Determine the perigee altitude of the elliptical orbit so that Satellites A and B occupy the same radial position when Satellite A firstly arrives the apogee point (in other words, Satellites A and B perform a rendezvous maneuver at apogee of satellite B).
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- A satellite in low-earth orbit experiences drag from the neutral atmosphere. Neglecting any space weather storms or events, provide two reasons why the drag force will naturally exhibit positive feedback (i.e. exponential growth over time).A geosynchronous orbit is one in which the satellite stays in the same relative position above the earth, as the earth rotates. To do so, the satellite needs to have an orbital period of 1 day. Given that the moon has an orbital period of 27.3 days and a semi-major axis of 384,000 km, determine the radius of a geosynchronous orbit using Kepler's 3rd law. Enter your answer in km.Calculate the orbital inclination required to place an earth-orbiting satellite in a 1000.0 km x 1500.0 km altitude, sun-synchronous orbit.
- The orbit of a 1.5 x 1010 kg comet around the Sun is elliptical, with an aphelion distance of 11.0 AU and perihelion distance of 0.890 AU. (Note: 1 AU = one astronomical unit = the average distance from the Sun to the Earth = 1.496 x 101" m.) (a) What is its orbital eccentricity? (b) What is its period? (Enter your answer in yr.) yr (c) At aphelion what is the potential energy (in J) of the comet-Sun system?A satellite describes an elliptic orbit of minimum altitude 606 km above the surface of the earth. The semimajor and semiminor axes are 17 440 km and 13 950 km, respectively. Knowing that the speed of the satellite at point C is 4.78 km/s, determine (a) the speed at point A, the perigee, (b) the speed at point B, the apogee.(a) Suppose that your measured weight at the equator is one-half your measured weight at the pole on a planet whose mass and diameter are equal to those of Earth. What is the rotational period of the planet? (b) Would you need to take the shape of this planet into account?
- A satellite is in a circular orbit at an altitude of 250km above the earth's surface. The onboard rocket provides a Av = 200m/s, calculate the new velocity at perigee (v2) in the transfer orbit, Specific angular momentum of the transfer orbit (h₂), and eccentricity of the transfer orbit (e₂). Hohmann transfer ellipse B Apoapsis AUB Circle Circle AVA A PeriapsisThe orbital speed of a satellite will depend on the strength of gravitational field at the orbital radius. Consider the following situations. Which identical satellite will be travelling faster in each case? Why? a- Satellite A orbits the Earth at twice the orbital radius of Satellite B. b- Satellite A orbits the Sun at the same orbital radius that Satellite B orbits the Earth.(