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The propellant in a single stage sounding rocket occupies 60 % of its initial mass. If all of it is expanded instantaneously at an equivalent exhaust velocity of 3000 m/s, what would be the altitude attained by the payload when launched vertically?
The propellant in a single stage sounding rocket occupies 60 % of its initial mass. If all of it is …
GATE

Kisan Kumar Asked on 8th October 2019 in Space dynamics.
- 862 views
- 1 answers
- 0 votes
An elliptic orbit has its perigee at 400 km above the earth’s surface and apogee at 3400 km above the earth’s surface. For this orbit, what is the eccentricity and semi-major axis respectively.
An elliptic orbit has its perigee at 400 km above the earth’s surface and apogee at 3400 km above the …
GATE

Kisan Kumar Asked on 14th October 2019 in Space dynamics.
- 876 views
- 1 answers
- 0 votes
Two satellites of masses m and 2m are on the same circular orbit around earth. If the velocity of the lighter satellite is v0, what is the velocity of the heavier satellite?
Two satellites of masses \(m\) and \(2\;m\) are on the same circular orbit around earth. If the velocity of the …
Kisan Kumar Asked on 19th October 2019 in Space dynamics.
- 942 views
- 1 answers
- 0 votes
Calculate the orbital and escape velocity from earth, mass of earth is \(5.9722 \times {10^{24}}\,kg\) and radius is \(6.378 \times {10^6}\,m\).
Calculate the orbital and escape velocity from earth, mass of earth is \(5.9722 \times {10^{24}}\,kg\) and radius is \(6.378 \times …
earth

space

Kumar59 Asked on 1st March 2021 in Space dynamics.
- 745 views
- 1 answers
- 0 votes
A communication satellite orbiting around earth has an eccentricity of \(0.0014\). Find the time period of the satellite, altitude at apogee and velocity at perigee, if the satellite has an altitude of \(400\,km\) at perigee from the surface of the earth.
A communication satellite orbiting around earth has an eccentricity of \(0.0014\). Find the time period of the satellite, altitude at …
earth

satellite

space

Worldtech Asked on 1st March 2021 in Space dynamics.
- 792 views
- 1 answers
- 0 votes
The satellite orbit is characterized by e = 0.508 and a/R = 3.34, and its launch point was r0/R = 2.0, Θ = 62°23′.
The satellite orbit is characterized by e = 0.508 and a/R = 3.34, and its launch point was r0/R = …
space

transfer orbit

Worldtech Asked on 8th November 2023 in Space dynamics.
- 157 views
- 1 answers
- 0 votes
Determine the differential equation for small oscillations about a circular orbit when the attractive force is -K/r².
Determine the differential equation for small oscillations about a circular orbit when the attractive force is -K/r².
space

transfer orbit

Worldtech Asked on 8th November 2023 in Space dynamics.
- 269 views
- 1 answers
- 0 votes
Poll Where will be the apogee and perigee for the Hohmann ellipse for earth-mars transfer orbit ?
The Hohmann ellipse used as Earth -Mars transfer orbit has
GATE

Kisan Kumar Asked on 3rd October 2019 in Space dynamics.
- 536 views
- 2 answers
- 0 votes
Poll Normalization of the specific impulse of the rocket.
A rocket is to be launched from the bottom of a very deep crater on mars for earth return.The specific …
transfer orbit

Kisan Kumar Asked on 3rd October 2019 in Space dynamics.
- 595 views
- 1 answers
- 0 votes

The propellant in a single stage sounding rocket occupies 60 % of its initial mass. If all of it is expanded instantaneously at an equivalent exhaust velocity of 3000 m/s, what would be the altitude attained by the payload when launched vertically?

An elliptic orbit has its perigee at 400 km above the earth’s surface and apogee at 3400 km above the earth’s surface. For this orbit, what is the eccentricity and semi-major axis respectively.

Two satellites of masses m and 2m are on the same circular orbit around earth. If the velocity of the lighter satellite is v0, what is the velocity of the heavier satellite?

Calculate the orbital and escape velocity from earth, mass of earth is \(5.9722 \times {10^{24}}\,kg\) and radius is \(6.378 \times {10^6}\,m\).

A communication satellite orbiting around earth has an eccentricity of \(0.0014\). Find the time period of the satellite, altitude at apogee and velocity at perigee, if the satellite has an altitude of \(400\,km\) at perigee from the surface of the earth.

The satellite orbit is characterized by e = 0.508 and a/R = 3.34, and its launch point was r0/R = 2.0, Θ = 62°23′.

Determine the differential equation for small oscillations about a circular orbit when the attractive force is -K/r².

Poll Where will be the apogee and perigee for the Hohmann ellipse for earth-mars transfer orbit ?

Poll Normalization of the specific impulse of the rocket.

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