The orbital speeds of satellite A and satellite B can be calculated using the formula V = √(GM/R), where G is the gravitational constant, M is the mass of the Earth, and R is the radius of the satellite's orbit. Plugging in the values, the orbital speed for satellite A is 7.67 km/s and for satellite B is 7.55 km/s.
The orbital speed of a satellite can be determined using the formula:
V = √(GM/R)
Where V is the orbital speed, G is the gravitational constant (6.67 x 10^-11 N m^2/kg^2), M is the mass of the Earth (5.97 x 10^24 kg), and R is the radius of the satellite's orbit. For satellite A, its orbit height is 535 km above the Earth's surface, so we need to add this height to the radius of the Earth (6,370 km) to get the total radius. Plugging in the values, we get:
Va = √((6.67 x 10⁻¹¹ N m²/kg²) x (5.97 x 10²⁴ kg) / (535 km + 6,370 km)) = 7.67 km/s
Similarly, for satellite B with a height of 892 km above the Earth's surface, we have:
Vb = √((6.67 x 10⁻¹¹ N m²/kg²) x (5.97 x 10²⁴ kg) / (892 km + 6,370 km)) = 7.55 km/s