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
|
|---|---|---|---|---|---|---|---|
34
|
bef97b27-a677-488c-9088-b835c0f3d1a8
|
Which formula gives the work to be performed in order to bring a unit mass from the Earth's surface to infinity? Assume that g0 is the standard gravitational acceleration for the surface of the Earth, R is the radius of the Earth, and p the atmospheric pressure.
| 1
|
[
"g0 * R * p",
"g0 * R^2",
"g0 * R * p^2",
"g0 * R"
] |
[
0,
0,
0,
1
] |
Which formula gives the work to be performed in order to bring a unit mass from the Earth's surface to infinity? Assume that g0 is the standard gravitational acceleration for the surface of the Earth, R is the radius of the Earth, and p the atmospheric pressure.
A. g0 * R * p
B. g0 * R^2
C. g0 * R * p^2
D. g0 * R
|
D. g0 * R
|
34
|
bef97b27-a677-488c-9088-b835c0f3d1a8
|
Which formula gives the work to be performed in order to bring a unit mass from the Earth's surface to infinity? Assume that g0 is the standard gravitational acceleration for the surface of the Earth, R is the radius of the Earth, and p the atmospheric pressure.
| 2
|
[
"g0 * R",
"g0 * R^2",
"g0 * R * p",
"g0 * R * p^2"
] |
[
1,
0,
0,
0
] |
Which formula gives the work to be performed in order to bring a unit mass from the Earth's surface to infinity? Assume that g0 is the standard gravitational acceleration for the surface of the Earth, R is the radius of the Earth, and p the atmospheric pressure.
A. g0 * R
B. g0 * R^2
C. g0 * R * p
D. g0 * R * p^2
|
A. g0 * R
|
35
|
57080b4d-b331-4816-985f-c76f499662f6
|
What is the formula to compute the escape velocity given mu (standard gravitational parameter), and r (the distance to the center of the central body)?
| 0
|
[
"V = sqrt( mu / 2r )",
"V = sqrt( 2 * mu / r )",
"V = sqrt( 2 * mu / r^3 )",
"V = sqrt( mu / r )",
"V = mu * r"
] |
[
0,
1,
0,
0,
0
] |
What is the formula to compute the escape velocity given mu (standard gravitational parameter), and r (the distance to the center of the central body)?
A. V = sqrt( mu / 2r )
B. V = sqrt( 2 * mu / r )
C. V = sqrt( 2 * mu / r^3 )
D. V = sqrt( mu / r )
E. V = mu * r
|
B. V = sqrt( 2 * mu / r )
|
35
|
57080b4d-b331-4816-985f-c76f499662f6
|
What is the formula to compute the escape velocity given mu (standard gravitational parameter), and r (the distance to the center of the central body)?
| 1
|
[
"V = sqrt( mu / 2r )",
"V = sqrt( 2 * mu / r^3 )",
"V = sqrt( mu / r )",
"V = sqrt( 2 * mu / r )",
"V = mu * r"
] |
[
0,
0,
0,
1,
0
] |
What is the formula to compute the escape velocity given mu (standard gravitational parameter), and r (the distance to the center of the central body)?
A. V = sqrt( mu / 2r )
B. V = sqrt( 2 * mu / r^3 )
C. V = sqrt( mu / r )
D. V = sqrt( 2 * mu / r )
E. V = mu * r
|
D. V = sqrt( 2 * mu / r )
|
35
|
57080b4d-b331-4816-985f-c76f499662f6
|
What is the formula to compute the escape velocity given mu (standard gravitational parameter), and r (the distance to the center of the central body)?
| 2
|
[
"V = sqrt( mu / r )",
"V = sqrt( mu / 2r )",
"V = sqrt( 2 * mu / r )",
"V = mu * r",
"V = sqrt( 2 * mu / r^3 )"
] |
[
0,
0,
1,
0,
0
] |
What is the formula to compute the escape velocity given mu (standard gravitational parameter), and r (the distance to the center of the central body)?
A. V = sqrt( mu / r )
B. V = sqrt( mu / 2r )
C. V = sqrt( 2 * mu / r )
D. V = mu * r
E. V = sqrt( 2 * mu / r^3 )
|
C. V = sqrt( 2 * mu / r )
|
36
|
808bd743-7703-452b-a0bb-05516948c7d4
|
The gravitational acceleration at the altitude of the ISS is about 8.68 m/s. However, the astronauts onboard the station are in weightlessness. Why?
| 0
|
[
"The ISS is constantly rotating around its main axis, creating the illusion of weightlessness.",
"The ISS is constanly falling towards the Earth, but with enough horizontal speed to create an opposing acceleration and equal in magnitude to the gravitational acceleration.",
"Thrusters are in constant use which generate a force such that there is weightlessness.",
"None of the above."
] |
[
0,
1,
0,
0
] |
The gravitational acceleration at the altitude of the ISS is about 8.68 m/s. However, the astronauts onboard the station are in weightlessness. Why?
A. The ISS is constantly rotating around its main axis, creating the illusion of weightlessness.
B. The ISS is constanly falling towards the Earth, but with enough horizontal speed to create an opposing acceleration and equal in magnitude to the gravitational acceleration.
C. Thrusters are in constant use which generate a force such that there is weightlessness.
D. None of the above.
|
B. The ISS is constanly falling towards the Earth, but with enough horizontal speed to create an opposing acceleration and equal in magnitude to the gravitational acceleration.
|
36
|
808bd743-7703-452b-a0bb-05516948c7d4
|
The gravitational acceleration at the altitude of the ISS is about 8.68 m/s. However, the astronauts onboard the station are in weightlessness. Why?
| 1
|
[
"Thrusters are in constant use which generate a force such that there is weightlessness.",
"None of the above.",
"The ISS is constanly falling towards the Earth, but with enough horizontal speed to create an opposing acceleration and equal in magnitude to the gravitational acceleration.",
"The ISS is constantly rotating around its main axis, creating the illusion of weightlessness."
] |
[
0,
0,
1,
0
] |
The gravitational acceleration at the altitude of the ISS is about 8.68 m/s. However, the astronauts onboard the station are in weightlessness. Why?
A. Thrusters are in constant use which generate a force such that there is weightlessness.
B. None of the above.
C. The ISS is constanly falling towards the Earth, but with enough horizontal speed to create an opposing acceleration and equal in magnitude to the gravitational acceleration.
D. The ISS is constantly rotating around its main axis, creating the illusion of weightlessness.
|
C. The ISS is constanly falling towards the Earth, but with enough horizontal speed to create an opposing acceleration and equal in magnitude to the gravitational acceleration.
|
36
|
808bd743-7703-452b-a0bb-05516948c7d4
|
The gravitational acceleration at the altitude of the ISS is about 8.68 m/s. However, the astronauts onboard the station are in weightlessness. Why?
| 2
|
[
"The ISS is constanly falling towards the Earth, but with enough horizontal speed to create an opposing acceleration and equal in magnitude to the gravitational acceleration.",
"None of the above.",
"The ISS is constantly rotating around its main axis, creating the illusion of weightlessness.",
"Thrusters are in constant use which generate a force such that there is weightlessness."
] |
[
1,
0,
0,
0
] |
The gravitational acceleration at the altitude of the ISS is about 8.68 m/s. However, the astronauts onboard the station are in weightlessness. Why?
A. The ISS is constanly falling towards the Earth, but with enough horizontal speed to create an opposing acceleration and equal in magnitude to the gravitational acceleration.
B. None of the above.
C. The ISS is constantly rotating around its main axis, creating the illusion of weightlessness.
D. Thrusters are in constant use which generate a force such that there is weightlessness.
|
A. The ISS is constanly falling towards the Earth, but with enough horizontal speed to create an opposing acceleration and equal in magnitude to the gravitational acceleration.
|
37
|
0d0d9c07-d33a-4624-9597-1222c4479572
|
A spacecraft is on a free trajectory in the vicinity of the Earth. From which statement can it be deduced that this spacecraft has sufficient energy to leave Earth's gravitational well (i.e. it is not on orbit around the Earth)? Assumption: Etot refers to the total energy of the spacecraft.
| 0
|
[
"Etot is close to + infinity",
"Etot < 0",
"Etot >= 0",
"Etot is close to - infinity"
] |
[
0,
0,
1,
0
] |
A spacecraft is on a free trajectory in the vicinity of the Earth. From which statement can it be deduced that this spacecraft has sufficient energy to leave Earth's gravitational well (i.e. it is not on orbit around the Earth)? Assumption: Etot refers to the total energy of the spacecraft.
A. Etot is close to + infinity
B. Etot < 0
C. Etot >= 0
D. Etot is close to - infinity
|
C. Etot >= 0
|
37
|
0d0d9c07-d33a-4624-9597-1222c4479572
|
A spacecraft is on a free trajectory in the vicinity of the Earth. From which statement can it be deduced that this spacecraft has sufficient energy to leave Earth's gravitational well (i.e. it is not on orbit around the Earth)? Assumption: Etot refers to the total energy of the spacecraft.
| 1
|
[
"Etot is close to + infinity",
"Etot is close to - infinity",
"Etot >= 0",
"Etot < 0"
] |
[
0,
0,
1,
0
] |
A spacecraft is on a free trajectory in the vicinity of the Earth. From which statement can it be deduced that this spacecraft has sufficient energy to leave Earth's gravitational well (i.e. it is not on orbit around the Earth)? Assumption: Etot refers to the total energy of the spacecraft.
A. Etot is close to + infinity
B. Etot is close to - infinity
C. Etot >= 0
D. Etot < 0
|
C. Etot >= 0
|
37
|
0d0d9c07-d33a-4624-9597-1222c4479572
|
A spacecraft is on a free trajectory in the vicinity of the Earth. From which statement can it be deduced that this spacecraft has sufficient energy to leave Earth's gravitational well (i.e. it is not on orbit around the Earth)? Assumption: Etot refers to the total energy of the spacecraft.
| 2
|
[
"Etot is close to - infinity",
"Etot is close to + infinity",
"Etot < 0",
"Etot >= 0"
] |
[
0,
0,
0,
1
] |
A spacecraft is on a free trajectory in the vicinity of the Earth. From which statement can it be deduced that this spacecraft has sufficient energy to leave Earth's gravitational well (i.e. it is not on orbit around the Earth)? Assumption: Etot refers to the total energy of the spacecraft.
A. Etot is close to - infinity
B. Etot is close to + infinity
C. Etot < 0
D. Etot >= 0
|
D. Etot >= 0
|
38
|
169dbc4a-48cf-40f8-b67b-654da412029f
|
The transfer velocity from an 1 AU orbit (i.e. Earth's orbit) is about 12 km/s. The transfer velocity from Mercury's orbit is 20 km/s. A probe is on an 1 AU orbit with the objective of going towards Mercury. What action must be taken?
| 0
|
[
"Increase the velocity by 12 km/s.",
"Decrease the energy of the probe.",
"Wait until the orbit is perturbed enough to flyby Mercury.",
"Increase the energy of the probe."
] |
[
0,
1,
0,
0
] |
The transfer velocity from an 1 AU orbit (i.e. Earth's orbit) is about 12 km/s. The transfer velocity from Mercury's orbit is 20 km/s. A probe is on an 1 AU orbit with the objective of going towards Mercury. What action must be taken?
A. Increase the velocity by 12 km/s.
B. Decrease the energy of the probe.
C. Wait until the orbit is perturbed enough to flyby Mercury.
D. Increase the energy of the probe.
|
B. Decrease the energy of the probe.
|
38
|
169dbc4a-48cf-40f8-b67b-654da412029f
|
The transfer velocity from an 1 AU orbit (i.e. Earth's orbit) is about 12 km/s. The transfer velocity from Mercury's orbit is 20 km/s. A probe is on an 1 AU orbit with the objective of going towards Mercury. What action must be taken?
| 1
|
[
"Increase the velocity by 12 km/s.",
"Decrease the energy of the probe.",
"Increase the energy of the probe.",
"Wait until the orbit is perturbed enough to flyby Mercury."
] |
[
0,
1,
0,
0
] |
The transfer velocity from an 1 AU orbit (i.e. Earth's orbit) is about 12 km/s. The transfer velocity from Mercury's orbit is 20 km/s. A probe is on an 1 AU orbit with the objective of going towards Mercury. What action must be taken?
A. Increase the velocity by 12 km/s.
B. Decrease the energy of the probe.
C. Increase the energy of the probe.
D. Wait until the orbit is perturbed enough to flyby Mercury.
|
B. Decrease the energy of the probe.
|
38
|
169dbc4a-48cf-40f8-b67b-654da412029f
|
The transfer velocity from an 1 AU orbit (i.e. Earth's orbit) is about 12 km/s. The transfer velocity from Mercury's orbit is 20 km/s. A probe is on an 1 AU orbit with the objective of going towards Mercury. What action must be taken?
| 2
|
[
"Decrease the energy of the probe.",
"Increase the velocity by 12 km/s.",
"Increase the energy of the probe.",
"Wait until the orbit is perturbed enough to flyby Mercury."
] |
[
1,
0,
0,
0
] |
The transfer velocity from an 1 AU orbit (i.e. Earth's orbit) is about 12 km/s. The transfer velocity from Mercury's orbit is 20 km/s. A probe is on an 1 AU orbit with the objective of going towards Mercury. What action must be taken?
A. Decrease the energy of the probe.
B. Increase the velocity by 12 km/s.
C. Increase the energy of the probe.
D. Wait until the orbit is perturbed enough to flyby Mercury.
|
A. Decrease the energy of the probe.
|
39
|
5f013dd6-d16e-4e1f-91f2-84dd2711e47c
|
What is the orbital velocity of the Hubble Space Telescope which is on a circular orbit at 555 km altitude? (answer in km/s)
| 0
|
[
"7.58",
"6.21",
"8.02",
"4.00"
] |
[
1,
0,
0,
0
] |
What is the orbital velocity of the Hubble Space Telescope which is on a circular orbit at 555 km altitude? (answer in km/s)
A. 7.58
B. 6.21
C. 8.02
D. 4.00
|
A. 7.58
|
39
|
5f013dd6-d16e-4e1f-91f2-84dd2711e47c
|
What is the orbital velocity of the Hubble Space Telescope which is on a circular orbit at 555 km altitude? (answer in km/s)
| 1
|
[
"8.02",
"6.21",
"7.58",
"4.00"
] |
[
0,
0,
1,
0
] |
What is the orbital velocity of the Hubble Space Telescope which is on a circular orbit at 555 km altitude? (answer in km/s)
A. 8.02
B. 6.21
C. 7.58
D. 4.00
|
C. 7.58
|
39
|
5f013dd6-d16e-4e1f-91f2-84dd2711e47c
|
What is the orbital velocity of the Hubble Space Telescope which is on a circular orbit at 555 km altitude? (answer in km/s)
| 2
|
[
"6.21",
"4.00",
"7.58",
"8.02"
] |
[
0,
0,
1,
0
] |
What is the orbital velocity of the Hubble Space Telescope which is on a circular orbit at 555 km altitude? (answer in km/s)
A. 6.21
B. 4.00
C. 7.58
D. 8.02
|
C. 7.58
|
40
|
7b343016-967c-4a4c-a892-be3e07a6992b
|
What is the strength of the Earth’s acceleration in LEO?
| 0
|
[
"10% of the acceleration on the surface of the Earth",
"90% of the acceleration on the surface of the Earth",
"No acceleration, that’s why you can float in space",
"Same acceleration than on the surface of the Earth"
] |
[
0,
1,
0,
0
] |
What is the strength of the Earth’s acceleration in LEO?
A. 10% of the acceleration on the surface of the Earth
B. 90% of the acceleration on the surface of the Earth
C. No acceleration, that’s why you can float in space
D. Same acceleration than on the surface of the Earth
|
B. 90% of the acceleration on the surface of the Earth
|
40
|
7b343016-967c-4a4c-a892-be3e07a6992b
|
What is the strength of the Earth’s acceleration in LEO?
| 1
|
[
"Same acceleration than on the surface of the Earth",
"90% of the acceleration on the surface of the Earth",
"10% of the acceleration on the surface of the Earth",
"No acceleration, that’s why you can float in space"
] |
[
0,
1,
0,
0
] |
What is the strength of the Earth’s acceleration in LEO?
A. Same acceleration than on the surface of the Earth
B. 90% of the acceleration on the surface of the Earth
C. 10% of the acceleration on the surface of the Earth
D. No acceleration, that’s why you can float in space
|
B. 90% of the acceleration on the surface of the Earth
|
40
|
7b343016-967c-4a4c-a892-be3e07a6992b
|
What is the strength of the Earth’s acceleration in LEO?
| 2
|
[
"Same acceleration than on the surface of the Earth",
"10% of the acceleration on the surface of the Earth",
"90% of the acceleration on the surface of the Earth",
"No acceleration, that’s why you can float in space"
] |
[
0,
0,
1,
0
] |
What is the strength of the Earth’s acceleration in LEO?
A. Same acceleration than on the surface of the Earth
B. 10% of the acceleration on the surface of the Earth
C. 90% of the acceleration on the surface of the Earth
D. No acceleration, that’s why you can float in space
|
C. 90% of the acceleration on the surface of the Earth
|
41
|
503e9f15-7799-4813-b0ad-b87c053b9cc3
|
Which of the following proportionnality relation with the orbital period T with respect to the semi-major axis a is correct?
| 0
|
[
"T is proportional to a",
"T^2 is proportional to a",
"T is proportional to a^(3/2)",
"T^2 is proportional to a^2"
] |
[
0,
0,
1,
0
] |
Which of the following proportionnality relation with the orbital period T with respect to the semi-major axis a is correct?
A. T is proportional to a
B. T^2 is proportional to a
C. T is proportional to a^(3/2)
D. T^2 is proportional to a^2
|
C. T is proportional to a^(3/2)
|
41
|
503e9f15-7799-4813-b0ad-b87c053b9cc3
|
Which of the following proportionnality relation with the orbital period T with respect to the semi-major axis a is correct?
| 1
|
[
"T^2 is proportional to a",
"T is proportional to a^(3/2)",
"T is proportional to a",
"T^2 is proportional to a^2"
] |
[
0,
1,
0,
0
] |
Which of the following proportionnality relation with the orbital period T with respect to the semi-major axis a is correct?
A. T^2 is proportional to a
B. T is proportional to a^(3/2)
C. T is proportional to a
D. T^2 is proportional to a^2
|
B. T is proportional to a^(3/2)
|
41
|
503e9f15-7799-4813-b0ad-b87c053b9cc3
|
Which of the following proportionnality relation with the orbital period T with respect to the semi-major axis a is correct?
| 2
|
[
"T is proportional to a",
"T is proportional to a^(3/2)",
"T^2 is proportional to a",
"T^2 is proportional to a^2"
] |
[
0,
1,
0,
0
] |
Which of the following proportionnality relation with the orbital period T with respect to the semi-major axis a is correct?
A. T is proportional to a
B. T is proportional to a^(3/2)
C. T^2 is proportional to a
D. T^2 is proportional to a^2
|
B. T is proportional to a^(3/2)
|
42
|
176ce268-f5ed-4c3e-bf98-b53c8c63fed0
|
An artificial Earth satellite is in an elliptical orbit with a perigee altitude of hp = 250 km and an apogee altitude of ha = 800 km. What is the correct expression of the orbital period?
| 0
|
[
"T = 2*pi * sqrt( a^2 / mu )",
"T = 2*pi * sqrt( a^3 / mu )",
"T = 2*pi * a^3 / mu",
"T = 2*pi * sqrt( a^(1/2) / mu )"
] |
[
0,
1,
0,
0
] |
An artificial Earth satellite is in an elliptical orbit with a perigee altitude of hp = 250 km and an apogee altitude of ha = 800 km. What is the correct expression of the orbital period?
A. T = 2*pi * sqrt( a^2 / mu )
B. T = 2*pi * sqrt( a^3 / mu )
C. T = 2*pi * a^3 / mu
D. T = 2*pi * sqrt( a^(1/2) / mu )
|
B. T = 2*pi * sqrt( a^3 / mu )
|
42
|
176ce268-f5ed-4c3e-bf98-b53c8c63fed0
|
An artificial Earth satellite is in an elliptical orbit with a perigee altitude of hp = 250 km and an apogee altitude of ha = 800 km. What is the correct expression of the orbital period?
| 1
|
[
"T = 2*pi * sqrt( a^(1/2) / mu )",
"T = 2*pi * sqrt( a^2 / mu )",
"T = 2*pi * a^3 / mu",
"T = 2*pi * sqrt( a^3 / mu )"
] |
[
0,
0,
0,
1
] |
An artificial Earth satellite is in an elliptical orbit with a perigee altitude of hp = 250 km and an apogee altitude of ha = 800 km. What is the correct expression of the orbital period?
A. T = 2*pi * sqrt( a^(1/2) / mu )
B. T = 2*pi * sqrt( a^2 / mu )
C. T = 2*pi * a^3 / mu
D. T = 2*pi * sqrt( a^3 / mu )
|
D. T = 2*pi * sqrt( a^3 / mu )
|
42
|
176ce268-f5ed-4c3e-bf98-b53c8c63fed0
|
An artificial Earth satellite is in an elliptical orbit with a perigee altitude of hp = 250 km and an apogee altitude of ha = 800 km. What is the correct expression of the orbital period?
| 2
|
[
"T = 2*pi * sqrt( a^(1/2) / mu )",
"T = 2*pi * sqrt( a^3 / mu )",
"T = 2*pi * a^3 / mu",
"T = 2*pi * sqrt( a^2 / mu )"
] |
[
0,
1,
0,
0
] |
An artificial Earth satellite is in an elliptical orbit with a perigee altitude of hp = 250 km and an apogee altitude of ha = 800 km. What is the correct expression of the orbital period?
A. T = 2*pi * sqrt( a^(1/2) / mu )
B. T = 2*pi * sqrt( a^3 / mu )
C. T = 2*pi * a^3 / mu
D. T = 2*pi * sqrt( a^2 / mu )
|
B. T = 2*pi * sqrt( a^3 / mu )
|
43
|
874c48df-381b-4887-a2b8-fa09963fbb2f
|
An artificial Earth satellite is in an elliptical orbit with a perigee altitude of hp and an apogee altitude of ha. How do you express the semi major of the axis of the satellite orbit "a" in function of hp, ha, and R where R is the Earth's radius?
| 0
|
[
"a = R ( hp + ha ) / 2",
"a = R ( ha - hp ) / 2",
"a = R + (ha + hp) / 2",
"a = 2R + (ha + hp) / 2",
"a = R - (hp + ha) / 2"
] |
[
0,
0,
1,
0,
0
] |
An artificial Earth satellite is in an elliptical orbit with a perigee altitude of hp and an apogee altitude of ha. How do you express the semi major of the axis of the satellite orbit "a" in function of hp, ha, and R where R is the Earth's radius?
A. a = R ( hp + ha ) / 2
B. a = R ( ha - hp ) / 2
C. a = R + (ha + hp) / 2
D. a = 2R + (ha + hp) / 2
E. a = R - (hp + ha) / 2
|
C. a = R + (ha + hp) / 2
|
43
|
874c48df-381b-4887-a2b8-fa09963fbb2f
|
An artificial Earth satellite is in an elliptical orbit with a perigee altitude of hp and an apogee altitude of ha. How do you express the semi major of the axis of the satellite orbit "a" in function of hp, ha, and R where R is the Earth's radius?
| 1
|
[
"a = R - (hp + ha) / 2",
"a = R ( hp + ha ) / 2",
"a = R + (ha + hp) / 2",
"a = R ( ha - hp ) / 2",
"a = 2R + (ha + hp) / 2"
] |
[
0,
0,
1,
0,
0
] |
An artificial Earth satellite is in an elliptical orbit with a perigee altitude of hp and an apogee altitude of ha. How do you express the semi major of the axis of the satellite orbit "a" in function of hp, ha, and R where R is the Earth's radius?
A. a = R - (hp + ha) / 2
B. a = R ( hp + ha ) / 2
C. a = R + (ha + hp) / 2
D. a = R ( ha - hp ) / 2
E. a = 2R + (ha + hp) / 2
|
C. a = R + (ha + hp) / 2
|
43
|
874c48df-381b-4887-a2b8-fa09963fbb2f
|
An artificial Earth satellite is in an elliptical orbit with a perigee altitude of hp and an apogee altitude of ha. How do you express the semi major of the axis of the satellite orbit "a" in function of hp, ha, and R where R is the Earth's radius?
| 2
|
[
"a = R ( hp + ha ) / 2",
"a = R - (hp + ha) / 2",
"a = R ( ha - hp ) / 2",
"a = 2R + (ha + hp) / 2",
"a = R + (ha + hp) / 2"
] |
[
0,
0,
0,
0,
1
] |
An artificial Earth satellite is in an elliptical orbit with a perigee altitude of hp and an apogee altitude of ha. How do you express the semi major of the axis of the satellite orbit "a" in function of hp, ha, and R where R is the Earth's radius?
A. a = R ( hp + ha ) / 2
B. a = R - (hp + ha) / 2
C. a = R ( ha - hp ) / 2
D. a = 2R + (ha + hp) / 2
E. a = R + (ha + hp) / 2
|
E. a = R + (ha + hp) / 2
|
44
|
6ef8b7da-7aea-4809-95ce-c17f64866bee
|
An artificial Earth satellite is in an elliptical orbit with a perigee altitude of hp = 250 km and an apogee altitude of ha = 800 km. What is its orbital period expressed in minutes?
| 0
|
[
"100.9",
"18.0",
"95.0",
"89.5"
] |
[
0,
0,
1,
0
] |
An artificial Earth satellite is in an elliptical orbit with a perigee altitude of hp = 250 km and an apogee altitude of ha = 800 km. What is its orbital period expressed in minutes?
A. 100.9
B. 18.0
C. 95.0
D. 89.5
|
C. 95.0
|
44
|
6ef8b7da-7aea-4809-95ce-c17f64866bee
|
An artificial Earth satellite is in an elliptical orbit with a perigee altitude of hp = 250 km and an apogee altitude of ha = 800 km. What is its orbital period expressed in minutes?
| 1
|
[
"95.0",
"100.9",
"18.0",
"89.5"
] |
[
1,
0,
0,
0
] |
An artificial Earth satellite is in an elliptical orbit with a perigee altitude of hp = 250 km and an apogee altitude of ha = 800 km. What is its orbital period expressed in minutes?
A. 95.0
B. 100.9
C. 18.0
D. 89.5
|
A. 95.0
|
44
|
6ef8b7da-7aea-4809-95ce-c17f64866bee
|
An artificial Earth satellite is in an elliptical orbit with a perigee altitude of hp = 250 km and an apogee altitude of ha = 800 km. What is its orbital period expressed in minutes?
| 2
|
[
"18.0",
"89.5",
"95.0",
"100.9"
] |
[
0,
0,
1,
0
] |
An artificial Earth satellite is in an elliptical orbit with a perigee altitude of hp = 250 km and an apogee altitude of ha = 800 km. What is its orbital period expressed in minutes?
A. 18.0
B. 89.5
C. 95.0
D. 100.9
|
C. 95.0
|
45
|
5064e3a3-16e9-431c-816e-3d8cd10c9331
|
A geostationary orbit is defined as an orbit were the satellite is always pointing towards the same point on the Earth's surface. What is its eccentricity?
| 0
|
[
"1",
"0",
"1.3",
"0.5"
] |
[
0,
1,
0,
0
] |
A geostationary orbit is defined as an orbit were the satellite is always pointing towards the same point on the Earth's surface. What is its eccentricity?
A. 1
B. 0
C. 1.3
D. 0.5
|
B. 0
|
45
|
5064e3a3-16e9-431c-816e-3d8cd10c9331
|
A geostationary orbit is defined as an orbit were the satellite is always pointing towards the same point on the Earth's surface. What is its eccentricity?
| 1
|
[
"1.3",
"0",
"0.5",
"1"
] |
[
0,
1,
0,
0
] |
A geostationary orbit is defined as an orbit were the satellite is always pointing towards the same point on the Earth's surface. What is its eccentricity?
A. 1.3
B. 0
C. 0.5
D. 1
|
B. 0
|
45
|
5064e3a3-16e9-431c-816e-3d8cd10c9331
|
A geostationary orbit is defined as an orbit were the satellite is always pointing towards the same point on the Earth's surface. What is its eccentricity?
| 2
|
[
"1",
"1.3",
"0.5",
"0"
] |
[
0,
0,
0,
1
] |
A geostationary orbit is defined as an orbit were the satellite is always pointing towards the same point on the Earth's surface. What is its eccentricity?
A. 1
B. 1.3
C. 0.5
D. 0
|
D. 0
|
46
|
6192c62d-489d-45e4-acf6-23083a809273
|
A geostationary orbit is defined as an orbit were the satellite is always pointing towards the same point on the Earth's surface. What is its inclination?
| 0
|
[
"0°",
"7.01°",
"3.2°",
"45°"
] |
[
1,
0,
0,
0
] |
A geostationary orbit is defined as an orbit were the satellite is always pointing towards the same point on the Earth's surface. What is its inclination?
A. 0°
B. 7.01°
C. 3.2°
D. 45°
|
A. 0°
|
46
|
6192c62d-489d-45e4-acf6-23083a809273
|
A geostationary orbit is defined as an orbit were the satellite is always pointing towards the same point on the Earth's surface. What is its inclination?
| 1
|
[
"45°",
"7.01°",
"0°",
"3.2°"
] |
[
0,
0,
1,
0
] |
A geostationary orbit is defined as an orbit were the satellite is always pointing towards the same point on the Earth's surface. What is its inclination?
A. 45°
B. 7.01°
C. 0°
D. 3.2°
|
C. 0°
|
46
|
6192c62d-489d-45e4-acf6-23083a809273
|
A geostationary orbit is defined as an orbit were the satellite is always pointing towards the same point on the Earth's surface. What is its inclination?
| 2
|
[
"3.2°",
"0°",
"45°",
"7.01°"
] |
[
0,
1,
0,
0
] |
A geostationary orbit is defined as an orbit were the satellite is always pointing towards the same point on the Earth's surface. What is its inclination?
A. 3.2°
B. 0°
C. 45°
D. 7.01°
|
B. 0°
|
47
|
bc2f3517-6e5a-4b39-89c6-fb11c2209392
|
In orbital mechanics, what is the meaning of the mean motion n = sqrt( mu / a^3 )?
| 0
|
[
"In the specific case where the eccentricity e tends to zero, the mean motion and the true anomaly tend to be equal.",
"The mean motion relates to the true position of a body moving along a Keplerian orbit.",
"It corresponds to the instantaneous angular rate for a non-circular orbit.",
"It can be defined only for parabolic orbits.",
"It is the average angular rate over one full orbit, in rad/s"
] |
[
0,
0,
0,
0,
1
] |
In orbital mechanics, what is the meaning of the mean motion n = sqrt( mu / a^3 )?
A. In the specific case where the eccentricity e tends to zero, the mean motion and the true anomaly tend to be equal.
B. The mean motion relates to the true position of a body moving along a Keplerian orbit.
C. It corresponds to the instantaneous angular rate for a non-circular orbit.
D. It can be defined only for parabolic orbits.
E. It is the average angular rate over one full orbit, in rad/s
|
E. It is the average angular rate over one full orbit, in rad/s
|
47
|
bc2f3517-6e5a-4b39-89c6-fb11c2209392
|
In orbital mechanics, what is the meaning of the mean motion n = sqrt( mu / a^3 )?
| 1
|
[
"In the specific case where the eccentricity e tends to zero, the mean motion and the true anomaly tend to be equal.",
"It corresponds to the instantaneous angular rate for a non-circular orbit.",
"It can be defined only for parabolic orbits.",
"The mean motion relates to the true position of a body moving along a Keplerian orbit.",
"It is the average angular rate over one full orbit, in rad/s"
] |
[
0,
0,
0,
0,
1
] |
In orbital mechanics, what is the meaning of the mean motion n = sqrt( mu / a^3 )?
A. In the specific case where the eccentricity e tends to zero, the mean motion and the true anomaly tend to be equal.
B. It corresponds to the instantaneous angular rate for a non-circular orbit.
C. It can be defined only for parabolic orbits.
D. The mean motion relates to the true position of a body moving along a Keplerian orbit.
E. It is the average angular rate over one full orbit, in rad/s
|
E. It is the average angular rate over one full orbit, in rad/s
|
47
|
bc2f3517-6e5a-4b39-89c6-fb11c2209392
|
In orbital mechanics, what is the meaning of the mean motion n = sqrt( mu / a^3 )?
| 2
|
[
"It can be defined only for parabolic orbits.",
"It corresponds to the instantaneous angular rate for a non-circular orbit.",
"The mean motion relates to the true position of a body moving along a Keplerian orbit.",
"In the specific case where the eccentricity e tends to zero, the mean motion and the true anomaly tend to be equal.",
"It is the average angular rate over one full orbit, in rad/s"
] |
[
0,
0,
0,
0,
1
] |
In orbital mechanics, what is the meaning of the mean motion n = sqrt( mu / a^3 )?
A. It can be defined only for parabolic orbits.
B. It corresponds to the instantaneous angular rate for a non-circular orbit.
C. The mean motion relates to the true position of a body moving along a Keplerian orbit.
D. In the specific case where the eccentricity e tends to zero, the mean motion and the true anomaly tend to be equal.
E. It is the average angular rate over one full orbit, in rad/s
|
E. It is the average angular rate over one full orbit, in rad/s
|
48
|
8d7cc580-c7b9-4875-9ba6-bf468df0a61d
|
What reference frame is the best suited for an interplanetary probe?
| 0
|
[
"Geographic coordinate system",
"Geo-centric coordinate system",
"Heliocentric-inertial coordinate system"
] |
[
0,
0,
1
] |
What reference frame is the best suited for an interplanetary probe?
A. Geographic coordinate system
B. Geo-centric coordinate system
C. Heliocentric-inertial coordinate system
|
C. Heliocentric-inertial coordinate system
|
48
|
8d7cc580-c7b9-4875-9ba6-bf468df0a61d
|
What reference frame is the best suited for an interplanetary probe?
| 1
|
[
"Geographic coordinate system",
"Heliocentric-inertial coordinate system",
"Geo-centric coordinate system"
] |
[
0,
1,
0
] |
What reference frame is the best suited for an interplanetary probe?
A. Geographic coordinate system
B. Heliocentric-inertial coordinate system
C. Geo-centric coordinate system
|
B. Heliocentric-inertial coordinate system
|
48
|
8d7cc580-c7b9-4875-9ba6-bf468df0a61d
|
What reference frame is the best suited for an interplanetary probe?
| 2
|
[
"Geo-centric coordinate system",
"Heliocentric-inertial coordinate system",
"Geographic coordinate system"
] |
[
0,
1,
0
] |
What reference frame is the best suited for an interplanetary probe?
A. Geo-centric coordinate system
B. Heliocentric-inertial coordinate system
C. Geographic coordinate system
|
B. Heliocentric-inertial coordinate system
|
49
|
e4fda0e7-b147-48fd-bcea-fbc007d2ee9b
|
The complete precessional cycle of the Earth lasts about 26000 years. What is the precession rate? (in degrees per year)
| 0
|
[
"0.00384",
"0.05384",
"0.01384",
"0.02384",
"0.04384",
"0.03384"
] |
[
0,
0,
1,
0,
0,
0
] |
The complete precessional cycle of the Earth lasts about 26000 years. What is the precession rate? (in degrees per year)
A. 0.00384
B. 0.05384
C. 0.01384
D. 0.02384
E. 0.04384
F. 0.03384
|
C. 0.01384
|
49
|
e4fda0e7-b147-48fd-bcea-fbc007d2ee9b
|
The complete precessional cycle of the Earth lasts about 26000 years. What is the precession rate? (in degrees per year)
| 1
|
[
"0.00384",
"0.05384",
"0.01384",
"0.02384",
"0.03384",
"0.04384"
] |
[
0,
0,
1,
0,
0,
0
] |
The complete precessional cycle of the Earth lasts about 26000 years. What is the precession rate? (in degrees per year)
A. 0.00384
B. 0.05384
C. 0.01384
D. 0.02384
E. 0.03384
F. 0.04384
|
C. 0.01384
|
49
|
e4fda0e7-b147-48fd-bcea-fbc007d2ee9b
|
The complete precessional cycle of the Earth lasts about 26000 years. What is the precession rate? (in degrees per year)
| 2
|
[
"0.05384",
"0.02384",
"0.00384",
"0.04384",
"0.03384",
"0.01384"
] |
[
0,
0,
0,
0,
0,
1
] |
The complete precessional cycle of the Earth lasts about 26000 years. What is the precession rate? (in degrees per year)
A. 0.05384
B. 0.02384
C. 0.00384
D. 0.04384
E. 0.03384
F. 0.01384
|
F. 0.01384
|
50
|
7c7013ed-cb14-4298-a435-259072390c40
|
What is the RAAN?
| 0
|
[
"The time of the periapsis transit.",
"The angle from a reference direction to the point where the satellite crosses the plane of reference, towards the south.",
"The angle from a reference direction to the point where the satellite crosses the plane of reference, towards the north.",
"The inclination of the orbital plane."
] |
[
0,
0,
1,
0
] |
What is the RAAN?
A. The time of the periapsis transit.
B. The angle from a reference direction to the point where the satellite crosses the plane of reference, towards the south.
C. The angle from a reference direction to the point where the satellite crosses the plane of reference, towards the north.
D. The inclination of the orbital plane.
|
C. The angle from a reference direction to the point where the satellite crosses the plane of reference, towards the north.
|
50
|
7c7013ed-cb14-4298-a435-259072390c40
|
What is the RAAN?
| 1
|
[
"The time of the periapsis transit.",
"The angle from a reference direction to the point where the satellite crosses the plane of reference, towards the north.",
"The angle from a reference direction to the point where the satellite crosses the plane of reference, towards the south.",
"The inclination of the orbital plane."
] |
[
0,
1,
0,
0
] |
What is the RAAN?
A. The time of the periapsis transit.
B. The angle from a reference direction to the point where the satellite crosses the plane of reference, towards the north.
C. The angle from a reference direction to the point where the satellite crosses the plane of reference, towards the south.
D. The inclination of the orbital plane.
|
B. The angle from a reference direction to the point where the satellite crosses the plane of reference, towards the north.
|
50
|
7c7013ed-cb14-4298-a435-259072390c40
|
What is the RAAN?
| 2
|
[
"The angle from a reference direction to the point where the satellite crosses the plane of reference, towards the north.",
"The time of the periapsis transit.",
"The inclination of the orbital plane.",
"The angle from a reference direction to the point where the satellite crosses the plane of reference, towards the south."
] |
[
1,
0,
0,
0
] |
What is the RAAN?
A. The angle from a reference direction to the point where the satellite crosses the plane of reference, towards the north.
B. The time of the periapsis transit.
C. The inclination of the orbital plane.
D. The angle from a reference direction to the point where the satellite crosses the plane of reference, towards the south.
|
A. The angle from a reference direction to the point where the satellite crosses the plane of reference, towards the north.
|
51
|
e5939e55-2802-4753-b849-2efdd4aafa9a
|
How long is a sideral day?
| 0
|
[
"24h04min",
"23h56min",
"11h56min",
"24h00min"
] |
[
0,
1,
0,
0
] |
How long is a sideral day?
A. 24h04min
B. 23h56min
C. 11h56min
D. 24h00min
|
B. 23h56min
|
51
|
e5939e55-2802-4753-b849-2efdd4aafa9a
|
How long is a sideral day?
| 1
|
[
"24h00min",
"23h56min",
"11h56min",
"24h04min"
] |
[
0,
1,
0,
0
] |
How long is a sideral day?
A. 24h00min
B. 23h56min
C. 11h56min
D. 24h04min
|
B. 23h56min
|
51
|
e5939e55-2802-4753-b849-2efdd4aafa9a
|
How long is a sideral day?
| 2
|
[
"24h00min",
"11h56min",
"24h04min",
"23h56min"
] |
[
0,
0,
0,
1
] |
How long is a sideral day?
A. 24h00min
B. 11h56min
C. 24h04min
D. 23h56min
|
D. 23h56min
|
52
|
3e8adab1-90a8-4d92-a636-f514f12d90cf
|
Where is an orbital maneuver Delta-V adding energy to a spacecraft on orbit best performed?
| 0
|
[
"Along the orbital velocity",
"Any direction of the Delta-V vector will add energy to the spacectaft on orbit.",
"Along the orbit angular momentum",
"Radially"
] |
[
1,
0,
0,
0
] |
Where is an orbital maneuver Delta-V adding energy to a spacecraft on orbit best performed?
A. Along the orbital velocity
B. Any direction of the Delta-V vector will add energy to the spacectaft on orbit.
C. Along the orbit angular momentum
D. Radially
|
A. Along the orbital velocity
|
52
|
3e8adab1-90a8-4d92-a636-f514f12d90cf
|
Where is an orbital maneuver Delta-V adding energy to a spacecraft on orbit best performed?
| 1
|
[
"Along the orbital velocity",
"Radially",
"Any direction of the Delta-V vector will add energy to the spacectaft on orbit.",
"Along the orbit angular momentum"
] |
[
1,
0,
0,
0
] |
Where is an orbital maneuver Delta-V adding energy to a spacecraft on orbit best performed?
A. Along the orbital velocity
B. Radially
C. Any direction of the Delta-V vector will add energy to the spacectaft on orbit.
D. Along the orbit angular momentum
|
A. Along the orbital velocity
|
52
|
3e8adab1-90a8-4d92-a636-f514f12d90cf
|
Where is an orbital maneuver Delta-V adding energy to a spacecraft on orbit best performed?
| 2
|
[
"Any direction of the Delta-V vector will add energy to the spacectaft on orbit.",
"Along the orbital velocity",
"Radially",
"Along the orbit angular momentum"
] |
[
0,
1,
0,
0
] |
Where is an orbital maneuver Delta-V adding energy to a spacecraft on orbit best performed?
A. Any direction of the Delta-V vector will add energy to the spacectaft on orbit.
B. Along the orbital velocity
C. Radially
D. Along the orbit angular momentum
|
B. Along the orbital velocity
|
53
|
b706586d-50b8-4d17-b9f2-890c679ff6e8
|
What is the Hohmann transfer for small Delta-V useful for?
| 0
|
[
"Interplanetary trajectories",
"Orbital rendez-vous",
"Earth-Moon transfer",
"Manoeuvers around small bodies (e.g. comets)"
] |
[
0,
1,
0,
0
] |
What is the Hohmann transfer for small Delta-V useful for?
A. Interplanetary trajectories
B. Orbital rendez-vous
C. Earth-Moon transfer
D. Manoeuvers around small bodies (e.g. comets)
|
B. Orbital rendez-vous
|
53
|
b706586d-50b8-4d17-b9f2-890c679ff6e8
|
What is the Hohmann transfer for small Delta-V useful for?
| 1
|
[
"Earth-Moon transfer",
"Orbital rendez-vous",
"Interplanetary trajectories",
"Manoeuvers around small bodies (e.g. comets)"
] |
[
0,
1,
0,
0
] |
What is the Hohmann transfer for small Delta-V useful for?
A. Earth-Moon transfer
B. Orbital rendez-vous
C. Interplanetary trajectories
D. Manoeuvers around small bodies (e.g. comets)
|
B. Orbital rendez-vous
|
53
|
b706586d-50b8-4d17-b9f2-890c679ff6e8
|
What is the Hohmann transfer for small Delta-V useful for?
| 2
|
[
"Earth-Moon transfer",
"Interplanetary trajectories",
"Manoeuvers around small bodies (e.g. comets)",
"Orbital rendez-vous"
] |
[
0,
0,
0,
1
] |
What is the Hohmann transfer for small Delta-V useful for?
A. Earth-Moon transfer
B. Interplanetary trajectories
C. Manoeuvers around small bodies (e.g. comets)
D. Orbital rendez-vous
|
D. Orbital rendez-vous
|
54
|
a972601f-0015-48b8-8747-5e5dd8e92e12
|
Where is the Delta-V for an inclination change smaller?
| 0
|
[
"at low altitudes",
"at the poles",
"at the equator",
"at high altitudes"
] |
[
0,
0,
0,
1
] |
Where is the Delta-V for an inclination change smaller?
A. at low altitudes
B. at the poles
C. at the equator
D. at high altitudes
|
D. at high altitudes
|
54
|
a972601f-0015-48b8-8747-5e5dd8e92e12
|
Where is the Delta-V for an inclination change smaller?
| 1
|
[
"at the equator",
"at the poles",
"at high altitudes",
"at low altitudes"
] |
[
0,
0,
1,
0
] |
Where is the Delta-V for an inclination change smaller?
A. at the equator
B. at the poles
C. at high altitudes
D. at low altitudes
|
C. at high altitudes
|
54
|
a972601f-0015-48b8-8747-5e5dd8e92e12
|
Where is the Delta-V for an inclination change smaller?
| 2
|
[
"at low altitudes",
"at the equator",
"at high altitudes",
"at the poles"
] |
[
0,
0,
1,
0
] |
Where is the Delta-V for an inclination change smaller?
A. at low altitudes
B. at the equator
C. at high altitudes
D. at the poles
|
C. at high altitudes
|
55
|
e723f537-9123-4794-99c4-6dc0f39f9e8f
|
What is the difference between geostationary and geosynchronous orbits?
| 0
|
[
"Geostationary has an orbital period of 24h whereas geosynchronous orbits is 23h56",
"All of the above",
"A geosynchronous satellite orbits the same location over Earth's surface while a geostationary satellite remains on average at the equator",
"The orbital parameters for geostationary are inclination = 0° and eccentricity = 0"
] |
[
0,
0,
0,
1
] |
What is the difference between geostationary and geosynchronous orbits?
A. Geostationary has an orbital period of 24h whereas geosynchronous orbits is 23h56
B. All of the above
C. A geosynchronous satellite orbits the same location over Earth's surface while a geostationary satellite remains on average at the equator
D. The orbital parameters for geostationary are inclination = 0° and eccentricity = 0
|
D. The orbital parameters for geostationary are inclination = 0° and eccentricity = 0
|
55
|
e723f537-9123-4794-99c4-6dc0f39f9e8f
|
What is the difference between geostationary and geosynchronous orbits?
| 1
|
[
"The orbital parameters for geostationary are inclination = 0° and eccentricity = 0",
"Geostationary has an orbital period of 24h whereas geosynchronous orbits is 23h56",
"All of the above",
"A geosynchronous satellite orbits the same location over Earth's surface while a geostationary satellite remains on average at the equator"
] |
[
1,
0,
0,
0
] |
What is the difference between geostationary and geosynchronous orbits?
A. The orbital parameters for geostationary are inclination = 0° and eccentricity = 0
B. Geostationary has an orbital period of 24h whereas geosynchronous orbits is 23h56
C. All of the above
D. A geosynchronous satellite orbits the same location over Earth's surface while a geostationary satellite remains on average at the equator
|
A. The orbital parameters for geostationary are inclination = 0° and eccentricity = 0
|
55
|
e723f537-9123-4794-99c4-6dc0f39f9e8f
|
What is the difference between geostationary and geosynchronous orbits?
| 2
|
[
"All of the above",
"A geosynchronous satellite orbits the same location over Earth's surface while a geostationary satellite remains on average at the equator",
"Geostationary has an orbital period of 24h whereas geosynchronous orbits is 23h56",
"The orbital parameters for geostationary are inclination = 0° and eccentricity = 0"
] |
[
0,
0,
0,
1
] |
What is the difference between geostationary and geosynchronous orbits?
A. All of the above
B. A geosynchronous satellite orbits the same location over Earth's surface while a geostationary satellite remains on average at the equator
C. Geostationary has an orbital period of 24h whereas geosynchronous orbits is 23h56
D. The orbital parameters for geostationary are inclination = 0° and eccentricity = 0
|
D. The orbital parameters for geostationary are inclination = 0° and eccentricity = 0
|
56
|
60f3877b-24ba-45fe-af9e-d67d14170174
|
The ground tracks for a satellite in LEO (typical orbital period is 90 min) is shifting to the west from one equator crossing to the next. What is the typical value of the shift in degrees?
| 0
|
[
"22.5",
"15",
"12.5",
"20",
"17.5"
] |
[
1,
0,
0,
0,
0
] |
The ground tracks for a satellite in LEO (typical orbital period is 90 min) is shifting to the west from one equator crossing to the next. What is the typical value of the shift in degrees?
A. 22.5
B. 15
C. 12.5
D. 20
E. 17.5
|
A. 22.5
|
56
|
60f3877b-24ba-45fe-af9e-d67d14170174
|
The ground tracks for a satellite in LEO (typical orbital period is 90 min) is shifting to the west from one equator crossing to the next. What is the typical value of the shift in degrees?
| 1
|
[
"22.5",
"15",
"12.5",
"17.5",
"20"
] |
[
1,
0,
0,
0,
0
] |
The ground tracks for a satellite in LEO (typical orbital period is 90 min) is shifting to the west from one equator crossing to the next. What is the typical value of the shift in degrees?
A. 22.5
B. 15
C. 12.5
D. 17.5
E. 20
|
A. 22.5
|
56
|
60f3877b-24ba-45fe-af9e-d67d14170174
|
The ground tracks for a satellite in LEO (typical orbital period is 90 min) is shifting to the west from one equator crossing to the next. What is the typical value of the shift in degrees?
| 2
|
[
"15",
"12.5",
"20",
"22.5",
"17.5"
] |
[
0,
0,
0,
1,
0
] |
The ground tracks for a satellite in LEO (typical orbital period is 90 min) is shifting to the west from one equator crossing to the next. What is the typical value of the shift in degrees?
A. 15
B. 12.5
C. 20
D. 22.5
E. 17.5
|
D. 22.5
|
58
|
41c719d0-9f62-40da-abeb-8bd99a86ef8b
|
Among the following assertion about Lagrange points, which one is true?
| 0
|
[
"The distance between the Lagrange points and the Earth varies drastically with the seasons",
"The Sun-Earth system does not have any Lagrange points because of the Moon",
"The Lagrange points orbit the Sun with the same orbital period as the Earth's",
"None of the above"
] |
[
0,
0,
1,
0
] |
Among the following assertion about Lagrange points, which one is true?
A. The distance between the Lagrange points and the Earth varies drastically with the seasons
B. The Sun-Earth system does not have any Lagrange points because of the Moon
C. The Lagrange points orbit the Sun with the same orbital period as the Earth's
D. None of the above
|
C. The Lagrange points orbit the Sun with the same orbital period as the Earth's
|
58
|
41c719d0-9f62-40da-abeb-8bd99a86ef8b
|
Among the following assertion about Lagrange points, which one is true?
| 1
|
[
"None of the above",
"The Lagrange points orbit the Sun with the same orbital period as the Earth's",
"The Sun-Earth system does not have any Lagrange points because of the Moon",
"The distance between the Lagrange points and the Earth varies drastically with the seasons"
] |
[
0,
1,
0,
0
] |
Among the following assertion about Lagrange points, which one is true?
A. None of the above
B. The Lagrange points orbit the Sun with the same orbital period as the Earth's
C. The Sun-Earth system does not have any Lagrange points because of the Moon
D. The distance between the Lagrange points and the Earth varies drastically with the seasons
|
B. The Lagrange points orbit the Sun with the same orbital period as the Earth's
|
58
|
41c719d0-9f62-40da-abeb-8bd99a86ef8b
|
Among the following assertion about Lagrange points, which one is true?
| 2
|
[
"The Lagrange points orbit the Sun with the same orbital period as the Earth's",
"None of the above",
"The Sun-Earth system does not have any Lagrange points because of the Moon",
"The distance between the Lagrange points and the Earth varies drastically with the seasons"
] |
[
1,
0,
0,
0
] |
Among the following assertion about Lagrange points, which one is true?
A. The Lagrange points orbit the Sun with the same orbital period as the Earth's
B. None of the above
C. The Sun-Earth system does not have any Lagrange points because of the Moon
D. The distance between the Lagrange points and the Earth varies drastically with the seasons
|
A. The Lagrange points orbit the Sun with the same orbital period as the Earth's
|
59
|
a2db30ce-3528-4548-a228-c27b103a545c
|
A spacecraft is below and behind the ISS, both are on circular orbits. What will happen to their relative position?
| 0
|
[
"The spacecraft will overtake the ISS",
"The ISS has a larger velocity than the spacecraft, so it will leave the spacecraft behind",
"The spacecraft will get to an higher altitude than the ISS",
"Nothing, they will stay at their initial distance"
] |
[
1,
0,
0,
0
] |
A spacecraft is below and behind the ISS, both are on circular orbits. What will happen to their relative position?
A. The spacecraft will overtake the ISS
B. The ISS has a larger velocity than the spacecraft, so it will leave the spacecraft behind
C. The spacecraft will get to an higher altitude than the ISS
D. Nothing, they will stay at their initial distance
|
A. The spacecraft will overtake the ISS
|
59
|
a2db30ce-3528-4548-a228-c27b103a545c
|
A spacecraft is below and behind the ISS, both are on circular orbits. What will happen to their relative position?
| 1
|
[
"The spacecraft will get to an higher altitude than the ISS",
"The ISS has a larger velocity than the spacecraft, so it will leave the spacecraft behind",
"Nothing, they will stay at their initial distance",
"The spacecraft will overtake the ISS"
] |
[
0,
0,
0,
1
] |
A spacecraft is below and behind the ISS, both are on circular orbits. What will happen to their relative position?
A. The spacecraft will get to an higher altitude than the ISS
B. The ISS has a larger velocity than the spacecraft, so it will leave the spacecraft behind
C. Nothing, they will stay at their initial distance
D. The spacecraft will overtake the ISS
|
D. The spacecraft will overtake the ISS
|
59
|
a2db30ce-3528-4548-a228-c27b103a545c
|
A spacecraft is below and behind the ISS, both are on circular orbits. What will happen to their relative position?
| 2
|
[
"The spacecraft will overtake the ISS",
"The ISS has a larger velocity than the spacecraft, so it will leave the spacecraft behind",
"Nothing, they will stay at their initial distance",
"The spacecraft will get to an higher altitude than the ISS"
] |
[
1,
0,
0,
0
] |
A spacecraft is below and behind the ISS, both are on circular orbits. What will happen to their relative position?
A. The spacecraft will overtake the ISS
B. The ISS has a larger velocity than the spacecraft, so it will leave the spacecraft behind
C. Nothing, they will stay at their initial distance
D. The spacecraft will get to an higher altitude than the ISS
|
A. The spacecraft will overtake the ISS
|
60
|
11665c59-aacf-437d-b83e-16aaa6921ced
|
What is the effect of a posigrade burn on a circular orbit?
| 0
|
[
"The altitude 180° from the burn point is decreased",
"The altitude 90° from the burn point is decreased",
"The altitude 180° from the burn point is increased",
"There is no effect"
] |
[
0,
0,
1,
0
] |
What is the effect of a posigrade burn on a circular orbit?
A. The altitude 180° from the burn point is decreased
B. The altitude 90° from the burn point is decreased
C. The altitude 180° from the burn point is increased
D. There is no effect
|
C. The altitude 180° from the burn point is increased
|
60
|
11665c59-aacf-437d-b83e-16aaa6921ced
|
What is the effect of a posigrade burn on a circular orbit?
| 1
|
[
"There is no effect",
"The altitude 180° from the burn point is decreased",
"The altitude 90° from the burn point is decreased",
"The altitude 180° from the burn point is increased"
] |
[
0,
0,
0,
1
] |
What is the effect of a posigrade burn on a circular orbit?
A. There is no effect
B. The altitude 180° from the burn point is decreased
C. The altitude 90° from the burn point is decreased
D. The altitude 180° from the burn point is increased
|
D. The altitude 180° from the burn point is increased
|
60
|
11665c59-aacf-437d-b83e-16aaa6921ced
|
What is the effect of a posigrade burn on a circular orbit?
| 2
|
[
"The altitude 180° from the burn point is increased",
"There is no effect",
"The altitude 90° from the burn point is decreased",
"The altitude 180° from the burn point is decreased"
] |
[
1,
0,
0,
0
] |
What is the effect of a posigrade burn on a circular orbit?
A. The altitude 180° from the burn point is increased
B. There is no effect
C. The altitude 90° from the burn point is decreased
D. The altitude 180° from the burn point is decreased
|
A. The altitude 180° from the burn point is increased
|
61
|
a28c168f-3f6a-4edb-b0c0-2ae974963858
|
What is the reference point of the rendezvous profile diagram?
| 0
|
[
"The control center",
"The chaser",
"The center of the Earth",
"The target"
] |
[
0,
0,
0,
1
] |
What is the reference point of the rendezvous profile diagram?
A. The control center
B. The chaser
C. The center of the Earth
D. The target
|
D. The target
|
61
|
a28c168f-3f6a-4edb-b0c0-2ae974963858
|
What is the reference point of the rendezvous profile diagram?
| 1
|
[
"The target",
"The center of the Earth",
"The chaser",
"The control center"
] |
[
1,
0,
0,
0
] |
What is the reference point of the rendezvous profile diagram?
A. The target
B. The center of the Earth
C. The chaser
D. The control center
|
A. The target
|
61
|
a28c168f-3f6a-4edb-b0c0-2ae974963858
|
What is the reference point of the rendezvous profile diagram?
| 2
|
[
"The control center",
"The center of the Earth",
"The chaser",
"The target"
] |
[
0,
0,
0,
1
] |
What is the reference point of the rendezvous profile diagram?
A. The control center
B. The center of the Earth
C. The chaser
D. The target
|
D. The target
|
62
|
e8b2cae4-92f6-48e6-9436-c5f33a5ac832
|
What is the shape of a circular orbit, for the chaser, in a rendezvous profile diagram? (assuming the target is higher than the chaser).
| 0
|
[
"A point",
"A cycloid",
"A periodic wavy and pointy curve",
"A line",
"A sinusoidal"
] |
[
0,
0,
0,
1,
0
] |
What is the shape of a circular orbit, for the chaser, in a rendezvous profile diagram? (assuming the target is higher than the chaser).
A. A point
B. A cycloid
C. A periodic wavy and pointy curve
D. A line
E. A sinusoidal
|
D. A line
|
62
|
e8b2cae4-92f6-48e6-9436-c5f33a5ac832
|
What is the shape of a circular orbit, for the chaser, in a rendezvous profile diagram? (assuming the target is higher than the chaser).
| 1
|
[
"A sinusoidal",
"A cycloid",
"A periodic wavy and pointy curve",
"A point",
"A line"
] |
[
0,
0,
0,
0,
1
] |
What is the shape of a circular orbit, for the chaser, in a rendezvous profile diagram? (assuming the target is higher than the chaser).
A. A sinusoidal
B. A cycloid
C. A periodic wavy and pointy curve
D. A point
E. A line
|
E. A line
|
62
|
e8b2cae4-92f6-48e6-9436-c5f33a5ac832
|
What is the shape of a circular orbit, for the chaser, in a rendezvous profile diagram? (assuming the target is higher than the chaser).
| 2
|
[
"A line",
"A periodic wavy and pointy curve",
"A cycloid",
"A sinusoidal",
"A point"
] |
[
1,
0,
0,
0,
0
] |
What is the shape of a circular orbit, for the chaser, in a rendezvous profile diagram? (assuming the target is higher than the chaser).
A. A line
B. A periodic wavy and pointy curve
C. A cycloid
D. A sinusoidal
E. A point
|
A. A line
|
63
|
61e3c07e-fd5e-4429-aeb1-66afe0919eda
|
A spacecraft on a circular orbit at 400 km does a retrograde burn of 1 m/s. What will be the change in the altitude (in km) of the perigee?
| 0
|
[
"1.5",
"2.5",
"4.5",
"3.5"
] |
[
0,
0,
0,
1
] |
A spacecraft on a circular orbit at 400 km does a retrograde burn of 1 m/s. What will be the change in the altitude (in km) of the perigee?
A. 1.5
B. 2.5
C. 4.5
D. 3.5
|
D. 3.5
|
63
|
61e3c07e-fd5e-4429-aeb1-66afe0919eda
|
A spacecraft on a circular orbit at 400 km does a retrograde burn of 1 m/s. What will be the change in the altitude (in km) of the perigee?
| 1
|
[
"3.5",
"2.5",
"1.5",
"4.5"
] |
[
1,
0,
0,
0
] |
A spacecraft on a circular orbit at 400 km does a retrograde burn of 1 m/s. What will be the change in the altitude (in km) of the perigee?
A. 3.5
B. 2.5
C. 1.5
D. 4.5
|
A. 3.5
|
63
|
61e3c07e-fd5e-4429-aeb1-66afe0919eda
|
A spacecraft on a circular orbit at 400 km does a retrograde burn of 1 m/s. What will be the change in the altitude (in km) of the perigee?
| 2
|
[
"2.5",
"3.5",
"4.5",
"1.5"
] |
[
0,
1,
0,
0
] |
A spacecraft on a circular orbit at 400 km does a retrograde burn of 1 m/s. What will be the change in the altitude (in km) of the perigee?
A. 2.5
B. 3.5
C. 4.5
D. 1.5
|
B. 3.5
|
64
|
9fc96902-8398-4630-b53b-6d3049c8254e
|
A chaser is on a circular orbit at the same altitude as the target and few kilometers behind. Where will the chaser be one orbit after a posigrade burn ?
| 0
|
[
"The chaser will be much further ahead",
"The chaser will be behind the target, further away than it was initally",
"The chaser will be higher than the target",
"The chaser will be lower than the target"
] |
[
0,
1,
0,
0
] |
A chaser is on a circular orbit at the same altitude as the target and few kilometers behind. Where will the chaser be one orbit after a posigrade burn ?
A. The chaser will be much further ahead
B. The chaser will be behind the target, further away than it was initally
C. The chaser will be higher than the target
D. The chaser will be lower than the target
|
B. The chaser will be behind the target, further away than it was initally
|
64
|
9fc96902-8398-4630-b53b-6d3049c8254e
|
A chaser is on a circular orbit at the same altitude as the target and few kilometers behind. Where will the chaser be one orbit after a posigrade burn ?
| 1
|
[
"The chaser will be higher than the target",
"The chaser will be lower than the target",
"The chaser will be behind the target, further away than it was initally",
"The chaser will be much further ahead"
] |
[
0,
0,
1,
0
] |
A chaser is on a circular orbit at the same altitude as the target and few kilometers behind. Where will the chaser be one orbit after a posigrade burn ?
A. The chaser will be higher than the target
B. The chaser will be lower than the target
C. The chaser will be behind the target, further away than it was initally
D. The chaser will be much further ahead
|
C. The chaser will be behind the target, further away than it was initally
|
64
|
9fc96902-8398-4630-b53b-6d3049c8254e
|
A chaser is on a circular orbit at the same altitude as the target and few kilometers behind. Where will the chaser be one orbit after a posigrade burn ?
| 2
|
[
"The chaser will be much further ahead",
"The chaser will be higher than the target",
"The chaser will be lower than the target",
"The chaser will be behind the target, further away than it was initally"
] |
[
0,
0,
0,
1
] |
A chaser is on a circular orbit at the same altitude as the target and few kilometers behind. Where will the chaser be one orbit after a posigrade burn ?
A. The chaser will be much further ahead
B. The chaser will be higher than the target
C. The chaser will be lower than the target
D. The chaser will be behind the target, further away than it was initally
|
D. The chaser will be behind the target, further away than it was initally
|
65
|
3fedeb91-5ab5-45de-be70-a2ce8ad59e10
|
What is the definition of the Astronomical Unit (AU)?
| 0
|
[
"It is the average distance betwteen the Moon and the Earth",
"It is the average radius of the Sun",
"It is the average radius of the solar system",
"It is the average distance between the Earth and the Sun"
] |
[
0,
0,
0,
1
] |
What is the definition of the Astronomical Unit (AU)?
A. It is the average distance betwteen the Moon and the Earth
B. It is the average radius of the Sun
C. It is the average radius of the solar system
D. It is the average distance between the Earth and the Sun
|
D. It is the average distance between the Earth and the Sun
|
65
|
3fedeb91-5ab5-45de-be70-a2ce8ad59e10
|
What is the definition of the Astronomical Unit (AU)?
| 1
|
[
"It is the average distance between the Earth and the Sun",
"It is the average radius of the solar system",
"It is the average radius of the Sun",
"It is the average distance betwteen the Moon and the Earth"
] |
[
1,
0,
0,
0
] |
What is the definition of the Astronomical Unit (AU)?
A. It is the average distance between the Earth and the Sun
B. It is the average radius of the solar system
C. It is the average radius of the Sun
D. It is the average distance betwteen the Moon and the Earth
|
A. It is the average distance between the Earth and the Sun
|
65
|
3fedeb91-5ab5-45de-be70-a2ce8ad59e10
|
What is the definition of the Astronomical Unit (AU)?
| 2
|
[
"It is the average distance between the Earth and the Sun",
"It is the average radius of the solar system",
"It is the average distance betwteen the Moon and the Earth",
"It is the average radius of the Sun"
] |
[
1,
0,
0,
0
] |
What is the definition of the Astronomical Unit (AU)?
A. It is the average distance between the Earth and the Sun
B. It is the average radius of the solar system
C. It is the average distance betwteen the Moon and the Earth
D. It is the average radius of the Sun
|
A. It is the average distance between the Earth and the Sun
|
66
|
6a0ff5bb-46cb-4b10-a12b-4573589bb59f
|
What is the sphere of influence?
| 0
|
[
"A sphere around each planet inside which the motion of a spacecraft is considered to be two-body Keplerian",
"A region in space that can be controlled by a spacecraft",
"A sphere around each planet inside which the motion of a spacecraft must be considered a three-body Keplerian problem",
"The region around the Sun in which only planets have a gravitational influence"
] |
[
1,
0,
0,
0
] |
What is the sphere of influence?
A. A sphere around each planet inside which the motion of a spacecraft is considered to be two-body Keplerian
B. A region in space that can be controlled by a spacecraft
C. A sphere around each planet inside which the motion of a spacecraft must be considered a three-body Keplerian problem
D. The region around the Sun in which only planets have a gravitational influence
|
A. A sphere around each planet inside which the motion of a spacecraft is considered to be two-body Keplerian
|
66
|
6a0ff5bb-46cb-4b10-a12b-4573589bb59f
|
What is the sphere of influence?
| 1
|
[
"A region in space that can be controlled by a spacecraft",
"A sphere around each planet inside which the motion of a spacecraft must be considered a three-body Keplerian problem",
"The region around the Sun in which only planets have a gravitational influence",
"A sphere around each planet inside which the motion of a spacecraft is considered to be two-body Keplerian"
] |
[
0,
0,
0,
1
] |
What is the sphere of influence?
A. A region in space that can be controlled by a spacecraft
B. A sphere around each planet inside which the motion of a spacecraft must be considered a three-body Keplerian problem
C. The region around the Sun in which only planets have a gravitational influence
D. A sphere around each planet inside which the motion of a spacecraft is considered to be two-body Keplerian
|
D. A sphere around each planet inside which the motion of a spacecraft is considered to be two-body Keplerian
|
66
|
6a0ff5bb-46cb-4b10-a12b-4573589bb59f
|
What is the sphere of influence?
| 2
|
[
"The region around the Sun in which only planets have a gravitational influence",
"A region in space that can be controlled by a spacecraft",
"A sphere around each planet inside which the motion of a spacecraft must be considered a three-body Keplerian problem",
"A sphere around each planet inside which the motion of a spacecraft is considered to be two-body Keplerian"
] |
[
0,
0,
0,
1
] |
What is the sphere of influence?
A. The region around the Sun in which only planets have a gravitational influence
B. A region in space that can be controlled by a spacecraft
C. A sphere around each planet inside which the motion of a spacecraft must be considered a three-body Keplerian problem
D. A sphere around each planet inside which the motion of a spacecraft is considered to be two-body Keplerian
|
D. A sphere around each planet inside which the motion of a spacecraft is considered to be two-body Keplerian
|
67
|
f274dd2f-9811-4424-abca-f3c6e4c61bd8
|
What is the hyperbolic excess velocity?
| 0
|
[
"The velocity needed to reach the sphere of influence",
"The velocity at which we cross the sphere of influence",
"The velocity needed to reach the arriving planet",
"The velocity required to get into a LEO orbit from the surface of the Earth"
] |
[
0,
1,
0,
0
] |
What is the hyperbolic excess velocity?
A. The velocity needed to reach the sphere of influence
B. The velocity at which we cross the sphere of influence
C. The velocity needed to reach the arriving planet
D. The velocity required to get into a LEO orbit from the surface of the Earth
|
B. The velocity at which we cross the sphere of influence
|
67
|
f274dd2f-9811-4424-abca-f3c6e4c61bd8
|
What is the hyperbolic excess velocity?
| 1
|
[
"The velocity needed to reach the arriving planet",
"The velocity needed to reach the sphere of influence",
"The velocity at which we cross the sphere of influence",
"The velocity required to get into a LEO orbit from the surface of the Earth"
] |
[
0,
0,
1,
0
] |
What is the hyperbolic excess velocity?
A. The velocity needed to reach the arriving planet
B. The velocity needed to reach the sphere of influence
C. The velocity at which we cross the sphere of influence
D. The velocity required to get into a LEO orbit from the surface of the Earth
|
C. The velocity at which we cross the sphere of influence
|
67
|
f274dd2f-9811-4424-abca-f3c6e4c61bd8
|
What is the hyperbolic excess velocity?
| 2
|
[
"The velocity required to get into a LEO orbit from the surface of the Earth",
"The velocity at which we cross the sphere of influence",
"The velocity needed to reach the arriving planet",
"The velocity needed to reach the sphere of influence"
] |
[
0,
1,
0,
0
] |
What is the hyperbolic excess velocity?
A. The velocity required to get into a LEO orbit from the surface of the Earth
B. The velocity at which we cross the sphere of influence
C. The velocity needed to reach the arriving planet
D. The velocity needed to reach the sphere of influence
|
B. The velocity at which we cross the sphere of influence
|
68
|
42d75d3d-7aed-4cc3-a784-814bfc3e0fd6
|
A interplanetary probe is in the sphere of influence of the Earth, in transit towards an inner planet. What is its energy with respect to the Earth?
| 0
|
[
"E <= 0",
"E < 0",
"E > 0",
"E = 0"
] |
[
0,
0,
1,
0
] |
A interplanetary probe is in the sphere of influence of the Earth, in transit towards an inner planet. What is its energy with respect to the Earth?
A. E <= 0
B. E < 0
C. E > 0
D. E = 0
|
C. E > 0
|
68
|
42d75d3d-7aed-4cc3-a784-814bfc3e0fd6
|
A interplanetary probe is in the sphere of influence of the Earth, in transit towards an inner planet. What is its energy with respect to the Earth?
| 1
|
[
"E > 0",
"E = 0",
"E <= 0",
"E < 0"
] |
[
1,
0,
0,
0
] |
A interplanetary probe is in the sphere of influence of the Earth, in transit towards an inner planet. What is its energy with respect to the Earth?
A. E > 0
B. E = 0
C. E <= 0
D. E < 0
|
A. E > 0
|
Subsets and Splits
No community queries yet
The top public SQL queries from the community will appear here once available.