Mass ratio required for altitude change

The previous section provides the methodology to determine the magnitude of the incremental velocity to achieve a given orbital altitude change, in a fixed orbital inclination. The propulsion systems described in Table 5.3 provide the specific impulse (7sp) for each of four systems. In space there is no atmospheric drag, so the ideal weight ratio equation (5.8) applies:

Orbital altitude (nautical miles)

Figure 5.7. Velocity requirement to change orbital altitude can approach one-half of the orbital speed.

Orbital altitude (nautical miles)

Figure 5.7. Velocity requirement to change orbital altitude can approach one-half of the orbital speed.

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