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
|
|---|---|---|---|---|---|---|---|
103
|
caf7a503-ce34-4d2e-a11a-a8eec2b04dbc
|
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
| 0
|
[
"QPSK",
"16-PSK",
"8-PSK",
"BPSK"
] |
[
1,
0,
0,
0
] |
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
A. QPSK
B. 16-PSK
C. 8-PSK
D. BPSK
|
A. QPSK
|
103
|
caf7a503-ce34-4d2e-a11a-a8eec2b04dbc
|
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
| 1
|
[
"16-PSK",
"BPSK",
"8-PSK",
"QPSK"
] |
[
0,
0,
0,
1
] |
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
A. 16-PSK
B. BPSK
C. 8-PSK
D. QPSK
|
D. QPSK
|
103
|
caf7a503-ce34-4d2e-a11a-a8eec2b04dbc
|
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
| 2
|
[
"8-PSK",
"16-PSK",
"QPSK",
"BPSK"
] |
[
0,
0,
1,
0
] |
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
A. 8-PSK
B. 16-PSK
C. QPSK
D. BPSK
|
C. QPSK
|
104
|
61719260-46e9-444f-875e-8ea04e07f2bf
|
Which of the following statements are true about Precipitation Losses for Communication Link Analysis?
| 0
|
[
"precipitation losses attenuates RF signals by absorption",
"Geographic databases of rainfall are needed for link analysis",
"precipitation losses attenuates RF signals by scattering (depolarization)",
"precipitation losses are inversely proportional to the humidity in the atmosphere"
] |
[
1,
1,
1,
0
] |
Which of the following statements are true about Precipitation Losses for Communication Link Analysis?
A. precipitation losses attenuates RF signals by absorption
B. Geographic databases of rainfall are needed for link analysis
C. precipitation losses attenuates RF signals by scattering (depolarization)
D. precipitation losses are inversely proportional to the humidity in the atmosphere
|
A. precipitation losses attenuates RF signals by absorption
B. Geographic databases of rainfall are needed for link analysis
C. precipitation losses attenuates RF signals by scattering (depolarization)
|
104
|
61719260-46e9-444f-875e-8ea04e07f2bf
|
Which of the following statements are true about Precipitation Losses for Communication Link Analysis?
| 1
|
[
"precipitation losses are inversely proportional to the humidity in the atmosphere",
"precipitation losses attenuates RF signals by scattering (depolarization)",
"Geographic databases of rainfall are needed for link analysis",
"precipitation losses attenuates RF signals by absorption"
] |
[
0,
1,
1,
1
] |
Which of the following statements are true about Precipitation Losses for Communication Link Analysis?
A. precipitation losses are inversely proportional to the humidity in the atmosphere
B. precipitation losses attenuates RF signals by scattering (depolarization)
C. Geographic databases of rainfall are needed for link analysis
D. precipitation losses attenuates RF signals by absorption
|
B. precipitation losses attenuates RF signals by scattering (depolarization)
C. Geographic databases of rainfall are needed for link analysis
D. precipitation losses attenuates RF signals by absorption
|
104
|
61719260-46e9-444f-875e-8ea04e07f2bf
|
Which of the following statements are true about Precipitation Losses for Communication Link Analysis?
| 2
|
[
"precipitation losses attenuates RF signals by absorption",
"Geographic databases of rainfall are needed for link analysis",
"precipitation losses are inversely proportional to the humidity in the atmosphere",
"precipitation losses attenuates RF signals by scattering (depolarization)"
] |
[
1,
1,
0,
1
] |
Which of the following statements are true about Precipitation Losses for Communication Link Analysis?
A. precipitation losses attenuates RF signals by absorption
B. Geographic databases of rainfall are needed for link analysis
C. precipitation losses are inversely proportional to the humidity in the atmosphere
D. precipitation losses attenuates RF signals by scattering (depolarization)
|
A. precipitation losses attenuates RF signals by absorption
B. Geographic databases of rainfall are needed for link analysis
D. precipitation losses attenuates RF signals by scattering (depolarization)
|
105
|
8a4c5031-a489-4d16-95b6-1049aa4806a3
|
Which of the following influence the total power at the receive amplifier in communication link analyses?
| 0
|
[
"mu, the Standard gravitational parameter",
"Ltx, the transmitter pointing losses",
"Ls, the Free-Space Losses",
"Na, the avogadro number",
"EIRP, the Equivalent Isotropic Radiated Power",
"Lin, the input losses to the receiver"
] |
[
0,
1,
1,
0,
1,
1
] |
Which of the following influence the total power at the receive amplifier in communication link analyses?
A. mu, the Standard gravitational parameter
B. Ltx, the transmitter pointing losses
C. Ls, the Free-Space Losses
D. Na, the avogadro number
E. EIRP, the Equivalent Isotropic Radiated Power
F. Lin, the input losses to the receiver
|
B. Ltx, the transmitter pointing losses
C. Ls, the Free-Space Losses
E. EIRP, the Equivalent Isotropic Radiated Power
F. Lin, the input losses to the receiver
|
105
|
8a4c5031-a489-4d16-95b6-1049aa4806a3
|
Which of the following influence the total power at the receive amplifier in communication link analyses?
| 1
|
[
"Ls, the Free-Space Losses",
"Lin, the input losses to the receiver",
"EIRP, the Equivalent Isotropic Radiated Power",
"Ltx, the transmitter pointing losses",
"Na, the avogadro number",
"mu, the Standard gravitational parameter"
] |
[
1,
1,
1,
1,
0,
0
] |
Which of the following influence the total power at the receive amplifier in communication link analyses?
A. Ls, the Free-Space Losses
B. Lin, the input losses to the receiver
C. EIRP, the Equivalent Isotropic Radiated Power
D. Ltx, the transmitter pointing losses
E. Na, the avogadro number
F. mu, the Standard gravitational parameter
|
A. Ls, the Free-Space Losses
B. Lin, the input losses to the receiver
C. EIRP, the Equivalent Isotropic Radiated Power
D. Ltx, the transmitter pointing losses
|
105
|
8a4c5031-a489-4d16-95b6-1049aa4806a3
|
Which of the following influence the total power at the receive amplifier in communication link analyses?
| 2
|
[
"Ls, the Free-Space Losses",
"Na, the avogadro number",
"EIRP, the Equivalent Isotropic Radiated Power",
"Ltx, the transmitter pointing losses",
"mu, the Standard gravitational parameter",
"Lin, the input losses to the receiver"
] |
[
1,
0,
1,
1,
0,
1
] |
Which of the following influence the total power at the receive amplifier in communication link analyses?
A. Ls, the Free-Space Losses
B. Na, the avogadro number
C. EIRP, the Equivalent Isotropic Radiated Power
D. Ltx, the transmitter pointing losses
E. mu, the Standard gravitational parameter
F. Lin, the input losses to the receiver
|
A. Ls, the Free-Space Losses
C. EIRP, the Equivalent Isotropic Radiated Power
D. Ltx, the transmitter pointing losses
F. Lin, the input losses to the receiver
|
106
|
2af4081d-5cf9-4a96-8177-f47711c45929
|
In spacecraft link analysis which is the name used to refer to the signal transmitted from end users (for instance military troops) to the satellite?
| 0
|
[
"Return downlink",
"Forward downlink",
"Forward uplink",
"Return uplink"
] |
[
0,
0,
0,
1
] |
In spacecraft link analysis which is the name used to refer to the signal transmitted from end users (for instance military troops) to the satellite?
A. Return downlink
B. Forward downlink
C. Forward uplink
D. Return uplink
|
D. Return uplink
|
106
|
2af4081d-5cf9-4a96-8177-f47711c45929
|
In spacecraft link analysis which is the name used to refer to the signal transmitted from end users (for instance military troops) to the satellite?
| 1
|
[
"Forward downlink",
"Return downlink",
"Return uplink",
"Forward uplink"
] |
[
0,
0,
1,
0
] |
In spacecraft link analysis which is the name used to refer to the signal transmitted from end users (for instance military troops) to the satellite?
A. Forward downlink
B. Return downlink
C. Return uplink
D. Forward uplink
|
C. Return uplink
|
106
|
2af4081d-5cf9-4a96-8177-f47711c45929
|
In spacecraft link analysis which is the name used to refer to the signal transmitted from end users (for instance military troops) to the satellite?
| 2
|
[
"Forward downlink",
"Return downlink",
"Forward uplink",
"Return uplink"
] |
[
0,
0,
0,
1
] |
In spacecraft link analysis which is the name used to refer to the signal transmitted from end users (for instance military troops) to the satellite?
A. Forward downlink
B. Return downlink
C. Forward uplink
D. Return uplink
|
D. Return uplink
|
107
|
a82da0e7-861e-420a-9cec-97be967adbc0
|
What does an engineer means when she say that "the link closes" in communication link analysis?
| 0
|
[
"The energy received by the receiving antenna is strictly equal to the emitted energy (outputting the emitter's amplifier)",
"The difference between the power-to-noise ratio and the detection threshold is negative",
"The link margin is negative",
"The communication is finished and there are no more signal passing through the communication chain",
"The difference between the power-to-noise ratio and the detection threshold is positive"
] |
[
0,
0,
0,
0,
1
] |
What does an engineer means when she say that "the link closes" in communication link analysis?
A. The energy received by the receiving antenna is strictly equal to the emitted energy (outputting the emitter's amplifier)
B. The difference between the power-to-noise ratio and the detection threshold is negative
C. The link margin is negative
D. The communication is finished and there are no more signal passing through the communication chain
E. The difference between the power-to-noise ratio and the detection threshold is positive
|
E. The difference between the power-to-noise ratio and the detection threshold is positive
|
107
|
a82da0e7-861e-420a-9cec-97be967adbc0
|
What does an engineer means when she say that "the link closes" in communication link analysis?
| 1
|
[
"The communication is finished and there are no more signal passing through the communication chain",
"The energy received by the receiving antenna is strictly equal to the emitted energy (outputting the emitter's amplifier)",
"The difference between the power-to-noise ratio and the detection threshold is positive",
"The difference between the power-to-noise ratio and the detection threshold is negative",
"The link margin is negative"
] |
[
0,
0,
1,
0,
0
] |
What does an engineer means when she say that "the link closes" in communication link analysis?
A. The communication is finished and there are no more signal passing through the communication chain
B. The energy received by the receiving antenna is strictly equal to the emitted energy (outputting the emitter's amplifier)
C. The difference between the power-to-noise ratio and the detection threshold is positive
D. The difference between the power-to-noise ratio and the detection threshold is negative
E. The link margin is negative
|
C. The difference between the power-to-noise ratio and the detection threshold is positive
|
107
|
a82da0e7-861e-420a-9cec-97be967adbc0
|
What does an engineer means when she say that "the link closes" in communication link analysis?
| 2
|
[
"The link margin is negative",
"The communication is finished and there are no more signal passing through the communication chain",
"The energy received by the receiving antenna is strictly equal to the emitted energy (outputting the emitter's amplifier)",
"The difference between the power-to-noise ratio and the detection threshold is positive",
"The difference between the power-to-noise ratio and the detection threshold is negative"
] |
[
0,
0,
0,
1,
0
] |
What does an engineer means when she say that "the link closes" in communication link analysis?
A. The link margin is negative
B. The communication is finished and there are no more signal passing through the communication chain
C. The energy received by the receiving antenna is strictly equal to the emitted energy (outputting the emitter's amplifier)
D. The difference between the power-to-noise ratio and the detection threshold is positive
E. The difference between the power-to-noise ratio and the detection threshold is negative
|
D. The difference between the power-to-noise ratio and the detection threshold is positive
|
108
|
2e40b8b7-9830-4de0-b220-d77ad8c90abf
|
Which satellite band in the electromagnetic spectrum correspond to the highest frequencies?
| 0
|
[
"Ka-band",
"C-band",
"Q-band",
"V-band"
] |
[
0,
0,
0,
1
] |
Which satellite band in the electromagnetic spectrum correspond to the highest frequencies?
A. Ka-band
B. C-band
C. Q-band
D. V-band
|
D. V-band
|
108
|
2e40b8b7-9830-4de0-b220-d77ad8c90abf
|
Which satellite band in the electromagnetic spectrum correspond to the highest frequencies?
| 1
|
[
"V-band",
"C-band",
"Q-band",
"Ka-band"
] |
[
1,
0,
0,
0
] |
Which satellite band in the electromagnetic spectrum correspond to the highest frequencies?
A. V-band
B. C-band
C. Q-band
D. Ka-band
|
A. V-band
|
108
|
2e40b8b7-9830-4de0-b220-d77ad8c90abf
|
Which satellite band in the electromagnetic spectrum correspond to the highest frequencies?
| 2
|
[
"V-band",
"Ka-band",
"Q-band",
"C-band"
] |
[
1,
0,
0,
0
] |
Which satellite band in the electromagnetic spectrum correspond to the highest frequencies?
A. V-band
B. Ka-band
C. Q-band
D. C-band
|
A. V-band
|
109
|
e55ec36c-b9b5-45fe-8136-5d52273b54bd
|
Which of the following satellite band is associated with its correct frequency range?
| 0
|
[
"Ka-band (18 to 30 GHz)",
"Q-band (2 to 4 GHz)",
"S-band (7 to 11 GHz)",
"Ku-band (11 to 18 GHz)",
"V-band (1 to 2 Gz)",
"C-band (4 to 7 GHz)"
] |
[
1,
0,
0,
1,
0,
1
] |
Which of the following satellite band is associated with its correct frequency range?
A. Ka-band (18 to 30 GHz)
B. Q-band (2 to 4 GHz)
C. S-band (7 to 11 GHz)
D. Ku-band (11 to 18 GHz)
E. V-band (1 to 2 Gz)
F. C-band (4 to 7 GHz)
|
A. Ka-band (18 to 30 GHz)
D. Ku-band (11 to 18 GHz)
F. C-band (4 to 7 GHz)
|
109
|
e55ec36c-b9b5-45fe-8136-5d52273b54bd
|
Which of the following satellite band is associated with its correct frequency range?
| 1
|
[
"Ku-band (11 to 18 GHz)",
"Ka-band (18 to 30 GHz)",
"V-band (1 to 2 Gz)",
"C-band (4 to 7 GHz)",
"Q-band (2 to 4 GHz)",
"S-band (7 to 11 GHz)"
] |
[
1,
1,
0,
1,
0,
0
] |
Which of the following satellite band is associated with its correct frequency range?
A. Ku-band (11 to 18 GHz)
B. Ka-band (18 to 30 GHz)
C. V-band (1 to 2 Gz)
D. C-band (4 to 7 GHz)
E. Q-band (2 to 4 GHz)
F. S-band (7 to 11 GHz)
|
A. Ku-band (11 to 18 GHz)
B. Ka-band (18 to 30 GHz)
D. C-band (4 to 7 GHz)
|
109
|
e55ec36c-b9b5-45fe-8136-5d52273b54bd
|
Which of the following satellite band is associated with its correct frequency range?
| 2
|
[
"Q-band (2 to 4 GHz)",
"Ku-band (11 to 18 GHz)",
"S-band (7 to 11 GHz)",
"V-band (1 to 2 Gz)",
"C-band (4 to 7 GHz)",
"Ka-band (18 to 30 GHz)"
] |
[
0,
1,
0,
0,
1,
1
] |
Which of the following satellite band is associated with its correct frequency range?
A. Q-band (2 to 4 GHz)
B. Ku-band (11 to 18 GHz)
C. S-band (7 to 11 GHz)
D. V-band (1 to 2 Gz)
E. C-band (4 to 7 GHz)
F. Ka-band (18 to 30 GHz)
|
B. Ku-band (11 to 18 GHz)
E. C-band (4 to 7 GHz)
F. Ka-band (18 to 30 GHz)
|
111
|
c41b75d1-8c13-49d1-ab68-ddf74eb73d52
|
Why are Decibels used for communication links analyses?
| 0
|
[
"Because link analyses involves calculations with numbers that may differ by many orders of magnitude, decibel is simpler, faster and less error-prone.",
"Because of Aristote",
"This is a standard introduced by German scientist in Huntsville, Alabama, during Rocket Engine Fire test and was kept for legacy purpose and now introduced in the ECSS",
"In hommage of George Mikari Decibels, the inventor of the mechanical speaker"
] |
[
1,
0,
0,
0
] |
Why are Decibels used for communication links analyses?
A. Because link analyses involves calculations with numbers that may differ by many orders of magnitude, decibel is simpler, faster and less error-prone.
B. Because of Aristote
C. This is a standard introduced by German scientist in Huntsville, Alabama, during Rocket Engine Fire test and was kept for legacy purpose and now introduced in the ECSS
D. In hommage of George Mikari Decibels, the inventor of the mechanical speaker
|
A. Because link analyses involves calculations with numbers that may differ by many orders of magnitude, decibel is simpler, faster and less error-prone.
|
111
|
c41b75d1-8c13-49d1-ab68-ddf74eb73d52
|
Why are Decibels used for communication links analyses?
| 1
|
[
"Because of Aristote",
"This is a standard introduced by German scientist in Huntsville, Alabama, during Rocket Engine Fire test and was kept for legacy purpose and now introduced in the ECSS",
"In hommage of George Mikari Decibels, the inventor of the mechanical speaker",
"Because link analyses involves calculations with numbers that may differ by many orders of magnitude, decibel is simpler, faster and less error-prone."
] |
[
0,
0,
0,
1
] |
Why are Decibels used for communication links analyses?
A. Because of Aristote
B. This is a standard introduced by German scientist in Huntsville, Alabama, during Rocket Engine Fire test and was kept for legacy purpose and now introduced in the ECSS
C. In hommage of George Mikari Decibels, the inventor of the mechanical speaker
D. Because link analyses involves calculations with numbers that may differ by many orders of magnitude, decibel is simpler, faster and less error-prone.
|
D. Because link analyses involves calculations with numbers that may differ by many orders of magnitude, decibel is simpler, faster and less error-prone.
|
111
|
c41b75d1-8c13-49d1-ab68-ddf74eb73d52
|
Why are Decibels used for communication links analyses?
| 2
|
[
"This is a standard introduced by German scientist in Huntsville, Alabama, during Rocket Engine Fire test and was kept for legacy purpose and now introduced in the ECSS",
"Because of Aristote",
"Because link analyses involves calculations with numbers that may differ by many orders of magnitude, decibel is simpler, faster and less error-prone.",
"In hommage of George Mikari Decibels, the inventor of the mechanical speaker"
] |
[
0,
0,
1,
0
] |
Why are Decibels used for communication links analyses?
A. This is a standard introduced by German scientist in Huntsville, Alabama, during Rocket Engine Fire test and was kept for legacy purpose and now introduced in the ECSS
B. Because of Aristote
C. Because link analyses involves calculations with numbers that may differ by many orders of magnitude, decibel is simpler, faster and less error-prone.
D. In hommage of George Mikari Decibels, the inventor of the mechanical speaker
|
C. Because link analyses involves calculations with numbers that may differ by many orders of magnitude, decibel is simpler, faster and less error-prone.
|
112
|
7aec6699-a608-4ed4-8140-446f0d5117dd
|
What is the decibel equivalent of a 135 W amplifier output power relative to a 1 W reference?
| 0
|
[
"23.4",
"18.2",
"21.3",
"16.0"
] |
[
0,
0,
1,
0
] |
What is the decibel equivalent of a 135 W amplifier output power relative to a 1 W reference?
A. 23.4
B. 18.2
C. 21.3
D. 16.0
|
C. 21.3
|
112
|
7aec6699-a608-4ed4-8140-446f0d5117dd
|
What is the decibel equivalent of a 135 W amplifier output power relative to a 1 W reference?
| 1
|
[
"16.0",
"21.3",
"23.4",
"18.2"
] |
[
0,
1,
0,
0
] |
What is the decibel equivalent of a 135 W amplifier output power relative to a 1 W reference?
A. 16.0
B. 21.3
C. 23.4
D. 18.2
|
B. 21.3
|
112
|
7aec6699-a608-4ed4-8140-446f0d5117dd
|
What is the decibel equivalent of a 135 W amplifier output power relative to a 1 W reference?
| 2
|
[
"18.2",
"23.4",
"16.0",
"21.3"
] |
[
0,
0,
0,
1
] |
What is the decibel equivalent of a 135 W amplifier output power relative to a 1 W reference?
A. 18.2
B. 23.4
C. 16.0
D. 21.3
|
D. 21.3
|
113
|
d1553f22-46fe-4dd8-9c35-a1df88727d49
|
How do you express the antenna gain G as a function of the antenna directivity D and various losses L?
| 0
|
[
"G = D^2 / L",
"G = (D - L) / L",
"G = D - L",
"G = D / L"
] |
[
0,
0,
1,
0
] |
How do you express the antenna gain G as a function of the antenna directivity D and various losses L?
A. G = D^2 / L
B. G = (D - L) / L
C. G = D - L
D. G = D / L
|
C. G = D - L
|
113
|
d1553f22-46fe-4dd8-9c35-a1df88727d49
|
How do you express the antenna gain G as a function of the antenna directivity D and various losses L?
| 1
|
[
"G = D - L",
"G = D / L",
"G = D^2 / L",
"G = (D - L) / L"
] |
[
1,
0,
0,
0
] |
How do you express the antenna gain G as a function of the antenna directivity D and various losses L?
A. G = D - L
B. G = D / L
C. G = D^2 / L
D. G = (D - L) / L
|
A. G = D - L
|
113
|
d1553f22-46fe-4dd8-9c35-a1df88727d49
|
How do you express the antenna gain G as a function of the antenna directivity D and various losses L?
| 2
|
[
"G = D / L",
"G = (D - L) / L",
"G = D - L",
"G = D^2 / L"
] |
[
0,
0,
1,
0
] |
How do you express the antenna gain G as a function of the antenna directivity D and various losses L?
A. G = D / L
B. G = (D - L) / L
C. G = D - L
D. G = D^2 / L
|
C. G = D - L
|
114
|
604dfbb9-035f-4144-968e-4fc8259362e6
|
What does A refer to in the formula G = etha * (4*pi / lambda^2 ) * A for communication link analyses
| 0
|
[
"A relates to the absorptivity of the emitting medium (dimensionless)",
"A to the antenna volume (m^3)",
"A relates to the physical size of the antenna aperture (m^2)"
] |
[
0,
0,
1
] |
What does A refer to in the formula G = etha * (4*pi / lambda^2 ) * A for communication link analyses
A. A relates to the absorptivity of the emitting medium (dimensionless)
B. A to the antenna volume (m^3)
C. A relates to the physical size of the antenna aperture (m^2)
|
C. A relates to the physical size of the antenna aperture (m^2)
|
114
|
604dfbb9-035f-4144-968e-4fc8259362e6
|
What does A refer to in the formula G = etha * (4*pi / lambda^2 ) * A for communication link analyses
| 1
|
[
"A to the antenna volume (m^3)",
"A relates to the absorptivity of the emitting medium (dimensionless)",
"A relates to the physical size of the antenna aperture (m^2)"
] |
[
0,
0,
1
] |
What does A refer to in the formula G = etha * (4*pi / lambda^2 ) * A for communication link analyses
A. A to the antenna volume (m^3)
B. A relates to the absorptivity of the emitting medium (dimensionless)
C. A relates to the physical size of the antenna aperture (m^2)
|
C. A relates to the physical size of the antenna aperture (m^2)
|
114
|
604dfbb9-035f-4144-968e-4fc8259362e6
|
What does A refer to in the formula G = etha * (4*pi / lambda^2 ) * A for communication link analyses
| 2
|
[
"A relates to the absorptivity of the emitting medium (dimensionless)",
"A relates to the physical size of the antenna aperture (m^2)",
"A to the antenna volume (m^3)"
] |
[
0,
1,
0
] |
What does A refer to in the formula G = etha * (4*pi / lambda^2 ) * A for communication link analyses
A. A relates to the absorptivity of the emitting medium (dimensionless)
B. A relates to the physical size of the antenna aperture (m^2)
C. A to the antenna volume (m^3)
|
B. A relates to the physical size of the antenna aperture (m^2)
|
115
|
883be593-9c9c-4437-a718-a0699882cc4c
|
How do you compute theta (in degrees), the half-power beamwidth in link analyses?
| 0
|
[
"Theta = - k*frequency, k is a tablulated constant",
"You cannot, you need to measure it",
"Theta = 21 / (frequency * Diameter)",
"Theta = frequency / Diameter"
] |
[
0,
0,
1,
0
] |
How do you compute theta (in degrees), the half-power beamwidth in link analyses?
A. Theta = - k*frequency, k is a tablulated constant
B. You cannot, you need to measure it
C. Theta = 21 / (frequency * Diameter)
D. Theta = frequency / Diameter
|
C. Theta = 21 / (frequency * Diameter)
|
115
|
883be593-9c9c-4437-a718-a0699882cc4c
|
How do you compute theta (in degrees), the half-power beamwidth in link analyses?
| 1
|
[
"Theta = 21 / (frequency * Diameter)",
"Theta = - k*frequency, k is a tablulated constant",
"Theta = frequency / Diameter",
"You cannot, you need to measure it"
] |
[
1,
0,
0,
0
] |
How do you compute theta (in degrees), the half-power beamwidth in link analyses?
A. Theta = 21 / (frequency * Diameter)
B. Theta = - k*frequency, k is a tablulated constant
C. Theta = frequency / Diameter
D. You cannot, you need to measure it
|
A. Theta = 21 / (frequency * Diameter)
|
115
|
883be593-9c9c-4437-a718-a0699882cc4c
|
How do you compute theta (in degrees), the half-power beamwidth in link analyses?
| 2
|
[
"You cannot, you need to measure it",
"Theta = frequency / Diameter",
"Theta = - k*frequency, k is a tablulated constant",
"Theta = 21 / (frequency * Diameter)"
] |
[
0,
0,
0,
1
] |
How do you compute theta (in degrees), the half-power beamwidth in link analyses?
A. You cannot, you need to measure it
B. Theta = frequency / Diameter
C. Theta = - k*frequency, k is a tablulated constant
D. Theta = 21 / (frequency * Diameter)
|
D. Theta = 21 / (frequency * Diameter)
|
116
|
b774f04e-e3a3-43a1-ab0b-d9bf87639636
|
Which is a major contribution to the antenna pointing error on-board satellite?
| 0
|
[
"thermal distortions",
"fixed misalignment",
"atmospheric residual drag"
] |
[
1,
0,
0
] |
Which is a major contribution to the antenna pointing error on-board satellite?
A. thermal distortions
B. fixed misalignment
C. atmospheric residual drag
|
A. thermal distortions
|
116
|
b774f04e-e3a3-43a1-ab0b-d9bf87639636
|
Which is a major contribution to the antenna pointing error on-board satellite?
| 1
|
[
"atmospheric residual drag",
"thermal distortions",
"fixed misalignment"
] |
[
0,
1,
0
] |
Which is a major contribution to the antenna pointing error on-board satellite?
A. atmospheric residual drag
B. thermal distortions
C. fixed misalignment
|
B. thermal distortions
|
116
|
b774f04e-e3a3-43a1-ab0b-d9bf87639636
|
Which is a major contribution to the antenna pointing error on-board satellite?
| 2
|
[
"thermal distortions",
"atmospheric residual drag",
"fixed misalignment"
] |
[
1,
0,
0
] |
Which is a major contribution to the antenna pointing error on-board satellite?
A. thermal distortions
B. atmospheric residual drag
C. fixed misalignment
|
A. thermal distortions
|
117
|
d7b25114-55fc-4143-bb47-9196a2a31f46
|
What does typical design allow for maximum satellite antennas pointing errors?
| 0
|
[
"Usually around 10% of the beamwidth, so 0.1 degree for 1 degree beamwidth",
"Usually up to 50% of the beamwidth because it is sized to account for that loss",
"Usually maximum 1% of the beamwidth, because beyond 1% the power-to-noise ratio decays exponentially minus infinity"
] |
[
1,
0,
0
] |
What does typical design allow for maximum satellite antennas pointing errors?
A. Usually around 10% of the beamwidth, so 0.1 degree for 1 degree beamwidth
B. Usually up to 50% of the beamwidth because it is sized to account for that loss
C. Usually maximum 1% of the beamwidth, because beyond 1% the power-to-noise ratio decays exponentially minus infinity
|
A. Usually around 10% of the beamwidth, so 0.1 degree for 1 degree beamwidth
|
117
|
d7b25114-55fc-4143-bb47-9196a2a31f46
|
What does typical design allow for maximum satellite antennas pointing errors?
| 1
|
[
"Usually up to 50% of the beamwidth because it is sized to account for that loss",
"Usually maximum 1% of the beamwidth, because beyond 1% the power-to-noise ratio decays exponentially minus infinity",
"Usually around 10% of the beamwidth, so 0.1 degree for 1 degree beamwidth"
] |
[
0,
0,
1
] |
What does typical design allow for maximum satellite antennas pointing errors?
A. Usually up to 50% of the beamwidth because it is sized to account for that loss
B. Usually maximum 1% of the beamwidth, because beyond 1% the power-to-noise ratio decays exponentially minus infinity
C. Usually around 10% of the beamwidth, so 0.1 degree for 1 degree beamwidth
|
C. Usually around 10% of the beamwidth, so 0.1 degree for 1 degree beamwidth
|
117
|
d7b25114-55fc-4143-bb47-9196a2a31f46
|
What does typical design allow for maximum satellite antennas pointing errors?
| 2
|
[
"Usually maximum 1% of the beamwidth, because beyond 1% the power-to-noise ratio decays exponentially minus infinity",
"Usually up to 50% of the beamwidth because it is sized to account for that loss",
"Usually around 10% of the beamwidth, so 0.1 degree for 1 degree beamwidth"
] |
[
0,
0,
1
] |
What does typical design allow for maximum satellite antennas pointing errors?
A. Usually maximum 1% of the beamwidth, because beyond 1% the power-to-noise ratio decays exponentially minus infinity
B. Usually up to 50% of the beamwidth because it is sized to account for that loss
C. Usually around 10% of the beamwidth, so 0.1 degree for 1 degree beamwidth
|
C. Usually around 10% of the beamwidth, so 0.1 degree for 1 degree beamwidth
|
118
|
7b251f74-511d-4057-8ed3-decd500f6bb6
|
Who is not a European Astronaut?
| 0
|
[
"Christina Koch",
"Samantha Cristoforetti",
"Jeremy Hansen",
"Thomas Pesquet"
] |
[
1,
0,
1,
0
] |
Who is not a European Astronaut?
A. Christina Koch
B. Samantha Cristoforetti
C. Jeremy Hansen
D. Thomas Pesquet
|
A. Christina Koch
C. Jeremy Hansen
|
118
|
7b251f74-511d-4057-8ed3-decd500f6bb6
|
Who is not a European Astronaut?
| 1
|
[
"Samantha Cristoforetti",
"Christina Koch",
"Thomas Pesquet",
"Jeremy Hansen"
] |
[
0,
1,
0,
1
] |
Who is not a European Astronaut?
A. Samantha Cristoforetti
B. Christina Koch
C. Thomas Pesquet
D. Jeremy Hansen
|
B. Christina Koch
D. Jeremy Hansen
|
118
|
7b251f74-511d-4057-8ed3-decd500f6bb6
|
Who is not a European Astronaut?
| 2
|
[
"Samantha Cristoforetti",
"Jeremy Hansen",
"Christina Koch",
"Thomas Pesquet"
] |
[
0,
1,
1,
0
] |
Who is not a European Astronaut?
A. Samantha Cristoforetti
B. Jeremy Hansen
C. Christina Koch
D. Thomas Pesquet
|
B. Jeremy Hansen
C. Christina Koch
|
119
|
ae4e517f-c4a6-440c-98ff-c3d8d11faf09
|
What is the key difference between a jet engine and a liquid rocket engine?
| 0
|
[
"The liquid rocket engine has to carry the oxidizer",
"The jet engine produce a long flamme tail after combustion",
"The jet engine is in general more expensive"
] |
[
1,
0,
0
] |
What is the key difference between a jet engine and a liquid rocket engine?
A. The liquid rocket engine has to carry the oxidizer
B. The jet engine produce a long flamme tail after combustion
C. The jet engine is in general more expensive
|
A. The liquid rocket engine has to carry the oxidizer
|
119
|
ae4e517f-c4a6-440c-98ff-c3d8d11faf09
|
What is the key difference between a jet engine and a liquid rocket engine?
| 1
|
[
"The jet engine produce a long flamme tail after combustion",
"The jet engine is in general more expensive",
"The liquid rocket engine has to carry the oxidizer"
] |
[
0,
0,
1
] |
What is the key difference between a jet engine and a liquid rocket engine?
A. The jet engine produce a long flamme tail after combustion
B. The jet engine is in general more expensive
C. The liquid rocket engine has to carry the oxidizer
|
C. The liquid rocket engine has to carry the oxidizer
|
119
|
ae4e517f-c4a6-440c-98ff-c3d8d11faf09
|
What is the key difference between a jet engine and a liquid rocket engine?
| 2
|
[
"The jet engine is in general more expensive",
"The liquid rocket engine has to carry the oxidizer",
"The jet engine produce a long flamme tail after combustion"
] |
[
0,
1,
0
] |
What is the key difference between a jet engine and a liquid rocket engine?
A. The jet engine is in general more expensive
B. The liquid rocket engine has to carry the oxidizer
C. The jet engine produce a long flamme tail after combustion
|
B. The liquid rocket engine has to carry the oxidizer
|
120
|
c2a98060-6a75-4353-9d4a-2e157218c1d0
|
How do satellite communication missions usually cover irregular areas such as the United States, without providing bandwidth to unwanted areas (oceans, prohibited areas)?
| 0
|
[
"Utilising higher frequency bands",
"Using shaped beam reflector antennas",
"Increasing satellite altitude",
"Encrypting the signal"
] |
[
0,
1,
0,
0
] |
How do satellite communication missions usually cover irregular areas such as the United States, without providing bandwidth to unwanted areas (oceans, prohibited areas)?
A. Utilising higher frequency bands
B. Using shaped beam reflector antennas
C. Increasing satellite altitude
D. Encrypting the signal
|
B. Using shaped beam reflector antennas
|
120
|
c2a98060-6a75-4353-9d4a-2e157218c1d0
|
How do satellite communication missions usually cover irregular areas such as the United States, without providing bandwidth to unwanted areas (oceans, prohibited areas)?
| 1
|
[
"Utilising higher frequency bands",
"Encrypting the signal",
"Using shaped beam reflector antennas",
"Increasing satellite altitude"
] |
[
0,
0,
1,
0
] |
How do satellite communication missions usually cover irregular areas such as the United States, without providing bandwidth to unwanted areas (oceans, prohibited areas)?
A. Utilising higher frequency bands
B. Encrypting the signal
C. Using shaped beam reflector antennas
D. Increasing satellite altitude
|
C. Using shaped beam reflector antennas
|
120
|
c2a98060-6a75-4353-9d4a-2e157218c1d0
|
How do satellite communication missions usually cover irregular areas such as the United States, without providing bandwidth to unwanted areas (oceans, prohibited areas)?
| 2
|
[
"Increasing satellite altitude",
"Using shaped beam reflector antennas",
"Utilising higher frequency bands",
"Encrypting the signal"
] |
[
0,
1,
0,
0
] |
How do satellite communication missions usually cover irregular areas such as the United States, without providing bandwidth to unwanted areas (oceans, prohibited areas)?
A. Increasing satellite altitude
B. Using shaped beam reflector antennas
C. Utilising higher frequency bands
D. Encrypting the signal
|
B. Using shaped beam reflector antennas
|
121
|
2a970ab4-5fd5-4e03-8e66-abaa2094b2cf
|
Assuming that D_ideal is the ideal antenna maximum directivity and A_theta is the coverage area in deg^2: Which of the following is a valid formula expressing the maximum directivity achievable for an ideal antenna that covers a small solid angle?
| 0
|
[
"D_ideal = 46.15 - 10 * log(A_theta)",
"D_ideal = A_theta / log(A_theta)",
"D_ideal = 10 * log (A_theta)",
"D_ideal = exp(-A_theta)"
] |
[
1,
0,
0,
0
] |
Assuming that D_ideal is the ideal antenna maximum directivity and A_theta is the coverage area in deg^2: Which of the following is a valid formula expressing the maximum directivity achievable for an ideal antenna that covers a small solid angle?
A. D_ideal = 46.15 - 10 * log(A_theta)
B. D_ideal = A_theta / log(A_theta)
C. D_ideal = 10 * log (A_theta)
D. D_ideal = exp(-A_theta)
|
A. D_ideal = 46.15 - 10 * log(A_theta)
|
121
|
2a970ab4-5fd5-4e03-8e66-abaa2094b2cf
|
Assuming that D_ideal is the ideal antenna maximum directivity and A_theta is the coverage area in deg^2: Which of the following is a valid formula expressing the maximum directivity achievable for an ideal antenna that covers a small solid angle?
| 1
|
[
"D_ideal = exp(-A_theta)",
"D_ideal = A_theta / log(A_theta)",
"D_ideal = 46.15 - 10 * log(A_theta)",
"D_ideal = 10 * log (A_theta)"
] |
[
0,
0,
1,
0
] |
Assuming that D_ideal is the ideal antenna maximum directivity and A_theta is the coverage area in deg^2: Which of the following is a valid formula expressing the maximum directivity achievable for an ideal antenna that covers a small solid angle?
A. D_ideal = exp(-A_theta)
B. D_ideal = A_theta / log(A_theta)
C. D_ideal = 46.15 - 10 * log(A_theta)
D. D_ideal = 10 * log (A_theta)
|
C. D_ideal = 46.15 - 10 * log(A_theta)
|
121
|
2a970ab4-5fd5-4e03-8e66-abaa2094b2cf
|
Assuming that D_ideal is the ideal antenna maximum directivity and A_theta is the coverage area in deg^2: Which of the following is a valid formula expressing the maximum directivity achievable for an ideal antenna that covers a small solid angle?
| 2
|
[
"D_ideal = 46.15 - 10 * log(A_theta)",
"D_ideal = exp(-A_theta)",
"D_ideal = 10 * log (A_theta)",
"D_ideal = A_theta / log(A_theta)"
] |
[
1,
0,
0,
0
] |
Assuming that D_ideal is the ideal antenna maximum directivity and A_theta is the coverage area in deg^2: Which of the following is a valid formula expressing the maximum directivity achievable for an ideal antenna that covers a small solid angle?
A. D_ideal = 46.15 - 10 * log(A_theta)
B. D_ideal = exp(-A_theta)
C. D_ideal = 10 * log (A_theta)
D. D_ideal = A_theta / log(A_theta)
|
A. D_ideal = 46.15 - 10 * log(A_theta)
|
122
|
33c67e43-0041-4b8f-b867-37165c71c612
|
In space communication link analyses, the ideal directivity calculations do not include antenna radiated efficiency, which is a measure of the power being radiated outside of the desired coverage area. What is the typical range of antenna efficiencies to adjust the ideal directivity?
| 0
|
[
"98 to 99.5%",
"55 to 75%",
"80 to 99%",
"20 to 40%"
] |
[
0,
1,
0,
0
] |
In space communication link analyses, the ideal directivity calculations do not include antenna radiated efficiency, which is a measure of the power being radiated outside of the desired coverage area. What is the typical range of antenna efficiencies to adjust the ideal directivity?
A. 98 to 99.5%
B. 55 to 75%
C. 80 to 99%
D. 20 to 40%
|
B. 55 to 75%
|
122
|
33c67e43-0041-4b8f-b867-37165c71c612
|
In space communication link analyses, the ideal directivity calculations do not include antenna radiated efficiency, which is a measure of the power being radiated outside of the desired coverage area. What is the typical range of antenna efficiencies to adjust the ideal directivity?
| 1
|
[
"20 to 40%",
"98 to 99.5%",
"55 to 75%",
"80 to 99%"
] |
[
0,
0,
1,
0
] |
In space communication link analyses, the ideal directivity calculations do not include antenna radiated efficiency, which is a measure of the power being radiated outside of the desired coverage area. What is the typical range of antenna efficiencies to adjust the ideal directivity?
A. 20 to 40%
B. 98 to 99.5%
C. 55 to 75%
D. 80 to 99%
|
C. 55 to 75%
|
122
|
33c67e43-0041-4b8f-b867-37165c71c612
|
In space communication link analyses, the ideal directivity calculations do not include antenna radiated efficiency, which is a measure of the power being radiated outside of the desired coverage area. What is the typical range of antenna efficiencies to adjust the ideal directivity?
| 2
|
[
"98 to 99.5%",
"55 to 75%",
"20 to 40%",
"80 to 99%"
] |
[
0,
1,
0,
0
] |
In space communication link analyses, the ideal directivity calculations do not include antenna radiated efficiency, which is a measure of the power being radiated outside of the desired coverage area. What is the typical range of antenna efficiencies to adjust the ideal directivity?
A. 98 to 99.5%
B. 55 to 75%
C. 20 to 40%
D. 80 to 99%
|
B. 55 to 75%
|
123
|
c41bef86-8e11-4f1d-a082-abbcecf64bd4
|
For ground or satellite antennas, which of the following are typical contributing components to the noise temperature?
| 0
|
[
"noise temperature that originates high energy ionizing particles deposited energy hitting the antenna structure",
"noise temperature that originates from the thermally radiated energy of objects that appear within the antenna's field of view",
"noise temperature that originates from the delta-phi (smalled boresight angle possible) product with the Earth reflected magnetic field when crossing of the south atlantic anomaly (SAA)",
"noise temperature that originates from the temperature of the antenna feed structure and transmission losses within the antenna and feed assembly itself"
] |
[
0,
1,
0,
1
] |
For ground or satellite antennas, which of the following are typical contributing components to the noise temperature?
A. noise temperature that originates high energy ionizing particles deposited energy hitting the antenna structure
B. noise temperature that originates from the thermally radiated energy of objects that appear within the antenna's field of view
C. noise temperature that originates from the delta-phi (smalled boresight angle possible) product with the Earth reflected magnetic field when crossing of the south atlantic anomaly (SAA)
D. noise temperature that originates from the temperature of the antenna feed structure and transmission losses within the antenna and feed assembly itself
|
B. noise temperature that originates from the thermally radiated energy of objects that appear within the antenna's field of view
D. noise temperature that originates from the temperature of the antenna feed structure and transmission losses within the antenna and feed assembly itself
|
123
|
c41bef86-8e11-4f1d-a082-abbcecf64bd4
|
For ground or satellite antennas, which of the following are typical contributing components to the noise temperature?
| 1
|
[
"noise temperature that originates from the delta-phi (smalled boresight angle possible) product with the Earth reflected magnetic field when crossing of the south atlantic anomaly (SAA)",
"noise temperature that originates high energy ionizing particles deposited energy hitting the antenna structure",
"noise temperature that originates from the thermally radiated energy of objects that appear within the antenna's field of view",
"noise temperature that originates from the temperature of the antenna feed structure and transmission losses within the antenna and feed assembly itself"
] |
[
0,
0,
1,
1
] |
For ground or satellite antennas, which of the following are typical contributing components to the noise temperature?
A. noise temperature that originates from the delta-phi (smalled boresight angle possible) product with the Earth reflected magnetic field when crossing of the south atlantic anomaly (SAA)
B. noise temperature that originates high energy ionizing particles deposited energy hitting the antenna structure
C. noise temperature that originates from the thermally radiated energy of objects that appear within the antenna's field of view
D. noise temperature that originates from the temperature of the antenna feed structure and transmission losses within the antenna and feed assembly itself
|
C. noise temperature that originates from the thermally radiated energy of objects that appear within the antenna's field of view
D. noise temperature that originates from the temperature of the antenna feed structure and transmission losses within the antenna and feed assembly itself
|
123
|
c41bef86-8e11-4f1d-a082-abbcecf64bd4
|
For ground or satellite antennas, which of the following are typical contributing components to the noise temperature?
| 2
|
[
"noise temperature that originates from the delta-phi (smalled boresight angle possible) product with the Earth reflected magnetic field when crossing of the south atlantic anomaly (SAA)",
"noise temperature that originates from the thermally radiated energy of objects that appear within the antenna's field of view",
"noise temperature that originates from the temperature of the antenna feed structure and transmission losses within the antenna and feed assembly itself",
"noise temperature that originates high energy ionizing particles deposited energy hitting the antenna structure"
] |
[
0,
1,
1,
0
] |
For ground or satellite antennas, which of the following are typical contributing components to the noise temperature?
A. noise temperature that originates from the delta-phi (smalled boresight angle possible) product with the Earth reflected magnetic field when crossing of the south atlantic anomaly (SAA)
B. noise temperature that originates from the thermally radiated energy of objects that appear within the antenna's field of view
C. noise temperature that originates from the temperature of the antenna feed structure and transmission losses within the antenna and feed assembly itself
D. noise temperature that originates high energy ionizing particles deposited energy hitting the antenna structure
|
B. noise temperature that originates from the thermally radiated energy of objects that appear within the antenna's field of view
C. noise temperature that originates from the temperature of the antenna feed structure and transmission losses within the antenna and feed assembly itself
|
124
|
815136a9-3969-44c6-87d5-8bcea3f9517c
|
What are realistic mission objectives for a missions to Mars?
| 0
|
[
"Geological and topological study to understand the historical Mars-Earth collision which led to the creation of Earth's Moon.",
"Oild fields scoutting for future super tanker missions",
"ISRU Technology Demonstration",
"Search for scientific evidence for past life on Mars"
] |
[
0,
0,
1,
1
] |
What are realistic mission objectives for a missions to Mars?
A. Geological and topological study to understand the historical Mars-Earth collision which led to the creation of Earth's Moon.
B. Oild fields scoutting for future super tanker missions
C. ISRU Technology Demonstration
D. Search for scientific evidence for past life on Mars
|
C. ISRU Technology Demonstration
D. Search for scientific evidence for past life on Mars
|
124
|
815136a9-3969-44c6-87d5-8bcea3f9517c
|
What are realistic mission objectives for a missions to Mars?
| 1
|
[
"Search for scientific evidence for past life on Mars",
"Geological and topological study to understand the historical Mars-Earth collision which led to the creation of Earth's Moon.",
"Oild fields scoutting for future super tanker missions",
"ISRU Technology Demonstration"
] |
[
1,
0,
0,
1
] |
What are realistic mission objectives for a missions to Mars?
A. Search for scientific evidence for past life on Mars
B. Geological and topological study to understand the historical Mars-Earth collision which led to the creation of Earth's Moon.
C. Oild fields scoutting for future super tanker missions
D. ISRU Technology Demonstration
|
A. Search for scientific evidence for past life on Mars
D. ISRU Technology Demonstration
|
124
|
815136a9-3969-44c6-87d5-8bcea3f9517c
|
What are realistic mission objectives for a missions to Mars?
| 2
|
[
"ISRU Technology Demonstration",
"Search for scientific evidence for past life on Mars",
"Geological and topological study to understand the historical Mars-Earth collision which led to the creation of Earth's Moon.",
"Oild fields scoutting for future super tanker missions"
] |
[
1,
1,
0,
0
] |
What are realistic mission objectives for a missions to Mars?
A. ISRU Technology Demonstration
B. Search for scientific evidence for past life on Mars
C. Geological and topological study to understand the historical Mars-Earth collision which led to the creation of Earth's Moon.
D. Oild fields scoutting for future super tanker missions
|
A. ISRU Technology Demonstration
B. Search for scientific evidence for past life on Mars
|
125
|
cc48db84-1b81-4670-a195-076dee267592
|
How long would a typical human crewed mission to Mars last (only the duration of the trip to reach Mars) for conjunction-type missions?
| 0
|
[
"more than 7 years",
"3 to 4 months",
"3 to 4 years",
"6 to 9 months"
] |
[
0,
0,
0,
1
] |
How long would a typical human crewed mission to Mars last (only the duration of the trip to reach Mars) for conjunction-type missions?
A. more than 7 years
B. 3 to 4 months
C. 3 to 4 years
D. 6 to 9 months
|
D. 6 to 9 months
|
125
|
cc48db84-1b81-4670-a195-076dee267592
|
How long would a typical human crewed mission to Mars last (only the duration of the trip to reach Mars) for conjunction-type missions?
| 1
|
[
"3 to 4 months",
"3 to 4 years",
"6 to 9 months",
"more than 7 years"
] |
[
0,
0,
1,
0
] |
How long would a typical human crewed mission to Mars last (only the duration of the trip to reach Mars) for conjunction-type missions?
A. 3 to 4 months
B. 3 to 4 years
C. 6 to 9 months
D. more than 7 years
|
C. 6 to 9 months
|
125
|
cc48db84-1b81-4670-a195-076dee267592
|
How long would a typical human crewed mission to Mars last (only the duration of the trip to reach Mars) for conjunction-type missions?
| 2
|
[
"6 to 9 months",
"3 to 4 months",
"3 to 4 years",
"more than 7 years"
] |
[
1,
0,
0,
0
] |
How long would a typical human crewed mission to Mars last (only the duration of the trip to reach Mars) for conjunction-type missions?
A. 6 to 9 months
B. 3 to 4 months
C. 3 to 4 years
D. more than 7 years
|
A. 6 to 9 months
|
126
|
73bf0237-afac-4dd9-a330-d8fcb3580379
|
How are the two types chemical compounds of bipropellant propulsion systems called?
| 0
|
[
"igniter and oxidizer",
"fuel and oxidizer",
"Igniter and fuel"
] |
[
0,
1,
0
] |
How are the two types chemical compounds of bipropellant propulsion systems called?
A. igniter and oxidizer
B. fuel and oxidizer
C. Igniter and fuel
|
B. fuel and oxidizer
|
126
|
73bf0237-afac-4dd9-a330-d8fcb3580379
|
How are the two types chemical compounds of bipropellant propulsion systems called?
| 1
|
[
"Igniter and fuel",
"fuel and oxidizer",
"igniter and oxidizer"
] |
[
0,
1,
0
] |
How are the two types chemical compounds of bipropellant propulsion systems called?
A. Igniter and fuel
B. fuel and oxidizer
C. igniter and oxidizer
|
B. fuel and oxidizer
|
126
|
73bf0237-afac-4dd9-a330-d8fcb3580379
|
How are the two types chemical compounds of bipropellant propulsion systems called?
| 2
|
[
"fuel and oxidizer",
"igniter and oxidizer",
"Igniter and fuel"
] |
[
1,
0,
0
] |
How are the two types chemical compounds of bipropellant propulsion systems called?
A. fuel and oxidizer
B. igniter and oxidizer
C. Igniter and fuel
|
A. fuel and oxidizer
|
127
|
64fc0fa7-43af-41d6-b8c4-268ba0c928c8
|
Which of the following rocket engine(s) is / were manufactured by "Aerojet" ?
| 0
|
[
"MONARC-445",
"CHT-20",
"MR-111C"
] |
[
0,
0,
1
] |
Which of the following rocket engine(s) is / were manufactured by "Aerojet" ?
A. MONARC-445
B. CHT-20
C. MR-111C
|
C. MR-111C
|
127
|
64fc0fa7-43af-41d6-b8c4-268ba0c928c8
|
Which of the following rocket engine(s) is / were manufactured by "Aerojet" ?
| 1
|
[
"MR-111C",
"CHT-20",
"MONARC-445"
] |
[
1,
0,
0
] |
Which of the following rocket engine(s) is / were manufactured by "Aerojet" ?
A. MR-111C
B. CHT-20
C. MONARC-445
|
A. MR-111C
|
127
|
64fc0fa7-43af-41d6-b8c4-268ba0c928c8
|
Which of the following rocket engine(s) is / were manufactured by "Aerojet" ?
| 2
|
[
"CHT-20",
"MR-111C",
"MONARC-445"
] |
[
0,
1,
0
] |
Which of the following rocket engine(s) is / were manufactured by "Aerojet" ?
A. CHT-20
B. MR-111C
C. MONARC-445
|
B. MR-111C
|
129
|
ea7c422b-60f6-4178-9732-0d615939c26f
|
Select all the combinations of propulsion system and applications that are typical among the following?
| 0
|
[
"Liquid monopropellant for attitude control",
"Liquid bipropellant for orbit insertion",
"Electric propulsion for orbit maintenance and maneuvering",
"Cold Gas propulsion for orbit insertion",
"Liquid monopropellant for orbit insertion",
"Solid propulsion for orbit insertion"
] |
[
1,
1,
1,
0,
0,
1
] |
Select all the combinations of propulsion system and applications that are typical among the following?
A. Liquid monopropellant for attitude control
B. Liquid bipropellant for orbit insertion
C. Electric propulsion for orbit maintenance and maneuvering
D. Cold Gas propulsion for orbit insertion
E. Liquid monopropellant for orbit insertion
F. Solid propulsion for orbit insertion
|
A. Liquid monopropellant for attitude control
B. Liquid bipropellant for orbit insertion
C. Electric propulsion for orbit maintenance and maneuvering
F. Solid propulsion for orbit insertion
|
129
|
ea7c422b-60f6-4178-9732-0d615939c26f
|
Select all the combinations of propulsion system and applications that are typical among the following?
| 1
|
[
"Solid propulsion for orbit insertion",
"Liquid monopropellant for orbit insertion",
"Cold Gas propulsion for orbit insertion",
"Liquid bipropellant for orbit insertion",
"Liquid monopropellant for attitude control",
"Electric propulsion for orbit maintenance and maneuvering"
] |
[
1,
0,
0,
1,
1,
1
] |
Select all the combinations of propulsion system and applications that are typical among the following?
A. Solid propulsion for orbit insertion
B. Liquid monopropellant for orbit insertion
C. Cold Gas propulsion for orbit insertion
D. Liquid bipropellant for orbit insertion
E. Liquid monopropellant for attitude control
F. Electric propulsion for orbit maintenance and maneuvering
|
A. Solid propulsion for orbit insertion
D. Liquid bipropellant for orbit insertion
E. Liquid monopropellant for attitude control
F. Electric propulsion for orbit maintenance and maneuvering
|
129
|
ea7c422b-60f6-4178-9732-0d615939c26f
|
Select all the combinations of propulsion system and applications that are typical among the following?
| 2
|
[
"Cold Gas propulsion for orbit insertion",
"Liquid monopropellant for attitude control",
"Electric propulsion for orbit maintenance and maneuvering",
"Liquid monopropellant for orbit insertion",
"Solid propulsion for orbit insertion",
"Liquid bipropellant for orbit insertion"
] |
[
0,
1,
1,
0,
1,
1
] |
Select all the combinations of propulsion system and applications that are typical among the following?
A. Cold Gas propulsion for orbit insertion
B. Liquid monopropellant for attitude control
C. Electric propulsion for orbit maintenance and maneuvering
D. Liquid monopropellant for orbit insertion
E. Solid propulsion for orbit insertion
F. Liquid bipropellant for orbit insertion
|
B. Liquid monopropellant for attitude control
C. Electric propulsion for orbit maintenance and maneuvering
E. Solid propulsion for orbit insertion
F. Liquid bipropellant for orbit insertion
|
130
|
3f9f6c75-740b-4c5f-a010-231506efad98
|
What is the typical range of specific impulse for liquid monopropellant systems?
| 0
|
[
"200 - 235s",
"500 - 3000s",
"45 - 75s",
"274 - 467s"
] |
[
1,
0,
0,
0
] |
What is the typical range of specific impulse for liquid monopropellant systems?
A. 200 - 235s
B. 500 - 3000s
C. 45 - 75s
D. 274 - 467s
|
A. 200 - 235s
|
130
|
3f9f6c75-740b-4c5f-a010-231506efad98
|
What is the typical range of specific impulse for liquid monopropellant systems?
| 1
|
[
"500 - 3000s",
"274 - 467s",
"45 - 75s",
"200 - 235s"
] |
[
0,
0,
0,
1
] |
What is the typical range of specific impulse for liquid monopropellant systems?
A. 500 - 3000s
B. 274 - 467s
C. 45 - 75s
D. 200 - 235s
|
D. 200 - 235s
|
130
|
3f9f6c75-740b-4c5f-a010-231506efad98
|
What is the typical range of specific impulse for liquid monopropellant systems?
| 2
|
[
"45 - 75s",
"274 - 467s",
"200 - 235s",
"500 - 3000s"
] |
[
0,
0,
1,
0
] |
What is the typical range of specific impulse for liquid monopropellant systems?
A. 45 - 75s
B. 274 - 467s
C. 200 - 235s
D. 500 - 3000s
|
C. 200 - 235s
|
131
|
beefd301-4e93-4e57-923b-3d992f6e8030
|
Select all the advantages of monopropellant hydrazine propulsion systems over bipropellants propulsion systems?
| 0
|
[
"lower toxicity",
"system simplicity",
"capability to restart",
"long term storability",
"higher specific impulse"
] |
[
0,
1,
1,
1,
0
] |
Select all the advantages of monopropellant hydrazine propulsion systems over bipropellants propulsion systems?
A. lower toxicity
B. system simplicity
C. capability to restart
D. long term storability
E. higher specific impulse
|
B. system simplicity
C. capability to restart
D. long term storability
|
131
|
beefd301-4e93-4e57-923b-3d992f6e8030
|
Select all the advantages of monopropellant hydrazine propulsion systems over bipropellants propulsion systems?
| 1
|
[
"system simplicity",
"capability to restart",
"lower toxicity",
"higher specific impulse",
"long term storability"
] |
[
1,
1,
0,
0,
1
] |
Select all the advantages of monopropellant hydrazine propulsion systems over bipropellants propulsion systems?
A. system simplicity
B. capability to restart
C. lower toxicity
D. higher specific impulse
E. long term storability
|
A. system simplicity
B. capability to restart
E. long term storability
|
131
|
beefd301-4e93-4e57-923b-3d992f6e8030
|
Select all the advantages of monopropellant hydrazine propulsion systems over bipropellants propulsion systems?
| 2
|
[
"lower toxicity",
"system simplicity",
"higher specific impulse",
"long term storability",
"capability to restart"
] |
[
0,
1,
0,
1,
1
] |
Select all the advantages of monopropellant hydrazine propulsion systems over bipropellants propulsion systems?
A. lower toxicity
B. system simplicity
C. higher specific impulse
D. long term storability
E. capability to restart
|
B. system simplicity
D. long term storability
E. capability to restart
|
132
|
2870f350-5488-40da-bd0c-e026b991b01f
|
How does the combustion takes place for hydrazine monoprop system?
| 0
|
[
"Hydrazine ignites spontaneous in contact of an hydrogen isotope, typically deuterium",
"Hydrazine decomposes on a micro-fluidic chip, typically made of palladium enriched carbon nanotubes in a sillicon wafer",
"Hydrazine decomposes on a catalyst material, typically iridium",
"Hydrazine ignites spontaneous in presence of an high-voltage electric discharge, typically 20,000 - 30,000 Volts"
] |
[
0,
0,
1,
0
] |
How does the combustion takes place for hydrazine monoprop system?
A. Hydrazine ignites spontaneous in contact of an hydrogen isotope, typically deuterium
B. Hydrazine decomposes on a micro-fluidic chip, typically made of palladium enriched carbon nanotubes in a sillicon wafer
C. Hydrazine decomposes on a catalyst material, typically iridium
D. Hydrazine ignites spontaneous in presence of an high-voltage electric discharge, typically 20,000 - 30,000 Volts
|
C. Hydrazine decomposes on a catalyst material, typically iridium
|
132
|
2870f350-5488-40da-bd0c-e026b991b01f
|
How does the combustion takes place for hydrazine monoprop system?
| 1
|
[
"Hydrazine ignites spontaneous in contact of an hydrogen isotope, typically deuterium",
"Hydrazine ignites spontaneous in presence of an high-voltage electric discharge, typically 20,000 - 30,000 Volts",
"Hydrazine decomposes on a catalyst material, typically iridium",
"Hydrazine decomposes on a micro-fluidic chip, typically made of palladium enriched carbon nanotubes in a sillicon wafer"
] |
[
0,
0,
1,
0
] |
How does the combustion takes place for hydrazine monoprop system?
A. Hydrazine ignites spontaneous in contact of an hydrogen isotope, typically deuterium
B. Hydrazine ignites spontaneous in presence of an high-voltage electric discharge, typically 20,000 - 30,000 Volts
C. Hydrazine decomposes on a catalyst material, typically iridium
D. Hydrazine decomposes on a micro-fluidic chip, typically made of palladium enriched carbon nanotubes in a sillicon wafer
|
C. Hydrazine decomposes on a catalyst material, typically iridium
|
132
|
2870f350-5488-40da-bd0c-e026b991b01f
|
How does the combustion takes place for hydrazine monoprop system?
| 2
|
[
"Hydrazine ignites spontaneous in contact of an hydrogen isotope, typically deuterium",
"Hydrazine decomposes on a micro-fluidic chip, typically made of palladium enriched carbon nanotubes in a sillicon wafer",
"Hydrazine ignites spontaneous in presence of an high-voltage electric discharge, typically 20,000 - 30,000 Volts",
"Hydrazine decomposes on a catalyst material, typically iridium"
] |
[
0,
0,
0,
1
] |
How does the combustion takes place for hydrazine monoprop system?
A. Hydrazine ignites spontaneous in contact of an hydrogen isotope, typically deuterium
B. Hydrazine decomposes on a micro-fluidic chip, typically made of palladium enriched carbon nanotubes in a sillicon wafer
C. Hydrazine ignites spontaneous in presence of an high-voltage electric discharge, typically 20,000 - 30,000 Volts
D. Hydrazine decomposes on a catalyst material, typically iridium
|
D. Hydrazine decomposes on a catalyst material, typically iridium
|
133
|
1a348c80-de10-43bc-ba82-d74ad7fd1f69
|
What is the name of the nozzle cooling technique, sometimes using in expander cycles, where one of the propellant (usually the fuel but not always) passes around the nozzle to cool it?
| 0
|
[
"Film cooling",
"Ablative cooling",
"Regenerative cooling"
] |
[
0,
0,
1
] |
What is the name of the nozzle cooling technique, sometimes using in expander cycles, where one of the propellant (usually the fuel but not always) passes around the nozzle to cool it?
A. Film cooling
B. Ablative cooling
C. Regenerative cooling
|
C. Regenerative cooling
|
133
|
1a348c80-de10-43bc-ba82-d74ad7fd1f69
|
What is the name of the nozzle cooling technique, sometimes using in expander cycles, where one of the propellant (usually the fuel but not always) passes around the nozzle to cool it?
| 1
|
[
"Ablative cooling",
"Regenerative cooling",
"Film cooling"
] |
[
0,
1,
0
] |
What is the name of the nozzle cooling technique, sometimes using in expander cycles, where one of the propellant (usually the fuel but not always) passes around the nozzle to cool it?
A. Ablative cooling
B. Regenerative cooling
C. Film cooling
|
B. Regenerative cooling
|
133
|
1a348c80-de10-43bc-ba82-d74ad7fd1f69
|
What is the name of the nozzle cooling technique, sometimes using in expander cycles, where one of the propellant (usually the fuel but not always) passes around the nozzle to cool it?
| 2
|
[
"Regenerative cooling",
"Ablative cooling",
"Film cooling"
] |
[
1,
0,
0
] |
What is the name of the nozzle cooling technique, sometimes using in expander cycles, where one of the propellant (usually the fuel but not always) passes around the nozzle to cool it?
A. Regenerative cooling
B. Ablative cooling
C. Film cooling
|
A. Regenerative cooling
|
134
|
ebd8e218-ba8f-482c-b7e1-6ee1eb7c92ec
|
What does ablative cooling in rocket engine propulsion systems refer to?
| 0
|
[
"chamber walls made of ablative material which decomposes into gas when heat up, hence acting as a coolant",
"combustion-generated heat is conducted through the chamber walls and rejected through radiation",
"the heat is absorbed by a thin film coating made of ablatium"
] |
[
1,
0,
0
] |
What does ablative cooling in rocket engine propulsion systems refer to?
A. chamber walls made of ablative material which decomposes into gas when heat up, hence acting as a coolant
B. combustion-generated heat is conducted through the chamber walls and rejected through radiation
C. the heat is absorbed by a thin film coating made of ablatium
|
A. chamber walls made of ablative material which decomposes into gas when heat up, hence acting as a coolant
|
134
|
ebd8e218-ba8f-482c-b7e1-6ee1eb7c92ec
|
What does ablative cooling in rocket engine propulsion systems refer to?
| 1
|
[
"the heat is absorbed by a thin film coating made of ablatium",
"combustion-generated heat is conducted through the chamber walls and rejected through radiation",
"chamber walls made of ablative material which decomposes into gas when heat up, hence acting as a coolant"
] |
[
0,
0,
1
] |
What does ablative cooling in rocket engine propulsion systems refer to?
A. the heat is absorbed by a thin film coating made of ablatium
B. combustion-generated heat is conducted through the chamber walls and rejected through radiation
C. chamber walls made of ablative material which decomposes into gas when heat up, hence acting as a coolant
|
C. chamber walls made of ablative material which decomposes into gas when heat up, hence acting as a coolant
|
134
|
ebd8e218-ba8f-482c-b7e1-6ee1eb7c92ec
|
What does ablative cooling in rocket engine propulsion systems refer to?
| 2
|
[
"combustion-generated heat is conducted through the chamber walls and rejected through radiation",
"chamber walls made of ablative material which decomposes into gas when heat up, hence acting as a coolant",
"the heat is absorbed by a thin film coating made of ablatium"
] |
[
0,
1,
0
] |
What does ablative cooling in rocket engine propulsion systems refer to?
A. combustion-generated heat is conducted through the chamber walls and rejected through radiation
B. chamber walls made of ablative material which decomposes into gas when heat up, hence acting as a coolant
C. the heat is absorbed by a thin film coating made of ablatium
|
B. chamber walls made of ablative material which decomposes into gas when heat up, hence acting as a coolant
|
135
|
19af499b-7a42-4a72-b393-e63bb4fd6e5c
|
What does AOCS usually refer to in Astronautics?
| 0
|
[
"Attitude and Orbit Control System",
"Aerodynamic Optimization for Crew Safety",
"Astronomical Observation and Calculation System",
"Advanced Orbital Communication Satellite"
] |
[
1,
0,
0,
0
] |
What does AOCS usually refer to in Astronautics?
A. Attitude and Orbit Control System
B. Aerodynamic Optimization for Crew Safety
C. Astronomical Observation and Calculation System
D. Advanced Orbital Communication Satellite
|
A. Attitude and Orbit Control System
|
135
|
19af499b-7a42-4a72-b393-e63bb4fd6e5c
|
What does AOCS usually refer to in Astronautics?
| 1
|
[
"Attitude and Orbit Control System",
"Advanced Orbital Communication Satellite",
"Astronomical Observation and Calculation System",
"Aerodynamic Optimization for Crew Safety"
] |
[
1,
0,
0,
0
] |
What does AOCS usually refer to in Astronautics?
A. Attitude and Orbit Control System
B. Advanced Orbital Communication Satellite
C. Astronomical Observation and Calculation System
D. Aerodynamic Optimization for Crew Safety
|
A. Attitude and Orbit Control System
|
135
|
19af499b-7a42-4a72-b393-e63bb4fd6e5c
|
What does AOCS usually refer to in Astronautics?
| 2
|
[
"Astronomical Observation and Calculation System",
"Aerodynamic Optimization for Crew Safety",
"Attitude and Orbit Control System",
"Advanced Orbital Communication Satellite"
] |
[
0,
0,
1,
0
] |
What does AOCS usually refer to in Astronautics?
A. Astronomical Observation and Calculation System
B. Aerodynamic Optimization for Crew Safety
C. Attitude and Orbit Control System
D. Advanced Orbital Communication Satellite
|
C. Attitude and Orbit Control System
|
137
|
70710915-a079-49fd-874a-28d9470489ea
|
In the LVLH coordinate system that is often used for AOCS, what is the direction of each axis ofr a spacecraft on orbit around the Earth?
| 0
|
[
"X towards the center of the Earth, Y towards the rear of the spacecraft, Z towards the north of the orbit",
"X towards the spacecraft velocity vector, Y towards the south of the orbit, Z towards the center of the Earth",
"X towards the Noth of the orbit, Y towards the center of the Earth, Z towards the spacecraft velocity vector"
] |
[
0,
1,
0
] |
In the LVLH coordinate system that is often used for AOCS, what is the direction of each axis ofr a spacecraft on orbit around the Earth?
A. X towards the center of the Earth, Y towards the rear of the spacecraft, Z towards the north of the orbit
B. X towards the spacecraft velocity vector, Y towards the south of the orbit, Z towards the center of the Earth
C. X towards the Noth of the orbit, Y towards the center of the Earth, Z towards the spacecraft velocity vector
|
B. X towards the spacecraft velocity vector, Y towards the south of the orbit, Z towards the center of the Earth
|
137
|
70710915-a079-49fd-874a-28d9470489ea
|
In the LVLH coordinate system that is often used for AOCS, what is the direction of each axis ofr a spacecraft on orbit around the Earth?
| 1
|
[
"X towards the Noth of the orbit, Y towards the center of the Earth, Z towards the spacecraft velocity vector",
"X towards the center of the Earth, Y towards the rear of the spacecraft, Z towards the north of the orbit",
"X towards the spacecraft velocity vector, Y towards the south of the orbit, Z towards the center of the Earth"
] |
[
0,
0,
1
] |
In the LVLH coordinate system that is often used for AOCS, what is the direction of each axis ofr a spacecraft on orbit around the Earth?
A. X towards the Noth of the orbit, Y towards the center of the Earth, Z towards the spacecraft velocity vector
B. X towards the center of the Earth, Y towards the rear of the spacecraft, Z towards the north of the orbit
C. X towards the spacecraft velocity vector, Y towards the south of the orbit, Z towards the center of the Earth
|
C. X towards the spacecraft velocity vector, Y towards the south of the orbit, Z towards the center of the Earth
|
137
|
70710915-a079-49fd-874a-28d9470489ea
|
In the LVLH coordinate system that is often used for AOCS, what is the direction of each axis ofr a spacecraft on orbit around the Earth?
| 2
|
[
"X towards the Noth of the orbit, Y towards the center of the Earth, Z towards the spacecraft velocity vector",
"X towards the spacecraft velocity vector, Y towards the south of the orbit, Z towards the center of the Earth",
"X towards the center of the Earth, Y towards the rear of the spacecraft, Z towards the north of the orbit"
] |
[
0,
1,
0
] |
In the LVLH coordinate system that is often used for AOCS, what is the direction of each axis ofr a spacecraft on orbit around the Earth?
A. X towards the Noth of the orbit, Y towards the center of the Earth, Z towards the spacecraft velocity vector
B. X towards the spacecraft velocity vector, Y towards the south of the orbit, Z towards the center of the Earth
C. X towards the center of the Earth, Y towards the rear of the spacecraft, Z towards the north of the orbit
|
B. X towards the spacecraft velocity vector, Y towards the south of the orbit, Z towards the center of the Earth
|
138
|
e904a2e2-67c6-4da6-820e-1861b040d617
|
ISS and Space Shuttle euler sequence was Pitch, Yaw, Roll. This is difference from most spacecraft. Which Euler sequence do spacecrafts in general?
| 0
|
[
"Roll Yaw Pitch (RYP)",
"Roll Pitch Yaw (RPY)",
"Yaw Pitch Roll (YPR)",
"Yaw Roll Pitch (YRP)"
] |
[
0,
0,
1,
0
] |
ISS and Space Shuttle euler sequence was Pitch, Yaw, Roll. This is difference from most spacecraft. Which Euler sequence do spacecrafts in general?
A. Roll Yaw Pitch (RYP)
B. Roll Pitch Yaw (RPY)
C. Yaw Pitch Roll (YPR)
D. Yaw Roll Pitch (YRP)
|
C. Yaw Pitch Roll (YPR)
|
138
|
e904a2e2-67c6-4da6-820e-1861b040d617
|
ISS and Space Shuttle euler sequence was Pitch, Yaw, Roll. This is difference from most spacecraft. Which Euler sequence do spacecrafts in general?
| 1
|
[
"Yaw Pitch Roll (YPR)",
"Roll Yaw Pitch (RYP)",
"Roll Pitch Yaw (RPY)",
"Yaw Roll Pitch (YRP)"
] |
[
1,
0,
0,
0
] |
ISS and Space Shuttle euler sequence was Pitch, Yaw, Roll. This is difference from most spacecraft. Which Euler sequence do spacecrafts in general?
A. Yaw Pitch Roll (YPR)
B. Roll Yaw Pitch (RYP)
C. Roll Pitch Yaw (RPY)
D. Yaw Roll Pitch (YRP)
|
A. Yaw Pitch Roll (YPR)
|
138
|
e904a2e2-67c6-4da6-820e-1861b040d617
|
ISS and Space Shuttle euler sequence was Pitch, Yaw, Roll. This is difference from most spacecraft. Which Euler sequence do spacecrafts in general?
| 2
|
[
"Yaw Roll Pitch (YRP)",
"Roll Yaw Pitch (RYP)",
"Roll Pitch Yaw (RPY)",
"Yaw Pitch Roll (YPR)"
] |
[
0,
0,
0,
1
] |
ISS and Space Shuttle euler sequence was Pitch, Yaw, Roll. This is difference from most spacecraft. Which Euler sequence do spacecrafts in general?
A. Yaw Roll Pitch (YRP)
B. Roll Yaw Pitch (RYP)
C. Roll Pitch Yaw (RPY)
D. Yaw Pitch Roll (YPR)
|
D. Yaw Pitch Roll (YPR)
|
139
|
c2bd96c1-08db-4bb3-bdc0-67097d6f174c
|
How it is possible to maintain a certain orientation by spinning a spacecraft?
| 0
|
[
"Due to the electron spin",
"Due to the gyroscopic effect",
"Due to the rotational speed being waved"
] |
[
0,
1,
0
] |
How it is possible to maintain a certain orientation by spinning a spacecraft?
A. Due to the electron spin
B. Due to the gyroscopic effect
C. Due to the rotational speed being waved
|
B. Due to the gyroscopic effect
|
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