Calculate the e, a (km), T (hr), ε (km2/s2), va, and vp for a satellite orbiting Earh, with a perigee radius of 7000.0 km and an apogee radius of 70000. km. Calculate the two values of the true anomaly (in degrees) at which the altitude is 35,500. km. (partial answer: Vp = 10.175 km/s)
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- A satellite in orbit around the earth is at an altitude of 107 percent of the earth's radius. Rounding off our old friend "g" to ten meters per second squared, what is the acceleration due to earth's gravity at the satellite? Your answer should be in meters per second squared, but do not put the unit, just the number.Calculate the escape velocity to an orbit of 457 km height from a planet with the radius of 2000 km and the density of 3400 kg⋅m-³. Give your answer in Sl units.Derive the of the time period of rerolution T ot the satellite around the plant. State clearly the assumptions Jou have taken calculate this expression.wether this formela is applícable for jupiter? Give a expression to reason for r your aunswer.
- We would like to be able to make meaningful interpretations of variations in the acceleration due to gravity, g, as small as 0.1 mgal. How accurate must our knowledge of the latitude of our gravity stations be? (A “gravity station" is just a location at which you make a gravity measurement.) You can assume your latitude is 45°.(a) Calculate the orbital inclination required to place a Venus-orbiting spacecraft in a 400 km-by-900 km sun-synchronous orbit. (b) Determine the periapsis and apoapsis for a Mars-orbiting spacecraft whose orbit satisfies all the following conditions: it is sun-synchronous, its argument of perigee is constant, and its period is 7 h.answer typed
- What are the speed and period of a satellite in an 85.00 km altitude lunar orbit? (what is Rmoon?) (mu_moon = 4903 km^3/s^2; v = 1.640 km/s)solve it clearly and correctly. i will rateEx/13: The mean radius of earth is 6400 km. The acceleration due to gravity at its surface is 9.8 m/s². Estimate the mass of earth. "" 11 › (G = 6.67 × 10-¹¹ Nm²/kg²)
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