[
1,
0,
0,
0
] |
Which of the following is the primary factor determine the voltage of a solar array?
A. The number of cells connected in series to form a string
B. The solar cell thickness
C. The temperature of the environment where the solar array is in
D. The mounting structure of the solar cell
|
A. The number of cells connected in series to form a string
|
142
|
ca57a7ff-3145-4c26-ad77-1e8b1ce2fcb1
|
Which of the following time point is used to size a satellite photovoltaic system?
| 0
|
[
"Average life power requirements plus a 10 to 20 margin",
"Beginning-of-life power requirements",
"End-of-life power requirements"
] |
[
0,
0,
1
] |
Which of the following time point is used to size a satellite photovoltaic system?
A. Average life power requirements plus a 10 to 20 margin
B. Beginning-of-life power requirements
C. End-of-life power requirements
|
C. End-of-life power requirements
|
142
|
ca57a7ff-3145-4c26-ad77-1e8b1ce2fcb1
|
Which of the following time point is used to size a satellite photovoltaic system?
| 1
|
[
"Beginning-of-life power requirements",
"End-of-life power requirements",
"Average life power requirements plus a 10 to 20 margin"
] |
[
0,
1,
0
] |
Which of the following time point is used to size a satellite photovoltaic system?
A. Beginning-of-life power requirements
B. End-of-life power requirements
C. Average life power requirements plus a 10 to 20 margin
|
B. End-of-life power requirements
|
142
|
ca57a7ff-3145-4c26-ad77-1e8b1ce2fcb1
|
Which of the following time point is used to size a satellite photovoltaic system?
| 2
|
[
"End-of-life power requirements",
"Beginning-of-life power requirements",
"Average life power requirements plus a 10 to 20 margin"
] |
[
1,
0,
0
] |
Which of the following time point is used to size a satellite photovoltaic system?
A. End-of-life power requirements
B. Beginning-of-life power requirements
C. Average life power requirements plus a 10 to 20 margin
|
A. End-of-life power requirements
|
143
|
848d888b-d844-46ad-a5db-7b9fbaf9cb93
|
Which of the following are the lower costs cells that could be in use for satellite solar arrays?
| 0
|
[
"Thin film amorphous Silicon cells",
"Gallium-Arsenide Triple Junction cells",
"Indium Phosphide cells"
] |
[
1,
0,
0
] |
Which of the following are the lower costs cells that could be in use for satellite solar arrays?
A. Thin film amorphous Silicon cells
B. Gallium-Arsenide Triple Junction cells
C. Indium Phosphide cells
|
A. Thin film amorphous Silicon cells
|
143
|
848d888b-d844-46ad-a5db-7b9fbaf9cb93
|
Which of the following are the lower costs cells that could be in use for satellite solar arrays?
| 1
|
[
"Thin film amorphous Silicon cells",
"Indium Phosphide cells",
"Gallium-Arsenide Triple Junction cells"
] |
[
1,
0,
0
] |
Which of the following are the lower costs cells that could be in use for satellite solar arrays?
A. Thin film amorphous Silicon cells
B. Indium Phosphide cells
C. Gallium-Arsenide Triple Junction cells
|
A. Thin film amorphous Silicon cells
|
143
|
848d888b-d844-46ad-a5db-7b9fbaf9cb93
|
Which of the following are the lower costs cells that could be in use for satellite solar arrays?
| 2
|
[
"Indium Phosphide cells",
"Gallium-Arsenide Triple Junction cells",
"Thin film amorphous Silicon cells"
] |
[
0,
0,
1
] |
Which of the following are the lower costs cells that could be in use for satellite solar arrays?
A. Indium Phosphide cells
B. Gallium-Arsenide Triple Junction cells
C. Thin film amorphous Silicon cells
|
C. Thin film amorphous Silicon cells
|
144
|
f84011f6-edb0-4748-ba0d-c5a01d1bee78
|
Which of the following rechargeable battery technologies used for satellite has the higher energy density?
| 0
|
[
"Li-ion",
"Ni-H2",
"Ni-Cd"
] |
[
1,
0,
0
] |
Which of the following rechargeable battery technologies used for satellite has the higher energy density?
A. Li-ion
B. Ni-H2
C. Ni-Cd
|
A. Li-ion
|
144
|
f84011f6-edb0-4748-ba0d-c5a01d1bee78
|
Which of the following rechargeable battery technologies used for satellite has the higher energy density?
| 1
|
[
"Li-ion",
"Ni-Cd",
"Ni-H2"
] |
[
1,
0,
0
] |
Which of the following rechargeable battery technologies used for satellite has the higher energy density?
A. Li-ion
B. Ni-Cd
C. Ni-H2
|
A. Li-ion
|
144
|
f84011f6-edb0-4748-ba0d-c5a01d1bee78
|
Which of the following rechargeable battery technologies used for satellite has the higher energy density?
| 2
|
[
"Ni-H2",
"Li-ion",
"Ni-Cd"
] |
[
0,
1,
0
] |
Which of the following rechargeable battery technologies used for satellite has the higher energy density?
A. Ni-H2
B. Li-ion
C. Ni-Cd
|
B. Li-ion
|
145
|
4efab579-4b0a-4647-9dff-4aaaf6f12713
|
Assuming a similar lifetime, and temperature maintained range, which of the following orbit would enable to use secondary batteries with a higher depth of discharge?
| 0
|
[
"Geostationary Orbit mission",
"Low-Earth Equatorial Orbit mission",
"Sun-Synchronous Polar Orbit mission"
] |
[
1,
0,
0
] |
Assuming a similar lifetime, and temperature maintained range, which of the following orbit would enable to use secondary batteries with a higher depth of discharge?
A. Geostationary Orbit mission
B. Low-Earth Equatorial Orbit mission
C. Sun-Synchronous Polar Orbit mission
|
A. Geostationary Orbit mission
|
145
|
4efab579-4b0a-4647-9dff-4aaaf6f12713
|
Assuming a similar lifetime, and temperature maintained range, which of the following orbit would enable to use secondary batteries with a higher depth of discharge?
| 1
|
[
"Low-Earth Equatorial Orbit mission",
"Geostationary Orbit mission",
"Sun-Synchronous Polar Orbit mission"
] |
[
0,
1,
0
] |
Assuming a similar lifetime, and temperature maintained range, which of the following orbit would enable to use secondary batteries with a higher depth of discharge?
A. Low-Earth Equatorial Orbit mission
B. Geostationary Orbit mission
C. Sun-Synchronous Polar Orbit mission
|
B. Geostationary Orbit mission
|
145
|
4efab579-4b0a-4647-9dff-4aaaf6f12713
|
Assuming a similar lifetime, and temperature maintained range, which of the following orbit would enable to use secondary batteries with a higher depth of discharge?
| 2
|
[
"Sun-Synchronous Polar Orbit mission",
"Geostationary Orbit mission",
"Low-Earth Equatorial Orbit mission"
] |
[
0,
1,
0
] |
Assuming a similar lifetime, and temperature maintained range, which of the following orbit would enable to use secondary batteries with a higher depth of discharge?
A. Sun-Synchronous Polar Orbit mission
B. Geostationary Orbit mission
C. Low-Earth Equatorial Orbit mission
|
B. Geostationary Orbit mission
|
146
|
a95ff8d7-d775-4602-a2b9-52aa613af262
|
Which of the following are typical ranges of load input power requirements in satellite engineering?
| 0
|
[
"Normal Steady State Voltage Range: 25 to 21 V DC",
"Normal Steady State Voltage Range: 5 to 7 V DC",
"Nominal Ripple 1 V peak to peak",
"Max Current 60 Amp",
"Normal Steady State Voltage Range: 150 to 220 V DC"
] |
[
1,
0,
1,
0,
0
] |
Which of the following are typical ranges of load input power requirements in satellite engineering?
A. Normal Steady State Voltage Range: 25 to 21 V DC
B. Normal Steady State Voltage Range: 5 to 7 V DC
C. Nominal Ripple 1 V peak to peak
D. Max Current 60 Amp
E. Normal Steady State Voltage Range: 150 to 220 V DC
|
A. Normal Steady State Voltage Range: 25 to 21 V DC
C. Nominal Ripple 1 V peak to peak
|
146
|
a95ff8d7-d775-4602-a2b9-52aa613af262
|
Which of the following are typical ranges of load input power requirements in satellite engineering?
| 1
|
[
"Max Current 60 Amp",
"Nominal Ripple 1 V peak to peak",
"Normal Steady State Voltage Range: 25 to 21 V DC",
"Normal Steady State Voltage Range: 5 to 7 V DC",
"Normal Steady State Voltage Range: 150 to 220 V DC"
] |
[
0,
1,
1,
0,
0
] |
Which of the following are typical ranges of load input power requirements in satellite engineering?
A. Max Current 60 Amp
B. Nominal Ripple 1 V peak to peak
C. Normal Steady State Voltage Range: 25 to 21 V DC
D. Normal Steady State Voltage Range: 5 to 7 V DC
E. Normal Steady State Voltage Range: 150 to 220 V DC
|
B. Nominal Ripple 1 V peak to peak
C. Normal Steady State Voltage Range: 25 to 21 V DC
|
146
|
a95ff8d7-d775-4602-a2b9-52aa613af262
|
Which of the following are typical ranges of load input power requirements in satellite engineering?
| 2
|
[
"Max Current 60 Amp",
"Normal Steady State Voltage Range: 150 to 220 V DC",
"Normal Steady State Voltage Range: 5 to 7 V DC",
"Normal Steady State Voltage Range: 25 to 21 V DC",
"Nominal Ripple 1 V peak to peak"
] |
[
0,
0,
0,
1,
1
] |
Which of the following are typical ranges of load input power requirements in satellite engineering?
A. Max Current 60 Amp
B. Normal Steady State Voltage Range: 150 to 220 V DC
C. Normal Steady State Voltage Range: 5 to 7 V DC
D. Normal Steady State Voltage Range: 25 to 21 V DC
E. Nominal Ripple 1 V peak to peak
|
D. Normal Steady State Voltage Range: 25 to 21 V DC
E. Nominal Ripple 1 V peak to peak
|
147
|
7bff3a67-9181-48dd-811b-48ca49851e30
|
Which are the most common power bus control techniques used in satellite electrical power subsystems?
| 0
|
[
"Alternating Current Frequency Adjustment (ACFA)",
"Voltage Multiplication Regulation (VMR)",
"Capacitive Load Stabilization (CLS)",
"Peak Power Tracker (PPT)",
"Direct Energy Transfer (DET)"
] |
[
0,
0,
0,
1,
1
] |
Which are the most common power bus control techniques used in satellite electrical power subsystems?
A. Alternating Current Frequency Adjustment (ACFA)
B. Voltage Multiplication Regulation (VMR)
C. Capacitive Load Stabilization (CLS)
D. Peak Power Tracker (PPT)
E. Direct Energy Transfer (DET)
|
D. Peak Power Tracker (PPT)
E. Direct Energy Transfer (DET)
|
147
|
7bff3a67-9181-48dd-811b-48ca49851e30
|
Which are the most common power bus control techniques used in satellite electrical power subsystems?
| 1
|
[
"Peak Power Tracker (PPT)",
"Voltage Multiplication Regulation (VMR)",
"Direct Energy Transfer (DET)",
"Alternating Current Frequency Adjustment (ACFA)",
"Capacitive Load Stabilization (CLS)"
] |
[
1,
0,
1,
0,
0
] |
Which are the most common power bus control techniques used in satellite electrical power subsystems?
A. Peak Power Tracker (PPT)
B. Voltage Multiplication Regulation (VMR)
C. Direct Energy Transfer (DET)
D. Alternating Current Frequency Adjustment (ACFA)
E. Capacitive Load Stabilization (CLS)
|
A. Peak Power Tracker (PPT)
C. Direct Energy Transfer (DET)
|
147
|
7bff3a67-9181-48dd-811b-48ca49851e30
|
Which are the most common power bus control techniques used in satellite electrical power subsystems?
| 2
|
[
"Alternating Current Frequency Adjustment (ACFA)",
"Voltage Multiplication Regulation (VMR)",
"Capacitive Load Stabilization (CLS)",
"Direct Energy Transfer (DET)",
"Peak Power Tracker (PPT)"
] |
[
0,
0,
0,
1,
1
] |
Which are the most common power bus control techniques used in satellite electrical power subsystems?
A. Alternating Current Frequency Adjustment (ACFA)
B. Voltage Multiplication Regulation (VMR)
C. Capacitive Load Stabilization (CLS)
D. Direct Energy Transfer (DET)
E. Peak Power Tracker (PPT)
|
D. Direct Energy Transfer (DET)
E. Peak Power Tracker (PPT)
|
148
|
ea3c5ee5-1439-4e00-9555-026fc3c8837f
|
Which of the following buck-boost derived regulator is the most complex among the following?
| 0
|
[
"Flyback",
"Full Bridge Regulator",
"Two-switch Forward"
] |
[
0,
1,
0
] |
Which of the following buck-boost derived regulator is the most complex among the following?
A. Flyback
B. Full Bridge Regulator
C. Two-switch Forward
|
B. Full Bridge Regulator
|
148
|
ea3c5ee5-1439-4e00-9555-026fc3c8837f
|
Which of the following buck-boost derived regulator is the most complex among the following?
| 1
|
[
"Two-switch Forward",
"Full Bridge Regulator",
"Flyback"
] |
[
0,
1,
0
] |
Which of the following buck-boost derived regulator is the most complex among the following?
A. Two-switch Forward
B. Full Bridge Regulator
C. Flyback
|
B. Full Bridge Regulator
|
148
|
ea3c5ee5-1439-4e00-9555-026fc3c8837f
|
Which of the following buck-boost derived regulator is the most complex among the following?
| 2
|
[
"Full Bridge Regulator",
"Flyback",
"Two-switch Forward"
] |
[
1,
0,
0
] |
Which of the following buck-boost derived regulator is the most complex among the following?
A. Full Bridge Regulator
B. Flyback
C. Two-switch Forward
|
A. Full Bridge Regulator
|
149
|
dda35b83-c23f-4682-b89c-b4d217366785
|
Which technique used on spacecraft power regulators (buck-boost) enables to further enhance their efficiency?
| 0
|
[
"Resonant Mode Switching",
"Voltage Ripple Reduction",
"Continuous Current Calibration"
] |
[
1,
0,
0
] |
Which technique used on spacecraft power regulators (buck-boost) enables to further enhance their efficiency?
A. Resonant Mode Switching
B. Voltage Ripple Reduction
C. Continuous Current Calibration
|
A. Resonant Mode Switching
|
149
|
dda35b83-c23f-4682-b89c-b4d217366785
|
Which technique used on spacecraft power regulators (buck-boost) enables to further enhance their efficiency?
| 1
|
[
"Voltage Ripple Reduction",
"Continuous Current Calibration",
"Resonant Mode Switching"
] |
[
0,
0,
1
] |
Which technique used on spacecraft power regulators (buck-boost) enables to further enhance their efficiency?
A. Voltage Ripple Reduction
B. Continuous Current Calibration
C. Resonant Mode Switching
|
C. Resonant Mode Switching
|
149
|
dda35b83-c23f-4682-b89c-b4d217366785
|
Which technique used on spacecraft power regulators (buck-boost) enables to further enhance their efficiency?
| 2
|
[
"Resonant Mode Switching",
"Continuous Current Calibration",
"Voltage Ripple Reduction"
] |
[
1,
0,
0
] |
Which technique used on spacecraft power regulators (buck-boost) enables to further enhance their efficiency?
A. Resonant Mode Switching
B. Continuous Current Calibration
C. Voltage Ripple Reduction
|
A. Resonant Mode Switching
|
150
|
8d14f358-de2e-46fa-8eb2-26edb2eee900
|
Which of the following power source in spacecraft design usually require storage in case of Eclipse?
| 0
|
[
"Radioistope Thermoelectric Generator",
"Solar Photovoltaic",
"Solar Thermal Dynamic",
"Fuell cells",
"Nuclear reactor"
] |
[
0,
1,
1,
0,
0
] |
Which of the following power source in spacecraft design usually require storage in case of Eclipse?
A. Radioistope Thermoelectric Generator
B. Solar Photovoltaic
C. Solar Thermal Dynamic
D. Fuell cells
E. Nuclear reactor
|
B. Solar Photovoltaic
C. Solar Thermal Dynamic
|
150
|
8d14f358-de2e-46fa-8eb2-26edb2eee900
|
Which of the following power source in spacecraft design usually require storage in case of Eclipse?
| 1
|
[
"Solar Thermal Dynamic",
"Radioistope Thermoelectric Generator",
"Solar Photovoltaic",
"Fuell cells",
"Nuclear reactor"
] |
[
1,
0,
1,
0,
0
] |
Which of the following power source in spacecraft design usually require storage in case of Eclipse?
A. Solar Thermal Dynamic
B. Radioistope Thermoelectric Generator
C. Solar Photovoltaic
D. Fuell cells
E. Nuclear reactor
|
A. Solar Thermal Dynamic
C. Solar Photovoltaic
|
150
|
8d14f358-de2e-46fa-8eb2-26edb2eee900
|
Which of the following power source in spacecraft design usually require storage in case of Eclipse?
| 2
|
[
"Nuclear reactor",
"Fuell cells",
"Solar Photovoltaic",
"Solar Thermal Dynamic",
"Radioistope Thermoelectric Generator"
] |
[
0,
0,
1,
1,
0
] |
Which of the following power source in spacecraft design usually require storage in case of Eclipse?
A. Nuclear reactor
B. Fuell cells
C. Solar Photovoltaic
D. Solar Thermal Dynamic
E. Radioistope Thermoelectric Generator
|
C. Solar Photovoltaic
D. Solar Thermal Dynamic
|
151
|
6a41ebbc-8a34-4036-a1b0-8507b0164ac1
|
Which of these statements are true of solid rockets?
| 0
|
[
"They are relatively simple to build and operate",
"They generate a lot of noise and vibration",
"They provide limited ability to control thrust",
"They inherently produce more thrust than liquid rockets"
] |
[
1,
1,
1,
0
] |
Which of these statements are true of solid rockets?
A. They are relatively simple to build and operate
B. They generate a lot of noise and vibration
C. They provide limited ability to control thrust
D. They inherently produce more thrust than liquid rockets
|
A. They are relatively simple to build and operate
B. They generate a lot of noise and vibration
C. They provide limited ability to control thrust
|
151
|
6a41ebbc-8a34-4036-a1b0-8507b0164ac1
|
Which of these statements are true of solid rockets?
| 1
|
[
"They provide limited ability to control thrust",
"They generate a lot of noise and vibration",
"They are relatively simple to build and operate",
"They inherently produce more thrust than liquid rockets"
] |
[
1,
1,
1,
0
] |
Which of these statements are true of solid rockets?
A. They provide limited ability to control thrust
B. They generate a lot of noise and vibration
C. They are relatively simple to build and operate
D. They inherently produce more thrust than liquid rockets
|
A. They provide limited ability to control thrust
B. They generate a lot of noise and vibration
C. They are relatively simple to build and operate
|
151
|
6a41ebbc-8a34-4036-a1b0-8507b0164ac1
|
Which of these statements are true of solid rockets?
| 2
|
[
"They provide limited ability to control thrust",
"They inherently produce more thrust than liquid rockets",
"They generate a lot of noise and vibration",
"They are relatively simple to build and operate"
] |
[
1,
0,
1,
1
] |
Which of these statements are true of solid rockets?
A. They provide limited ability to control thrust
B. They inherently produce more thrust than liquid rockets
C. They generate a lot of noise and vibration
D. They are relatively simple to build and operate
|
A. They provide limited ability to control thrust
C. They generate a lot of noise and vibration
D. They are relatively simple to build and operate
|
152
|
10f3799c-63b3-4154-af37-bb371b1fee35
|
Which of these statements are true of liquid rockets? Tell all that apply.
| 0
|
[
"They inherently produce less thrust than solid rockets",
"They must store the oxidizer and fuel propellant components onboard in separate compartments",
"They encounter high temperatures and pressures during combustion",
"To get high performance, they must use turbo pumps to direct the propellant into the combustion chamber"
] |
[
0,
1,
1,
1
] |
Which of these statements are true of liquid rockets? Tell all that apply.
A. They inherently produce less thrust than solid rockets
B. They must store the oxidizer and fuel propellant components onboard in separate compartments
C. They encounter high temperatures and pressures during combustion
D. To get high performance, they must use turbo pumps to direct the propellant into the combustion chamber
|
B. They must store the oxidizer and fuel propellant components onboard in separate compartments
C. They encounter high temperatures and pressures during combustion
D. To get high performance, they must use turbo pumps to direct the propellant into the combustion chamber
|
152
|
10f3799c-63b3-4154-af37-bb371b1fee35
|
Which of these statements are true of liquid rockets? Tell all that apply.
| 1
|
[
"They encounter high temperatures and pressures during combustion",
"They must store the oxidizer and fuel propellant components onboard in separate compartments",
"They inherently produce less thrust than solid rockets",
"To get high performance, they must use turbo pumps to direct the propellant into the combustion chamber"
] |
[
1,
1,
0,
1
] |
Which of these statements are true of liquid rockets? Tell all that apply.
A. They encounter high temperatures and pressures during combustion
B. They must store the oxidizer and fuel propellant components onboard in separate compartments
C. They inherently produce less thrust than solid rockets
D. To get high performance, they must use turbo pumps to direct the propellant into the combustion chamber
|
A. They encounter high temperatures and pressures during combustion
B. They must store the oxidizer and fuel propellant components onboard in separate compartments
D. To get high performance, they must use turbo pumps to direct the propellant into the combustion chamber
|
152
|
10f3799c-63b3-4154-af37-bb371b1fee35
|
Which of these statements are true of liquid rockets? Tell all that apply.
| 2
|
[
"They inherently produce less thrust than solid rockets",
"They encounter high temperatures and pressures during combustion",
"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"
] |
[
0,
1,
1,
1
] |
Which of these statements are true of liquid rockets? Tell all that apply.
A. They inherently produce less thrust than solid rockets
B. They encounter high temperatures and pressures during combustion
C. They must store the oxidizer and fuel propellant components onboard in separate compartments
D. To get high performance, they must use turbo pumps to direct the propellant into the combustion chamber
|
B. They encounter high temperatures and pressures during combustion
C. They must store the oxidizer and fuel propellant components onboard in separate compartments
D. To get high performance, they must use turbo pumps to direct the propellant into the combustion chamber
|
153
|
195bc8ba-e67d-435d-b384-7d23ecc1e3c8
|
When applying the idea rocket equation, which components usually comprise the the rocket initial mass ?
| 0
|
[
"Structure",
"Propellant",
"Payload"
] |
[
1,
1,
1
] |
When applying the idea rocket equation, which components usually comprise the the rocket initial mass ?
A. Structure
B. Propellant
C. Payload
|
A. Structure
B. Propellant
C. Payload
|
153
|
195bc8ba-e67d-435d-b384-7d23ecc1e3c8
|
When applying the idea rocket equation, which components usually comprise the the rocket initial mass ?
| 1
|
[
"Payload",
"Propellant",
"Structure"
] |
[
1,
1,
1
] |
When applying the idea rocket equation, which components usually comprise the the rocket initial mass ?
A. Payload
B. Propellant
C. Structure
|
A. Payload
B. Propellant
C. Structure
|
153
|
195bc8ba-e67d-435d-b384-7d23ecc1e3c8
|
When applying the idea rocket equation, which components usually comprise the the rocket initial mass ?
| 2
|
[
"Structure",
"Payload",
"Propellant"
] |
[
1,
1,
1
] |
When applying the idea rocket equation, which components usually comprise the the rocket initial mass ?
A. Structure
B. Payload
C. Propellant
|
A. Structure
B. Payload
C. Propellant
|
154
|
85b1737f-ce24-40eb-9cac-71220489ded7
|
When applying the idea rocket equation, which components usually comprise the the rocket final mass ?
| 0
|
[
"Structure",
"Payload",
"Propellant"
] |
[
1,
1,
0
] |
When applying the idea rocket equation, which components usually comprise the the rocket final mass ?
A. Structure
B. Payload
C. Propellant
|
A. Structure
B. Payload
|
154
|
85b1737f-ce24-40eb-9cac-71220489ded7
|
When applying the idea rocket equation, which components usually comprise the the rocket final mass ?
| 1
|
[
"Structure",
"Propellant",
"Payload"
] |
[
1,
0,
1
] |
When applying the idea rocket equation, which components usually comprise the the rocket final mass ?
A. Structure
B. Propellant
C. Payload
|
A. Structure
C. Payload
|
154
|
85b1737f-ce24-40eb-9cac-71220489ded7
|
When applying the idea rocket equation, which components usually comprise the the rocket final mass ?
| 2
|
[
"Payload",
"Structure",
"Propellant"
] |
[
1,
1,
0
] |
When applying the idea rocket equation, which components usually comprise the the rocket final mass ?
A. Payload
B. Structure
C. Propellant
|
A. Payload
B. Structure
|
155
|
9c2d1b44-c462-4db4-9664-7625b8b054c6
|
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?
| 0
|
[
"ΔV will be cut in half",
"ΔV will double",
"ΔV will stay the same"
] |
[
0,
0,
1
] |
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?
A. ΔV will be cut in half
B. ΔV will double
C. ΔV will stay the same
|
C. ΔV will stay the same
|
155
|
9c2d1b44-c462-4db4-9664-7625b8b054c6
|
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?
| 1
|
[
"ΔV will double",
"ΔV will be cut in half",
"ΔV will stay the same"
] |
[
0,
0,
1
] |
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?
A. ΔV will double
B. ΔV will be cut in half
C. ΔV will stay the same
|
C. ΔV will stay the same
|
155
|
9c2d1b44-c462-4db4-9664-7625b8b054c6
|
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?
| 2
|
[
"ΔV will stay the same",
"ΔV will double",
"ΔV will be cut in half"
] |
[
1,
0,
0
] |
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?
A. ΔV will stay the same
B. ΔV will double
C. ΔV will be cut in half
|
A. ΔV will stay the same
|
156
|
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. What is the structure fraction of this rocket?
| 0
|
[
"0.075",
"0.053",
"0.087",
"0.019"
] |
[
0,
0,
1,
0
] |
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?
A. 0.075
B. 0.053
C. 0.087
D. 0.019
|
C. 0.087
|
156
|
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. What is the structure fraction of this rocket?
| 1
|
[
"0.053",
"0.019",
"0.075",
"0.087"
] |
[
0,
0,
0,
1
] |
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?
A. 0.053
B. 0.019
C. 0.075
D. 0.087
|
D. 0.087
|
156
|
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. What is the structure fraction of this rocket?
| 2
|
[
"0.053",
"0.087",
"0.019",
"0.075"
] |
[
0,
1,
0,
0
] |
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?
A. 0.053
B. 0.087
C. 0.019
D. 0.075
|
B. 0.087
|
157
|
830a0d7a-0ce6-4c92-9a65-e7599ac1b700
|
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?
| 0
|
[
"11991 m/s",
"12991 m/s",
"9991 m/s",
"10991 m/s",
"8991 m/s"
] |
[
0,
0,
0,
0,
1
] |
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?
A. 11991 m/s
B. 12991 m/s
C. 9991 m/s
D. 10991 m/s
E. 8991 m/s
|
E. 8991 m/s
|
157
|
830a0d7a-0ce6-4c92-9a65-e7599ac1b700
|
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?
| 1
|
[
"12991 m/s",
"10991 m/s",
"9991 m/s",
"11991 m/s",
"8991 m/s"
] |
[
0,
0,
0,
0,
1
] |
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?
A. 12991 m/s
B. 10991 m/s
C. 9991 m/s
D. 11991 m/s
E. 8991 m/s
|
E. 8991 m/s
|
157
|
830a0d7a-0ce6-4c92-9a65-e7599ac1b700
|
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?
| 2
|
[
"12991 m/s",
"11991 m/s",
"8991 m/s",
"9991 m/s",
"10991 m/s"
] |
[
0,
0,
1,
0,
0
] |
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?
A. 12991 m/s
B. 11991 m/s
C. 8991 m/s
D. 9991 m/s
E. 10991 m/s
|
C. 8991 m/s
|
158
|
3cd7b8d6-030b-491f-a92a-85afac24d921
|
What would be the Delta V in m/s of the first stage of a rocket under the following conditions?
| 0
|
[
"5519",
"4519",
"3519",
"1519",
"2519"
] |
[
0,
0,
0,
0,
1
] |
What would be the Delta V in m/s of the first stage of a rocket under the following conditions?
A. 5519
B. 4519
C. 3519
D. 1519
E. 2519
|
E. 2519
|
158
|
3cd7b8d6-030b-491f-a92a-85afac24d921
|
What would be the Delta V in m/s of the first stage of a rocket under the following conditions?
| 1
|
[
"3519",
"5519",
"2519",
"4519",
"1519"
] |
[
0,
0,
1,
0,
0
] |
What would be the Delta V in m/s of the first stage of a rocket under the following conditions?
A. 3519
B. 5519
C. 2519
D. 4519
E. 1519
|
C. 2519
|
158
|
3cd7b8d6-030b-491f-a92a-85afac24d921
|
What would be the Delta V in m/s of the first stage of a rocket under the following conditions?
| 2
|
[
"1519",
"4519",
"5519",
"3519",
"2519"
] |
[
0,
0,
0,
0,
1
] |
What would be the Delta V in m/s of the first stage of a rocket under the following conditions?
A. 1519
B. 4519
C. 5519
D. 3519
E. 2519
|
E. 2519
|
159
|
493d3084-22a2-475c-8227-aeba4bae1c27
|
What Delta V can be achieve by the second stage of a rocket, after first stage has been jettisoned and under the following assumptions?
| 0
|
[
"6910 m/s",
"8910 m/s",
"9910 m/s",
"7910 m/s"
] |
[
0,
0,
0,
1
] |
What Delta V can be achieve by the second stage of a rocket, after first stage has been jettisoned and under the following assumptions?
A. 6910 m/s
B. 8910 m/s
C. 9910 m/s
D. 7910 m/s
|
D. 7910 m/s
|
159
|
493d3084-22a2-475c-8227-aeba4bae1c27
|
What Delta V can be achieve by the second stage of a rocket, after first stage has been jettisoned and under the following assumptions?
| 1
|
[
"8910 m/s",
"7910 m/s",
"6910 m/s",
"9910 m/s"
] |
[
0,
1,
0,
0
] |
What Delta V can be achieve by the second stage of a rocket, after first stage has been jettisoned and under the following assumptions?
A. 8910 m/s
B. 7910 m/s
C. 6910 m/s
D. 9910 m/s
|
B. 7910 m/s
|
159
|
493d3084-22a2-475c-8227-aeba4bae1c27
|
What Delta V can be achieve by the second stage of a rocket, after first stage has been jettisoned and under the following assumptions?
| 2
|
[
"7910 m/s",
"9910 m/s",
"6910 m/s",
"8910 m/s"
] |
[
1,
0,
0,
0
] |
What Delta V can be achieve by the second stage of a rocket, after first stage has been jettisoned and under the following assumptions?
A. 7910 m/s
B. 9910 m/s
C. 6910 m/s
D. 8910 m/s
|
A. 7910 m/s
|
160
|
e9c6d3d7-c413-49b8-9877-4f95294d4b70
|
What does ECLSS refer to in astronautics?
| 0
|
[
"Electrical Circuitry and Load Support Systems",
"Extra-terrestrial Colonization and Landing Systems",
"Environmental Control and Life Support System",
"Engineering Calibration and Logistics Support Services"
] |
[
0,
0,
1,
0
] |
What does ECLSS refer to in astronautics?
A. Electrical Circuitry and Load Support Systems
B. Extra-terrestrial Colonization and Landing Systems
C. Environmental Control and Life Support System
D. Engineering Calibration and Logistics Support Services
|
C. Environmental Control and Life Support System
|
160
|
e9c6d3d7-c413-49b8-9877-4f95294d4b70
|
What does ECLSS refer to in astronautics?
| 1
|
[
"Environmental Control and Life Support System",
"Engineering Calibration and Logistics Support Services",
"Electrical Circuitry and Load Support Systems",
"Extra-terrestrial Colonization and Landing Systems"
] |
[
1,
0,
0,
0
] |
What does ECLSS refer to in astronautics?
A. Environmental Control and Life Support System
B. Engineering Calibration and Logistics Support Services
C. Electrical Circuitry and Load Support Systems
D. Extra-terrestrial Colonization and Landing Systems
|
A. Environmental Control and Life Support System
|
160
|
e9c6d3d7-c413-49b8-9877-4f95294d4b70
|
What does ECLSS refer to in astronautics?
| 2
|
[
"Environmental Control and Life Support System",
"Electrical Circuitry and Load Support Systems",
"Extra-terrestrial Colonization and Landing Systems",
"Engineering Calibration and Logistics Support Services"
] |
[
1,
0,
0,
0
] |
What does ECLSS refer to in astronautics?
A. Environmental Control and Life Support System
B. Electrical Circuitry and Load Support Systems
C. Extra-terrestrial Colonization and Landing Systems
D. Engineering Calibration and Logistics Support Services
|
A. Environmental Control and Life Support System
|
161
|
326efd57-822c-45e9-a16e-707e7389f102
|
Which of the following environmental control requirements are in general specific to human spaceflight, hence not applicable to unmanned satellite missions?
| 0
|
[
"Water and Food",
"Atmospheric Pressure Control",
"Temperature Control",
"Waste Disposal"
] |
[
1,
1,
0,
1
] |
Which of the following environmental control requirements are in general specific to human spaceflight, hence not applicable to unmanned satellite missions?
A. Water and Food
B. Atmospheric Pressure Control
C. Temperature Control
D. Waste Disposal
|
A. Water and Food
B. Atmospheric Pressure Control
D. Waste Disposal
|
161
|
326efd57-822c-45e9-a16e-707e7389f102
|
Which of the following environmental control requirements are in general specific to human spaceflight, hence not applicable to unmanned satellite missions?
| 1
|
[
"Temperature Control",
"Water and Food",
"Waste Disposal",
"Atmospheric Pressure Control"
] |
[
0,
1,
1,
1
] |
Which of the following environmental control requirements are in general specific to human spaceflight, hence not applicable to unmanned satellite missions?
A. Temperature Control
B. Water and Food
C. Waste Disposal
D. Atmospheric Pressure Control
|
B. Water and Food
C. Waste Disposal
D. Atmospheric Pressure Control
|
161
|
326efd57-822c-45e9-a16e-707e7389f102
|
Which of the following environmental control requirements are in general specific to human spaceflight, hence not applicable to unmanned satellite missions?
| 2
|
[
"Temperature Control",
"Water and Food",
"Atmospheric Pressure Control",
"Waste Disposal"
] |
[
0,
1,
1,
1
] |
Which of the following environmental control requirements are in general specific to human spaceflight, hence not applicable to unmanned satellite missions?
A. Temperature Control
B. Water and Food
C. Atmospheric Pressure Control
D. Waste Disposal
|
B. Water and Food
C. Atmospheric Pressure Control
D. Waste Disposal
|
162
|
e1058454-feef-4ace-9213-a4ebdffc01ca
|
Which of the following is true about ECLSS Closed Loop System in comparison to Open-Loop ECLSS?
| 0
|
[
"Resource scale linearly with flight duration",
"They are more complex and more expensive",
"They are reliable because there are a few moving parts",
"Recycling equipment can increase the launch mass",
"They require less resupply"
] |
[
0,
1,
0,
1,
1
] |
Which of the following is true about ECLSS Closed Loop System in comparison to Open-Loop ECLSS?
A. Resource scale linearly with flight duration
B. They are more complex and more expensive
C. They are reliable because there are a few moving parts
D. Recycling equipment can increase the launch mass
E. They require less resupply
|
B. They are more complex and more expensive
D. Recycling equipment can increase the launch mass
E. They require less resupply
|
162
|
e1058454-feef-4ace-9213-a4ebdffc01ca
|
Which of the following is true about ECLSS Closed Loop System in comparison to Open-Loop ECLSS?
| 1
|
[
"Resource scale linearly with flight duration",
"They require less resupply",
"Recycling equipment can increase the launch mass",
"They are more complex and more expensive",
"They are reliable because there are a few moving parts"
] |
[
0,
1,
1,
1,
0
] |
Which of the following is true about ECLSS Closed Loop System in comparison to Open-Loop ECLSS?
A. Resource scale linearly with flight duration
B. They require less resupply
C. Recycling equipment can increase the launch mass
D. They are more complex and more expensive
E. They are reliable because there are a few moving parts
|
B. They require less resupply
C. Recycling equipment can increase the launch mass
D. They are more complex and more expensive
|
162
|
e1058454-feef-4ace-9213-a4ebdffc01ca
|
Which of the following is true about ECLSS Closed Loop System in comparison to Open-Loop ECLSS?
| 2
|
[
"They are more complex and more expensive",
"Recycling equipment can increase the launch mass",
"They are reliable because there are a few moving parts",
"They require less resupply",
"Resource scale linearly with flight duration"
] |
[
1,
1,
0,
1,
0
] |
Which of the following is true about ECLSS Closed Loop System in comparison to Open-Loop ECLSS?
A. They are more complex and more expensive
B. Recycling equipment can increase the launch mass
C. They are reliable because there are a few moving parts
D. They require less resupply
E. Resource scale linearly with flight duration
|
A. They are more complex and more expensive
B. Recycling equipment can increase the launch mass
D. They require less resupply
|
163
|
c90f0fdc-9909-403e-892b-5e0e24bfcd1c
|
What is the primary driver to choose between a closed-loop or an open-loop ECLSS?
| 0
|
[
"Mission Duration",
"Crew Size",
"Launcher reliability",
"Spacecraft Size"
] |
[
1,
0,
0,
0
] |
What is the primary driver to choose between a closed-loop or an open-loop ECLSS?
A. Mission Duration
B. Crew Size
C. Launcher reliability
D. Spacecraft Size
|
A. Mission Duration
|
163
|
c90f0fdc-9909-403e-892b-5e0e24bfcd1c
|
What is the primary driver to choose between a closed-loop or an open-loop ECLSS?
| 1
|
[
"Crew Size",
"Launcher reliability",
"Mission Duration",
"Spacecraft Size"
] |
[
0,
0,
1,
0
] |
What is the primary driver to choose between a closed-loop or an open-loop ECLSS?
A. Crew Size
B. Launcher reliability
C. Mission Duration
D. Spacecraft Size
|
C. Mission Duration
|
163
|
c90f0fdc-9909-403e-892b-5e0e24bfcd1c
|
What is the primary driver to choose between a closed-loop or an open-loop ECLSS?
| 2
|
[
"Crew Size",
"Spacecraft Size",
"Launcher reliability",
"Mission Duration"
] |
[
0,
0,
0,
1
] |
What is the primary driver to choose between a closed-loop or an open-loop ECLSS?
A. Crew Size
B. Spacecraft Size
C. Launcher reliability
D. Mission Duration
|
D. Mission Duration
|
164
|
74a14b36-92c8-4971-b30e-7beaf23cb073
|
Which of the following recycling is represent the more mass savings using a closed loop ECLSS?
| 0
|
[
"Water recycling",
"Oxygen recovery from CO2",
"Leaks prevention",
"Food production from wastes"
] |
[
1,
0,
0,
0
] |
Which of the following recycling is represent the more mass savings using a closed loop ECLSS?
A. Water recycling
B. Oxygen recovery from CO2
C. Leaks prevention
D. Food production from wastes
|
A. Water recycling
|
164
|
74a14b36-92c8-4971-b30e-7beaf23cb073
|
Which of the following recycling is represent the more mass savings using a closed loop ECLSS?
| 1
|
[
"Food production from wastes",
"Leaks prevention",
"Water recycling",
"Oxygen recovery from CO2"
] |
[
0,
0,
1,
0
] |
Which of the following recycling is represent the more mass savings using a closed loop ECLSS?
A. Food production from wastes
B. Leaks prevention
C. Water recycling
D. Oxygen recovery from CO2
|
C. Water recycling
|
164
|
74a14b36-92c8-4971-b30e-7beaf23cb073
|
Which of the following recycling is represent the more mass savings using a closed loop ECLSS?
| 2
|
[
"Leaks prevention",
"Water recycling",
"Food production from wastes",
"Oxygen recovery from CO2"
] |
[
0,
1,
0,
0
] |
Which of the following recycling is represent the more mass savings using a closed loop ECLSS?
A. Leaks prevention
B. Water recycling
C. Food production from wastes
D. Oxygen recovery from CO2
|
B. Water recycling
|
165
|
ae4ace16-3c61-48db-8670-78a4d51ee9da
|
Which of the following are the most import source of water consumption on-board ISS missions?
| 0
|
[
"Food preparation water",
"Drinking water",
"Clothes wash water"
] |
[
0,
1,
0
] |
Which of the following are the most import source of water consumption on-board ISS missions?
A. Food preparation water
B. Drinking water
C. Clothes wash water
|
B. Drinking water
|
165
|
ae4ace16-3c61-48db-8670-78a4d51ee9da
|
Which of the following are the most import source of water consumption on-board ISS missions?
| 1
|
[
"Clothes wash water",
"Drinking water",
"Food preparation water"
] |
[
0,
1,
0
] |
Which of the following are the most import source of water consumption on-board ISS missions?
A. Clothes wash water
B. Drinking water
C. Food preparation water
|
B. Drinking water
|
165
|
ae4ace16-3c61-48db-8670-78a4d51ee9da
|
Which of the following are the most import source of water consumption on-board ISS missions?
| 2
|
[
"Drinking water",
"Food preparation water",
"Clothes wash water"
] |
[
1,
0,
0
] |
Which of the following are the most import source of water consumption on-board ISS missions?
A. Drinking water
B. Food preparation water
C. Clothes wash water
|
A. Drinking water
|
166
|
b3098ceb-1287-4387-a56b-399b5a34ca53
|
Assuming there are 3 sources of independent errors on the knowledge of the volume of a given reservoir. These independent errors are 0.1 L, 0.2 L and 0.5 L. Which is the combined errors of these 3 sources of errors?
| 0
|
[
"0.30 L",
"0.50 L",
"0.55 L",
"0.80 L"
] |
[
0,
0,
1,
0
] |
Assuming there are 3 sources of independent errors on the knowledge of the volume of a given reservoir. These independent errors are 0.1 L, 0.2 L and 0.5 L. Which is the combined errors of these 3 sources of errors?
A. 0.30 L
B. 0.50 L
C. 0.55 L
D. 0.80 L
|
C. 0.55 L
|
166
|
b3098ceb-1287-4387-a56b-399b5a34ca53
|
Assuming there are 3 sources of independent errors on the knowledge of the volume of a given reservoir. These independent errors are 0.1 L, 0.2 L and 0.5 L. Which is the combined errors of these 3 sources of errors?
| 1
|
[
"0.55 L",
"0.80 L",
"0.30 L",
"0.50 L"
] |
[
1,
0,
0,
0
] |
Assuming there are 3 sources of independent errors on the knowledge of the volume of a given reservoir. These independent errors are 0.1 L, 0.2 L and 0.5 L. Which is the combined errors of these 3 sources of errors?
A. 0.55 L
B. 0.80 L
C. 0.30 L
D. 0.50 L
|
A. 0.55 L
|
166
|
b3098ceb-1287-4387-a56b-399b5a34ca53
|
Assuming there are 3 sources of independent errors on the knowledge of the volume of a given reservoir. These independent errors are 0.1 L, 0.2 L and 0.5 L. Which is the combined errors of these 3 sources of errors?
| 2
|
[
"0.50 L",
"0.80 L",
"0.55 L",
"0.30 L"
] |
[
0,
0,
1,
0
] |
Assuming there are 3 sources of independent errors on the knowledge of the volume of a given reservoir. These independent errors are 0.1 L, 0.2 L and 0.5 L. Which is the combined errors of these 3 sources of errors?
A. 0.50 L
B. 0.80 L
C. 0.55 L
D. 0.30 L
|
C. 0.55 L
|
167
|
09f6c3fa-76f5-4d6b-97f0-aab965ae525b
|
What is the formula used to combined errors (e1, e2, e3) which are depend from each other? Assume that all errors are given in absolute values.
| 0
|
[
"error = e1 + e2 + e3",
"error = e1ˆ2 + e2ˆ2 + e3ˆ2",
"error = max(e1, e2, e3)",
"error = sqrt(e1ˆ2 + e2ˆ2 + e3ˆ2)",
"error = sqrt(e1 + e2 + e3)"
] |
[
1,
0,
0,
0,
0
] |
What is the formula used to combined errors (e1, e2, e3) which are depend from each other? Assume that all errors are given in absolute values.
A. error = e1 + e2 + e3
B. error = e1ˆ2 + e2ˆ2 + e3ˆ2
C. error = max(e1, e2, e3)
D. error = sqrt(e1ˆ2 + e2ˆ2 + e3ˆ2)
E. error = sqrt(e1 + e2 + e3)
|
A. error = e1 + e2 + e3
|
167
|
09f6c3fa-76f5-4d6b-97f0-aab965ae525b
|
What is the formula used to combined errors (e1, e2, e3) which are depend from each other? Assume that all errors are given in absolute values.
| 1
|
[
"error = sqrt(e1 + e2 + e3)",
"error = max(e1, e2, e3)",
"error = sqrt(e1ˆ2 + e2ˆ2 + e3ˆ2)",
"error = e1ˆ2 + e2ˆ2 + e3ˆ2",
"error = e1 + e2 + e3"
] |
[
0,
0,
0,
0,
1
] |
What is the formula used to combined errors (e1, e2, e3) which are depend from each other? Assume that all errors are given in absolute values.
A. error = sqrt(e1 + e2 + e3)
B. error = max(e1, e2, e3)
C. error = sqrt(e1ˆ2 + e2ˆ2 + e3ˆ2)
D. error = e1ˆ2 + e2ˆ2 + e3ˆ2
E. error = e1 + e2 + e3
|
E. error = e1 + e2 + e3
|
167
|
09f6c3fa-76f5-4d6b-97f0-aab965ae525b
|
What is the formula used to combined errors (e1, e2, e3) which are depend from each other? Assume that all errors are given in absolute values.
| 2
|
[
"error = e1ˆ2 + e2ˆ2 + e3ˆ2",
"error = max(e1, e2, e3)",
"error = sqrt(e1 + e2 + e3)",
"error = e1 + e2 + e3",
"error = sqrt(e1ˆ2 + e2ˆ2 + e3ˆ2)"
] |
[
0,
0,
0,
1,
0
] |
What is the formula used to combined errors (e1, e2, e3) which are depend from each other? Assume that all errors are given in absolute values.
A. error = e1ˆ2 + e2ˆ2 + e3ˆ2
B. error = max(e1, e2, e3)
C. error = sqrt(e1 + e2 + e3)
D. error = e1 + e2 + e3
E. error = sqrt(e1ˆ2 + e2ˆ2 + e3ˆ2)
|
D. error = e1 + e2 + e3
|
168
|
b9ccd97e-47bc-4acd-979b-85027aefc4ec
|
How do you usually compute a risk score in aerospace risk management?
| 0
|
[
"Multiplication of probability of occurrence by risk",
"Average probability of occurrence of all risks",
"Summation of individual risk severity",
"Division of severity by probability of occurrence"
] |
[
1,
0,
0,
0
] |
How do you usually compute a risk score in aerospace risk management?
A. Multiplication of probability of occurrence by risk
B. Average probability of occurrence of all risks
C. Summation of individual risk severity
D. Division of severity by probability of occurrence
|
A. Multiplication of probability of occurrence by risk
|
168
|
b9ccd97e-47bc-4acd-979b-85027aefc4ec
|
How do you usually compute a risk score in aerospace risk management?
| 1
|
[
"Division of severity by probability of occurrence",
"Average probability of occurrence of all risks",
"Multiplication of probability of occurrence by risk",
"Summation of individual risk severity"
] |
[
0,
0,
1,
0
] |
How do you usually compute a risk score in aerospace risk management?
A. Division of severity by probability of occurrence
B. Average probability of occurrence of all risks
C. Multiplication of probability of occurrence by risk
D. Summation of individual risk severity
|
C. Multiplication of probability of occurrence by risk
|
168
|
b9ccd97e-47bc-4acd-979b-85027aefc4ec
|
How do you usually compute a risk score in aerospace risk management?
| 2
|
[
"Summation of individual risk severity",
"Multiplication of probability of occurrence by risk",
"Average probability of occurrence of all risks",
"Division of severity by probability of occurrence"
] |
[
0,
1,
0,
0
] |
How do you usually compute a risk score in aerospace risk management?
A. Summation of individual risk severity
B. Multiplication of probability of occurrence by risk
C. Average probability of occurrence of all risks
D. Division of severity by probability of occurrence
|
B. Multiplication of probability of occurrence by risk
|
169
|
223e2e5e-34c6-4d14-9158-2122edc90d01
|
What is usually true when talking about spacecraft active redundancy systems?
| 0
|
[
"No action is needed to ensure the service continuity after the failure",
"Requires manual switching to backup components upon failure",
"Often used in critical application",
"Suitable for digital systems but not for mechanical systems",
"Often used in non-critical application"
] |
[
1,
0,
1,
0,
0
] |
What is usually true when talking about spacecraft active redundancy systems?
A. No action is needed to ensure the service continuity after the failure
B. Requires manual switching to backup components upon failure
C. Often used in critical application
D. Suitable for digital systems but not for mechanical systems
E. Often used in non-critical application
|
A. No action is needed to ensure the service continuity after the failure
C. Often used in critical application
|
169
|
223e2e5e-34c6-4d14-9158-2122edc90d01
|
What is usually true when talking about spacecraft active redundancy systems?
| 1
|
[
"Requires manual switching to backup components upon failure",
"Often used in critical application",
"No action is needed to ensure the service continuity after the failure",
"Suitable for digital systems but not for mechanical systems",
"Often used in non-critical application"
] |
[
0,
1,
1,
0,
0
] |
What is usually true when talking about spacecraft active redundancy systems?
A. Requires manual switching to backup components upon failure
B. Often used in critical application
C. No action is needed to ensure the service continuity after the failure
D. Suitable for digital systems but not for mechanical systems
E. Often used in non-critical application
|
B. Often used in critical application
C. No action is needed to ensure the service continuity after the failure
|
169
|
223e2e5e-34c6-4d14-9158-2122edc90d01
|
What is usually true when talking about spacecraft active redundancy systems?
| 2
|
[
"Requires manual switching to backup components upon failure",
"Often used in critical application",
"Often used in non-critical application",
"No action is needed to ensure the service continuity after the failure",
"Suitable for digital systems but not for mechanical systems"
] |
[
0,
1,
0,
1,
0
] |
What is usually true when talking about spacecraft active redundancy systems?
A. Requires manual switching to backup components upon failure
B. Often used in critical application
C. Often used in non-critical application
D. No action is needed to ensure the service continuity after the failure
E. Suitable for digital systems but not for mechanical systems
|
B. Often used in critical application
D. No action is needed to ensure the service continuity after the failure
|
170
|
5b7a8008-b65d-44c0-99c8-7acb5ac6a59d
|
What are trade trees in astronautics?
| 0
|
[
"A new class algorithms for optimizing fuel consumption during space missions",
"A catalog of spacecraft components traded on international markets",
"A hierarchical decomposition of decisions to make the most important decisions first",
"Mathematical models for predicting the trajectory of celestial bodies"
] |
[
0,
0,
1,
0
] |
What are trade trees in astronautics?
A. A new class algorithms for optimizing fuel consumption during space missions
B. A catalog of spacecraft components traded on international markets
C. A hierarchical decomposition of decisions to make the most important decisions first
D. Mathematical models for predicting the trajectory of celestial bodies
|
C. A hierarchical decomposition of decisions to make the most important decisions first
|
170
|
5b7a8008-b65d-44c0-99c8-7acb5ac6a59d
|
What are trade trees in astronautics?
| 1
|
[
"A new class algorithms for optimizing fuel consumption during space missions",
"A catalog of spacecraft components traded on international markets",
"Mathematical models for predicting the trajectory of celestial bodies",
"A hierarchical decomposition of decisions to make the most important decisions first"
] |
[
0,
0,
0,
1
] |
What are trade trees in astronautics?
A. A new class algorithms for optimizing fuel consumption during space missions
B. A catalog of spacecraft components traded on international markets
C. Mathematical models for predicting the trajectory of celestial bodies
D. A hierarchical decomposition of decisions to make the most important decisions first
|
D. A hierarchical decomposition of decisions to make the most important decisions first
|
170
|
5b7a8008-b65d-44c0-99c8-7acb5ac6a59d
|
What are trade trees in astronautics?
| 2
|
[
"A new class algorithms for optimizing fuel consumption during space missions",
"Mathematical models for predicting the trajectory of celestial bodies",
"A catalog of spacecraft components traded on international markets",
"A hierarchical decomposition of decisions to make the most important decisions first"
] |
[
0,
0,
0,
1
] |
What are trade trees in astronautics?
A. A new class algorithms for optimizing fuel consumption during space missions
B. Mathematical models for predicting the trajectory of celestial bodies
C. A catalog of spacecraft components traded on international markets
D. A hierarchical decomposition of decisions to make the most important decisions first
|
D. A hierarchical decomposition of decisions to make the most important decisions first
|
171
|
4cea1cab-95b0-430e-91c3-13a4a67ba123
|
Which of the following best describe push broom scanning technique for electro-optical instruments?
| 0
|
[
"Scanning covering a full swath width using a linear arrangement of detector elements",
"Scanning using a 2-dimensional array of detector element",
"Scanning a single detector element on the ground in the cross-track direction"
] |
[
1,
0,
0
] |
Which of the following best describe push broom scanning technique for electro-optical instruments?
A. Scanning covering a full swath width using a linear arrangement of detector elements
B. Scanning using a 2-dimensional array of detector element
C. Scanning a single detector element on the ground in the cross-track direction
|
A. Scanning covering a full swath width using a linear arrangement of detector elements
|
171
|
4cea1cab-95b0-430e-91c3-13a4a67ba123
|
Which of the following best describe push broom scanning technique for electro-optical instruments?
| 1
|
[
"Scanning using a 2-dimensional array of detector element",
"Scanning a single detector element on the ground in the cross-track direction",
"Scanning covering a full swath width using a linear arrangement of detector elements"
] |
[
0,
0,
1
] |
Which of the following best describe push broom scanning technique for electro-optical instruments?
A. Scanning using a 2-dimensional array of detector element
B. Scanning a single detector element on the ground in the cross-track direction
C. Scanning covering a full swath width using a linear arrangement of detector elements
|
C. Scanning covering a full swath width using a linear arrangement of detector elements
|
171
|
4cea1cab-95b0-430e-91c3-13a4a67ba123
|
Which of the following best describe push broom scanning technique for electro-optical instruments?
| 2
|
[
"Scanning covering a full swath width using a linear arrangement of detector elements",
"Scanning a single detector element on the ground in the cross-track direction",
"Scanning using a 2-dimensional array of detector element"
] |
[
1,
0,
0
] |
Which of the following best describe push broom scanning technique for electro-optical instruments?
A. Scanning covering a full swath width using a linear arrangement of detector elements
B. Scanning a single detector element on the ground in the cross-track direction
C. Scanning using a 2-dimensional array of detector element
|
A. Scanning covering a full swath width using a linear arrangement of detector elements
|
173
|
a7800b29-9996-40ff-9b1f-f6a35588d522
|
Which of the following was the first known SAR in space?
| 0
|
[
"CALIPSO",
"ICESAT",
"SEASAT",
"TRMM"
] |
[
0,
0,
1,
0
] |
Which of the following was the first known SAR in space?
A. CALIPSO
B. ICESAT
C. SEASAT
D. TRMM
|
C. SEASAT
|
173
|
a7800b29-9996-40ff-9b1f-f6a35588d522
|
Which of the following was the first known SAR in space?
| 1
|
[
"TRMM",
"CALIPSO",
"ICESAT",
"SEASAT"
] |
[
0,
0,
0,
1
] |
Which of the following was the first known SAR in space?
A. TRMM
B. CALIPSO
C. ICESAT
D. SEASAT
|
D. SEASAT
|
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