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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.
- 559 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.
- 375 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.
- 1K 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.
- 972 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.
- 1K 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.
- 1K 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?
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.
- 1K views
- 1 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.
- 712 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.
- 661 views
- 2 answers
- 0 votes

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

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′.

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.

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

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?

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.

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?

Poll Normalization of the specific impulse of the rocket.

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

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